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1
Pismennyi, V. L. "Bypass Turbojet Engines." Proceedings of Higher Educational Institutions. Маchine Building, no. 6 (711) (June 2019): 50–59. http://dx.doi.org/10.18698/0536-1044-2019-6-50-59.
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Subsonic bypass turbojet engines of the fifth generation have reached technical maturity, with overall efficiency of 35–38%. Without changing the thermodynamic cycle of the engine, any further work in this direction is futile. The researcher proposes a method of increasing the thermodynamic effectiveness of heat engines based on the so called internal thermodynamic cycles (Pismennyi cycles). The internal cycles possess remarkable characteristics: they increase the effective work output and the heat engine efficiency (thermal and effective); furthermore, they remove temperature restrictions. A gas dynamic design of a bypass turbojet engine is developed based on the internal thermodynamic cycle. Two heat exchangers (circulating and regenerating) are installed in the bypass duct, the first of which can increase the gas temperature before the fan to 2300 K and higher, while the second one can cool the exhaust temperature down to the level comparable to the air temperature behind the fan. Depending on the thrust, general efficiency of the engine in cruise mode (H = 11 km, M = 0.8) can reach 45–55 %. Compared to bypass turbojet engines of the fifth generation (Trent 1000, GP7270, PW4460, etc.), fuel savings with the new design are estimated to be more than 20 %. With the adoption of the proposed jet engine design the total economic impact for airlines can exceed $10 billion annually.
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Andoga, Rudolf, Ladislav Főző, Radovan Kovács, Károly Beneda, Tomáš Moravec, and Michal Schreiner. "Robust Control of Small Turbojet Engines." Machines 7, no. 1 (January 4, 2019): 3. http://dx.doi.org/10.3390/machines7010003.
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Modern turbojet engines mainly use computerized digital engine control systems. This opens the way for application of advanced algorithms aimed at increasing their operational efficiency and safety. The theory of robust control is a set of methods known for good results in complex control tasks, making them ideal candidates for application in the current turbojet engine control units. Different methodologies in the design of robust controllers, utilizing a small turbojet engine with variable exhaust nozzle designated as iSTC-21v, were therefore investigated in the article. The resulting controllers were evaluated for efficiency in laboratory conditions. The aim was to find a suitable approach and design method for robust controllers, taking into account the limitations and specifics of a real turbojet engine and its hardware, contrary to most studies which have used only simulated environments. The article shows the most effective approach in the design of robust controllers and the resulting speed controllers for a class of small turbojet engines, which can be applied in a discrete digital control environment.
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Улитенко, Юрий Александрович. "АНАЛИЗ ХАРАКТЕРИСТИК ТУРБОРЕАКТИВНОГО ДВУХКОНТУРНОГО ДВИГАТЕЛЯ С ФОРСАЖНОЙ КАМЕРОЙ СГОРАНИЯ С ВПРЫСКОМ ВОДЫ ЗА ВХОДНЫМ УСТРОЙСТВОМ." Aerospace technic and technology, no. 1 (March 7, 2019): 29–38. http://dx.doi.org/10.32620/aktt.2019.1.03.
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Development of perspective high-speed aircraft inseparably depends on the level of aircraft propulsion engineering as engine performances to determine aircraft capabilities as a whole. The basic requirements to engines of high-speed aircraft are increase speed and flight height. The new generation of turbojet bypass engine with afterburner each their specific thrust and a specific impulse increases, also the application of high technologies raises leads to substantial growth of the engine cost too. At the same time, existing engines design has big reserves for modernization. The system of water injection to the input at the turbojet bypass engine with afterburner is one of the accessible ways for design improvement. Those advanced engines theoretically will allow to satisfy requirements from designers of high-speed aircraft concerning to thrust and other key parameters, at the same time to secure continuity of already existing types of power-plants. The possibility of range extension of turbojet bypass engine with classical scheme afterburner operation till Mach number 3 is considered in this article. The analysis of existing developments is carried out. Impact of water injection to the input at turbojet bypass engine with afterburner on its performance is investigated. Results of calculations for the influence of water injection to reaction mass parameters on the engine duct and its thrust characteristics are proved. Received results will allow to increase thermodynamic efficiency and to expand range extension of turbojet bypass engine with afterburner provided to use materials that applied in aviation manufacture, as well as to reduce terms of development competitive engines for high-speed aircraft at the expense of purposeful search of their rational thermodynamic and is constructive-geometrical architecture.
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Ekinci, Sinan, and İlkay Yavrucuk. "Fast engine model for FMU-less small turbojet engines." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 234, no. 2 (August 5, 2019): 416–27. http://dx.doi.org/10.1177/0954410019867013.
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The focus of this paper is on small low-cost turbojet engines equipped with a gear-type fuel pump rather than a more traditional fuel metering unit. The incorporation of such type of fuel flow actuation devices introduce additional nonlinearities into the system and therefore make traditional modeling and system identification methods difficult to apply. In this paper, we propose a nonlinear fast engine model structure that can be used for various applications, including identification, modeling and simulation, and controller design of such sub-class turbojet engines. A high-fidelity turbojet engine model including its nonlinear gear-type fuel pump is developed, which is later used to generate the fast engine model. The parameters of the fast engine model are estimated using regression analysis. The identification procedure is also applied to real engine test data to verify the proposed approach.
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Derbel, Khaoula, and Károly Beneda. "LINEAR DYNAMIC MATHEMATICAL MODEL AND IDENTIFICATION OF MICRO TURBOJET ENGINE FOR TURBOFAN POWER RATIO CONTROL." Aviation 23, no. 2 (December 18, 2019): 54–64. http://dx.doi.org/10.3846/aviation.2019.11653.
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Micro turbojets can be used for propulsion of civilian and military aircraft, consequently their investigation and control is essential. Although these power plants exhibit nonlinear behaviour, their control can be based on linearized mathematical models in a narrow neighbourhood of a selected operating point and can be extended by using robust control laws like H∞ or Linear Quadratic Integrating (LQI). The primary aim of the present paper is to develop a novel parametric linear mathematical model based on state space representation for micro turbojet engines and the thrust parameter being Turbofan Power Ratio (TPR). This parameter is used by recent Rolls-Royce commercial turbofan engines but can be applied for single stream turbojet power plants as well, as it has been proven by the authors previously. An additional goal is to perform the identification for a particular type based on measurements of a real engine. This model has been found suitable for automatic control of the selected engine with respect of TPR, this has been validated by simulations conducted in MATLAB® Simulink® environment using acquired data from transient operational modes.
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Meher-Homji, Cyrus B., and Erik Prisell. "Pioneering Turbojet Developments of Dr. Hans Von Ohain—From the HeS 1 to the HeS 011." Journal of Engineering for Gas Turbines and Power 122, no. 2 (January 3, 2000): 191–201. http://dx.doi.org/10.1115/1.483194.
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On March 13, 1998, Dr. Hans Joachim Pabst von Ohain, co-inventor of the turbojet, passed away at the age of 86. As a young doctoral student, von Ohain conceived of and built a demonstrator turbojet engine. He was hired by the Heinkel Aircraft Company in 1936 and under intense time pressure imposed by Ernst Heinkel, designed the world’s first flight turbojet engine. This paper traces the technical antecedents leading to historic jet-powered flight made on August 27, 1939 by a Heinkel He 178 aircraft powered by von Ohain’s HeS 3B turbojet. During his tenure at Heinkel and thereafter at the Heinkel-Hirth Company, he was responsible for a series of turbojet engines culminating in the advanced second generation HeS 011 with a thrust of 2860 lbs. This paper is a tribute to an outstanding scientist who made possible the turbojet revolution and who will forever be remembered as the inventor of the world’s first flight turbojet. [S0742-4795(00)02102-5]
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Kuznetsov, V. I., and D. D. Shpakovsky. "Methodology for estimating the specific fuel consumption of a two-circuit turbojet engine." Journal of «Almaz – Antey» Air and Defence Corporation, no. 2 (July 19, 2020): 93–102. http://dx.doi.org/10.38013/2542-0542-2020-2-93-102.
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A technique was developed for determining the minimum specific fuel consumption of a two-circuit turbojet engine using statistical data on the polytropic efficiency of individual compressor and turbine stages. The proposed method allows the presence of a technological advantage in specific fuel consumption compared to similar engines to be identified at the initial stage of designing a two-circuit turbojet engine.
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Andoga, Rudolf, Ladislav Főző, Martin Schrötter, Marek Češkovič, Stanislav Szabo, Róbert Bréda, and Michal Schreiner. "Intelligent Thermal Imaging-Based Diagnostics of Turbojet Engines." Applied Sciences 9, no. 11 (May 31, 2019): 2253. http://dx.doi.org/10.3390/app9112253.
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There are only a few applications of infrared thermal imaging in aviation. In the area of turbojet engines, infrared imaging has been used to detect temperature field anomalies in order to identify structural defects in the materials of engine casings or other engine parts. In aviation applications, the evaluation of infrared images is usually performed manually by an expert. This paper deals with the design of an automatic intelligent system which evaluates the technical state and diagnoses a turbojet engine during its operation based on infrared thermal (IRT) images. A hybrid system interconnecting a self-organizing feature map and an expert system is designed for this purpose. A Kohonen neural network (the self-organizing feature map) is successfully applied to segment IRT images of a turbojet engine with high precision, and the expert system is then used to create diagnostic information from the segmented images. This paper represents a proof of concept of this hybrid system using data from a small iSTC-21v turbojet engine operating in laboratory conditions.
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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 (April 30, 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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Iwata, Kakuya, Koji Matsubara, Kazumasa Kawasaki, and Osamu Matsumoto. "Turbojet Engine for Aerial Cargo Robot (ACR)." Journal of Robotics and Mechatronics 24, no. 6 (December 20, 2012): 1040–45. http://dx.doi.org/10.20965/jrm.2012.p1040.
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Turbine engines have been used as high reliable, safe engines in airline transportation. Safety is the most important factor in the social use of aerial robots. We started research on Aerial Cargo Robots (ACR) in 2004. The first flight of an ACR prototype was successfully achieved on November 22, 2005. The ACR prototype consists of a flexible airfoil, twin micro-turbo-jet engines and a gravity center control unit. The ACR meets the following requirements for safety: touchable, i.e., without propellers or rotors; a low sink rate the same as a parachute, i.e., below 1.0 m/sec; a low stall speed, i.e., less than 30 km/h; and a redundancy arrangement control system. The most important safety specification is the use of a silent turbojet engine for the ACR thruster. This paper reports the results of turbojet engine development for aerial robots.
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OKELAH, M. "THE CO-TURBOJET ENGINE: A NOVEL CONCEPT FOR MILTI-SPOOL TURBOJET ENGINES." International Conference on Aerospace Sciences and Aviation Technology 1, CONFERENCE (May 1, 1985): 1–10. http://dx.doi.org/10.21608/asat.1985.26520.
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Andoga, Rudolf, Ladislav Főző, Jozef Judičák, Róbert Bréda, Stanislav Szabo, Róbert Rozenberg, and Milan Džunda. "Intelligent Situational Control of Small Turbojet Engines." International Journal of Aerospace Engineering 2018 (June 26, 2018): 1–16. http://dx.doi.org/10.1155/2018/8328792.
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Improvements in reliability, safety, and operational efficiency of aeroengines can be brought in a cost-effective way using advanced control concepts, thus requiring only software updates of their digital control systems. The article presents a comprehensive approach in modular control system design suitable for small gas turbine engines. The control system is based on the methodology of situational control; this means control of the engine under all operational situations including atypical ones, also integrating a diagnostic system, which is usually a separate module. The resulting concept has been evaluated in real-world laboratory conditions using a unique design of small turbojet engine iSTC-21v as well as a state-of-the-art small turbojet engine TJ-100. Our results show that such advanced control system can bring operational quality of an engine with old turbocompressor core iSTC-21v on par with state-of-the-art engines.
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Andoga, Rudolf, Ladislav Főző, Martin Schrötter, and Stanislav Szabo. "The Use of Ethanol as an Alternative Fuel for Small Turbojet Engines." Sustainability 13, no. 5 (February 26, 2021): 2541. http://dx.doi.org/10.3390/su13052541.
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The use of alternative fuels to traditional kerosene-based ones in turbo-jet engines is currently being widely explored and researched. However, the application of alternative fuels in the area of small turbojet engines with thrust ratings up to 2 kilo-newtons, which are used as auxiliary power units or to propel small aircraft or drones, is not as well researched. This paper explores the use of ethanol as a sustainable fuel and its effects on the operation of a small turbojet engine under laboratory conditions. Several concentrations of ethanol and JET A-1 mixtures are explored to study the effects of this fuel on the basic parameters of a small turbojet engine. The influence of the different concentrations of the mixture on the start-up process, speed of the engine, exhaust gas temperature, and compressor pressure are evaluated. The measurements shown in the article represent a pilot study, the results of which show that ethanol can be reliably used as an alternative fuel only when its concentration in a mixture with traditional fuel is lower than 40%, yielding positive effects on the operating temperatures and small negative effects on the speed or thrust of the engine.
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Ahmed, Heersh, and Boris Osipov. "MULTI-MODE IDENTIFICATION OF OBTAINING THE ADEQUATE MODEL OF TURBOJET ENGINE TJ-100A-Z FOR DIAGNOSTICS BY THERMALGASDYNAMIC PARAMETERS." Perm National Research Polytechnic University Aerospace Engineering Bulletin, no. 60 (2020): 5–14. http://dx.doi.org/10.15593/2224-9982/2020.60.01.
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When monitoring and diagnosing the state of gas turbine engines by thermodynamic parameters, adequate mathematical models of these engines are used. This name means diagnostic methods based on special processing and analysis of the values of thermogasdynamic and other parameters measured on a working turbojet engine [1] using its mathematical model. The most important in the system of technical diagnostics is the mathematical model of the engine. Its creation is a problem since, as a rule, the specifications of engine components are not given in the technical documentation. In this regard, obtaining complete mathematical models of engines for diagnostic purposes is an urgent task. There are various approaches to obtaining the characteristics of nodes and one of them is the use of generalized characteristics, for example, developed at the N.E. Zhukovsky Air Force Engineering Academy at the Department 201 "Theory of Air-Jet Engines" under the direction of Professor Nechayev Yu.N. Experience using such characteristics has shown that such characteristics can be used, but in a fairly narrow range of throttle modes. As a rule, this range was limited to no more than 40 % of the calculated (nominal) mode, which significantly limits the capabilities of the mathematical model of turbojet engines when implementing diagnostics using thermodynamic and dynamic parameters. This article proposes an algorithm developed by the authors a lot of mode identification, implemented as a computer program. As an object of study used turbojet engine TJ-100A-Z manufactured in the Czech Republic. For this, the turbojet engine obtained the characteristics of the main components (compressor, combustion chamber, turbine and nozzle) using the throttle characteristics given in the technical conditions. The calculation results are presented in the form of tables and graphs with error analysis in the calculation before and after identification. The comparison of the errors of the parameters of the throttle characteristics with the errors of the sensors for measuring these parameters is given.
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Şöhret, Yasin. "ECOLOGIC PERFORMANCE AND SUSTAINABILITY EVALUATION OF A TURBOJET ENGINE UNDER ON-DESIGN CONDITIONS." Aviation 22, no. 4 (December 14, 2018): 166–73. http://dx.doi.org/10.3846/aviation.2018.7085.
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Interest in air transportation in the last decade has seen aviation fleet growth and a rise in the energy consumption of aircraft. In accordance with the latest data, the air transportation sector consumes 7.5% of total oil consumption worldwide. This high share by air transportation forces designers and researchers to develop more efficient propulsion systems by considering the constant rise in energy costs. In the current paper, an exergy based sustainability assessment of a turbojet engine under design point conditions is presented while two novel ecological performance indicators, namely the ecological objective function and ecological coefficient of performance, are introduced for the turbojet engine. These ecological performance indicators can be considered useful for improving the efficiency of any turbojet engine. As a result of an exemplifying analysis, the exergy efficiency, exergy sustainability index, ecological objective function and ecological coefficient of performance have been calculated to be 50.13%, 0.503, 68.294 kW and 1.005, respectively. In the light of the results, the author concludes that the exergy destruction rate of the turbojet engine should be minimized to improve the sustainability index and ecological coefficient of performance, while increasing or maintaining a constant thrust of the examined turbojet engine.
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Işık, Gültekin, Selçuk Ekici, and Gökhan Şahin. "A neural network model for UAV propulsion system." Aircraft Engineering and Aerospace Technology 92, no. 8 (July 14, 2020): 1177–84. http://dx.doi.org/10.1108/aeat-04-2020-0064.
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Purpose Determining the performance parameters of the propulsion systems of the aircraft, which is the key product of the aviation industry, plays a critical role in reducing adverse environmental impacts. Therefore, the purpose of this paper is to present a temperature performance template for turbojet engines at the design stage using a neural network model that defines the relationship between the performance parameters obtained from ground tests of a turbojet engine used in unmanned aerial vehicles (UAV). Design/methodology/approach The main parameters of the flow passing through the engine of the UAV propulsion system, where ground tests were performed, were obtained through the data acquisition system and injected into a neural network model created. Fifteen sensors were mounted on the engine – six temperature sensors, six pressure sensors, two flow meters and one load cell were connected to the data acquisition system to make sense of this physical environment. Subsequently, the artificial neural network (ANN) model as a complement to the approach was used. Thus, the predicted model relationship with the experimental data was created. Findings Fuel flow and thrust parameters were estimated using these components as inputs in the feed-forward neural network. In the network experiments to estimate fuel flow parameter, r-square and mean absolute error were calculated as 0.994 and 0.02, respectively. Similarly, for thrust parameter, these metrics were calculated as 0.994 and 1.42, respectively. In addition, the correlation between fuel flow, thrust parameters and each input parameters was examined. According to this, air compressor inlet (ACinlet,temp) and outlet (ACoutlet,temp) temperatures and combustion chamber (CCinlet,temp, CCoutlet,temp) temperature parameters were determined to affect the output the most. The proposed ANN model is applicable to any turbojet engines to model its behavior. Practical implications Today, deep neural networks are the driving force of artificial intelligence studies. In this study, the behavior of a UAV is modeled with neural networks. Neural networks are used here as a regressor. A neural network model has been developed that predicts fuel flow and thrust parameters using the real parameters of a UAV turbojet engine. As a result, satisfactory findings were obtained. In this regard, fuel flow and thrust values of any turbojet engine can be estimated using the neural network hyperparameters proposed in this study. Python codes of the study can be accessed from https://github.com/tekinonlayn/turbojet. Originality/value The originality of the study is that it reports the relationships between turbojet engine performance parameters obtained from ground tests using the neural network application with open source Python code. Thus, small-scale unmanned aerial propulsion system provides designers with a template showing the relationship between engine performance parameters.
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Kowalski, Mirosław, and Wojciech Kotlarz. "The Advantages of Using a Bleed of Air from Behind the Compressor and Supplying It Behind the Turbine in an Aircraft Engine." Journal of KONBiN 50, no. 3 (October 1, 2020): 381–94. http://dx.doi.org/10.2478/jok-2020-0067.
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AbstractThe research paper discusses the advantages of using compressor downstream air partial bleed and supplying it downstream of the turbine, which was applied in a prototype of a “bypass” turbojet engine. The impact of such a solution on the value of achieved basic operating parameters of the engine was described, i.e., unit thrust and unit power consumption. The presented attempt to compare these parameters with the parameters achieved for a turbojet, single flow engine is very important; in the first case without air bleed, and in the second, with air bleed to the environment and with the parameters of a turbojet, turbofan engine with a jet mixer.
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Ehyaei, M. A., A. Anjiridezfuli, and M. A. Rosen. "Exergetic analysis of an aircraft turbojet engine with an afterburner." Thermal Science 17, no. 4 (2013): 1181–94. http://dx.doi.org/10.2298/tsci110911043e.
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An exergy analysis is reported of a J85-GE-21 turbojet engine and its components for two altitudes: sea level and 11,000 meters. The turbojet engine with afterburning operates on the Brayton cycle and includes six main parts: diffuser, compressor, combustion chamber, turbine, afterburner and nozzle. Aircraft data are utilized in the analysis with simulation data. The highest component exergy efficiency at sea level is observed to be for the compressor, at 96.7%, followed by the nozzle and turbine with exergy efficiencies of 93.7 and 92.3%, respectively. At both considered heights, reducing of engine intake air speed leads to a reduction in the exergy efficiencies of all engine components and overall engine. The exergy efficiency of the turbojet engine is found to decrease by 0.45% for every 1?C increase in inlet air temperature.
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Way, S. "Comments on the Development of the Early Westinghouse Turbojets, 1941-1946." Journal of Engineering for Gas Turbines and Power 116, no. 2 (April 1, 1994): 315–21. http://dx.doi.org/10.1115/1.2906822.
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The early thinking leading to the American Turbojet engine is reviewed. This included ideas pertaining to ramjets and rockets, and culminated in the axial flow turbojet engine concept. The role of the NACA Subcommittee on Jet Propulsion under the leadership of Dr. W. F. Durand is stressed. Early problems with the new engine are mentioned, including flame tube light-off, interconnecting tubes, and fuel injection problems. An early major design innovation was the change to a single annular combustion chamber, replacing the 24 cans. This change culminated in the 19XB engine. The purposes of this paper are to show the magnitude of the problems encountered, and to give credit to the many dedicated persons who made the American Axial Flow Turbojet Engine a success.
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Derbel, Khaoula, and Károly Beneda. "Sliding Mode Control for Micro Turbojet Engine Using Turbofan Power Ratio as Control Law." Energies 13, no. 18 (September 16, 2020): 4841. http://dx.doi.org/10.3390/en13184841.
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The interest in turbojet engines was emerging in the past years due to their simplicity. The purpose of this article is to investigate sliding mode control (SMC) for a micro turbojet engine based on an unconventional compound thermodynamic parameter called Turbofan Power Ratio (TPR) and prove its advantage over traditional linear methods and thrust parameters. Based on previous research by the authors, TPR can be applied to single stream turbojet engines as it varies proportionally to thrust, thus it is suitable as control law. The turbojet is modeled by a linear, parameter-varying structure, and variable structure sliding mode control has been selected to control the system, as it offers excellent disturbance rejection and provides robustness against discrepancies between mathematical model and real plant as well. Both model and control system have been created in MATLAB® Simulink®, data from real measurement have been taken to evaluate control system performance. The same assessment is conducted with conventional Proportional-Integral-Derivative (PID) controllers and showed the superiority of SMC, furthermore TPR computation using turbine discharge temperature was proven. Based on the results of the simulation, a controller layout is proposed and its feasibility is investigated. The utilization of TPR results in more accurate thrust output, meanwhile it allows better insight into the thermodynamic process of the engine, hence it carries an additional diagnostic possibility.
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Akçay, Ismail Hakki Hakkı, Habib Gürbüz, Hüsameddin Akçay, and Mustafa Aldemir. "An investigation of euro diesel-hydrogen dual-fuel combustion at different speeds in a small turbojet engine." Aircraft Engineering and Aerospace Technology 93, no. 4 (June 7, 2021): 701–10. http://dx.doi.org/10.1108/aeat-10-2020-0235.
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Purpose This study seeks the effect on static thrust, thrust specific energy consumption (TSEC) and exhaust emissions of euro diesel-hydrogen dual-fuel combustion in a small turbojet engine. Design/methodology/approach Experimental studies are performed in a JetCat P80-SE type small turbojet engine. Euro diesel and hydrogen is fed through two different inlets in a common rail distributing fuel to the nozzles. Euro diesel fuel is fed by a liquid fuel pump to the engine, while hydrogen is fed by a fuel-line with a pressure of 5 bars from a gas cylinder with a pressure of approximately 200 bars. Findings At different engine speeds, it is found that there is a decrease at the TSEC between a range of 1% and 4.8% by different hydrogen energy fractions (HEF). Research limitations/implications The amount of hydrogen is adjusted corresponding to a range of 0–20% of the total heat energy of the euro diesel and hydrogen fuels. The small turbojet engine is operated between a range of 35,000 and 95,000 rpm engine speeds. Practical implications On the other hand, remarkable improvements in exhaust emissions (i.e. CO, CO2, HC and NOx) are observed with HEFs. Originality/value This is through providing improvements in performance and exhaust emissions using hydrogen as an alternative to conventional jet fuel in gas turbine engines.
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Huang, Jingjing, and Longxi Zheng. "Noise analysis of the turbojet and turbofan engine tests." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 228, no. 13 (December 23, 2013): 2414–23. http://dx.doi.org/10.1177/0954410013518035.
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Aerogine noise leads to environment pollution largely when aerogine is tested. In this paper, the power spectrum analysis method of the aeroengine test noise was discussed, and the noise measurement and analysis experiments of a turbojet engine and a turbofan engine tests were carried out. The noise level, main noise resource, and noise characteristics of the two turbojet and turbofan engines were analyzed. Meanwhile, the indoor noise and far-field noise of the turbojet engine were both measured, the noise spread characteristics were analyzed and the noise reduction performance of the test bench was evaluated. The noise generated by the turbojet engine test had the discrete characteristic of high frequency. The higher frequencies when peak values occurred were the blade passage frequencies and the noises with lower frequencies were the broad band noises, especially the jet noise, and the maximum of the peak values occurred at the basic frequencies or harmonic frequencies of the compressor. Meanwhile, the noises generated by the turbofan engine, focused on the high frequencies and the peak values corresponded to the rotation noise of the fan blades. The experimental results were consistent with the theory basically, which indicated that the aeroengine operating status information could be identified by the noise power spectrum analysis. In addition to the aeroengine noise reduction research, the noise power spectrum analysis could also be used to diagnose the fault of the aeroengine structure and performance. On the other hand, the indoor and far-field noise measurement experimental results implied that the noise was suppressed from 136 dB to 85 dB and could provide the reference to the noise reduction design of the aeroengine test bench.
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Gusarov, Sergey Alexandrovich, Vladimir Nikolaevich Karasev, Yuri Alexandrovich Kostikov, Yuri Alexandrovich Rzhavin, and Aleksandr Mikhailovich Romanenkov. "DEVELOPMENT OF SOFTWARE FOR CALCULATION AND MATHEMATICAL MODELING OF THE FLOW PARTS OF TURBOJET ENGINE." Computational nanotechnology 6, no. 2 (June 30, 2019): 53–56. http://dx.doi.org/10.33693/2313-223x-2019-6-2-53-56.
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To date, the turbojet dual-circuit engine (turbojet) is the most common air-jet aircraft engine due to low fuel consumption and a number of other advantages. The purpose of this work is to develop a software package for calculating the parameters of the flow part of the turbojet with an intuitive and user-friendly modern interface that allows further expansion of the functionality due to the modular architecture. The developed software package is allowed to raise the process of designing the flow part of the turbojet to a higher level, thereby reducing not only the time of its development, but also the costs.
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GAWRON, Bartosz, and Tomasz BIAŁECKI. "Measurement of exhaust gas emissions from miniature turbojet engine." Combustion Engines 167, no. 4 (October 1, 2016): 58–63. http://dx.doi.org/10.19206/ce-2016-406.
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This paper presents a methodology developed to measure exhaust gas emissions during operation of a miniature turbojet engine, using a laboratory test rig. The rig has been built for research and development works aimed at modelling and investigating processes and phenomena occurring in jet engines. The miniature jet engines, similarly to full–scale ones used commonly in air transport, are characterized by variable exhaust gas emissions, depending on engine operating parameters. For this reason, an attempt has been made to determine the characteristic features of miniature engine operation modes and to define the variability of operation parameters and exhaust gas emissions as a function of time. According to the authors, the preliminary tests allowed for defining specific profile of engine test, which enables proper measurement regarding exhaust gas emissions using the miniature jet engine. The paper also presents test results for Jet A-1 fuel, according to the used methodology.
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Ekici, Selcuk, Yasin Sohret, Kahraman Coban, Onder Altuntas, and T. Hikmet Karakoc. "Sustainability Metrics of a Small Scale Turbojet Engine." International Journal of Turbo & Jet-Engines 35, no. 2 (May 25, 2018): 113–19. http://dx.doi.org/10.1515/tjj-2016-0036.
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Abstract Over the last decade, sustainable energy consumption has attracted the attention of scientists and researchers. The current paper presents sustainability indicators of a small scale turbojet engine, operated on micro-aerial vehicles, for discussion of the sustainable development of the aviation industry from a different perspective. Experimental data was obtained from an engine at full power load and utilized to conduct an exergy-based sustainability analysis. Exergy efficiency, waste exergy ratio, recoverable exergy ratio, environmental effect factor, exergy destruction factor and exergetic sustainability index are evaluated as exergetic sustainability indicators of the turbojet engine under investigation in the current study. The exergy efficiency of the small scale turbojet engine is calculated as 27.25 % whereas the waste exergy ratio, the exergy destruction factor and the sustainability index of the engine are found to be 0.9756, 0.5466 and 0.2793, respectively.
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Calmon, J. "From Sir Frank Whittle to the year 2000 — what is new in propulsion?" Aeronautical Journal 92, no. 920 (December 1988): 397–408. http://dx.doi.org/10.1017/s0001924000016535.
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It is with great admiration and much humility that I am able to give this talk in front of Sir Frank Whittle, universally recognised as the genuine pioneer of turbojet propulsion in the formula that made a success of aviation. As a matter of fact, the patent request filed by Sir Frank Whittle in 1930 (Fig. 1) comprised all the components of today’s turbojets: multi-stage axial compressor followed by a centrifugal compressor, combustion chamber, turbine coupled direct to the compressor and propulsion nozzle. In April 1937, with the assistance of British Thomson Houston, Sir Frank Whittle ran his first turbojet on the bench at a thrust of 200 daN (Fig. 2). The year after saw the beginning of the Whittle Wl turbojet tests at a thrust of 380 daN. This engine was to receive consecration by a first flight in May 1941 in a Gloster E28/39 specially built for the purpose. Subsequently, this aircraft was fitted with a 650 daN version incorporating an air cooled turbine.
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Mahulikar, S. P., S. K. Sane, U. N. Gaitonde, and A. G. Marathe. "Numerical studies of infrared signature levels of complete aircraft." Aeronautical Journal 105, no. 1046 (April 2001): 185–92. http://dx.doi.org/10.1017/s0001924000025422.
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Abstract This paper begins with an outline of the procedure for predicting the infrared signature emissions from the airframe, engine casing, and the plume, and their attenuation by the intervening atmosphere. These emissions are contrasted against the background, to obtain the infrared signature levels. The infrared detector’s — noise equivalent flux density, is proposed as an operational constraint on the flight envelope. The shift of this newly imposed constraint on the flight envelope for several engine-operating conditions, and for turbojet and turbofan engines is studied. The signature levels from the casing and plume, of a turbofan and equivalent turbojet engine, are compared at different operating points on the flight envelope. Result in the form of a polar plot of infrared signature level variation with aspect is also examined for low flying missions. The results are analysed to direct stealth design and operation.
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Tkachenko, Andrey, Evgeny Filinovaroslav Ostapyuk, Viktor Rybakov, and Daria Kolmakova. "Thermodynamic designing of the small-scale gas turbine engine family with common core." MATEC Web of Conferences 220 (2018): 03007. http://dx.doi.org/10.1051/matecconf/201822003007.
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The paper describes the method of selecting the working process parameters of a family of small-scale gas turbine engines (GTE) with common core. As an example, the thermodynamic design of a family of small-scale gas turbine engines (SGTE) with common core was carried out. The engine family includes a small-scale turbojet engine (STJE) and a gas turbine plant (GTP), which electric generator is driven by power turbine. The selection of rational values for the working process parameters of STJE and GTP was carried out in CAE system ASTRA on the basis of nonlinear optimization of these parameters, taking into account functional and parametric constraints. The quantitative results of deterioration in the performance of the engines of the family with common core are obtained in comparison with the engines with the optimum core for each type. However, the advanced creation of a common core can reduce the cost and timing of the engine creation, ensure its higher reliability (due to the development of the base common core) and reduce the cost of its production. The method of selecting the parameters of the working process of the GTE family with common core presents the solution to more complex problems, such as the possibility of developing a family consisting of five engines: a turbojet engine, turbofan engine, turbofan engine with a complex cycle, GTE with power turbine (GTE-PT), GTE-PT with recovery.
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Turan, Onder, and T. Hikmet Karakoc. "Exergetic and Energetic Response Surfaces for Small Turbojet Engine." Applied Mechanics and Materials 110-116 (October 2011): 1054–58. http://dx.doi.org/10.4028/www.scientific.net/amm.110-116.1054.
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Exergy analysis permits meaningful efficiencies to be evaluated for a system or process, and the sources, causes and locations of thermodynamic losses to be determined. This study presents exergetic modeling of a small turbojet engine via exergetic response surfaces. Turbojet engine consists of an inlet, a centrifugal compressor, reverse flow combustion chamber, axial-flow turbine and exhaust nozzle. The flight Mach number and altitude are examined on the exergetic efficiencies of total engine performance. The results of analysis are given as three dimensional exergetic response surface plots related to these operating parameters.
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Yuksel, Burak, Ozgur Balli, Huseyin Gunerhan, and Arif Hepbasli. "Comparative Performance Metric Assessment of A Military Turbojet Engine Utilizing Hydrogen And Kerosene Fuels Through Advanced Exergy Analysis Method." Energies 13, no. 5 (March 5, 2020): 1205. http://dx.doi.org/10.3390/en13051205.
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This study dealt with evaluating the (J85-GE-5H) military turbojet engine (TJE) in terms of exergetic and advanced exergetic analyses at Military (MIL) and Afterburner (AB) process modes by utilizing kerosene (JP-8) and hydrogen (H2) fuels. First, exergy and advanced exergy analyses of the engine were performed using JP-8 fuel as per actual engine operating conditions. These analyses of the turbojet engine using hydrogen fuel were also examined parametrically. The performance evaluation of the engine was lastly executed by comparing the obtained results for both fuels. Based on the parametric studies undertaken, the entire engine’s exergetic efficiency with JP-8 was reckoned 30.85% at the MIL process mode while it was calculated as 16.98% at the AB process mode. With the usage of H2, the efficiencies of the engine decreased to 28.62% and 15.33% for the above mentioned two modes, respectively. As the supreme exergy destructions occurred in the combustion chamber (CC) and afterburner exhaust duct (ABED) segments, the new technological developments should be considered to design more efficient engines. As a result, the engine worked less efficiently with hydrogen fuel due to the enhancement in exergy destructions. Conversely, the greenhouse gas (GHG) emission parameters lessened with the utilization of H2 fuel.
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Dunn, M. G., C. Padova, J. E. Moller, and R. M. Adams. "Performance Deterioration of a Turbofan and a Turbojet Engine Upon Exposure to a Dust Environment." Journal of Engineering for Gas Turbines and Power 109, no. 3 (July 1, 1987): 336–43. http://dx.doi.org/10.1115/1.3240045.
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Results are reported for a measurement program designed to investigate the performance deterioration of a TF33 turbofan and a J57 turbojet engine upon exposure to a dust-laden environment. Engine parameters were measured in order to facilitate the recognition of incipient engine difficulties. In addition, a successful effort was made to operate the engines satisfactorily when they were severely damaged. Two TF33 engines have been operated in the same dust mixture but under different operating conditions and a J57 engine was operated at the same conditions as one of the TF33 engines. The JS7 is the core engine of the TF33 with some differences that will be described in the paper. A description of the experimental technique, the operating experiences, photographs of the components taken from the J57 engine in a post-test teardown, and a discussion of the results are presented.
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Cican, Grigore, Marius Deaconu, Radu Mirea, and Andrei Tiberiu Cucuruz. "Influence of Bioethanol Blends on Performances of a Micro Turbojet Engine." Revista de Chimie 71, no. 5 (May 29, 2020): 229–38. http://dx.doi.org/10.37358/rc.20.5.8131.
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This paper proposes a study regarding the use of bioethanol as fuel for turbine engines used in aviation. For this purpose, three blends of 5, 10, and 15% concentrations of bioethanol mixed with Jet A fuel were tested on JET CAT P80 microturbo engine. During the engine testing, the following parameters were monitored: engine speed, generated force, temperature in front of the turbine, fuel volumetric flow rate, and vibration levels measured both on axial and radial direction. The tests were performed by maintaining the microturbo engine for about 1 min at three operating regimes: idle, cruise, and maximum speed. In addition, a comparative analysis between fuels for a test with the microturbo engine from the idle position to maximum position is presented. After the tests were conducted, a jet engine cycle analysis was performed at the max regime and the fuel specific consumption, the efficiency of the combustion chamber, and the thermal efficiency of the engine for each fuel blend were calculated. The tests were made without making any modifications to the engine components or automation system.
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Jafari, Soheil, and Theoklis Nikolaidis. "Turbojet Engine Industrial Min–Max Controller Performance Improvement Using Fuzzy Norms." Electronics 7, no. 11 (November 11, 2018): 314. http://dx.doi.org/10.3390/electronics7110314.
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The Min–Max control strategy is the most widely used control algorithm for gas turbine engines. This strategy uses minimum and maximum mathematical functions to select the winner of different transient engine control loops at any instantaneous time. This paper examines the potential of using fuzzy T and S norms in Min–Max selection strategy to improve the performance of the controller and the gas turbine engine dynamic behavior. For this purpose, different union and intersection fuzzy norms are used in control strategy instead of using minimum and maximum functions to investigate the impact of this idea in gas turbine engines controller design and optimization. A turbojet engine with an industrial Min–Max control strategy including steady-state and transient control loops is selected as the case study. Different T and S norms including standard, bounded, Einstein, algebraic, and Hamacher norms are considered to be used in control strategy to select the best transient control loop for the engine. Performance indices are defined as pilot command tracking as well as the engine response time. The simulation results confirm that using Einstein and Hamacher norms in the Min–Max selection strategy could enhance the tracking capability and the response time to the pilot command respectively. The limitations of the proposed method are also discussed and potential solutions for dealing with these challenges are proposed. The methodological approach presented in this research could be considered for enhancement of control systems in different types of gas turbine engines from practical point of view.
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Huang, Jin-Quan, and Jian-Guo Sun. "Multivariable Adaptive Control Using Only Input and Output Measurements for Turbojet Engines." Journal of Engineering for Gas Turbines and Power 117, no. 2 (April 1, 1995): 314–19. http://dx.doi.org/10.1115/1.2814096.
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Current and future aircraft engines are increasingly relying upon the use of multivariable control approach for meeting advanced performance requirements. A multivariable model reference adaptive control (MRAC) scheme is proposed in this paper. The adaptation law is derived using only input and output (I/O) measurements. Simulation studies are performed for a two-spool turbojet engine. The satisfactory transient responses are obtained at different operating points from idle to maximum dry power within the flight envelope. These show insensitivity of the design to engine power level and flight condition. Simulation results also show high effectiveness of reducing interaction in multivariable systems with significant coupling. Using the multivariable MRAC controller, the engine acceleration time is reduced by about 19 percent in comparison with the conventional engine controller.
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Karakoc, T. Hikmet, and Onder Turan. "Exergetic Destruction Effects of Operating Conditions on the Turbojet Engine Components." Applied Mechanics and Materials 110-116 (October 2011): 2390–94. http://dx.doi.org/10.4028/www.scientific.net/amm.110-116.2390.
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The minimization of exergy destruction brings the design as closely as permissible to the theoretical limit. This study presents exergy destruction analysis of a turbojet engine for different flight Mach number and altitudes. Turbojet engine being considered consists of an inlet, a centrifugal compressor, reverse flow combustion chamber, axial-flow turbine and exhaust nozzle. The flight Mach number and altitude are examined on the exergetic destructions of compressor, combustion chamber, turbine and exhaust nozzle. The results of component-based destruction analysis are given as three dimensional exergetic-destruction response surface plots related to altitude and flight Mach number.
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Langston, Lee S. "Powering Out of Trouble." Mechanical Engineering 135, no. 12 (December 1, 2013): 36–41. http://dx.doi.org/10.1115/1.2013-dec-3.
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This article presents a study of Pratt & Whitney’s J58, till date the best and high-powered engine for manufacturing lessons required for the development of F35 Joint Strike Fighter. The J58 Blackbird engine is a variable cycle engine, a turbojet/ramjet combined-cycle engine. It is a conventional afterburning turbojet for take-off and transonic flight, and it approximates a ramjet during high-speed supersonic cruise. The power plant for the Blackbirds is a marvelous development on the part of Pratt & Whitney, as it is the only engine of its kind in the world. The noise and vibration from a J58 test was so great that it could rattle the side-view mirror off nearby cars. The engine was developed at an isolated research center in Florida. At take-off and low-speed flight, the J58 engine/afterburner provides most of the thrust. Both of the Blackbird’s twin nacelles contain an engine supersonic inlet, the J58 engine with its afterburner, and an exhaust ejector nozzle. All three components contribute to the Blackbird’s propulsive thrust in varying proportions, depending on flight speed.
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Large, James, and Apostolos Pesyridis. "Investigation of Micro Gas Turbine Systems for High Speed Long Loiter Tactical Unmanned Air Systems." Aerospace 6, no. 5 (May 14, 2019): 55. http://dx.doi.org/10.3390/aerospace6050055.
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In this study, the on-going research into the improvement of micro-gas turbine propulsion system performance and the suitability for its application as propulsion systems for small tactical UAVs (<600 kg) is investigated. The study is focused around the concept of converting existing micro turbojet engines into turbofans with the use of a continuously variable gearbox, thus maintaining a single spool configuration and relative design simplicity. This is an effort to reduce the initial engine development cost, whilst improving the propulsive performance. The BMT 120 KS micro turbojet engine is selected for the performance evaluation of the conversion process using the gas turbine performance software GasTurb13. The preliminary design of a matched low-pressure compressor (LPC) for the proposed engine is then performed using meanline calculation methods. According to the analysis that is carried out, an improvement in the converted micro gas turbine engine performance, in terms of thrust and specific fuel consumption is achieved. Furthermore, with the introduction of a CVT gearbox, the fan speed operation may be adjusted independently of the core, allowing an increased thrust generation or better fuel consumption. This therefore enables a wider gamut of operating conditions and enhances the performance and scope of the tactical UAV.
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TSURUNO, Seizo, Noboru KAGAWA, and Atsushi MATSUGUCHI. "Education of Gas Turbine Using Turbojet Engine." Proceedings of the Fluids engineering conference 2000 (2000): 285–86. http://dx.doi.org/10.1299/jsmefed.2000.285.
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Ragupathy, R., and R. K. Mishra. "Availability Analysis of a Military Turbojet Engine." Journal of Failure Analysis and Prevention 19, no. 3 (June 2019): 814–20. http://dx.doi.org/10.1007/s11668-019-00663-5.
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Sato, Tetsuya, Hideyuki Taguchi, Hiroaki Kobayashi, Takayuki Kojima, Katsuyoshi Fukiba, Daisaku Masaki, Keiichi Okai, Kazuhisa Fujita, Motoyuki Hongo, and Shujiro Sawai. "Development study of a precooled turbojet engine." Acta Astronautica 66, no. 7-8 (April 2010): 1169–76. http://dx.doi.org/10.1016/j.actaastro.2009.10.006.
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Meher-Homji, C. B. "The Development of the Junkers Jumo 004B—The World’s First Production Turbojet." Journal of Engineering for Gas Turbines and Power 119, no. 4 (October 1, 1997): 783–89. http://dx.doi.org/10.1115/1.2817055.
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This paper describes the pioneering work of Anselm Franz who, while working for the Junkers Engine company in Germany, designed and made operational the world’s first production jet engine, the Junkers Jumo 004, which was the powerplant for the formidable Messerschmitt ME 262 fighter. The paper covers the historical background of jet engine development in Germany during the Second World War and discusses design details of this remarkable axial flow, 1980 lb (900 kg) thrust engine. The development represented a historic achievement for Anselm Franz and his design team at Junkers. Approximately 6000 engines were built at the end of the Second World War in the face of acute shortages and damage to German industry. The Jumo was brought from conceptual design to production in a span of four years. Franz joined Avco Lycoming in 1952 and worked for 16 years. He retired as Vice President in 1968 after making prolific contributions to the development of several Lycoming engines including the T53, the T55, and the AGT-1500. Anselm Franz passed away at the age of 94 in Stratford, Connecticut. This paper is a modest tribute to a jet engine pioneer who, in spite of his extensive contributions to gas turbine technology, will always be remembered as the man who designed the world’s first production turbojet.
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Cican, Grigore, Marius Deaconu, and Daniel-Eugeniu Crunteanu. "Impact of Using Chevrons Nozzle on the Acoustics and Performances of a Micro Turbojet Engine." Applied Sciences 11, no. 11 (June 2, 2021): 5158. http://dx.doi.org/10.3390/app11115158.
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This paper presents a study regarding the noise reduction of the turbojet engine, in particular the jet noise of a micro turbojet engine. The results of the measurement campaign are presented followed by a performances analysis which is based on the measured data by the test bench. Within the tests, beside the baseline nozzle other two nozzles with chevrons were tested and evaluated. First type of nozzle is foreseen with eight triangular chevrons, the length of the chevrons being L = 10 percentages from the equivalent diameter and an immersion angle of I = 0 deg. For the second nozzle the length and the immersion angle were maintained, only the chevrons number were increased at 16. The micro turbojet engine has been tested at four different regimes of speed. The engine performances were monitored by measuring the fuel flow, the temperature in front of the turbine, the intake air flow, the compression ratio, the propulsion force and the temperature before the compressor. In addition, during the testing, the vibrations were measured on axial and radial direction which indicate a normal functioning of the engine during the chevron nozzles testing. Regarding the noise, it was concluded that at low regimes the noise doesn’t presents any reduction when using the chevron nozzles, while at high regimes an overall noise reduction of 2–3 dB(A) was achieved. Regarding the engine performances, a decrease in the temperature in front of the turbine, compression ratio and the intake air and fuel flow was achieved and also a drop of few percent of the propulsion force.
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Balli, Ozgur, Alper Dalkıran, and Tahir Hikmet Karakoç. "Energetic, exergetic, exergoeconomic, environmental (4E) and sustainability performances of an unmanned aerial vehicle micro turbojet engine." Aircraft Engineering and Aerospace Technology 93, no. 7 (August 20, 2021): 1254–75. http://dx.doi.org/10.1108/aeat-03-2021-0088.
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Purpose This study aims to investigate the aviation, energetic, exergetic, environmental, sustainability and exergoeconomic performances of a micro turbojet engine used in unmanned aerial vehicles at four different modes. Design/methodology/approach The engine data were collected from engine test cell. The engine performance calculations were performed for four different operation modes. Findings According to the results, maximum energy and exergy efficiency were acquired as 19.19% and 18.079% at Mode 4. Total cost rate was calculated as 6.757 $/h at Mode-1, which varied to 10.131 $/h at Mode-4. Exergy cost of engine power was observed as 0.249 $/MJ at Mode-1, which decreased to 0.088 $/MJ at Mode-4 after a careful exergoeconomic analysis. Originality/value The novelty of this work is the capability to serve as a guide for similar systems with a detailed approach in the thermodynamic, thermoeconomic and environmental assessments by prioritizing efficiency, fuel consumption and cost formation. This investigation intends to establish a design of the opportunities and benefits that the thermodynamic approach provides to turbojet engine systems.
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Prisacariu, Vasile, Constantin Rotaru, and Mihai Leonida Niculescu. "Considerations and simulations about Pulse Detonation Engine." MATEC Web of Conferences 290 (2019): 04009. http://dx.doi.org/10.1051/matecconf/201929004009.
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PDE propulsion can work from a subsonic regime to hypersonic regimes; this type of engine can have higher thermodynamic efficiency compared to other turbojet or turbofan engines due to the removal of rotating construction elements (compressors and turbines) that can reduce the mass and total cost of propulsion system. The PDE experimental researches focused on both the geometric configuration and the thermo-gas-dynamic flow aspects to prevent uncontrolled self-ignition. This article presents a series of numerical simulations on the functioning of PDE with hydrogen at supersonic regimens.
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Gunasekar, P., S. Manigandan, Venkatesh S., R. Gokulnath, Rakesh Vimal, and P. Boomadevi. "Effect of hydrogen addition on exergetic performance of gas turbine engine." Aircraft Engineering and Aerospace Technology 92, no. 2 (October 26, 2019): 180–85. http://dx.doi.org/10.1108/aeat-05-2019-0095.
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Purpose The depletion of fossil fuel and emissions of harmful gases forced the pioneers in search of alternate energy source. The purpose of this study is to present an effective use of hydrogen fuel for turbojet engines based on its exergetic performance. Design/methodology/approach This study was performed to measure the assessment of exergetic data of turbojet engines. Initially, the test was carried out on the Jet A-1 fuel. Then, a series of similar tests were carried out on turbojet engines with hydrogen fuel to measure their performance results. Finally, the exergetic values of both were compared with each other. Findings The introduction of hydrogen fuel reduced the exergy efficiency, and a 10 per cent reduction was observed in exergy efficiency. Simultaneously, the waste exergy rate increased by 9 per cent. However, because of the high specific fuel exergy, hydrogen fuel was better than Jet A-1 fuel. Note that parameters such as environmental effect factor and ecological effect witnessed an increase in their index owing to the addition of hydrogen. Practical implications Introduction of alternative blends is necessary for achieving lower emission of gases such as CO, NOx and CO2 from gas turbine engines without compromising on performance. The Jet A fuels were replaced by blends to obtain better emission characteristics. Originality/value The use of hydrogen in turbojet engines showed an adverse effect on exergetic performance. However, it was very impressive to see a 200 per cent reduction in emissions. From the comparison of exergy efficiency results of inlet, combustion and nozzle, it is evident that the combustion chamber has the largest values of exergy ratio, waste exergy ratio, cost flow, ecological factor, environmental factor and fuel ratio owing to irreversibility in the combustion process.
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Gawron, Bartosz, and Tomasz Białecki. "The laboratory test rig with miniature jet engine to research aviation fuels combustion process." Journal of KONBiN 36, no. 1 (December 1, 2015): 79–90. http://dx.doi.org/10.1515/jok-2015-0058.
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Abstract This article presents laboratory test rig with a miniature turbojet engine (MiniJETRig – Miniature Jet Engine Test Rig), that was built in the Air Force Institute of Technology. The test rig has been developed for research and development works aimed at modelling and investigating processes and phenomena occurring in full scale jet engines. In the article construction of a test rig is described, with a brief discussion on the functionality of each of its main components. Additionally examples of measurement results obtained during the realization of the initial tests have been included, presenting the capabilities of the test rig.
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Omar, H., V. S. Kuz'michev, and A. Yu Tkachenko. "Improving the efficiency of aviation turbofan engines by using an intercooler and a recuperative heat exchanger." VESTNIK of Samara University. Aerospace and Mechanical Engineering 19, no. 3 (December 30, 2020): 85–99. http://dx.doi.org/10.18287/2541-7533-2020-19-3-85-99.
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Continuous improvement of fuel efficiency of aircraft engines is the main global trend in modern engine construction. To date, aviation gas turbine engines have reached a high degree of thermodynamic and design-and technology perfection. One of the promising ways to further improve their fuel efficiency is the use of complex thermodynamic cycles with turbine exhaust heat regeneration and with intermediate cooling in the process of air compression. Until recently, the use of cycles with a recuperative heat exchanger and an intercooler in aircraft gas turbine engines was restrained by a significant increase in the mass of the power plant due to the installation of heat exchangers. Currently, it has become technologically possible 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 focuses on the statement of the task of optimization and choice of rational parameters of the working process of a bypass three-shaft turbojet engine with an intercooler and a recuperative heat exchanger. On the basis of the developed method multi-criteria optimization was carried out by means of numerical simulations. The results of optimization of thermodynamic cycle parameters of a bypass three-shaft turbojet engine with an intercooler and a recuperative heat exchanger in the aircraft system according to such criteria as the total weight of the engine and fuel required for the flight, and the aircraft specific fuel consumption per ton - kilometer of the payload are presented. A passenger aircraft of the Airbus A310-300 type was selected. 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 is presented. The developed methods and models are implemented in the ASTRA program. The possibility of improving the efficiency of turbofan engines due to the use of complex thermodynamic cycles is shown.
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Dunn, M. G., R. M. Adams, and V. S. Oxford. "Response of Large Turbofan and Turbojet Engines to a Short-Duration Overpressure." Journal of Engineering for Gas Turbines and Power 111, no. 4 (October 1, 1989): 740–47. http://dx.doi.org/10.1115/1.3240321.
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The influences of thrust setting and overpressure level on engine operating characteristics have been obtained for two different high-thrust engines. The thrust setting was varied from engine-off to take-off rated thrust (TRT) and the overpressure was varied from 6.9 kPa (1.0 psi) to 19.4 kPa (2.8 psi). The specific engines under consideration were the Pratt/Whitney TF33 low bypass ratio turbofan and the Pratt/Whitney J57 turbojet. The experimental results suggest that overpressure has little influence on either the HP compressor speed or the exhaust gas total temperature. However, the magnitude of the overpressure has a large influence on turbine exhaust total pressure and on the inlet casing and the diffuser casing radial displacements. The J57 turbine casing was significantly influenced by the overpressure, whereas the TF33 turbine casing was relatively insensitive. The J57 inlet casing radial displacement was noticeably greater than the corresponding turbofan displacement. Even though the component radial displacements for the TF33 exceeded the steady-state red-line limit by more than 300 percent, the engine did not sustain any permanent damage. The J57 did, however, experience an internal rub at an overpressure of about 14.5 kPa (2.1 psi).
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Самойлов, M. Samoylov, Бурцев, S. Burtsev, Симаков, and M. Simakov. "Ecological Aspects of Implementing Prospective Propulsion Schemes of Short and Medium Haul Aircrafts." Safety in Technosphere 4, no. 2 (April 25, 2015): 67–72. http://dx.doi.org/10.12737/11335.
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The influence of the circuitry of the hybrid power plant short and medium haul aircraft on their fuel efficiency and
environmental characteristics have been investigated. Directions of improvement of traditional patterns of power plants of
aircraft on the example of PD-14 engine were analyzed. It has been shown that the use of turbojet engines and traditional
schemes operating on aviation kerosene, will not allow to fulfill the demands made by the International Civil Aviation
Organization (ICAO) to perspective plane 2025–2035. The analysis of the three schemes hybrid propulsion systems has
been performed. It has been shown that using the presented hybrid propulsion systems of alternative fuels can reduce CO2
emissions by 19% to 20% compared with conventional turbojet engines, which run on kerosene TS-1. It has been shown
that this fuel efficiency is increased by 2–3%, and the total mass of the power plant increases of 6 to 16%.
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Trazzi, P. E. "DESIGN AND DEVELOPMENT OF A 70 N THRUST CLASS TURBOJET ENGINE." Revista de Engenharia Térmica 3, no. 1 (June 30, 2004): 09. http://dx.doi.org/10.5380/reterm.v3i1.3484.
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Small turbojet engines are being used for propulsion of radio-controlled
model airplanes. The design and development of the model 505 small jet
engine are reviewed. Small size gas turbines present special design and
construction difficulties, some of which are addressed; design choices
leading to the final configuration are discussed. Aero-thermodynamic
aspects are covered along with experimental data when available. The unit
is comprised of a radial compressor, an annular combustion chamber, and
an axial turbine plus accessories; details on these components and on
production aspects are presented.