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

流体力学与飞行力学

本期目录 | 过刊浏览 | 高级检索

前一篇 | 后一篇

基于通流方法的某涡喷发动机整机数值仿真

刘晓恒¹, 周成华¹, 宋满祥¹, 金东海^1,2, 桂幸民^1,2

1. 北京航空航天大学能源与动力工程学院, 北京 100083;
2. 北京航空航天大学先进航空发动机协同创新中心, 北京 100083

收稿日期:2019-06-06 修回日期:2019-07-03 出版日期:2020-01-15 发布日期:2019-10-10
通讯作者: 金东海 E-mail:jdh@buaa.edu.cn
基金资助:
国家科技重大专项（2017-Ⅰ-0005-0006）

Overall simulation of a turbojet engine based on throughflow method

LIU Xiaoheng¹, ZHOU Chenghua¹, SONG Manxiang¹, JIN Donghai^1,2, GUI Xingmin^1,2

1. School of Energy and Power Engineering, Beihang University, Beijing 100083, China;
2. Collaborative Innovation Center for Advanced Aero-Engine, Beihang University, Beijing 100083, China

Received:2019-06-06 Revised:2019-07-03 Online:2020-01-15 Published:2019-10-10
Supported by:
National Science and Technology Major Project(2017-Ⅰ-0005-0006)

摘要/Abstract

摘要： 采用轴对称方法对带有黏性力的三维Euler方程组进行降维，利用时间推进方法求解，得到适用于航空发动机整机计算的准三维数值仿真软件，并对某涡喷发动机整机进行设计点和非设计点数值模拟。首先，对地面静止状态节流特性进行研究，将计算结果与试验数据对比可知：推力的最大相对误差为-5.1%，单位燃油消耗率的最大相对误差为+4.8%，相对转速为95%时，单位燃油消耗率最低；其次，获取了飞行马赫数为0.7工况下的高度特性以及飞行高度为3 km工况下的速度特性，将计算结果与设计参数对比可知：对于高度特性，推力的最大相对误差为-4.61%，单位燃油消耗率的最大相对误差为+5%，对于速度特性，推力的最大相对误差为-5.83%，单位燃油消耗率的最大相对误差为+5.92%；再次，分别对压气机/涡轮进行部件模拟，预测了发动机的共同工作线；最后，对发动机设计工况下的流场以及气动参数的展向分布进行了分析。

关键词: 叶轮机械, 整机仿真, 涡喷发动机, 通流方法, 地面节流特性, 高度/速度特性

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

中图分类号:

V231.3

刘晓恒, 周成华, 宋满祥, 金东海, 桂幸民. 基于通流方法的某涡喷发动机整机数值仿真[J]. 航空学报, 2020, 41(1): 123199-123199.

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.

参考文献 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.

E-mail：hkxb@buaa.edu.cn

关于我们

期刊社服务

专业学科

封面文章

友情链接

主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

基于通流方法的某涡喷发动机整机数值仿真

Overall simulation of a turbojet engine based on throughflow method

PDF (PC)

可视化

摘要/Abstract

引用本文

使用本文

参考文献 30

相关文章 15

编辑推荐

Metrics

本文评价

[1]	张东飞, 高军辉. GPU加速高阶谱差分方法在风扇噪声中的应用[J]. 航空学报, 2024, 45(8): 128941-128941.
[2]	刘汉儒, 陈南树, 刘宇, 胡之颉. 多孔介质流动控制及气动降噪研究进展[J]. 航空学报, 2023, 44(16): 27923-027923.
[3]	杨金广, 王春雪, 王大磊, 邵伏永, 杨晨, 吴虎. 基于时间推进的通流计算方法:现状及展望[J]. 航空学报, 2017, 38(9): 520996-520996.
[4]	许坤波, 乔渭阳, 常心悦, 银涛, 霍施宇. 基于组合传声器阵列方法的风扇宽频噪声[J]. 航空学报, 2017, 38(12): 121324-121324.
[5]	许坤波, 乔渭阳, 霍施宇, 程颢颐, 仝帆. 基于旋转轴向阵列的风扇宽频噪声实验[J]. 航空学报, 2017, 38(11): 121132-121132.
[6]	许坤波, 乔渭阳, 王良峰, 仝帆. 轴流风扇宽频噪声声功率实验研究[J]. 航空学报, 2015, 36(9): 2939-2946.
[7]	胡国暾, 杜林, 孙晓峰. 基于浸入式边界法的叶栅颤振数值模拟[J]. 航空学报, 2015, 36(7): 2269-2278.
[8]	王良锋, 乔渭阳, 纪良, 仝帆. 基于流场/声场混合模型的叶轮机械单音噪声研究[J]. 航空学报, 2014, 35(9): 2481-2490.
[9]	胡国暾, 杜林, 孙晓峰. 基于浸入式边界法的振荡转子叶片数值模拟[J]. 航空学报, 2014, 35(8): 2112-2125.
[10]	杨金广, 吴虎. 双方程k-ω SST湍流模型的显式耦合求解及其在叶轮机械中的应用[J]. 航空学报, 2014, 35(1): 116-124.
[11]	郑礼宝. 全尺寸二元喷管红外辐射特性研究[J]. 航空学报, 2002, 23(2): 140-142.
[12]	邹正平;徐力平. 叶轮机三维非定常流动数值模拟的研究[J]. 航空学报, 2001, 22(1): 10-14.
[13]	郭秉衡;许彪;张登洲. 双转子涡喷发动机风车特性的计算与分析[J]. 航空学报, 1995, 16(5): 528-533.
[14]	廉小纯;吴虎;陈辅群;沈韶瀛. 涡喷发动机压气机的单元控制体模型[J]. 航空学报, 1995, 16(4): 109-113.
[15]	郑庆雄;廉小纯;陈辅群;沈韶瀛. 畸变进气对双轴涡喷发动机性能的影响[J]. 航空学报, 1993, 14(10): 529-531.