串联式TBCC进气道模态转换模拟器设计及其特性分析

doi:10.7527/S1000-6893.2016.0103

流体力学与飞行力学

本期目录 | 过刊浏览 | 高级检索

前一篇 | 后一篇

串联式TBCC进气道模态转换模拟器设计及其特性分析

刘君, 袁化成, 葛宁

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

收稿日期:2016-01-18 修回日期:2016-03-28 出版日期:2016-12-15 发布日期:2016-03-29
通讯作者: 袁化成,Tel.:025-84892200-2415,E-mail:yuanhuacheng@nuaa.edu.cn E-mail:yuanhuacheng@nuaa.edu.cn
作者简介:刘君,男,博士研究生。主要研究方向:组合动力进气道设计及仿真。Tel.:025-84892200-2415,E-mail:liujunnever@163.com;袁化成,男,博士,副教授。主要研究方向:高超声速进气道设计、仿真及试验技术。Tel.:025-84892200-2415,E-mail:yuanhuacheng@nuaa.edu.cn;葛宁,男,博士,教授。主要研究方向:气轮机动力学及设计。Tel.:025-84892200-2613,E-mail:gening@nuaa.edu.cn
基金资助:
航空科学基金（2015ZB52016）；中央高校基本科研业务费（NS2015025）

Design and flow characteristics analysis of mode transition simulator for tandem type TBCC inlet

LIU Jun, YUAN Huacheng, GE Ning

Jiangsu Province Key Laboratory of Aerospace Power Systems, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

Received:2016-01-18 Revised:2016-03-28 Online:2016-12-15 Published:2016-03-29
Supported by:
Aeronautical Science Foundation of China (2015ZB52016); the Fundamental Research Funds for the Central Universities (NS2015025)

摘要/Abstract

摘要：

为了实现涡轮基组合循环（TBCC）推进系统平稳模态转换过程的模拟，在前期风洞试验研究的基础上对串联式TBCC进气道模态转换模拟器进行重新设计。采用线性化及非对称的思路对该模拟器进行设计并对其特性展开数值仿真研究。结果表明：该模拟器不仅需要模拟发动机工况改变引起的背压变化，而且能通过流通截面面积线性变化，实现两个通道的流量分配。该装置的特点是能保证模态转换过程中每一点的涡轮/冲压通道的总堵塞比不变，使本文所研究的进气道在总堵塞比保持为65%时进行模态转换，结尾激波基本维持在喉道等直段内且进气道出口马赫数基本维持在0.30，流量系数基本为0.45，涡轮/冲压通道流量呈线性变化，与预期目标一致。

关键词: 吸气式高超声速推进系统, 涡轮基组合循环(TBCC), 串联式TBCC进气道, 模态转换模拟器, 风洞试验

Abstract:

In order to simulate the smooth mode transition of turbine based combined cycle (TBCC) propulsion system, the mode transition simulator for tandem type TBCC inlet is redesigned based on the experiences learned from the high speed wind tunnel test. The linear and asymmetric methods are then used to design this simulator, and its flow characteristics is analyzed through numerical simulation. The results indicate that the simulator is used not only to simulate the change of back-pressure caused by the change of engine operation condition, but also to distribute the mass flow into the two flowpaths linearly during the mode transition. The new simulator can keep the sum of the throttle ratios of turbojet/ramjet flowpaths as a constant in every moment during the process. For the inlet discussed in this paper, when the total throttle ratio is equal to 65% during the mode transition, the terminal shock locates in the throat of the TBCC inlet, the Mach number at the aerodynamic interface plane of this inlet is basically equal to 0.30, the flow ratio of this section is basically equal to 0.45, and the flow ratio into two flowpaths is distributed linearly. This simulator thus can meet the needs of expected goal.

Key words: airbreathing hypersonic propulsion system, turbine based combined cycle (TBCC), tandem type TBCC inlet, mode transition simulator, wind tunnel test

中图分类号:

V236

刘君, 袁化成, 葛宁. 串联式TBCC进气道模态转换模拟器设计及其特性分析[J]. 航空学报, 2016, 37(12): 3675-3684.

LIU Jun, YUAN Huacheng, GE Ning. Design and flow characteristics analysis of mode transition simulator for tandem type TBCC inlet[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2016, 37(12): 3675-3684.

参考文献

[1] 吴颖川, 贺元元, 贺伟, 等. 吸气式高超声速飞行器机体推进一体化技术研究进展[J]. 航空学报, 2015, 36(1):245-260. WU Y C, HE Y Y, HE W, el al. Progress in airframe-propulsion integration technology of air-breathing hypersonic vehicle[J]. Acta Aeronautica et Astronautica Sinica, 2015, 36(1):245-260(in Chinese).
[2] RONDEAU C M, JORRIS T R. X-51A scramjet demonstrator program waverider ground and flight test:ADA593742[R]. Virginia:Armed Services Technical Information Agency Documents, 2013.
[3] SOSOUNOV V A, TSKHOVREBOV M M, SOLONIN V I, et al. The study of experimental turboramjets:AIAA-1992-3720[R]. Reston:AIAA, 1992.
[4] 张华军, 郭荣伟, 李博. TBCC进气道研究现状及其关键技术[J]. 空气动力学报, 2010, 28(5):613-620. ZHANG H J, GUO R W, LI B. Research status of TBCC inlet and its key technologies[J]. Acta Aerodynamic Sinica, 2010, 28(5):613-620(in Chinese).
[5] SACHER P W. The engineering design of engine/airframe integration for the Sänger fully reusable space transportation system:ADA592434[R]. Virginia:Armed Services Technical Information Agency Documents, 2010.
[6] LEDERER R, VOSS N, SCHWAB R R. Hypersonic airbreathing propulsion activities for Sänger:AIAA-1991-5040[R]. Reston:AIAA, 1991.
[7] MIYAGI H, MIYAGAWA H, MONJI T, et al. Combined cycle engine research in Japanese HYPR project:AIAA-1995-2751[R]. Reston:AIAA, 1995.
[8] MIYAGI H, KIMURA H, KISHI K, et al. Combined cycle engine research in Japanese HYPR program:AIAA-1998-3278[R]. Reston:AIAA, 1998.
[9] TAKAO O, YOSHINARI E, HIDEMASA N, et al. Experimental approach to HYPR Mach 5 ramjet propulsion system:AIAA-1998-3277[R]. Reston:AIAA, 1998.
[10] SAUNDERS J D, SLATER J W, DIPPOLD V, et al. Inlet mode transition screening test for a turbine-based combined-cycle propulsion system[J]. Jannaf, 2008.
[11] ANDRE W M, ASHWANI K G, LEWIS M J. Critical issues in TBCC modeling:AIAA-2004-3827[R]. Reston:AIAA, 2004.
[12] SAUNDERS J D, STUEBER T J, THOMAS S R, et al. Testing of the NASA hypersonic project combined cycle engine large scale inlet mode transition experiment (CCE LIMX):NASA/TM-2012-217217[R]. Washington, D.C.:NASA, 2012.
[13] 陈敏, 唐海龙, 刘大响, 等. 最大飞行马赫数3.5的吸气式动力方案初步研究[J]. 航空动力学报, 2009, 24(7):1564-1569. CHEN M, TANG H L, LIU D X, et al. Conceptual design of Mach number 3.5 air-breathing propulsion system[J]. Journal of Aerospace Power, 2009, 24(7):1564-1569(in Chinese).
[14] 陈敏, 唐海龙, 朱大明, 等. 高超声速串联式组合动力装置方案[J]. 北京航空航天大学学报, 2007, 33(3):265-268. CHEN M, TANG H L, ZHU D M, et al. Hypersonic combined cycle engine concept with tandem layout[J]. Journal of Beijing University of Aeronautics and Astronautics, 2007, 33(3):265-268(in Chinese).
[15] CHEN M, ZHU Z L, ZHU D M, et al. Performance analysis tool for turbine based combined cycle engine concept[J]. Journal of Astronautics, 2006, 27(5):854-859.
[16] 刘增文, 王占学, 蔡元虎, 等. 涡轮基组合循环发动机性能数值模拟[J]. 推进技术, 2009, 30(1):1-5. LIU Z W, WANG Z X, CAI Y H, et al. Numerical simulation of performance for turbine based combined cycle propulsion system[J]. Journal of Propulsion Technology, 2009, 30(1):1-5(in Chinese).
[17] 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, 2009, 24(12):2756-2762. HUANG H C, WANG Z X, CAI Y H. Analysis of mode transition with thrust smoothing of small turbine/ramjet combined cycle engine[J]. Journal of Aerospace Power, 2009, 24(12):2756-2762(in Chinese).
[18] 袁化成, 刘君, 华正旭, 等. 一种串联式TBCC变几何进气道气动设计及实验验证[C]//第十七届中国空气动力学物理气体动力学学术交流会暨第三届高超声速冲压发动机内外流耦合流动研讨会论文集,2015. YUAN H C, LIU J, HUA Z X, et al. The design and experiment investigation of variable geometry TBCC inlet of tandem type[C]//17th Aerodynamics & Physics Gas Dynamics Academic Conference of China, 2015(in Chinese).
[19] 王亚岗, 袁化成, 郭荣伟. TBCC用轴对称进气道流量控制技术研究[J]. 推进技术, 2013, 34(12):1606-1615. WANG Y G, YUAN H C, GUO R W. Research on mass-flow controlling technology of TBCC axisymmetric inlet[J].Journal of Propulsion Technology, 2013, 34(12):1606-1615(in Chinese).
[20] 张华军, 刘兴国, 郭荣伟, 等. TBCC进气道涡轮通道扩张段设计及涡轮模态特性[J]. 航空动力学报, 2014, 29(1):181-191. ZHANG H J, LIU X G, GUO R W, et al. Design of turbo diffuser for TBCC inlet and characteristics of turbo mode[J]. Journal of Aerospace Power, 2014, 29(1):181-191(in Chinese).
[21] 李璞, 郭荣伟. 一种带前体的高超声速矩转圆形进气道研究[J]. 航空学报, 2009, 30(4):625-629. LI P, GUO R W. Investigation of a hypersonic inlet with rectangular-to-circular shape transition and forebody[J]. Acta Aeronautica et Astronautica Sinica, 2009, 30(4):625-629(in Chinese).

E-mail：hkxb@buaa.edu.cn

关于我们

期刊社服务

专业学科

封面文章

友情链接

主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

串联式TBCC进气道模态转换模拟器设计及其特性分析

Design and flow characteristics analysis of mode transition simulator for tandem type TBCC inlet

PDF (PC)

可视化

摘要/Abstract

引用本文

使用本文

参考文献

相关文章 15

编辑推荐

Metrics

本文评价

[1]	孙朋朋, 刘平安, 樊枫, 曾伟. 悬停状态共轴刚性旋翼机身气动干扰特性[J]. 航空学报, 2024, 45(9): 529284-529284.
[2]	王畅, 何龙, 徐栋霞, 唐敏, 马率, 吴希明. 共轴刚性旋翼桨毂流动控制减阻研究[J]. 航空学报, 2024, 45(9): 529084-529084.
[3]	张卫国, 唐敏, 武杰, 彭先敏, 章贵川, 聂博文, 王亮权, 李超群. 倾转旋翼机风洞试验综述[J]. 航空学报, 2024, 45(9): 530114-530114.
[4]	聂博文, 王亮权, 黄志银, 何龙, 杨仕鹏, 颜鸿涛, 章贵川. 复合式高速无人直升机飞行动力学建模与控制策略设计[J]. 航空学报, 2024, 45(9): 529848-529848.
[5]	刘柳, 向先宏, 张宇飞, 陈海昕, 魏闯, 朱剑, 杨普. 一种高升阻比非常规翼身融合燕尾气动布局[J]. 航空学报, 2024, 45(6): 629630-629630.
[6]	李海星, 周峰, 颜巍, 白峰, 赵克良. 砂纸冰对民机平尾气动特性的影响[J]. 航空学报, 2024, 45(2): 128657-128657.
[7]	李学良, 李创创, 苏伟, 吴杰. 分布式粗糙元对高超声速边界层不稳定性的影响试验[J]. 航空学报, 2024, 45(2): 128627-128627.
[8]	刘宇, 秦梦婕, 王强, 易贤. 含盐海水飞沫的结冰风洞试验相似准则[J]. 航空学报, 2023, 44(S2): 729297-729297.
[9]	杨秋明, 朱永峰, 陈华伟, 刘晓林. 镂空图案化电加热组件防冰性能试验研究[J]. 航空学报, 2023, 44(S2): 729334-729334.
[10]	高世琦, 丁博, 解旭祯, 李铮, 陈林, 钱首元, 焦子涵, 白光辉. 等离子体激励在高速流动中的减阻机制[J]. 航空学报, 2023, 44(S2): 729373-729373.
[11]	许岭松, 吴渊, 朱东宇, 张付昆, 刘昱. FL⁃61结冰风洞翼型俯仰振荡机构研制[J]. 航空学报, 2023, 44(S2): 729296-729296.
[12]	金毅, 孙姝, 郭赟杰, 谭慧俊, 张悦. 超声速可调进气道内流双解现象及其节流特性[J]. 航空学报, 2023, 44(7): 127134-127134.
[13]	李俊红, 靳旭红, 刘春风, 苗文博, 程晓丽. 临近空间高速飞行器微量气动力试验及计算[J]. 航空学报, 2023, 44(6): 127072-127072.
[14]	曾宪昂, 赵冬强, 李俊杰, 严泽洲, 刘成玉. 弹性机翼阵风减缓控制策略风洞试验[J]. 航空学报, 2023, 44(4): 226869-226869.
[15]	刘畅, 张耘隆, 闫指江, 赵磊, 季辰. 锤头体火箭弹性模型脉动压力风洞试验[J]. 航空学报, 2023, 44(23): 128384-128384.