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1
Bester, Paul, F. C. Aggenbacht, and Imdaadulah Adam. "Design and additive manufacturing of Ti-6Al-4V test-piece for use in aeronautical turboshaft engine heat exchanger." MATEC Web of Conferences 406 (2024): 01002. https://doi.org/10.1051/matecconf/202440601002.
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While post-compression intercooling is commonly used to modify the performance characteristics of traditional turbocharged internal combustion engine layouts, there may be benefits to installing similar modifications in aeronautical turboshaft engines. The rise of Additive Manufacturing (AM) techniques offers the potential for lighter and more compact heat exchanger designs to be manufactured. To this end, a heat exchanger was designed to cool the charge air supplied by the compressor stages of a turboshaft engine. Using dimensional analysis techniques, a model was manufactured to assess the suitability of a heat exchanger produced using AM for aeronautical turboshaft engines.
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Vladov, Serhii, Ruslan Yakovliev, Maryna Bulakh, and Victoria Vysotska. "Neural Network Approximation of Helicopter Turboshaft Engine Parameters for Improved Efficiency." Energies 17, no. 9 (2024): 2233. http://dx.doi.org/10.3390/en17092233.
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The work is devoted to the development of a method for neural network approximation of helicopter turboshaft engine parameters, which is the basis for researching engine energy characteristics to improve efficiency, reliability, and flight safety. It is proposed to use a three-layer direct propagation neural network with linear neurons in the output layer for training in which the scale conjugate gradient algorithm is modified by introducing a moment coefficient into the analytical expression. This modification helps in calculating new model parameters to avoid falling into a local minimum. The dependence of the energy released during helicopter turboshaft engine compressor rotation on the gas-generator rotor r.p.m. was obtained. This enables the determination of the optimal gas-generator rotor r.p.m. region for a specific type of helicopter turboshaft engine. The optimal ratio of energy consumption and compressor operating efficiency is achieved, thereby ensuring helicopter turboshaft engines’ optimal performance and reliability. Experimental data support the high efficiency of using a three-layer feed-forward neural network with linear neurons in the output layer, trained using a modified scale conjugate gradient algorithm, for approximating parameters of helicopter turboshaft engines compared to the analogues. Specifically, this method better predicts the relations between the energy release during compressor rotation and gas-generator rotor r.p.m. The efficiency coefficient of the proposed method was 0.994, which exceeded that of the closest analogue (0.914) by 1.09 times.
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Ji, Zifei, Ruize Duan, Renshuai Zhang, Huiqiang Zhang, and Bing Wang. "Comprehensive Performance Analysis for the Rotating Detonation-Based Turboshaft Engine." International Journal of Aerospace Engineering 2020 (July 2, 2020): 1–11. http://dx.doi.org/10.1155/2020/9587813.
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The potential advantages of rotating detonation combustion are gradually approved, and it is becoming a stable and controllable energy conversion way adopted to the propulsion devices or ground-engines. This study focuses on the rotating detonation-based turboshaft engine, and the architecture is presented for this form of engine with compatibility between the turbomachinery and rotating detonation combustor being realized. The parametric performance simulation model for the rotating detonation-based turboshaft engine are developed. Further, the potential performance benefits as well as their generation mechanism are revealed, based on the comprehensive performance analysis of the rotating detonation-based turboshaft engine. Comparisons between the rotating detonation turboshaft engine and the conventional one reveal that the former holds significant improvements in specific power, thermal efficiency, and specific fuel consumption at lower compressor pressure ratios, and these improvements decrease with the increase of compressor pressure ratio and increase as turbine inlet temperature increases. The critical compressor pressure ratio corresponding to the disappearance of specific power improvement is higher than that corresponding to the disappearance of thermal efficiency and specific fuel consumption. These critical compressor pressure ratios are positively correlated with flight altitude and negatively correlated with flight velocity. The conductive research conclusion is guidable for the design and engineering application of rotating detonation-based engines.
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Kozak, Dariusz, and Paweł Mazuro. "Review of Small Gas Turbine Engines and Their Adaptation for Automotive Waste Heat Recovery Systems." International Journal of Turbomachinery, Propulsion and Power 5, no. 2 (2020): 8. http://dx.doi.org/10.3390/ijtpp5020008.
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Current commercial and heavy-duty powertrains are geared towards emissions reduction. Energy recovery from exhaust gases has great potential, considering the mechanical work to be transferred back to the engine. For this purpose, an additional turbine can be implemented behind a turbocharger; this solution is called turbocompounding (TC). This paper considers the adaptation of turbine wheels and gearboxes of small turboshaft and turbojet engines into a two-stage TC system for a six-cylinder opposed-piston engine that is currently under development. The initial conditions are presented in the first section, while a comparison between small turboshaft and turbojet engines and their components for TC is presented in the second section. Based on the comparative study, a total number of 7 turbojet and 8 turboshaft engines were considered for the TC unit.
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Hocko, Marián, and Samer Al-Rabeei. "Impact of dust erosion on the reduction of axial compressor efficiency of a turboshaft engine and on the stability of its operation." MATEC Web of Conferences 367 (2022): 00008. http://dx.doi.org/10.1051/matecconf/202236700008.
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This paper aimed to solve the impact of operational abrasive wear on the rotor blades of the axial compressor of the turboshaft engine on the decrease in its total compression efficiency ηCt and its transition into unstable work mode (surge). This process is analyzed based on the obtained data by operating TV3-117 helicopter turboshaft engines in high dust atmosphere conditions. Abrasive wear of the rotor blades of axial compressors causes mechanical damage to the blades, reducing their strength, changing their geometry, and aerodynamic properties, reducing the life of the whole compressor and thus the entire engine. Destruction of the compressor of a turboshaft engine may occur suddenly as a result of unstable compressor operation caused by damaged axial compressor blades due to their damage by the abrasive effect of dust.
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Kazhaev, V. P., D. Y. Kiselev, and Y. V. Kiselev. "DIAGNOSTIC MODEL OF HELICOPTER TURBOSHAFT ENGINE." Izvestiya of Samara Scientific Center of the Russian Academy of Sciences 25, no. 1 (2023): 99–106. http://dx.doi.org/10.37313/1990-5378-2023-25-1-99-106.
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The article presents a qualitative assessment of the impact on the engine components characteristics of the malfunction occurrence in the flow part of the aviation gas turbine engines, which lead to changes in its geometry. Using the example of a compressor, it is shown that when defects appear in it, two of its characteristics are deformed: efficiency and pressure characteristics (which is confirmed by a significant number of studies). It is concluded that in order to reliably diagnose aviation gas turbine engines by thermogasodynamic parameters, the mathematical model must take into account the change in two characteristics for each engine component of the flow part (and not only the change in the characteristics of the efficiency of the nodes). A linear mathematical model of a helicopter turboshaft turbine engine is presented and the results of calculating the influence coefficient for a given control law are presented. The peculiarity of the presented model is that the state of each engine component is characterized by two state parameters: for compressors, this is the head characteristic and the efficiency characteristic, for turbines, performance characteristics and efficiency.
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Czarnecki, Michal, John Olsen, and Ruixian Ma. "PZL-10 Turboshaft Engine–System Design Review." Journal of KONES 26, no. 1 (2019): 23–29. http://dx.doi.org/10.2478/kones-2019-0003.
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Abstract The PZL – 10-turboshaft gas turbine engine is straight derivative of GTD-10 turboshaft design by OKMB (Omsk Engine Design Bureau). Prototype engine first run take place in 1968. Selected engine is interested platform to modify due gas generator layout 6A+R-2, which is modern. For example axial compressor design from successful Klimov designs TB2-117 (10A-2-2) or TB3-117 (12A-2-2) become obsolete in favour to TB7-117B (5A+R-2-2). In comparison to competitive engines: Klimov TB3-117 (1974 – Mi-14/17/24), General Electric T-700 (1970 – UH60/AH64), Turbomeca Makila (1976 – II225M) the PZL-10 engine design is limited by asymmetric power turbine design layout. This layout is common to early turboshaft design such as Soloview D-25V (Mil-6 power plant). Presented article review base engine configuration (6A+R+2+1). Proposed modifications are divided into different variants in terms of design complexity. Simplest variant is limited to increase turbine inlet temperature (TIT) by safe margin. Advanced configuration replace engine layout to 5A+R+2-2 and increase engine compressor pressure ratio to 9.4:1. Upgraded configuration after modification offers increase of generated power by 28% and SFC reduction by 9% – validated by gas turbine performance model. Design proposal corresponds to a major trend of increasing available power for helicopter engines – Mi-8T to Mi-8MT – 46%, H225M – Makila 1A to 1A2 — 9%), Makila 1A2 to Makila 2-25%.
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Dobromirescu, Cristian, and Valeriu Vilag. "Energy conversion and efficiency in turboshaft engines." E3S Web of Conferences 85 (2019): 01001. http://dx.doi.org/10.1051/e3sconf/20198501001.
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This paper discusses the methods of energy conversion in a turboshaft engine. Those methods cover the thermodynamic cycle and the engine performances, the possible energy sources and their impact on environment as well as the optimal solutions for maximum efficiency in regards to turbine design and application. The paper also analyzes the constructive solutions that limit the efficiency and performances of turboshaft engines. For the purpose of this paper a gas-turbine design task is performed on an existing engine to appreciate the methods presented. In the final part of this paper it is concluded that in order to design an engine it is necessary to balance the thermodynamic aspects, for maximum efficiency, and the constructive elements, so that the engine can be manufactured.
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Welch, G. E., S. M. Jones, and D. E. Paxson. "Wave-Rotor-Enhanced Gas Turbine Engines." Journal of Engineering for Gas Turbines and Power 119, no. 2 (1997): 469–77. http://dx.doi.org/10.1115/1.2815598.
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The benefits of wave rotor topping in small (300- to 500-kW [400- to 700-hp] class) and intermediate (2000- to 3000-kw [3000- to 4000-hp] class) turboshaft engines, and large (350- to 450-kN [80,000- to 100,000-lbf] class) high-bypass-ratio turbofan engines are evaluated. Wave rotor performance levels are calculated using a one-dimensional design/analysis code. Baseline and wave-rotor-enhanced engine performance levels are obtained from a cycle deck in which the wave rotor is represented as a burner with pressure gain. Wave rotor topping is shown to enhance the specific fuel consumption and specific power of small- and intermediate-sized turboshaft engines significantly. The specific fuel consumption of the wave-rotor-enhanced large turbofan engine can be reduced while it operates at a significantly reduced turbine inlet temperature. The wave-rotor-enhanced engine is shown to behave off-design like a conventional engine. Discussion concerning the impact of the wave rotor/gas turbine engine integration identifies technical challenges.
10
Remchukov, S. S., V. S. Lomazov, R. N. Lebedinskiy, I. V. Demidyuk, and I. S. Ptitsyn. "Special Aspects of Designing High Temperature Plate Heat Exchangers for Small Gas Turbine Engines." Herald of the Bauman Moscow State Technical University. Series Mechanical Engineering, no. 3 (142) (September 2022): 57–70. http://dx.doi.org/10.18698/0236-3941-2022-3-57-70.
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An increase in the fuel efficiency of small-sized gas turbine engines can be achieved by regenerating the heat of the turbine exhaust gases. A rational layout solution in this case is a turboshaft scheme, where the effective power is generated on the shaft of a free turbine, and the turbine exhaust gases are released into the environment without doing useful work. When creating a turboshaft engine with heat recovery, the concept of developing engine family on the base of unified gas-generator was considered. The concept involves the development of a modular system, where the addition or exclusion of individual large units allows changing the type of engine at minimal cost. The article presents the layout solution of a small-sized turboshaft gas turbine engine with heat recovery, developed on the basis of a unified gas-generator and using a gearbox to transfer effective power to a propeller or a rotor. A plate heat exchanger module with a corrugated heat exchange surface for a small-sized turboshaft gas turbine engine has been designed. The heat exchange matrix was developed using a complex techniques of computer-aided design, calculation and manufacture of plate heat exchangers. Some design features of high-temperature plate heat exchangers are identified, the most important of which is the non-uniformity of temperature fields in the heat exchange matrix. Taking into account the non-uniformity of temperature fields, the heat exchanger module is a collapsible structure allowing the replacement of the heat exchange matrix and providing compensation for thermal expansion of the heat exchanger elements. The designed plate heat exchanger module for a small turboshaft gas turbine engine will be manufactured and tested on the bench
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Yepifanov, Sergiy, та Oleksii Bondarenko. "Формування математичної моделі турбовального двигуна". Aerospace Technic and Technology, № 4sup1 (24 серпня 2023): 85–94. http://dx.doi.org/10.32620/aktt.2023.4sup1.12.
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The subject of the study is the process of forming a mathematical model (MM) of a turboshaft gas turbine engine and a twin-engine helicopter power plant, which provides the determination of parameters of the working process in steady and transient operating modes for use in the estimation of dynamic characteristics, in the analysis and synthesis of engine and helicopter automatic control systems. The goal is to substantiate the structure and methodology of MM formation intended for use in real and accelerated time scale systems. Tasks: implementation of the previously proposed MM structure taking into account the turboshaft engine performances, development of a methodology for determining the MM coefficients based on known information about the static and dynamic properties of the engine, and formation of the MM structure of a two-engine helicopter power plant. For this, the methods of the theory of airjet engines and the theory of linear dynamic systems are used. The following results were obtained: the structure of a multimode high-speed MM of a turboshaft engine and a two-engine power plant was formed and tested. The scientific and practical novelty of the obtained results is as follows: the structure of the multimode linearized MM of the turboshaft engine is formed, which consists of static and dynamic submodels implemented in corrected parameters; the modeling technique was worked out on a simplified model, compiled considering expert information about the static and dynamic properties of the engine in the considered operation area. Formulas were obtained that relate the coefficients of the linear dynamic model to the values of the time constants of the rotors and the sensitivities obtained from the static characteristics; transient characteristics of the engine based on changes in fuel consumption and load power are determined, which correspond to physical knowledge about the engine; the modeling methodology and MM structure of a two-engine power plant were formed, which is distinguished by the combination of individual static and linear dynamic models of two engines with a single nonlinear dynamic model of the helicopter rotor; a simplified MM load necessary for testing the MM of the engine installation is proposed, which provides the calculation of the power consumed by the rotor, depending on the angular position of the blades.
12
Wang, Yong, Qiangang Zheng, Haibo Zhang, and Mingyang Chen. "The LQG/LTR control method for turboshaft engine with variable rotor speed based on torsional vibration suppression." Journal of Low Frequency Noise, Vibration and Active Control 39, no. 4 (2019): 1145–58. http://dx.doi.org/10.1177/1461348419847010.
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In order to realize the rapid response control for turboshaft engine during the process of variable rotor speed, the linear quadratic Gaussian with loop transfer recovery (LQG/LTR) control method for turboshaft engine based on torsional vibration suppression is proposed. Firstly, the two-speed dual clutch transmission model is applied to realize the variable rotor speed of helicopter. Then, based on the state variable model of turboshaft engine, the proper LQG/LTR controller is available. In order to eliminate the limitation of low-order torsional vibration on the bandwidth of LQG/LTR controller, a frequency-domain analysis method for the effect of torsional vibration suppression on LQG/LTR controller performance is developed. Finally, the numerical simulation is conducted to verify the LQG/LTR control for turboshaft engine with variable rotor speed based on torsional vibration suppression. The results show that the bandwidth of the LQG/LTR control loop can increase by 2–3 times under torsional vibration suppression. Meanwhile, when the rotor speed varies continuously by 40%, the overshoot and sag of the power turbine speed can decrease to less than 2% through LQG/LTR controller based on torsional vibration suppression, which achieves the rapid response control of the turboshaft engine.
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Filippone, Antonio, and Nicholas Bojdo. "Turboshaft engine air particle separation." Progress in Aerospace Sciences 46, no. 5-6 (2010): 224–45. http://dx.doi.org/10.1016/j.paerosci.2010.02.001.
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Zhang, Mengwei, Zhixiang Lin, Haiyang Huang, and Tianhong Zhang. "Design and verification of model predictive control for micro-turboshaft engine." Advances in Mechanical Engineering 11, no. 12 (2019): 168781401989019. http://dx.doi.org/10.1177/1687814019890198.
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In this article, a nonlinear model predictive control algorithm for a micro-turboshaft engine is designed. The control effect is verified by a bench test. First, a micro-turboshaft engine test bench is built, and the open-loop control experiment was carried out on it. Based on experiment data, a linear parameter varying prediction model is established. Then, by online rolling optimization based on multistep output prediction, together with feedback correction, a nonlinear model predictive control algorithm is obtained. The influence of algorithm parameters on the control effect is studied, and reasonable prediction period M, control period N, and control coefficient R are designed. Finally, the application of nonlinear model predictive control in micro-turboshaft engine is verified by bench test. The results show that with the changing of pitch angle, nonlinear model predictive control algorithm has a faster adjustment speed and smaller overshoot, compared with the conventional cascade proportional–integral control with feedforward. It is proofed that nonlinear model predictive control can be applied to a real turboshaft engine and has a better control effect.
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Wu, Heng, Shufan Zhao, Jijun Zhang, Bo Sun, and Hanqiang Song. "Gas turbine power calculation method of turboshaft based on simulation and performance model." MATEC Web of Conferences 189 (2018): 02003. http://dx.doi.org/10.1051/matecconf/201818902003.
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Gas turbine power of turboshaft engine cannot be measured, a total of five typical steady state point test data from the ground slow state to the maximum state were selected according to the factory acceptance test drive of a certain type of carrier-based helicopter turboshaft engine. Combustion chamber three-dimensional simulation model was established to carry on simulation analysis of different typical steady state combustion process. The simulated combustion chamber exit section parameters are input into the established gas turbine isentropic adiabatic aerodynamic calculation model to obtain the gas turbine power and outlet temperature. Select five typical steady state points of five sets of turboshaft engines on the same type to repeat the above calculation process, and compare the calculated value of gas turbine outlet temperature with the acceptance test values, it is found that the error values are all within 5%, and the effectiveness and accuracy of the gas turbine power calculation method are verified.
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Hocko, Marián, and Samer Al-Rabeei. "Analysis of unstable mode of a free gas turbine of turbo-compressors engines." MATEC Web of Conferences 345 (2021): 00009. http://dx.doi.org/10.1051/matecconf/202134500009.
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This paper analyses unstable mode of a free gas turbine of turboshaft helicopter engine TV3-117. The analysis is focused on the conditions of this phenomenon and the possibilities of its solution in a turboshaft helicopter engine and an industrial turbocharger engine with a free gas turbine. Knowing the causes of the unstable mode of operation of a free gas turbine will allow helicopter pilots to prevent accidents and increase the level of flight safety.
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Wei, Zhengchao, Yue Ma, Changle Xiang, and Dabo Liu. "Power Prediction-Based Model Predictive Control for Energy Management in Land and Air Vehicle with Turboshaft Engine." Complexity 2021 (August 27, 2021): 1–24. http://dx.doi.org/10.1155/2021/2953241.
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In recent years, the green aviation technology draws more attention, and more hybrid power units have been applied to the aerial vehicles. To achieve the high performance and long lifetime of components during varied working conditions, the effective regulation of the energy management is necessary for the vehicles with hybrid power unit (HPU). In this paper, power prediction-based model predictive control (P2MPC) for energy management strategy (EMS) is proposed for the vehicle equipped with HPU based on turboshaft engine in order to maintain proper battery’s state of charge (SOC) and decrease turboshaft engine’s exhaust gas temperature (EGT). First, a modeling approach based on data-driven method is adopted to obtain the mathematical model of turboshaft engine considering time delay and inertial of states. An integrated power predictor consisting of the classification of input status and the subpredictors are developed based on the deep learning method to improve the accuracy of the prediction model of the model predictive control (MPC). Subsequently, an EMS based on MPC using the proposed power predictor is introduced to regulate the SOC of battery and the EGT of turboshaft engine. The comparison with experimental results shows the high accuracy of mathematical model of turboshaft engine. The simulation results show the effectiveness of the proposed EMS for the vehicle, and the effects of different weight coefficients of objective function on the proposed EMS are discussed.
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Donateo, Teresa, Ludovico Cucciniello, Luciano Strafella, and Antonio Ficarella. "Control Oriented Modelling of a Turboshaft Engine for Hybrid Electric Urban Air-Mobility." E3S Web of Conferences 197 (2020): 05003. http://dx.doi.org/10.1051/e3sconf/202019705003.
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The electrification of aircraft is a well-established trend in recent years in order to achieve economic and environmental sustainability. In this framework, an application particularly interesting for hybrid electric power system is represented by urban air-mobility. For this application, the authors presented a parallel hybrid electric power system including a turboshaft engine and two electric motors and proposed a quasi-stationary simulation tool. As a further step, this paper deals with the dynamic modelling of the same turboshaft engine within the framework of a hybrid electric system where the pilot command is interpreted as a power request to be satisfied by the engine and the electric machine according to the selected energy management strategy. In this work, the dynamic behaviour of the turboshaft engine is analysed with and without the help of the electric motors to satisfy the power demand.
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Catana, Razvan Marius, and Gabriel Dediu. "Analytical Calculation Model of the TV3-117 Turboshaft Working Regimes Based on Experimental Data." Applied Sciences 13, no. 19 (2023): 10720. http://dx.doi.org/10.3390/app131910720.
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The paper presents a practical and relevant analytical calculation model for free turbine turboshaft working regimes and engine performance. The analytical calculation model is based on a post-processing method that analyzes a series of experimental data, specifically focusing on the percentage variations of the engine’s main parameters from the minimum to the takeoff working regime. The experimental data were acquired from three different types of engines: TV2-117A turboshaft, AI-20K turboprop, and Viper 632-41 turbojet. The analysis method aimed to identify, through calculations, certain similarity parameters that exhibit nearly constant variations or variations within tight limits. These parameters can then be used as approximate constants in the calculation model. By utilizing these constants related to similarity parameters, a mathematical connection between different engine regimes is established; more exactly, for the engine data from a known to unknown regime. In the current case, only the engine data from the takeoff regime are requested to be known, and in this way, the other working regimes of several engines can be calculated.
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He, Dongjing, Rui Zhang, Cheng Wen, and Jianliang Teng. "Performance Simulation of Thermodynamic Design for a New Turboshaft Engine." Journal of Physics: Conference Series 2658, no. 1 (2023): 012048. http://dx.doi.org/10.1088/1742-6596/2658/1/012048.
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Abstract For a search and rescue (SAR) helicopter, the requirements of long-range and twin-engine are becoming increasingly important. In this paper, the overall performance of a new turboshaft engine for SAR helicopters is simulated. Firstly, the main performance parameters of competitor engines are collected and compared, and the thermodynamic cycle parameters of the new engine are proposed subsequently. Then, an engine model is created in Turbomatch and the overall performance of this model at the design point is calculated. Finally, the off-design performances at different conditions of output power, ambient temperature, altitudes and flight Mach numbers (Ma) are investigated. A strategy of variable stator vane (VSV) for the anti-surge control of the axial compressor is also introduced. The results of the performance simulation indicate that this engine is quite competitive with lower specific fuel consumption (SFC) and higher specific power (SP) compared to the current SAR helicopter engines.
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Magnani, Mattia, Giacomo Silvagni, Vittorio Ravaglioli, and Fabrizio Ponti. "0-D Dynamic Performance Simulation of Hydrogen-Fueled Turboshaft Engine." Aerospace 11, no. 10 (2024): 816. http://dx.doi.org/10.3390/aerospace11100816.
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In the last few decades, the problem of pollution resulting from human activities has pushed research toward zero or net-zero carbon solutions for transportation. The main objective of this paper is to perform a preliminary performance assessment of the use of hydrogen in conventional turbine engines for aeronautical applications. A 0-D dynamic model of the Allison 250 C-18 turboshaft engine was designed and validated using conventional aviation fuel (kerosene Jet A-1). A dedicated, experimental campaign covering the whole engine operating range was conducted to obtain the thermodynamic data for the main engine components: the compressor, lateral ducts, combustion chamber, high- and low-pressure turbines, and exhaust nozzle. A theoretical chemical combustion model based on the NASA-CEA database was used to account for the energy conversion process in the combustor and to obtain quantitative feedback from the model in terms of fuel consumption. Once the engine and the turbomachinery of the engine were characterized, the work focused on designing a 0-D dynamic engine model based on the engine’s characteristics and the experimental data using the MATLAB/Simulink environment, which is capable of replicating the real engine behavior. Then, the 0-D dynamic model was validated by the acquired data and used to predict the engine’s performance with a different throttle profile (close to realistic request profiles during flight). Finally, the 0-D dynamic engine model was used to predict the performance of the engine using hydrogen as the input of the theoretical combustion model. The outputs of simulations running conventional kerosene Jet A-1 and hydrogen using different throttle profiles were compared, showing up to a 64% reduction in fuel mass flow rate and a 3% increase in thermal efficiency using hydrogen in flight-like conditions. The results confirm the potential of hydrogen as a suitable alternative fuel for small turbine engines and aircraft.
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Vladov, Serhii, Lukasz Scislo, Valerii Sokurenko, et al. "Neural Network Signal Integration from Thermogas-Dynamic Parameter Sensors for Helicopters Turboshaft Engines at Flight Operation Conditions." Sensors 24, no. 13 (2024): 4246. http://dx.doi.org/10.3390/s24134246.
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The article’s main provisions are the development and application of a neural network method for helicopter turboshaft engine thermogas-dynamic parameter integrating signals. This allows you to effectively correct sensor data in real time, ensuring high accuracy and reliability of readings. A neural network has been developed that integrates closed loops for the helicopter turboshaft engine parameters, which are regulated based on the filtering method. This made achieving almost 100% (0.995 or 99.5%) accuracy possible and reduced the loss function to 0.005 (0.5%) after 280 training epochs. An algorithm has been developed for neural network training based on the errors in backpropagation for closed loops, integrating the helicopter turboshaft engine parameters regulated based on the filtering method. It combines increasing the validation set accuracy and controlling overfitting, considering error dynamics, which preserves the model generalization ability. The adaptive training rate improves adaptation to the data changes and training conditions, improving performance. It has been mathematically proven that the helicopter turboshaft engine parameters regulating neural network closed-loop integration using the filtering method, in comparison with traditional filters (median-recursive, recursive and median), significantly improve efficiency. Moreover, that enables reduction of the errors of the 1st and 2nd types: 2.11 times compared to the median-recursive filter, 2.89 times compared to the recursive filter, and 4.18 times compared to the median filter. The achieved results significantly increase the helicopter turboshaft engine sensor readings accuracy (up to 99.5%) and reliability, ensuring aircraft efficient and safe operations thanks to improved filtering methods and neural network data integration. These advances open up new prospects for the aviation industry, improving operational efficiency and overall helicopter flight safety through advanced data processing technologies.
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Shang, Yiman. "The Latest Development of Turboshaft Engines." Highlights in Science, Engineering and Technology 71 (November 28, 2023): 268–75. http://dx.doi.org/10.54097/hset.v71i.12709.
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As the main power of rotor aircraft, the turboshaft engine has always been the focus of scientific and engineering research and has achieved rich research results. This paper reviews and summarizes the research results at home and abroad in the past 10 years from the aspects of control systems, oil-electric mixing, pollutant emission and compressor internal flow field optimization. High altitude and low temperature is the best condition for turboshaft engine operation. Pre-mission fuel estimation is good for low emissions. Oil-electric mixing engines can effectively improve efficiency, but reducing weight and cost is a problem that needs to be solved. The interaction between the leakage vortex and the excitation wave in the compressor increases the total pressure loss in the vortex core downstream of the excitation wave. The modes associated with wheezing can be stabilised by feeding back small-amplitude perturbations. The universality of the surge suppression of transonic centrifugal compressors and the stability of most of the compressor surges by small disturbance feedback are the next research focus.
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Pu, Chenghan, and Wenxiang Zhou. "Aero-engine Model Correction Technology Based on Adaptive Neural Network." Journal of Physics: Conference Series 2187, no. 1 (2022): 012064. http://dx.doi.org/10.1088/1742-6596/2187/1/012064.
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Abstract In this paper, a neural network-based algorithm is proposed to adapt the performance maps of engine component models for the mismatches between aero-engine simulation models and actual engine characteristics. Based on the general characteristics data of rotating components in GasTurb, a neural network capable of calculating the efficiency and mass flow of rotating components is trained. This neural network is introduced into the engine nonlinear component model to calculate the deviation between the output parameter of each section of the engine component model and the real engine performance indicators. The linear relationship between the parameters of the nonlinear model is solved by applying perturbation theory. The error between the output characteristics of the neural network and the real engine component characteristics is derived based on the simulation error, which makes the neural network is further optimized so that it can track the current real engine performance. In this paper, a model of one turboshaft engine is used as the simulation object, and the simulation of component model building and performance maps adaptation is carried out. The simulation results show that the proposed performance maps adaptation algorithm can effectively improve the accuracy of the component-level model of the turboshaft engine, and is applicable to model correction of various types of gas turbine engines.
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Petro, Kachanov, Lytviak Oleksandr, Derevyanko Oleksandr, and Komar Sergii. "DEVELOPMENT OF AN AUTOMATED HYDRAULIC BRAKE CONTROL SYSTEM FOR TESTING AIRCRAFT TURBOSHAFT GAS TURBINE ENGINES." Eastern-European Journal of Enterprise Technologies 6, no. 2 (102) (2019): 52–57. https://doi.org/10.15587/1729-4061.2019.185539.
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To absorb the power generated by a free turbine, hydraulic brake systems of various designs are used in ground tests of aircraft turboshaft gas turbine engines. Ground tests of aircraft turboshaft gas turbine engines with the use of such hydraulic brakes can result in emergency modes of automated engine control in the area of operation of a free turbine speed regulator. Mismatch between the hydraulic brake loading characteristics and the loading characteristics of the rotor driven by a free turbine of the engine is the main cause of emergency operation of automated control systems. The presented experimental loading characteristics of the hydraulic brake and the helicopter rotor show their significant difference in terms of gain. To eliminate this difference, a possibility of modeling dynamic parameters of rotors by simple automation means was considered. To solve this problem, a linear dynamic model and a block diagram of an automated hydraulic brake control system for ground testing of turboshaft gas turbine engines were elaborated. The law of regulation of the hydraulic brake loading was substantiated. A structurally dynamic diagram of the developed automated control system was presented and calculation formulas for determining the regulator parameters were given. Transient characteristics of the hydraulic brake unit without automation means and with the use of an automated loading control system were calculated. The presented calculation results have shown that the use of automation make it possible to fully emulate characteristics of the helicopter rotors
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Zhang, Xinglong, Lingwei Li, and Tianhong Zhang. "Research on Real-Time Model of Turboshaft Engine with Surge Process." Applied Sciences 12, no. 2 (2022): 744. http://dx.doi.org/10.3390/app12020744.
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The main data source for the verification of surge detection methods still rely on test rigs of the compressor or the whole engine, which makes the development of models of the whole engine surge process an urgent need to replace the high-cost and high-risk surge test. In this paper, a novel real-time surge model based on the surge mechanism is proposed. Firstly, the turboshaft engine component level model (CLM) and the classic surge dynamic model, Moore-Greitzer (MG) model is established. Then the stability of the MG model is analyzed and the compressor characteristics in the classical MG model are extended to establish the extended MG model. Finally, this paper considers the coupling relationship of the compressor’s rotor speed, mass flow and pressure between CLM and the extended MG model to establish the real-time model of the turboshaft engine with surge process. The simulation results show that this model can realize the whole surge process of the turboshaft engine under multiple operating states. The change characteristics of the rotor speed, compressor outlet pressure, mass flow, exhaust gas temperature and other parameters are consistent with the test data, which means that the model proposed can be further applied to the research of surge detection and anti-surge control.
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Vladov, Serhii, Oleksii Lytvynov, Victoria Vysotska, Viktor Vasylenko, Petro Pukach, and Myroslava Vovk. "An Innovative Applied Control System of Helicopter Turboshaft Engines Based on Neuro-Fuzzy Networks." Applied System Innovation 7, no. 6 (2024): 118. https://doi.org/10.3390/asi7060118.
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This study focuses on helicopter turboshaft engine innovative fault-tolerant fuzzy automatic control system development to enhance safety and efficiency in various flight modes. Unlike traditional systems, the proposed automatic control system incorporates a fuzzy regulator with an adaptive control mechanism, allowing for dynamic fuel flow and blade pitch angle adjustment based on changing conditions. The scientific novelty lies in the helicopter turboshaft engines distinguishing separate models and the fuel metering unit, significantly improving control accuracy and adaptability to current flight conditions. During experimental research on the TV3-117 engine installed on the Mi-8MTV helicopter, a parametric modeling system was developed to simulate engine operation in real time and interact with higher-level systems. Innovation is evident in the creation of the failure model that accounts for dynamic changes and probabilistic characteristics, enabling the prediction of failures and minimizing their impact on the system. The results demonstrate high effectiveness for the proposed model, achieving an accuracy of 99.455%, while minimizing the loss function, confirming its reliability for practical application in dynamic flight conditions.
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Scott, Robert. "Historical Trends in Turboshaft Engine Procurement Cost." Journal of the American Helicopter Society 62, no. 3 (2017): 1–9. http://dx.doi.org/10.4050/jahs.62.032011.
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Guedel, A., and A. Farrando. "Experimental study of turboshaft engine core noise." Journal of Aircraft 23, no. 10 (1986): 763–67. http://dx.doi.org/10.2514/3.45378.
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Chullai, E. T., Bodduluri Prasanna Sai, Dappili Sasindra Reddy, Kosaraju Pavan Kumar, and Yetukuri Manikanta. "Analysis of turboshaft engine-low power margin." International Journal of Advanced Intelligence Paradigms 29, no. 2/3 (2024): 248–62. http://dx.doi.org/10.1504/ijaip.2024.10067796.
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Reddy, Dappili Sasindra, Kosaraju Pavan Kumar, Yetukuri Manikanta, Bodduluri Prasanna Sai, and E. T. Chullai. "Analysis of turboshaft engine-low power margin." International Journal of Advanced Intelligence Paradigms 29, no. 2/3 (2024): 248–62. http://dx.doi.org/10.1504/ijaip.2024.142671.
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Zaitseva, Alina A., Matvey V. Belyavtsev, Evgeny A. Zaitsev, Dmitriy K. Kilmakov, Ivan P. Silin, and Vladislav F. Gavrilov. "SYNTHESIS OF AN INTEGRATED CONTROL SYSTEM FOR A HELICOPTER MULTI-ENGINE POWER PLANT ACCORDING TO A COMPLEX OF INTRA-ENGINE PARAMETERS." Electrical and data processing facilities and systems 20, no. 1 (2024): 97–105. http://dx.doi.org/10.17122/1999-5458-2024-20-1-97-105.
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Relevance The problem of engine synchronization within the framework of a multi-engine helicopter power plant is considered. The relevance of this research lies in the development of an integrated control system for the helicopter power plant based on a set of intra-engine parameters that sufficiently characterize the engine power. Aim of research The aim of such synchronization is to prevent unacceptable operating conditions and to ensure uniform consumption of the resource by each of the engines. The objectives of the study are: 1. development of a mathematical model of the helicopter power plant control system consisting of two ARRIUS 2G turboshaft engines with a gearbox and a double-row propeller, which allows for a comprehensive assessment of the behavior of the main gas-dynamic parameters for automatic and manual control modes; 2. a method has been developed for the synthesis of an integrated control system for a helicopter power plant using a set of gas-dynamic parameters that make it possible to estimate the available engine powers and equalize their values. Research method The problems were solved using methods of system analysis, theory of automatic control systems, linear algebra, functional analysis, fuzzy sets, and computer modeling. Results 1. A mathematical model of the helicopter power plant control system consisting of two ARRIUS 2G turboshaft engines with a gearbox and a double-row propeller has been developed, which made it possible to justify the choice of a set of controlled parameters that sufficiently characterize the power of each engine. 2. A method has been developed for synthesizing an integrated helicopter power plant control system that ensures synchronization of engine operating modes, which eliminates uneven load on the main transmission gearbox and uneven service life due to the difference in power supplied by each engine.
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Vladov, Serhii, Viacheslav Kovtun, Valerii Sokurenko, Oleksandr Muzychuk, and Victoria Vysotska. "Helicopter Turboshaft Engine Residual Life Determination by Neural Network Method." Electronics 13, no. 15 (2024): 2952. http://dx.doi.org/10.3390/electronics13152952.
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A neural network method has been developed for helicopter turboshaft engine residual life determination, the basis of which is a hierarchical system, which is represented in neural network model form, consisting of four layers, which determines the numerical value of the residual life. To implement a hierarchical system, a justified multilayer perceptron is used. A multilayer perceptron training algorithm has been developed, which, by introducing an initial parameter to the output layer, yields a prediction accuracy of up to 99.3%, and the adaptive Adam training rate ensures an accuracy of up to 99.4% in helicopter turboshaft engine residual life determination. A method for constructing a degradation curve has been developed that takes into account both the parameter predictions and similarities with past patterns, allowing you to determine the range of possible values of the residual life estimate, with a probability of up to 95%. The article considers an example of solving the task of determining the thermally stressed state of helicopter turboshaft engine compressor turbine blades and assessing their residual life. A computational experiment was carried out to determine the residual life of helicopter turboshaft engine compressor turbine blades, and the results, with 160 training epochs, recorded an accuracy of 99.3%, with a reduction in losses from 2.5% to 0.5% thanks to training process optimization by applying an adaptive training rate. The comparative analysis results showed that use of the multilayer perceptron as a hierarchical system gives better results than the classical RBF network and the least squares method. The first and second types of error were reduced by 2.23 times compared to the RBF network and by 4.74 times compared to the least squares method.
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Férand, Mélissa, Thomas Livebardon, Stéphane Moreau, and Marlène Sanjosé. "Numerical Prediction of Far-Field Combustion Noise from Aeronautical Engines." Acoustics 1, no. 1 (2019): 174–98. http://dx.doi.org/10.3390/acoustics1010012.
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A hybrid methodology combining a detailed Large Eddy Simulation of a combustion chamber sector, an analytical propagation model of the extracted acoustic and entropy waves at the combustor exit through the turbine stages, and a far-field acoustic propagation through a variable exhaust temperature field was shown to predict far-field combustion noise from helicopter and aircraft propulsion systems accurately for the first time. For the single-stream turboshaft engine, the validation was achieved from engine core to the turbine exit. Propagation to the far field was then performed through a modeled axisymmetric jet. Its temperature modified the acoustic propagation of combustion noise significantly and a simple analytical model based on the Snell–Descarte law was shown to predict the directivity for axisymmetric single jet exhaust accurately. Good agreement with measured far-field spectra for all turboshaft-engine regimes below 2 kHz stresses that combustion noise is most likely the dominant noise source at low frequencies in such engines. For the more complex dual-stream turbofan engine, two regime computations showed that direct noise is mostly generated by the unsteady flame dynamics and the indirect combustion noise by the temperature stratification induced by the dilution holes in the combustion chamber, as found previously in the turboshaft case. However, in the turboengine, direct noise was found dominant at the combustor exit for the low power case and equivalent contributions of both combustion noise sources for the high power case. The propagation to the far-field was achieved through the temperature field provided by a Reynolds-Averaged Navier–Stokes simulation. Good agreement with measured spectra was also found at low frequencies for the low power turboengine case. At high power, however, turboengine jet noise overcomes combustion noise at low frequencies.
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Vogt, R. L. "Future Trends in Turboshaft Engines up to the 5000 Horsepower Class." Journal of Engineering for Gas Turbines and Power 114, no. 4 (1992): 797–801. http://dx.doi.org/10.1115/1.2906659.
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Advanced technology now being demonstrated in the test cell will provide growth in existing engine ratings in the near term and substantially improve new technology engines early in the twenty-first century. The benefits these advancements provide, to the engines, to the salient characteristics important to users and designers, and to the vehicles they will power, are discussed.
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Jarvis, M. S., W. J. Ostergren, and B. Smith. "The Applicability of Electrically Driven Accessories for Turboshaft Engines." Journal of Engineering for Gas Turbines and Power 117, no. 2 (1995): 221–26. http://dx.doi.org/10.1115/1.2814084.
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Improved electrical power generation and actuation systems offer new design approaches for performing the engine control and accessory functions in helicopter propulsion systems. Present helicopter technology utilizes turboshaft engines with mechanically driven accessories. These accessories perform the functions of starting, fuel and lube pumping, variable stator actuation, and inlet particle separation. This paper discusses the applicability of replacing the mechanically driven accessories with their electrically driven counterparts. An electric accessory system is defined, which includes a switched reluctance starter/generator and its associated control unit; an electric pumping and actuation system; and the engine mounting for the starter/generator. A comparison between the mechanically and electrically driven accessory systems is performed on the basis of cost, weight, and reliability. Experience to date with switched reluctance machines and electrically driven turbo shaft accessory systems is summarized. The benefits of electrically driven accessories are shown and recommendations for future activity for his important technology are discussed.
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Catana, R. M., G. Cican, and G. Dediu. "Gas Turbine Engine Starting Applicated on TV2-117 Turboshaft." Engineering, Technology & Applied Science Research 7, no. 5 (2017): 2005–9. http://dx.doi.org/10.48084/etasr.1315.
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The paper presents the examination of two different types of engine starting configurations, applicated on TV2-117A turboshaft, running into the test bench. The first type of starting configuration is a normal starting, with the engine connected to the dynamometer which controls the free turbine speed by the dynamometer load. The second type of starting is a different one, the engine is not connected with the dynamometer, therefore it results that there is no control of the free turbine speed from the dynamometer, only from the engine but in particular conditions. To achieve the starting phase an instrumentation scheme is created, to control and monitor the engine, and a starting sequence with all the parameters, confirmations and commands that are involved into the starting phase. The engine starting is performed by the test bench operating system, composed of an acquisition system and a programmable controller, wherewith is running the starting sequence.
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R., M. Catana, G. Cican, and G. Dediu. "Gas Turbine Engine Starting Applicated on TV2-117 Turboshaft." Engineering, Technology & Applied Science Research 7, no. 5 (2017): 2005–9. https://doi.org/10.5281/zenodo.1037212.
Full textAbstract:
The paper presents the examination of two different types of engine starting configurations, applicated on TV2-117A turboshaft, running into the test bench. The first type of starting configuration is a normal starting, with the engine connected to the dynamometer which controls the free turbine speed by the dynamometer load. The second type of starting is a different one, the engine is not connected with the dynamometer, therefore it results that there is no control of the free turbine speed from the dynamometer, only from the engine but in particular conditions. To achieve the starting phase an instrumentation scheme is created, to control and monitor the engine, and a starting sequence with all the parameters, confirmations and commands that are involved into the starting phase. The engine starting is performed by the test bench operating system, composed of an acquisition system and a programmable controller, wherewith is running the starting sequence.
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Boyko, Ludmila, Vadym Datsenko, Aleksandr Dyomin, and Nataliya Pizhankova. "Devising a method for calculating the turboshaft gas turbine engine performance involving a blade-by-blade description of the multi-stage compressor in a two-dimensional setting." Eastern-European Journal of Enterprise Technologies 4, no. 8(112) (2021): 59–66. http://dx.doi.org/10.15587/1729-4061.2021.238538.
Full textAbstract:
The design and adjustment of modern gas turbine engines significantly rely on the use of numerical research methods. This paper reports a method devised for calculating the thermogasdynamic parameters and characteristics of a turboshaft gas turbine engine. The special feature of a given method is a two-dimensional blade-by-blade description of the compressor in the engine system. Underlying the calculation method is a nonlinear mathematical model that makes it possible to describe the established processes occurring in individual nodes and in the engine in general. To build a mathematical model, a modular principle was chosen, involving the construction of a system of interrelated and coordinated models of nodes and their elements. The approach used in modeling a two-dimensional flow in the compressor makes it possible to estimate by calculation a significant number of parameters that characterize its operation. With the help of the reported method, it is possible to estimate the effect of changing the geometric parameters of the compressor height on the characteristics of the engine. To take into consideration the influence of variable modes of air intake or overflow in various cross-sections along the compressor tract, to determine the effect of the input radial unevenness on the parameters of the compressor and engine in general. To verify the method described, the calculation of thermogasdynamic parameters and throttle characteristics of a single-stage turboshaft gas turbine engine with a 12-stage axial compressor was performed. Comparison of the calculation results with experimental data showed satisfactory convergence. Thus, the standard deviation of the calculation results from the experimental data is 0.45 % for the compressor characteristics, 0.4 % for power, and 0.15 % for specific fuel consumption. Development and improvement of methods for calculating the parameters and characteristics of gas turbine engines make it possible to improve the quality of design and competitiveness of locally-made aircraft engines.
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Johnson, E. T., and H. Lindsay. "Advanced Technology Programs for Small Turboshaft Engines: Past, Present, Future." Journal of Engineering for Gas Turbines and Power 113, no. 1 (1991): 33–39. http://dx.doi.org/10.1115/1.2906528.
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This paper addresses approximately 15 years of advanced technology programs sponsored by the United States Army Aviation Applied Technology Directorate and its predecessor organizations and conducted by GE Aircraft Engines (GEAE). Included in these programs is the accomplishment of (1) the 1500 shp demonstrator (GE12), which led to the 1700, and (2) the 5000 shp Modern Technology Demonstrator Engine (MTDE/GE27). Also included are several advanced technology component programs that have been completed or are ongoing through the early 1990s. The goals for the next generation of tri-service small advanced gas generator demonstration programs are shown. A prediction is thus made of the advancements required to fulfill the aircraft propulsion system established by the DoD/NASA Integrated High-Performance Turbine Engine Technology (IHPTET) initiative through the year 2000.
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Koruyucu, Elif, Onder Altuntas, and T. Hikmet Karakoc. "Exergetic Investigation of a Turboshaft Helicopter Engine Related to Engine Power." SAE International Journal of Aerospace 13, no. 2 (2020): 257–67. http://dx.doi.org/10.4271/01-13-02-0019.
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Chen, Yifeng, Yingqing Guo, Xinghui Yan, and Haotian Mao. "Multiple Delay-Dependent Guaranteed Cost Control for Distributed Engine Control Systems with Aging and Deterioration." Aerospace 9, no. 2 (2022): 88. http://dx.doi.org/10.3390/aerospace9020088.
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Distributed control architecture can bring many benefits to the engine control system, but the delay and packet dropout introduced by network communication will bring negative effects to the control system. The aging and deterioration of the engine are also obstacles in the design of the engine control system. This paper is concerned with the problem of guaranteed cost control for a distributed engine control system (DECS) with these negative constraints. Firstly, a model of DECS with multiple delays, packet dropouts and uncertainties is built. Secondly, a multiple delay-dependent guaranteed cost controller design method is proposed in the form of a set of linear matrix inequalities (LMIs). The non-convex optimal controller design problem is transformed into a convex optimization problem through the cone complementarity linearization (CCL) method, and the suboptimal controller is designed iteratively. Thirdly, turboshaft engine aging and deterioration are treated as sources of uncertainties, and the norm-bounded uncertain model of the turboshaft engine is modeled. Finally, the numerical simulations demonstrate the effectiveness and applicability of the guaranteed cost controller designed for DECS with multiple delays, packet dropouts, engine aging and deteriorations.
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Gu, Nannan, Xi Wang, and Meiyin Zhu. "Multi-Parameter Quadratic Programming Explicit Model Predictive Based Real Time Turboshaft Engine Control." Energies 14, no. 17 (2021): 5539. http://dx.doi.org/10.3390/en14175539.
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The traditional model predictive control (tMPC) algorithms have a large amount of online calculation, which makes it difficult to apply them directly to turboshaft engine–rotor systems because of real time requirements. Therefore, based on the theory of the perturbed piecewise affine system (PWA) and multi-parameter quadratic programming explicit model predictive control (mpQP-eMPC) algorithm, we develop a controller design method for turboshaft engine–rotor systems, which can be used for engine steady-state, transient state and limit protection control. This method consists of two steps: controller offline design and online implementation. Firstly, the parameter space of the PWA system is divided into several partitions offline based on the disturbance and performance constraints. Each partition has its own control law, which is in the form of piecewise affine linear function between the controller and the parameters. The control laws for those partitions are also obtained in this offline step. After which, for the online control implementation step, the corresponding control law can be obtained by a real-time query of a corresponding partition, which the current engine state falls into. This greatly reduces the amount of online calculation and thus improves the real-time performance of the MPC controller. The effectiveness of the proposed method is verified by simulating the steady-state and transient process of a turboshaft engine–rotor system with a limit protection requirement. Compared with tMPC, an mpQP-eMPC based controller can not only guarantee good steady-state, dynamic control performance and limit protection, but can also significantly improve the real-time performance of the control system.
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Salehi, Amin, and Morteza Montazeri-Gh. "Hardware-in-the-loop simulation of fuel control actuator of a turboshaft gas turbine engine." Proceedings of the Institution of Mechanical Engineers, Part M: Journal of Engineering for the Maritime Environment 233, no. 3 (2018): 969–77. http://dx.doi.org/10.1177/1475090218803727.
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The turboshaft engine is the major component in the propulsion system of most marine vehicles, and proper control of its function as a sub-system in the propulsion system has a direct impact on the performance of the vehicle’s propulsion control system. The engine performance control is performed through the fuel control system. The fuel control system of a turboshaft gas turbine engine consists of two parts: electronic control unit and fuel control unit which is the actuator of the fuel control system. In this article, a hardware-in-the-loop simulation is presented for testing and verifying the performance of the fuel control unit. In the hardware-in-the-loop simulation, the fuel control unit in hardware form is tested in connection with the numerically simulated model of engine and electronic control unit. In this simulation, a Wiener model for the turboshaft engine is developed which is validated with the experimental data. Subsequently, a multi-loop fuel controller algorithm is designed for the engine and the parameters are optimized so that the time response and physical constraints are satisfied. In the next step, a state-of-the-art hydraulic test setup is built and implemented to perform the hardware-in-the-loop test. The test system contains personal and industrial computer, sensors, hydraulic components, and data acquisition cards to connect software and hardware parts to each other. In this hardware-in-the-loop simulator, a host–target structure is used for real-time simulation of the software models. The results show the effectiveness of hardware-in-the-loop simulation in fuel control unit evaluation and verify the steady and transient performance of the designed actuator.
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Kang, Young Seok, Yong Min Jun, and Jae Hwan Kim. "Main Components Design of a Small Turboshaft Engine." KSFM Journal of Fluid Machinery 21, no. 2 (2018): 19–26. http://dx.doi.org/10.5293/kfma.2018.21.2.019.
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Omar, H. H., V. S. Kuz'michev, A. O. Zagrebelnyi, and V. A. Grigoriev. "The effect of heat recovery on the optimal values of helicopter turboshaft engine parameters." VESTNIK of Samara University. Aerospace and Mechanical Engineering 19, no. 4 (2020): 43–57. http://dx.doi.org/10.18287/2541-7533-2020-19-4-43-57.
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Recent studies related to fuel economy in air transport conducted in our country and abroad show that the use of recuperative heat exchangers in aviation gas turbine engines can significantly, by up to 20...30%, reduce fuel consumption. Until recently, the use of cycles with heat recovery in aircraft gas turbine engines was restrained by a significant increase in the mass of the power plant due to the installation of a heat exchanger. Currently, there is a technological opportunity to create compact, light, high-efficiency heat exchangers for use on aircraft without compromising their performance. An important target in the design of engines with heat recovery is to select the parameters of the working process that provide maximum efficiency of the aircraft system. The article focused on setting of the optimization problem and the choice of rational parameters of the thermodynamic cycle parameters of a gas turbine engine with a recuperative heat exchanger. On the basis of the developed method of multi-criteria optimization the optimization of thermodynamic cycle parameters of a helicopter gas turbine engine with a ANSAT recuperative heat exchanger was carried out by means of numerical simulations according to such criteria as the total weight of the engine and fuel required for the flight, the specific fuel consumption of the aircraft for a ton- kilometer of the payload. The results of the optimization are presented in the article. The calculation of engine efficiency indicators was carried out on the basis of modeling the flight cycle of the helicopter, taking into account its aerodynamic characteristics. The developed mathematical model for calculating the mass of a compact heat exchanger, designed to solve optimization problems at the stage of conceptual design of the engine and simulation of the transport helicopter flight cycle is presented. The developed methods and models are implemented in the ASTRA program. It is shown that optimal parameters of the working process of a gas turbine engine with a free turbine and a recuperative heat exchanger depend significantly on the heat exchanger effectiveness. The possibility of increasing the efficiency of the engine due to heat regeneration is also shown.
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Yan, Siqi, Yun Zhang, Benwei Li, and Chenguang Liu. "Surge margin monitoring of one turboshaft engine with inlet distortion." Journal of Physics: Conference Series 2472, no. 1 (2023): 012053. http://dx.doi.org/10.1088/1742-6596/2472/1/012053.
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Abstract In order to explore the engine surge when inlet distortion index and engine surge margin, the relationship between the parameter characteristics of research engine surge, strengthen safety monitoring assessment engine, this paper designed a kind of a certain type of engine bench test surge monitoring system, and unstable flow field of a certain type of vortex axis engine working parameters for monitoring and analysis. In this paper, a plug-plate distortion generator is used to induce a surge engine, and the circumferential static pressure changes of the inlet and outlet of the engine, the axial compressor and the centrifugal compressor under different working conditions are obtained. The changes of circumferential unevenness and mean turbulence, the pressure ratio at working point and the converted air flow rate at working point are analyzed with the increase of the height of the plug-plate under different working conditions. The results show that the distortion index of the working point increases and the surge margin decreases with the increase of the height of the plug-plate at the same rotating speed. When the height of the plug-plate is similar, the higher the speed is, the greater the distortion index of the working point is, and the smaller the surge margin is.
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Gounet, Helene, and Serge Lewy. "Three-Dimensional Sound Directivity around a Helicopter Turboshaft Engine." Journal of the American Helicopter Society 57, no. 4 (2012): 1–10. http://dx.doi.org/10.4050/jahs.57.042002.
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Turboshaft engines can be the main source of noise due to a helicopter at takeoff. Some new silencing designs of the inlets and of the ejector were tested on a Turbomeca Arrius 2B2 engine in an open-air static facility. Intake and exhaust are not axisymmetric, and conventional directivity patterns of sound field on a horizontal arc of circle are insufficient. A special microphone array on a vertical half-circle translating axially was built. Data processing has been implemented to plot maps of sound pressure levels in third-octave bands and to compute sound power levels. Intake and exhaust radiations are separated thanks to mufflers on the other side. The lined fins in the secondary lateral inlet well reduce the compressor tone, which is largely dominant in intake radiation. Its sound power level is decreased by 7 dB. The novel ejector is also successful to reduce exhaust broadband noise above 1 kHz with a gain of 5 dB on sound power level. Finally, the benefit on the acoustic emission of the helicopter in flight is appraised.
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Wang, Qingping, Wenchao Zhang, Xin Yuan, Yixuan Wang, Zhongliang Shen, and Fei Wang. "Research on the Impact of the Sand and Dust Ingestion Test on the Overall Performance of Turboshaft Engines." Aerospace 12, no. 2 (2025): 146. https://doi.org/10.3390/aerospace12020146.
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Based on GJB 242A, a detailed experimental procedure for the sand and dust ingestion of a turboshaft engine was established. A specific type of turboshaft engine was used to conduct 54 h full-engine sand and dust ingestion experiments. This research studied the impact of sand and dust ingestion on the engine’s common operating line, power loss, specific fuel consumption, and gas turbine exhaust temperature, among other performance parameters. The experimental results indicate that under the same equivalent power conditions, the impact of short-term sand and dust ingestion on the engine’s common operating line is minimal; as the sand and dust ingestion time increases, the equivalent airflow decreases significantly, causing the engine’s common operating line to shift upward and the gas turbine exhaust temperature to rise, with the maximum increase reaching 27.9 °C. However, the impact of sand and dust ingestion on the gas turbine exhaust temperature at high power levels is relatively small. After completing the sand and dust ingestion test, the engine’s power loss at maximum continuous operation was approximately 11.33%, and the specific fuel consumption increased by about 6.05%. The power loss does not meet the requirement of being less than 10% as stipulated in GJB 242A. Based on the engine disassembly inspection results, subsequent improvement suggestions were proposed. The findings of this paper can provide a scientific and rational basis and reference for the sand and dust resistance design and sand ingestion testing of similar aero-engines.
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Ludmila, Boyko, Datsenko Vadym, Dyomin Aleksandr, and Pizhankova Nataliya. "Devising a method for calculating the turboshaft gas turbine engine performance involving a blade-by-blade description of the multi-stage compressor in a two-dimensional setting." Eastern-European Journal of Enterprise Technologies 4, no. 8 (112) (2021): 59–66. https://doi.org/10.15587/1729-4061.2021.238538.
Full textAbstract:
The design and adjustment of modern gas turbine engines significantly rely on the use of numerical research methods. This paper reports a method devised for calculating the thermogasdynamic parameters and characteristics of a turboshaft gas turbine engine. The special feature of a given method is a two-dimensional blade-by-blade description of the compressor in the engine system. Underlying the calculation method is a nonlinear mathematical model that makes it possible to describe the established processes occurring in individual nodes and in the engine in general. To build a mathematical model, a modular principle was chosen, involving the construction of a system of interrelated and coordinated models of nodes and their elements. The approach used in modeling a two-dimensional flow in the compressor makes it possible to estimate by calculation a significant number of parameters that characterize its operation. With the help of the reported method, it is possible to estimate the effect of changing the geometric parameters of the compressor height on the characteristics of the engine. To take into consideration the influence of variable modes of air intake or overflow in various cross-sections along the compressor tract, to determine the effect of the input radial unevenness on the parameters of the compressor and engine in general. To verify the method described, the calculation of thermogasdynamic parameters and throttle characteristics of a single-stage turboshaft gas turbine engine with a 12-stage axial compressor was performed. Comparison of the calculation results with experimental data showed satisfactory convergence. Thus, the standard deviation of the calculation results from the experimental data is 0.45 % for the compressor characteristics, 0.4 % for power, and 0.15 % for specific fuel consumption. Development and improvement of methods for calculating the parameters and characteristics of gas turbine engines make it possible to improve the quality of design and competitiveness of locally-made aircraft engines.