Premix fuel nozzle assembly

Patent metadata

Field	Value
Publication number	US-2016146459-A1
Application number	US-201414555074-A
Country	US
Kind code	A1
Filing date	Nov 26, 2014
Priority date	Nov 26, 2014
Publication date	May 26, 2016
Grant date	—

Abstract

A premix fuel nozzle assembly includes a center body including a sleeve having an inner surface and a pilot premix fuel nozzle assembly that extends axially through the center body within the sleeve and defines a pilot air passage within the center body. The pilot premix fuel nozzle assembly includes a premix tip having a plurality of premix tubes that define premix passages in fluid communication with the pilot air passage. At least one of the premix tubes includes a fuel port. The premix fuel nozzle assembly further includes a pilot fuel flow path that is defined radially between the pilot premix fuel nozzle assembly and the inner surface of the sleeve and a fuel plenum that is at least partially defined between the sleeve inner surface and an outer surface of the premix tip. The fuel ports provide for fluid communication between the fuel plenum and the premix passages.

First claim

What is claimed is:

1 . A premix fuel nozzle assembly, comprising;
a center body at least partially defined by a sleeve having an inner surface; a pilot premix fuel nozzle assembly that extends axially through the center body within the sleeve and defines a pilot air passage within the center body, the pilot premix fuel nozzle assembly including a premix tip having a plurality of premix tubes, each premix tube defining a premix passage and a fuel port, wherein the premix passage is in fluid communication with the pilot air passage; a pilot fuel flow path defined radially between the pilot premix fuel nozzle assembly and the inner surface of the sleeve of the center body; and a fuel plenum at least partially defined between the sleeve inner surface and an outer surface of the premix tip, wherein the fuel ports provide for fluid communication between the fuel plenum and the premix passages.

2 . The premix fuel nozzle assembly as in claim 1 , wherein the pilot fuel flow path extends axially between an inlet passage and the fuel plenum.

3 . The premix fuel nozzle assembly as in claim 1 , wherein the premix fuel nozzle is a dual fuel premix fuel nozzle.

4 . The premix fuel nozzle assembly as in claim 1 , wherein the pilot premix fuel nozzle assembly includes a stem, a coupling collar, a bellows and a flow expansion collar connected in sequence upstream from the premix tip.

5 . The premix fuel nozzle assembly as in claim 4 , further comprising a liner that circumferentially surrounds the bellows.

6 . The premix fuel nozzle assembly as in claim 5 , wherein the bellows and the liner at least partially defined a plenum therebetween.

7 . The premix fuel nozzle assembly as in claim 1 , wherein the plurality of premix tubes is annularly arranged around the outer surface of the premix tip within the fuel plenum.

8 . The premix fuel nozzle assembly as in claim 1 , wherein each premix tube of the plurality of premix tubes extends radially outwardly from the outer surface of the premix tip within the fuel plenum.

9 . The premix fuel nozzle assembly as in claim 1 , wherein the pilot premix fuel nozzle assembly includes one or more radial offset features which extend radially outwardly from one or more outer surfaces of the pilot premix fuel nozzle assembly within the premix fuel flow path.

10 . A combustor comprising:
an end cover; a plurality of premix fuel nozzle assemblies annularly arranged about a center fuel nozzle, each premix fuel nozzle assembly of the plurality of premix fuel nozzle assemblies and the center fuel nozzle being fixedly connected to the end cover, each of the premix fuel nozzle assemblies being a dual fuel type premix fuel nozzle assembly, wherein each premix fuel nozzle assembly comprises;
a center body at least partially defined by a sleeve having an inner surface;
a pilot premix fuel nozzle assembly that extends axially through the center body within the sleeve and defines a pilot air passage within the center body, the pilot premix fuel nozzle assembly including a premix tip having a plurality of premix tubes, each premix tube having an inlet end, and outlet end and a premix passage defined therebetween, each premix tube having a fuel port, wherein the inlet end of the premix tube is in fluid communication with the pilot air passage;
a pilot fuel flow path defined radially between the pilot premix fuel nozzle assembly and the inner surface of the sleeve of the center body; and
a fuel plenum at least partially defined between the sleeve inner surface and an outer surface of the premix tip, wherein the fuel ports provide for fluid communication between the fuel plenum and the premix passages.

11 . The combustor as in claim 10 , wherein the pilot fuel flow path extends axially between an inlet passage and the fuel plenum.

12 . The combustor as in claim 10 , wherein the premix fuel nozzle assembly is a dual fuel premix fuel nozzle.

13 . The combustor as in claim 10 , wherein the pilot premix fuel nozzle assembly includes a stem, a coupling collar, a bellows and a flow expansion collar connected in sequence upstream from the premix tip.

14 . The combustor as in claim 13 , wherein the pilot premix fuel nozzle assembly further comprises a liner that circumferentially surrounds the bellows.

15 . The combustor as in claim 14 , wherein the bellows and the liner at least partially defined a plenum therebetween.

16 . The combustor as in claim 10 , wherein the plurality of premix tubes of the pilot premix fuel nozzle assembly is annularly arranged around the outer surface of the premix tip within the fuel plenum.

17 . The combustor as in claim 10 , wherein each premix tube of the plurality of premix tubes extends radially outwardly from the outer surface of the premix tip within the fuel plenum.

18 . The combustor as in claim 10 , wherein the pilot premix fuel nozzle assembly includes one or more radial offset features which extend radially outwardly from one or more outer surfaces of the pilot premix fuel nozzle assembly within the premix fuel flow path.

19 . The combustor as in claim 10 , wherein the combustor is a component of a gas turbine.

20 . The combustor as in claim 10 , wherein the outlet ends of the premix tubes of the plurality of premix tubes is annularly arranged about a fuel distribution disk portion of the premix tip.

Assignees

• Gen Electric

Inventors

• Gibson Michael Christopher
• Ouellet Dereck Joseph

Classifications

• F23D2900/14003

  with more than one nozzle · CPC title

• F23D2900/00017

  Assembled burner modules · CPC title

• F23R3/286

  having fuel-air premixing devices (F23R3/30 takes precedence) · CPC title

• F23D14/08

  with axial outlets at the burner head · CPC title

• 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