Numerical study on matching mechanism and efficiency ofpulse detonation combustor and impulse turbine

邓芃; 郑龙席; 王凌羿

doi:10.13224/j.cnki.jasp.2018.08.009

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Numerical study on matching mechanism and efficiency ofpulse detonation combustor and impulse turbine

更新时间：2026-07-07

- Numerical study on matching mechanism and efficiency ofpulse detonation combustor and impulse turbine
- Vol. 33, Issue 8, Pages: 1864-1871(2018)
- 作者机构：
  
  西北工业大学动力与能源学院,西安,710072
- 作者简介：
- 基金信息：
- DOI：10.13224/j.cnki.jasp.2018.08.009
  CLC：
- Published：2018
- 稿件说明：
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邓芃, 郑龙席, 王凌羿. 脉冲爆震燃烧室与冲击式涡轮匹配机理及效率的数值研究[J]. 航空动力学报, 2018, 33(8): 1864-1871.

doi: 10.13224/j.cnki.jasp.2018.08.009
邓芃, 郑龙席, 王凌羿. 脉冲爆震燃烧室与冲击式涡轮匹配机理及效率的数值研究[J]. 航空动力学报, 2018, 33(8): 1864-1871. DOI： 10.13224/j.cnki.jasp.2018.08.009.

doi: 10.13224/j.cnki.jasp.2018.08.009 DOI：

摘要

针对脉冲爆震燃烧室（PDC）与涡轮共同工作时

涡轮入口为强非稳态气流的特点

结合涡轮损失机理

确定适合脉冲爆震来流的涡轮类型并开展气动设计工作

运用数值方法计算所设计涡轮的效率和探究PDC与涡轮相互作用的机理。研究结果表明：部分进气、小反力度的冲击式涡轮更适合脉冲爆震来流；在喷嘴收缩段、动叶叶片前缘以及动叶压力面生成向上游传播的反射激波

造成能量损失；在设计点

涡轮效率约为75%。上述研究结果可以为脉冲爆震涡轮发动机的涡轮设计提供一定的参考。

Abstract

As the turbine inlet was dominated by strong unsteady airflow when working with the pulse detonation combustor (PDC)

the type of turbine was determined based on the loss mechanism and the aerodynamic design work of turbine components was carried out.The numerical method was used to calculate the efficiency of the designed turbine and explore the mechanism of the interaction between the PDC and the turbine.The results showed that partial intake

impulse turbine with less reaction degree was more suitable for PDC; a strong reflection shock wave was formed on the contraction section of nozzle

the leading edge and the pressure surface of the rotor blade

which cause energy loss; the efficiency of turbine was about 75% at the design point. The results can provide some reference for turbine design of pulse detonation turbine engine.

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