基于通流方法的某涡喷发动机整机数值仿真

doi:10.7527/S1000-6893.2019.23199

Abstract

Abstract: Based on the axisymmetric method, three-dimensional Euler equations with viscous force are turned into two-dimensional problems. The problems are solved using time-marching method, and the obtained software can be applied to the overall simulation of aircraft engine. By means of this tool, a turbojet engine on design point as well as off-design point is simulated. First, the throttle characteristics on the ground are firstly studied and are compared with the experimental data. The results reveal that the maximum error for thrust is -5.1% and that of specific fuel consumption is +4.8%. The specific fuel consumption is the smallest at 95% rotational speed. Second, altitude characteristic at flighting Mach number 0.7 and velocity characteristic on the height of 3 km are obtained through this method. The comparison between the designed value and the computation results show that, for altitude characteristic, the maximum errors of thrust and specific fuel consumption are -4.61% and +5%. For velocity characteristic, the maximum errors of both parameters are -5.83% and +5.92%. Third, Co-operating line of the engine is acquired through simulations of compressor and turbine individually. At last, flow field and spanwise distribution of aerodynamic parameters of the engine on design point are analyzed.

Key words: turbomachinery, overall simulation, turbojet engine, throughflow method, ground throttle characteristic, altitude/velocity characteristic

CLC Number:

V231.3

LIU Xiaoheng, ZHOU Chenghua, SONG Manxiang, JIN Donghai, GUI Xingmin. Overall simulation of a turbojet engine based on throughflow method[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2020, 41(1): 123199-123199.

References 30

[1]	TURNER M G, NORRIS A, VERES J. High fidelity 3D simulation of the GE90:AIAA-2003-3996[R]. Reston, VA:AIAA, 2003.
[2]	ADAMCZYK J J, MULAC R A, CELESTINA M L. A model for closing the inviscid form of the average-passage equation system[J]. Journal of Turbomachinery, 1986,108(2):180-186.
[3]	ADAMCZYK J J. Aerodynamic analysis of multistage turbomachinery flows in support of aerodynamic design[J]. Journal of Turbomachinery, 2000,122(2):189-217.
[4]	LIU N S. On the comprehensive modeling and simulation of combustion systems:AIAA-2001-0805[R]. Reston, VA:AIAA, 2001.
[5]	SIMON J F. Contribution to throughflow modelling for axial flow turbomachines[D]. Liege:University of Liege, 2007:7-18.
[6]	HORLOCK J H, DENTON J D. A review of some early design practice using computational fluid dynamics and a current perspective[J]. Journal of Turbomachinery, 2005, 127(1):5-13.
[7]	WU C H. A general through-flow theory of fluid flow with subsonic or supersonic velocity in turbomachines of arbitrary hub and casing shapes:NACA-TN-2302[R].Washington, D.C.:NACA, 1951.
[8]	WU C H. A general theory of three-dimensional flow in subsonic and supersonic turbomachines of axial-, radial-, and mixed-flow type:NACA-TN-2604[R]. Washington, D.C.:NACA, 1952.
[9]	SPURR A. The prediction of 3D transonnic flow in turbomachinery using a combined throughflow and blade-to-blade time marching method[J]. International Journal of Heat Fluid Flow, 1980,2(4):189-199.
[10]	YAO Z, HIRSCH C H. Throughflow model using 3D Euler or Navier-Stokes solver[C]//1st European Conference on Turbomachinery Fluid Dynamics and Thermodynamics, 1995:51-61.
[11]	DAWES W N. Toward improved throughflow capability:The use of three dimensional viscous flow solvers in a multistage environment[J]. Journal of Turbomachinery, 1992, 114(1):8-17.
[12]	DAMLE S V, DANG T Q, REDDY D R. Throughflow method for turbomachines applicable for all regimes[J]. Journal of Turbomachinery, 1997,119(2):256-262.
[13]	IVANOV M J, MAMAEV B I. United modeling of working process in aircraft gas turbine engines:GT2008-50185[R]. New York:ASME, 2008.
[14]	IVANOV M J, NIGMATULLIN R Z. Quasi-3D numerical model of a flow passage of the aviation gas turbine engines[C]//10th International Symposium on Air Breathing Engines (ISABE), 1991:299-305.
[15]	NIGMATULLIN R Z, IVANOV M J. The mathematical models of flow passage for gas turbine engines and their components:AGARD-LS-198[R]. Paris:AGARD, 1994.
[16]	PETROVIC M V, RAHMAN A A, WIEDERMANN A. A quick method for full flange-to-flange industrial gas turbine analysis based on through-flow modelling[J]. International Journal of Gas Turbine, Propulsion and Power Systems, 2016, 8(1):9-18.
[17]	PETROVIC M V, WIEDERMANN A. Fully coupled through-flow method for industrial gas turbine analysis:GT2015-42111[R]. New York:ASME, 2015.
[18]	施发树, 刘兴洲. 多部件模型在全尺寸小型双函道涡扇发动机气流数值模拟中的应用[J]. 推进技术,1998,19(4):22-26. SHI F S, LIU X Z. Multicomponent models in application to numerical simulation of a small full-sized by-pass turbofan engine[J]. Journal of Propulsion Technology, 1998, 19(4):22-26(in Chinese).
[19]	黄家骅, 于廷臣, 冯国泰. 某小型涡扇发动机全流道准三维数值解法[J]. 航空发动机,2005,31(2):42-45. HUANG J H, YU T C, FENG G T. Quasi-3D numerical method for a small turbofan engine flow passage[J]. Aeroengine, 2005, 31(2):42-45(in Chinese).
[20]	冯国泰, 黄家骅, 王松涛. 航空发动机数值仿真试验台建立中几个关键技术问题的讨论[J]. 航空动力学报,2002,17(4):483-488. FENG G T, HUANG J H, WANG S T. Discussion on key technical problems in developing numerical simulation test-bed for aeroengine[J]. Journal of Aerospace Power, 2002,17(4):483-488(in Chinese).
[21]	曹志鹏, 刘大响, 桂幸民, 等.某小型涡喷发动机二维数值仿真[J]. 航空动力学报,2009,24(2):439-444. CAO Z P, LIU D X, GUI X M, et al. Two dimensional numerical simulation of small turbojet engine[J]. Journal of Aerospace Power, 2009,24(2):439-444(in Chinese).
[22]	万科, 朱芳, 金东海, 等.周向平均方法在某风扇/增压级分析中的应用[J]. 航空学报,2014,35(1):132-140. WAN K, ZHU F, JIN D H, et al. Application of circumferentially averaged method in fan/booster[J]. Acta Aeronautica et Astronautica Sinica, 2014, 35(1):132-140(in Chinese).
[23]	BLAZEK J. Computational fluid dynamics:Principles and applications[M]. 2nd ed. Amsterdam:Elsevier, 2005:29-31.
[24]	KOCH C C, SMITH L H. Loss sources and magnitudes in axial-flow compressors[J]. Journal of Engineering for Gas Turbines and Power, 1976, 98(3):411-424.
[25]	CREVELING H, CARMODY R. Axial flow compressor computer program for calculating off design performance:NASA-CR-72427[R]. Washington, D.C.:NASA, 1968.
[26]	HOWELL A R. Fluid dynamics of axial compressors[J]. Proceedings of the Institution of Mechanical Engineers,1945, 153(1):441-452.
[27]	AUNGIER R, FAROKHI S. Axial-flow compressors:A strategy for aerodynamic design and analysis[J]. Applied Mechanics Reviews, 2004, 57(4):B22.
[28]	GALVAS M R. Analytical correlation of centrifugal compressor design geometry for maximum efficiency with specific speed:NASA-TN-D-6729[R]. Washington, D.C.:NASA,1972.
[29]	KACKER S C, OKAPUU U. A mean line prediction method for axial flow turbine efficiency[J]. Journal of Engineering for Gas Turbines and Power, 1982, 104(1):111-119.
[30]	CARTER A, HUGHES H. A theoretical investigation into the effect of profile shape on the performance of aerofoils in cascade:No. 2384[R]. London:British Aeronautical Research Council, 1946.

Overall simulation of a turbojet engine based on throughflow method

PDF (PC)

Knowledge

Abstract

Cite this article

share this article

References 30

Related Articles 15

Recommended Articles

Metrics

Comments

[1]	GUI Xingmin, JIN Donghai, ZHANG Jiancheng, SONG Manxiang, ZHAO Yang, HU Daquan. Flow mechanism of bowed and swept blades with consideration of circumferential fluctuation source term before blade leading edge [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(10): 527371-527371.
[2]	ZHANG Wanfu, WANG Yingfei, ZHANG Xiaobin, YANG Xingchen, LI Chun. Experimental identification for rotordynamic coefficients of labyrinth seal based on impedance method [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(1): 424719-424719.
[3]	ZHOU Yu, CHEN Silian, DU Farong, DING Shuiting. Automatic extraction algorithm of parameterized streamlines from a radial-inflow turbomachinery ruled blade [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2017, 38(5): 420592-420592.
[4]	XU Kunbo, QIAO Weiyang, CHANG Xinyue, YIN Tao, HUO Shiyu. Fan broadband noise based on combined sensor array method [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2017, 38(12): 121324-121324.
[5]	XU Kunbo, QIAO Weiyang, HUO Shiyu, CHENG Haoyi, TONG Fan. Experimental of fan broadband noise determination based on rotating axial arrays [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2017, 38(11): 121132-121132.
[6]	XU Kunbo, QIAO Weiyang, WANG Liangfeng, TONG Fan. Experimental research of broadband sound power determination in axial fan [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(9): 2939-2946.
[7]	HU Guotun, DU Lin, SUN Xiaofeng. Numerical simulation of an oscillating cascade based on immersed boundary method [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(7): 2269-2278.
[8]	ZHOU Di, LU Zhiliang, GUO Tongqing, SHEN Ennan. Stall flutter computation of turbomachinery blade based on a CFD/CSD coupling method [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(4): 1076-1085.
[9]	WANG Liangfeng, QIAO Weiyang, JI Liang, TONG Fan. Turbomachinery Tonal Noise Study Based on Flow-field/acoustic-field Hybrid Model [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2014, 35(9): 2481-2490.
[10]	HU Guotun, DU Lin, SUN Xiaofeng. An Immersed Boundary Method for Simulating Oscillating Rotor Blades [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2014, 35(8): 2112-2125.
[11]	YANG Jinguang, WU Hu. Explicit Coupled Solution of Two-equation k-ω SST Turbulence Model and Its Application in Turbomachinery Flow Simulation [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2014, 35(1): 116-124.
[12]	QUAN Jinlou, ZHANG Weiwei, SU Dan, YE Zhengyin. Flutter Analysis of Turbomachinery Cascades Based on Coupled CFD/CSD Method [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2013, 34(9): 2019-2028.
[13]	SU Dan, ZHANG Weiwei, ZHANG Chen'an, YE Zhengyin. An Unsteady Aerodynamic Modeling for Turbomachinery Based on System Identification [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2012, 33(2): 242-248.
[14]	GUO En min;ZHOU Sheng;LU Ya jun . INVESTIGATION ON BLADE ROW INTERACTION EFFECT ON FLUTTER AND FORCED RESPONSE [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 1999, 20(4): 56-60.
[15]	Zheng Qing-xiong;Lian Xiao-chun;Chen fu-qun;Shen Shao-ying. INFLUENCE OF INLET DISTORTION ON THE PERFORMANCE OF TWIN-SPOOL TURBOJET ENGINES [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 1993, 14(10): 529-531.