Patent ID: 6676370
Filing Date: 2004-01-13
Classification: F01D,F02C,F05D,F23M,F23R

Abstract:
A guide ring for use in a gas turbine, comprising:a base plate having a radially outward side and a radially inward side, said radially inward side being exposed to a working medium of said gas turbine; a first and second metal guide plate formed on said radially outward side of said base plate; an inlet coolant connection formed on said radially outward side of said base plate, said inlet coolant connection penetrating through said first and second metal guide plates; a flow-inlet space formed by said first and second metal guide plates and in communication with said inlet coolant connection; and a flow passage formed by said first metal guide plate and said base plate, said flow passage being in communication with said flow inlet space via an inflow region, whereby in cross section the flow passage extends over substantially the entire width of the guide ring with respect to the axial direction of the guide ring.