F - Mech Eng,Light,Heat,Weapons – 02 – C
Patent
F - Mech Eng,Light,Heat,Weapons
02
C
F02C 7/12 (2006.01) F01D 5/18 (2006.01) F01D 11/08 (2006.01) F01D 25/12 (2006.01)
Patent
CA 2065679
To cool the shroud in the high pressure turbine section of a gas turbine engine, high pressure cooling air is directed in metered flow to baffle plenums and thence through baffle perforations to impingement cool the shroud rails and back surface. Impingement cooling air then flows through elongated, convection cooling passages 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.
Albers Robert Joseph
Brainch Gulcharan Singh
Hess John Raymond
Plemmons Larry Wayne
Proctor Robert
Company General Electric
Craig Wilson And Company
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