The high flow dual variable cycle engine (HFDVCE) achieves high performance by synchronously combining high flow rate, high throttle ratio, bypass ratio, and boost ratio regulation in the full speed range, as well as high turbine front tem-perature and other aerodynamic and thermodynamic schemes, meeting the requirements of low-speed economy and high-speed high thrust. Compared to conventional engines, HFDVCE has more prominent aerodynamic stability issues within the full range and mode switching. Therefore, this article is dedicated to conducting research on the aerodynamic stability of HFDVCE, and proposes an HFDVCE model with instability simulation to address the lack of overall instability simulation and parameter mismatch between sub models under multiple operating conditions in current research. Firstly, a high-precision engine nonlinear model is established based on the component method to obtain the aerodynamic pa-rameters of the compression components. Then, a dynamic modeling method for aerodynamic instability of compression components was proposed. By introducing a torque term to characterize the influence of rotational speed on the charac-teristics of the instability model, an instability model with two types of unstable conditions, stall and surge, was estab-lished to avoid the assumption of constant rotational speed and solve the problem of coefficient mismatch between multi-ple instability sub models. Furthermore, the coupling relationship between the instability model of compression compo-nents and the nonlinear model of the engine was clarified. The impact of aerodynamic instability of the compression sys-tem on the overall performance of the engine was characterized by the instability coefficient, and an HFDVCE model with instability simulation was established to achieve dynamic simulation of overall instability. Finally, simulation experiments were conducted on four typical instability modes of HFDVCE, verifying the effectiveness of the model and providing a simulation platform for active stability control design.
[1] SHENG H L, CHEN Q, ZHANG J, et al. A high-safety active/passive hybrid control approach for compressor surge based on nonlinear model predic-tive control[J]. Chinese Journal of Aeronautics, 2023, 36(1): 396-412.
[2] JOHNSON J. E. Variable Cycle Engine Developments at General Electric [J]. Developments in High-Speed Vehicle Propulsion Systems. AIAA, 1996,165: 105-158.
[3] 丁水汀,刘传凯,王家俊等. 一种基于多涵道进气级间燃烧室的变循环发动机构型: CN114776473A[P]. 2022-07-22.
DING S T, LIU C K, WANG J J, et al. A Variable Cy-cle Engine Configuration Based on Multi Channel In-ter Stage Combustion Chamber: CN114776473A[P]. 2022-07-22 (in Chinese).
[4] GREITZER E. M. Surge and Rotating Stall in Axial Flow Compressors—Part I: Theoretical Compression System Model[J]. Journal of Engineering for Power, 1976, 98(2): 190-198.
[5] MOORE F. K. A theory of rotating stall of multistage axial compressors: Part I—Small Disturbances[J]. Journal of Engineering for Gas Turbines and Power, 1983, 106(2): 313-320.
[6] MOORE F. K. , GREITZER E. M. A Theory of post-stall transients in axial compression systems: Part I—Development of Equations[J]. Journal of Engineering for Gas Turbines and Power, 1986, 108(1): 68–76.
[7] WANG H.O. , ADOMAITIS R. A. , ABED E.H. Non-linear analysis and control of rotating stall in axial flow compressors[C]// Proceedings of 1994 American Control Conference. Baltimore, MD, USA: IEEE, 1994: 2317–2321.
[8] HAYNES J. M. , HENDRICKS G. J. , EPSTEIN A. H. Active Stabilization of Rotating Stall in a Three-Stage Axial Compressor[J]. Journal of Turbomachinery, 1994, 116(2): 226-239.
[9] GRAVDAHL J. T. , EGELAND O. A Moore-Greitzer axial compressor model with spool dynamics[C]// Proceedings of the 36th IEEE Conference on Deci-sion and Control. San Diego, CA, USA: IEEE, 1997: 4714–4719.
[10] BOTROS K. K. Transient Phenomena in Compressor Stations During Surge[J]. Journal of Engineering for Gas Turbines & Power, 1994, 116(1): 133-142.
[11] HYNES T. , GREITZER E. A method for assessing effects of circumferential flow distortion on compres-sor stability[J]. Journal of Turbomachinery. 1987, 109(3): 371–379.
[12] HU J. , FOTTNER L. A new simplified model of post stall transients in axial compression systems[J]. Jour-nal of Thermal Science. 1999, 8(3): 176–189.
[13] MANSOUX C. A. , GYSLING D. L. , SETIAWAN J. D. , et al. Distributed nonlinear modeling and sta-bility analysis of axial compressor stall and surge[C]// Proceedings of the 1994 American Control Confer-ence - ACC '94. Baltimore, MD, USA: IEEE, 1994: 2305–2316.
[14] BONNAURE L. P. Modelling high speed multistage compressor stability[D]. Cambridge, Massachusetts, USA: Massachusetts Institute of Technology, 1991:72-79.
[15] FEULNER M. R. , HENDRICKS G. J. , PADUANO J. D. Modeling for control of rotating stall in high speed multi-stage axial compressors[C]// MATTHEW R. FEULNER, GAVIN J. HENDRICKS, JAMES D. PADUANO. ASME 1994 International Gas Turbine and Aeroengine Congress and Exposition. The Hague, Netherlands: ASME, 1994: 13–16.
[16] HENDRICKS G. J. , SABNIS J. S. , FEULNER M. R. Analysis of instability inception in high-speed multi-stage axial-flow compressors[J]. Journal of Tur-bomachinery. 1997, 119(4): 714–722.
[17] CHUNG K. , LEAMY K. , COLLINS T. A turbine engine aerodynamic model for in-stall transient simu-lation[C]// 21st Joint Propulsion Conference, Monte-rey, CA, USA: AIAA, 1985: 1-10.
[18] HOSNY W. , BITTER S. , STEENKEN W. Turbofan-engine nonrecoverable stall computer-simulation de-velopment and validation[C]. the 21st Joint Propul-sion Conference, Monterey, CA, USA: AIAA, 1985: 8–10.
[19] 杨帆, 胡骏, 严伟. 航空发动机过失速及退喘模型研究[J]. 航空发动机, 2017, 43(1): 41-47.
YANG F, HU J, YAN W. Model Research on Post Stall and Recovering from Stall for Aeroengine[J]. Aeroengine, 2017, 43(1): 41-47 (in Chinese).
[20] XINGLONG ZHANG , LINGWEI LI , TIANHONG ZHANG. Research on Real-Time Model of Tur-boshaft Engine with Surge Process [J].Applied Sci-ence, 2022, 12(2) :744-761.
[21] 黄稳. 轴流压气机动态测试信号的特征分析方法研究[D]. 中国, 江苏, 南京: 南京航空航天大学, 2011.
HUANG W. Model Research on Feature Analysis Methods of Dynamic Signal of Axial-flow Compres-sor [D]. Nanjing Jiangsu China: Nanjing University of Aeronautics and Astronautics, 2009: 1-2 (in Chi-nese).
[22] XINGLONG ZHANG , TIANHONG ZHANG , HANLIN SHENG.A novel aeroengine real-time mod-el for active stability control: Compressor instabilities integration[J].Aerospace Science and Technology, 2024, 145(0): 108844.
[23] SIEROS G , STAMATIS A , MATHIOUDAKIS K . Analytical representation of jet engine turbomachin-ery components characteristic for use in engine per-formance modeling and diagnosis: ISABE95-7030[R]. 1995.
[24] 李志刚,陶增元,丁康乐,等. 一种改进的变几何压气机特性计算方法[J]. 航空发动机, 2004, 30(4): 7-9.
LI ZHIGANG , TAO ZENGYUAN , DING KANGLE , et al. Simulation of variable geometry compressor characteristics[J]. Aeroengine, 2004, 30(4): 7-9 (in Chinese).
[25] 林雪平. 变几何发动机稳态性能计算研究[D]. 西安: 西北工业大学, 2004: 22-26.
LIN XUEPING. Study on steady-state performance calculation of variable geometry engine[D]. Xi an: Northwestern Polytechnical University, 2004: 22-26. (in Chinese)
[26] AINLEY D. G. , MATHESON G. C. R. A method of performance estimation for aixal-flow turbines: ARC/R&M-2974[R]. London: Her Majesty’s Station-ery Office, 1951.
[27] STEINKE R J. STGSTK: A computer code for predict-ing multistage axial flow compressor performance by a meanline stage stacking method: 19820017374-NASA-TP-2020 [R]. Cleveland, OH: NASA Lewis Research Center, 1982
[28] LI P F, ZUO Z T, LI J X, et al. Characteristics of inlet guide vane adjustment of multi-stage axial compres-sor in compressed air energy storage sys-tem[J].Journal of Energy Storage, 2023, 72(Part C): 108342.
[29] SIRINOGLOU A. Implementation of variable geome-try for gas turbomatch improvement [D]. Cranfield, Bedfordshire, UK: Canfield Institute of Technology, 1992:27-53.
[30] MUIR D E , SARAVANAMUTTO H I H , MARSHALL D J . Health monitoring of variable ge-ometry gas turbines for the Canadian navy[J]. J. Eng. Gas Turbines Power, 1989, 111(2): 244-250.
[31] YAO Y J, TAO Z, ZHOU K, et al. Aerodynamic per-formance measurement of a novel variable geometry turbine adjustable guide vane scheme by experi-mental study[J]. Aerospace Science and Technology, 2023, 140(0): 108413.
[32] SHAHRIYARI M., KHALEGHI H., HEINRICH M, A Model for Predicting Post-Stall Behavior of Axial Compressors[J]. Journal of Applied Fluid Mechanics, 2021, 14(3): 897-908.
[33] J.T. GRAVDAHL, O. EGELAND, A moore-greitzer axial compressor model with spool dynamics[C]// 36th IEEE Conference on Decision and Control. San Diego 5: IEEE, 1997.
[34] 陈晓松, 武文倩, 潘天宇, 等. 进口导叶角对叶根失稳压气机流动失稳的影响[J]. 航空动力学报, 2023, 38(1): 215-222.
CHEN X S, WU W G, PAN T Y, et al. Influence of in-let guide vane angle on flow instability of hub insta-bility compressor[J]. Joural of Aerospace Power, 2023, 38(1): 215-222(in Chinese).
[35] 郁新华,杨精波,廉小纯.涡扇发动机过失速性能数值模拟[J]. 推进技术,2000, 21(2): 12-14.
YU XINHUA,YANG JINGBO,LIAN XIAOCHUN. Numerical simulation on post-stall behavior of turbo-fan engine[J].Journal of Propulsion Technology, 2000, 21(2): 12-14(in Chinese).
CJA