Patent ID: 6508620
Filing Date: 2003-01-21
Classification: F01D,F05B,F05D

Abstract:
A stator blade assembly for a gas turbine engine, comprising:an outer shroud with an air supply port adapted to receive compressed air from a high pressure stage of a compressor of the engine; an inner shroud including a blade platform and a plenum enclosure defining a plenum bounded by an inner surface of the blade platform; a blade spanning between the outer and inner shrouds, the blade having a leading edge portion and trailing edge, the leading edge portion having a passage communicating between the plenum and the air supply port of the outer shroud, the blade including an internal blade cooling channel communicating between the passage and a plurality of apertures adjacent the trailing edge of the blade; an impingement plate disposed within the plenum, the impingement plate disposed a distance from the inner surface of blade platform thus defining an impingement cooling chamber within the plenum, the impingement plate including a plurality of impingement cooling apertures; and an air flow restriction plate covering an inner end of the passage, the restriction plate including a compressed air metering aperture.