Relevant bibliographies by topics / Turbojet engine

Contents

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

Academic literature on the topic 'Turbojet engine'

Author: Grafiati
Published: 4 June 2021
Last updated: 16 February 2022

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Journal articles on the topic "Turbojet engine"

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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Dissertations / Theses on the topic "Turbojet engine"

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Hackaday, Gary L. "Thrust augmentation for a small turbojet engine." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 1999. http://handle.dtic.mil/100.2/ADA362981.

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Thesis (M.S. in Aeronautical Engineering) Naval Postgraduate School, March 1999.
Thesis advisor(s): Garth V. Hobson. "March 1999". Includes bibliographical references (p. 75). Also available online.
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Andreou, Loukas. "Performance of a ducted micro-turbojet engine." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 1999. http://handle.dtic.mil/100.2/ADA370851.

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Thesis (M.S. in Aeronautical Engineering) Naval Postgraduate School, September 1999.
"September 1999". Thesis advisor(s): Garth V. Hobson. Includes bibliographical references (p. 79). Also available online.
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Fahlström, Simon, and Rikard Pihl-Roos. "Design and construction of a simple turbojet engine." Thesis, Uppsala universitet, Industriell teknik, 2016. http://urn.kb.se/resolve?urn=urn:nbn:se:uu:diva-303970.

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This project deals with researching, designing and building jet-engines. A simple turbojet engine was designed and construction was begun. The design was made by studying the work done by industry and researchers over the course of the history of jet engines. The methods were then discussed and chosen in a way that would simplify the design work as well as the construction of the engine. The goal was to create a self-sustaining combustion within the engine. The design settled upon consists of a radial compressor, an annular combustion chamber and an axial turbine. Since the compressor would have been the most difficult part to machine the decision was made early on to use the compressor from a turbocharger out of an automotive engine. Upon further study it was discovered that the characteristics of this compressor was not compatible with the rest of the design, as the compressor was made for an RPM range outside of what we could achieve and the compression ratio was too low. Most of the rest of the engine had already been built, and there was not enough time to design and build another compressor so work was aborted on the engine.
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Yarlagadda, Santosh. "Performance Analysis of J85 Turbojet Engine Matching Thrust with Reduced Inlet Pressure to the Compressor." University of Toledo / OhioLINK, 2010. http://rave.ohiolink.edu/etdc/view?acc_num=toledo1271367584.

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Bell, Jabin Todd. "Measurements of forced and unforced aerodynamic disturbances in a turbojet engine." Thesis, Massachusetts Institute of Technology, 1993. http://hdl.handle.net/1721.1/46423.

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Ceylanoglu, Arda. "An Accelerated Aerodynamic Optimization Approach For A Small Turbojet Engine Centrifugal Compressor." Master's thesis, METU, 2009. http://etd.lib.metu.edu.tr/upload/12611371/index.pdf.

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Centrifugal compressors are widely used in propulsion technology. As an important part of turbo-engines, centrifugal compressors increase the pressure of the air and let the pressurized air flow into the combustion chamber. The developed pressure and the flow characteristics mainly affect the thrust generated by the engine. The design of centrifugal compressors is a challenging and time consuming process including several tests, computational fluid dynamics (CFD) analyses and optimization studies. In this study, a methodology on the geometry optimization and CFD analyses of the centrifugal compressor of an existing small turbojet engine are introduced as increased pressure ratio being the objective. The purpose is to optimize the impeller geometry of a centrifugal compressor such that the pressure ratio at the maximum speed of the engine is maximized. The methodology introduced provides a guidance on the geometry optimization of centrifugal impellers supported with CFD analysis outputs. The original geometry of the centrifugal compressor is obtained by means of optical scanning. Then, the parametric model of the 3-D geometry is created by using a CAD software. A design of experiments (DOE) procedure is applied through geometrical parameters in order to decrease the computation effort and guide through the optimization process. All the designs gathered through DOE study are modelled in the CAD software and meshed for CFD analyses. CFD analyses are carried out to investigate the resulting pressure ratio and flow characteristics. The results of the CFD studies are used within the Artificial Neural Network methodology to create a fit between geometric parameters (inputs) and the pressure ratio (output). Then, the resulting fit is used in the optimization study and a centrifugal compressor with higher pressure ratio is obtained by following a single objective optimization process supported by design of experiments methodology.
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Pavelec, Sterling Michael. "The development of turbojet aircraft in Germany, Britain, and the United States : a multi-national comparison of aeronautical engineering, 1935-1946 /." The Ohio State University, 2004. http://www.ohiolink.edu/etd/send-pdf.cgi/Pavelec%20Sterling%20Michael.pdf?acc_num=osu1082396007.

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Polat, Cuma. "An Electronic Control Unit Design For A Miniature Jet Engine." Master's thesis, METU, 2009. http://etd.lib.metu.edu.tr/upload/12611442/index.pdf.

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Gas turbines are widely used as power sources in many industrial and transportation applications. This kind of engine is the most preferred prime movers in aircrafts, power plants and some marine vehicles. They have different configurations according to their mechanical constructions such as turbo-prop, turbo-shaft, turbojet, etc. These engines have different efficiencies and specifications and some advantages and disadvantages compared to Otto-Cycle engines. In this thesis, a small turbojet engine is investigated in order to find different control algorithms. AMT Olympus HP small turbojet engine has been used to determine the mathematical model of a gas turbine engine. Some important experimental data were taken from AMT Olympus engine by making many experiments. All components of the engine have been modeled by using laws of thermodynamics and some arithmetic calculations such as numerical solution of nonlinear differential equations, digitizing compressor and turbine map etc. This mathematical model is employed to create control algorithm of the engine. At first, standard control strategies had been considered such as P (proportional), PI (proportional integral), and PID (proportional-integral-differential) controllers. Because of the nonlinearities in gas turbines, standard control algorithms are not commonly used in literature. At the second stage fuzzy logic controllers have been designed to control the engine efficiently. This control algorithm was combined with mathematical of the engine in MATLAB environment and input-output relations were investigated. Finally, fuzzy logic control algorithm was embedded into an electronic controller.
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KAMARAJ, JAYACHANDRAN. "MODELING AND SIMULATION OF SINGLE SPOOL JET ENGINE." University of Cincinnati / OhioLINK, 2004. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1073935505.

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Avrat, Jan. "Metody údržby a diagnostiky lopatkových motorů." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2009. http://www.nusl.cz/ntk/nusl-228602.

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This master`s thesis deals with methods of turbojet engines maintenance and diagnostics. First specify and review methods. Then choose acceptable and perspective methods of non-destructive testing. Based on this choosing will be designed modern service center.
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Books on the topic "Turbojet engine"

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Hackaday, Gary L. Thrust augmentation for a small turbojet engine. Monterey, Calif: Naval Postgraduate School, 1999.

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North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Comparative engine performance measurements. Neuilly sur Seine, France: AGARD, 1990.

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Abdelwahab, Mahmood. Measurement uncertaintyfor the uniform engine testing program conducted at the NASA Lewis Research Center. [Washington, DC: National Aeronautics and Space Administration, 1987.

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North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Comparative engine performance measurements (Mesures comparatives des performances des moteurs). Neuilly-sur-Seine, France: AGARD, 1990.

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Plencner, Robert M. Plotting component maps in the Navy/NASA Engine Program (NNEP): A method and its usage. [Washington, DC]: National Aeronautics and Space Administration, 1989.

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Parallel processing for jet engine control. London: Springer-Verlag, 1992.

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Garvin, R. V. Starting something big: The commercial emergence of GE aircraft engines. Reston, VA: American Institute of Aeronautics and Astronautics, 1998.

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Kay, Antony L. German jet engine and gas turbine development, 1930-1945. Shrewsbury, England: Airlife, 2002.

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Jaw, Link C. Aircraft engine controls: Design, system analysis, and health monitoring. Reston, VA: American Institute of Aeronautics and Astronautics, 2009.

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Rickey, June Elizabeth. The effect of altitude conditions on the particle emissions of a J85-GE-5L turbojet engine. [Washington, DC]: National Aeronautics and Space Administration, 1995.

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Book chapters on the topic "Turbojet engine"

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Babu, V. "The Turbojet Engine." In Fundamentals of Propulsion, 61–81. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-79945-8_5.

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Ginevsky, A. S., Ye V. Vlasov, and R. K. Karavosov. "Reduction of Turbojet Engine Noise." In Foundations of Engineering Mechanics, 189–208. Berlin, Heidelberg: Springer Berlin Heidelberg, 2004. http://dx.doi.org/10.1007/978-3-540-39914-8_8.

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Şöhret, Yasin, and T. Hikmet Karakoç. "Greenization Factor of a Turbojet Engine." In Advances in Sustainable Aviation, 243–48. Cham: Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-67134-5_17.

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Yuksel, Burak, Ozgur Balli, Huseyin Gunerhan, Arif Hepbasli, and Halil Atalay. "Exergetic and Environmental Analyses of Turbojet Engine." In Environmentally-Benign Energy Solutions, 387–401. Cham: Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-030-20637-6_21.

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Szybicki, Dariusz, Andrzej Burghardt, Piotr Gierlak, and Krzysztof Kurc. "Robot-Assisted Quality Inspection of Turbojet Engine Blades." In Lecture Notes in Electrical Engineering, 337–50. Cham: Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-030-11187-8_28.

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Kahraman, Coban, Sohret Yasin, Colpan C. Ozgur, and Karakoc T. Hikmet. "Second Law Analysis of an Experimental Micro Turbojet Engine." In Exergy for A Better Environment and Improved Sustainability 1, 753–66. Cham: Springer International Publishing, 2018. http://dx.doi.org/10.1007/978-3-319-62572-0_48.

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Főző, Ladislav, Rudolf Andoga, and Ladislav Madarász. "Mathematical Model of a Small Turbojet Engine MPM-20." In Computational Intelligence in Engineering, 313–22. Berlin, Heidelberg: Springer Berlin Heidelberg, 2010. http://dx.doi.org/10.1007/978-3-642-15220-7_25.

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Jie, Min Seok, Eun Jong Mo, Gyo Young Hong, and Kang Woong Lee. "Fuzzy Logic Controller for Turbojet Engine of Unmanned Aircraft." In Lecture Notes in Computer Science, 29–36. Berlin, Heidelberg: Springer Berlin Heidelberg, 2006. http://dx.doi.org/10.1007/11892960_4.

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Göing, Jan, Andreas Kellersmann, Christoph Bode, and Jens Friedrichs. "System Dynamics of a Single-Shaft Turbojet Engine Using Pseudo Bond Graph." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 427–36. Cham: Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-030-25253-3_41.

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Jie, Min-Seok, and Beyong-In Jung. "Speed and Surge Control for an Unmanned Aircraft Vehicle with Turbojet Engine." In Lecture Notes in Electrical Engineering, 735–43. Dordrecht: Springer Netherlands, 2011. http://dx.doi.org/10.1007/978-94-007-2792-2_72.

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Conference papers on the topic "Turbojet engine"

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Rancourt, Gregory, Donald Gipe, and Ryan Starkey. "Biofueled Miniature Turbojet Engine (BIOMITE)." In 50th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2012. http://dx.doi.org/10.2514/6.2012-109.

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Shen, Jiwu, Konstanty Masiulaniec, and Abdollah Afjeh. "Turbojet Engine Simulation Using Dymola." In 42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2006. http://dx.doi.org/10.2514/6.2006-4796.

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Ashry, Mahmoud M., Mohamed K. Kamel, and Ahmed M. Shehata. "Modeling of Micro Turbojet Engine." In AIAA Propulsion and Energy 2019 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2019. http://dx.doi.org/10.2514/6.2019-3911.

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Katolicky, Zdenek, Bohuslav Busov, and Milada Bartlova. "Turbojet engine innovation and TRIZ." In 2014 16th International Conference on Mechatronics - Mechatronika (ME). IEEE, 2014. http://dx.doi.org/10.1109/mechatronika.2014.7018230.

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shehata, Ahmed M., Mohamed K. khalil, and Mahmoud M. Ashry. "Controller Design for Micro Turbojet Engine." In 2020 12th International Conference on Electrical Engineering (ICEENG). IEEE, 2020. http://dx.doi.org/10.1109/iceeng45378.2020.9171762.

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Barbosa, João Roberto, and Daniel Jonas Dezan. "Turbojet Engine Noise Prediction Utilizing Empirical Methods." In ASME Turbo Expo 2013: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/gt2013-95274.

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This work deals with the prediction of noise generated by gas turbines, which includes engines being designed. One has in mind the fulfillment of the ever-increasing concerns with environment, in particular noise. Analytical and empirical methods have been focused by researchers and industry, although only empirical prediction methods are utilized in this work, for the calculation of the one-third octave band sound pressure levels associated to the main engine noise sources. The methodology for the calculation of the engine noise has been combined with performance and design computational programs to evaluate the noise emitted by each engine component and, by proper combination, the engine total noise. A newly designed and manufactured 5 kN/1.2 MW turbojet engine serves as the basis for the noise prediction. For the study, the main noise sources are: compressor, combustor, turbine and propelling nozzle. In terms of the overall sound pressure level, OASPL, are compatible with the noise produced by similar engines. The noise predictions are performed at engine design speeds in the range of 100% down to 70% of the design speed (28,150 rpm). The engine has not run yet, but it is expected that measured noise will be available in the near future. However, it is important to emphasize that all prediction models used to evaluate the radiated noise from the engine were validated. The engine operating conditions were calculated using a high fidelity engine simulator developed to provide the data used in this study. The methods to estimate the one-third octave band sound pressure levels are reported in NASA TM-195480, SAE ARP-876D, NASA-ANOPP and ESDU Item 98019. No atmospheric attenuation and ground reflection were considered in this work.
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Buchan, Greg, and Jenn Rossmann. "Quantifying Confidence Envelopes for Efficiency Values in the SR-30 Turbojet Engine." In ASME 2011 International Mechanical Engineering Congress and Exposition. ASMEDC, 2011. http://dx.doi.org/10.1115/imece2011-62135.

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Turbojet engines power most of the large military and commercial aircraft in production today. These types of engines are chosen over conventional piston-driven engines because of the turbojet’s superior fuel economy and thrust. To understand how turbojet engines can be compared and optimized, it is necessary to fully characterize their performance. This is generally achieved by calculating thermodynamic efficiency values for each component in the engine, and for the engine as a whole. For this research project, the Turbine Technologies SR-30 centrifugal flow turbojet engine was investigated. An adjustable coupling was designed to permit a single-point thermocouple to be moved and secured within the engine. From the data taken at multiple locations and throttle settings, temperature profiles of the compression and combustion chambers were created. A thermal/fluid dynamic equation routine was developed using Engineering Equation Solver (EES), in order to propagate these temperature profiles through efficiency and thrust calculations. The temperature profiles did not significantly affect theoretical thrust values. However, the dependence of component efficiency values on spatial temperature variation within the engine was significant. In the compression chamber, it was found that a 30°C variation in the temperature across the chamber resulted in a 15% variation in the calculated compressor efficiency. In the inner region of the combustion chamber, a variation in 20°C yielded a 20% variation in calculated turbine efficiency. In the outer region of the combustion chamber, where the temperature varied by almost 400 degrees Celsius, the turbine efficiency varied by about 600%. This work suggests optimal placement of the compression and combustion stage thermocouples when the SR-30 turbojet is to be used for undergraduate laboratories. It also highlights the risks posed by relying on single-point measurements to characterize complex flows.
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Jeronymo, Daniel, and Felipe Stark. "Particle Swarm Optimization of Turbojet Engine Thrust." In 24th ABCM International Congress of Mechanical Engineering. ABCM, 2017. http://dx.doi.org/10.26678/abcm.cobem2017.cob17-2836.

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DUE, H. "Development of the Model 373 turbojet engine." In 23rd Joint Propulsion Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1987. http://dx.doi.org/10.2514/6.1987-1908.

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Andoga, Rudolf, Ladislav Fozo, and Ladislav Madarasz. "Basic approaches to small turbojet engine modeling." In 2008 6th International Symposium on Intelligent Systems and Informatics (SISY 2008). IEEE, 2008. http://dx.doi.org/10.1109/sisy.2008.4664980.

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Reports on the topic "Turbojet engine"

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AIR FORCE RESEARCH LAB EDWARDS AFB CA. KLIN Cycle Engine - Deeply Cooled Turbojet (DCTJ) Engine Performance Formulation. Fort Belvoir, VA: Defense Technical Information Center, July 2000. http://dx.doi.org/10.21236/ada404927.

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