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GAS TURBINE ENGINE COMPONENT COMPRISING A TRAILING EDGE COOLING USING ANGLED IMPINGEMENT ON SURFACE ENHANCED WITH CAST CHEVRON ARRANGEMENTS
GAS TURBINE ENGINE COMPONENT COMPRISING A TRAILING EDGE COOLING USING ANGLED IMPINGEMENT ON SURFACE ENHANCED WITH CAST CHEVRON ARRANGEMENTS
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机译:燃气轮机发动机部件,其通过在加注式雪佛龙形布置增强的表面上进行有角度的冲击来形成尾缘冷却
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摘要
A gas turbine engine component, including: a pressure side (12) having an interior surface (34); a suction side (14) having an interior surface (36); a trailing edge portion (30); and a plurality of suction side and pressure side impingement orifices (24) disposed in the trailing edge portion (30). Each suction side impingement orifice is configured to direct an impingement jet (48) at an acute angle (52) onto a target area (60) that encompasses a tip (140) of a chevron (122) within a chevron arrangement (120) formed in the suction side interior surface. Each pressure side impingement orifice is configured to direct an impingement jet at an acute angle onto an elongated target area that encompasses a tip of a chevron within a chevron arrangement formed in the pressure side interior surface.
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