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首页> 外文会议>ASME(American Society of Mechanical Engineers) Turbo Expo vol.4 pt.B; 20070514-17; Montreal(CA) >SIMULATION OF A MULTI-STAGE COOLING SCHEME FOR GAS TURBINE ENGINES: PART I
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SIMULATION OF A MULTI-STAGE COOLING SCHEME FOR GAS TURBINE ENGINES: PART I

机译：燃气轮机多级冷却方案的仿真：第一部分

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摘要

This paper presents heat transfer characteristics for a Multi-Stage Cooling Scheme (MSCS) design applicable to high temperature gas turbine engines in aerospace and electric power generation. The film cooling and impingement techniques are considered concurrently throughout this study. The proposed design involves passing cooling air from the inside of the turbine blade to the outside through three designed stages. The coolant air is passed through a circular hole into an internal gap creating an impingement of air inside the blade. It then exits through a sequence of two differently shaped holes onto the blade's external surface. The film cooling effectiveness is enhanced by increasing the internal gap height and offset distance. This effect is significantly diminished however by changing the inclination angle from 90° to 30° at large gap height. The coolant momentum became more uniform by creating the internal gap consequently the coolant air is spread closer to the external blade surface. This reduces jet liftoff as the air exits its hole and also provides internal cooling for the blade. The hole exit positioned on the outer surface of the blade is designed to give a positive and a wide downstream lateral spreading. The MSCS demonstrates greater film cooling effectiveness performance than traditional schemes.
机译：本文介绍了适用于航空航天和电力生产中的高温燃气涡轮发动机的多级冷却方案（MSCS）设计的传热特性。在整个研究过程中同时考虑了薄膜冷却和撞击技术。提出的设计涉及通过三个设计阶段将冷却空气从涡轮叶片的内部传递到外部。冷却剂空气通过圆孔进入内部间隙，从而在叶片内部产生空气撞击。然后，它通过一系列两个形状不同的孔退出到刀片的外表面。通过增加内部间隙高度和偏移距离，可以提高薄膜冷却效果。但是，通过在较大的间隙高度处将倾斜角度从90°更改为30°，该效果会大大降低。通过产生内部间隙，冷却剂动量变得更均匀，因此冷却剂空气更靠近叶片外表面扩散。当空气离开孔时，这会减少喷射升力，并为叶片提供内部冷却。定位在叶片外表面上的孔出口设计成可产生正向且较宽的下游横向扩展。 MSCS展示了比传统方案更高的薄膜冷却效果。

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