Patent ID: 10746048

Abstract:
A gas turbine engine includes an annular casing and a plurality of shroud segments forming an annular shroud. The annular shroud forms with the annular casing an annular cavity therebetween. The annular cavity includes an inlet and an outlet. An annular ring assembly is disposed in the annular cavity between the casing and the shroud and cooperating therewith to provide a first annular chamber and a second annular chamber. The annular ring assembly and a first portion of the shroud form the first annular chamber. The annular ring assembly and a second portion of the shroud form the second annular chamber. The annular ring assembly forms an intermediate annular chamber disposed between the first annular chamber and the second annular chamber. A flow path for coolant air is sequentially defined through the inlet, the first annular chamber, the intermediate annular chamber, the second annular chamber and the outlet.