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首页> 外文会议>World Virtual Conference on Advanced Research in Mechanical and Materials Engineering >Film-Cooling Techniques at the End of Combustor and Inlet of Turbine in a Gas Turbine Engine: A Review
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Film-Cooling Techniques at the End of Combustor and Inlet of Turbine in a Gas Turbine Engine: A Review

机译：燃气涡轮发动机中燃烧器和涡轮机入口的薄膜冷却技术：综述

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This study was done to extend database knowledge about the film cooling holes function at the end of combustor and inlet of turbine. Using the well-known Brayton cycle, rising the turbine inlet temperature, is the key to get higher engine efficiency in gas turbine engines. But the high temperature of the combustor exit flow causes non-uniformities. These non-uniformities lead to a reduction in the expected life of critical components. Therefore a cooling technique should be designed to protect these parts. Film cooling is one of the most effective external cooling methods. In this system, a low temperature thin boundary layer such as buffer zone is formed and attached on the protected surface. In this study, a literature survey was done on the limited surveys.
机译：完成了该研究以延长关于燃烧器和涡轮机入口的薄膜冷却孔功能的数据库知识。使用众所周知的布雷顿循环，涡轮机入口温度上升，是燃气轮机发动机升高发动机效率的关键。但是燃烧器出口的高温导致非均匀性。这些不均匀性导致关键组分的预期寿命减少。因此，应设计冷却技术以保护这些部件。薄膜冷却是最有效的外部冷却方法之一。在该系统中，形成诸如缓冲区的低温薄边界层并附接在受保护的表面上。在这项研究中，在有限的调查中完成了文献调查。

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