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为了实现燃机涡轮叶片气冷结构的设计和优化,利用绝热和气热耦合方法开展了气膜冷却效果的数值模拟研究;24核并行求解的方法提高了模型网格数目在107量级时的计算效率;对比分析了绝热和耦合计算方法中气膜冷却的效率和均匀性;利用耦合方法进一步研究了叶片尾缘的冷却方案以及冷气进气压力对冷却效率的影响。研究结果对于涡轮叶片气膜孔、尾缘冷却结构的设计以及冷却气体进气压力的选择具有一定的指导意义。
In order to realize the design and optimization of the air-cooled structure of the gas turbine turbine blades, numerical simulation of the cooling effect of the gas film was carried out by the method of adiabatic and gas-heat coupling. The method of 24-core parallel solving increased the number of model meshes The efficiency and uniformity of the film cooling in the adiabatic and coupled calculation are compared and analyzed. The cooling scheme of the trailing edge of the blade and the effect of the inlet air pressure on the cooling efficiency are further studied by using the coupling method. The research results have certain guiding significance for the design of the cooling film and the cooling structure of the turbine blade, as well as the choice of inlet pressure of cooling gas.