Radial flow fuel nozzle for a combustor of a gas turbine

Patent metadata

Field	Value
Publication number	US-9383098-B2
Application number	US-201213664705-A
Country	US
Kind code	B2
Filing date	Oct 31, 2012
Priority date	Oct 31, 2012
Publication date	Jul 5, 2016
Grant date	Jul 5, 2016

Abstract

A combustor for a gas turbine generally includes a radial flow fuel nozzle having a fuel distribution manifold, and a fuel injection manifold axially separated from the fuel distribution manifold. The fuel injection manifold generally includes an inner side portion, an outer side portion, and a plurality of circumferentially spaced fuel ports that extend through the outer side portion. A plurality of tubes provides axial separation between the fuel distribution manifold and the fuel injection manifold. Each tube defines a fluid communication path between the fuel distribution manifold and the fuel injection manifold.

First claim

What is claimed is:

1. A radial flow fuel nozzle for a combustor of a gas turbine, comprising:
a. a fuel distribution manifold shaped as a ring and having a bottom side wall axially spaced from a top side wall, wherein the bottom side wall defines at least one inlet that provides for fuel flow into the fuel distribution manifold and the to side wall defines a plurality of outlets circumferentially spaced about the top side wall;
b. a fuel injection manifold shaped as a ring and axially separated from and coaxially aligned with the fuel distribution manifold, the fuel injection manifold having an inner side portion radially spaced from an outer side portion, a bottom side portion axially spaced from a top side portion and perpendicular to the outer side portion and a plurality of circumferentially spaced fuel ports that extend through the outer side portion, wherein the bottom side portion defines a plurality of inlets circumferentially spaced about the bottom side portion; and
c. a plurality of circumferentially spaced tubes that extend axially from the top side wall of the fuel distribution manifold to the bottom side portion of the injection manifold, wherein the plurality of circumferentially spaced tubes is annularly arranged about an axial centerline of the radial flow fuel nozzle, each tube of the plurality of circumferentially spaced tubes defining a respective fluid communication path between a respective outlet of the plurality of outlets of the fuel distribution manifold and a respective inlet of the plurality of inlets of the fuel injection manifold.

2. The radial flow fuel nozzle as in claim 1 , further comprising a plurality of atomizers, wherein each atomizer is disposed within a respective fuel port of the plurality of circumferentially spaced fuel ports of the fuel injection manifold.

3. The radial flow fuel nozzle as in claim 1 , further comprising an inner shroud at least partially surrounded by the inner side portion of the fuel injection manifold.

4. The radial flow fuel nozzle as in claim 1 , further comprising an outer shroud that circumferentially surrounds the fuel injection manifold, the outer shroud having a downstream end, the outer shroud defining a plurality of circumferentially spaced passages that extend radially through the outer shroud, each passage being aligned with a respective fuel port of the plurality of circumferentially spaced fuel ports of the fuel injection manifold.

5. The radial flow fuel nozzle as in claim 4 , wherein a radial gap is defined between an inner surface of the outer shroud and the outer side portion of the fuel injection manifold.

6. The radial flow fuel nozzle as in claim 4 , further comprising an impingement plate adjacent to the downstream end of the outer shroud.

7. The radial flow fuel nozzle as in claim 4 , further comprising a cap plate adjacent to the downstream end of the outer shroud.

8. The radial flow fuel nozzle as in claim 4 , further comprising an alignment pin that extends between the fuel injection manifold and the outer shroud.

9. A combustor for a gas turbine, comprising:
a. an end cover having an outer side axially separated from an inner side;
b. a center fuel nozzle that extends axially away from the inner side of the end cover; and
c. a radial flow fuel nozzle that at least partially surrounds the center fuel nozzle, the radial flow fuel nozzle comprising:
i. a fuel distribution manifold shaped as a ring and having a bottom side wall axially spaced from a topside wall, wherein the bottom side wall defines at least one inlet that provides for fuel flow into the fuel distribution manifold and the top side wall defines a plurality of outlet circumferentially spaced about the top side wall;
ii. a fuel injection manifold coaxially aligned with and axially spaced downstream from the fuel distribution manifold, the fuel injection manifold being shaped as a ring having a plurality of circumferentially spaced fuel ports that extend radially through an outer side portion of the fuel injection manifold, wherein a bottom side portion of the fuel injection manifold is perpendicular to the outer side portion and defines a plurality of inlets circumferentially spaced about the bottom side portion; and
iii. a plurality of circumferentially spaced tubes that extend between the fuel distribution manifold and the fuel injection manifold, wherein the plurality of circumferentially spaced tubes is annularly arranged about an axial centerline of the radial flow fuel nozzle, each tubes of the plurality of circumferentially spaced tubes defining a respective fluid communication path between a respective outlet of the plurality of outlets of the fuel distribution manifold and a respective inlet of the plurality of inlets of the fuel injection manifold.

10. The combustor as in claim 9 , wherein the radial flow fuel nozzle further comprises a plurality of atomizers, each atomizer being disposed within a respective one fuel port of the plurality of circumferentially spaced fuel ports of the fuel injection manifold.

11. The combustor as in claim 9 , further comprising a flexible conduit in fluid communication with the fuel distribution manifold, wherein the flexible conduit is in fluid communication with a liquid fuel supply.

12. The combustor as in claim 9 , wherein the radial flow fuel nozzle further comprises an outer shroud that circumferentially surrounds the fuel injection manifold, the outer shroud having a downstream end, the outer shroud defining a plurality of circumferentially spaced passages that extend radially through the outer shroud, each passage being aligned with a respective fuel ports of the plurality of circumferentially spaced fuel ports of the fuel injection manifold.

13. The combustor as in claim 12 , wherein the radial flow fuel nozzle further comprises an annular impingement plate adjacent to the downstream end of the outer shroud.

14. The combustor as in claim 12 , wherein the radial flow fuel nozzle further comprises an annular cap plate adjacent to the downstream end of the outer shroud.

15. The combustor as in claim 12 , wherein the radial flow fuel nozzle further comprises an inner shroud at least partially surrounded by the inner side portion of the fuel injection manifold.

16. The combustor as in claim 15 , wherein the radial flow fuel nozzle further comprises an alignment pin that extends between the fuel injection manifold and at least one of the inner shroud or the outer shroud.

17. A combustor for a gas turbine, comprising:
a, an annular array of tube bundles that extends radially across at least a portion of the combustor, each tube bundle having a respective downstream plate and a respective plurality of tubes that extend through the downstream plate;
b. a fuel nozzle passage that extends axially through the annular array of tube bundles; and
c. a radial flow fuel nozzle that extends axially through the fuel nozzle passage, the radial flow fuel nozzle comprising:
i. a fuel distribution manifold;
ii. a fuel injection manifold downstream from the fuel distribution manifold, the fuel injection manifold having an inner side portion, an outer side portion, and a plurality of circumferentially spaced fuel ports that extend through the outer side portion;
iii. a plurality of tubes that extends between the fuel distribution manifold and the fuel injection manifold, each tube defining a fluid communication path between the fuel distribution manifold and the fuel injection manifold; and
iv. an outer shroud that circumferentially surrounds the fuel injection manifold, the outer shroud defining a

Assignees

• Gen Electric

Inventors

• Means Gregory Scott
• Boardman Gregory Allen
• Berry Jonathan Dwight

Classifications

• F23R2900/00012

  Details of sealing devices · CPC title

• F23D14/00

  Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid · CPC title

• F23R3/46

  Combustion chambers comprising an annular arrangement of {several essentially tubular} flame tubes within a common annular casing or within individual casings · CPC title

• F23D2900/00015

  Pilot burners specially adapted for low load or transient conditions, e.g. for increasing stability · 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