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发明授权
CN107083997B 涡轮部件级、燃气涡轮发动机及相关方法 有权

涡轮部件级、燃气涡轮发动机及相关方法
摘要：
本发明提供一种燃气涡轮发动机，所述燃气涡轮发动机包括压缩机部分、燃烧部分和涡轮部分。所述涡轮部分包括涡轮部件级，所述涡轮部件级包括多个涡轮部件，所述多个涡轮部件共同包括沿所述燃气涡轮发动机的周向延伸的流动通道表面。所述流动通道表面部分限定所述燃气涡轮发动机的核心气流通道并且进一步限定沿所述周向的轮廓。所述轮廓的重复频率小于涡轮部件的个数，以适应流过所述涡轮部分的热气层。
摘要（英）：

A gas turbine engine includes a compressor section, combustion section 26, and turbine section. The turbine section includes a turbine component stage, the turbine component stage including a plurality of turbine components together including a flowpath surface along a circumferential direction (C) of the gas turbine engine. The flowpath surface defines in part a core air flowpath 37 of the gas turbine engine and further defines a contour along the circumferential direction (C). The contour repeats less frequently than once per turbine component to accommodate a hot gas streak through the turbine section.

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