一种双流路变几何涡轮基组合循环进气道的设计与仿真

王德鹏; 庄逸; 谭慧俊; 张鸿; 杜沫辰; 李光胜

doi:10.13224/j.cnki.jasp.2015.11.018

一种双流路变几何涡轮基组合循环进气道的设计与仿真

doi: 10.13224/j.cnki.jasp.2015.11.018

1. 南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室, 南京 210016;
2. 先进航空发动机协同创新中心, 北京 100191;
3. 中国民航大学中欧航空工程师学院, 天津 300300

基金项目:

国家自然科学基金(91216112, 11172133,1172136)

教育部新世纪优秀人才支持计划(NCTE-11-0831)

国防基础科研

详细信息

作者简介:
王德鹏(1990-),男,甘肃白银人,硕士生,主要从事内流动力学的计算与实验研究.

中图分类号: V211.3
计量
- 文章访问数: 1039
- HTML浏览量: 4
- PDF量: 647
- 被引次数: 0
出版历程
- 收稿日期: 2014-04-12
- 刊出日期: 2015-11-28

Design and simulation of a dual-channel variable geometryturbine based combined cycle inlet

1. Jiangsu Province Key Laboratory of Aerospace Power Systems, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;
2. Collaborative Innovation Center for Advanced Aero-Engine, Beijing 100191, China;
3. Sino-European Institute of Aviation Engineering, Civil Aviation University of China, Tianjin 300300, China

摘要

摘要: 针对涡轮基组合循环(TBCC)发动机宽速域的工作需求,提出了一种外并联双流路的变几何进气道方案.通过转动涡轮和亚燃通道的唇罩前缘,可对进气道的捕获高度进行调节,并可实现模态切换;通过亚燃通道下壁面的多连杆机构,可对进气道的内收缩比进行调节,以实现进气道在宽马赫数范围的高效工作.通过对该进气道进行CFD数值模拟,获得了其流动和工作特性,并与定几何进气道方案进行了对比分析.研究结果表明:该变几何进气道具较宽的工作马赫数范围,且具有良好气动性能.与定几何方案相比,该变几何进气道在来流马赫数Ma为2.5,3.0,4.0时的总压恢复系数分别高出了12.5%,30.2%,133.3%.
- 涡轮基组合循环 /
- 变几何进气道 /
- 外并联 /
- 双流路 /
- 亚燃通道
Abstract: To meet the demand of turbine based combined cycle (TBCC) engine, a design concept of external parallel dual-channel variable inlet was proposed. By rotating cowls of turbine channel and ramjet channel, the inlet can regulate mass flow capture height and realize mode transition. Besides, the inlet can obtain good performance in a wide Mach range by adjusting internal contraction ratio with the Multi-linkages mechanism under the lower wall of ramjet channel. Numerical simulation method was applied to investigate the flow characteristics and the performance of the inlet. The results reveal that the variable inlet can work in a wide Mach range with good performance in the work envelope. Compared with fixed geometry inlet, the variable geometry inlet can increase total pressure recovery coefficient up to 12.5%, 30.2% and 133.3% at Mach number is 2.5,3.0 and 4.0, respectively.
- turbine based combined cycle(TBCC) /
- variable inlet /
- external parallel /
- dual-channel /
- ramjet channel

HTML

参考文献(22)

[1]	Cockrell C E,Jr,Auslender A H,Guy R W,et al.Technology roadmap for dual-mode scramjet propulsion to support space-access vision vehicle development[R].AIAA-2002-5188,2002.
[2]	Thomas S R.TBCC discipline overview hypersonic project[R].NASA/TM-2011-011395,2011.
[3]	Marshall A W,Gupta A K,Lewis M J,et al.Critical issues in TBCC modeling[R].AIAA-2004-3827,2004.
[4]	Tanatsugu N,Naruo Y,Rokutanda I.Test results of the air turbo ramjet for a future space plane[J].Acta Astronautica,1994,32(12):785-796.
[5]	Sato T,Tanatsugu N,Naruo Y,et al.Developmentstudy on ATREX engine[R].AIAA 1996-4553,1996.
[6]	Miyagi H,Kimura H,Kishi K,et al.Combined cycle engine research in Japanese HYPR program[R].AIAA 1998-3287, 1998.
[7]	Miyagi H,Kimura H,Kishi K,et al.Combined cycle engine research in Japanese HYPR project[R].AIAA 1995-2751,1995.
[8]	Itahara H,Nakata Y,Kimura T,et al.Research and development of HYPR90-T variable cycle turbo engine for HST[R].ISABE 1997-7013,1997.
[9]	Gippet J M,Rollin G,Murakami A,et al.Design evaluation of a hypersonic inlet for a SST/HST engine by CFD and test[R].ISABE-1997-7030,1997.
[10]	Utaka Y,Taneda H,Murakami A,et al.The aerodynamic design and wind tunnel tests of a combined intake for a supersonic transport[R].ISABE 1997-7139,1997.
[11]	Futamura H,Yanagi R,Mitani T.Experimental approach to the HYPR Mach 5 ramjet propulsion system[R].AIAA 1998-3277,1998.
[12]	Clinton C R,Hunt J L.Airbreathing hypersonic technology vision vehicles and development dreams[R].AIAA 1999-4978,1999.
[13]	Pegg R J,Hunt J L,Petley D H.Design of a hypersonic waverider-derived airplane[R].AIAA 1993-0401,1993.
[14]	Spoth K A,Moses P L.Structural design and analysis of a Mach zero to five turbo-ramjet sysem[R].AIAA 1993-1983,1993.
[15]	Snyder L E,Escher D W,De Francesco R L,et al.Turbine based combination cycle (TBCC) propulsion subsystem integration[R].AIAA-2004-3649,2004.
[16]	Albertson C W,Emami S,Trexler C A.Mach 4 test results of a dual-flowpath,turbine based combined cycle inlet[R].AIAA-2006-8138,2006.
[17]	Dippold III V F.Computational analyses of the LIMX TBCC inlet high-speed flowpath[R].NASA/TM-2012-217219, 2012.
[18]	李龙,李博.涡轮基组合循环发动机并联式进气道的气动特性[J].推进技术,2008,29(6):667-672. LI Long,LI Bo.Aerodynamic characteristics of over/under inlet for turbine based combined cycle engine[J].Journal of Propulsion Technology,2008,29(6):667-672.(in Chinese)
[19]	严红明,钟兢军,杨凌,等.组合发动机可调进气道气动性能[J].航空动力学报,2011,26(2):458-467. YAN Hongming,ZHONG Jingjun,YANG Ling,et al.Aerodynamic characteristics research on variable geometry inlet of combined cycle engine[J].Journal of Aerospace Power,2011,26(2):458-467.(in Chinese)
[20]	张华军,郭荣伟,谢旅荣.内并联型TBCC进气道方案设计及验证[J].航空动力学报,2012,27(11):2475-2483. ZHANG Huajun,GUO Rongwei,XIE Lürong.The design and test of internal parallel TBCC inlet[J].Journal of Aerospace Power,2012,27(11):2475-2483.(in Chinese)
[21]	张华军,郭荣伟,谢旅荣.TBCC进气道变几何泄流腔研究[J].航空动力学报,2012,27(12):2714-2723. ZHANG Huajun,GUO Rongwei,XIE Lürong.The investigation of variable geometry bleed chamber of TBCC inlet[J].Journal of Aerospace Power,2012,27(12):2714-2723.(in Chinese)
[22]	Herrman C D,Koschel W W.Experimental investigation of the internal compression of a hypersonic intake[R].AIAA-2002-4130,2002.