串联式TBCC发动机风车冲压模态性能模拟

张明阳; 王占学; 张晓博; 周莉

doi:10.13224/j.cnki.jasp.2018.12.014

串联式TBCC发动机风车冲压模态性能模拟

doi: 10.13224/j.cnki.jasp.2018.12.014

西北工业大学动力与能源学院，西安 710129

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出版历程
- 收稿日期: 2018-02-26
- 刊出日期: 2018-12-28

Simulation of windmilling-ram mode performance for tandem TBCC engine

摘要

摘要: 建立了基于部件低转速特性匹配的串联式涡轮基组合循环（TBCC）发动机风车冲压模态性能计算模型，提出了压气机低转速大流量特性扩展方法，由换算扭矩代替等熵效率表示旋转部件特性，解决了低转速部件效率不连续相关问题。分析了冲压外涵面积变化和涡轮功率提取对风车冲压模态性能及部件匹配的影响规律，并基于推力、流量连续准则设计了涡轮模态至冲压模态转换过程（含风车冲压模态）的参数调节规律。计算结果表明：在风车冲压模态下，冲压外涵面积变化对风扇工作状态有显著影响，对压气机影响较小；涡轮可提取功率随着风车转速的减小先增加后降低，比冲随提取功率的增加基本呈线性降低趋势，功率提取位置（高、低压涡轮）对部件匹配有显著影响。
- 涡轮基组合循环（TBCC） /
- 风车冲压 /
- 低转速特性拓展 /
- 功率提取 /
- 模态转换
Abstract: The windmilling-ram mode performance simulation model was developed for a tandem turbine-based combined cycle (TBCC) engine based on the matching of the component low-speed characteristics. Extrapolation method for the compressor characteristics at low-speed and high flow region was proposed, and the issues associated with the component efficiency discontinuity at low speeds were solved through substitution of isentropic efficiency by corrected torque while describing the characteristics map of rotational component. Influence of ram bypass area variation and turbine power offtake on the windmilling-ram mode performance and component matching was analyzed, and parameter regulating laws during mode transition, including the windmilling-ram mode, were investigated based on the smooth variation of engine thrust and airflow. The simulation results showed that: under the windmilling-ram mode, the fan operation was strongly related to the ram bypass area variation, exerting a relatively small influence on the compressor operation; with the increase of the windmilling spool speed, turbine power offtake first rose and then dropped, and the specific impulse was linearly reduced with the increase of turbine power offtake, while the power offtake location of high-pressure or low-pressure turbine had a significant influence on the component matching.
- tandem turbine-based combined cycle (TBCC) /
- windmilling-ram /
- low-speed characteristics extrapolation /
- power offtake /
- mode transition

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参考文献(24)

[1]	MCNELIS N,BARTOLOTTA.Revolutionary turbine accelerator (RTA) demonstrator［R］.AIAA-2005-3250,2005.
[2]	LEDERER R,SCHWAB R,VOSS N.Hypersonic airbreathing propulsion activities for SNGER［R］.AIAA 91-5040,1991.
[3]	SOSOUNOV V A,TSKHOVREBOV M M,SOLONIN V I,et al.The study of experimental turboramjets［R］.AIAA 92-3720,1992.
[4]	MIYAGI H,KIMURA H,KISHI K,et al.Combined cycle engine research in Japanese HYPR program［R］.AIAA 98-3278,1998.
[5]	BLEVINS G,HARTSEL J,POWELL T.Variable concepts for high Mach applications［R］.AIAA 87-2103,1987.
[6]	刘增文.高超声速飞行器/涡轮基组合循环发动机一体化设计研究［D］.西安:西北工业大学,2010.LIU Zengwen.Integrated design of turbine based combined cycle engine and hypersonic vehicle［D］.Xian:Northwestern Polytechnical University,2010.(in Chinese)
[7]	何时慧,吴国钏,华清.涡扇发动机风车特性计算［J］.航空发动机,1997,23(3):1-9.
[8]	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):19-23.LI Shaowei,WANG Rugen,WU Peigen.Research on effect of stator setting angle adjustment on the highly loaded fan performance during windmilling［J］.Journal of Air Force Engineering University,2013,14(4):19-23.(in Chinese)
[9]	黄红超,王占学,蔡元虎.基于推力连续准则的小型涡轮冲压组合发动机模态转换过程分析［J］.航空动力学报,2010,25(12):2756-2762.HUANG Hongchao,WANG Zhanxue,CAI Yuanhu.Analysis of mode transition with thrust smoothing of small turbine/ramjet combined cycle engine［J］.Journal of Aerospace Power,2010,25(12):2756-2762.(in Chinese)
[10]	CHEN M,TANG H L,ZHU Z L.Goal programming for stable mode transition in tandem turbo-ramjet engines［J］.Chinese Journal of Aeronautics,2009,22(5):486-492.
[11]	MIYAGI H,MIYAGAWA H,MONJI T,et al.Combined cycle engine research in Japanese HYPR project［R］.AIAA 95-2751,1995.
[12]	KONDO M,MORII S,MURASHIMA K.Overview of the Japanese national project “super/hyper-sonic transport propulsion system program”［R］.AIAA 95-2445,1995.
[13]	YANAGI R,MORITA M,WATANABE Y,et al.Conceptual design of turbo-accelerator for HST combined cycle engine［R］.ASME Paper 92-GT-253,1992.
[14]	ITAHARA H,KOHARA S,TAKAGI S,et al.Turbo engine research in Japanese HYPR project for HST combined cycle engines［R］.AIAA 94-3358,1994.
[15]	SUZUKI M,KUNO N,TOBITA A,et al.Current status of fan component research in HYPR program［R］.AIAA 98-3280,1998.
[16]	KAWANO M,KUYAMA T,KOBAYASHI M,et al.Development of a high temperature combustor for HYPR Mach 3 turbojet engines［R］.AIAA 98-3281,1998.
[17]	SHIMIZU K,NOGAMI R.Current status of low pressure turbine component research in HYPR program［R］.AIAA 98-3282,1998.
[18]	KUO S C,DOERNBACH J D,CHAMPAGNE G,et al.A scoping study for hypersonic transport propulsion systems［R］.ASME Paper 92-GT-409,1992.
[19]	WALSH P P,FLETCHER P.Gas turbine performance［M］.2nd.Oxford,UK:Blackwell Science ltd,2004.
[20]	KURZKE J.How to get component maps for aircraft gas turbine performance calculations［R］.ASME Paper 96-GT-164,1996.
[21]	REIGLER C,BAUER M,KURZKE J.Some aspects of modeling compressor behavior in gas turbine performance calculations［J］.Journal of Turbomachinery,2001,123(2):372-378.
[22]	王宇,刘建勋,李应红,等.基于抛物线外推的压气机低转速特性研究［J］.航空动力学报,2009,24(5):1136-1142.WANG Yu,LIU Jianxun,LI Yinghong,et al.Research on low speed characteristics of compressor based on parabola extrapolation［J］.Journal of Aerospace Power,2009,24(5):1136-1142.(in Chinese)
[23]	SEXTON W R.A method to control turbofan engine starting by varying compressor surge valve bleed［D］.Blacksburg,Virginia:The Virginia Polytechnic Institute and State University,2001.
[24]	GAUDET S R,GAUTHIER D.A simple sub-idle component map extrapolation method［R］.ASME Paper GT2007-27193,2007.