水平起降Ma4高速飞机用涡轮冲压组合发动机研制关键技术难点解析及对策研究

推进技术 ›› 2018, Vol. 39 ›› Issue (10): 2303-2312.

水平起降Ma4高速飞机用涡轮冲压组合发动机研制关键技术难点解析及对策研究

王奉明^1,2,3,朱俊强¹,陈博⁴,徐纲¹

中国科学院工程热物理研究所，北京 100190; 中国科学院大学，北京 100190; 中国航空发动机研究院，北京 101304,中国科学院工程热物理研究所，北京 100190,空军装备部，北京 100081,中国科学院工程热物理研究所，北京 100190

发布日期:2021-08-15
作者简介:王奉明，男，博士生，高工，研究领域为航空发动机总体论证。

Study of Key Technologies and Development Proposals on Turbo-Ramjet Combined Cycle Engines for a Horizontal Takeoff and Landing Ma4 High Speed Aircraft

Institute of Engineering Thermo Physics，Chinese Academy of Sciences，Beijing 100190，China;University of the Chinese Academy of Sciences，Beijing 100190，China;Aero Engine Academy of China，Beijing 101304，China,Institute of Engineering Thermo Physics，Chinese Academy of Sciences，Beijing 100190，China,Equipment Department of China PLA Air Force，Beijing 100081，China and Institute of Engineering Thermo Physics，Chinese Academy of Sciences，Beijing 100190，China

Published:2021-08-15

摘要/Abstract

摘要： 水平起降Ma4高速飞机是目前研究的热点，涡轮冲压组合发动机是其可行动力形式之一，但历经50多年发展，Ma3.5以上涡轮冲压组合动力目前仍然停留在地面试验阶段，为了探明限制涡轮冲压组合发动机从技术研究转入工程研制的关键因素，本文设计了一个配装两台涡轮-亚燃冲压组合发动机、最高飞行速度为Ma4左右的水平起降高速飞机模型，设定了飞行任务剖面，计算出了整个飞行过程中飞机对发动机的推力需求，并对比现有航空发动机技术能力，分析出了阻碍涡轮冲压组合发动机向工程应用迈进的三大核心要素:飞机高空高速爬升阶段发动机存在一个巨大的“推力缺口”，现有发动机推重比不够高导致飞机有效载荷和航程受到极大限制，发动机长时间高Ma数飞行导致可靠性和寿命低。据此针对性提出了技术研究措施建议。

关键词: 涡轮-亚燃冲压组合发动机；水平起降Ma4高速飞机；推力缺口；任务剖面优化

Abstract: The horizontal takeoff and landing Ma4 high speed aircraft is currently a hot research field， and the turbo-ramjet combined cycle (TRCC) engine is one of the feasible power form. But after 50 years of development， the TRCC exceed Ma3.5 still does not carry out the flight test. To study the factors which block the TRCC engine from the technological areas to the engineering areas， a horizontal takeoff and landing Ma4 high speed aircraft equipped with two TRCC engines， whose maximum flight speed is Ma4 was modeled， and the flight mission profiles was set up. Then the aircraft’s thrust requirements in the whole flight process was calculated. Compared with the calculated results and the engine technology ability， three core elements which limited the TRCC engine from the technological areas to the engineering areas were found. The first is that there is a huge ‘thrust gap’ when the aircraft is climbing at high speed in the high altitude. The second is that the engine thrust weight ratio is too low to the payload and flight distance of the aircraft. The third is that we attribute the low reliability and short life to the long-term working with afterburner at high flight Mach number conditions. At last， some technological development proposals were advised.

Key words: Turbo-ramjet combined cycle engine；Horizontal takeoff and landing Ma4 high speed aircraft；Thrust gap；Mission profiles optimal design

王奉明,朱俊强,陈博,徐纲. 水平起降Ma4高速飞机用涡轮冲压组合发动机研制关键技术难点解析及对策研究[J]. 推进技术, 2018, 39(10): 2303-2312.

WANG Feng-ming^1,2,3,ZHU Jun-qiang¹,CHEN Bo⁴,XU Gang¹. Study of Key Technologies and Development Proposals on Turbo-Ramjet Combined Cycle Engines for a Horizontal Takeoff and Landing Ma4 High Speed Aircraft[J]. Journal of Propulsion Technology, 2018, 39(10): 2303-2312.

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