飞机快速机动过程中进气道/发动机一体化计算分析

田金虎; 乔渭阳; 彭生红

飞机快速机动过程中进气道/发动机一体化计算分析

1.
西北工业大学动力与能源学院, 西安 710072
2.
中国航空工业集团公司中国燃气涡轮研究院航空发动机高空模拟航空科技重点实验室, 四川江油 621703

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出版历程
- 收稿日期: 2012-07-14
- 刊出日期: 2013-08-28

Calculation and analysis on air inlet/engine integrated in fast maneuvering flight

1.
School of Power and Energy, Northwestern Polytechnical University, Xi'an 710072
2.
Aero-Engine Altitude Simulated Key Laboratory, China Gas Turbine Establishment, Aviation Industry Corporation of China, Jiangyou Sichuan 621703, China

摘要

摘要: 基于进气道/发动机推进系统一体化动态数值模拟计算系统,对飞机快速俯仰机动飞行过程中的性能进行了计算分析研究,获取了飞机快速俯仰过程中的推进系统气动性能的变化特征,数值计算结果表明:快速变化的外部扰动会诱发发动机内部热力循环参数和性能更大的动态波动;在机动飞行的同时,增大燃油量,发动机推力下降程度得以减缓,发动机的单位燃油消耗率上升.
- 高机动性飞机 /
- 飞机/发动机匹配 /
- 进气道/发动机匹配 /
- 一体化设计 /
- 耦合计算
Abstract: Based on an air inlet/engine integrated dynamic simulation system,the engine performance parameters were investigated and obtained in fast maneuvering flight.The numerical calculation shows that fast-changing exterior turbulence reflects on more dynamic fluctuation of thermal cycle parameters and performance parameters,due to the history of engine fuel mass flow,engine thrust descend degree minishs,on the contrary,engine specific fuel consumption ascends with increase of attack angle.
- highly maneuverable aircraft /
- aircraft/engine matching /
- air inlet/engine matching /
- integrated design /
- coupled calculation

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参考文献(15)

[1]	SAE S-16 Committee.ARP1420B gas turbine engine inlet flow distortion guidelines[M].Washington D C:Society of Automotive Engineers,2002.
[2]	Davis M,Baker W,Power G,et al.A proposal for integration of wind tunnel and engine test programs for the evaluation of air frame-propulsion compatibility using numerical simulations[J].Journal of Engineering for Gas Turbines and Power,2002,124(3):447-458.
[3]	Hale A,Davis M,Sirbaughet J,et al.A numerical simulation capability for analysis of aircraft inlet-engine compatibility[J].Journal of Engineering for Gas Turbines and Power,2006,128(3):473-481.
[4]	Haldeman C W,Dunn M G,Abhari R S,et al.Experimental and computational investigation of the time-averaged and time-resolved pressure loading on a waneless counter-rotating turbine [R].ASME Paper 2000-GT-0445,2000.
[5]	Beale D,O'Dowd K,Davis M,et al.An example for integrated gas turbine engine testing and analysis using modeling and simulation [R].Las Cruces:The 2006 ITEA Modeling and Simulation Conference,2006.
[6]	Davis M,Hale A.A parametric study on the effects of inlet swirl on compression system performance and operability using numerical simulations [R].ASME Paper GT-2007-27033,2007.
[7]	Beale D,Davis M,Sirbaugh J.Requirements and advances in simulating aircraft inlet total-pressure distortion in turbine engine ground tests [R].ASME Paper GT-2006-90038,2006.
[8]	Davis M.Parametric investigation into the combined effects of pressure and temperature distortion on compression system stability [R].AIAA 91-1895,1991.
[9]	Batterton P G,Gold H.Experimental test results of a generalized-parameter fuel control [R].NASA TN D-7198,1973.
[10]	Calogeras J E.Experimental investigation of dynamic distortion in a Mach 2.50 inlet with 60 percent internal contraction and its effect on turbojet stall margin [R].NASA TM X- 1842,1969.
[11]	Burstadt P L,Calogeras J E,Choby D A.Unstart and stall interactions between a turbojet engine and an axisymmetric inlet with 60-percent internal-area contraction [R].NASA TM X-2192,1971.
[12]	Hale A A, Davis M W, Sirbaugh J H. A numerical simulation capability for analysis of aircraft inlet-engine compatibility [R].ASME Paper 2004-GT-53473,2004.
[13]	Costakis W G,Wenzel L M.An experimental investigation of compressor stall using an on-line distortion indicator and signal conditioner [R].NASA TM X-3 182,1975.
[14]	Davis M W,Owen A K,O'Brien W F,et al.Joint dynamic airbreathing propulsion simulations partnership JDAPS [R].ASME Paper 95-GT-143 1995.
[15]	Garrard G D.ATEC:the aerodynamic turbine engine code for the analysis of transient and dynamic turbine engine system operations [D].Knoxville:The University of Tennessee,1995.