System for dissipating fuel egress in fuel supply conduit assemblies

1. A system for dissipating fuel egress, the system comprising:

a fuel supply assembly having a fuel supply line providing fuel and a purge air conduit arranged co-axially around the fuel supply line, thereby defining an annular channel around the fuel supply line;

a fuel injector for a combustor, the fuel injector including a perimeter body defining a portion of the fuel injector, a fuel injection port associated with the perimeter body, and an internal mixing chamber downstream of the fuel injection port in a direction of fuel flow;

wherein the fuel supply line provides fuel to the fuel injection port; and

wherein the perimeter body of the fuel injector defines a fuel egress passage therethrough, the fuel egress passage having an inlet in fluid communication with the annular channel and an outlet in fluid communication with the mixing chamber, the fuel egress passage further comprising a fuel purge cavity between the inlet and the outlet, the fuel purge cavity being defined as an annular cavity within a circumference of the perimeter body.

2. The system of claim 1 , wherein the outlet of the fuel egress passage is downstream of the fuel injection port.

3. The system of claim 1 , wherein the fuel egress passage includes a first portion upstream of the fuel purge cavity and a second portion downstream of the fuel purge cavity, the first portion including the inlet and the second portion including the outlet.

4. The system of claim 1 , wherein a plurality of outlets extends from the fuel purge cavity, each of the plurality of outlets being downstream of the fuel injection port.

5. The system of claim 1 , further comprising a protective housing positioned radially outward of the purge air conduit and the fuel injector.

6. The system of claim 1 , wherein the fuel injector further comprises a center body located radially inward of the perimeter body.

7. The system of claim 5 , wherein the fuel injector further comprises a plurality of swirl vanes disposed between the center body and the perimeter body.

8. The system of claim 5 , wherein the center body defines a fuel plenum therein, the fuel plenum being in fluid communication with the fuel supply line and the fuel injection port being defined through the center body.

9. The system of claim 1 , wherein the inlet is a plurality of inlets and the outlet is a plurality of outlets, wherein the fuel egress passage comprises a plurality of upstream portions and a plurality of downstream portions, each of the plurality of upstream portions including one of the plurality of inlets, each of the plurality of downstream portions including one of the plurality of outlets, and wherein the fuel purge cavity is between the plurality of upstream portions and the plurality of downstream portions.

10. The system of claim 9 , wherein the number of downstream portions is greater than the number of upstream portions.

11. The system of claim 9 , wherein the plurality of outlets is spaced around an interior surface of the perimeter body.

12. A gas turbine combustor comprising:

an axial fuel staging (AFS) system comprising:

a fuel supply assembly having a fuel supply line providing fuel and a purge air conduit arranged co-axially around the fuel supply line, thereby defining an annular channel around the fuel supply line;

a fuel injector for a combustor, the fuel injector including a perimeter body defining a portion of the fuel injector, a fuel injection port associated with the perimeter body, and an internal mixing chamber downstream of the fuel injection port in a direction of fuel flow;

wherein the fuel supply line provides fuel to the fuel injection port; and

wherein the perimeter body of the fuel injector defines a fuel egress passage therethrough, the fuel egress passage having an inlet in fluid communication with the annular channel and an outlet in fluid communication with the mixing chamber, the fuel egress passage further comprising a fuel purge cavity between the inlet and the outlet, the fuel purge cavity being defined as an annular cavity within a circumference of the perimeter body.

13. The gas turbine combustor of claim 12 , further comprising a liner having a forward end and an aft end and defining therebetween a combustion chamber, the fuel injector being located along the liner between the forward end and the aft end to inject fuel in a radial direction into the combustion chamber relative to a longitudinal axis of the combustor.

14. The gas turbine combustor of claim 13 , wherein the fuel injector is one of a plurality of fuel injectors located along the liner, each of the plurality of fuel injectors having a respective fuel supply assembly.

15. The gas turbine combustor of claim 12 , wherein the outlet of the fuel egress passage is downstream of the fuel injection port.

16. The gas turbine combustor of claim 12 , wherein the fuel egress passage includes a first portion upstream of the fuel purge cavity and a second portion downstream of the fuel purge cavity, the first portion including the inlet and the second portion including the outlet.

17. The gas turbine combustor of claim 12 , wherein a plurality of outlets extends from the fuel purge cavity, each of the plurality of outlets being downstream of the fuel injection port.

18. The gas turbine combustor of claim 12 , wherein the fuel injector further comprises a center body located radially inward of the perimeter body.

19. The gas turbine combustor of claim 18 , wherein the fuel injector further comprises a plurality of swirl vanes disposed between the center body and the perimeter body.

20. The gas turbine combustor of claim 18 , wherein the center body defines a fuel plenum therein, the fuel plenum being in fluid communication with the fuel supply line and the fuel injection port being defined through the center body.