Characteristics of the rotating detonation combustor under continuously adjustable inlet area

SONG Feilong; WU Yun; CHEN Xin; LI Hao; QIU Han; KANG Jinhui

doi:10.7638/kqdlxxb-2025.0072

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Characteristics of the rotating detonation combustor under continuously adjustable inlet area

更新时间：2026-05-28

- Characteristics of the rotating detonation combustor under continuously adjustable inlet area
- Vol. 43, Issue 9, Pages: 105-114(2025)
- 作者机构：
  
  1. 空军工程大学航空工程学院，航空动力系统与等离子体技术全国重点实验室,西安,710032
  2. 西安交通大学机械工程学院，航空动力系统与等离子体技术全国重点实验室,西安,710049
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2025.0072
  CLC： O381;V231.22
- Published：2025
- 稿件说明：
移动端阅览
宋飞龙, 吴云, 陈鑫, 等. 进气面积连续可变旋转爆震燃烧室特性研究[J]. 空气动力学学报, 2025, 43(9): 105−114.

SONG Feilong, WU Yun, CHEN Xin, et al. Characteristics of the rotating detonation combustor under continuously adjustable inlet area[J]. 2025, 43(9): 105-114.
宋飞龙, 吴云, 陈鑫, 等. 进气面积连续可变旋转爆震燃烧室特性研究[J]. 空气动力学学报, 2025, 43(9): 105−114. DOI： 10.7638/kqdlxxb-2025.0072

SONG Feilong, WU Yun, CHEN Xin, et al. Characteristics of the rotating detonation combustor under continuously adjustable inlet area[J]. 2025, 43(9): 105-114. DOI： 10.7638/kqdlxxb-2025.0072.

摘要

针对涡轮基旋转爆震发动机宽工况适应性需求，本研究提出了进气面积连续可调的旋转爆震燃烧室构型。通过实验手段系统探究了进气面积连续调节过程中燃烧室模态分布、进气堵塞特性及性能参数变化规律。结果表明：燃烧室存在旋转爆震、轴向脉冲爆震与爆燃3种典型模态，起爆后连续调节进气面积仍能维持原有模态工作；进气喉道面积增大以及当量比的升高会使得进气堵塞比例提升与进气压比降低，在当量比为0.75时，进气堵塞比例最高为0.535，最低为0.286，同时动态调节过程中存在压力响应滞后现象，导致调节过程中的进气堵塞比例高于固定工况；由于滞后效应，燃烧室燃烧效率与总压恢复系数与固定工况时存在一定偏差，而调节结束后与固定工况参数吻合，进气喉道面积增大分别使燃烧效率与总压恢复系数提升，燃烧效率与总压恢复系数最高分别可达96.6%与92.3%。该研究为旋转爆震燃烧室进气几何调节规律提供了关键实验依据，推动了其在涡轮发动机中的工程化应用。

Abstract

This study presents a novel rotating detonation combustor configuration with continuously adjustable inlet areas to improve the operational flexibility of turbine-based rotating detonation engines. The modal evolution in the combustor

the inlet blockage characteristics

and the combustor’s performance during the continuous inlet area adjustment have been systematically examined by experiments. By varying the inlet area and equivalence ratio

three typical operational modes are identified: rotating detonation

longitudinal pulse detonation

and deflagration. Notably

the combustor maintains its initial operation mode when the inlet area is continuously adjusted follwing the initiation. The inlet air blockage ratio increases with a decreasing nozzle-to-inlet area ratio and an increasing equivalence ratio. The enhanced inlet blockage reduces the inlet air pressure ratio

thereby strengthening the coupling between the gas plenum and the combustor. Under stable operation states

the continuous adjustable condition and the fixed-area condition yield the same inlet blockage ratio. However

due to the pressure response delay in the combustor and the gas plenum to the inlet area adjustment

the continuously adjustable condition eventually leads to a higher inlet blockage ratio. When the nozzle-to-inlet area ratio decreases due to the pressure response delay

the combustion efficiency temporarily exceeds that of the fixed-area condition during the adjustment process

eventually recovering to the fixed-condition value after the adjustment process. Meanwhile

the total pressure recovery coefficient gradually increases

but remains comparable to that under fixed-working conditions throughout the adjustment process. These experimental findings establish a fundamental basis for developing adaptive control methodologies for rotating detonation combustors under variable operating conditions

significantly enhancing their engineering viability for turbine engine applications.

关键词

Keywords

references

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