Gas turbine engine diffuser and combustion chamber and gas turbine engine comprising same
View Patent ↗A gas turbine engine diffuser defined between an external casing and an internal casing of the engine and supplied with air via an upstream annular diffuser duct is disclosed. The diffuser includes a combustion chamber of the convergent type, forming an external annular duct with the external casing and an internal annular duct with the internal casing, and a cowling partially closing off the external annular duct. The cowling is positioned toward the closed end of the combustion chamber.
1. A gas turbine engine diffuser defined between an external casing and an internal casing of said engine and supplied with air via an upstream annular diffuser duct, the diffuser comprising:
a combustion chamber of the convergent type, defining an external annular duct with the external casing and an internal annular duct with the internal casing; and
a cowling disposed between the external casing and the combustion chamber so as to partially close off the external annular duct,
wherein the cowling includes a body with a symmetry of revolution about a cowling axis, the body includes a substantially flat cross section with a radially external end and a radially internal end, a radially external edge which extends from the radially external end and a radially internal edge which extends from the radially internal end, and
wherein the radially external edge of the cowling rests against an internal face of the external casing.
2. The diffuser as claimed in claim 1 , wherein the cowling is positioned toward a closed end of the combustion chamber.
3. The diffuser as claimed in claim 1 , wherein the body of the cowling extends between two planes which are substantially transverse with respect to the cowling axis.
4. The diffuser as claimed in claim 3 , wherein the two planes coincide and the body is an annular portion of a disk.
5. The diffuser as claimed in claim 3 , wherein the two planes are distinct from one another and the body is frustoconical, widening in the direction from downstream to upstream.
6. The diffuser as claimed in claim 1 , wherein the cowling includes at least one aperture disposed in the body of the cowling.
7. The diffuser as claimed in claim 6 , wherein the aperture includes turned down edges.
8. The diffuser as claimed in claim 1 , wherein the cowling further comprises fixing means for fixing the cowling to the combustion chamber.
9. The diffuser as claimed in claim 8 , wherein said fixing means are positioned on the radially internal edge of the cowling.
10. A combustion chamber positioned in a diffuser as claimed in claim 1 , the combustion chamber comprising:
an external wall;
an internal wall; and
a chamber end wall connecting the external wall and the internal wall,
wherein the cowling is fixed to the chamber end wall.
11. The combustion chamber as claimed in claim 10 , wherein the cowling is fixed to the combustion chamber toward the connection between the chamber end wall and the external wall.
12. The combustion chamber as claimed in claim 10 , wherein the radially internal edge of the cowling is fixed to an upstream face of the chamber end wall.
13. A gas turbine engine comprising a diffuser as claimed in claim 1 .
14. The gas turbine engine as claimed in claim 13 comprising a combustion chamber including:
an external wall;
an internal wall; and
a chamber end wall connecting the external wall and internal wall,
wherein the cowling is fixed to the chamber end wall.
15. The gas turbine engine as claimed in claim 14 , wherein the combustion chamber is disposed between the external casing and the internal casing.
16. The gas turbine engine as claimed in claim 15 , wherein the cowling is disposed to allow an axial clearance between the cowling and the external casing.
17. The diffuser as claimed in claim 9 , wherein the fixing means are positioned on a flange of an external wall of the combustion chamber and a flange of an end wall of the combustion chamber.