Abstract: The effects of the different inlet conditions on flow structure were tested to investigate the flow field in combustor. Measurements of the flow field in a triple axial swirl combustor were performed by means of two-dimensional Particle Image Velocimetry (PIV)， including four cases: Case 1 at normal temperature and low pressure (0.49MPa)， Case 2 at normal temperature and middling pressure (0.98MPa)， Case 3 at normal temperature and high pressure (1.64MPa)， Case 4 at real operating condition (high temperature 813K and high pressure 2.78MPa). The PIV results show that the different inlet conditions (velocity， temperature， pressure) lead to similar flow field structures， but some differences present in the sizes of central recirculation zone， the sizes of corner recirculation zone and the details of both primary hole jets and dilution hole jets. About the present model at higher inlet pressure， the central recirculation zone expands downstream， the corner recirculation zone contracts， the jet mass flux ratios of the primary holes and dilution holes increase while the jet velocities increase.

Key words: Aeroengine；Combustor；Triple-stage axial swirling flow；Particle image velocimetry；Real operating condition

摘要： 为深入了解燃烧室内流场，研究不同来流状态对燃烧室流场结构的影响，基于粒子成像速度仪(PIV)技术，对采用三级轴向旋流器的航空发动机燃烧室进行流场测量，分别在Case 1常温低压(0.49MPa)、Case 2常温中压(0.98MPa)、Case 3常温高压(1.64MPa)、Case 4全状态(高温813K高压2.78MPa)来流条件下进行。研究结果表明，同一燃烧室模型在不同速度、温度和压力来流下有基本相同的流场结构，但在中心回流区尺寸、角落回流区尺寸、主燃孔和掺混孔射流等细节方面仍有明显差异，来流压力较高的流场中心回流区向下游扩展更深入，角落回流区被压缩，主燃孔和掺混孔射流速度增加且进气比例增大。

关键词: 航空发动机；燃烧室；三级轴向旋流；粒子成像速度仪；全状态