Arrangement for a jet engine combustion chamber

1. 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.

2. The arrangement as claimed in claim 1 , wherein the sleeve includes a cup with an end seat on which the floating ring slides and a rim, and the floating ring is retained by a closure ring welded to the rim.

3. The arrangement as claimed in claim 1 , wherein the fitting ring passes through the passage hole in the chamber endwall.

4. The arrangement as claimed in claim 1 , wherein the first tenons protrude in a radially outward direction and wherein the second tenons protrude in a radially inward direction.

5. The arrangement as claimed in claim 2 , wherein the antirotation means includes a tongue for the orientation of the floating ring, which tongue cooperates with a slot disposed in the rim of the sleeve.

6. The arrangement as claimed in claim 1 , wherein said arrangement comprises an orientation finger which passes through the chamber endwall and which engages at a first end into a slot for the orientation of the deflector and at a second end into a slot for the orientation of the sleeve, the orientation finger imposing a defined angular orientation of the deflector and of the sleeve with respect to the chamber endwall and defines an angular orientation of the sleeve and of the deflector with respect to one another.

7. The arrangement as claimed in claim 1 , wherein the ventilation holes in the floating ring are arranged opposite the deflector in a region where there is a clearance between the injection system and the deflector that is below a limit value and are disengaged from the deflector in a region where the clearance between the injection system and the deflector is above the limit value.

8. A jet engine which comprises an arrangement as claimed in claim 1 .

9. A sleeve forming part of an arrangement as claimed in claim 1 .

10. An injection system forming part of an arrangement as claimed in claim 1 .

11. A deflector forming part of an arrangement as claimed in claim 1 .

12. The arrangement according to claim 7 , wherein air flows through the ventilation holes to cool the deflector when the clearance between the injection system and the deflector is above the limit value.