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为了研究某型涡轮过渡段气动性能,采用数值模拟方法研究了子午型线对某带支板的涡轮过渡段气动性能和流场特性的影响,探讨了四种机匣型线时过渡段及上游高压涡轮的气动参数分布及流动情况,并给出了不同方案时总损失对比分析。结果表明,过渡段机匣子午型线对上游高压涡轮的影响不大,仅方案Case_1的气流角发生了明显变化。由于不同的过渡段子午型线使得流道中的静压分布发生变化,气流逆压梯度的变化引起机匣附近的流动分离改变,进而使得过渡段出口的损失变化,极大地影响过渡段的整体气动性能。
In order to study the aerodynamic performance of a turbine turbulent transition section, the numerical simulation is used to study the effect of meridian profile on the aerodynamic performance and flow field characteristics of a turbine turbulent transition section. The aerodynamic parameter distribution and flow of high-pressure turbine are given, and the comparison and analysis of total losses when different schemes are given. The results show that the transition section casing meridian line has little effect on the upstream high-pressure turbine, and only the airflow angle of Case_1 has changed obviously. Because of the different meridional transition lines, the distribution of hydrostatic pressure in the flow channel changes. The change of the pressure gradient causes the flow separation near the receiver to change, which in turn causes the loss of the transition section to change greatly and greatly affects the overall aerodynamic performance.