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Journal articles on the topic 'Aircraft engines'
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1
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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Lewitowicz, Jerzy, Mirosław Kowalski, and Andrzej Żyluk. "Modern Diagnostics of Aircraft Gas Turbine Engines – Some Selected Issues / Nowoczesna Diagnostyka Lotniczych Silników Turbinowych - Wybrane Zagadnienia." Journal of KONBiN 29, no. 1 (December 1, 2014): 33–40. http://dx.doi.org/10.2478/jok-2014-0004.
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Abstract In aeronautics, the question of maintaining the highest possible level of flight safety is the most crucial issue. This is the reason why the scientists, engineers, and aerospace/aviation engineering staff keep searching for ever newer and more reliable methods of increasing the safety level. Therefore, new methods - primarily nondestructive ones - to diagnose aircraft turbine engines are looked for. These methods are expected to prove useful for the real-time monitoring of actual health of the engine and its assemblies. The paper has been intended to outline the most recent methods of diagnosing aircraft turbine engines, including the computed tomography methods as applied to assess health/maintenance status of turbine blades, for the phase mapping of increments in the engine’s rotational speed, to diagnose health/maintenance status of the compressor’s 1st stage rotor blades in pure jets. Other methods discussed are, e.g. vibroacoustic and tribological ones
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Tamargazin, Aleksandr, and Liudmyla Pryimak. "NEURAL NETWORK INTERPOLATION PARAMETERS OF A MULTI-MODE DYNAMIC MODEL OF THE AIRCRAFT ENGINE." Aerospace technic and technology, no. 7 (August 31, 2020): 98–104. http://dx.doi.org/10.32620/aktt.2020.7.14.
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The foundations of the concept of creation of intelligent aircraft engine control systems based on the decomposition of control processes within the architecture of open information systems are considered. Unlike well-known approaches, the suggested approach allows achieving the management goal based on the principle of minimum entropy by redistributing system resources in conditions of their shortage, as well as adapting system characteristics when changing the management situation based on self-learning and self-organization of intelligent control systems. Based on an analysis of the development trends of aircraft engines, as well as development trends of production and technological systems, including the creation of new composite materials and new technologies for the manufacture and control of parts and components of aircraft engines, the intellectualization of their automatic control systems is discussed. Moreover, the development trends of aircraft engine control systems are considered from the development of their structures, functions, properties, and abilities for new qualitative changes. The article gives the general characteristics and the main directions of the design of intelligent control systems for aircraft engines as complex technical objects. The problem of designing nonlinear dynamic models of aircraft engines using artificial neural networks is discussed. The statement of this problem and possible approaches to its solution are being formed. The results of the neural network identification of an aircraft engine are compared using the least-squares method. Such a technique for designing a model of aircraft engines makes it possible to indirectly calculate engine coordinates inaccessible to measurement - traction, fuel consumption, etc. The suggested approach allows calculation of the design of neural networks simulating aircraft engines at each step using standard procedures, which makes it possible to automate the creation of neural networks. To reduce the computation time, it is suggested using the optimization algorithms taking into account changes in the state entropy. This simplifies the implementation of the neural network model of an aircraft engine in real time as part of an onboard computer complex.
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Fryś, Andrzej. "Aircraft Diesel engines CENTURION 1,7 i 4,0." Combustion Engines 120, no. 1 (February 1, 2005): 50–53. http://dx.doi.org/10.19206/ce-117411.
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Contemporary land transportation including locomotives, trucks, buses, coaches as well as passenger cars are propelled with a diesel engine. Diesel engines are widely appplied in marine transportation and aviation. The article is a presentation of the history of development of aviation engines and a showcase of the JUMO and CENTURION engines.
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Sabaruddin, Ainul Aniyah, Surjatin Wiriadidjaja, Dayang Laila Abang Abdul Majid, Harijono Djojodihardjo, and Mohamed Tarmizi Ahmad. "An Investigation on the Effect of Variable Valve Timing on Piston Engine for Lightweight Aircraft." Applied Mechanics and Materials 225 (November 2012): 245–49. http://dx.doi.org/10.4028/www.scientific.net/amm.225.245.
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As the Lycoming engine had failed its attempt on using variable valve timing for aircraft piston engine back in 1940s, the idea of the technology was abandoned as the turbines were then introduced in the aviation for better performance and greater power. Since piston engines produce smaller power efficiently in the low speed than turbine engines, they are presently still practically used in most of lightweight aircraft. With the use of a variable valve timing mechanism, it may help to increase the amount of air inlet and to provide more power output with lesser fuel consumption. With the use of this new valve system, improvements in the performance of automobile engines have been recorded. The indicated improvements, however, are limited to automobile engines running with high revolutions only. Engine simulation program was run in this investigation as an attempt to predict engine performances that are appropriate for lightweight aircraft.
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Pawlak, Małgorzata, and Michał Kuźniar. "Determination of CO2 Emissions for Selected Flight Parameters of a Business Jet Aircraft." Journal of KONES 26, no. 3 (September 1, 2019): 155–63. http://dx.doi.org/10.2478/kones-2019-0069.
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Abstract In the last two decades, there has been observed a noticeable increase in the popularity and availability of air transport services, including regional ones. This intensive development of transport is accompanied by an increase in the adverse impact to the environment, increases noise level, and exhausts emissions, despite the modification and modernization of engines. Determining the emission for regional flights takes into account the specificity of the aircrafts design, such as the size of the aircraft and the performance of the engines. In this article, an attempt was made to determine the CO2 emissions of a business jet flying from Gdansk to Rzeszow. The methodology of the research (the method of calculating emissions based on fuel consumption) and the performance characteristics of the aircraft engines have been described. In the first part of the article, the speed-altitude characteristics of the DGEN-380 engine for different cruise parameters were determined using the virtual engine test bench WESTT CS/B. These characteristics have enabled the engine to match the flight characteristics (altitude, speed). For specific flight parameters, the thrust and fuel consumption were determined. On this basis, for the adopted trajectory and flight time of an aircraft equipped with two DGEN-380 engines, total fuel consumption and CO2 emission factors and values in CRUISE phase was determined with regard to the wind speed and direction. The obtained results were illustrated graphically and discussed.
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Rogulenko, Tatyana, and Oleg Smolyakov. "Methods of economic efficiency assessment of the operation stage of the aviation engines life cycle." Upravlenie 7, no. 1 (May 7, 2019): 91–95. http://dx.doi.org/10.26425/2309-3633-2019-1-91-95.
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The relevance of the evaluation of the technical and economic efficiency of aircraft engines and one of its main indicators – direct operating costs has been noted in the article. Their place in ensuring the competitiveness of aircraft in the relevant sectors of the market has been established. One of the main indicators of the efficiency of aviation equipment is its technical and economic evaluation. Tough competition, existing, at present between foreign players in the aircraft industry and difficulties of maintaining their positions to Russian aircraft manufacturers have been designated. The features of existing foreign and domestic methods and approaches to the economic evaluation of aircraft engines have been noted, and their comparative analysis has been carried out. Problematic issues when considering the efficiency of the aircraft as a whole and the difficulties of technical and economic assessment of the aircraft engine as a subsystem of the aircraft have been revealed. The need has been indicated to take into account the condition under which, if we consider the aircraft as a whole, the efficiency of its operation is mainly determined by the perfection of the engines of the power plant. It has been noticed, that the engine can act on the market as an independent product, having a market price. But, at the same time, it is necessary to take into account that the aircraft engine is a subsystem of the aircraft, therefore, it follows to carry out its technical and economic assessment, taking into account, if possible, the characteristics of the aircraft and the characteristics of its operation, which is a difficult task and this is a necessary procedure in case of economic evaluation. The need for careful selection of performance indicators, contributing to a reliable assessment of the competitiveness of the proposed product has been designated. At the same time, it is necessary to adhere to a certain framework, namely when comparing competing engines, the technical and economic evaluation of aircraft engines should be carried out under the same conditions regarding the operation and maintenance of the aircraft as a whole. Moreover, engines should have similar indicators: dimensionality, installation on a plane of the same class, etc.
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Lister, A. "II — A. Lister." Journal of Navigation 38, no. 3 (September 1985): 431–35. http://dx.doi.org/10.1017/s0373463300032793.
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Several years ago, when Airbus Industrie launched their twin-engined A 300 Airbus, it became apparent that a new generation of long-range aircraft was about to add a different facet to the shape of international air travel. The enormous power available from the big fan engines coming into use meant that adequate performance was available even when an engine failure meant the loss of half the installed thrust. Coupled to this was a standard of fuel economy and tank capacity which meant that the new aircraft were capable of operating over ranges far in excess of those previously attained by twin-engined aircraft.
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Ismail, I. H., and F. S. Bhinder. "Simulation of Aircraft Gas Turbine Engines." Journal of Engineering for Gas Turbines and Power 113, no. 1 (January 1, 1991): 95–99. http://dx.doi.org/10.1115/1.2906536.
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The paper describes a computer program to simulate aircraft gas turbine engines. The program has been written for IBM-compatible microcomputers and is modular in its appraoch. Either analytical equations or detailed performance characteristics of individual components are used to model the steady-state operation of the complete engine.
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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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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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Khrulev, Alexander, and Iryna Saraievа. "EXPERT STUDIES OF VIOLATIONS OF THE OPERATING CONDITIONS OF AUTOMOBILE ENGINES WHEN USING THEM IN AVIATION." Vehicle and electronics. Innovative technologies, no. 19 (May 1, 2021): 53–59. http://dx.doi.org/10.30977/veit.2021.19.0.53.
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Problem. The features of the design and operation of piston engines in general aviation are considered. Comparative analysis of design features and parameters of automobile and aircraft engines is carried out. It is shown that car engines, despite the high technical level achieved at the beginning of the 21st century, do not technically meet aviation requirements. At the same time, engines created on the basis of automobiles through their deep modernization meet aviation requirements, however, modernization and adaptation of a standard automobile engine to aviation use in terms of costs compared to the creation of a new engine. Purpose. Carry out research on the failure of automobile engines used in light aviation. Methodology. Rough calculations of the service life of an automobile engine were made based on standard driving tests and a flight plan. According to the results of calculations, it has been established that the resource of a standard automobile engine in aviation is reduced many times due to prolonged operation at high loads and rotational speed that are not characteristic of ordinary automotive applications. Results. Experimental data have been obtained on the actual failure of standard automobile engines in aviation during the operating time, significantly less resource of aircraft engines of well-known brands. Based on the results of the study, it was concluded that the use of general aviation automobile engines is economically ineffective due to a short resource and insufficient reliability. Originality. Modern automobile engines, despite their technical perfection, cannot be used in aviation, since they do not correspond to aviation operating conditions. At the same time, adaptation of automobile engines to aviation applications is possible, but requires significant design changes, which makes their single use, as a rule, technically impractical and economically ineffective. Practical value. Due to the fact that saving on an aircraft engine is unacceptable from the point of view of flight safety, the aviation use of automobile engines without special modernization carries excessive risks of failures and their consequences. As a result, serial aircraft engines Lycoming, Continental, Jabiru, ULPower, Rotax, Limbach and others have virtually no alternative in general aviation.
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Wilson, Eugene E. "AMERICAN AIRCOOLED AIRCRAFT ENGINES." Journal of the American Society for Naval Engineers 39, no. 3 (March 18, 2009): 533–43. http://dx.doi.org/10.1111/j.1559-3584.1927.tb02029.x.
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TAKAKSA, Yoshio. "Contemporary aircraft piston engines." Journal of the Japan Society for Aeronautical and Space Sciences 35, no. 403 (1987): 370–78. http://dx.doi.org/10.2322/jjsass1969.35.370.
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Ovchinnikov, V. V., and Yu V. Petrov. "Study of running engines inertial and gyroscopic properties influence on the dynamic system engine – pylon – wing structural capabilities." Civil Aviation High Technologies 23, no. 3 (July 3, 2020): 63–72. http://dx.doi.org/10.26467/2079-0619-2020-23-3-63-72.
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A modern large-sized aircraft dynamic properties analysis, determined by the specificity of its layout scheme, demonstrates that the engines on under the wing elastic pylons lightly damped oscillations cause a number of undesirable phenomena, including intense accumulation of fatigue damage of the pylon-to-the-wing attachment, in fact in the area of engine installation in the pylon and the wing. The results of theoretical and experimental research show that with some engine attachment to the pylon structural modification it becomes possible to use the engines inertial and gyroscopic properties to absorb these oscillations. In this case, the motor tones damping coefficients increase by an order of magnitude or even more, so the gyroscopic coupling of elastic vibration tones is realized. With the rational choice of the additional parameters of elastic and dissipative bonds in the engine attachments it is possible to affect the aircraft wing and engines aero elastic vibrations effectively, which has a significant effect on the aircraft elements structural capabilities. A mathematical model of aero elasticity (MMAE) with respect to the kinetic moment of the engine rotors and specially designed units for attaching the engines to the pylons was developed in order to study the influence and the selection of rational elastic-dissipative parameters of the pylons-under-the-wing aircraft engine mounts. The method of predetermined basic forms is used for the aircraft with running engines on the pylons MMAE synthesis. The given forms are considered as the aircraft basic structure forms natural vibrations in the void. This work treats the engine nacelle and the rotor as absolutely rigid bodies, the elasticity of the rotor to the nacelle attachment is neglected. The pylon is modeled by an elastic beam, and the elastic and dissipative properties of the pylon-to-the-wing and the engine-to-the-pylon attachments are correspondingly by elastic-dissipative bonds. Schematic diagrams of the engine to the pylon attachments are proposed. The results of the study devoted to the influence of the proposed attachment points modifications on the load and integral strength characteristics of the main structural elements of the engine – pylon – wing dynamic system on the example of an An-124 aircraft are presented. The practical implementation of the proposed solutions aimed to reduce the level of fatigue damage to structural elements of the aircraft feasibility is proved.
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Yu, Bing, Wenjun Shu, and Can Cao. "A Novel Modeling Method for Aircraft Engine Using Nonlinear Autoregressive Exogenous (NARX) Models Based on Wavelet Neural Networks." International Journal of Turbo & Jet-Engines 35, no. 2 (May 25, 2018): 161–69. http://dx.doi.org/10.1515/tjj-2017-0005.
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Abstract A novel modeling method for aircraft engine using nonlinear autoregressive exogenous (NARX) models based on wavelet neural networks is proposed. The identification principle and process based on wavelet neural networks are studied, and the modeling scheme based on NARX is proposed. Then, the time series data sets from three types of aircraft engines are utilized to build the corresponding NARX models, and these NARX models are validated by the simulation. The results show that all the best NARX models can capture the original aircraft engine’s dynamic characteristic well with the high accuracy. For every type of engine, the relative identification errors of its best NARX model and the component level model are no more than 3.5 % and most of them are within 1 %.
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Myers, Bradford A., Edward D. White, Jonathan D. Ritschel, and R. David Fass. "Quantifying the Effects of Aircraft Engine Upgrades on Operating and Support Costs." Optimizing Operations 28, no. 97 (July 1, 2021): 320–43. http://dx.doi.org/10.22594/10.22594/dau.20-862.28.03.
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For fixed wing aircraft within the U.S. Air Force, Operating and Support (O&S) costs encompass a large portion of total life-cycle costs. O&S costs include fuel, maintenance, and engine upgrades. To the authors’ knowledge, no study to date has attempted to empirically quantify the realized effects of new aircraft engines on sustainment costs. Utilizing the Air Force Total Ownership Cost database, they focused on new engines appearing on the C-5s, C-130s, and C-135s. Although narrow in scope, results suggest newer engines have lower fuel costs. Maintenance costs for newer engines were not consistently higher or lower than the engines they replaced, although Contractor Logistics Support was not tracked by engine in this study. We found that savings from improved fuel efficiency tended to be greater than a potential increase in maintenance costs.
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Jamil, Mohd Khairuladha, Mohd Ezwani Kadir, Mohamad Zikri Zainol, Abu Hanifah Abdullah, and Abu Zaid Bakar. "Preliminary Development of Electric Motorcycle Engine for Sport Aviation Vehicles." Applied Mechanics and Materials 225 (November 2012): 250–54. http://dx.doi.org/10.4028/www.scientific.net/amm.225.250.
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Flying activities of sport aviation vehicles normally use Internal Combustion Engines (ICE) for their powerplant, which emits Carbon Dioxide (CO2) and also produces noise. Environmental issues regarding harmful gas emission and noise may restrict the sport aviation activities and resulting in reduction of interest in flying as a sport activity. The feasible solution for this issue is by replacing the Internal Combustion Engines (ICE) with Electric Engines on all sport flying vehicles. The Modenas CTric Electric Engines was tested to measure the parameters required by comparable Internal Combustion Engine used by sport aviation flyers. Other parameters; engine endurance, temperature and performance, were also tested. The bench test was conducted using specially design test rig. The results show that there is a possibility for the Modenas CTric Motorcycles Electric Engine used as an alternate source of powerplant for paramotors and microlight aircraft. However, there is penalty on the vehicle payloads due to weight of the battery. Lighter battery technology integration is to be developed to reduce the weight of the flight vehicles. This study serves as a platform for further work in electric engine technology for commercial aircraft application. Availability of green engine (no emission and noise output) will generate more interest in sport aviation activities and prepare for the future commercial Electric Engine aircraft application.
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Chumachenko, Olha. "Scientific and research work of Zaporizhzhia aircraft engine builders in the 1970’s." History of science and technology 11, no. 1 (June 26, 2021): 10–25. http://dx.doi.org/10.32703/2415-7422-2021-11-1-10-25.
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On the basis of a wide base of sources, the article highlights and analyzes the development of research work of aircraft engine companies in Zaporizhzhia during the 1970s. The existence of a single system of functioning of the Zaporizhzhia production association “Motorobudivnyk” (now the Public Joint Stock Company “Motor Sich”) and the Zaporizhzhia Machine-Building Design Bureau “Progress” (now the State Enterprise “Ivchenko – Progress”) is taken into account. The directions of research work that were peculiar to the specified period are established. These were inventive activities, development of technological processes, increasing the reliability and durability of gas turbine engines, automation and mechanization of production, cooperation with industry firms in other countries, and cooperation with research institutions. The development of a scientific-theoretical and technical basis for the production of aircraft engines is comprehensively assessed. Its dependence on structural subdivisions, which at the aircraft engine enterprises were the department of scientific and technical information, the Information and Computing Center, the department of patenting, innovation and invention of the plant, was determined. They were engaged in the accumulation, generalization and dissemination among specialists of their own and borrowed experience of both past and present. The activity of the scientific and technical council, which included leading specialists of Zaporizhia aircraft engine companies, was monitored. Factors that contributed to the revival of research in the second half of the 1970’s were identified. Among them, the leading place belongs to the creation and production of D-36 and D-18T aircraft engines. The design advantages of these engines are described. Some shortcomings and miscalculations made during their design are taken into account. Methods and measures aimed at overcoming the difficulties associated with the design, manufacture, operation and repair of aircraft engines are summarized. The research is based on the following methods: actualization, comparative-historical, problem-chronological, multifactor analysis, principles of historicism and objectivity.
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Balicki, Włodzimierz, Paweł Głowacki, Stefan Szczecinski, Ryszard Chachurski, and Jerzy Szczeciński. "Effect of the Atmosphere on the Performances of Aviation Turbine Engines." Acta Mechanica et Automatica 8, no. 2 (August 15, 2014): 70–73. http://dx.doi.org/10.2478/ama-2014-0012.
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Abstract The paper presents how the parameters defining the state of the atmosphere: pressure, temperature, humidity, are affecting performance of the aircraft turbine engines and their durability. Also negative impact of dust pollution level is considered as an important source of engine deterioration. Article highlights limitation of the aircraft takeoff weight (TOW) and requirements for length of the runways depending on weather condition changes. These problems stem from the growing “demand” of gas turbine engines for an air. The highest thrust engines have air mass flow more than 1000 kg/s. Engine inlet ice formation is presented as a result of weather conditions and inlet duct design features.
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OPARA, Tadeusz. "History and future of turbine aircraft engines." Combustion Engines 127, no. 4 (November 1, 2006): 3–18. http://dx.doi.org/10.19206/ce-117335.
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This paper discusses stages of development of air propulsion from piston engines up to three-rotor turbine ones. Limitations in speed and altitude of flight, caused by traditional system of a piston engine and an airscrew, became an impulse to conduct research on jet propulsion. Accomplishments of the designers of the first jet-propelled engines: F. Whitle and H. von Ohain are a reflection of rivalry in this field. In the second half of the 20th centur y turbine propulsion (turbojet, turboprop and helicopter engines) dominated air force and civil aviation. In 1960 the age of turbofans began, owing to better operating properties and electronic and digital systems of automatic regulation. Further development of turbine engines is connected with application of qualitatively new materials (particularly composites), optimization of the shape of compressor and turbine blades and technologies of their production. The paper discusses design changes decreasing the destructive effects of foreign matter suction and indicates the possibility of increasing the maneuverability of airplanes by thrust vectoring. Finally, development prospects of turbine propulsion are analyzed.
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Spicer, C. W., M. W. Holdren, D. L. Smith, D. P. Hughes, and M. D. Smith. "Chemical Composition of Exhaust From Aircraft Turbine Engines." Journal of Engineering for Gas Turbines and Power 114, no. 1 (January 1, 1992): 111–17. http://dx.doi.org/10.1115/1.2906292.
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This paper reports measurements of the chemical composition of exhaust from two aircraft turbine engines. The two engines are the F101, used on the B-1B aircraft, and the F110, used on the F-16C and F-16D aircraft. Samples were collected from each engine using a probe positioned just behind the exhaust nozzle. The measurements reported here were made at four power settings from idle to intermediate power. Exhaust composition measurements included carbon monoxide, carbon dioxide, nitrogen oxides, total hydrocarbons, and individual organic species. The principal focus of this paper is on the detailed organic species results.
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Grabowski, Łukasz, Konrad Pietrykowski, and Paweł Karpiński. "Energetic Analysis of the Aircraft Diesel Engine." MATEC Web of Conferences 252 (2019): 05012. http://dx.doi.org/10.1051/matecconf/201925205012.
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The analysis of the distribution of thermal energy generated during the combustion process in internal combustion engines and the estimation of individual losses are important regarding performance and efficiency. The article analyses the energy balance of the designed two-stroke opposed piston diesel engines with offset, i.e. the angle by which the crankshaft at the side of exhaust ports is ahead of the crankshaft at the side of intake ports. Based on the developed zero-dimensional engine model, a series of simulations were performed in steady-state conditions using the AVL BOOST software. The values of individual energy losses, including cooling losses, exhaust gas losses, friction losses were obtained. The influence of decreasing and increasing the offset on the performance of the tested engine was analysed.
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Feilden, G. B. R. "Lionel Haworth. 4 August 1912 — 12 April 2000." Biographical Memoirs of Fellows of the Royal Society 51 (January 2005): 195–220. http://dx.doi.org/10.1098/rsbm.2005.0013.
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Lionel Haworth was one of the leading aero engine designers in the world. After initial training in 1934 to 1936 with the Associated Equipment Company of Southall–the builders of London's buses—he moved to Rolls–Royce, Derby, where he worked until 1963 when he transferred to the Bristol Siddeley engine company, which merged with Rolls–Royce in 1966. Throughout his career he was very much a 'hands on' engineer who insisted in keeping close to work on any new engine for which he was responsible. He worked on Rolls–Royce engines for aircraft ranging from the Meteor to Concorde, his crowning achievement in Derby being the Dart engine, which was an extremely successful, admirably simple turboprop that powered the Vickers Viscount and 11 other aircraft and had a wide influence on the future of civil aviation around the world. In Bristol, as Chief Designer, he took overall responsibility for the Concorde, Harrier and Tornado as well as all other aero engines being developed and built by Rolls–Royce, Bristol, between 1963 and 1977.
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Langston, Lee S. "Gears Steer New Engine Designs." Mechanical Engineering 139, no. 09 (September 1, 2017): 54–55. http://dx.doi.org/10.1115/1.2017-sep-7.
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This article reviews the development of geared turbofan (GTF) engines. GTF engines have a hub-mounted epicyclic gearbox that drives the front-mounted fan at lower rotational speeds than the engine turbine section that powers the fan. The turbine driving the fan is most efficient at high-rotational speeds. The fan operates most efficiently and creates less noise at lower rpm. The operating gear reduction ratio also permits increasing the engine’s bypass ratio with larger fans. Gear trains are one of the oldest known machines, and none is more closely identified by the general public with the profession of mechanical engineering. Pratt & Whitney is in production of their first generation of GTF engines in the 18,000–30,000 lbt range, which power twin engine single-aisle, narrow body 70–200 passenger aircraft. The GTF combines existing jet engine technology with the well-established mechanical engineering technology of gears.
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Rohacs, Jozsef, Istvan Jankovics, Istvan Gal, Jerzy Bakunowicz, Giuseppe Mingione, and Antonio Carozza. "Small Aircraft Infrared Radiation Measurements Supporting the Engine Airframe Aero-thermal Integration." Periodica Polytechnica Transportation Engineering 47, no. 1 (March 12, 2018): 51–63. http://dx.doi.org/10.3311/pptr.11514.
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The large, EU Supported ESPOSA (Efficient Systems and propulsion for Small Aircraft) project has developed new small gas turbines for small aircraft. One of the important tasks was the engine - airframe aero-thermal radiation integration that included task of minimizing the infrared radiation of the small aircraft, too. This paper discusses the factors influencing on the aircraft infrared radiation, its possible simulation and measurements and introduces the results of small aircraft infrared radiation measurements. The temperature of aircraft hot parts heated by engines were determined for validation of methodology developed and applied to engine - aircraft thermal integration.
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BERBENTE, Sorin, Irina-Carmen ANDREI, Gabriela STROE, and Mihaela-Luminita COSTEA. "Topical Issues in Aircraft Health Management with Applications to Jet Engines." INCAS BULLETIN 12, no. 1 (March 1, 2020): 13–26. http://dx.doi.org/10.13111/2066-8201.2020.12.1.2.
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Aircraft Health Management Technology for jet engines represents a very important problem, since it develops a large impact on reducing the engine life cycle costs, improving the fuel efficiency, increasing the engines durability and life cycle. This technology is high-end and, in order to enable an improved level of performance that far exceeds the current one, propulsion systems must comply with terms of reducing harmful emissions, maximizing fuel efficiency and minimizing noise, while improving system’s affordability and safety. Aircraft Health Management Technology includes multiple goals of aircraft propulsion control, diagnostics problems, prognostics realized, and their proper integration in control systems. Modern control for Aircraft Health Management Technology is based on improved control techniques and therefore provides improved aircraft propulsion system performances. The study presented in this paper approaches a new concept, of attractive interest currently, that is the intelligent control; in this context, the Health Management of jet engines is crucial, being focused on engine controllers which are designed to match certain operability and performance constraints. Automated Engine Health Management has the capacity to significantly reduce the maintenance effort and propulsion systems’ logistical footprint. In order to prioritize and resolve problems in the field of support engineering there are required more detailed data on equipment reliability and failures detection and management; the equipment design, operations and maintenance procedures and tooling are also very important.
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Hansen, L. D., G. D. Kucera, J. S. Clemons, and J. Lee. "Aircraft Gas Turbine Engine Fuel Pumping Systems in the 21st Century." Journal of Engineering for Gas Turbines and Power 119, no. 3 (July 1, 1997): 591–97. http://dx.doi.org/10.1115/1.2817025.
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Since their introduction, main engine fuel pumping systems for aircraft gas turbine engines have remained relatively unchanged. The main engine fuel pump has been an engine accessory gearbox driven, positive displacement pump (except for the Concorde), until recently when centrifugal pumps were introduced on Pratt-Whitney and General Electric military engines. This paper describes some of the issues that must be addressed as pumping system technology moves into the 21st century and gives a description of two programs that address these issues.
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Gryadunov, K. I., A. N. Kozlov, M. L. Nemchikov, and I. S. Mel’nikova. "AVIATION ENGINES DIAGNOSTICS BY ESTIMATING THE METAL CONTAMINATION IN OILS." Civil Aviation High TECHNOLOGIES 22, no. 3 (June 29, 2019): 35–44. http://dx.doi.org/10.26467/2079-0619-2019-22-3-35-44.
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Current trends of civil aviation development show a significant increase in the number of aircraft with aircraft piston engines. The Ministry of Transport of the Russian Federation is preparing a draft order on amendments to the Federal aviation rules for the preparation and performance of flights in civil aviation (FAP-128), which stipulate for simplified procedures of paid excursion flights implementation for light and ultralight aircraft and helicopters. It is obvious that this circumstance will significantly affect the expansion of the fleet of these aircraft. Accordingly, the state of piston engines operating on aviation gasoline value questions are becoming increasingly relevant. The current problems of aviation engines diagnostics by metal contents in oils are observed in the article. Their bugs, possible ways of solving this problems and bugs, actual developments in this direction are shown. The application examples of early diagnostic methods using the automated diagnostic complex “Prisma” are shown. The oil samples taken from An-2 aircraft АШ-62ИР piston engine analyses results attract the most interest. They show that with proper training of personnel the valuable information coming from the oil samples can be a source of important conclusions not only in aircraft engines accessories and assemblies state value, but also others systems, and also conclusions about the quality of fuel and lubricants used. Estimating the residual life method of the engine at various stages of its operating time on the metal content in the oils and the procedure for oil selecting, allowing to obtain reliable results, are suggested.
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Yildirim, Mustagime Tülin, and Bülent Kurt. "Aircraft Gas Turbine Engine Health Monitoring System by Real Flight Data." International Journal of Aerospace Engineering 2018 (2018): 1–12. http://dx.doi.org/10.1155/2018/9570873.
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Modern condition monitoring-based methods are used to reduce maintenance costs, increase aircraft safety, and reduce fuel consumption. In the literature, parameters such as engine fan speeds, vibration, oil pressure, oil temperature, exhaust gas temperature (EGT), and fuel flow are used to determine performance deterioration in gas turbine engines. In this study, a new model was developed to get information about the gas turbine engine’s condition. For this model, multiple regression analysis was carried out to determine the effect of the flight parameters on the EGT parameter and the artificial neural network (ANN) method was used in the identification of EGT parameter. At the end of the study, a network that predicts the EGT parameter with the smallest margin of error has been developed. An interface for instant monitoring of the status of the aircraft engine has been designed in MATLAB Simulink. Any performance degradation that may occur in the aircraft’s gas turbine engine can be easily detected graphically or by the engine performance deterioration value. Also, it has been indicated that it could be a new indicator that informs the pilots in the event of a fault in the sensor of the EGT parameter that they monitor while flying.
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Gloeckner, Peter, and W. Sebald. "A New Method of Calculating the Attainable Life and Reliability in Aerospace Bearings." European Journal of Engineering Research and Science 5, no. 6 (June 30, 2020): 745–50. http://dx.doi.org/10.24018/ejers.2020.5.6.1977.
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The aviation industry made significant progress improving reliability, efficiency and performance throughout the last decades. Especially aircraft engines and helicopter transmission systems contributed significantly to these improvements. The kerosene consumption decreased by 70 % and the CO2 emissions due to air transport decreased by 30 % per passenger kilometer within the last 20 years. Simultaneously, the flight safety was increased with aircraft engine in-flight-shut-downs as low as 1 ppm and „unscheduled engine removals” as low as 4 ppm. Flight safety is equal to the reliability of the systems in service. Failure of these systems directly leads to exposure of human life. Among the most critical aviation systems are aircraft engines including the rolling element bearings which support the rotors. A serious damage to the aircraft engine main shaft bearings during flight requires shout-down of the engine to avoid a further damage escalation subsequently leading to engine fire. Today, it is a requirement for aircraft to operate with one engine shut down. However, each in-flight-engine-shut-down typically is connected with flight diversion or abort and immediate landing. Inflight-shut-downs translate into increased risk for passengers and crew and substantial on cost. Therefore, rolling element bearings for aircraft engines are developed – similar to other aircraft engine components – targeting a reliability of nearly 100 % over an operation time of more than 10 000 hours prior to overhaul. To achieve this requirement despite the extreme operating conditions such as high speed and temperatures occurring in gas turbines, special high-performance materials are used for the rolling bearing components which are partially integrated in surrounding engine parts like shafts and housings. These special conditions - deviating from conventional industrial rolling element bearing applications - are currently not sufficiently considered in the standardized method of calculating the bearing life per ISO 281. A new method of calculating the attainable life of rolling elements bearing in aerospace applications is presented. This method considers the special aerospace conditions and materials and thus enables a higher reliability of the theoretical analysis and life prediction.
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Чумак, Оксана Анатольевна, and Виталий Григорьевич Харченко. "О ТРЕБОВАНИЯХ К ДОКУМЕНТАЦИИ ПО РЕМОНТУ АВИАЦИОННЫХ ДВИГАТЕЛЕЙ С МОДЕРНИЗАЦИЕЙ." Aerospace technic and technology, no. 8 (August 31, 2019): 152–57. http://dx.doi.org/10.32620/aktt.2019.8.22.
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The role of modernization of aircraft engines in the repair and the requirements for the design documentation. It is analyzed a set of repair documentation, which should include design repair and process documentation for repairs with product upgrades. Emphasis is placed on the repair design documentation, which includes drawings, specifications, diagrams containing data for the preparation of repair production, repair and control of the product after repair. These drawings, as a rule, contain only those images of the product, dimensions, maximum dimensional deviations, parts of the product, parts, circuit elements and additional data that are needed to carry out repairs and control of the product during and after repair. The differences of modernization from the repair of products of aircraft engines are established and the definition of repair with modernization is given. The purpose of the repair with the modernization of the aircraft engine is to obtain a new product modification (engine park). Engineers continue to improve the design of aircraft engines while pursuing, basically, two goals at once - reducing noise and reducing fuel consumption. While retaining all the advantages of the base engines, each subsequent modification of the engine is planned to implement the following new solutions: optimization of the blade shape, measures to expand the operating temperature range, the use of modern electrical systems, plasma ignition, fuel injection system with electronic control system, parts design and assembly units of light modern materials, reducing the size and more. The design documentation is an important link. These are graphic and text documents, which, complete or separately, determine the composition and design of the product and contain all the necessary data for monitoring, operation, and repair. The set of design documentation for a product or its part necessarily includes the main design document, which fully and unambiguously identifies this product and its composition.Repair with modernization is an improvement of the product, a change in the design following the requirements of modernity, which is one of the most important components of the transition to an effective market structure focused on customer satisfaction.
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Wang, Hao Xiang, and Hong Sen Yan. "An Adaptive Assembly Scheduling Approach in Knowledgeable Manufacturing." Applied Mechanics and Materials 433-435 (October 2013): 2347–50. http://dx.doi.org/10.4028/www.scientific.net/amm.433-435.2347.
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To address the uncertainty of production environment in aircraft engine assembly, an adaptive optimization scheduling algorithm is designed for an aircraft engine assembly line in knowledgeable manufacturing. A Q-learning adaptive scheduling model of aircraft engine assembly is built on the objective function of minimizing earliness penalty. Simulation experiments indicate that the proposed algorithm outperforms other scheduling rules much. Especially, better results are generally achieved with the increase in number of engines to show good adaptive performance.
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Antonopoulos, AK, RG Papagiannakis, and DT Hountalas. "Application of a diagnostic technique for evaluating the quality of the air–fuel mixture and the ignition quality of a spark-ignition reciprocating aircraft piston engine." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 232, no. 3 (December 20, 2016): 571–82. http://dx.doi.org/10.1177/0954410016683414.
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The performance characteristics of an aircraft piston engine are affected mainly by the air–fuel mixture quality (i.e. condition of the fuel injection system) and by the spark timing and spark duration (i.e. condition of ignition system). Thus, the present work focuses on investigating the effect of both fuel injection and spark ignition systems on performance characteristics of two aircraft piston engines which are of the same type but have overhauled by two different workshops. The investigation is conducted by applying an existing diagnostic technique, which is based on the simultaneous recording and processing of two electric signals: one corresponding to cylinder pressure and the second corresponding to the ignition system. The basic characteristics of the proposed methodology are simplicity and field applicability on engines of this type. A detailed experimental investigation has been conducted on the aforementioned two aircraft piston engines on a dedicated test bench. From the results, it is revealed that the proposed diagnostic methodology provides reliable information for the effect of both the ignition and fuel injection systems on engine performance characteristics. The results derived from the specific work enable the comparative evaluation of the engines and their ignition and fuel injection systems. Finally, based on this first investigation, the proposed methodology seems to be promising, because it can be easily applied on any type of spark-ignited engine and especially on aircraft piston engine, where due to its geometry and multicylinder nature, the application of lab techniques on the field is, if not impossible, extremely difficult.
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Dowling, A. P., and T. Hynes. "Towards a silent aircraft." Aeronautical Journal 110, no. 1110 (August 2006): 487–94. http://dx.doi.org/10.1017/s000192400000138x.
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Abstract We set a target for a ‘Silent’ aircraft to be imperceptible outside the airfield perimeter in an urban environment, and then address conceptual designs to meet this requirement. Avoiding some traditional aircraft noise sources requires a radical rethink about the configuration. An all-lifting design has many benefits, enabling a closer integration of airframe and engine than the traditional ‘tube and wing’. Low-noise design includes taking advantage of shielding of engine noise by the airframe; low-noise engines with large, low speed jets; an order of magnitude increase in absorption by liners; and operations for low-noise informing the design. Progress to date on the Silent Aircraft Initiative is presented, along with some conceptual aircraft and engine designs. The further work needed to develop these into viable future aircraft is discussed.
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Донець, О. Д., and В. П. Іщук. "КОНЦЕПЦІЯ СТВОРЕННЯ СИЛОВОЇ УСТАНОВКИ СІМЕЙСТВА РЕГІОНАЛЬНИХ ПАСАЖИРСЬКИХ ЛІТАКІВ АН-148/АН-158." Open Information and Computer Integrated Technologies, no. 84 (July 2, 2019): 50–63. http://dx.doi.org/10.32620/oikit.2019.84.02.
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The basic results of calculation and research works carried out in the process of creation of power unit of regional passenger airplanes’ family are given. The design features of the propulsion engines and engine of the auxiliary power plant are described. The aforementioned propulsion system includes propulsion engines D-436-148 and engine AI-450-MS of auxiliary power plant. In order to comply with the requirements of Section 4 of the ICAO standard (noise reduction of the aircraft in site), in part of ensuring the noise reduction of engines, when creating the power plant of the An-148/An-158 aircraft family, a single- and double-layer acoustic filler was used in the structure of the engine nacelle and air intake. The use of electronic system for automatic control of propulsion engines such as FADEC and its integration into the digital airborne aircraft complex ensured the operation of engines, included in the power plant provided with high specific fuel consumption, as well as increased the level of automation of the power plant control and monitoring, and ensured aircraft automation landing in ICAO category 3A. In addition, the use of the aforementioned electronic system, allowed to operate the power plant of the aircraft in accordance with technical status. The use of the AI-450-MS auxiliary power plant with an electronic control system such as FADEC, and the drive of the service compressor from a free turbine, eliminated the effect of changes in power and air takeoff, on the deviation of the engine from optimal mode, which also minimized the fuel consumption. The use of fuel metering system TIS-158, allowed to ensure control of its condition and assemblies, without the use of auxiliary devices, built-in control means. In the fire protection system, the use of the electronic control and monitor unit, as well as the use of digital serial code for the exchange of information between the elements of the system and the aircraft systems, has reduced the number of connections, which increased the reliability of the system and reduced its weight characteristics.
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Semenov, V. L., V. Yu Aleksandrov, A. N. Prokhorov, K. Yu Arefyev, and S. V. Kruchkov. "Methodological Aspects of Determining Thrust of Irrotational Air-Breathing Jet Engines in Bench and Flight Tests." Proceedings of Higher Educational Institutions. Маchine Building, no. 11 (716) (November 2019): 86–97. http://dx.doi.org/10.18698/0536-1044-2019-11-86-97.
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This article examines methodological aspects of the indirect calculation of thrust characteristics of irrotational air-breathing jet engines using telemetry data that can be obtained during high-speed aircraft flight tests. Specific features of determining thrust characteristics during bench and flight tests are described. Mathematical models are developed for data analysis and calculation of the thrust and the specific impulse of an irrotational air-breathing jet engine by internal parameters, as well as its effective thrust in integration with a high-speed aircraft. The proposed approaches are tested, and the developed mathematical models are validated according to the results of experimental bench tests of the thrust characteristics of irrotational air-breathing jet engines in integration with a model fuselage of a high-speed aircraft. Satisfactory convergence of the results of indirect and direct (experimental) force measurements is shown. The data obtained can be used for further development of the method and analysis of bench and flight tests of aircraft with irrotational air-breathing jet engines.
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MASAKI, Shoju. "Aircraft engines and composite materials." Journal of the Japan Society for Composite Materials 14, no. 1 (1988): 2–8. http://dx.doi.org/10.6089/jscm.14.2.
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Cwojdziński, Leszek, and Jerzy Lewitowicz. "FIELD REPAIRS OF AIRCRAFT ENGINES." Journal of KONES. Powertrain and Transport 19, no. 4 (January 1, 2015): 131–38. http://dx.doi.org/10.5604/12314005.1138321.
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Pollock, Tresa M. "Alloy design for aircraft engines." Nature Materials 15, no. 8 (July 22, 2016): 809–15. http://dx.doi.org/10.1038/nmat4709.
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Tucker, Reginald. "Chromalloy Keeps Aircraft Engines Aloft." Metal Finishing 111, no. 3 (May 2013): 44–46. http://dx.doi.org/10.1016/s0026-0576(13)70234-4.
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