Device for injecting a mixture of air and fuel, and a combustion chamber and turbomachine provided with such a device
View Patent ↗A device for injecting a mixture of air and fuel into a combustion chamber of a turbomachine is disclosed. The injection device has symmetry of revolution about an axis and includes radial swirl inducers of outside diameter D 2 , a bowl spaced axially from the radial swirl inducers, and a support ring for supporting the injection device, which is arranged around the bowl. The bowl has a cylindrical wall extended by a flared wall, the flared wall being provided with air intake holes. The support ring includes a first cylindrical portion of outside diameter D 3 , connected to a second cylindrical portion of outside diameter D 4 spaced axially from the first cylindrical portion, the first cylindrical portion being connected to the cylindrical wall of the bowl by a plurality of support tabs.
1. A device for injecting a mixture of air and fuel into a combustion chamber of a turbomachine, the injection device having symmetry of revolution about an axis, comprising:
radial swirl inducers of outside diameter D 2 ;
a bowl spaced axially downstream in a gas flow direction from the radial swirl inducers, the bowl including a cylindrical wall extended by a flared wall, the flared wall being provided with air intake holes; and
a support ring configured to support the injection device, which support ring is arranged around the bowl,
wherein the support ring comprises a first cylindrical portion of outside diameter D 3 , and a second cylindrical portion of outside diameter D 4 spaced axially downstream in the gas flow direction from the first cylindrical portion, the first cylindrical portion being connected to the cylindrical wall of the bowl by a plurality of support tabs, and
wherein an outer circumference of the first cylindrical portion of the support ring directly contacts a chamber endwall.
2. The injection device as claimed in claim 1 , wherein the diameter D 3 is less than the diameter D 2 .
3. The injection device as claimed in claim 1 , wherein the support tabs are distributed circumferentially and uniformly around the bowl.
4. The injection device as claimed in claim 1 , wherein the consecutive air intake holes are connected by a residual wall and wherein the support tabs are arranged opposite the residual wall.
5. The injection device as claimed in claim 1 , wherein, in the circumferential direction, the support tabs include a thickness which is less than the thickness of the residual wall disposed between two consecutive air intake holes.
6. The injection device as claimed in claim 1 , wherein the diameter D 3 is less than the diameter D 4 .
7. The injection device as claimed in claim 1 , wherein the second cylindrical portion of the support ring is provided with an annular radial protuberance directed toward the axis of the cylindrical portion.
8. The injection device as claimed in claim 7 , wherein the radial protuberance is provided with cooling holes.
9. A combustion chamber comprising an internal wall, an external wall and a chamber endwall, which combustion chamber is provided with at least one injection device as claimed in claim 1 .
10. A turbomachine provided with a combustion chamber as claimed in claim 9 .
11. The injection device as claimed in claim 1 , wherein an outer circumference of the second cylindrical portion of the support ring directly contacts a deflector.
12. The injection device as claimed in claim 1 , wherein a deflector and support ring are integrally formed and the deflector extends radially outward from the second cylindrical portion of the support ring.
13. The injection device as claimed in claim 1 , wherein the support ring is a single piece unit.
14. The injection device as claimed in claim 7 , wherein the radial protuberance directly contacts an outer surface of the flared wall of the bowl.