Turbine ring for a gas turbine engine

Claim 1

A turbine ring for a gas turbine comprising: a turbine casing; an annular metallic carrier mounted within the casing; a one-piece ring of ceramic abradable material mounted within the annular carrier, said carrier having means for reducing heat transfer from said ceramic ring to said carrier and means for applying a compression force to the ceramic ring under all operational phases of the gas turbine; means connected to a bleed of a compressor of said gas turbine for supplying cooling fluid to the annular carrier; and means for regulating the supply of cooling fluid to the annular carrier, whereby only the temperature of the annular carries is controlled, wherein said means for reducing heat transfer includes means for providing a small cross-section of contact between said ceramic ring and said carrier, said means for providing a small area of contact comprising a plurality of projections which extend radially between juxtaposed surfaces of the ceramic ring and the annular carrier, and wherein said means for suppying cooling fluid to the annular carrier lacks means to cool directly other parts of the turbine ring and comprises: (a) fluid distribution chamber means defined by the turbine casing and an annular outwardly opening casing of the annular carrier, (b) cavity means in the annular carrier adjacent a radially inner surface thereof, (c) aperture means in the annular carrier for providing communication between the distribution chamber means and said cavity means, and (d) exhaust duct means for exhausting the fluid from said cavity means, said exhaust duct means comprising an opening in said turbine casing, and annular collection chamber in said turbine casing and communicating said annular collection chamber with said cavity means.