| Citation: | HUANG Congcong, XU Guoqiang, WEN Jie, et al. Analysis of blade cooling performance based on improved temperature assessment model[J]. Journal of Aerospace Power, 2023, 38（4）：816-829 doi: 10.13224/j.cnki.jasp.20210530
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In order to meet the development trend of aero-engine turbine cooling technology, based on the traditional blade temperature evaluation model, an improved model suitable for internal and external coupled turbine blades was proposed. The improved temperature evaluation model was embedded into the engine thermal performance calculation model. And the cooling performance of the high pressure turbine guide vane of F-16 fighter within typical flight missions and flight envelope was studied through the coupling analysis of aircraft and engine. Results showed that: when analyzed on the whole flight mission, under the conditions of practical lift limit, take-off and high climb rate, the blade worked in bad thermal environment and was prone to overheat; the blade surface temperature increased along the radial direction and reached the maximum value at the blade tip. When analyzed in the flight envelope, the blade temperature changed obviously with the height; the maximum temperature and thermal stress of the blade in the high altitude region with low Mach number were the largest, and the maximum temperature of the blade can reach 1342 K; compared with the highest cooling efficiency in flight envelope, the comprehensive cooling efficiency in the high altitude region with low Mach number was reduced obviously by 34.2%. When conducting sensitivity analysis of model parameters, compared with the benchmark scheme, when the input parameters changed by the same proportion, changing the inlet temperature of cool air had the most significant effect on blade temperature.
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