| 摘要 |
PURPOSE: To obtain an improved shroud cooling assembly for keeping a shroud surrounding a rotor in high pressure turbine section of a gas turbine engine within a safe temperature range and using less amount of pressurized cooling air. CONSTITUTION: High pressure cooling air is directed in metered flow to baffle high pressure plenums 72 and thenceforth through perforations 78 of the baffle 68 to impingement cool shroud rails 46, 48, 50 and a back surface 44a. Impingement cooling air then flows through elongated, convection cooling passages 80 in a shroud 22 and exits to flow along a front surface 44b of the shroud with the main gas stream to provide film cooling. The perforations 78 of the baffle 68 and the convection cooling passages 80 are interactively located to achieve maximum cooling benefit and highly efficient cooling air utilization.
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