主燃孔对模型燃烧室流场的影响

Effects of different primary holes on flow fields within the model combustor

关键词:  航空、航天推进系统  环形燃烧室  双级轴向旋流器  液雾燃烧流场

Key words:  Aerospace propulsion system  Annular combustor  Double axial swirler  Spray combusting flow field

摘要:

为了深入了解主燃孔参数变化对双级轴向旋流器模型环形燃烧室内气流组织与气动性能的影响,采用PIV测速仪对该燃烧室内冷态和液雾燃烧流场进行测量,试验研究在冷、热态情况下不同主燃孔参数对模型燃烧室内回流区的形成、轴向平均速度u,轴向脉动速度Urms,雷诺剪切应力u′v′分布的影响。研究结果表明:主燃孔参数变化对燃烧室内冷、热态流场有着重要的影响;燃烧室在燃烧情况下所得的中心回流区长度要比冷态短,但回流负速度、脉动速度和雷诺应力都明显大于冷态,所得的研究结果可为燃烧室优化设计提供有用的依据。

Abstract:

To investigate the effects of the different primary holes parameters on flow structure and aerodynamic characteristics in the model annular combustor with the double axial swirler,the isothermal and spray combusting flow fields within the model annular combustor with the double axial swirler are measured by a Particle Image Velocimetry (PIV) system.Effects of the different primary dilution hole parameters on the formation of recirculation zone,profiles of axial velocity u,axial fluctuating velocity Urms and Reynolds shear stress u’v’-in the combustors are investigated experimentally.Results of the PIV show that effects of different primary dilution holes parameters on isothermal and reacting flow fields are considerable.The lengths of central recirculation zone of the combusting cases are shorter than that of the non-reacting cases.However,recirculation velocity,Urms and the Reynolds shear stress of reacting flows are higher than that of non-reacting flows.Investigations may provide useful information for the optimum design of the gas turbine combustor.