Gas Turbine Components

A gas turbine component is provided. The gas turbine component includes an airfoil having a leading edge 222,230, a trailing edge 224,232, a suction side 226,234 extending from the leading edge to the trailing edge, and a pressure side 228,236 extending from the leading edge to the trailing edge opp...

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Bibliographische Detailangaben
Hauptverfasser: BRAD WILSON VAN TASSEL, CODY JERMAINE FORD
Format: Patent
Sprache:chi ; eng
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Beschreibung
Zusammenfassung:A gas turbine component is provided. The gas turbine component includes an airfoil having a leading edge 222,230, a trailing edge 224,232, a suction side 226,234 extending from the leading edge to the trailing edge, and a pressure side 228,236 extending from the leading edge to the trailing edge opposite the suction side. The gas turbine component also includes a thermal barrier coating 240 applied to the airfoil pressure side such that an uncoated margin 278 is defined on the pressure side at the trailing edge. 提供种燃气涡轮构件。燃气涡轮构件包括翼型件,其具有前边缘(222、230)、后边缘(224、232)、从前边缘延伸到后边缘的吸力侧(226、234)和从前边缘延伸到后边缘的、与吸力侧相反的压力侧(228、236)。燃气涡轮构件还包括隔热涂层(240),其应用于翼型件压力侧,使得未涂覆边界(278)限定在压力侧上,在后边缘处。