| Citation: | WAN Zhaobao, ZHOU Fei, DENG Shaochun, et al. Simulation and experimental study on radial temperature distribution control technology based on flame tube cooling holes[J]. Journal of Aerospace Power, 2026, 41（5）：20250466 doi: 10.13224/j.cnki.jasp.20250466
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In order to effectively reduce the tip temperature at the combustion chamber outlet and ensure smooth resolution of the turbine blade tip crown fracture failure, a simulation and experimental study on the radial temperature distribution control based on the cooling holes of the flame tube was conducted for the combustion chamber. Through analysis of the flow field and flow distribution, a control scheme was proposed to increase the geometric area of the 8th row of cooling holes in the outer ring by 65.3%. The numerical simulation results showed that this scheme increased the proportion of hole flow by 60.63%, while the proportion of flow in other intake structures decreased by 2.95% to 3.45% accordingly, and the temperature at the outlet blade tip was significantly reduced by 56 K. Component tests and complete machine tests further verified the effectiveness of the scheme. Component tests showed that the tip temperature of the control scheme was 51 K lower than that of the prototype, and the radial distribution of the outlet temperature presented the characteristics of lower temperatures at the tip and root, with the peak at about 2/3 of the blade height. Both outlet temperature distribution factor （OTDF） and radial temperature distribution factor （RTDF） met the design requirements, and the scheme did not have adverse effect on other key performances of the combustion chamber, which was beneficial to the reliability of the turbine blade. The temperature distribution trends of the simulation and component tests were consistent, providing an effective technical path for the precise control of the combustion chamber outlet temperature field.
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