Application of Exergy Analysis in SynergisticAir-Breathing Rocket Engine

doi:10.13675/j.cnki. tjjs. 180542

Journal of Propulsion Technology ›› 2019, Vol. 40 ›› Issue (8): 1693-1701.DOI: 10.13675/j.cnki. tjjs. 180542

• System • Previous Articles Next Articles

Application of Exergy Analysis in SynergisticAir-Breathing Rocket Engine

School of Astronautics,Beihang University,Beijing 100191,China

Published:2021-08-15

㶲分析在协同吸气式火箭发动机中的应用

北京航空航天大学宇航学院，北京 100191

作者简介:屈原，硕士生，研究领域为液体火箭发动机和组合循环发动机技术。E-mail：quyuanbuaa@sina.com
基金资助:
国家自然科学基金青年科学基金 51706010国家自然科学基金青年科学基金（51706010）。

Abstract

Abstract: In order to study the loss distribution and performance characteristics of the Synergistic Air-Breathing Rocket Engine (SABRE) circulatory system, the exergy analysis was carried out for SABRE4 engine system. The representative flight Mach number Ma=4 was chosen as the main operating condition to study the effects of different working parameters on the exergy loss distribution and exergy efficiency. The maximum exergy efficiency could be obtained by adjusting the exergy loss distribution. The results show that the engine exergy loss is mainly concentrated in the combustion process and gas discharge. For a given flight condition, the exergy efficiency of the engine will be greater as the hydrogen consumption is smaller. when the total hydrogen flow remains unchanged, there is a suitable oxygen-fuel ratio which makes the engine exergy efficiency maximum by changing the oxygen-fuel ratio of the preburner. For a given total hydrogen flow, the engine exergy efficiency increases first and then decreases with increasing the flight Mach number. The maximum exergy efficiency occurring in the vicinity of Ma=4 is 64.6%. The corresponding combustion exergy loss is 16.2% and 13.8% for gas exergy loss. Through the exergy analysis of the system, the exergy loss distribution of the engine is clarified.

Key words: Circulatory system;Loss distribution;Exergy analysis;Exergy loss;Exergy efficiency;SABRE

摘要： 为了研究协同吸气式火箭发动机（SABRE）循环系统的损失分布规律以及性能特性，针对SABRE4发动机系统开展了?分析，选择具有代表性的飞行马赫数Ma=4作为主要工况，研究不同工作参数对系统?损失分布和?效率的影响，通过调节?损失分布以获得最大?效率。研究结果表明：发动机?损失主要集中在燃烧过程和燃气排出，对于给定飞行条件，耗氢量越小，发动机?效率越大；当主路氢流量固定，调节预燃室氧燃比，存在合适的氧燃比使得发动机?效率最大；在给定主路氢流量条件下，发动机?效率随着飞行马赫数增大呈先增大后减小，在Ma=4附近达到最大，最大?效率为64.6%，对应的?损失分别为燃烧?损失16.2%，燃气排出?损失13.8%。通过对系统的?分析研究，明确了发动机内部损失分布。

关键词: 循环系统;损失分布;?分析;?损失;?效率;协同吸气式火箭发动机

References

[1] Taguchi H, Futamura H， Shimodaira K， et al. Design Study on Hypersonic Engine Components for TBCC Space Planes[C]. Norfolk: 12th AIAA International Space Planes and Hypersonic Systems and Technologies Conference， 2003.
[2] Snyder L， Escher D， DeFrancesco R， et al. Turbine Based Combination Cycle (TBCC) Propulsion Subsystem Integration[C]. Fort Lauderdale: 40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit， 2004.
[3] 程晓军，范育新，宫继双，等. TBCC内涵流动模拟试验模型设计及研究[J]. 推进技术， 2013， 34(2): 219-224.
[4] Kothari A， Livingston J， Tarpley C， et al. Rocket Based Combined Cycle Hypersonic Vehicle Design for Orbital Access[C]. San Francisco: 17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference， 2011.
[5] Hueter U. Rocket-based Combined Cycle Propulsion Technology for Access-to-Space Applications[C]. Norfolk: 9th AIAA International Space Planes and Hypersonic Systems and Technologies Conference， 1999.
[6] 汤祥，何国强，秦飞. RBCC发动机超燃/火箭模式流场数值模拟研究[J]. 推进技术， 2013， 34(12): 1643-1649. (TANG Xiang， HE Guo-qiang， QIN Fei. Numerical Simulations on RBCC Engine in Scramjet/Rocket Mode[J]. Journal of Propulsion Technology， 2013， 34(12): 1643-1649.)
[7] Hong-liang P， Peng Z. ATR Performance Improvement Based on Optimization Technique on Components Matching[R]. AIAA2009-0717.
[8] 刘洋，蒲晓航，李江，等. 固体燃料 ATR 涡轮/压气机匹配方法研究[J]. 推进技术， 2015， 36(3): 378-384.
[9] 韦宝禧，凌文辉，冮强，等. TRRE发动机关键技术分析及推进性能探索研究[J]. 推进技术， 2017， 38(2): 298-305.
[10] 邹正平，刘火星，唐海龙，等. 高超声速航空发动机强预冷技术研究[J]. 航空学报， 2015， 36(8): 2544-2562.
[11] Sebens J， Burton R， Jacobi A， et al. Combining Liquid Air Cycles with Turbine Engines for RLVs[C]. Norfolk: 12th AIAA International Space Planes and Hypersonic Systems and Technologies Conference， 2003.
[12] 黄奕勇，张育林. 空气液化发动机参数分析[J]. 推进技术， 2001， 22(1): 22-25. (HUANG Yi-yong， ZHANG Yu-lin. Parameter Analysis of the Liquid Air Cycle Engine[J]. Journal of Propulsion Technology， 2001， 22(1): 22-25.)
[13] Andrews D， Andrews J. Air Collection and Enrichment System (ACES) for Advanced 2nd Generation RLVs[C]. Salt Lake City: 37th Joint Propulsion Conference and Exhibit， 2001.
[14] Balepin V， Hendrick P. Application of the KLIN Cycle to a Vertical Takeoff Lifting Body Launcher[C]. Norfolk: 8th AIAA International Space Planes and Hypersonic Systems and Technologies Conference， 1998.
[15] 邢秀清，赵晓路. 深冷涡喷—火箭组合循环发动机初步分析[J]. 推进技术， 2000， 21(6): 10-13. (XING Xiu-qing， ZHAO Xiao-lu. Primary Analysis of Deep Cooled Turbojet-liquid Rocket Engine Combined Cycle[J]. Journal of Propulsion Technology， 2000， 21(6): 10-13.)
[16] Varvill R， Bond A. A Comparison of Propulsion Concepts for SSTO Reusable Launchers[J]. Journal of the British Interplanetary Society， 2003， 56(3-4): 108-117.
[17] Longstaff R， Bond A. The Skylon Project[C]. San Francisco: 17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference， 2011.
[18] Sato T， Tanatsugu N， Hatta H， et al. Development Study of the ATREX Engine for TSTO Spaceplane[C]. Kyoto: 10th AIAA International Space Planes and Hypersonic Systems and Technologies Conference， 2001.
[19] Taguchi H， Yanagi R. A Study on Pre-Cooled Turbojet-Scramjet Rocket Combined Engines[C]. Cleveland： 34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit， 1998.
[20] Wang Z， Wang Y， Zhang J， et al. Overview of the Key Technologies of Combined Cycle Engine Precooling Systems and the Advanced Applications of Micro-Channel Heat Transfer[J]. Aerospace Science and Technology， 2014， 39: 31-39.
[21] Varvill R， Bond A. The Skylon Spaceplane: Progress to Realisation[J]. Journal of the British Interplanetary Society， 2008， 61(10): 412-418.
[22] 牛文，李文杰. SKYLON 飞行器与 SABRE 发动机研究[J]. 飞航导弹， 2013， (3): 70-75.
[23] Davies P， Hempsell M， Varvill R. Progress on Skylon and SABRE[C]. Jerusalem: 66th International Astronautical Congress， 2015.
[24] Hempsell M， Bond A， Varvill R， et al. Progress on the SKYLON and SABRE Development Programme[C]. Cape Town: 62nd International Astronautical Congress， 2011.
[25] Webber H， Feast S， Bond A. Heat Exchanger Design in Combined Cycle Engines[J]. Journal of the British Interplanetary Society， 2009， 62: 122-130.
[26] Bartha J， Webber H. SABRE Technology Development [R]. IAC 2016-C4.9.2.

Application of Exergy Analysis in SynergisticAir-Breathing Rocket Engine

㶲分析在协同吸气式火箭发动机中的应用

PDF

Knowledge

Abstract

Cite this article

share this article

References

Related Articles 0

Recommended Articles

Metrics

Comments