Study on Scheme and Performance of Evaporative Turbine Inter-blade Combustor
In order to improve the overall performance and thermodynamic cycle mode of aero-engine,an evaporative turbine inter-blade combustion scheme was designed,and the combustion performance changes of the inter-blade combustor under different oil/gas ratios were studied experimentally.Parameters such as fuel distribution and component distribution in the combustor were obtained by numerical calculation.The results show that fuel atomization and stable combustion can be effectively promoted by using evaporative stabilizer in the inter-blade channel of the turbine guide.The maximum temperature rise of the inter-blade combustor is 694.4 K under test conditions,and the combustion efficiency is 90.3%.
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