Annular Concentric Fuel Nozzle Assembly

Patent metadata

Field	Value
Publication number	US-2020158343-A1
Application number	US-201816196383-A
Country	US
Kind code	A1
Filing date	Nov 20, 2018
Priority date	Nov 20, 2018
Publication date	May 21, 2020
Grant date	—

Abstract

A fuel nozzle for a gas turbine engine is generally provided. The fuel nozzle includes an outer sleeve extended circumferentially around a fuel nozzle centerline and extended along a longitudinal direction substantially co-directional to the fuel nozzle centerline. 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. The fuel nozzle further includes a centerbody positioned radially inward of the outer sleeve. The centerbody is extended along the longitudinal direction substantially co-directional to the fuel nozzle centerline and wherein the centerbody is concentric to the fuel nozzle centerline and the outer sleeve. The centerbody defines a plurality of second radially oriented air inlet ports through the centerbody in circumferential arrangement relative to the fuel nozzle centerline. The centerbody further defines an annular centerbody groove or depression relative to the fuel nozzle centerline at a downstream end directly adjacent to a combustion chamber. The fuel nozzle further includes an inner sleeve extended circumferentially around the fuel nozzle centerline and extended along the longitudinal direction substantially co-directional to the fuel nozzle centerline. The inner sleeve is positioned radially between the outer sleeve and the centerbody. The inner sleeve further defines an annular inner sleeve depression relative to the fuel nozzle centerline at the downstream end directly adjacent to the combustion chamber. The outer sleeve and the inner sleeve together define a first fuel air mixing passage radially therebetween and extended substantially along the longitudinal direction in direct fluid communication with the combustion chamber. The inner sleeve and the centerbody together further define a second fuel air mixing passage radially therebetween and extended substantially along the longitudinal direction in direct fluid communication with the combustion chamber.

First claim

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 substantially 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, wherein the centerbody is extended along the longitudinal direction substantially co-directional to the fuel nozzle centerline and wherein the centerbody is concentric to the fuel nozzle centerline and the outer sleeve, and further wherein the centerbody defines a plurality of second radially oriented air inlet ports through the centerbody in circumferential arrangement relative to the fuel nozzle centerline, and wherein the centerbody defines an annular centerbody depression relative to the fuel nozzle centerline at a downstream end directly adjacent to a combustion chamber; and an inner sleeve extended circumferentially around the fuel nozzle centerline and extended along the longitudinal direction substantially co-directional to the fuel nozzle centerline, wherein the inner sleeve is positioned radially between the outer sleeve and the centerbody, and wherein the inner sleeve defines an annular inner sleeve depression relative to the fuel nozzle centerline at the downstream end directly adjacent to the combustion chamber; wherein the outer sleeve and the inner sleeve together define a first fuel air mixing passage radially therebetween and extended substantially along the longitudinal direction in direct fluid communication with the combustion chamber, and further wherein the inner sleeve and the centerbody together define a second fuel air mixing passage radially therebetween and extended substantially along the longitudinal direction in direct fluid communication with the combustion chamber.

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 inner sleeve.

3 . The fuel nozzle of claim 1 , wherein the second fuel air mixing passage is extended circumferentially around the fuel nozzle centerline between the inner sleeve and the centerbody.

4 . The fuel nozzle of claim 1 , wherein the outer sleeve, the inner sleeve, and the centerbody are together in concentric arrangement relative to the fuel nozzle centerline.

5 . The fuel nozzle of claim 4 , wherein the first fuel air mixing passage and the second fuel air mixing passage are in concentric arrangement relative to the fuel nozzle centerline.

6 . The fuel nozzle of claim 1 , further comprising:
an end wall positioned at an upstream end of the fuel nozzle, wherein the end wall is coupled to the outer sleeve, the inner sleeve, and the centerbody.

7 . The fuel nozzle of claim 6 , 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.

8 . The fuel nozzle of claim 7 , 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.

9 . The fuel nozzle of claim 7 , wherein the first fuel injection port is extended substantially along the longitudinal direction.

10 . The fuel nozzle of claim 6 , wherein the end wall defines a second fuel injection port in fluid communication with the second fuel air mixing passage, wherein the end wall is configured to provide a flow of fuel to the second fuel air mixing passage via the second fuel injection port.

11 . The fuel nozzle of claim 10 , wherein the plurality of second radially oriented air inlet ports are defined directly radially inward 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.

12 . The fuel nozzle of claim 10 , wherein the second fuel injection port is extended substantially along the longitudinal direction.

13 . The fuel nozzle of claim 1 , wherein the centerbody defines a substantially radially oriented centerbody fuel injection port configured to provide a jet-in-crossflow flow of fuel to the second fuel air mixing passage.

14 . The fuel nozzle of claim 1 , wherein the centerbody defines a substantially longitudinally oriented centerbody fuel injection port configured to provide a substantially longitudinal flow of fuel to the combustion chamber.

15 . The fuel nozzle of claim 1 , wherein the inner sleeve defines a plurality of third radially oriented air inlet ports through the inner sleeve in circumferential arrangement relative to the fuel nozzle centerline.

16 . The fuel nozzle of claim 1 , wherein the first fuel air mixing passage defines a first exit height at the downstream end of the first fuel air mixing passage directly adjacent to the combustion chamber, wherein the first exit height is between an inner surface of the outer sleeve and an outer surface of the inner sleeve, and further wherein the first exit height is between approximately 0.25 centimeters and approximately 0.90 centimeters.

17 . The fuel nozzle of claim 1 , wherein the second fuel air mixing passage defines a second exit height at the downstream end of the second fuel air mixing passage directly adjacent to the combustion chamber, wherein the second exit height is between an inner surface of the inner sleeve and an outer surface of the centerbody, and further wherein the second exit height is between approximately 0.25 centimeters and approximately 0.90 centimeters.

18 . The fuel nozzle of claim 1 , wherein the annular centerbody depression defines a substantially semi-circular cross sectional centerbody depression into the centerbody.

19 . The fuel nozzle of claim 1 , wherein the annular inner sleeve depression defines a substantially semi-circular cross sectional depression into the inner sleeve.

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 a fuel nozzle disposed adjacent to the combustion chamber configured to provide a flow of fuel to the combustion chamber, wherein the fuel nozzle comprises; an outer sleeve extended circumferentially around a fuel nozzle centerline and extended along a longitudinal direction substantially 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, wherein the centerbody is extended along the longitudinal direction substantially co-directional to the fuel nozzle centerline and wherein the centerbody is concentric to the fuel nozzle centerline and the outer sleeve, and further wherein the centerbody defines a plurality of second radially oriented air inlet ports through the centerbody in circumferential arrangement relative to the fuel nozzle centerline, and wherein the centerbody defines an a

Assignees

• Gen Electric

Inventors

• Boardman Gregory Allen
• Giridharan Manampathy Gangadharan
• Benjamin Michael Anthony
• Naik Pradeep
• Cooper Clayton Stuart
• Kediya Vishal Sanjay

Classifications

• F05D2240/35

  Combustors or associated equipment · CPC title

• F02C7/22

  Fuel supply systems · CPC title

• F23R3/286 Primary

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

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F23R3/12

  inducing a vortex · CPC title