变循环涡扇冲压组合发动机发展现状及关键技术分析

doi:10.13675/j.cnki.tjjs.200321

推进技术 ›› 2020, Vol. 41 ›› Issue (9): 1921-1934.DOI: 10.13675/j.cnki.tjjs.200321

• 总体与系统 • 下一篇

变循环涡扇冲压组合发动机发展现状及关键技术分析

王占学¹，张明阳²，张晓博¹，周莉¹

1.西北工业大学动力与能源学院，陕西省航空发动机内流动力学重点实验室，陕西西安 710129;2.中国航发贵阳发动机设计研究所，贵州贵阳 550081

出版日期:2020-09-15 发布日期:2020-09-15
作者简介:王占学，博士，教授，研究领域为航空发动机总体设计。E-mail：wangzx@nwpu.edu.cn
基金资助:
国家自然科学基金（51876176；51906214）；民机专项科研项目。

Development Status and Key Technologies of Variable Cycle Turbofan-Ramjet Engine

1.Shaanxi Key Laboratory of Internal Aerodynamics in Aero-Engine,School of Power and Energy, Northwestern Polytechnical University,Xi’an 710129,China;2.AECC Guiyang Aero-Engine Research Institute,Guiyang 550081,China

Online:2020-09-15 Published:2020-09-15

摘要/Abstract

摘要： 总结了国内外变循环涡扇冲压组合发动机的发展现状，对比分析了有/无能量传递构型的变循环涡扇冲压组合发动机的工作原理及优缺点。提炼了变循环涡扇冲压组合发动机的关键技术，包括总体性能仿真技术、高速宽工况风扇设计技术、加力/冲压燃烧室设计技术、热管理系统设计技术以及模态转换设计技术。基于国内需求和相关技术研究现状，给出了变循环涡扇冲压组合发动机后续重点研究方向的建议，包括发动机总体性能设计与仿真工具、发动机多设计点多学科耦合设计方法、发动机热管理系统设计与仿真建模以及关键部件的设计与试验。

关键词: 变循环;涡扇冲压组合发动机;发展现状;关键技术;综述

Abstract: The development status of variable cycle turbofan-ramjet (VCTR) engines at home and abroad was summarized, and the operating principles, advantages and disadvantages of two typical configurations of VCTR engines, with or without energy transfer between the turbine engine and the ramjet flowpaths, were comparatively analyzed. The key technologies of VCTR engines are defined and discussed, including engine performance design and simulation technology, high-speed and wide-range fan design technology, after/ram burner (hyperburner) design technology, thermal management system (TMS) design technology, and mode transition design technology. Based on the domestic need and related research status for the VCTR engines, the following issues are proposed to be further investigated: VCTR engine performance design and simulation tool, multi-design points and multi-disciplinary coupling design methodology, TMS design and modeling, and design and test of critical components.

Key words: Variable cycle;Turbofan-ramjet engine;Development Status;Key technologies;Review

王占学，张明阳，张晓博，周莉. 变循环涡扇冲压组合发动机发展现状及关键技术分析[J]. 推进技术, 2020, 41(9): 1921-1934.

WANG Zhan-xue¹, ZHANG Ming-yang², ZHANG Xiao-bo¹, ZHOU Li¹. Development Status and Key Technologies of Variable Cycle Turbofan-Ramjet Engine[J]. Journal of Propulsion Technology, 2020, 41(9): 1921-1934.

参考文献

[1] Bartolotta P A, McNelis N B, Shafer D G. High Speed Turbines: Development of a Turbine Accelerator (RTA) for Space Access[R]. AIAA 2003-6943.
[2] Dusa D J. High Mach Propulsion System Installation and Exhaust System Design Considerations[R]. AIAA 87-2941.
[3] McNelis N, Bartolotta P. Revolutionary Turbine Accelerator (RTA) Demonstrator[R]. AIAA 2005-3250.
[4] Miyagi H, Kimura H, Kishi K, et al. Combined Cycle Engine Research in Japanese HYPR Program[R]. AIAA 98-3278.
[5] Sosounov V A, Tskhovrebov M M, Solonin V I, et al. The Study of Experimental Turboramjets[R]. AIAA 92-3720.
[6] Sippel M. Research on TBCC Propulsion for a Mach 4.5 Supersonic Cruise Airliner[R]. AIAA 2006-7976.
[7] Johnson J E, Sprunger E V, Simmons J R. Variable Cycle Turbofan-Ramjet Engine[P]. USA： 5694768, 1997-12-09.
[8] Ito M. International Collaboration in Super/Hypersonic Propulsion System Research Project[J]. The Aeronautical Journal, 2000, 104: 445-451.
[9] Kuo S C, Doernbach J D, Champagne G, et al. A Scoping Study for Hypersonic Transport Propulsion Systems[R]. ASME 92-GT-409.
[10] Ichimaru O, Ishizuka M, Murashima K. Overview of the Japanese National Project for Super/Hyper-Sonic Transport Propulsion System[R]. ASME 92-GT-252.
[11] Yanagi R, Morita M, Watanabe Y, et al. Conceptual Design of Turbo-Accelerator for HST Combined Cycle Engine[R]. ASME 92-GT-253.
[12] Itahara H, Kohara S, Takagi S, et al. Turbo Engine Research in Japanese HYPR Project for HST Combined Cycle Engine[R]. AIAA 94-3358.
[13] Fujimura T, Ishii K, Takagi S, et al. HYPR90-T Turbo Engine Research for HST Combined Cycle Engine[R]. SAE-951991, 1995.
[14] Miyagi H, Miyagawa H, Monji T, et al. Combined Cycle Engine Research in Japanese HYPR Project[R]. AIAA 95-2751.
[15] Itahara H, Nakata Y, Kimura T, et al. Research and Development of HYPR90-T Variable Cycle Turbo Engine for HST[R]. ISABE 97-7013.
[16] Fujimura T, Tsugumi S, Kimura H, et al. Research and Development of High Temperature Core Engine for HST[R]. AIAA 98-3279.
[17] Okazaki M, Miyazawa K, Ishizawa K. Engineering Research for Super/Hypersonic Transport Propulsion System (HYPR)[R]. ISABE 99-7004.
[18] Ohshima T, Kanbe K, Kimura H, et al. Control of the Intake Shock-Position in the Test Rig for Ramjet Engine[R]. AIAA 97-2885.
[19] Suzuki M, Kuno N, Tobita A, et al. Current Status of Fan Component Research in HYPR Program[R]. AIAA 98-3280.
[20] Kawano M, Kuyama T, Kobayashi M, et al. Development of a High Temperature Combustor for HYPR Mach 3 Turbojet Engines[R]. AIAA 98-3281.
[21] Shimizu K, Nogami R. Current Status of Low Pressure Turbine Component Research in HYPR Program[R]. AIAA 98-3282.
[22] Hirai K, Kodama H, Miyagi H, et al. Analysis of Flow in the Front-Mixing Region of Hypersonic Combined-Cycle Engine[R]. AIAA 96-0379.
[23] Kinoshita Y, Kitajima J, Seki Y, et al. Experimental Studies on Methane-Fuel Laboratory Scale Ram Combustor[R]. ASME 94-GT-369.
[24] Ohshima T, Enomoto Y, Nakanishi H, et al. Experimental Approach to the HYPR Mach 5 Ramjet Propulsion System[R]. AIAA 98-3277.
[25] Kishi K, Kuno N, Kashiwagi T, et al. Exhaust Nozzle Research in Japanese HYPR Program[R]. AIAA 95-2606.
[26] Nakamura Y, Oishi T. Development of Mixer-Ejector with Ceramic Acoustic Liner[R]. AIAA 99-1928.
[27] Soga Y, Kurosaki M, Tsuzuki Y, et al. Control of HYPR Demonstrator Engine[R]. AIAA 98-3283.
[28] Nakamura Y, Oishi T. Sub-Scale Engine Noise Test for High Speed Jet Noise Suppression System[R]. AIAA 2000-1958.
[29] Hueter U, McClinton C. NASA's Advanced Space Transportation Hypersonic Program[R]. AIAA 2002-5175.
[30] Cook S A, Morris C E K, Tyson R W. Technology Innovations from NASA's Next Generation Launch Technology Program[C]. Vancouver: 55th International Astronautical Congress, 2004.
[31] Bradley M, Bowcutt K, McComb J, et al. Revolutionary Turbine Accelerator (RTA) Two-Stage-To-Orbit (TSTO) Vehicle Study[R]. AIAA 2002-3902.
[32] Shafer D G, McNelis N B. Development of a Ground Based Mach 4+ Revolutionary Technology Demonstrator (RTATD) for Access to Space[R]. ISABE 2003-1125.
[33] 刘红霞, 梁春华, 孙明霞. 美国高超声速涡轮基组合循环发动机的进展及分析[J]. 航空发动机, 2017, 43(4): 96-102.
[34] Murthy S N B, Curran E T. Developments in High-Speed-Vehicle Propulsion Systems[M]. Virginia: AIAA Press, 1996.
[35] Brazier M E, Paulson R E. Variable Cycle Engine Concept[R]. ISABE 93-7065.
[36] Sippel M, Klevanski J. Preliminary Definition of Supersonic and Hypersonic Airliner Configurations[R]. AIAA 2006-7984.
[37] Sippel M, Okai K. Preliminary Definition of a TBCC Propulsion System for a Mach 4.5 Supersonic Cruise Airliner[R]. ISABE 2007-1204.
[38] Okai K, Sippel M. Component Analysis of TBCC Propulsion for a Mach 4.5 Supersonic Cruise Airliner[C]. Belgium: 2nd European Conference for Aerospace Science, 2007.
[39] 扈鹏飞, 芮长胜. 涡轮冲压组合动力涡轮基技术发展思考[C]. 西安: 中国航天第三专业信息网第三十七届技术交流会暨第一届空天动力联合会议, 2016.
[40] Chen M, Zhu Z, Zhu D, et al. Performance Analysis Tool for Turbine Based Combined Cycle Engine Concept[J]. Journal of Astronautics, 2006, 27(5): 854-859.
[41] 张明阳. 变循环涡扇冲压组合发动机性能仿真建模与分析[D]. 西安: 西北工业大学, 2020.
[42] 徐思远, 朱之丽, 刘振德, 等. 革新涡轮加速模态转换特性研究[J]. 推进技术, 2020, 41(3): 516-526.
[43] Snyder L E, Escher D W. High Mach Turbine Engines for Access to Space Launch Systems[R]. AIAA 2003-5036.
[44] ISO 16290-2013. Space Systems-Definition of the Technology Readiness Levels (TRLs) and Their Criteria of Assessment[S].
[45] Suder K L, Prahst P S, Thorp S A. Results of an Advanced Fan Stage Operating Over a Wide Range of Speed & Bypass Ratio,Part Ⅰ: Fan Stage Design and Experimental Results[R]. ASME GT 2010-22825.
[46] Vyvey P, Bosschaerts W, Villace V F, et al. Study of an Airbreathing Variable Cycle Engine[R]. AIAA 2011-5758.
[47] Alexiou A, Mathioudakis K. Development of Gas Turbine Performance Models Using a Generic Simulation Tool[R]. ASME GT 2005-68678.
[48] Alexiou A, Mathioudakis K. Gas Turbine Engine Performance Model Applications Using an Object-Oriented Simulation Tool[R]. ASME GT 2006-90339.
[49] Alexiou A, Baalbergen E H, Kogenhop O, et al. Advanced Capabilities for Gas Turbine Engine Performance Simulations[R]. ASME GT 2007-27086.
[50] Wood P J, Zenon R L, LaChapelle D G, et al. Turbofan Gas Turbine Engine with Variable Fan Outlet Guide Vanes[P]. USA: 7730714 2, 2010-06-08.
[51] Suder K L. TBCC Fan Stage Operability and Performance[C]. Cleveland: NASA FAP Annual Meeting-Hypersonic Project, 2007.
[52] Hah C. Near Stall Flow Analysis in the Transonic Fan of the RTA Propulsion System[R]. AIAA 2010-277.
[53] Celestina M L, Suder K L, Kulkarni S. Results of an Advanced Fan Stage Over a Wide Operating Range of Speed and Bypass Ratio, Part 2: Comparison of CFD and Experimental Results[R]. ASME GT 2010-23386.
[54] To W M. A CFD Case Study of a Fan Stage with Split Flow Path Subject to Total Pressure Distortion Inflow[R]. NASA/CR-2017-219698.
[55] 李少伟, 王如根, 吴培根. 风车状态静子角度调节对高负荷风扇性能的影响[J]. 空军工程大学学报, 2013, 14(4): 19-24.
[56] Lee J, Winslow R, Buehrle R J. The GE-NASA RTA Hyperburner Design and Development[R]. NASA/TM-2005-213803.
[57] Davoudzadeh F, Buehrle R, Liu N, et al. Numerical Simulation of the RTA Combustion Rig[R]. NASA/TM-2005-213899.
[58] 朱志新, 何小民, 薛冲, 等. 涡轮基组合循环发动机超级燃烧室燃烧性能试验[J]. 航空动力学报, 2015, 30(9): 2115-2121.
[59] 程晓军. 串联式TBCC超级燃烧室燃烧组织及性能研究[D]. 南京: 南京航空航天大学, 2015.
[60] Lederer R, Schwab R, Voss N. Hypersonic Airbreathing Propulsion Activities for Sanger[R]. AIAA 91-5040.
[61] Rued K, Ebenhoch G, Mark H. Thermal Management of Propulsion Systems in Hypersonic Vehicles[R]. AIAA 92-0516.
[62] Snyder L E, Escher D W, DeFrancesco R L, et al. Turbine Based Combination Cycle (TBCC) Propulsion Subsystem Integration[R]. AIAA 2004-3649.
[63] Gamble E J, Haid D. Thermal Management and Fuel System Model for TBCC Dynamic Simulation[R]. AIAA 2010-6642.
[64] Daniel A H, Eric J G. Integrated Turbine-Based Combined Cycle Dynamic Simulation Model[C]. Arlington: 58th Joint Army-Navy-NASA-Air-Force Propulsion Meeting, 2011.
[65] French M W, Allen G L. NASA VCE Test Bed Engine Aerodynamic Performance Characteristics and Test Results[R]. AIAA 81-1594.
[66] 唐海龙. 面向对象的航空发动机性能仿真系统及其应用[D]. 北京: 北京航空航天大学, 2000.
[67] 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.
[68] 贾琳渊. 变循环发动机控制规律设计方法研究[D]. 西安: 西北工业大学, 2017.
[69] Chen M, Tang H, Zhu Z. Goal Programming for Stable Mode Transition in Tandem Turbo-Ramjet Engines[J]. Chinese Journal of Aeronautics, 2009, 22(5): 486-492.
[70] 张明阳, 王占学, 张晓博, 等. 串联式TBCC发动机风车冲压模态性能模拟[J]. 航空动力学报, 2018, 33(12): 2939-2949.
[71] Lytle J K. The Numerical Propulsion System Simulation: An Overview[R]. NASA/TM 2000-209915.

变循环涡扇冲压组合发动机发展现状及关键技术分析

Development Status and Key Technologies of Variable Cycle Turbofan-Ramjet Engine

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