An Investigation of Coupling Method Between Two-Dimensional Core Driven Fan Stage Model and Zero-Dimensional VariableCycle Engine Model

doi:10.13675/j.cnki.tjjs.190176

Journal of Propulsion Technology ›› 2020, Vol. 41 ›› Issue (3): 500-508.DOI: 10.13675/j.cnki.tjjs.190176

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An Investigation of Coupling Method Between Two-Dimensional Core Driven Fan Stage Model and Zero-Dimensional VariableCycle Engine Model

School of Power and Energy,Northwestern Polytechnical University,Xi’an710129,China

Published:2021-08-15

核心机驱动风扇级二维仿真模型与变循环发动机零维仿真模型耦合方法的研究

宋甫¹,周莉¹,王占学¹,张明阳¹,张晓博¹

西北工业大学动力与能源学院，陕西西安710129

作者简介:宋甫，博士生，研究领域为航空发动机总体性能仿真。E-mail：sf_antifragile@163.com
基金资助:
国家自然科学基金（51876167；51576163）。

Abstract

Abstract: In order to improve the reliability and accuracy of the zero-dimensional variable cycle engine (VCE) model, the two-dimensional model of core driven fan stage (CDFS) was built and integrated into zero-dimensional VCE model with fully coupled approach and the multi-level VCE model was established finally. The differences of results between the zero-dimensional VCE model and multi-level VCE model were analyzed, and the effects of radial non-uniform distribution of aerodynamic parameters of CDFS on VCE performance was studied with the multi-level model. The result indicates that the iterative variables and balance equations need to be adjusted on the basis of the boundary conditions of two-dimensional CDFS model so as to establish the multi-level VCE model with fully coupled approach. Compared with the zero-dimensional CDFS model, the two-dimensional CDFS model containing the physical information such as geometric parameters can provide more practical and physical CDFS characteristics for VCE cycle analysis. The change of CDFS performance will lead to the change of working points of other components and VCE performance with constraint of the flow continuity and power balance. The maximum difference of thrust between the zero-dimensional VCE model and multi-level VCE model is 2.99%. Combining with CDFS bypass ratio, the radial non-uniform distribution of aerodynamic parameters of CDFS outlet can be integrated into VCE cycle analysis. More reasonable initial values for iterative variables are needed to solve the multi-level VCE model. Therefore, the result of the zero-dimensional VCE model is used to initialize the iterative variables of multi-level VCE model.

摘要： 为了提高变循环发动机（VCE）零维仿真模型的可靠性和精度，建立了核心机驱动风扇级（CDFS）二维仿真模型，基于完全耦合方法，将CDFS二维仿真模型耦合于VCE零维仿真模型，发展了VCE多维度仿真模型，分析了VCE零维仿真模型与多维度仿真模型计算结果的差异，使用VCE多维度仿真模型，分析了CDFS气动参数径向非均匀分布对VCE性能的影响。结果表明，结合CDFS二维仿真模型对边界条件的要求，重新选取VCE仿真模型中的迭代变量和平衡方程，可以基于完全耦合方法建立VCE多维度仿真模型；与零维仿真模型相比，CDFS二维仿真模型考虑了部件几何参数等物理信息，可以为VCE循环参数分析提供更加真实的部件工作特性，并在功率平衡与流量平衡等条件的约束下引起其它部件工作点及VCE性能的变化；VCE零维仿真模型与多维度仿真模型所得推力的最大差异为2.99%；结合CDFS涵道比，可以将CDFS出口气动参数径向非均匀分布这一流动特性耦合到VCE循环参数分析中；VCE多维度仿真模型对迭代变量初值的选取提出了更高的要求，需要使用VCE零维仿真模型的解作为初值以保证收敛性。

关键词: 变循环发动机;核心机驱动风扇级;二维仿真模型;多维度仿真模型;完全耦合方法

SONG Fu¹,ZHOU Li¹,WANG Zhan-xue¹,ZHANG Ming-yang¹,ZHANG Xiao-bo¹. An Investigation of Coupling Method Between Two-Dimensional Core Driven Fan Stage Model and Zero-Dimensional VariableCycle Engine Model[J]. Journal of Propulsion Technology, 2020, 41(3): 500-508.

宋甫,周莉,王占学,张明阳,张晓博. 核心机驱动风扇级二维仿真模型与变循环发动机零维仿真模型耦合方法的研究[J]. 推进技术, 2020, 41(3): 500-508.

References

[1] Allan R D.General Electric Company Variable Cycle Engine Technology Demonstrator Program[R].AIAA79-1311.
[2] Johnson J E.Variable Cycle Engines-the Next Step in Propulsion Evolution[R].AIAA76-758.
[3] Piccirillo A C.Origins of the F-22 Raptor[R].AIAA98-5566.
[4] Thomas R D.Engine Wars: Competition for US Fighter Engine Production[R].AIAA98-3115.
[5] 倪金刚.GE航空发动机百年史话[M].北京：航空工业出版社，2015.
[6] Silva W A，Sanetrik M D，Chwalowski P，et al.Computational Aeroelastic Analysis of a Low-Boom Supersonic Conguration[R].NF1676L-20147.
[7] Connolly J W，Kopasakis G，Chwalowski P，et al.Towards an Aero-Propulso-Servo-Elasticity Analysis of a Commercial Supersonic Transport[R].AIAA2016-1320.
[8] Scharnhorst R K.Characteristics of Future Military Aircraft Propulsion Systems[R].AIAA2013-0466.
[9] Bradley M，Bowcutt K，McComb J.Revolutionary Turbine Accelerator (RTA) Two-Stage-to-Orbit (TSTO) Vehicle Study[R].AIAA2002-3902.
[10] Lee J，Winslow R，Buehrle R J.The GE-NASA RTA Hyperburner Design and Development[R].NASA TM-2005-213803.
[11] Evans A L，Follen G，Naiman C，et al.Numerical Propulsion System Simulation’s National Cycle Program[R].AIAA98-3113.
[12] Alexiou A，Baalbergen E H，Kogenhop O，et al.Advanced Capabilities for Gas Turbine Engine Performance Simulation[R].ASME GT2007-27086.
[13] Pilet J，Lecordix J L，Nicolas G，et al.Towards a Fully Coupled Component Zooming Approach in Engine Performance Simulation[R].ASME GT2011-46320.
[14] Templalexis I，Alexiou A，Pachicis V，et al.Direct Coupling of a Turbofan Engine Performance Simulation[R].ASME GT2016-56617.
[15] Connolly J W，Kopasakis G，Carlsonz J，et al.Nonlinear Dynamic Modeling of a Supersonic Commercial Transport Turbo-Machinery Propulsion System for Aero-Propulso-Servo-Elasticity Research[R].NASA TM-2012-217273.
[16] Connolly J W，Friedlander D.Kopasakis G. Computational Fluid Dynamics Modeling of a Supersonic Nozzle and Integration into a Variable Cycle Engine Model[R].NASA TM-2015-218479.
[17] 周红.变循环发动机特性分析及其与飞机一体化设计研究[D].西安:西北工业大学，2016.
[18] 彭利方.变循环发动机建模与非线性控制方法研究[D].南京:南京航空航天大学，2015.
[19] 刘佳鑫，王志强，严伟，等.单/双涵道模式转换过程的数值研究[J].推进技术，2017，38(8):1699-1708.
[20] 刘勤，李刚团，黄红超.三外涵变循环发动机循环参数匹配模拟[J].航空发动机，2016，42(6):51-54.
[21] 韩佳，苏桂英，张跃学.基于近似模型的变循环发动机稳态性能分析及优化[J].燃气涡轮试验与研究，2017，30(3):16-20.
[22] 刘宝杰，贾少锋，于贤君.变循环核心压气机可调特性的数值研究[J].工程热物理学报，2016，37(9):1850-1855.
[23] 刘宝杰，贾少锋，于贤君.变循环发动机前可调涵道引射器的通流计算方法[J].推进技术，2017，38(8):1689-1698.(LIU Bao-jie， JIA Shao-feng， YU Xian-jun.Throughflow Calculation Method of Variable Cycle Engine Forward Area Bypass Injector[J].2017，38(8):1689-1698.)
[24] Byvey P，Bosschaerts W，Villace V F，et al.Study of an Airbreathing Variable Cycle Engine[R].AIAA2011-5758.
[25] Joachim K.How to Get Component Maps for Aircraft Gas Turbine Performance Calculations[R].ASME 96-GT-164.
[26] Sullivan T J，Parker D E.Design Study and Performance Analysis of a High-Speed Mulistage Variable-Geometry Fan for a Variable Cycle Engine[R].NASA CR-159545.
[27] Johnsen I A，Bullock R O.Aerodynamic Design of Axial-Flow Compressors,Volume 2[R].NACA RM-E56B03A.
[28] Aungier R.Axial-Flow Compressor-a Strategy for Aerodynamic Design and Analysis[M].New York:ASME Press，2003.
[29] Cetin M，Uecer A S，Hirsch C，et al.Application of Modified Loss and Deviation Correlations to Transonic Axial Compressors[R].AGARD-R-745，1987.
[30] 祝启鹏，高丽敏，李瑞宇，等.跨声速多级轴流压气机特性预估及分析[J].推进技术，2014，35(10):1342-1348.
[31] Boyer K M.An Improved Streamline Curvature Approach for Off-Design Analysis of Transonic Compression Systems[D].Virginia:Virginia Polytechnic Institute and State University，2001.
[32] Miller G R，Lewis G M，Hartmann M J.Shock Losses in Transonic Compressor Blade Rows[J].Journal of Engineering for Power，1961，83(3):235-241.
[33] 楚武利，刘前智，胡春波.航空叶片机原理[M].西安:西北工业大学出版社，2009.

An Investigation of Coupling Method Between Two-Dimensional Core Driven Fan Stage Model and Zero-Dimensional VariableCycle Engine Model

核心机驱动风扇级二维仿真模型与变循环发动机零维仿真模型耦合方法的研究

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