Patent ID: 9689276
Date: 2017-06-27
CPC Classifications: F01D,F05D

Claim:
1. A gas turbine engine comprising: an annular shroud encircling one of a stator and a rotor, the shroud having a first portion and a second portion axially disposed downstream of the first portion of the shroud relative to a rotation axis of the engine and a direction of airflow through the rotor in use; an annular casing outwardly spaced-apart from the shroud and mounted thereto to define an annular cavity between the casing and the shroud, the cavity including an inlet communicating with a source of coolant air and an outlet communicating with gas path; an annular ring assembly disposed in the cavity between the casing and the shroud and configured to cooperate with the casing and the shroud, the annular ring assembly and the first portion of the shroud forming a first annular chamber by abutment surfaces of annular shape circumferentially formed between the annular shroud and the annular ring such that the first annular chamber is enclosed between the first portion of the shroud, the annular ring assembly and the abutment surfaces, the annular ring assembly and the second portion of the shroud forming a second annular chamber, the ring forming an intermediate annular chamber disposed between the first annular chamber and the second annular chamber, the annular ring assembly having: