Optimum design method oriented thrust for over-under TBCC combined nozzle
-
摘要:
针对宽速域飞机机体/推进的强耦合，提出一种在给定几何尺寸约束下面向推力优化的并联涡轮冲压组合发动机（TBCC）组合喷管设计方法。通过理论分析和数值模拟相结合的手段，实现了宽速域组合喷管在欠膨胀和过膨胀流动状态下涡轮/冲压流道面积膨胀比的优化分配。在研究的涡轮/冲压落压比范围内，相比基准组合喷管，面向推力优化设计得到的组合喷管均能具有更高的推力性能，两者综合推力系数的差异在涡轮单独工作的过膨胀流动状态尤为明显，通过推力优化可使得马赫数为0.2和3时的推力系数分别提高4.89%和4.14%。推力优化喷管的升力和俯仰力矩随飞行马赫数的变化幅度相比基准喷管分别减小了33%和47.3%，这可以有效减小机体/推进耦合下全机气动焦点的变化范围，有利于减小宽速域飞机配平阻力并降低飞行器操稳控制难度。
Abstract:Considering the requirements on integration of aircraft/engines, a design method of over-under turbine based combined cycle engine (TBCC) nozzle oriented thrust optimization under a given geometric constraint was proposed. The optimal allocation of the area expansion ratio of the turbo-engine/ramjet nozzle at under-expansion and over-expansion state was realized by means of theoretical analysis and numerical simulation. Within the range of turbo-engine/ramjet pressure-drop-ratio, the TBCC nozzle designed for thrust optimization can achieve higher thrust performance than the baseline nozzle, and the difference in composite thrust coefficient was particularly obvious under the over-expansion state, where the thrust coefficients at Mach number of 0.2 and 3 can be increased by 4.89% and 4.14%, respectively, through thrust optimization. Furthermore, the lift force and pitching moment of thrust optimization nozzle changing with the Mach number were 33% and 47.3% smaller than those of the baseline nozzle, which can effectively reduce the range of aerodynamic focus of the whole aircraft, helping to reduce the trim resistance of wide-speed-range aircraft and the difficulty of flight control.
-
图 5 欠膨胀状态下理论计算与数值仿真结果对比
Figure 5. Comparison of theoretical results and numerical results for under-expansion state
图 6 过膨胀状态下的组合喷管推力系数
Figure 6. Thrust coefficient of combined nozzle for over-expansion state
图 7 过膨胀状态下转级板调节过程组合喷管马赫数分布
Figure 7. Mach number contour of combined nozzle during regulation for over-expansion state
图 8 组合喷管综合推力系数对比
Figure 8. Comparison of comprehensive thrust coefficient of combined nozzle
图 9 组合喷管涡轮单独工作状态马赫数分布对比
Figure 9. Comparison of Mach number contour of combined nozzle under turbofan-only conditions
图 10 组合喷管共同工作状态马赫数分布对比
Figure 10. Comparison of Mach number contour of combined nozzle under turbofan-ramjet conditions
图 12 组合喷管的俯仰力矩特性对比
Figure 12. Comparison of pitching moment characteristics of combined nozzle
表 1 组合喷管计算工况
Table 1. Calculation conditions for combined nozzle
状态 Ma h/km π Tt/K WL CY WL CY 涡轮
单独工作0.2～3 0～18 3～25 1～20 2000 290～600 涡轮、冲压
共同工作2～3.5 12～20 10～45 15～35 2000 2000 
下载: 导出CSV
表 2 欠膨胀状态下的计算参数
Table 2. Calculation parameters for under-expansion state
Ma h/km π Tt/K $ A_{\text {out,ideal}} $/H $ A_{\text {out,real}} $/H WL CY WL CY 2.5 15 12 20 2000 2000 1.225 1
下载: 导出CSV
表 3 过膨胀状态下的计算参数
Table 3. Calculation parameters for over-expansion state
Ma h/km π Tt/K $ A_{\text {out,ideal}} $/H $ A_{\text {out,real}} $/H WL CY WL CY 1.5 9 8 1.5 2000 330 0.625 1
下载: 导出CSV
-
[1] COCKRELL C, AUSLENDER A, GUY R, et al. Technology roadmap for dual-mode scramjet propulsion to support space-access vision vehicle development[R]. Orleans, US: AIAA/AAAF 11th International Space Planes and Hypersonic Systems and Technologies Conference, 2002. [2] SNYDER L E, ESCHER D W. Turbine based combination cycle (TBCC) propulsion subsystem integration[R]. AIAA 2004-3649, 2004. [3] MICHAEL K, RONALD M, JOHN O. What’s cheaper to fly: rocket or TBCC? Why?[R]. AIAA 2010-2326, 2010. [4] BARTOLOTTA P A, MCNELIS N B, SHAFER D G. High speed turbines: development of a turbine accelerator (RTA) for space access[R]. Norfolk, US: 12th AIAA International Space Planes and Hypersonic Systems and Technologies, 2011. [5] MAKOTO O, KAZUO M, KAZUHIKO I. Engineering research for super/hyper-sonic transport propulsion system[R]. ISABE 99-7004, 1999. [6] STEELANT J. LAPCAT: high-speed propulsion technology[R]. Educational Notes RTO-EN-AVT-150, 2008. [7] 陈博,桂丰,李茜,等. 国外并联式涡轮基组合循环发动机技术发展途径浅析[J]. 燃气涡轮试验与研究,2019,32(1): 57-62. doi: 10.3969/j.issn.1672-2620.2019.01.011CHEN Bo,GUI feng,LI Qian,et al. Study on the development approach of foreign over/under TBCC engine technology[J]. Gas Turbine Experiment and Research,2019,32(1): 57-62. (in Chinese) doi: 10.3969/j.issn.1672-2620.2019.01.011 [8] 马松,林鹏,左林玄,等. 并联TBCC动力对高超声速飞行器性能的影响[J]. 国防科技大学学报,2019,41(2): 1-7. doi: 10.11887/j.cn.201902001MA Song,LIN Peng,ZUO Linxuan,et al. Influence of over-under TBCC on the performance of hypersonic aircraft[J]. Journal of National University of Defense Technology,2019,41(2): 1-7. (in Chinese) doi: 10.11887/j.cn.201902001 [9] 左林玄,张辰琳,王霄,等. 高超声速飞机动力需求探讨[J]. 航空学报,2021,42(8): 77-93.ZUO Linxuan,ZHANG Chenlin,WANG Xiao,et al. Requirement of hypersonic aircraft power[J]. Acta Aeronautica et Astronautica Sinica,2021,42(8): 77-93. (in Chinese) [10] 郑日恒,陈操斌. 涡轮基组合循环发动机推力陷阱问题解决方案[J]. 火箭推进,2021,47(6): 21-32. doi: 10.3969/j.issn.1672-9374.2021.06.003ZHENG Riheng,CHEN Caobin. Overview of solutions to TBCC engine thrust trap problem[J]. Journal of Rocket Propulsion,2021,47(6): 21-32. (in Chinese) doi: 10.3969/j.issn.1672-9374.2021.06.003 [11] 凌文辉,侯金丽,韦宝禧,等. 空天组合动力技术挑战及解决途径的思考[J]. 推进技术,2018,39(10): 2171-2176. doi: 10.13675/j.cnki.tjjs.2018.10.002LING Wenhui,HOU Jinli,WEI Baoxi,et al. Technical challenge and potential solution for aerospace combined cycle engine[J]. Journal of Propulsion Technology,2018,39(10): 2171-2176. (in Chinese) doi: 10.13675/j.cnki.tjjs.2018.10.002 [12] EDWARDS C, SMALL W, WEIDNER J, et al. Studies of scramjet/airframe integration techniques for hypersonic aircraft[R]. Pasadena, US: 13th Aerospace Sciences Meeting, 1975. [13] LEDERER R, KRUGER W. Nozzle development as a key element for hypersonics[R]. Munich, Germany: 5th International Aerospace Planes and Hypersonics Technologies Conference, 1993. [14] WERNER W H,JONATHAN M K. Aeropropulsion design challenges for Mach 7 reusable combined- cycle flight demonstrator[J]. Technology Review Journal,2006(1): 14-28. [15] 莫建伟,徐惊雷,乔松松. 并联式TBCC发动机排气系统性能数值模拟[J]. 推进技术,2013,34(4): 463-469. doi: 10.13675/j.cnki.tjjs.2013.04.008MO Jianwei,XU Jinglei,QIAO Songsong. Numerical study of the over-under TBCC exhaust system[J]. Journal of Propulsion Technology,2013,34(4): 463-469. (in Chinese) doi: 10.13675/j.cnki.tjjs.2013.04.008 [16] MO J,XU J,ZHANG L. Design and experimental study of an over-under TBCC exhaust system[J]. Journal of Engineering for Gas Turbines and Power,2014,136(1): 014501.1-014501.8. [17] 丁煜朔, 液体火箭发动机喷管型面设计与传热仿真分析研究[D]. 北京: 中国运载火箭技术研究院, 2019.DING Yusuo. Study on contour design and heat transfer simulation of liquid rocket engine nozzle[D]. Beijing: China Academy of Launch Vehicle Technology, 2019. (in Chinese) [18] SPAID F W, KEENER E R. Hypersonic nozzle-afterbody CFD code validation: Part Ⅰ experimental measurements[R]. AIAA 1993-0607, 1993. [19] 于洋. RBCC单边膨胀喷管过膨胀流动分离现象及机理研究[D]. 南京: 南京航空航天大学, 2017.YU Yang. Research on the separation phenomena and mechanism of over-expanded single expansion ramp nozzle for RBCC engine[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2017. (in Chinese) -
点击查看大图
计量
- 文章访问数: 813
- HTML浏览量: 659
- PDF量: 103
- 被引次数: 0