SYSTEMS AND METHODS FOR CREATING A SEAL ABOUT A LIQUID FUEL INJECTOR IN A GAS TURBINE ENGINE

• US 20160281989A1
• Filed: 03/26/2015
• Published: 09/29/2016
• Est. Priority Date: 03/26/2015
• Status: Active Grant

• Current Assignee: GE Infrastructure Technology, LLC (General Electric Company)
• Original Assignee: General Electric Company
• Inventors: Johnson, Thomas Edward, Graham, Kaitlin Marie
• Granted Patent: US 10,060,628 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: F02C 3/04 having a turbine driving a compressor power transmission arrangements F02C7/36; control of working fluid flow F02C9/16
• CPC Class Codes: F23D 11/383 with swirl means
• CPC Class Codes: F23R 2900/00012 Details of sealing devices
• CPC Class Codes: F23R 3/283 Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
• CPC Class Codes: F23R 3/286 having fuel-air premixing devices F23R3/30 takes precedence
• CPC Class Codes: F23R 3/36 Supply of different fuels

Abstract

A fuel nozzle assembly for a gas turbine engine is disclosed herein. The fuel nozzle assembly may include a fuel injector including an outer jacket having a first end and a second end with a threaded surface disposed therebetween. The first end of the fuel injector may include a cylindrical sealing surface. The fuel nozzle assembly also may include an annular hub including an aperture having a first end and a second end with a threaded surface disposed therebetween. The aperture may be configured to at least partially house the fuel injector therein and includes a conical seat about the first end. The cylindrical sealing surface may swage inward along the conical seat to form a seal therebetween as the liquid fuel injector is threaded into the aperture.

Claims

1. A fuel nozzle assembly for a gas turbine engine, comprising:

a fuel injector comprising an outer jacket having a first end and a second end with a threaded surface disposed therebetween, wherein the first end of the fuel injector comprises a cylindrical sealing surface; and

an annular hub comprising an aperture having a first end and a second end with a threaded surface disposed therebetween, wherein the aperture is configured to at least partially house the fuel injector therein and comprises a conical seat about the first end, wherein the cylindrical sealing surface swages inward along the conical seat to form a seal therebetween as the liquid fuel injector is threaded into the aperture.

2. The fuel nozzle assembly of claim 1, wherein the fuel injector comprises an atomizing liquid fuel injector, a plain jet liquid fuel injector, or a simple orifice liquid fuel injector.

3. The fuel nozzle assembly of claim 1, wherein the aperture is in communication with a liquid fuel passage.

4. The fuel nozzle assembly of claim 1, wherein the outer jacket comprises:

an internal passageway between the first end and the second end; and

an orifice disposed about the second end, wherein the orifice is narrower than the internal passage.

5. A fuel nozzle assembly for a gas turbine engine, comprising:

a liquid fuel injector comprising an outer jacket having a first end and a second end with a threaded surface disposed therebetween, wherein the first end of the liquid fuel injector comprises a cylindrical sealing surface; and

an annular hub comprising an aperture having a first end and a second end with a threaded surface disposed therebetween, wherein the aperture is configured to at least partially house the liquid fuel injector therein and comprises a conical seat about the first end that is configured to mate with the cylindrical sealing surface of the liquid fuel injector as the liquid fuel injector is threaded into the aperture.

6. The fuel nozzle assembly of claim 5, wherein the second end of the liquid fuel injector comprises a seating surface.

7. The fuel nozzle assembly of claim 6, wherein the second end of the aperture comprises a seating surface configured to mate with the seating surface of the liquid fuel injector as the liquid fuel injector is threaded into the aperture.

8. The fuel nozzle assembly of claim 5, wherein the aperture is in communication with a liquid fuel passage.

9. The fuel nozzle assembly of claim 8, wherein the liquid fuel passage comprises a fuel plenum therein.

10. The fuel nozzle assembly of claim 5, wherein the outer jacket comprises an internal passageway between the first end and the second end, wherein the internal passageway is in communication with an orifice disposed about the second end.

11. The fuel nozzle assembly of claim 10, wherein the orifice is narrower than the internal passage.

12. The fuel nozzle assembly of claim 10, further comprising a swirler disposed within the internal passage.

13. The fuel nozzle assembly of claim 5, wherein the liquid fuel injector comprises an atomizing liquid fuel injector, a plain jet liquid fuel injector, or a simple orifice liquid fuel injector.

14. A gas turbine engine, comprising:

a compressor;

a combustor in communication with the compressor, the combustor including a fuel nozzle assembly, comprising;

a fuel injector comprising an outer jacket having a first end and a second end with a threaded surface disposed therebetween, wherein the first end of the fuel injector comprises a cylindrical sealing surface; and

an annular hub comprising an aperture having a first end and a second end with a threaded surface disposed therebetween, wherein the aperture is configured to at least partially house the fuel injector therein and comprises a conical seat about the first end, wherein the cylindrical sealing surface swages inward along the conical seat to form a seal therebetween as the liquid fuel injector is threaded into the aperture; and

a turbine in communication with the combustor.

15. The gas turbine engine of claim 14, wherein the second end of the fuel injector comprises a seating surface.

16. The gas turbine engine of claim 15, wherein the second end of the aperture comprises a seating surface configured to mate with the seating surface of the fuel injector as the fuel injector is threaded into the aperture.

17. The gas turbine engine of claim 14, wherein the aperture is in communication with a liquid fuel passage.

18. The gas turbine engine of claim 14, wherein the outer jacket comprises an internal passageway between the first end and the second end, wherein the internal passageway is in communication with an orifice disposed about the second end.

19. The gas turbine engine of claim 18, wherein the orifice is narrower than the internal passage.

20. The gas turbine engine of claim 14, wherein the liquid fuel injector comprises an atomizing liquid fuel injector, a plain jet liquid fuel injector, or an simple orifice liquid fuel injector.