Relevant bibliographies by topics / Aircraft engines

Contents

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

Academic literature on the topic 'Aircraft engines'

Author: Grafiati
Published: 4 June 2021
Last updated: 10 February 2022

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Journal articles on the topic "Aircraft engines"

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A., Armaan, and Srinivas G. "In Tune with Times: Recent Developments in Theoretical, Experimental and Numerical techniques of Aircraft Engines." International Journal of Engineering & Technology 7, no. 2 (May 23, 2018): 805. http://dx.doi.org/10.14419/ijet.v7i2.10910.

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Today the aircraft engine designing and development work is increasing drastically. Especially aircraft engines play a vital role in order to decide the aircrafts speed and its performance. Broadly turbojet, turboprop, turbo shaft and turbofan engines comes under the category of air breathing engines. Every engine has its own purpose and application. But modern aircrafts require much more advancements. Designing a new aircraft engine has been a really challenging task to the researchers. But giving a complete holistic view of aircraft engines and research gap would definitely help a lot to the new designers. Once identified the drawbacks of engine performance can be corrected in the future. For any new design of aircraft engine researchers are suggested to take Theoretical, Experimental and Numerical approaches. Therefore present paper makes an effort to review complete recent Theoretical, Experimental and Numerical approaches which are followed till date. Under all the three approaches all the air breathing engines have been clearly explained and solicited. The effort is to identify the gaps between different approaches which are hampering the process of engine development. The paper also gives the research gaps that need to be incorporated for effective performance enhancement of the aircraft engines for aeromechanical features.
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Glowacki, Pawel Jan. "Aircraft piston engines on-condition exploitation." Aircraft Engineering and Aerospace Technology 90, no. 7 (October 1, 2018): 1095–103. http://dx.doi.org/10.1108/aeat-01-2017-0042.

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Purpose Currently, in many countries, aviation safety regulations allow piston engines exploitation above Time Between Overhaul (TBO) recommended by manufacturers. Upon fulfillment of certain requirements, which are already included in the manufacturers’ documentation, TBO extension is granted. National Aviation Authority has approved exploitation of piston engines to something like quasi on-condition maintenance, which has no technical proof behind. This leads to the conclusion that the current, simple way of the engine’s life extension is not the best solution for maintaining flight safety. Aircraft piston engines TBO extension requires changes in the current exploitation system. Design/methodology/approach The paper provides methodology for aircraft piston engines on-condition exploitation based on engine flight parameters (from cruise and takeoff) and engine oil particles analysis. The paper describes a method of diagnostic limits for certain engine parameters and elements in the oil assignation assuming that they come under rules of normal distribution. Findings It has been found that piston engines installed on maximum takeoff mass <5,700 kg class aircraft are the second biggest contributor as a source of aviation events, thereby having a significant impact on aviation safety. Engine flight parameters and elements content in the oil meet Gaussian rules. Practical implications Introduction of the engine on-condition exploitation into operation practices reduces the operator’s engine direct maintenance cost and increases technical knowledge of the employees and has a positive impact on flight safety. Originality/value It is the first scientific description in Poland, which proposes an empirically proved methodology of the aviation piston engines on-condition exploitation.
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Zuo, Yu Yu. "Analysis of Gas Turbine Engines Auxiliary Power Units." Applied Mechanics and Materials 533 (February 2014): 13–16. http://dx.doi.org/10.4028/www.scientific.net/amm.533.13.

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As aircraft became more complex a need was created for a power source to operate the aircraft systems on the ground without the necessity for operating the aircrafts main engines. This became the task of the Auxiliary Power Unit (APU). The use of an APU on an aircraft also meant that the aircraft was not dependant on ground support equipment at an airfield. It can provide the necessary power for operation of the aircrafts Electrical, Hydraulic and Pneumatic systems. It should come as no surprise that the power unit selected to do this task is a Gas Turbine Engine.
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GĘCA, Michał, Zbigniew CZYŻ, and Mariusz SUŁEK. "Diesel engine for aircraft propulsion system." Combustion Engines 169, no. 2 (May 1, 2017): 7–13. http://dx.doi.org/10.19206/ce-2017-202.

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Stricter requirements for power in engines and difficulties in fueling gasoline engines at the airport make aircraft engine manufac-turers design new engines capable of combusting fuel derived from JET-A1. New materials used in compression-ignition engines enable weight reduction, whereas the technologies of a Common Rail system, supercharging and 2-stroke working cycle enable us to increasethe power generated by an engine of a given displacement. The paper discusses the parameters of about 40 types of aircraft compression ignition engines. The parameters of these engines are compared to the spark-ignition Rotax 912 and the turboprop. The paper also shows trends in developing aircraft compression-ignition engines.
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Cur, Krzysztof, Mirosław Kowalski, Paweł Stężycki, and Dariusz Ćwik. "Checking Aircraft Engines Adjustment." Journal of KONBiN 51, no. 2 (June 1, 2021): 153–62. http://dx.doi.org/10.2478/jok-2021-0029.

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Abstract The paper presents a new approach to the process of regulating the basic parameters of a turbine jet engine. It presents a system for monitoring these parameters developed and put into operation and the creation of the so-called phase mapping of the engine speed increment. Its modular structure is described, which allows it to be adapted quite quickly to other types of aircraft engine units. Individual modules are based on mathematical descriptions from the theory of aircraft engines. The phase mapping of the engine speed indicates a dynamic change of this parameter. On this basis, the characteristic ranges and individual points of engine operation are presented. The following are examples of characteristics and their interpretation.
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Lee, J. Lawrence. "The Mechanics of Flight." Mechanical Engineering 122, no. 07 (July 1, 2000): 54–59. http://dx.doi.org/10.1115/1.2000-jul-2.

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This article illustrates contribution of mechanical engineering in the aviation industry. The most obvious role of the mechanical engineer involves the design of engines. From the Wrights’ four cylinders, 12-horsepower engine, aircraft propulsion has evolved into today’s high-bypass turbofans developing over 90,000 pounds of thrust in some instances. The most visible contribution of mechanical engineers to aviation, engines are far from their only contribution. Changes in the design, construction, and capabilities of increasingly modern aircraft challenged the mechanical engineering in many other regards. The introduction of gas-turbine power required a concurrent revolution in manufacturing, test, and maintenance facilities and techniques at the engine builders. As advancements in aircraft construction and power opened the door to higher and faster flight, virtually every system within the airplane had to become more sophisticated, and new ones had to be devised. Air conditioning systems also changed, both to better suit the gas turbine prime mover and to accommodate wider external temperature extremes.
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Geiß, Ingmar, and Rudolf Voit-Nitschmann. "Sizing of fuel-based energy systems for electric aircraft." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 231, no. 12 (August 4, 2017): 2295–304. http://dx.doi.org/10.1177/0954410017721254.

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Optimized electric motors are lighter and smaller than conventional piston engines. As a result, new airplane configurations are feasible as motors can be placed in unconventional positions. Through careful aircraft design higher aerodynamic efficiencies of airframe, propeller, and propeller integration can be achieved. The energy density of current batteries, however, still limits strongly the range of purely battery powered aircraft. But if the energy is stored in liquid fuel and converted by a generator into electric energy, then the advantages of electric propelled airplanes and conventional combustion engines can be combined. But which combustion engine is optimal for such a serial-hybrid electric aircraft? In this new propulsion chain, other boundary conditions apply to the combustion engine than in conventional aircraft designs. These boundary conditions interact with the characteristics of combustion engines. An example for an engine characteristic is that different kinds of piston engines exist. It can be observed that technologies, which result in lighter piston engines, are associated with lower efficiencies and vice versa. In this paper it will be shown through considerations on aircraft level, that the optimal combustion engine for an electric-hybrid airplane should be heavier and more efficient than the optimal combustion engine for a conventional aircraft.
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Улитенко, Ю. А. "ВІДНОСНИЙ КРИТЕРІЙ ЕФЕКТИВНОСТІ ВИСОКОШВИД-КІСНОГО ЛІТАЛЬНОГО АПАРАТА." Open Information and Computer Integrated Technologies, no. 85 (July 29, 2019): 151–66. http://dx.doi.org/10.32620/oikit.2019.85.09.

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Development of perspective high-speed aircrafts inseparably linked with level of aircraft propulsion engineering as engine performances to determine aircraft capabilities as a whole. The basic requirements to engines of high-speed aircrafts are increase speed and flight height. With each new generation of turbojet bypass engine with afterburner their specific thrust and a specific impulse are increase, also application of high technologies raises leads to substantial growth of the engine cost too. At the same time existing engines design has the big reserves for modernization. For a quantitative assessment of the degree of influence of the new technical solution on the quality of the task performance by the aviation complex, criteria (indicators) of efficiency are used. However, it is not possible to find a direct functional dependence of the overall criterion of the effectiveness of the aviation complex on the technical and operational characteristics, conditions of use of a high-speed aircraft. The purpose of this work is to develop a methodology for determining the economic criterion for assessing the degree of influence of a new technical solution on the quality of the task performance by the aviation complex (the value of the integrated performance criterion). The text of the paper provides an analysis of recent research and publications. The developed relative criterion of the efficiency of a high-speed aircraft makes it possible to accomplish the goal set, as well as to estimate the costs at the cost of which the final result is achieved. It is shown that boosting engines with water injection has some advantage over other options for increasing the thrust of high-speed aircraft engines. The application of the obtained results can be used to substantiate new technical solutions and establish their impact on the quality of the task performance by the aviation complex, as well as reduce the time to create competitive high-speed aircraft.
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Denning, R. M., and N. A. Mitchell. "Trends in Military Aircraft Propulsion." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 203, no. 1 (January 1989): 11–23. http://dx.doi.org/10.1243/pime_proc_1989_203_049_01.

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The major factors determining the choice of engine cycle for a combat aircraft are the requirements of the design mission and those of aircraft speed and agility. The requirement for jet-borne flight in short take-off vertical landing (STOVL) aircraft imposes further demands on cycle and configuration. The changing nature of combat aircraft requirements is the reason for changes in engine design. Specific thrust is shown to be the major parameter defining engine suitability for a particular role. An examination of mixed turbofan characteristics shows that specific thrust is also the key to understanding the relationships between engine characteristics. The future development of combat engines is discussed, in particular the implications of stoichiometric limits on cycle temperatures and the benefits of variable cycle engines are examined. Recent work on advanced STOVL (ASTOVL) aircraft is reviewed and aircraft/engine concepts designed to meet the requirements of the role are assessed. Experience shows that the technology for these advanced engines must be fully demonstrated before production to minimize the risks and costs of the development programme.
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Naeem, M., R. Singh, and D. Probert. "Impacts of aero-engine deteriorations on military aircraft mission's effectiveness." Aeronautical Journal 105, no. 1054 (December 2001): 685–96. http://dx.doi.org/10.1017/s0001924000012768.

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Abstract International political and socio-economic developments have led the armed forces of many countries to become more aware of how their increasingly-stringent financial budgets are spent. One major expenditure for military authorities is upon aero-engines, because in-service deterioration in any mechanical device, such as an aircraft's gas-turbine engine, is inevitable. Each deterioration has an adverse effect on the performance and shortens the reliable operational life of the engine, thereby resulting in higher life-cycle costs. For a military aircraft's mission-profiles, the consequences of an aero-engine's deterioration upon the aircraft's operational-effectiveness as well as its fuel consumption and life have been predicted in this project using validated computer-simulations. These help in making wiser management-decisions, so leading to the achievement of improved engine utilisation, lower overall life-cycle costs and optimal mission effectiveness for squadrons of aircraft.
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Dissertations / Theses on the topic "Aircraft engines"

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Chan, Nicholas Y. S. "Scaling considerations for small aircraft engines." Thesis, Massachusetts Institute of Technology, 2008. http://hdl.handle.net/1721.1/45236.

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Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2008.
Includes bibliographical references (p. 81-84).
Small aircraft engines traditionally have poorer performance compared to larger engines, which until recently, has been a factor that outweighed the aerodynamic benefits of commoditized and distributed propulsion. Improvements in the performance of small engines have, however, prompted another look at this old concept. This thesis examines aspects of aircraft engines that may have application to commodity thrust or distributed propulsion applications. Trends of engine performance with size and time are investigated. These trends are further extended to justify parameter choices for conceptual engines of the current, mid-term (10 years) and far-term (20 years). Uninstalled and installed performances are evaluated for these engines, and parametric studies are performed to determine the most influential and limiting factors. It is found that scaling down of engines is detrimental to SFC and fuel burn, mainly due to the Reynolds number effect. The more scaling done, the more prominent the effect. It is determined that new technology such as higher TIT, OPR and turbomachinery [eta]poly's for small aircraft engines enable the operation of larger bypass ratios, which is the most influential parameter to SFC and fuel bum. The increase of bypass ratio up to a value of 8 is found to be effective for such improvement. SFC decrease from the current to mid-term model is found to be ~20% and ~9% from mid-term to far-term. Range and endurance improvements are found to be ~30% and ~10% respectively for the mission examined. Finally, the mid-term engine model has performance comparable to that of a current, larger state-of-the-art engine, thus suggesting that improvement in small gas turbine technology in the next 10 years will make the application of commodity thrust or distributed propulsion an attractive option for future aircraft.
by Nicholas Y.S. Chan.
S.M.
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Lee, Victoria D. Lee (Victoria Dawn). "Waste heat reclamation in aircraft engines." Thesis, Massachusetts Institute of Technology, 2014. http://hdl.handle.net/1721.1/97318.

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Thesis: S.M., Massachusetts Institute of Technology, Department of Mechanical Engineering, 2014.
Cataloged from PDF version of thesis.
Includes bibliographical references (pages 94-96).
Introduction: Rotorcraft engines can lose up to 70% of the potential chemical energy of their fuel as waste heat. Harvesting this waste heat and converting it to useful work would improve the efficiency and power output of the engine. Figure 1 shows two possible engine systems in which a secondary engine could be used to harvest waste heat. For the gas turbine engine in Figure 1A, the main source of waste heat is the enthalpy of the engine's exhaust gases. In the case of the spark ignition engine in Figure 1B, there are three sources of waste heat: the enthalpy available in the exhaust gases, the heat rejected by the coolant loop, and the heat rejected by the oil loop. For each engine system, the heat from waste heat engine is rejected to the ambient air. Possible candidate systems for waste heat recovery include closed cycle systems such as the Rankine and Brayton engines. Rankine engines typical use water as a working fluid. The performance of water-based Rankine engines suffer from low pressures in the working fluid at the temperatures of the ambient and, therefore, require large low pressure expanders and condensers to operate efficiently. Organic working fluids have higher vapor pressures and can be used in Rankine engines instead of water. The higher vapor pressures of these fluids allow the use of smaller expanders. However, organic working fluids are limited to temperatures below 250 C, which is substantially lower than the typical temperatures available in the waste streams. Brayton engines can operate at higher temperatures using inert gases such as helium and argon as working fluids. In either of these engines, the turbomachinery and heat exchangers must remain leak tight as the working fluid is cycled through at high temperatures and high pressures. As a consequence of this requirement, these cycles will not be considered further in this work. Thermoelectric devices, on the other hand, do not require leak tight passages or turbomachinery. These are compacted and are expected to have a higher reliability since they have no moving parts. These advantages have motivated this study on thermoelectrically-based waste heat engine. For a thermoelectrically-based waste heat engine to be feasible, it must be capable of absorbing and rejecting large amounts of heat in part to compensate for the low efficiencies of thermoelectric materials. It must also be light weight and compact to address concerns of power to weight ratios and space constraints in rotorcraft. Therefore, the waste heat engine must be designed to minimize thermal resistance while also minimizing the mass and volume of the heat exchangers.
by Victoria D. Lee.
S.M.
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Ford, Sean T. "Aerothermodynamic cycle design and optimization method for aircraft engines." Thesis, Georgia Institute of Technology, 2014. http://hdl.handle.net/1853/53006.

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This thesis addresses the need for an optimization method which can simultaneously optimize and balance an aerothermodynamic cycle. The method developed is be able to control cycle design variables at all operating conditions to meet the performance requirements while controlling any additional variables which may be used to optimize the cycle and maintaining all operating limits and engine constraints. The additional variables represent degrees of freedom above what is needed for conservation of mass and energy in the engine system. The motivation for such a method is derived from variable cycle engines, however it is general enough to use with most engine architectures. The method is similar to many optimization algorithms but differs in its implementation to an aircraft engine by combining the cycle balance and optimization using a Newton-Raphson cycle solver to efficiently find cycle designs for a wide range of engine architectures with extra degrees of freedom not needed to balance the cycle. Combination of the optimization with the cycle solver greatly speeds up the design and optimization process. A detailed process description for implementation of the method is provided as well as a proof of concept using several analytical test functions. Finally, the method is demonstrated on a separate flow turbofan model. Limitations and applications of the method are further explored including application to a multi-design point methodology.
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Ismail, Ibrahim H. "Simulation of aircraft gas turbine engine." Thesis, University of Hertfordshire, 1991. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.303465.

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Sangwian, Sirirat. "Multivariable Sliding Mode Control for Aircraft Engines." Cleveland State University / OhioLINK, 2011. http://rave.ohiolink.edu/etdc/view?acc_num=csu1315587541.

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Ebel, Kathryn C. "Adaptive Sliding Mode Control for Aircraft Engines." Cleveland State University / OhioLINK, 2011. http://rave.ohiolink.edu/etdc/view?acc_num=csu1323882562.

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Mahmoud, Saad M. "Effective optimal control of a fighter aircraft engine." Thesis, Loughborough University, 1988. https://dspace.lboro.ac.uk/2134/7287.

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Typical modem fighter aircraft use two-spool, low by-pass ratio, turbojet engines to provide the thrust needed to carry out the combat manoeuvres required by present-day air warfare tactics. The dynamic characteristics of such aircraft engines are complex and non-linear. The need for fast, accurate control of the engine throughout the flight envelope is of paramount importance and this research was concerned with the study of such problems and subsequent design of an optimal linear control which would improve the engine's dynamic response and provide the required correspondence between the output from the engine and the values commanded by a pilot. A detailed mathematical model was derived which, in accuracy and complexity of representation, was a large improvement upon existing analytical models, which assume linear operation over a very small region of the state space, and which was simpler than the large non-analytic representations, which are based on matching operational data. The non-linear model used in this work was based upon information obtained from DYNGEN, a computer program which is used to calculate the steady-state and transient responses of turbojet and turbofan engines. It is a model of fifth order which, it is shown, correctly models the qualitative behaviour of a representative jet engine. A number of operating points were selected to define the boundaries used for the flight envelope. For each point a performance investigation was carried out and a related linear model was established. By posing the problem of engine control as a linear quadratic problem, in which the constraint was the state equation of the linear model, control laws appropriate for each operating point were obtained. A single control was effective with the linear model at every point. The same control laws were then applied to the non-linear mathematical model adjusted for each operating point, and the resulting responses were carefully studied to determine if one single control law could be used with all operating points. Such a law was established. This led, naturally, to the determination of an optimal linear tracking control law, and a further investigation to determine whether there existed an optimal non-linear control law for the non-linear model. In the work presented in this dissertation these points are fully discussed and the reasons for choosing to find an optimal linear control law for the non-linear model by solving the related two-point, boundary value problem using the method of quasilinearisation are presented. A comparison of the effectiveness of the respective optimal control laws, based upon digital simulation, is made before suggestions and recommendations for further work are presented.
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Alizadeh, Sohail. "Flowfield prediction of NOx and smoke production in aircraft engines." Thesis, Cranfield University, 1993. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.359437.

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Helmick, Daniel Martin. "Engine modeling, control, and synchronization for an unmanned aerial vehicle." Thesis, Georgia Institute of Technology, 1998. http://hdl.handle.net/1853/16750.

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Harris, P. K. "Erosion in centrifugal compressor impellers." Thesis, Cranfield University, 1996. http://dspace.lib.cranfield.ac.uk/handle/1826/10622.

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An experimental and theoretical study of erosion in centrifugal compressor impellers is presented. An experimental rig using laser anemometry techniques was employed to create a database of particle restitution ratios for a range of materials. This data was unique in that the particle rebound was measured in a quiescent condition where the aerodynamic effects had been minimised, and also parametric factors not previously available were included. These values were incorporated into the existing Particle Trajectory Code developed by Cranfield University and Rolls Royce PLC. The code is used to calculate the trajectories of discrete particles in three dimensional gas turbine geometries, and the ensuing erosion. It was modified to include the effects of the periodic boundary conditions, particle fragmentation, splitter blades, and variations in inlet dust concentration profile. Flowfield calculations were performed on a Rolls Royce GEM-2 and splittered GEM-60 impeller, which both represent the high pressure stage of the axial + centrifugal compression system of GEM engines. A procedure developed by Tourlidakis, for the analysis of steady viscous flow in high speed centrifugal compressors with tip leakage, was used to generate the flowfields. The GEM-2 impeller flowfield was analysed at 1009c speed, and validated with calculations and measurements which had been taken for previous projects. Simulated erosion data under the same conditions was checked using practical results obtained in a Rolls Royce PLC Helicopter Engine Environmental Protection Programme, and good agreement was achieved. In order to provide a qualitative, experimental assessment of erosion, a GEM-60 impeller was coated with four layers of paint of different colours. Two sizes of quartz particle, each at three different vane heights, were then seeded into the impeller while it was run cold at (the maximum) 70% speed. The erosion patterns generated compared well with the results generated by the Particle Trajectory Code.
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Books on the topic "Aircraft engines"

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Chrysler aircraft engines. Huntsville (Ala.): Weak Force Press, 2012.

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Aircraft engines and gas turbines. 2nd ed. Cambridge, Mass: MIT Press, 1992.

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Richard, Finch. Converting auto engines for experimental aircraft. [Titusville, Fla.]: Finch Books, 1985.

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Loomis, William R. Liquid lubricants for advanced aircraft engines. [Washington, DC]: National Aeronautics and Space Administration, 1992.

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Kay, Antony L. Junkers aircraft and engines, 1913-1945. London: Putnam Aeronautical Books, 2004.

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North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Test cases for computation of internal flows in aero engine components. Neuilly sur Seine, France: AGARD, 1990.

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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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L, McKinley James, ed. Aircraft powerplants. 5th ed. New York: Gregg Division, McGraw-Hill, 1985.

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G, Holder William. Full power: Aircraft engines that made history. Charlottesville, VA: Howell Press, 2001.

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British piston aero-engines and their aircraft. Shrewsbury, England: Airlife, 1994.

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Book chapters on the topic "Aircraft engines"

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El-Sayed, Ahmed F. "Turbine-Based Engines: Turbojet, Turbofan, and Turboramjet Engines." In Fundamentals of Aircraft and Rocket Propulsion, 403–529. London: Springer London, 2016. http://dx.doi.org/10.1007/978-1-4471-6796-9_6.

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El-Sayed, Ahmed F. "Piston Engines and Propellers." In Fundamentals of Aircraft and Rocket Propulsion, 219–314. London: Springer London, 2016. http://dx.doi.org/10.1007/978-1-4471-6796-9_4.

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El-Sayed, Ahmed F. "Performance Parameters of Jet Engines." In Fundamentals of Aircraft and Rocket Propulsion, 161–218. London: Springer London, 2016. http://dx.doi.org/10.1007/978-1-4471-6796-9_3.

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El-Sayed, Ahmed F. "Pulsejet, Ramjet, and Scramjet Engines." In Fundamentals of Aircraft and Rocket Propulsion, 315–401. London: Springer London, 2016. http://dx.doi.org/10.1007/978-1-4471-6796-9_5.

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Nagappa, Rajaram, Sankarkumar Jeyaraman, and C. Kishore Kumar. "Design and Structures of Aircraft Engines." In Aerospace Materials and Material Technologies, 279–303. Singapore: Springer Singapore, 2016. http://dx.doi.org/10.1007/978-981-10-2143-5_14.

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El-Sayed, Ahmed F. "Shaft Engines Turboprop, Turboshaft, and Propfan." In Fundamentals of Aircraft and Rocket Propulsion, 531–88. London: Springer London, 2016. http://dx.doi.org/10.1007/978-1-4471-6796-9_7.

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Chapman, C. John. "The Reduction of Sound from Aircraft Engines." In UK Success Stories in Industrial Mathematics, 117–23. Cham: Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-25454-8_15.

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Witcomb, R. C., P. J. C. Skitt, and P. D. Hewitt. "The Adaptive Acoustic Monitoring of Aircraft Engines." In COMADEM 89 International, 194–98. Boston, MA: Springer US, 1989. http://dx.doi.org/10.1007/978-1-4684-8905-7_32.

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Hazan, Aurélien, Michel Verleysen, Marie Cottrell, and Jérôme Lacaille. "Trajectory Clustering for Vibration Detection in Aircraft Engines." In Advances in Data Mining. Applications and Theoretical Aspects, 362–75. Berlin, Heidelberg: Springer Berlin Heidelberg, 2010. http://dx.doi.org/10.1007/978-3-642-14400-4_28.

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Gauthier, G., G. Bessenay, and Y. Honnorat. "CMC Evaluation for Use in Military Aircraft Engines." In 4th International Symposium on Ceramic Materials and Components for Engines, 970–84. Dordrecht: Springer Netherlands, 1992. http://dx.doi.org/10.1007/978-94-011-2882-7_108.

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Conference papers on the topic "Aircraft engines"

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Tanner, G. F. "An integrated engine health monitoring system for gas turbine aero-engines." In Aircraft Airborne Condition Monitoring. IEE, 2003. http://dx.doi.org/10.1049/ic:20030005.

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DRUZHININ, L., and M. MOLCHANOVA. "Combined cycle aircraft engines." In 27th Joint Propulsion Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1991. http://dx.doi.org/10.2514/6.1991-2377.

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Tanis, Peter G. "Heating Aircraft Reciprocating Engines." In General, Corporate & Regional Aviation Meeting & Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1999. http://dx.doi.org/10.4271/1999-01-1568.

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Vogt, Robert L. "Advanced Aircraft Engines Under 7MW." In ASME 1994 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1994. http://dx.doi.org/10.1115/94-gt-241.

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Advanced turboprop/turboshaft aircraft engines now under development will out perform the current fleet in specific power, specific weight and specific fuel consumption. These new engines will have lower costs per unit power in constant dollars and will have considerably reduced life-cycle-costs. This paper discusses the trade-offs involving one and two spools and the relative importance of inefficiencies. Current development activities are identified and references cited from the underlying enabling core engine program.
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Pasini, S., U. Ghezzi, R. Andriani, and L. Ferri. "Heat recovery from aircraft engines." In 35th Intersociety Energy Conversion Engineering Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2000. http://dx.doi.org/10.2514/6.2000-2901.

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Dinesh Kumar, U., J. Crocker, and J. Knezevic. "Evolutionary maintenance for aircraft engines." In Annual Reliability and Maintainability. Symposium. 1999 Proceedings (Cat. No.99CH36283). IEEE, 1999. http://dx.doi.org/10.1109/rams.1999.744098.

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Viassolo, Daniel E., Shreeder Adibhatla, Brent J. Brunell, John H. Down, Nathan S. Gibson, Aditya Kumar, H. Kirk Mathews, and Lisa D. Holcomb. "Advanced Estimation for Aircraft Engines." In 2007 American Control Conference. IEEE, 2007. http://dx.doi.org/10.1109/acc.2007.4283155.

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Ming, Li, Wang Peng, Shan Xingjian, and Wang Lulu. "Reliability allocation for aircraft engines." In 2017 Prognostics and System Health Management Conference (PHM-Harbin). IEEE, 2017. http://dx.doi.org/10.1109/phm.2017.8079162.

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Pegors, Douglas E. "Advanced Allison Small Turboprop Engines." In General Aviation Aircraft Meeting and Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1987. http://dx.doi.org/10.4271/871055.

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Mount, Robert E., and Gaston Guaroa. "Stratified Charge Rotary Engines for Aircraft." In ASME 1988 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1988. http://dx.doi.org/10.1115/88-gt-311.

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Substantial progress has been made over the past two years in the technological status and production aspects of Stratified Charge Rotary Engines, a new propulsion technology for aircraft of the 1990’s. A 400 HP aircraft engine, designed in cooperation with Avco-Lycoming (during late 1986) is currently undergoing testing at John Deere’s Rotary Engine Division. Current status and design features are reported in this paper and related to overall research and technology enablement efforts toward several families of advanced liquid cooled, turbocharged and intercooled engines over a wide power range for commercial general aviation. Capabilities for high altitude, long endurance, military unmanned aircraft missions are examined. Application to fixed and rotary wing aircraft are planned.
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Reports on the topic "Aircraft engines"

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Shockey, Donald A., Takao Kobayashi, Naoki Saito, Jean-Marie Aubry, and Alberto Grunbaum. Fractographic Analysis of High-Cycle Fatigue in Aircraft Engines. Fort Belvoir, VA: Defense Technical Information Center, January 2000. http://dx.doi.org/10.21236/ada386670.

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Shumway, L. A. Characterization of Jet Engine Exhaust Particulates for the F404, F118, T64, and T58 Aircraft Engines. Fort Belvoir, VA: Defense Technical Information Center, March 2002. http://dx.doi.org/10.21236/ada405470.

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Gerstle, Tom, and Mark D. Wade. Clean Air Act Emission Testing of the T-38C Aircraft Engines. Fort Belvoir, VA: Defense Technical Information Center, September 2002. http://dx.doi.org/10.21236/ada411925.

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Micallef, Roger A., and Alan T. Squires. Reclamation of Used MIL-L-23699 Lubricants for Reuse in Military Aircraft Turbine Engines. Fort Belvoir, VA: Defense Technical Information Center, November 1987. http://dx.doi.org/10.21236/ada190859.

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Arsenlis, Athanasios, and John Allison. Integrated Computational Materials Engineering (ICME) Tools for Optimizing Strength of Forged Al-Li Turbine Blades for Aircraft Engines Final Report CRADA No. TC02238.0. Office of Scientific and Technical Information (OSTI), September 2017. http://dx.doi.org/10.2172/1425447.

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Arsenlis, A., and J. Allison. Integrated Computational Materials Engineering (ICME) Tools for Optimizing Strength of Forged Al-Li Turbine Blades for Aircraft Engines Final Report CRADA No. TC02238.0. Office of Scientific and Technical Information (OSTI), March 2021. http://dx.doi.org/10.2172/1774219.

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Bennett, M. V., and J. M. Bennett. Aircraft Engine/APU Fire Extinguishing System Design Model (HFC-125). Fort Belvoir, VA: Defense Technical Information Center, May 1997. http://dx.doi.org/10.21236/ada373212.

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Gerstle, Thomas, Peter Virage, Mark Wade, and Larry Kimm. Aircraft Engine and Auxiliary Power Unit Emissions Testing: Volume 1, Executive Summary. Fort Belvoir, VA: Defense Technical Information Center, March 1999. http://dx.doi.org/10.21236/ada361474.

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Johnson, Alan M. Optical Fire Detector Testing in the Aircraft Engine Nacelle Fire Test Simulator. Fort Belvoir, VA: Defense Technical Information Center, March 1988. http://dx.doi.org/10.21236/ada197974.

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Vance, John M. AFRAPT Program at Texas A and M University Research for Advanced Aircraft Engine Structures. Fort Belvoir, VA: Defense Technical Information Center, October 1991. http://dx.doi.org/10.21236/ada247040.

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