Numerical Simulation Study on a New Integrated Inclined Combustion Chamber Scheme
In order to improve the thrust-weight ratio of aero-engine,an integrated inclined combustion chamber scheme coupling compressor outlet guider and turbine inlet guider was designed.Based on the numerical simulation method,the numerical simulation analyses of the inclined combustion chamber and the conventional combustion chamber were carried out respectively.The calculation results show that compared with the conventional combustion chamber,the inclined combustion chamber designed in this paper can shorten the length of the combustion chamber flame tube by 29.26％under the condition that the total pressure loss and combustion efficiency are basically unchanged and the outlet temperature distri-bution is reasonable.The circumferential width of the recirculation zone in the inclined combustion cham-ber is reduced,and the return flow is reduced.Although the outlet temperature distribution of the in-clined combustion chamber is reasonable,the uniformity of the temperature distribution decreases.On the outlet section of the inclined combustion chamber,the airflow deflects in the circumferential direction to impact the turbine working blade.The airflow deflection angle is high at both ends and low in the mid-dle.Compared with the cold state results,the airflow deflection angle is smaller in the combustion state.In the cold state,the outlet airflow deflects 33° to 68°.In the combustion state,the outlet airflow deflects 21° to 38°.
thrust-weight ratio of aero-engineinclined combustion chambernumerical calculationtemperature distributionairflow deflection angle
NETL
NSTL
万方数据
