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小涡扇发动机总体要求以及高压涡轮工作特点,决定了小涡扇发动机高压涡轮气动设计上具有低展弦比、二次流损失及叶尖间隙泄漏损失大的特点。根据总体性能结构要求,设计了膨胀比为3.4的单级高压涡轮,三维黏性数值计算表明涡轮性能达到要求,具有较高效率,并重点描述了导向器内部流动现象.为了更好地评估实际工作环境下高压涡轮流动特点,对转静子冷却封严二股气流进行了数值模拟研究,详细分析其对转子二次流动及叶型攻角的影响。
The overall requirements of small turbofan engine and the characteristics of high-pressure turbine work determine the low aspect ratio, secondary flow loss and large leakage loss of tip clearance of small turbofan high-pressure turbine. According to the requirements of the overall performance structure, a single-stage high-pressure turbine with an expansion ratio of 3.4 was designed. The three-dimensional viscous numerical calculation shows that the performance of the turbine meets the requirements with high efficiency and the flow phenomenon inside the guideline is mainly described. In order to better evaluate the actual In the work environment, the characteristics of the high pressure turbine flow were numerically studied, and the influence of the secondary flow and the angle of attack on the rotor of the rotor was analyzed.