当前申请(专利权)人地址：
Incorporated in USA - New York, 1 River Road, Schenectady 12345, New York, United States of America
摘要：
A fuel nozzle 100 for a gas turbine comprising outer sleeve 110 extended circumferentially around a fuel nozzle centreline 112 and extended along a longitudinal direction co-directional to the fuel nozzle centerline. The outer sleeve defines a plurality of first radially oriented air inlet ports 113 through the outer sleeve in circumferential arrangement relative to the fuel nozzle centerline. A centerbody 130 is positioned radially inward of the outer sleeve. The centerbody includes an outer annular wall 131 extended circumferentially around the fuel nozzle centerline and extended along the longitudinal direction co-directional to the fuel nozzle centerline. The outer sleeve further includes a first radial wall 134 extended from a downstream end of the outer annular wall, the centerbody defining a plenum radially inward thereof. The outer annular wall and the outer sleeve together define a first fuel air mixing passage 115 extended along the longitudinal direction therebetween. A fuel injector 120 is disposed in the plenum, the fuel injector comprising a tubular outerwall 124 extended co-directional to the fuel nozzle centerline. The outer wall defines a second fuel air mixing passage 125 there within. The second fuel air mixing passage is extended through the first radial wall of the centerbody.
权利要求：
WHAT IS CLAIMED IS:
1. A fuel nozzle for a gas turbine engine, the fuel nozzle comprising:
an outer sleeve extended circumferentially around a fuel nozzle centerline and extended along a longitudinal direction co-directional to the fuel nozzle centerline, wherein the outer sleeve defines a plurality of first radially oriented air inlet ports through the outer sleeve in circumferential arrangement relative to the fuel nozzle centerline;
a centerbody positioned radially inward of the outer sleeve, the centerbody comprising an outer annular wall extended circumferentially around the fuel nozzle centerline and extended along the longitudinal direction co-directional to the fuel nozzle centerline, wherein the outer sleeve further comprises a first radial wall extended from a downstream end of the outer annular wall, and further wherein the centerbody defines a plenum radially inward of the centerbody, and wherein the outer annular wall and the outer sleeve together define a first fuel air mixing passage extended along the longitudinal direction therebetween; and
a fuel injector disposed in the plenum, wherein the fuel injector comprises a tubular outer wall extended co-directional to the fuel nozzle centerline, wherein the outer wall defines a second fuel air mixing passage therewithin, and wherein the second fuel air mixing passage is extended through the first radial wall of the centerbody.
2. The fuel nozzle of claim 1, wherein the first fuel air mixing passage is extended circumferentially around the fuel nozzle centerline between the outer sleeve and the centerbody.
3. The fuel nozzle of claim 1 or 2, the fuel nozzle comprising a plurality of fuel injectors disposed in the plenum, wherein each fuel injector defines the second fuel air mixing passage extended through the first radial wall of the centerbody in fluid communication with a combustion chamber
4. The fuel nozzle of any of claims 1 to 3, wherein the fuel injector is disposed concentric to the fuel nozzle centerline.
5. The fuel nozzle of any of claims 1 to 4, the fuel nozzle comprising a plurality of the fuel injectors disposed in the plenum in circumferential arrangement relative to the fuel nozzle centerline.
6. The fuel nozzle of claim 5, wherein two or more fuel injectors converge to a single fuel-air outlet opening.
7. The fuel nozzle of claim 6, wherein the two or more fuel injectors each comprise a reference fuel injector centerline, and each fuel injector is extended such as to dispose each fuel injector centerline of each fuel injector at a non-parallel angle relative to one another.
8. The fuel nozzle of any of claims 1 to 7, wherein the fuel nozzle defines a groove through the first radial wall, wherein the groove protrudes into the first radial wall toward the upstream direction relative to the fuel nozzle.
9 The fuel nozzle of claim 8, wherein the groove is extended into the first radial wall circumferentially relative to the fuel nozzle centerline axis.
10. The fuel nozzle of claim 8 or 9, wherein the groove is extended into the first radial wall at least partially along the radial direction extended from the fuel nozzle centerline.
11. The fuel nozzle of any of claims 8 to 10, wherein the fuel-air outlet opening is defined at the groove such that the fuel-air outlet opening is recessed into the first radial wall.
12. The fuel nozzle of any of claims 1 to 11, further comprising:
an end wall positioned at an upstream end of the fuel nozzle, wherein the end wall is coupled to the outer sleeve, and wherein the end wall defines a first fuel injection port in fluid communication with the first fuel air mixing passage, wherein the end wall is configured to provide a flow of fuel to the first fuel air mixing passage via the first fuel injection port.
13. The fuel nozzle of claim 12, wherein the plurality of first radially oriented air inlet ports are defined directly radially outward of a first fuel injection exit opening defined at the first fuel injection port in direct fluid communication with the first fuel air mixing passage.
14. The fuel nozzle of any of claims 1 to 13, wherein the fuel injector defines a second fuel injection port in fluid communication with the second fuel air mixing passage, wherein the fuel injector is configured to provide a flow of fuel to the second fuel air mixing passage via the second fuel injection port.
15. The fuel nozzle of claim 14, wherein the plurality of second radially oriented air inlet ports are defined directly radially outward of a second fuel injection exit opening defined at the second fuel injection port in direct fluid communication with the second fuel air mixing passage.
16. The fuel nozzle of claim 14 or 15, wherein the second fuel injection port is extended substantially along the longitudinal direction.
17. The fuel nozzle of any of claims 1 to 16, wherein the centerbody further comprises an inner annular wall and a second radial wall extended from the inner annular wall together defining a cavity therebetween.
18. The fuel nozzle of claim 17, wherein the second radial wall defines a radial wall opening therethrough providing fluid communication between the plenum and the cavity.
19. The fuel nozzle of claim 17 or 18, wherein the inner annular wall defines an annular wall opening therethrough providing fluid communication between the cavity and first fuel air mixing passage.
20 A gas turbine engine, the gas turbine engine comprising:
a combustion section comprising a combustor assembly defining a combustion chamber, and wherein the combustion section further comprises the fuel nozzle of any of claims 1 to 19 disposed adjacent to the combustion chamber configured to provide a flow of fuel to the combustion chamber.