Shroud cooling assembly for gas turbine engine.

摘要

To cool the shroud [22] in the high pressure turbine section of a gas turbine engine, high pressure cooling air is directed in metered flow to baffle plenums [72] and thence through baffle perforations [78] to impingement cool the shroud rails and back surface. Impingement cooling air then flows through elongated, convection cooling passages [80] in the shroud and exits to flow along the shroud front surface with the main gas stream to provide film cooling. The baffle perforations and the convection cooling passages are interactively located to achieve maximum cooling benefit and highly efficient cooling air utilization. <IMAGE>