Thermodynamic process and operating characteristics of air turbo rocket engine

NAN Xiangyi; LIU Yi; MA Yuan; YANG Shunhua; MA Jicheng

doi:10.7638/kqdlxxb-2022.0033

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Thermodynamic process and operating characteristics of air turbo rocket engine

更新时间：2026-05-28

- Thermodynamic process and operating characteristics of air turbo rocket engine
- Vol. 40, Issue 1, Pages: 181-189(2022)
- 作者机构：
  
  1. 西安航天动力研究所,西安,710100
  2. 中国空气动力研究与发展中心,绵阳,621000
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2022.0033
  CLC： V236
- Published：2022
- 稿件说明：
移动端阅览
南向谊, 刘轶, 马元, 等. 空气涡轮火箭发动机热力过程及工作特性[J]. 空气动力学学报, 2022, 40(1): 181−189.

NAN Xiangyi, LIU Yi, MA Yuan, et al. Thermodynamic process and operating characteristics of air turbo rocket engine[J]. 2022, 40(1): 181-189.
南向谊, 刘轶, 马元, 等. 空气涡轮火箭发动机热力过程及工作特性[J]. 空气动力学学报, 2022, 40(1): 181−189. DOI： 10.7638/kqdlxxb-2022.0033

NAN Xiangyi, LIU Yi, MA Yuan, et al. Thermodynamic process and operating characteristics of air turbo rocket engine[J]. 2022, 40(1): 181-189. DOI： 10.7638/kqdlxxb-2022.0033.

摘要

对空气涡轮火箭（Air Turbo Rocket，ATR）发动机国内外研究概况进行了介绍。采用热力循环分析方法对ATR发动机热力过程和发生器温比、压气机压比、涡轮落压比等关键特征参数影响规律进行了分析，在此基础上开展了单组元和双组元推进剂ATR发动机系统和性能仿真研究，将部分结果与试验结果进行了对比。ATR发动机的起动特性和高空特性的理论和试验对比研究表明，ATR发动机在马赫数0～4的爬升包线中能够提供较大的剩余推力，起动时间在5 s以内。这一显著特点，使其在与冲压发动机并联组合后，可以实现高、低速流道的快速切换，从而实现推力连续过度，为宽域组合动力提供了一个新的技术路线。最后总结分析了ATR发动机的技术优势和发展前景，以及ATR发动机在应用方面的问题和思路。通过技术继承、拓展，ATR组合动力是构建新型临近空间超声速和高超声速动力创新技术途径。

Abstract

Air turbo rocket (ATR) engines

which are usually used as the power of independent air-launch platforms and near-space aircraft

have been developed for decades. This paper presents an overview of the research progress of ATR engines first. Then the effects of key parameters on the thermodynamic process of ATR engines are investigated. These parameters are the temperature ratio in the gas generator

the pressure ratio in the compressor

and the pressure ratio in the turbine. On this basis

the overall performance of ATR engines with monopropellant and bipropellant is studied through numerical simulations and experiments. By analyzing the start-up and operation characteristics under a high-attitude working condition

it is found that large thrust and short start-up time (less than five seconds) can be obtained in flight envelopes with the Mach number less than four. To increase the velocity range and reduce the fuel consumption of ATR engines

an innovative scheme integrating the ATR engine and the scramjet engine is proposed. This combined-cycle engine takes full advantage of ATR’s good acceleration ability and scramjet’s hypersonic cruise capability. Results show that continuous thrust can be obtained during the mode transition between the ATR and ramjet

providing a prospective power solution for supersonic and hypersonic near-space aircraft.

关键词

Keywords

references

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