Patent ID: 8756935

Claim:
A combustion chamber for a gas turbine engine comprising: a deflector comprising ceramic matrix composite (CMC) material which is mounted on a chamber end wall including an opening for a carbureted air supply device; and a metal sleeve secured to an interior edge of the opening of the chamber end wall, wherein the deflector comprises an opening, corresponding to the chamber end wall opening, with an annular cylindrical part, wherein an outer circumferential surface of the cylindrical part comprises an annular groove collaborating with an annular tooth provided on an inner circumferential surface of the metal sleeve, wherein the deflector is free of a weld joint and free of a brazed joint, and wherein a cylindrical centering cup is fixed at a first end to the sleeve and housed with clearance inside the cylindrical part when the combustion chamber is cold, the clearance becoming smaller if not being eliminated at the combustion chamber operating temperatures.