Influence Of Inlet Velocity Distomrtion And Turbine Guide Vane On Combustor Performance

Usually,the structure design and performance optimization of the combustor are carried out under the condition of uniform intake.But in the actual situation,the distortion of air flow at the compressor inlet and the uneven flow field generated by the compressor work and blade wake lead to the increase of the uneven flow field at the compressor outlet.Therefore,the air flow at the inlet of the combustor has a certain degree of distortion.So it is of great significance and reference value to investigate the action law of inlet velocity distortion on the multi-physical field and the variation of performance parameters in the combustor.The combustor and turbine are closely connected high-temperature components,their mutual influence cannot be ignored.Exploring the influence of turbine guide vane on combustor performance provides an important reference for aerodynamic performance matching and optimization design among components,and has guiding significance for further improving combustor performance.This paper takes annular combustor as the research object,and numerically studies the distribution of multiple physical fields and performance parameters of combustor under the intake velocity distortion,turbine guide vane layout and the joint effect of inlet velocity distortion and turbine guide vane.The main work contents are as follows:(1)The influence law of inlet velocity radial distortion and circumferential distortion on combustor performance was investigated.The results show that: Combustion efficiency is insensitive to both radial and circumferential velocity distortion.However,compared with the uniform intake,the total pressure loss increases.The maximum change rates of total pressure loss under radial and circumferential distortion are 16% and 19.7%,respectively.The influence of circumferential distortion on the total pressure loss is greater than that of radial distortion.(2)The variation of combustor performance parameters under the turbine guide vane layout,under the combined effect of inlet velocity radial distortion and turbine guide vane are investigated.The results show that: Flow distribution,combustion efficiency and total pressure loss are insensitive to turbine guide blades.But the temperature distribution coefficient at the combustor outlet changes significantly.When the turbine guide vane layout mode is that axis of the swirler is directly facing the leading edge of the blade,the OTDF deterioration by 3.5% compared with that without turbine guide vane.Under the combined action of radial intake velocity distortion and turbine guide vane,the combustion efficiency is basically not affected,but the total pressure loss increases with the increase of the maximum radial velocity.Compared with turbine guide vane,the influence of inlet velocity distortion on total pressure loss plays a dominant role.When the axis of the swirler is directly facing the leading edge of the blade,under the condition of inlet velocity distortion,the temperature distribution coefficient of combustor outlet deteriorates obviously,and its maximum increment is 4.2%.(3)The structure of the annular combustion chamber is improved.Secondly,the influence law of inlet velocity radial distortion,inlet velocity radial distortion and turbine guide vane on the performance parameters of the improved combustor was explored respectively.The results are compared with those of the prototype combustion chamber.The results show that: the outlet temperature distribution coefficient and total pressure loss of improved combustor are effectively improved.When there is a turbine guide vane,the improved combustor can effectively improve the outlet temperature distribution coefficient under the inlet velocity distortion condition,the maximum reduction is 8.3% compared to the prototype combustor.