Patent ID: 7775051

Claim:
An arrangement for a jet engine combustion chamber, said chamber comprising a chamber endwall perforated by at least one circular passage hole, the arrangement comprising: an injection system associated with said circular passage hole and mounted so that the injection system slides diametrically with respect to the circular passage hole in the chamber endwall; a deflector mounted fixedly on the chamber endwall inside the combustion chamber, the deflector including a fitting ring which includes first tenons which are spaced circumferentially and project radially; a sleeve which is coaxial to the fitting ring of the deflector and includes second tenons which are spaced circumferentially and project radially; and a floating ring which is slidably mounted in the sleeve, wherein the first and the second tenons are sufficiently spaced to allow passage of the first tenons between the second tenons and then, through a rotation, engagement of the first tenons behind the second tenons prohibits the deflector and the sleeve from separating in an axial direction, wherein the injection system is slidably mounted in the sleeve, wherein an antirotation means is provided to prevent a rotation of the injection system with respect to the sleeve, and wherein the floating ring is provided with a plurality of ventilation holes.