# US 2025/0093031 A1 · Gas turbine engine and fuel nozzle therefor

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- Number: US 2025/0093031 A1
- Document ID: US20250093031A1
- Status: Published application
- Kind: A1
- Application number: 18/469,174
- Filed: 2023-09-18
- Published: 2025-03-20
- Earliest claimed: 2023-09-18
- Assignees: GE Marmara Technology Center Muhendislik Hizmetleri Ltd; General Electric Company
- Applicants: GE Marmara Technology Center Muhendislik Hizmetleri Ltd; General Electric Company
- Inventors: Volkan Ataman; Fatih Yasar; Emrah Deniz; Michael T. Bucaro
- Web page: https://patentgrep.com/patent/US20250093031A1

## CPC

- F23R 3/28: characterised by the fuel supply (burners F23D)
- F23R 3/283: {Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances}
- F02C 7/22: Fuel supply systems
- F16L 41/14: by screwing an intermediate part against the inside or outside of the wall {(F16L41/086 takes precedence)}
- F23R 3/002: {Wall structures (F23R3/02 and F23R3/007 take precedence)}
- F23R 3/60: Support structures; Attaching or mounting means
- F23R: GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS (fluidised bed combustion apparatus specially adapted for operation at superatmospheric pressures F23C10/16)
- F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00)
- F16L: PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL

## Abstract

A gas turbine engine comprising a combustion section enshrouded by a casing having at least one through passage, the combustion section comprising a dome wall and a liner at least partially defining a combustion chamber; a fuel nozzle connected to the dome wall and having a nozzle tube; and a coupling securing the fuel nozzle with casing and disposed at least partially in the at least one through passage.

## Claims

### Claim 1

A gas turbine engine comprising:
a combustion section enshrouded by a casing having at least one through passage, the combustion section comprising:
a dome wall and a liner at least partially defining a combustion chamber;
a fuel nozzle connected to the dome wall and having a nozzle tube; and
a coupling securing the fuel nozzle with an inner surface of the casing and disposed at least partially in the at least one through passage;
wherein the coupling includes a flange disposed at the inner surface of the casing, a first shaft engaged with the flange, and a second shaft disposed at least partially around the first shaft and engaged with the flange.

### Claim 2 (depends on 1)

The gas turbine engine of claim 1, wherein the fuel nozzle is rigidly fixed to the inner surface of the casing by the coupling and rigidly fixed to the dome wall.

### Claim 3 (depends on 1)

The gas turbine engine of claim 1, wherein the first shaft includes a first fluid passage, the flange includes a second fluid passage fluidly coupled with the first fluid passage, and the nozzle tube includes a third fluid passage fluidly coupled with the second fluid passage.

### Claim 4 (depends on 1)

The gas turbine engine of claim 1, wherein the first shaft and the second shaft extend into the through passage and are disposed partially outside the casing; and
wherein the second shaft is disposed partially in a space inside the casing.

### Claim 5 (depends on 1)

The gas turbine engine of claim 1, wherein the coupling includes a nut disposed at an outer surface of the casing and engaged with the second shaft.

### Claim 6 (depends on 5)

The gas turbine engine of claim 5, wherein the flange is engaged with a threaded outer surface of the second shaft;
wherein the nut is engaged with the threaded outer surface of the second shaft; and
wherein a portion of the casing is disposed between the flange and the nut.

### Claim 7 (depends on 6)

The gas turbine engine of claim 6, wherein an axial surface of the first shaft includes a plurality of formations engaged with a corresponding plurality of formations of an axial surface of the flange to restrict relative rotation between the first shaft and the flange.

### Claim 8 (depends on 6)

The gas turbine engine of claim 6, wherein the first shaft includes a first fluid passage, the flange includes a second fluid passage fluidly coupled with the first fluid passage, and the nozzle tube includes a third fluid passage fluidly coupled with the second fluid passage.

### Claim 9 (depends on 6)

The gas turbine engine of claim 6, wherein the first shaft, the second shaft, and the flange at least partially define a leak path providing fluid communication from inside the coupling to a space outside of the casing.

### Claim 10 (depends on 9)

The gas turbine engine of claim 9, wherein the leak path includes a leak channel of the first shaft, a leak channel of the second shaft, or both; and
wherein the leak path includes a radial gap between the first shaft and the second shaft.

### Claim 11 (depends on 1)

The gas turbine engine of claim 1, wherein the coupling includes a first seal disposed in a first seal recess in an axial surface of the flange and in contact with the first shaft, and a second seal disposed in a second seal recess of the flange and in contact with the inner surface of the casing;
wherein the flange includes a channel disposed radially between the first seal recess and the second seal recess; and
wherein a portion of the second shaft is disposed in the channel.

### Claim 12 (depends on 1)

The gas turbine engine of claim 1, wherein the coupling includes a nut disposed at an outer surface of the casing;
wherein the coupling includes a third shaft disposed at least partially around the second shaft; and
wherein the third shaft is engaged with the flange and the nut.

### Claim 13 (depends on 12)

The gas turbine engine of claim 12, wherein the third shaft includes a threaded surface engaged with the flange and the nut;
wherein the second shaft incudes a second shaft threaded surface engaged with the flange; and
wherein portions of the second shaft and the third shaft are disposed in a channel of the flange.

### Claim 14 (depends on 12)

The gas turbine engine of claim 12, wherein the first shaft, the second shaft, the third shaft, and the nut include flat portions disposed outside of the casing.

### Claim 15

A fuel nozzle assembly for a gas turbine engine, the fuel nozzle assembly comprising:
a first shaft including a first fluid passage;
a flange connected to the first shaft and including a second fluid passage fluidly coupled with the first fluid passage;
a nozzle tube connected to the flange and including a third fluid passage fluidly coupled with the second fluid passage, the nozzle tube disposed at a first side of the flange;
a second shaft connected to the flange, the first shaft disposed at least partially in the second shaft; and
a nut disposed at a second side of the flange, the second side opposite the first side.

### Claim 16 (depends on 15)

The fuel nozzle assembly of claim 15, wherein the flange, the first shaft, and the second shaft at least partially define a leak path.

### Claim 17 (depends on 16)

The fuel nozzle assembly of claim 16, wherein the leak path includes:
a radial gap between the first shaft and the second shaft; and
a leak channel in an axial surface of at least one of the first shaft or the second shaft.

### Claim 18 (depends on 15)

The fuel nozzle assembly of claim 15, wherein one of the flange or the first shaft includes a plurality of axially-extending teeth disposed in a recess of the other of the flange and the first shaft to restrict rotation between the flange and the first shaft.

### Claim 19 (depends on 15)

The fuel nozzle assembly of claim 15, wherein the first shaft extends axially beyond the second shaft such that flat portions of the first shaft are not covered by the second shaft.

### Claim 20 (depends on 15)

The fuel nozzle assembly of claim 15, further comprising a third shaft disposed at least partially around the second shaft;
wherein the first shaft is disposed at least partially in the third shaft; and
wherein the second shaft and the third shaft are threadedly engaged with the flange.