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System and method for supporting fuel nozzles in a gas turbine combustor utilizing a support plate

Imported: 24 Feb '17 | Published: 06 Jan '04

David J. Wiebe

USPTO - Utility Patents

Abstract

A system for supporting a plurality of fuel nozzles in a combustor includes a plurality of fuel nozzles coupled to a fuel nozzle support housing proximate an upstream end of each fuel nozzle, a plurality of swirler vanes rigidly coupled to respective fuel nozzles proximate an intermediate portion of the fuel nozzle, a plurality of shrouds rigidly coupled to respective swirler vanes, each shroud having an upstream end adjacent the intermediate portion of the fuel nozzle and a downstream end and a support plate rigidly coupled to the plurality of shrouds proximate an intermediate portion of each of the shrouds. The support plate has a perimeter approximately equal to an inside perimeter of combustor housing which allow the support plate to limit the movement and vibration of the fuel nozzles.

Description

Other technical advantages are readily apparent to one skilled in the art from the following figures, descriptions, and claims.

BRIEF DESCRIPTION OF THE DRAWINGS

For a more complete understanding of the invention, and for further features and advantages, reference is now made to the following description, taken in conjunction with the accompanying drawings, in which:

FIG. 1A is a cross-sectional side view, and FIG. 1B is a cross-sectional end view, of a system for supporting fuel nozzles in a gas turbine combustor according to one embodiment of the present invention;

FIG. 2A is a plan view, and FIG. 2B an edge cross-sectional view, of one embodiment of a support plate used in the system of FIGS. 1A and 1B;

FIG. 3 is a partial cross-sectional view of the system of FIG. 1A and 1B illustrating the system in more detail;

FIG. 4 is a partial cross-sectional view of the system of FIGS. 1A and 1B illustrating an additional embodiment of the system;

FIG. 5 is a partial cross-sectional view of the system of FIGS. 1A and 1B illustrating an additional embodiment of the system; and

FIG. 6A is a cross-sectional side view, and FIG. 6B is a cross-sectional end view, illustrating one embodiment of aligning a support plate with a combustor housing.

Claims

1. A support system for a fuel nozzle assembly, in a combustor having a combustor housing; a fuel nozzle support housing; a plurality of fuel nozzles coupled to the fuel nozzle support housing proximate an upstream end of each fuel nozzle; a plurality of swirler vanes, each swirler vane rigidly coupled to a respective fuel nozzle proximate an intermediate portion of the fuel nozzle; a plurality of shrouds, each shroud rigidly coupled to a respective swirler vane, each shroud having an upstream end adjacent the intermediate portion of the fuel nozzle and a downstream end, further comprising:

2. The system of claim 1, wherein the support plate has a plurality of generally circular holes formed therein and the fuel nozzles are positioned therethrough.

3. The system of claim 2, wherein each fuel nozzle is rigidly coupled to a fuel nozzle support housing with a fastener selected from the group consisting of a bolt and a weld, wherein the fuel nozzles, the swirler vanes, and the shrouds are formed integral with each other and the fuel nozzle support shrouds being rigidly attached to the support plate.

4. The system of claim 2, wherein the perimeter edge of the support plate includes a radial protuberance formed thereon, the radial protuberance operable to engage a depression on an inside of the housing of the combustor to align the support plate and fuel nozzles in the combustor housing.

5. The system of claim 1, wherein the support plate has an upstream side and a downstream side, the downstream side having a chamfer formed around the perimeter of the support plate.

6. A support system for a combustor for a turbine engine fuel nozzle assembly, the combustor having: a fuel nozzle support housing; a plurality of fuel nozzles coupled to the fuel nozzle support housing proximate an upstream end of each fuel nozzle; a plurality of swirler vanes, each swirler vane rigidly coupled to a respective fuel nozzle proximate an intermediate portion of the fuel nozzle; a plurality of circular fore shrouds, each fore shroud rigidly coupled to a respective swirler vane, each fore shroud having an upstream end adjacent the intermediate portion of the fuel nozzle and a downstream end; a plurality of circular aft shrouds, each aft shroud having an upstream end coupled to the downstream end of a respective fore shroud, each aft shroud having a downstream end; a combustor housing baseplate having a plurality of circular holes formed therein, the circular holes adapted to accept the downstream ends of the aft shrouds; a circular combustor housing coupled to the combustor housing baseplate; the support system comprising:

7. The system of claim 6, wherein each fuel nozzle is rigidly coupled to the fuel nozzle support housing;

8. The system of claim 6, wherein the fuel nozzles, the swirler vanes, and the fore shrouds are formed integral with each other, and the aft shrouds and the combustor housing baseplate are formed integral with each other, and the support plate is attached to flanges on the downstream ends of the plurality of fore shrouds and to flanges on the upstream ends of the plurality of aft shrouds.

9. The system of claim 6, wherein the support plate has an upstream side and a downstream side, the downstream side having a chamfer formed around the circumference of the support plate.

10. The system of claim 6, wherein the circumferential edge of the support plate includes a radial protuberance formed thereon operable to engage a depression formed on an inside of the combustor housing to align the fuel nozzles in the combustor housing.