Fuel injector for supplying fuel to a combustor

Patent metadata

Field	Value
Publication number	US-9534790-B2
Application number	US-201313735340-A
Country	US
Kind code	B2
Filing date	Jan 7, 2013
Priority date	Jan 7, 2013
Publication date	Jan 3, 2017
Grant date	Jan 3, 2017

Abstract

A fuel injector for a combustor generally includes an annular outer body having an inlet and an outlet. The outer body at least partially defines an outer flow passage. An inner flow passage extends at least partially through the outer flow passage and a radial swirler is disposed at the inlet of the outer body. The radial swirler includes a first radial passage separated from a second radial passage. The first radial passage has a first plurality of swirler vanes and the second radial passage has a second plurality of swirler vanes. The first radial passage is in fluid communication with the outer flow passage and the second radial passage is in fluid communication with the inner flow passage.

First claim

What is claimed is:

1. A fuel injector for a combustor, the fuel injector comprising:
a. an annular outer body having an inlet at an upstream end, the outer body at least partially defining an outer flow passage;
b. an inner flow passage that extends at least partially through the outer flow passage of the outer body; and
c. a radial swirler disposed at the inlet of the outer body of the fuel injector, the radial swirler comprising:
a radially extending cap plate disposed at a top portion of the radial swirler;
a radially extending annular plate disposed between the inlet of the outer body and the cap plate, the annular plate at least partially defining an inner flow passage that extends within the outer flow passage;
a first radial passage having a first plurality of swirler vanes that extend axially between the upstream end of the outer body and the annular plate, wherein the first radial passage is in fluid communication with the outer flow passage of the outer body, wherein the first plurality of swirler vanes is oriented perpendicular to an axial centerline of the fuel injector;
a second radial passage having a second plurality of swirler vanes that extend axially between the annular plate and the cap plate, wherein the second radial passage is in fluid communication with the inner flow passage, wherein the second plurality of swirler vanes is oriented perpendicular to the axial centerline of the fuel injector; and
a liquid fuel plenum that extends through the cap plate, the liquid fuel plenum being in fluid communication with at least one of the second radial passage or the inner flow passage.

2. The fuel injector as in claim 1 , further comprising an axial flow path that extends at least partially through the liquid fuel plenum and into at least one of the second radial passage or the inner flow passage.

3. The fuel injector as in claim 1 , further comprising a fuel circuit that extends at least partially through the outer body, wherein at least one of the swirler vanes of the first plurality of swirler vanes or at least one of the swirler vanes of the second plurality of swirler vanes includes a fuel injection port, the fuel injection port being in fluid communication with the fuel circuit.

4. The fuel injector as in claim 1 , further comprising an annular inner body that further defines the inner flow passage, wherein the inner body extends downstream from the annular plate.

5. The fuel injector as in claim 1 , wherein each swirler vane of the first plurality of swirler vanes includes a leading edge and a trailing edge, the trialing edge being arranged at a first swirl angle with respect to a first radial line that extends between the axial centerline of fuel infector and the leading edge.

6. The fuel injector as in claim 5 , wherein each swirler vane of the second plurality of swirler vanes includes a leading edge and a trailing edge, the trialing edge being arranged at a second swirl angle with respect to a second radial line that extends between the axial centerline of fuel injector and the leading edge, wherein the first swirl angle with respect to the first radial line and the second swirl angle with respect to the second radial line are different.

7. A gas turbine comprising:
a. a compressor, a combustor downstream from the compressor and a turbine downstream from the combustor, the combustor comprising:
a combustion chamber;
a liner that circumferentially surrounds at least a portion of the combustion chamber;
a plurality of fuel nozzles coupled to an end cover of the combustor and extending axially downstream from the end cover and terminating upstream from the combustion chamber; and
a fuel injector that extends radially through the liner downstream from the plurality of fuel nozzles, the fuel injector comprising:
(1) an annular outer body defining an inlet, an outlet and an outer flow passage, wherein the outer flow passage tapers radially inwardly along an axial centerline of the fuel injector from the inlet to the outlet;
(2) an inner flow passage that extends at least partially through the outer flow passage; and
(3) a radial swirler disposed at the inlet of the outer body, the radial swirler having a first radial passage including a first plurality of swirler vanes and a second radial passage including a second plurality of swirler vanes, the first radial passage being in fluid communication with the outer flow passage and the second radial passage being in fluid communication with the inner flow passage, wherein at least one of the swirler vanes of the first plurality of swirler vanes includes a fuel injection port and at least one of the swirler vanes of the second plurality of swirler vanes includes a fuel injection port.

8. The gas turbine as in claim 7 , wherein each swirler vane of the first plurality of swirler vanes includes a leading edge and a trailing edge, the trialing edge being arranged at a first swirl angle with respect to a first radial line that extends between the axial centerline of fuel injector and the leading edge.

9. The gas turbine as in claim 8 , wherein each swirler vane of the second plurality of swirler vanes includes a leading edge and a trailing edge, the trialing edge being arranged at a second swirl angle with respect to a second radial line that extends between the axial centerline of fuel injector and the leading edge, wherein the first swirl angle with respect to the first radial line and the second swirl angle with respect to the second radial line are different.

10. The gas turbine as in claim 7 , wherein the fuel injector further comprises a fuel circuit defined within the outer body, wherein the fuel injection port of the swirler vane of the first plurality of swirler vanes and the fuel injection port of the swirler vane of the second plurality of swirler vanes are in fluid communication with the fuel circuit.

11. A fuel injector for a combustor, the fuel injector comprising:
an annular outer body defining an inlet, an outlet and an outer flow passage, wherein the outer flow passage tapers radially inwardly along an axial centerline of the fuel injector from the inlet to the outlet; and
a radial swirler extending radially across and axially outwardly from an upstream end of the outer body, the radial swirler including a cap plate, an annular plate disposed axially between the cap plate and the upstream end of the outer body, a first plurality of swirler vanes that extends from the upstream end of the outer body to the annular plate within a first radial passage defined therebetween and a second plurality of swirler vanes that extends from the annular plate to the cap plate within a second radial passage defined therebetween;
wherein the annular plate defines an inner sleeve that defines an inner flow passage within the outer flow passage, wherein the first radial passage is in fluid communication with the outer flow passage and wherein the inner flow passage is in fluid communication with the second radial passage.

12. The fuel injector as in claim 11 , wherein the inner sleeve terminates upstream from the outlet of the outer tow passage.

13. The fuel injector as in claim 11 , further comprising a fuel circuit at least partially within the outer body, wherein the fuel injection port of the swirler vane of the first plurality of swirler vanes and the fuel injection port of the swirler vane of the second plurality of swirler vanes are in fluid communication with the fuel circuit.

14. The fuel injector as in claim 11 , wherein each swirler vane of the first plurality of swirler vanes includes a leading edge and a trailing edge, the trialing edge being arranged at a f

Assignees

• Gen Electric

Inventors

• Cai Jun
• Boardman Gregory Allen
• Karim Hasan
• Stoia Lucas John

Classifications

• F23C2900/07001

  Air swirling vanes incorporating fuel injectors · CPC title

• F23R3/346 Primary

  for staged combustion · CPC title

• F23R3/14

  by using swirl vanes · CPC title

• F23R3/286

  having fuel-air premixing devices (F23R3/30 takes precedence) · CPC title