Fuel nozzle with integrated metering and flashback system

Patent metadata

Field	Value
Publication number	US-11525403-B2
Application number	US-202117308158-A
Country	US
Kind code	B2
Filing date	May 5, 2021
Priority date	May 5, 2021
Publication date	Dec 13, 2022
Grant date	Dec 13, 2022

Abstract

A fuel supply system for an aircraft engine, comprises a gaseous fuel source and a fuel nozzle. The fuel nozzle includes a housing having a housing interior chamber and a fuel swirler disposed inside the housing interior chamber. The fuel swirler is fluidly connected to the gaseous fuel source for directing gaseous fuel to a combustor of the aircraft engine. The fuel swirler defines a gaseous fuel path extending from a fuel inlet to a fuel outlet. The gaseous fuel path includes a plurality of discrete apertures distributed around a circumference of the fuel swirler, each of the plurality of discrete apertures having a cross-sectional area selected to prevent a flame from propagating in an upstream direction through the gaseous fuel path towards the gaseous fuel source.

First claim

The invention claimed is:

1. A fuel supply system for an aircraft engine, comprising:
a gaseous fuel source;
a fuel nozzle including:
a housing having a housing interior chamber; and
a fuel swirler disposed inside the housing interior chamber, the fuel swirler fluidly connected to the gaseous fuel source for directing gaseous fuel to a combustor of the aircraft engine, the fuel swirler defining a gaseous fuel path extending from a fuel inlet to a fuel outlet, the gaseous fuel path including a plurality of discrete apertures distributed around a circumference of the fuel swirler, each of the plurality of discrete apertures having a cross-sectional area selected to prevent a flame from propagating in an upstream direction through the gaseous fuel path towards the gaseous fuel source, wherein the plurality of discrete apertures are positioned at the fuel inlet of the fuel swirler, and wherein the plurality of discrete apertures are defined through a radially exterior surface of the fuel swirler relative to a longitudinal axis of the fuel swirler.

2. The fuel supply system as defined in claim 1 , wherein the plurality of discrete apertures have circular cross-sectional shapes.

3. The fuel supply system as defined in claim 2 , wherein the plurality of discrete apertures have cross-sectional diameters of at most 0.024 inches.

4. The fuel supply system as defined in claim 1 , further comprising a second fuel path in fluid communication with a second fuel source and terminating at a second fuel outlet.

5. The fuel supply system as defined in claim 1 , wherein the fuel outlet is positioned on an outer surface of the fuel swirler bordering a mixing site downstream of the fuel swirler, the fuel outlet leading directly to the mixing site.

6. The fuel supply system of claim 1 , wherein the gaseous fuel source contains hydrogen.

7. The fuel supply system as defined in claim 1 , wherein the plurality of discrete apertures are arranged in an evenly spaced, multi-row staggered formation.

8. A fuel supply system for an aircraft engine, comprising:
a gaseous fuel source;
a fuel nozzle including:
a housing having a housing interior chamber;
a fuel swirler disposed inside the housing interior chamber, the fuel swirler fluidly connected to the gaseous fuel source for directing gaseous fuel to a combustor of the aircraft engine, the fuel swirler defining a gaseous fuel path extending from a fuel inlet to a fuel outlet and defining a general fuel flow direction; and
a combined flashback arrestor and flow restrictor disposed about a circumference of the fuel swirler, the combined flashback arrestor and flow restrictor operable to prevent a flame from traveling upstream towards the gaseous fuel source and to selectively restrict a flow of gaseous fuel from the gaseous fuel source towards the combustor, wherein the combined flashback arrestor and flow restrictor is an insert with an annular body, the insert positioned between the housing and the fuel swirler at the fuel inlet of the fuel swirler, the insert including a plurality of discrete apertures.

9. The fuel supply system as defined in claim 8 , wherein plurality of discrete apertures have circular cross-sectional shapes.

10. The fuel supply system as defined in claim 9 , wherein the plurality of discrete apertures have cross-sectional diameters of at most 0.024 inches.

11. The fuel supply system as defined in claim 8 , further comprising a second fuel path in fluid communication with a second fuel source and terminating at a second fuel outlet.

12. The fuel supply system as defined in claim 8 , wherein the fuel outlet is positioned on an outer surface of the fuel swirler bordering a mixing site downstream of the fuel swirler, the fuel outlet leading directly to the mixing site.

13. The fuel supply system of claim 8 , wherein the insert is provided in the form of a corrugated screen.

14. The fuel supply system of claim 8 , wherein the gaseous fuel source contains hydrogen.

Assignees

• Pratt & Whitney Canada

Inventors

• Morenko Oleg
• Wong Owen Ho-Yin

Classifications

• F05D2240/35

  Combustors or associated equipment · CPC title

• F23D14/24

  at least one of the fluids being submitted to a swirling motion · CPC title

• F23C1/08

  liquid and gaseous fuel · CPC title

• F05D2250/141

  circular · CPC title

• F23R2900/00002

  Gas turbine combustors adapted for fuels having low heating value [LHV] · CPC title