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发明授权
US09206699B2 Mid-section of a can-annular gas turbine engine with a cooling system for the transition 有权
具有用于过渡的冷却系统的罐环式燃气涡轮发动机的中段

Mid-section of a can-annular gas turbine engine with a cooling system for the transition
摘要：
A cooling system is provided for a transition (420) of a gas turbine engine (410). The cooling system includes a cowling (460) configured to receive an air flow (111) from an outlet of a compressor section of the gas turbine engine (410). The cowling (460) is positioned adjacent to a region of the transition (420) to cool the transition region upon circulation of the air flow within the cowling (460). The cooling system further includes a manifold (121) to directly couple the air flow (111) from the compressor section outlet to an inlet (462) of the cowling (460). The cowling (460) is configured to circulate the air flow (111) within an interior space (426) of the cowling (460) that extends radially outward from an inner diameter (423) of the cowling to an outer diameter (424) of the cowling at an outer surface.
摘要（中）：

为燃气涡轮发动机（410）的过渡（420）提供冷却系统。 冷却系统包括构造成从燃气涡轮发动机（410）的压缩机部分的出口接收空气流（111）的整流罩（460）。 整流罩（460）定位成邻近过渡区域（420），以在气流（460）内的空气流循环时冷却过渡区域。 冷却系统还包括将空气流（111）从压缩机部分出口直接联接到整流罩（460）的入口（462）的歧管（121）。 整流罩（460）构造成使得空气流（111）在整流罩（460）的内部空间（426）内循环，该整流罩（460）从整流罩的内径（423）径向向外延伸到外壳 在外表面的整流罩。

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