Anti-coking liquid fuel injector assembly for a combustor

Patent metadata

Field	Value
Publication number	US-10006636-B2
Application number	US-201314082677-A
Country	US
Kind code	B2
Filing date	Nov 18, 2013
Priority date	Nov 21, 2012
Publication date	Jun 26, 2018
Grant date	Jun 26, 2018

Abstract

A liquid fuel cartridge assembly for a gas turbine combustor comprising an elongated stem provided with a fuel injector tip at an aft end of said stem, said injector tip provided with a pilot fuel passage extending to a pilot fuel orifice; a plurality of air channels surrounding said pilot fuel passage and in communication with plural air holes; an annular main fuel passage surrounding said plurality of air channels and in communication with plural fuel exit holes; and a plurality of substantially radially oriented air supply holes in said stem upstream but proximate to a forward end of said tip in communication with said plurality of air channels.

First claim

What is claimed is:

1. A liquid fuel cartridge assembly for a gas turbine combustor comprising:
an elongated stem having an aft end;
a fuel injector tip mounted to the aft end of the elongated stem and extending axially beyond the aft end, wherein the fuel injector tip includes a pilot fuel passage extending to a pilot fuel orifice and said fuel injector tip extending axially beyond the aft end of the elongated stem;
air channels in the fuel injector tip and arranged around the pilot fuel passage and in communication with air exit openings;
an annular main fuel passage arranged around the air channels and in communication with fuel exit holes, wherein the pilot fuel passage and the annular main fuel passage forms a double helix that extends axially through the elongated stem; and
radially oriented air supply holes in the elongated stem upstream and proximate to a forward end of the fuel injector tip in communication with the air channel.

2. The liquid fuel cartridge assembly of claim 1 wherein a nozzle insert is located within said fuel injector tip and is provided with said pilot fuel orifice.

3. The liquid fuel cartridge assembly of claim 2 wherein said nozzle insert includes the air exit openings.

4. The liquid fuel cartridge assembly of claim 3 wherein said nozzle insert includes a first inwardly-tapered portion extending to said pilot fuel orifice, and a second outwardly-tapered portion downstream of said pilot fuel orifice, wherein said air exit openings are located in said second outwardly-tapered portion.

5. The liquid fuel cartridge assembly of claim 1 wherein said fuel injector tip is comprised of an outer sleeve, a concentrically-arranged inner sleeve and a concentrically-arranged center core; and
said pilot fuel passage and said air channels are formed in said concentrically-arranged center core;
wherein said annular main fuel passage is formed in a radial space between said concentrically-arranged inner sleeve and said concentrically-arranged center core.

6. The liquid fuel cartridge assembly of claim 5 wherein said concentrically-arranged inner sleeve is formed at an aft end with an annular flanged end, and wherein circumferentially-spaced main fuel orifices are in communication with said annular main fuel passage and are located on an upstream side of said annular flanged end.

7. The liquid fuel cartridge assembly of claim 3 wherein said air exit openings comprise at least one annular row of holes or an annular row of slots slanted in a circumferential direction.

8. The liquid fuel cartridge assembly of claim 4 wherein a swirler is located within said nozzle insert, upstream and adjacent of the first inwardly-tapered portion.

9. The liquid fuel cartridge assembly of claim 7 wherein the air exit openings comprise a radially inner row of holes and a radially outer row of slots, and further wherein the holes in said at least one annular row of holes and the slots in said radially outer row of slots are slanted in different directions.

10. A liquid fuel cartridge assembly for a combustor of a gas turbine comprising:
an elongated, hollow stem including an aft end;
a fuel injector tip mounted to the aft end of said elongated, hollow stem and extending axially beyond the elongated, hollow stem, wherein the fuel injector tip extends axially beyond the aft end of the elongated, hollow stem and the fuel injector tip is provided with a pilot fuel passage centered within said fuel injector tip along a longitudinal axis of said fuel injector tip and extending to a pilot fuel orifice;
air channels in the fuel injector tip, arranged around the pilot fuel passage and in communication with air exit openings at an aft end of the fuel injector tip;
an annular main fuel passage in the fuel injector tip, arranged around the air channels and in communication with fuel exit holes proximate the aft end of the fuel injector tip and radially outward of the air exit openings;
radially oriented air supply holes in the elongated, hollow stem upstream of the fuel injector tip in communication with the air channels; and
wherein said elongated, hollow stem encloses a first pilot fuel supply pipe in fluid communication with said pilot fuel passage and a second main fuel supply pipe in fluid communication with said annular main fuel passage, wherein the first pilot fuel supply pipe and the second main fuel supply pipe forms a double helix that extends axially through said elongated, hollow stem.

11. The liquid fuel cartridge assembly of claim 10 wherein a nozzle insert is located within said fuel injector tip and is provided with a said pilot fuel orifice, and said air exit holes.

12. The liquid fuel cartridge assembly of claim 11 wherein said nozzle insert comprises a first inwardly-tapered portion extending to said pilot fuel orifice and a second outwardly-tapered portion downstream of said pilot fuel orifice, wherein said air exit openings are in said second outwardly-tapered portion.

13. The liquid fuel cartridge assembly of claim 12 wherein the air exit openings comprise at least one radially inner, annular row of holes and a radially outer, annular row of slots, and further wherein holes in said at least one row of holes and/or slots in said annular row of slots are slanted in a circumferential direction.

14. The liquid fuel cartridge assembly of claim 12 wherein an annular air chamber is formed between said first inwardly-tapered portion and said second outwardly-slanted portion, externally of said nozzle insert.

15. A liquid fuel cartridge assembly for a combustor of a gas turbine comprising:
an elongated stem including an aft end, wherein the elongated stem encloses a main fuel pipe and a pilot fuel pipe;
a fuel injector tip at the aft end of said elongated stem and extending axially beyond the aft end, wherein the fuel injector tip includes a pilot fuel passage centered within said fuel injector tip along a longitudinal axis of said fuel injector tip;
air channels in the fuel injector tip and arranged around the pilot fuel passage;
an annular main fuel passage in the fuel injector tip and arranged around the air channels; and
radially oriented air supply holes in the elongated stem upstream, adjacent the fuel injector tip and in communication with the air channels;
wherein the fuel injector tip includes an outer sleeve, a concentrically-arranged inner sleeve and a concentrically-arranged center core;
said pilot fuel passage and said air channels are in said center core; and
said annular main fuel passage formed in a radial space between the concentrically-arranged inner sleeve and the concentrically-arranged center core,
wherein the pilot fuel passage and the annular main fuel passage forms a double helix that extends axially through the elongated stem.

16. The liquid fuel cartridge assembly of claim 15 wherein a nozzle insert is in the fuel injector tip, said nozzle insert is provided with said pilot fuel orifice and air exit openings in communication with said air channels, and a swirler upstream of said pilot fuel orifice.

17. The liquid fuel cartridge assembly of claim 16 wherein said nozzle insert includes a first inwardly-tapered portion extending to said pilot fuel orifice, and a second outwardly-tapered portion downstream of said pilot fuel orifice, wherein said air exit openings are in said second outwardly-tapered portion.

18. The liquid fuel cartridge assembly of claim 17 wherein said air exit openings comprise at least one radially inner annular row of holes and a radially outer annular row of slots, and further wherein t

Assignees

• Gen Electric

Inventors

• Ginessin Leonid Yulievich
• Shershnyov Borys Borysovich

Classifications

• F23R3/343

  Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion (ignition in gas-turbine plants F02C7/264; pilot flame igniters F23Q9/00) · CPC title

• F23R2900/00004

  Preventing formation of deposits on surfaces of gas turbine components, e.g. coke deposits · CPC title

• F23R3/283

  Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances · CPC title

• F23D11/107

  at least one of both being subjected to a swirling motion · CPC title

• F23R3/28

  characterised by the fuel supply (burners F23D) · CPC title