AERODYNAMIC FASTENING OF TURBOMACHINE FUEL INJECTORS

• US 20180363909A1
• Filed: 06/19/2017
• Published: 12/20/2018
• Est. Priority Date: 06/19/2017
• Status: Active Grant

• Current Assignee: GE Infrastructure Technology, LLC (General Electric Company)
• Original Assignee: General Electric Company
• Inventors: Johnson, Thomas Edward, Graham, Kaitlin Marie, Myers, Geoffrey David
• Granted Patent: US 10,641,493 B2
• Time in Patent Office: Days
• CPC Class Codes: F02C 9/26 Control of fuel supply F02C9/48 takes precedence; fuel valves F02C7/232
• CPC Class Codes: F02M 61/14 Arrangements of injectors with respect to engines; Mounting of injectors
• CPC Class Codes: F02M 61/18 Injection nozzles, e.g. having valve seats; Details of valve member seated ends, not otherwise provided for
• CPC Class Codes: F23D 11/38 Nozzles; Cleaning devices therefor
• 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 premixing fuel nozzle assembly for a turbomachine is disclosed as having at least one fuel injector with an outer jacket having a first end and a second end and a threaded surface disposed therebetween. The first end has a cylindrical sealing surface and the second end has at least one wrenching pocket. An annular hub is disclosed as having an aperture with a first end and a second end and a threaded surface disposed therebetween, wherein the aperture is configured to at least partially house the fuel injector therein and the annular hub further has a conical seat about the first end. The fuel injector cylindrical sealing surface swages inward to form a hermetic seal when contacting the annular hub conical seat as the fuel injector is threaded into the aperture.

Claims

1. A premixing fuel nozzle assembly for a turbomachine, comprising:

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

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, the annular hub further comprising a conical seat about the first end; and

wherein the fuel injector cylindrical sealing surface swages inward to form a hermetic seal when contacting the annular hub conical seat as the fuel injector is threaded into the aperture.

2. The fuel nozzle assembly of claim 1, wherein the at least one wrenching pocket comprises a recessed cylindrical bore, a recessed oval bore, a recessed square bore, and combinations thereof.

3. The fuel nozzle assembly of claim 1, wherein the fuel injector comprises an atomizing liquid fuel injector, a plain jet liquid fuel injector, a simple orifice liquid fuel injector, and combinations thereof.

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

5. The fuel nozzle assembly of claim 4, wherein the liquid fuel passage comprises a fuel plenum therein.

6. A fuel nozzle assembly of claim 5, wherein a thermal break is disposed between the liquid fuel passage and the liquid fuel injector.

7. 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.

8. The fuel nozzle assembly of claim 7, further comprising a swirler disposed within the internal passage

9. The fuel nozzle assembly of claim 1, wherein the second end of the outer jacket comprises a seating surface.

10. The fuel nozzle assembly of claim 9, 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.

11. A turbomachine, comprising:

a compressor;

a combustor in communication with the compressor, the combustor comprising at least one premixing fuel nozzle assembly, comprising;

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

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, the annular hub further comprising a conical seat about the first end; and

wherein the fuel injector cylindrical sealing surface swages inward to form a hermetic seal when contacting the conical seat as the fuel injector is threaded into the aperture.

12. The turbomachine of claim 11, wherein the at least one wrenching pocket comprises a recessed cylindrical bore, a recessed oval bore, a recessed square bore, and combinations thereof.

13. The turbomachine of claim 11, wherein the fuel injector comprises an atomizing liquid fuel injector, a plain jet liquid fuel injector, a simple orifice liquid fuel injector, and combinations thereof.

14. The turbomachine of claim 11, wherein the aperture is in communication with a liquid fuel passage.

15. The turbomachine of claim 14, wherein the liquid fuel passage comprises a fuel plenum therein.

16. The turbomachine of claim 15, wherein a thermal break is disposed between the liquid fuel passage and the liquid fuel injector.

17. The turbomachine of claim 11, 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.

18. The turbomachine of claim 17, further comprising a swirler disposed within the internal passage

19. The turbomachine of claim 11, wherein the second end of the outer jacket comprises a seating surface.

20. The turbomachine of claim 19, 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.