| Citation: | ZHOU Fei, WAN Zhaobao, YANG Yang, et al. Design and experimental verification of an improved scheme for increasing total pressure recovery coefficient of the combustion chamber[J]. Journal of Aerospace Power, 2025, 40（8）：20230430 doi: 10.13224/j.cnki.jasp.20230430
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In view of the total pressure recovery coefficient of the combustion chamber at the level of 0.915, the total pressure recovery coefficient of the combustion chamber is required to increase by 0.01 in the design. In order to improve the total pressure recovery coefficient of the combustion chamber, the pre-diffuser and cowling were improved, and the flow mass distribution and flow field of the flame tube were matched in the design. The component experimental study on the performance of the full-ring combustor showed that the total pressure recovery coefficient of the improved scheme was 0.929, which increased by about 0.014 on the basis of the prototype combustor of 0.915 up to the design requirement, and the diffuser designed in the improved scheme at least contributed not less than 0.005 to increase the total pressure recovery coefficient. The quality of the outlet temperature field can meet the design requirement, the wall temperature of the flame tube can meet the requirement of material use, and lean-burn boundary of slow state engine and combustion efficiency were slightly lower than the prototype combustion chamber. The ground experiment of the overall engines showed that the improved scheme under the intermediate thrust index can increase the air flow rate of the compressor by 0.48 kg/s, reduce fuel consumption by 2%, and reduce the temperature before the turbine by 6 ℃ on the basis of the prototype combustion chamber, which can improve engine performance and reliability.
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