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为了理清一体化过渡段中大叶片的引入对涡轮部件气动性能和流动情况造成的影响,以带一体化动力涡轮过渡段的发动机的整个涡轮部件为研究对象,通过采用数值模拟的方法对其流动进行了研究。研究结果表明在地面起飞和最大巡航两种发动机工作状态下,一体化过渡段中大叶片的引入对低压涡轮和动力涡轮的性能均有显著影响,膨胀比和功率的影响量级达到1%;低涡动叶和动涡一导轴向力的影响量级分别为2%和5%;动涡一导和动涡一动进口气流角的影响量级分别为0.5°和2.5°。由于地面和空中两种状态下动力涡轮和排气支板的工作状态不同,故一体化过渡段大叶片的引入对其气动损失的影响机理不同,从而造成其损失和效率的变化趋势和量级不同。
In order to sort out the influence of the introduction of large blades in the integrated transitional section on the aerodynamic performance and flow of turbine components, the whole turbomachine of the engine with integrated power turbine transitional section was studied. The numerical simulation Flow was studied. The results show that under the condition of ground takeoff and maximum cruise, the introduction of large blades in the integrated transitional section has a significant impact on the performance of LP turbine and power turbine. The influence of expansion ratio and power reaches 1%. The influencing magnitude of low vortex blade and moving vortex guide axial force are respectively 2% and 5%. The effect of moving vortex guide angle and moving inlet vortex angle are 0.5 ° and 2.5 ° respectively. Due to the different working conditions of the power turbine and the exhaust support under the two conditions of ground and air, the influence mechanism of the introduction of large blades in the integrated transitional section on the aerodynamic loss is different, resulting in the change trend and magnitude of the loss and efficiency different.