预冷涡轮发动机研究趋势及宽域预冷涡轮组合动力创新方案

姚照辉; 郭远钊; 何纬峰; 余天昊; 陈嘉; 鲍文

doi:10.13224/j.cnki.jasp.20220446

预冷涡轮发动机研究趋势及宽域预冷涡轮组合动力创新方案

doi: 10.13224/j.cnki.jasp.20220446

1.
西安电子科技大学空间科学与技术学院，西安 710126
2.
南京航空航天大学能源与动力学院，南京 210016
3.
哈尔滨工业大学能源科学与工程学院，哈尔滨 150001

基金项目: 工业和信息化部“两机”基础科学中心揭榜挂帅重大项目（P2021-A-Ⅰ-001-002）

详细信息

作者简介:
姚照辉（1982-），男，研究员，博士，从事空天推进系统及其控制技术研究。E-mail：yaoz@xidian.edu.cn

中图分类号: V231
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出版历程
- 收稿日期: 2022-06-21
- 网络出版日期: 2024-09-28

Research trends of pre-cooled turbo engine and a wide-range scheme of pre-cooled turbo combined cycle power

1.
School of Aerospace Science and Technology，Xidian University，Xi’an 710126，China
2.
College of Energy and Power Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China
3.
School of Energy Science and Engineering，Harbin Institute of Technology，Harbin 150001，China

摘要

摘要:
系统梳理了英国SABRE、日本ATREX、PCTJ及西安航天动力研究所的PATR等国际国内预冷组合循环动力最新研究进展，总结归纳出高效紧凑换热、液氢燃料氢脆、结霜抑制、复杂控制匹配等是现阶段预冷涡轮动力存在的关键技术难题，并据此预测新型高热沉燃料、复杂热力循环是预冷涡轮动力的重要发展趋势。在此现状下，充分考虑我国实际国情，创新提出了一种具有我国自主知识产权和鲜明技术特色的基于吸热型碳氢燃料预冷来流空气的新型预冷涡轮火箭组合发动机新方案。分析了该创新方案的关键技术，开展了总体概念设计、性能评估及工作机理分析，得出其工作马赫数范围为0～5、工作高度为0～30 km、燃料工作在常温的工作特点，可以支撑临近空间飞行器宽范围、高性能工作，从而从理论上分析证明了该创新方案的可行性和先进性，由此得出本文提出的串联式预冷涡轮火箭组合循环发动机气动热力新构型是实现临近空间飞行器的重要动力途径。
- 组合循环动力 /
- 涡轮火箭发动机 /
- 预冷发动机 /
- 吸热型碳氢燃料 /
- 发动机总体设计
Abstract:
Latest international and domestic research progresses of pre-cooled combined cycle engine were clarified, including Synergetic Air Breathing Rocket Engine (SABRE) developed by the UK, the Air Turbo Ramjet of Expander Cycle (ATREX) and Precooled Turbojet Engine (PCTJ) developed by Japan, as well as the Pre-cooling Air Turbo Rocket (PATR) developed by Xi’an Aerospace Propulsion Institute of China. The existing problems were summarized, including the challenges of efficient and compact heat transfer, hydrogen embrittlement problem of liquid hydrogen fuel, frost suppression, and complex control matching. It was predicted that those new propulsions with high heat sink fuels and complex thermodynamic cycles showed important trends for pre-cooled turbine engine. In this situation, fully considering actual national conditions of China, a new pre-cooled turbo rocket combined engine with independent intellectual property rights and distinctive technical characteristics in China was innovatively proposed for the first time, using endothermic hydrocarbon fuel to pre-cool incoming air. The key technologies of this new engine were analyzed, and a general conceptual engine design, performance evaluation, and working mechanism analysis were carried out. Many new characteristics of this engine were concluded: the flight Mach number ranging from 0 to 5, the flight altitude ranging from 0 to 30 km, and the fuel working at room temperature, which can support a wide-range and high-performance flight for near-space vehicles. Thus the feasibility and progressiveness of the new engine were theoretically verified. A conclusion was drawn that the new serial-type pre-cooled turbo-rocket engine with new aerodynamics and thermodynamics is an important way to achieve near-space flight vehicles.
- combined cycle power /
- turbo rocket engine /
- pre-cooled engine /
- endothermic hydrocarbon fuel /
- overall design of engines

HTML

图 1 SABRE热力循环系统方案

Figure 1. Thermal cycle system scheme of SABRE

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图 2 PATR发动机热力循环系统方案

Figure 2. Thermal cycle system scheme of PATR engine

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图 3 NUAA-PTRE 气动热力循环方案

Figure 3. Aerodynamic thermodynamic cycle of NUAA-PTRE engine

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图 4 NUAA-PTRE系统组成

Figure 4. Configuration and composition of NUAA-PTRE engine

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图 5 空气回路理想热力循环

Figure 5. Ideal thermal cycle of air circuit

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图 6 沿典型飞行轨迹的推力比冲性能变化

Figure 6. Variations of thrust and specific impulse on typical flight trajectory

下载: 全尺寸图片幻灯片

表 1 不同类型预冷组合发动机对比

Table 1. Comparison of different types of pre-cooled combined engines

比较维度	ATREX	SABRE	ATRDC	MIPCC
工质类型	氢燃料	氢燃料	氢燃料	氢燃料
循环效率	高	高	高	一般
系统复杂度	较高	高	高	高
技术成熟度	高	高	较高	一般

下载: 导出CSV

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