Relevant bibliographies by topics / Turboshaft engine

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  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers

Academic literature on the topic 'Turboshaft engine'

Author: Grafiati
Published: 4 June 2021
Last updated: 18 June 2025

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Journal articles on the topic "Turboshaft engine"

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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.
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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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Dissertations / Theses on the topic "Turboshaft engine"

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Suhr, Stephen Andrew. "Preliminary Turboshaft Engine Design Methodology for Rotorcraft Applications." Thesis, Georgia Institute of Technology, 2006. http://hdl.handle.net/1853/14128.

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In the development of modern rotorcraft vehicles, many unique challenges emerge due to the highly coupled nature of individual rotorcraft design disciplines therefore, the use of an integrated product and process development (IPPD) methodology is necessary to drive the design solution. Through the use of parallel design and analysis, this approach achieves the design synthesis of numerous product and process requirements that is essential in ultimately satisfying the customers demands. Over the past twenty years, Georgia Techs Center for Excellence in Rotorcraft Technology (CERT) has continuously focused on refining this IPPD approach within its rotorcraft design course by using the annual American Helicopter Society (AHS) Student Design Competition as the design requirement catalyst. Despite this extensive experience, however, the documentation of this preliminary rotorcraft design approach has become out of date or insufficient in addressing a modern IPPD methodology. In no design discipline is this need for updated documentation more prevalent than in propulsion system design, specifically in the area of gas turbine technology. From an academic perspective, the vast majority of current propulsion system design resources are focused on fixed-wing applications with very limited reference to the use of turboshaft engines. Additionally, most rotorcraft design resources are centered on aerodynamic considerations and largely overlook propulsion system integration. This research effort is aimed at bridging this information gap by developing a preliminary turboshaft engine design methodology that is applicable to a wide range of potential rotorcraft propulsion system design problems. The preliminary engine design process begins by defining the design space through analysis of the initial performance and mission requirements dictated in a given request for proposal (RFP). Engine cycle selection is then completed using tools such as GasTurb and the NASA Engine Performance Program (NEPP) to conduct thorough parametric and engine performance analysis. Basic engine component design considerations are highlighted to facilitate configuration trade studies and to generate more detailed engine performance and geometric data. Throughout this approach, a comprehensive engine design case study is incorporated based on a two-place, turbine training helicopter known as the Georgia Tech Generic Helicopter (GTGH). This example serves as a consistent propulsion system design reference highlighting the level of integration and detail required for each step of the preliminary turboshaft engine design methodology.
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Baslamisli, Ufuk. "Helicopter Turboshaft Engine Ground Preformance With Alternative Fuels." Master's thesis, METU, 2012. http://etd.lib.metu.edu.tr/upload/12614098/index.pdf.

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In recent years, extensive studies on alternative fuels have been conducted to find environmentally friendly, economically feasible fuels due to finite petroleum sources, environmental and economical reasons. In this thesis, effects of alternative fuels on engine performance and exhaust emission are studied experimentally. Cold and reacting tests have been performed. Volumetric flow rate, discharge pressure are measured according to different pump speed. Droplet diameters, droplet distribution, spray cone angle and two dimensional velocity distribution from combustor fuel nozzle are determined by IPI and PIV technique. The comparative performance of alternative fuels and JET A-1 are investigated by atmospheric combustion tests and experimental turbojet tests in terms of exhaust gas temperatures, emissions, combustion chamber efficiency. Emissions, combustion chamber exit temperature profile, power turbine inlet and exhaust gas temperatures, effects of fuels on engine performance are observed and measured in detail at RR Allison 250 C-18 turbo-shaft engine.
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Chiang, Kenneth H. "Fuzzy logic mode selection for a recuperative turboshaft engine." Thesis, Massachusetts Institute of Technology, 1992. http://hdl.handle.net/1721.1/74846.

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Miste', Gianluigi. "Variable speed rotor helicopters: optimization of main rotor-turboshaft engine integration." Doctoral thesis, Università degli studi di Padova, 2015. http://hdl.handle.net/11577/3424123.

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Variable speed rotors (VSRs) represent an innovative research field for the development of new rotorcraft designs. The possibility to change the rotational speed of a helicopter rotor, as a function of the specific flight condition, makes it possible to achieve optimum performance and relevant fuel consumption reductions. However, issues related to employing a main rotor variable speed are numerous and require an interdisciplinary approach. The present study represents the first effort in the open literature aimed at understanding the performance implications of coupling helicopter trim and turboshaft engine simulations for a VSR model. A gas turbine simulation code, TSHAFT, and a helicopter performance tool, TCOPTER, have been implemented in order to be able to carry out the coupled analysis. Following this, the VSR concept has been tested on a real helicopter case: the models of a UH-60 Black Hawk helicopter and a GE T700 turboshaft engine have been implemented and validated against experimental data. Subsequently, an optimization routine has been employed to find the optimal main rotor speeds which minimize fuel consumption in different helicopter flight conditions. Two different approaches to VSRs have been analyzed: the former employing a traditional fixed ratio transmission (FRT), the latter assuming a continuously variable transmission (CVT). In the FRT case, since the turbine and main rotor speeds are in a fixed ratio, the optimal speed has been calculated as the best compromise between optimal main rotor speed and optimal turbine speed. In the CVT case, the study has been carried out assuming that main rotor and turbine speeds were free to rotate at their optimal speeds. Different simulation cases have been analyzed in order to quantify the benefits related to the optimal main rotor speed depending on flight conditions, altitude and helicopter gross weight. It has been found that coupling both the helicopter and engine model is important to adequately determine the correct rotational speed corresponding to minimum fuel consumption. More than 13% fuel saving has been shown to be feasible. Finally, possible improvements to the VSR concept have been studied. In particular, a trial has been made to redesign the power turbine of the GE T700 in order to improve the efficiency of the engine in a wide speed variation range.<br>I rotori a velocità di rotazione variabile (Variable Speed Rotors, VSR) rappresentano un argomento di ricerca innovativo per lo sviluppo di nuove configurazioni di velivoli a decollo verticale, quali l’elicottero o il convertiplano. La possibilità di modificare la velocità di rotazione del rotore principale, in funzione della specifica condizione di volo, permette di ottenere prestazioni ottimali e significative riduzioni del consumo di carburante. Tuttavia, le problematiche connesse all’impiego di una velocità di rotazione variabile sono numerose e richiedono un approccio di analisi interdisciplinare. Il presente studio si configura come il primo esempio in letteratura di analisi prestazionale eseguita con simulazioni accoppiate rotore e motore turbo-albero per un modello di VSR. Due strumenti di simulazione sono stati implementati al fine di effettuare la suddetta analisi accoppiata: un codice di simulazione di turbomotori a gas (TSHAFT) e un software per la stima dell’assetto e delle prestazioni di un elicottero (TCOPTER). La validità del concetto di rotore a velocità variabile è stata testata su un caso reale: a tale scopo i modelli di un elicottero UH-60 Black Hawk e di un motore turbo-albero GE T700 sono stati implementati e sottoposti a validazione su dati sperimentali. Successivamente, si è proceduto alla costruzione di una routine di ottimizzazione capace di individuare le velocità ottimali del rotore, in funzione delle diverse condizioni di volo dell’elicottero; tali velocità corrispondono alla condizione di minimo consumo di carburante. Sono state analizzate a livello puramente prestazionale due differenti tipologie di VSR: la prima contempla l’utilizzo di una trasmissione tradizionale a rapporto di riduzione fisso (Fixed Ratio Transmission, FRT); la seconda prevede l’impiego un’ipotetica trasmissione a variazione continua (Continuously Variable Transmission, CVT). Nel caso FRT, poiché le velocità di rotazione della turbina e del rotore principale sono in un rapporto fisso, la velocità ottimale è stata calcolata come il miglior compromesso tra la velocità ottimale del rotore principale e quella della turbina. Nel caso CVT, invece, lo studio è stato effettuato assumendo che le velocità di rotore e turbina fossero libere di ruotare alle rispettive velocità ottimali. Diversi casi di simulazione sono stati analizzati, al fine di quantificare i benefici legati alla possibilità di operare alla velocità ottimale del rotore in funzione delle condizioni di volo, dell’altitudine e del peso dell'elicottero. L'accoppiamento del modello dell'elicottero e del modello di motore turbo-albero è risultato determinante per un’adeguata individuazione della velocità corrispondente a consumo minimo. La massima riduzione nei consumi di carburante è stata stimata attorno al 13%. Infine, sono state studiate possibili soluzioni progettuali in grado di apportare ulteriori margini di miglioramento a elicotteri operanti con VSR. In particolare, è stato effettuato un tentativo di riprogettazione preliminare della turbina di potenza del GE T700 con l’obiettivo di incrementarne l’intervallo di funzionamento a massima efficienza. In sostanza si è cercato di rendere le prestazioni della turbina meno sensibili alle variazioni nel numero di giri, cercando di estendere la zona di rendimento massimo attorno al punto di progetto.
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Novikov, Yaroslav. "Development Of A High-fidelity Transient Aerothermal Model For A Helicopter Turboshaft Engine For Inlet Distortion And Engine Deterioration Simulations." Master's thesis, METU, 2012. http://etd.lib.metu.edu.tr/upload/12614389/index.pdf.

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Presented in this thesis is the development of a high-fidelity aerothermal model for GE T700 turboshaft engine. The model was constructed using thermodynamic relations governing change of flow properties across engine components, and by applying real component maps for the compressor and turbines as well as empirical relations for specific heats. Included in the model were bleed flows, turbine cooling and heat sink effects. Transient dynamics were modeled using inter-component volumes method in which mass imbalance between two engine components was used to calculate the inter-component pressure. This method allowed fast, high-accuracy and iteration-free calculation of engine states. Developed simulation model was successfully validated against previously published simulation results, and was applied in the simulation of inlet distortion and engine deterioration. Former included simulation of steady state and transient hot gas ingestion as well as transient decrease in the inlet total pressure. Engine deterioration simulations were performed for four different cases of component deterioration with parameters defining engine degradation taken from the literature. Real time capability of the model was achieved by applying time scaling of plenum volumes which allowed for larger simulation time steps at very little cost of numerical accuracy. Finally, T700 model was used to develop a generic model by replacing empirical relations for specific heats with temperature and FAR dependent curve fits, and scaling T700 turbine maps. Developed generic aerothermal model was applied to simulate steady state performance of the Lycoming T53 turboshaft engine.
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Nelson, Eric Benjamin 1974. "An experimental study of surge control in the Allied Signal LTS-101 helicopter turboshaft engine." Thesis, Massachusetts Institute of Technology, 1998. http://hdl.handle.net/1721.1/50386.

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Zhang, Chengyu [Verfasser], Volker [Akademischer Betreuer] Gümmer, Volker [Gutachter] Gümmer, and Harald [Gutachter] Klein. "Evaluation of the Potential of Recuperator on a 300-kW Turboshaft Helicopter Engine / Chengyu Zhang ; Gutachter: Volker Gümmer, Harald Klein ; Betreuer: Volker Gümmer." München : Universitätsbibliothek der TU München, 2020. http://d-nb.info/1211725332/34.

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Ondráček, Vladimír. "Regulace přívodu paliva turbohřídelového motoru." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2013. http://www.nusl.cz/ntk/nusl-230889.

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Elaborated project gives a complex design of backup hydro-mechanical unit for fuel supply of turboshaft engine TS 100. Required function of backup unit is to secure basic function of engine TS 100 over failure of primary electro-mechanical fuel system. Backup hydro-mechanical unit consists of hydrostatic fuel pump, centrifugal regulator, valve of maximum and minimum pressure, switch valve and signalization of activation hydro-mechanical unit. Parameters of hydro-mechanical unit are designed considering requested rotations speed of output shaft of engine and its allowed fluctuation. Calculation of basic parameters and dynamical calculation of behavior of the system regulator with engine is made in program DYNAST Shell. Additional calculations were made in program Microsoft Excel. Own design of hydro-mechanical unit is made in 3D design software Pro/Engineer.
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Duran, Celio. "Modélisation du comportement dynamique non-linéaire et transitoire de turbomoteur avec multitouches rotor/stator." Thesis, Lyon, INSA, 2014. http://www.theses.fr/2014ISAL0144.

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Cette thèse traite de la dynamique non-linéaire multi-contact des ensembles rotor/stator et s’applique en particulier aux tur-bomoteurs d’hélicoptère conçus par Turboméca, groupe Safran. L’amélioration des performances des turbines à gaz pousse les constructeurs à réduire les jeux fonctionnels rotor-stator no-tamment, tout en garantissant robustesse et fiabilité. Cela nécessite de développer des modèles les plus précis possible afin de prévoir et maîtriser des situations à risques telles que les interactions rotor/stator entre les parties fixes et tournantes déclen-chées principalement, dans le cas des turbomoteurs d’hélicoptère, par la perte d’aubes. La partie 1 présente une synthèse bibliographique des principaux phénomènes physiques rencontrés suite à une touche ro-tor/stator en s’appuyant sur l’expérimentation et le calcul. Un bilan sur les différents modèles numériques de gestion du con-tact frottant est détaillé. La dualité entre méthodes temporelles et fréquentielles est aussi abordée comme la méthode de la ba-lance harmonique et les schémas d’intégration temporelle de la famille de Newmark. Il est aussi décrit deux outils d’analyse fréquentielle : le spectrogramme pour analyser l’évolution d’un spectre fréquentiel dans le temps, le full-spectrum pour pren-dre en compte les précessions du rotor. La partie 2 se focalise sur des systèmes dynamiques académiques : un oscillateur forcé à double butées, un rotor de Jeffcott et un rotor à 3 disques avec tous deux une interaction disque/carter. Compte tenu du caractère transitoire du comportement des turbomoteurs, il s’agit de tester des méthodes d’intégration temporelle pas à pas et aussi des lois de contact. Il en ressort que la méthode de Newmark à accélération moyenne, et les lois de contact type « pénalité amortie » combinées à une régularisation de la raideur et de l’amortissement par une fonction arc tangente sont pertinentes. La modélisation de rotor en flexion en ré-gime transitoire et avec plusieurs touches possibles est réalisée avec la méthode des éléments finis et l’intégration des mé-thodes et techniques précédentes. L’ensemble de la modélisation est mise en œuvre sous l’environnement Matlab et se traduit au final par un logiciel nommé ToRoS (Touche Rotor-Stator). Le turbomoteur de l’Ardiden 1H fait l’objet de la dernière partie. Le logiciel ToRoS développé est utilisé pour prévoir la dyna-mique transitoire de sa turbine libre soumise à de multiples touches, consécutifs à un départ d’aubes. Les lois de contacts ap-pliquées dépendent du type de contact : disque/carter, labyrinthe/stator, palier/butée. Durant la descente en vitesse, la ligne d’arbre adopte, en fonction du niveau de balourd, de la vitesse de rotation, des paramètres du contact et du frottement, un comportement avec un contact quasi-permanent en précession directe<br>This PhD thesis deals with the nonlinear transient dynamic response of rotor/stator assemblies in the case of multi-contacts, it is applied on Turbomeca’s helicopter turbo-engine. In order to improve gas turbine performances, constructors have to reduce rotor/stator clearances, while continuing to maintain component’s reliability, durability and safety. It implies the development of models to predict and control unsafe situations as, rotor/stator interactions between fixed and rotating parts, mainly triggered by a blade-loss in helicopters turbo-engine case. The first part of this document is concerned with a bibliographical summary of the main physical phenomena observed after a rotor/stator interaction, this is supported by experiments and numerical calculations. A review of the various sliding contact numerical models is presented. The duality between time and/or frequency simulation response methods as, harmonic balance method vs Newmark time integration scheme is discussed. Then two numerical tools for frequency domain analysis are described: the spectrogram to analyze frequency spectrum as a function of the time, the full-spectrum for analyzing the rotor whirl motions. The second part is focused on the time response simulation of some academic systems: an excited oscillator with two end-stops, a Jeffcott rotor and finally a 3 disks rotor both subjected to disk/casing interactions. Given the transient behavior exhibited by turbo-engine rotors following a rotor/stator contact, the purpose is to test several step-by-step time integration scheme combined with different contact laws. This analysis has shown that the Newmark scheme with constant acceleration used with damped contact penalty laws combined to stiffness and damping coefficients smoothed by arctangent functions are relevant. The rotor bending modeling during transient motion considering possible multi-contacts with the stator is realized using the finite element method and the previously reviewed contact modeling methods. The simulation is implemented under Matlab environment and is named ToRoS. (Rotor/Stator Touch). Finally, the developed modeling is applied to the Ardiden 1H turbo-engine. The ToRoS software is used to predict the transient dynamic response of the free power turbine subjected to multi-contacts, after a sudden blade-loss which is modeled by a sudden unbalance. Contact laws are applied and depend on contact type and location: disk/casing, seals, thrust bearing. Depending on the mass unbalance level, the speed of rotation, the contact and friction parameters, the rotor can be in a quasi-permanent contact state in forward whirl while the rotation speed is running-down
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Neklapil, Libor. "Návrh souosého vysokootáčkového reduktoru." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2008. http://www.nusl.cz/ntk/nusl-228136.

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The thesis deal with design of coaxial high-speed gear box for small-scale turboshaft engines. At the beginning a study of problems was performed and for design concept was elected version of single-shaft turbo-engine with electric generator. Kinematic diagram, type of gear design, material and lubrication method was designed. Further was solved proposal of basic gearing parameters, choice of the number of tooth and basic proposal calculations were performed. Was performed check calculation of gearing, calculation of bearings durability and was processed design documentation in required range. Designed gear reducer has two stage with three coutershafts, that are deployed evenly about main axis of reducer. First stage is gear with external gearing, second stage with internal gearing. The thesis may be used as a template for next similar gear reducers design.
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Books on the topic "Turboshaft engine"

1

S, Litt Jonathan, Guo Ten-Huei, and Lewis Research Center, eds. Neural network-based sensor validation for turboshaft engines. National Aeronautics and Space Administration, Lewis Research Center, 1998.

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S, Litt Jonathan, Guo Ten-Huei, and Lewis Research Center, eds. Neural network-based sensor validation for turboshaft engines. National Aeronautics and Space Administration, Lewis Research Center, 1998.

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S, Litt Jonathan, Guo T. H, and Lewis Research Center, eds. Neural network-based sensor validation for turboshaft engines. National Aeronautics and Space Administration, Lewis Research Center, 1998.

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S, Litt Jonathan, Guo Ten-Huei, and Lewis Research Center, eds. Neural network-based sensor validation for turboshaft engines. National Aeronautics and Space Administration, Lewis Research Center, 1998.

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D'Angelo, Martin. Wide speed range turboshaft study. National Aeronautics and Space Administration, 1995.

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E, Paxson D., Schobeiri M. T, and United States. National Aeronautics and Space Administration., eds. Dynamic simulation of a wave rotor topped turboshaft engine. National Aeronautics and Space Administration, 1997.

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Chen, Ku, Litt Jonathan S, United States. Army Aviation Systems Command., and United States. National Aeronautics and Space Administration., eds. A simplified dynamic model of the T700 turboshaft engine. National Aeronautics and Space Administration, 1992.

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Karl, Owen A., United States. National Aeronautics and Space Administration., and U.S. Army Research Laboratory., eds. Forced response testing of an axi-centrifugal turboshaft engine. National Aeronautics and Space Administration, U.S. Army Research Laboratory, 1997.

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Karl, Owen A., and United States. National Aeronautics and Space Administration., eds. Forced response testing of an axi-centrifugal turboshaft engine. National Aeronautics and Space Administration, 1996.

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Center, Ames Research, ed. A high fidelity real-time simulation of a small turboshaft engine. National Aeronautics and Space Administration, Ames Research Center, 1988.

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Book chapters on the topic "Turboshaft engine"

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Jia, Linyuan, Zi’ao Chen, Cheng Ren, Keyu Yang, and Yuchun Chen. "Overall Performance Study of Turboshaft-Turbofan Variable Cycle Engine." In Springer Aerospace Technology. Springer Nature Singapore, 2025. https://doi.org/10.1007/978-981-96-3240-4_24.

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Yan, Ming, Chunyu Yang, and Xin Chen. "Research on Flight Test Technology of Turboshaft Engine Installation Performance Loss." In Lecture Notes in Electrical Engineering. Springer Singapore, 2021. http://dx.doi.org/10.1007/978-981-16-7423-5_37.

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Wei, Yanyan, Chunlei Chang, Hongyu Wang, and Di Kang. "Analysis on Modeling of Constant Pressure Difference Valve of Certain Turboshaft Engine." In Lecture Notes in Electrical Engineering. Springer Singapore, 2019. http://dx.doi.org/10.1007/978-981-13-3305-7_221.

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Jia, Tianhao, and Yue Ma. "A Non-iterative Turboshaft Engine Model with Its Neural Network Control Algorithm." In Lecture Notes in Electrical Engineering. Springer Nature Singapore, 2023. http://dx.doi.org/10.1007/978-981-99-6886-2_39.

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Yan, Dongxu, Hailong Tang, Min Chen, Jiyuan Zhang, Pengcheng Dong, and Junhao Zhou. "Modeling and Control Law Optimization Design of Starting Process of the Three-Shaft Turboshaft Engine." In 2023 Asia-Pacific International Symposium on Aerospace Technology (APISAT 2023) Proceedings. Springer Nature Singapore, 2024. http://dx.doi.org/10.1007/978-981-97-4010-9_4.

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Jia, Linyuan, Zhuocheng Li, Yunfei Bai, Jichang Wu, Le Gao, and Ziao Chen. "Design of the Turboshaft Engine Acceleration and Deceleration Control Schedules Based on Direct Simulation Method." In Springer Aerospace Technology. Springer Nature Singapore, 2025. https://doi.org/10.1007/978-981-96-3240-4_29.

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Yu, Haibin, Huguo Sun, Ling Yan, and Kai Zhang. "Study on the Condition Monitoring System of Certain Type of Turboshaft Engine Based on Flight Data." In Proceedings of the First Symposium on Aviation Maintenance and Management-Volume I. Springer Berlin Heidelberg, 2014. http://dx.doi.org/10.1007/978-3-642-54236-7_25.

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Wei, Zhengchao, Yue Ma, Changle Xiang, and Dabo Liu. "Velocity Prediction Based Model Predictive Control for Energy Management in Land and Air Vehicle with Turboshaft Engine." In Communications in Computer and Information Science. Springer Singapore, 2021. http://dx.doi.org/10.1007/978-981-16-7210-1_25.

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Greatrix, David R. "Turboprop and Turboshaft Engines." In Powered Flight. Springer London, 2012. http://dx.doi.org/10.1007/978-1-4471-2485-6_8.

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El-Sayed, Ahmed F. "Shaft Engines Turboprop, Turboshaft, and Propfan." In Fundamentals of Aircraft and Rocket Propulsion. Springer London, 2016. http://dx.doi.org/10.1007/978-1-4471-6796-9_7.

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Conference papers on the topic "Turboshaft engine"

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Carpentier, Pierre. "Turboshaft After-Market Positioning: A Strategy Based Approach." In Vertical Flight Society 70th Annual Forum & Technology Display. The Vertical Flight Society, 2014. http://dx.doi.org/10.4050/f-0070-2014-9615.

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Due to its subjective nature, the concept of value is not one that is easily defined. Marketers often refer to a product's 'value proposition' as an explanation to why an operator should buy a product or use a service. This statement should convince a potential operator that one particular product or service will add more value or better solve a problem than other similar offerings. In the rotorcraft market, this value proposition is often tied to capabilities of the helicopter and is typically defined as a composite metric. This metric is then compared to the acquisition cost to get a sense of helicopter value. Helicopter manufacturer's marketing and sales departments then go to the market and sell the benefits, either in range, take-off weight, reliability, operating cost, etc… One major difference in the value stream of rotorcraft products as compared to typical consumer products is that it is standard for a second-level supplier, in this case the engine manufacturer, to offer its own services and support. This creates an environment where both the helicopter and engine manufacturer have direct contact with the end operator and can influence their perception of value. A method for an engine manufacturer to define value can aid the helicopter manufacturer, and ultimately, the operator, to make an informed decision regarding the right product for their mission objectives. In order to derive a metric for the concept of value for a helicopter engine, one must understand the important aspects from an operational perspective, as opposed to the technical focus typically associated to this type of product. This paper focuses on the derivation of such a composite metric by using terms that represent a product's reliability, maintainability, and capability as compared to its direct operating cost as the acquisition cost of the engine is transparent to the end operator. Looking at the helicopter engine competitive environment in such a way serves two purposes: one for the engine manufacturer to be able to gauge the competitiveness of their product, and one for the operators to understand an engine's value proposition and how it fits into the helicopter capabilities. The details of how the metric of engine productivity were derived will not be elaborated as they are considered intellectual property to Pratt and Whitney Canada, but the benefits and concepts of viewing helicopter engines in such a way can be discussed.
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Soares, Alvaro, Brian LeFevre, Treven Baker, and Mark Davis. "Automated Power Assurance Refinement for a Turboshaft Engine." In Vertical Flight Society 71st Annual Forum & Technology Display. The Vertical Flight Society, 2015. http://dx.doi.org/10.4050/f-0071-2015-10244.

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Automated power assurance technology consists of a real-time software module which processes measurements collected by various sensors on an aircraft and calculates key characteristic engine parameters and performance limits which are used for maintenance and mission planning purposes. The technical effort undertaken as part of the Capability-Based Operations and Sustainment Technology-Aviation (COST-A) program, and described in this paper, sought to improve overall algorithm performance from the baseline established under past development programs and further advance the technology along the path to transition to use by the UH-60 BLACK HAWK fleet. After analysis of UH-60 HUMS data and other full-scale test data, all of the technical performance goals for automated power assurance were met. These goals included compensating for the use of customer (i.e., compressor) bleed air and other engine operating conditions while maintaining Engine Torque Factor (ETF) to within a specified tolerance from ground truth as established in a calibrated test cell. In addition, ETF repeatability was within the expected tolerance at a 3-sigma confidence level. Given the positive results that were obtained under COST-A, the next steps for the automated power assurance software include a flight test of the algorithm in Q3 2015, where the software will be embedded within the on-board system of an UH-60 aircraft. This test will further validate the technical performance of the algorithms and reduce integration risk, thus enabling a transition to production applications.
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Mayda, Anil, Emre Sancar, A. Daldal, et al. "Engine Installed Performance Testing Activities." In Vertical Flight Society 80th Annual Forum & Technology Display. The Vertical Flight Society, 2024. http://dx.doi.org/10.4050/f-0080-2024-1297.

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T-625 helicopter, created by the Turkish Aerospace Helicopter Group, serves as a light utility multi role helicopter. It is powered by a pair of CTS800-4AT turboshaft engines, which were developed by the Light Helicopter Turbine Engine Company (LHTEC). This paper presents aspects of performance characteristics for air intakes, exhaust system and engine vents in powerplant integration of the T-625 helicopter, together with the results of engine installed performance flight test campaign, which are performed to determine the engine installation losses.
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Martin, John, Gordon Alexander, Greg Duane, and Bennett Hlavac. "Modeling CT7/T700 Maintenance Costs." In Vertical Flight Society 71st Annual Forum & Technology Display. The Vertical Flight Society, 2015. http://dx.doi.org/10.4050/f-0071-2015-10234.

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Turboshaft engines are a significant contributor to rotary wing aircraft life cycle costs, typically over 40%. Maintenance costs are the largest portion of the life cycle cost of an engine, as compared to development, acquisition, and fuel costs. Understanding these costs is important to guiding engine design and maintenance practice decisions. This paper describes the development and use of deterministic and probabilistic simulation model of the CT7 commercial turboshaft engine and its application to US Army maintenance of a military version of the engine. The model is used on several commercial aircraft to quantify engine maintenance costs ($/EFH), time on wing (TOW), field maintenance labor hours, and required sparing. The application of this model to the US Army T700-GE-701D engine is described. Maintenance practices are analyzed to optimize readiness at best value. Engine design tradeoffs are evaluated based on overall Life Cycle Cost. The influence of operating environments is also addressed, such as accounting for the impact of harsh environments. Recommendations to reduce maintenance cost per hour are described.
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Mas, Lorenzo, Rita Ponza, and Ernesto Benini. "Assessment and Calibration of Semi-Empirical Models for Predicting Pollutant Emissions of the Erica Tiltrotor Turboshaft Engine." In Vertical Flight Society 70th Annual Forum & Technology Display. The Vertical Flight Society, 2014. http://dx.doi.org/10.4050/f-0070-2014-9622.

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In this paper, the most meaningful EINOx and EICO zero-dimensional emission prediction methods from the literature are described and reviewed, while a selection of them are tuned and validated against publicly available experimental data. The equations of these models are implemented in TSHAFT, a proprietary engine simulator developed at the University of Padova which predicts the performance of turbojet engines in both design and off-design operation modes under variable ambient conditions. Then, TSHAFT is set up to predict the emissions of a generic turboshaft engine ranging in power from 1,800 shp to over 5,000 shp, and the results are compared to proprietary experimental data obtained during an aircraft landing and take-off cycle (LTO) at standard sea level conditions. Finally, the emissions of a turboshaft engine of 3000 SHP engine are calculated for two flight conditions (i.e. hover and forward flight cruise) of the ERICA tiltrotor. Finally, the paper presents the results of the comparison in terms of pollutant emissions between the engine emissions related to the baseline installation geometry, and the optimized intake/exhaust configuration.
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Sancar, Emre, Abdurrahman Daldal, Taylan Çakiroğlu, Akay Bayat, and Ahmet Ezertaş. "Modeling Activities of Propulsion System Engine Installation Survey." In Vertical Flight Society 80th Annual Forum & Technology Display. The Vertical Flight Society, 2024. http://dx.doi.org/10.4050/f-0080-2024-1352.

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The multi-role utility helicopter T625 GÖKBEY is designed by Turkish Aerospace and it is equipped with a pair of two-spool CTS800-4AT turboshaft engine developed by Light Helicopter Turbine Engine Company (LHTEC). Components of the cowlings, intakes and exhausts were designed with supplementing CFD analyses and performance of various alternatives were evaluated. Final designs were achieved based on the helicopter performance and engine limits. In order to verify the estimated engine installed performance in design phase, performance of the instrumented engine with its integrated equipment on the platform is examined using flight test data. This paper focuses on the CFD simulations based performance predictions of the air induction system, exhaust system, and IPS blower exhaust. A comprehensive study is assessed to create more realistic models by using flight test data.
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Pyle, Terry, and Dan Aldrich. "Garrett’s Turboshaft Engines and Technologies for the 1990s." In ASME 1990 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1990. http://dx.doi.org/10.1115/90-gt-204.

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Garrett Engine Division of Allied-Signal Aerospace, Inc., which supplies small-to-medium size gas turbine propulsion engines to the fixed-wing aviation market, is expanding its product line to include the small-to-medium turboshaft engine for the rotary wing (helicopter) aviation market. The recent win of the T800-LHT-800 down-select formed a firm foundation for this expansion. Garrett is developing the T800 in a partnership with the Allison Gas Turbine Division of General Motors Corporation, under the company name of Light Helicopter Turbine Engine Company (LHTEC). The T800 turboshaft engine (1300-shp, 1000-kW class), which has superior performance in this power class (10 to 30 percent better specific fuel consumption and power-to-weight than current production turboshaft engines), is designed to power the U.S. Army’s LHX light attack helicopter. Garrett is pursuing complementary technologies focused on serving a full spectrum of turboshaft engine requirements for the 1990s and beyond. Garrett is also teamed with General Electric Aircraft Engines (GEAE), for the Joint Turbine Advanced Gas Generator (JTAGG) demonstrator program. JTAGG supports the Integrated High Performance Turbine Engine Technology (IHPTET) initiative of doubling propulsion system capabilities by the year 2003. New technologies incorporated in the T800, and emerging technologies and concepts applicable to future turboshafts, are discussed.
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Burguburu, Stephane, and Pierre-Marie Basset. "Turboshaft Engine Predesign and Performance Assessment." In 48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. American Institute of Aeronautics and Astronautics, 2012. http://dx.doi.org/10.2514/6.2012-3813.

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HIRSCHKRON, R., and C. RUSSO. "Small turboshaft/turboprop engine technology study." In 22nd Joint Propulsion Conference. American Institute of Aeronautics and Astronautics, 1986. http://dx.doi.org/10.2514/6.1986-1623.

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Anderson, William G., Sandra Hoff, Dave Winstanley, John Phillips, and Scott DelPorte. "Heat Pipe Cooling of Turboshaft Engines." In ASME 1993 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1993. http://dx.doi.org/10.1115/93-gt-220.

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Reduction in turbine engine cooling flows is required to meet the IHPTET Phase II engine performance levels. Heat pipes, which are devices with very high thermal conductance, can help reduce the required cooling air. A survey was conducted to identify potential applications for heat pipes in turboshaft engines. The applications for heat pipe cooling of turbine engine components included the power turbine first stage vanes, shroud, and case, the HP turbine vanes and shroud, and the T5 temperature probe. Other potential applications for heat pipe cooling include regenerative cycle and intercooling, bearing cooling, IR signature reduction, and active clearance control. Calculated performance benefits included an increase in specific shaft horsepower, and a decrease in specific fuel consumption, as determined with an IHPTET Phase II turboshaft engine performance model. For example, using heat pipes to cool the power turbine vanes, shroud, and case would increase the specific shaft horsepower by 6 percent, while decreasing the specific fuel consumption by 2.2 percent. While this study examined turboshaft engines, most of the applications are also applicable to turbofan engines.
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