Seal cooling method and apparatus

Details Seal cooling method and apparatus Seal cooling method and apparatus

F - Mech Eng,Light,Heat,Weapons

02

C

170/67

F02C 7/12 (2006.01) F01D 11/04 (2006.01)

Patent

CA 1140474

13DV-7018 SEAL COOLING METHOD AND APPARATUS ABSTRACT OF THE DISCLOSURE An improved seal cooling method and apparatus is provided for use in a gas turbine engine. In a particular embodiment, this method and apparatus is used to minimize leakage in a labyrinth-type pressure seal of a gas turbine engine by using tighter seal clearance made possible through lower seal operating temperatures. The seal operating temperature is reduced by injecting relatively cool air from a compressor drump diffuser outlet into an interior region between labyrinth teeth of the seal at an angle in the direction of rotation of injected air. Additionally, an outlet for the cooling air is provided to a cavity forward of the seal to purge this cavity and prevent stagnant air from heating the seal structure and other turbine components.

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