反推状态下大涵道比涡扇发动机气动稳定性预测与评估

doi:10.7527/S1000-6893.2016.0143

流体力学与飞行力学

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反推状态下大涵道比涡扇发动机气动稳定性预测与评估

王志强¹, 沈锡钢², 胡骏¹

1. 南京航空航天大学能源与动力学院, 南京 210016;
2. 中国航发沈阳发动机研究所, 沈阳 110015

收稿日期:2016-03-07 修回日期:2016-05-06 出版日期:2017-02-15 发布日期:2016-05-23
通讯作者: 王志强,E-mail:wangzq1981@126.com E-mail:wangzq1981@126.com
基金资助:
中国博士后科学基金（2014M551590）

Prediction and evaluation of aerodynamic stability of high bypass ratio turbofan engine deployed with thrust reverser

WANG Zhiqiang¹, SHEN Xigang², HU Jun¹

1. College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;
2. Aero Engine(Group) Corporation of China Shenyang Engine Research Institute, Shenyang 110015, China

Received:2016-03-07 Revised:2016-05-06 Online:2017-02-15 Published:2016-05-23
Supported by:
China Postdoctoral Science Foundation (2014M551590)

摘要/Abstract

摘要：

为了预测与评估反推状态下，反推气流再吸入对大涵道比涡扇发动机气动稳定性的影响，采用反推气流扰流流场三维CFD数值模拟、发动机整机稳定性计算分析以及反推状态下发动机进气畸变台架试验相结合的方法，开展了反推气流对大涵道比涡扇发动机气动稳定性影响的研究。通过三维CFD数值模拟手段，捕获了反推状态下发动机进口流场的畸变程度。在此基础上，通过采用稳定性计算程序预测了发动机的气动稳定性，并进一步通过发动机台架试验，验证了预测结果。CFD计算结果表明，随着相对来流马赫数的减小，反推气流被发动机重新吸入的可能性不断增大，当相对来流马赫数减小到0.05时，外侧发动机进口的流场畸变情况变得最为严重。进气畸变情况下的整机稳定性计算分析以及发动机台架试验结果表明，在所考核的目标状态，若只存在因反推气流再吸入引起的进口流场畸变，是不会导致发动机失稳的。

关键词: 大涵道比涡扇发动机, 反推力装置, 反推气流再吸入, 流场畸变, 气动稳定性, 数值模拟, 试验验证

Abstract:

Three-dimensional CFD numerical simulation, engine stability calculation and bench test of engine inlet distortion are combined to predict and assess the influence of re-ingestion of the reverser flow on the aerodynamic stability of the high bypass ratio turbofan engine when the thrust reverser is deployed. By means of three-dimensional CFD numerical simulation, the distortion degree of the engine inlet flow field is acquired. On this basis, the aerodynamic stability of the engine is predicted by the stability calculation program, and the prediction results are verified by the engine bench test. The CFD calculation results show that, with the decrease of the relative flow Mach number, the possibility of re-ingestion of the reverser flow is increased, and the inlet flow field distortion of the outboard engine is the most serious when the relative flow Maher number decreases to 0.05. The results of stability calculation analysis and engine bench test in the inlet distortion situation show that, in the assessment of the target state, if the inlet distortion is only caused by the re-ingestion of the reverser flow, the engine will not be unstable.

Key words: high bypass ratio turbofan engine, thrust reverser, reverser flow re-ingestion, flow field distortion, aerodynamic stability, numerical simulation, experimental verification

中图分类号:

V235.15

王志强, 沈锡钢, 胡骏. 反推状态下大涵道比涡扇发动机气动稳定性预测与评估[J]. 航空学报, 2017, 38(2): 120192-120202.

WANG Zhiqiang, SHEN Xigang, HU Jun. Prediction and evaluation of aerodynamic stability of high bypass ratio turbofan engine deployed with thrust reverser[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2017, 38(2): 120192-120202.

参考文献

[1] 方昌德. 大涵道比涡扇发动机关键技术[J]. 国际航空, 2008(1):38-40. FANG C D. Key technologies for high bypass turbofan engines[J]. International Aviation, 2008(1):38-40(in Chinese).
[2] 沈锡钢, 齐晓雪, 郝勇. 大涵道比涡扇发动机发展研究[J]. 航空发动机, 2013, 39(6):1-5. SHEN X G, QI X X, HAO Y. Investigation of high bypass ratio turbofan engine development[J]. Aeroengine, 2013, 39(6):1-5(in Chinese).
[3] TRAPP L G, OLIVEIRA G L. Aircraft thrust reverser cascade configuration evaluation through CFD:AIAA-2003-0723[R]. Reston:AIAA, 2003.
[4] LORINCZ D, CHIARELLI C,HUNT B. Effect of in-flight thrust reverser deployment on tactical aircraft stability and control:AIAA-1981-1446[R]. Reston:AIAA, 1981.
[5] CHIARELLI C, LORINCZ D, HUNT B. Thrust reverser induced flow interference on tactical aircraft stability and control:AIAA-1982-1133[R]. Reston:AIAA, 1982.
[6] 赖安卿, 胡骏, 赵运生, 等. 大涵道比涡扇发动机整机稳定边界预测方法[J]. 航空计算技术, 2013, 43(1):81-84. LAI A Q, HU J, ZHAO Y S, et al. Numerical simulation of aerodynamic stability limit of high bypass turbofan engine[J]. Aeronautical Computing Technique, 2013, 43(1):81-84(in Chinese).
[7] 邵万仁, 叶留增, 沈锡钢, 等. 反推力装置关键技术及技术途径初步探讨[C]//大型飞机关键技术高层论坛暨中国航空学会2007年年会论文集. 北京:中国航空学会, 2007. SHAO W R, YE L Z, SHEN X G, et al. Preliminary discussion on key techniques and technical approaches of thrust reverser[C]//Proceedings of High-level Forum on Key Technology of Large Aircraft and 2007 Annual Conference of Chinese Society of Aeronautics and Astronautics. Beijing:Chinese Society of Aeronautics and Astronautics, 2007(in Chinese).
[8] CHUCK C. Computational procedures for complex three-dimensional geometries including thrust reverser effluxes and APUs:AIAA-2001-3747[R]. Reston:AIAA, 2001.
[9] STRASH D J, SUMMA J M, FRANK J H, et al. Aerodynamic analysis of an installed thrust reverser[J]. Journal of Propulsion & Power, 2000, 16(1):10-15.
[10] DE ANDRADE F O, FERREIRA S B, DA SILVA L F F, et al. Study of the influence of aircraft geometry on the computed flow field during thrust reversers operation:AIAA-2006-3673[R]. Reston:AIAA, 2006.
[11] QIAN R Z, ZHU Z Q, DUAN Z Y. Thrust reverser optimization for safety with CFD[J]. Procedia Engineering, 2011(17):595-602.
[12] 刘大响, 叶培梁, 胡骏, 等. 航空燃气涡轮发动机稳定性设计与评定技术[M]. 北京:航空工业出版社, 2004. LIU D X, YE P L, HU J, et al. Stability design and evaluation technology of aero gas turbine engine[M]. Beijing:Aviation Industry Press, 2004(in Chinese).
[13] NAKANO T, BREEZE A. A method for evaluating the effect of circumferential inlet distortion on the aerodynamic stability of multi-stage axial-flow compressors[C]//Proceedings of ASME Turbo Expo 2010:Power for Land, Sea, and Air. New York:ASME, 2010:2671-2683.
[14] 胡骏, 赵运生, 丁宁, 等. 进气畸变对大涵道比涡扇发动机稳定性的影响[J]. 航空发动机, 2013, 39(6):6-12. HU J, ZHAO Y S, DING N, et al. Investigation of influence of inlet distortion on high bypass ratio turbofan engine stability[J]. Aeroengine, 2013, 39(6):6-12(in Chinese).
[15] 王玉新. 飞机发动机反推力装置的创新设计[C]//大型飞机关键技术高层论坛暨中国航空学会2007年年会论文集. 北京:中国航空学会, 2007. WNAG Y X. Innovative design of thrust reverser for aircraft engine[C]//Proceedings of High-level Forum on Key Technology of Large Aircraft and 2007 Annual Conference of Chinese Society of Aeronautics and Astronautics. Beijing:Chinese Society of Aeronautics and Astronautics, 2007(in Chinese).
[16] 杨权, 叶巍, 陆德雨, 等. 航空发动机稳定性评定试验装置的选择[J]. 燃气涡轮试验与研究, 2001, 14(4):16-21. YANG Q, YE W, LU D Y, et al. A selection of testers for aero-engine stability assessment[J]. Gas Turbine Experiment & Research, 2001, 14(4):16-21(in Chinese).
[17] 叶巍, 陆德雨, 李丹, 等. 畸变模拟板的设计与试验研究[J]. 燃气涡轮试验与研究, 2001, 14(2):1-8. YE W, LU D Y, LI D, et al. Design and experimental investigation of simulating plates[J]. Gas Turbine Experiment & Research, 2001, 14(2):1-8(in Chinese).
[18] 陆德雨, 叶巍, 李丹, 等. 缩尺模拟板相关性研究[J]. 燃气涡轮试验与研究, 2002, 15(2):12-16. LU D Y, YE W, LI D, et al. Investigation of correlation between sub-scale and full-scale models of simulating plates[J]. Gas Turbine Experiment & Research, 2002, 15(2):12-16(in Chinese).

E-mail：hkxb@buaa.edu.cn

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反推状态下大涵道比涡扇发动机气动稳定性预测与评估

Prediction and evaluation of aerodynamic stability of high bypass ratio turbofan engine deployed with thrust reverser

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