航空涡轮发动机射流预冷技术研究

doi:10.13675/j.cnki.tjjs.190445

推进技术 ›› 2020, Vol. 41 ›› Issue (4): 721-728.DOI: 10.13675/j.cnki.tjjs.190445

• 综述 • 下一篇

航空涡轮发动机射流预冷技术研究

林阿强¹，郑群¹，吴锋^2,3，杨昊³，张海¹

1.哈尔滨工程大学动力与能源工程学院，黑龙江哈尔滨 150001;2.中国航发四川燃气涡轮研究院高空模拟技术重点实验室，四川绵阳 621700;3.中国航发四川燃气涡轮研究院，四川成都 610500

发布日期:2021-08-15
作者简介:林阿强，博士生，研究领域为高速涡轮发动机射流预冷技术。E-mail：linaqiang493@sina.com
基金资助:
国家科技重大专项基金（2017-I-0009-0010；2017-II-0006-0019）；哈尔滨工程大学博士研究生科研创新基金（3072019GIP0304）；中央高校基本科研业务专项基金（3072019CFJ0309）。

Investigation on Mass Injection Pre-Cooling Technology of Aero-Turbine Engine

1.College of Power and Energy Engineering,Harbin Engineering University,Harbin 150001,China;2.Science and Technology on Altitude Simulation Laboratory,AECC Sichuan Gas Turbine Establishment, Mianyang 621700,China;3.AECC Sichuan Gas Turbine Establishment,Chengdu 610500,China

Published:2021-08-15

摘要/Abstract

摘要： 利用雾化蒸发的高效冷却技术，可以将高温进气降低到发动机材料允许的工作温度。针对射流预冷涡轮基冲压组合循环发动机，对比分析了国内外已有射流预冷技术的进展，详细介绍了射流预冷发动机的理论和试验验证情况，总结了射流预冷对航空涡轮发动机性能的影响，针对射流装置和喷水/液氧降温效果进行研究和验证。国内外已有研究表明，依靠射流预冷技术不会对发动机性能产生太大的不利影响，具有技术成型快、成本低，有效地扩展飞行包线，不受飞行高度和马赫数限制等优势。射流预冷技术可以解决涡轮发动机与冲压发动机在模态转换过程的“推力鸿沟”问题，具有潜在的技术优势，值得引起关注并开展进一步的深入研究。

关键词: 涡轮发动机;推力鸿沟;高温进气;射流预冷;射流装置

Abstract: High-temperature inlet air can be reduced to the allowable working temperature of engine material by using the atomization evaporation that is an efficient cooling technology. For mass injection pre-cooling turbine-based ramjet combined cycle engine (MIPCC-TBCC), this study compares and analyzes the development of mass injection pre-compressor cooling (MIPCC) technology existing at home and abroad, introduces the theoretical and experimental verification of MIPCC engine in detail, summarizes the influence of mass injection pre-cooling on engine performance, and studies and verifies the effect of mass injection device and water/ liquid oxygen injection cooling characteristics. All the researches showed that the MIPCC technology will not have too much adverse impact on engine performance. It has the advantages of fast formation, low cost, effective expansion of flight envelope, and is not limited by flight altitude and Mach number. Simultaneously, MIPCC can solve the ‘thrust gap’ problem between turbo-engine and ramjet in the process of mode conversion, which has potential technical advantages. Therefore, MIPCC engine deserves attention and further research.

Key words: Turbine engine;Thrust gap;High-temperature inlet air;Mass injection pre-cooling;Mass injection device

林阿强，郑群，吴锋，杨昊，张海. 航空涡轮发动机射流预冷技术研究[J]. 推进技术, 2020, 41(4): 721-728.

LIN A-qiang¹, ZHENG Qun¹, WU Feng^2,3, YANG Hao³, ZHANG Hai¹. Investigation on Mass Injection Pre-Cooling Technology of Aero-Turbine Engine[J]. Journal of Propulsion Technology, 2020, 41(4): 721-728.

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航空涡轮发动机射流预冷技术研究

Investigation on Mass Injection Pre-Cooling Technology of Aero-Turbine Engine

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