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对低压涡轮后机匣进行实验研究。对不同来流马赫数及不同来流气流角下的涡轮后机匣流场参数进行测量,分析其在不同来流条件下的整流及损失情况。研究结果表明:支板叶型为前加载且按最大厚度积叠的涡轮后机匣在设计点及非设计点状态都将气流从偏离轴向偏转到基本接近轴向,且总压损失都较小。来流马赫数的改变对后机匣出口气流角影响不大,但来流马赫数的增加会导致其总压损失增加;而来流气流角改变对其出口气流角及总压损失的影响相对较小,但出口气流角及总压损失沿径向的分布会随来流气流角的改变发生变化。
Experimental research on the low-pressure turbine rear casing. The flow field parameters of the turbine after the turbulence at different flow Mach numbers and different incoming flow angles were measured and their rectification and loss under different incoming flow conditions were analyzed. The results show that the turbine rear casing with front-loading and maximum-thickness stacking deflects the air flow from the axial direction to the near axial direction at both design point and non-design point, and the total pressure loss is small. However, the increase of Mach number will lead to an increase of total pressure loss. However, the influence of the change of airflow angle on outlet airflow angle and total pressure loss is relatively Smaller, but the distribution of outlet airflow angle and total pressure loss along the radial direction will change with the change of airflow angle.