当前申请(专利权)人地址：
Incorporated in USA - New York, 1 River Road, Schenectady, New York 12345, United States of America
摘要：
A fuel injector assembly 70 for a gas turbine engine (10 Fig 1) has at least one fuel injector 100 that includes a first centerbody 110 surrounding a first walled fuel injection circuit 120 with a first fuel injection port 130 extended at least partially radially through the first centerbody. The first centerbody defines a cooling circuit 140 surrounding the first walled fuel injection circuit and includes a plurality of cooling openings 115 at a downstream end 98 and an axially extended cooling outlet 117 also at the downstream end. The first centerbody may be a frusto-conical structure 113 and/or may include a bulbous structure 114. A further fuel injector 200 with associated centerbody 210 and fuel circuit 220 may be provided which includes a second fuel injection port 230 and may include a third fuel injection circuit 320 with port 325. In use, the first fuel injector port may deliver a lean fuel mixture and the third fuel injector port may deliver a richer fuel mixture compared to the second fuel injection port. The arrangement provides enhanced combustion stability, lower NOx and enhanced lean blow out capability.
权利要求：
WHAT IS CLAIMED IS:
1. A fuel injector assembly for a gas turbine engine, the fuel injector assembly comprising:
a first fuel injector comprising a first centerbody surrounding a first walled fuel injection circuit, wherein a first fuel injection port is extended at least partially radially through the first centerbody in fluid communication with the first walled fuel injection circuit, and further wherein the first centerbody defines a cooling circuit surrounding the first walled fuel injection circuit, and wherein the first centerbody defines a plurality of cooling openings at a downstream end of the first centerbody, wherein the plurality of cooling openings is in fluid communication with the cooling circuit, and further wherein the first centerbody defines an axially extended cooling outlet at the downstream end of the first centerbody.
2. The fuel injector assembly of claim 1, wherein the cooling outlet is in direct fluid communication with a combustion chamber of the gas turbine engine, and further wherein the cooling outlet is defined axially adjacent to the combustion chamber.
3. The fuel injector assembly of claim 1 or 2, wherein the plurality of cooling openings is defined through the first centerbody at least partially upstream of the cooling outlet.
4. The fuel injector assembly of any of claims 1 to 3, wherein the plurality of cooling openings is defined substantially axially through the first centerbody.
5. The fuel injector assembly of any of claims 1 to 4, wherein the first centerbody comprises a conical or frusto-conical structure.
6. The fuel injector assembly of any of claims 1 to 5, wherein the first centerbody comprises a bulbous structure.
7. The fuel injector assembly of any of claims 1 to 6, wherein the first centerbody defines a throat area between the cooling circuit and the axially extended cooling outlet, and wherein the cooling outlet defines an increasing cross sectional area from the throat area to the downstream end of the first centerbody.
8. The fuel injector assembly of any of claims 1 to 7, wherein the first fuel injector further comprises an internal shroud disposed within the first centerbody, wherein the internal shroud surrounds the first walled fuel injection circuit.
9 The fuel injector assembly of claim 8, wherein the internal shroud defines a conical or frusto-conical structure defining a decreasing cross sectional area from an upstream end to a downstream end.
10. The fuel injector assembly of claim 8 or 9, wherein the internal shroud defines a cooling cavity between the internal shroud and the first walled fuel injection circuit.
11. The fuel injector assembly of any of claims 1 to 10, wherein the first fuel injector is configured to provide only a flow of air through the downstream end of the first centerbody via the cooling opening.
12. The fuel injector assembly of any of claims 1 to 11, wherein the first fuel injector is configured to provide only a flow of air through the first centerbody downstream of the first fuel injection port.
13. The fuel injector assembly of any of claims 1 to 12, further comprising:
a second fuel injector comprising a second centerbody surrounding a second walled fuel injection circuit, wherein a second fuel injection port is extended at least partially radially through the second centerbody in fluid communication with the second walled fuel injection circuit, and further wherein the second centerbody defines a cooling circuit surrounding the second walled fuel injection circuit, and further wherein the second walled fuel injection circuit defines an axially extended third fuel injection port at a downstream end of the second centerbody.
14. The fuel injector assembly of claim 13, wherein the second fuel injector is configured to provide a flow of fuel through the downstream end of the second centerbody via the third fuel injection port.
15. The fuel injector assembly of claim 13 or 14, wherein the second centerbody of the second fuel injector defines a second cooling outlet at the downstream end of the second centerbody surrounding the third fuel injection port.
16. The fuel injector assembly of any of claims 1 to 15, further comprising:
a swirler assembly disposed upstream of the first fuel injection port.
17. A gas turbine engine, the engine comprising:
a first fuel injector comprising a first centerbody surrounding a first walled fuel injection circuit, wherein a first fuel injection port is extended at least partially radially through the first centerbody in fluid communication with the first walled fuel injection circuit, and further wherein the first centerbody defines a cooling circuit surrounding the first walled fuel injection circuit, and wherein the first centerbody defines a plurality of cooling openings at a downstream end of the first centerbody, wherein the plurality of cooling openings is in fluid communication with the cooling circuit, and further wherein the first centerbody defines an axially extended cooling outlet at the downstream end of the first centerbody.
18. The gas turbine engine of claim 17, wherein the first fuel injector further comprises an internal shroud disposed within the first centerbody, wherein the internal shroud surrounds the first walled fuel injection circuit.
19. The gas turbine engine of claim 17 or 18, further comprising:
a second fuel injector comprising a second centerbody surrounding a second walled fuel injection circuit, wherein a second fuel injection port is extended at least partially radially through the second centerbody in fluid communication with the second walled fuel injection circuit, and further wherein the second centerbody defines a cooling circuit surrounding the second walled fuel injection circuit, and further wherein the second walled fuel injection circuit defines an axially extended third fuel injection port at a downstream end of the second centerbody.
20. The gas turbine engine of claim 19, wherein the first fuel injector and the second fuel injector are arranged asymmetrically around an axial centerline axis of the engine.