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EP-4524470-B1 - GAS TURBINE ENGINE AND FUEL NOZZLE THEREFOR

EP4524470B1EP 4524470 B1EP4524470 B1EP 4524470B1EP-4524470-B1

Inventors

  • ATAMAN, VOLKAN
  • Yasar, Fatih
  • DENIZ, Emrah
  • BUCARO, Michael

Dates

Publication Date
20260513
Application Date
20240718

Claims (11)

  1. A gas turbine engine (10) comprising: a combustion section (14) enshrouded by a casing (29) having at least one through passage (76), the combustion section (14) comprising: a dome wall (46) and a liner at least partially defining a combustion chamber (50); a fuel nozzle (38, 1038) connected to the dome wall (46) and having a nozzle tube (70, 1070); and a coupling (80, 1080) securing the fuel nozzle (38, 1038) with an inner surface (60) of the casing (29) and disposed at least partially in the at least one through passage (76); wherein the coupling (80, 1080) includes a flange (82, 1082) disposed at the inner surface (60) of the casing (29), a first shaft (84, 1084) engaged with the flange (82, 1082), and a second shaft (86, 1086) disposed at least partially around the first shaft (84, 1084) and engaged with the flange (82, 1082); wherein the coupling (80, 1080) includes a nut (88, 1088) disposed at an outer surface (62) of the casing (29) and engaged with the second shaft (86, 1086); wherein the flange (82, 1082) is engaged with a threaded surface (170, 1170) of the second shaft (86, 1086); wherein the first shaft (84, 1084), the second shaft (86, 1086), and the flange (82, 1082) at least partially define a leak path providing fluid communication from inside the coupling (80, 1080) to a space (200) outside of the casing (29); wherein the leak path includes a leak channel (154, 1154) of the first shaft (84, 1084), a leak channel (182, 1182) of the second shaft (86, 1086), or both; and wherein the leak path includes a radial gap (212, 1212) between the first shaft (84, 1084) and the second shaft (86, 1086).
  2. The gas turbine engine (10) of claim 1, wherein the fuel nozzle (38, 1038) is rigidly fixed to the inner surface (60) of the casing (29) by the coupling (80, 1080) and rigidly fixed to the dome wall (46).
  3. The gas turbine engine (10) of any preceding claim, wherein the first shaft (84, 1084) includes a first fluid passage (100, 1100), the flange (82, 1082) includes a second fluid passage (102, 1102) fluidly coupled with the first fluid passage (100, 1100), and the nozzle tube (70, 1070) includes a third fluid passage (104, 1104) fluidly coupled with the second fluid passage (102, 1102).
  4. The gas turbine engine (10) of any preceding claim, wherein the first shaft (84, 1084) and the second shaft (86, 1086) extend into the through passage (76).
  5. The gas turbine engine (10) of claim 1, wherein an axial surface (120, 1120) of the first shaft (84, 1084) includes a formation engaged with and a corresponding formation of an axial surface (120, 1120) of the flange (82, 1082).
  6. The gas turbine engine (10) of claim 1 or 5, wherein the first shaft (84, 1084) includes a first fluid passage (100, 1100), the flange (82, 1082) includes a second fluid passage (102, 1102) fluidly coupled with the first fluid passage (100, 1100), and the nozzle tube (70, 1070) includes a third fluid passage (104, 1104) fluidly coupled with the second fluid passage (102, 1102).
  7. The gas turbine engine (10) of any preceding claim, wherein the coupling (80, 1080) includes a first seal (144, 1144) disposed in a first seal recess (140, 1140) of the flange (82, 1082), and a second seal (146, 1146) disposed in a second seal recess (142, 1142) of the flange (82, 1082); wherein the flange (82, 1082) includes a channel (114, 1114) disposed radially between the first seal recess (140, 1140) and the second seal recess (142, 1142); and wherein a portion of the second shaft (86, 1086) is disposed in the channel (114, 1114).
  8. The gas turbine engine (10) of any preceding claim, wherein the coupling (80, 1080) includes a nut (88, 1088) disposed at an outer surface (62) of the casing (29); wherein the coupling (80, 1080) includes a third shaft (1090) disposed at least partially around the second shaft (86, 1086); and wherein the third shaft (1090) is engaged with the flange (82, 1082) and the nut (88, 1088).
  9. The gas turbine engine (10) of claim 8, wherein the third shaft (1090) includes a threaded surface (1230) engaged with the flange (82, 1082) and the nut (88, 1088); wherein the second shaft (86, 1086) includes a second shaft (86, 1086) threaded surface (170, 1170) engaged with the flange (82, 1082); and wherein portions of the second shaft (86, 1086) and the third shaft (1090) are disposed in a channel (114, 1114) of the flange (82, 1082).
  10. The gas turbine engine (10) of claim 8 or 9, wherein the first shaft (84, 1084), the second shaft (86, 1086), the third shaft (1090), and the nut (88, 1088) include flat portions (158, 176, 192, 1158, 1176, 1192, 1236) disposed outside of the casing (29).
  11. The gas turbine engine (10) of claim 10, wherein the nut (88, 1088) is disposed outside of the casing (29), and the flange (82, 1082) is disposed inside the casing (29).

Description

TECHNICAL FIELD The present subject matter relates generally to a gas turbine engine having a fuel nozzle. BACKGROUND Turbine engines are driven by a flow of combustion gases passing through the engine to rotate a multitude of turbine blades, which, in turn, rotate a compressor to provide compressed air to the combustor for combustion. A combustor can be provided within the turbine engine and is fluidly coupled with a turbine into which the combusted gases flow. Historically, hydrocarbon fuels are used in the combustor of a turbine engine. Generally, air and fuel are fed to a combustion chamber, the air and fuel are mixed, and then the fuel is burned in the presence of the air to produce hot gas. The hot gas is then fed to a turbine where it cools and expands to produce power. By-products of the fuel combustion typically include environmentally unwanted byproducts, such as nitrogen oxide and nitrogen dioxide (collectively called NOx), carbon monoxide (CO), unburned hydrocarbons (UHC) (e.g., methane and volatile organic compounds that contribute to the formation of atmospheric ozone), and other oxides, including oxides of sulfur (e.g., SO2 and SO3). To reduce the environmentally unwanted byproducts, other fuels, such as hydrogen, are being explored. Hydrogen or hydrogen mixed with another element has a higher flame temperature than traditional hydrocarbon fuels. That is, hydrogen or a hydrogen mixed fuel typically has a wider flammable range and a faster burning velocity than traditional hydrocarbon-based fuels. US 5,279,112 A1 relates to a fuel line fitting to connect an external fuel line to an internal fuel line feeding an internal fuel manifold in a combustor of a gas turbine engine; the fitting includes a first joint half terminating the internal fuel line and a second joint half terminating the external fuel line, the joint halves being united to provide a threaded fluid joint; the first joint half is integrally formed with a cup-shaped reservoir containing the fluid joint and having an outwardly turned brim which is affixed to a combustor casing in surrounding relation to a casing hole; the reservoir thus serves to shunt mechanical loads from the fluid joint and to collect any fuel leakage therefrom. BRIEF DESCRIPTION OF THE DRAWINGS In the drawings: FIG. 1 is a schematic cross-sectional view of a turbine engine having a compression section, a combustion section, and a turbine section in accordance with various aspects described herein.FIG. 2 is a schematic view of the combustion section of FIG. 1 along line II-II in accordance with various aspects described herein.FIG. 3 is a schematic view illustrating portions of a fuel nozzle connected to a casing and a dome wall in accordance with various aspects described herein.FIG. 4 is a schematic sectional view of the fuel nozzle of FIG. 3.FIG. 5 is a perspective view of a flange of a coupling of a fuel nozzle in accordance with various aspects described herein.FIGs. 6 and 7 are perspective views of a first shaft of a coupling of a fuel nozzle in accordance with various aspects described herein.FIG. 8 is a perspective view of a second shaft of a coupling of a fuel nozzle in accordance with various aspects described herein.FIG. 9 is an enlarged sectional view of a coupling of a fuel nozzle connected to a casing in accordance with various aspects described herein.FIG. 10 is a schematic perspective view illustrating portions of a fuel nozzle connected to a casing and a dome wall in accordance with various aspects described herein.FIG. 11 is a schematic sectional view of the fuel nozzle of FIG. 10.FIG. 12 is a perspective view of a flange of a coupling of a fuel nozzle in accordance with various aspects described herein.FIG. 13 is a perspective view of a second shaft of a coupling of a fuel nozzle in accordance with various aspects described herein.FIG. 14 is a perspective view of a third shaft of a coupling of a fuel nozzle in accordance with various aspects described herein.FIG. 15 is an enlarged sectional view of a coupling of a fuel nozzle connected to a casing in accordance with various aspects described herein.FIG. 16 is a flow diagram illustrating a method of assembling a fuel nozzle assembly in a gas turbine engine in accordance with various aspects described herein. DETAILED DESCRIPTION A gas turbine engine according to the invention is defined in the appended claims. Aspects of the disclosure described herein are directed to a combustor. For purposes of illustration, the present disclosure will be described with respect to a turbine engine. It will be understood, however, that aspects of the disclosure described herein are not so limited and that a combustor as described herein can be implemented in engines, including but not limited to turbojet, turboprop, turboshaft, and turbofan engines. Aspects of the disclosure discussed herein may have general applicability within non-aircraft engines having a combustor, such as other mobile applications and non-