Micromixing cap assembly

Patent metadata

Field	Value
Publication number	US-9534787-B2
Application number	US-201313797925-A
Country	US
Kind code	B2
Filing date	Mar 12, 2013
Priority date	Mar 12, 2013
Publication date	Jan 3, 2017
Grant date	Jan 3, 2017

Abstract

A system includes a combustor cap assembly for a multi-tube fuel nozzle. The combustor cap assembly includes a support structure defining an interior volume configured to receive an air flow, a plurality of mixing tubes disposed within the interior volume, wherein each of the plurality of mixing tubes comprises a respective fuel injector and is individually removable from the combustor cap assembly, an air distributor disposed within the interior volume and configured to distribute the air flow received by the interior volume to each of the plurality of mixing tubes, and a combustor cap removably coupled to the support structure.

First claim

The invention claimed is:

1. A system, comprising:
A combustor cap assembly for a multi fuel nozzle, comprising:
a support structure defining an interior volume configured to receive an air flow;
a plurality of mixing tubes disposed within the interior volume, wherein each of the plurality of mixing tubes comprises a respective fuel injector and is individually removable from the combustor cap assembly;
an air distributor disposed within the interior volume, wherein the air distributor is configured to distribute the air flow received by the interior volume to each of the plurality of mixing tubes, wherein the air distributor comprises a plate comprising a plurality of air passages; and
the air distributor is disposed at angle within the interior volume relative to an axis of each mixing tube of the plurality of mixing tubes; and
a combustor cap face removably coupled to the support structure.

2. The system of claim 1 , wherein the combustor cap face is removably coupled to the support structure with a radial spring.

3. The system of claim 1 , wherein the air distributor comprises a plurality of apertures, wherein each of the plurality of mixing tubes extends through one of the plurality of apertures, and each of the plurality of mixing tubes is individually removable from the air distributor.

4. The system of claim 3 , wherein at least one of the plurality of apertures comprises a radial spring that supports one of the plurality of mixing tubes.

5. The system of claim 3 , wherein at least one of the plurality of apertures comprises a venturi contour.

6. The system of claim 3 , wherein the air distributor comprises a plate coupled to the support structure.

7. The system of claim 1 , comprising a retainer plate disposed within the interior volume and removably coupled to the support structure, wherein the retainer plate is configured to at least partially support the plurality of mixing tubes.

8. The system of claim 1 , wherein the air distributor comprises a wire mesh.

9. The system of claim 1 , wherein the support structure is disposed within a combustion liner.

10. A combustor cap assembly for a multi-tube fuel nozzle, comprising:
a support structure defining an interior volume configured to receive an air flow; and
an air distributor plate, comprising:
a plurality of apertures, wherein each of the plurality of apertures is configured to receive one of a plurality of mixing tubes; and
a plurality of air passages configured to distribute the air flow to the plurality of mixing tubes, wherein the air distributor plate is disposed at an angle within the interior volume relative to an axis of each of the plurality of mixing tubes.

11. The combustor cap assembly of claim 10 , wherein each of the plurality of air passages has a common size and shape.

12. The combustor cap assembly of claim 10 , wherein at least one of the plurality of air passages extends along at least three of the plurality of apertures.

13. The combustor cap assembly of claim 10 , wherein the air distributor plate comprises a multi-piece configuration.

14. The combustor cap assembly of claim 10 , wherein at least one of the plurality of air passages comprises a contour configured to reduce a pressure drop across the air distributor plate.

15. A system, comprising:
a combustor cap assembly for a multi-tube fuel nozzle, comprising:
a support structure defining an interior volume, wherein the interior volume is configured to receive an air flow;
a plurality of mixing tubes disposed within the interior volume, wherein each of the plurality of mixing tubes is configured to receive the air flow from the interior volume, and each of the plurality of mixing tubes is individually removable from the combustor cap assembly;
a plurality of fuel injectors, wherein each of the plurality of fuel injectors is at least partially disposed within a respective one of the plurality of mixing tubes and is configured to inject a fuel flow into the respective one of the mixing tubes;
an air distributor disposed within the interior volume, wherein the air distributor comprises a plurality of air passages configured to distribute the air flow within the interior volume to the plurality of mixing tubes, and the air distributor comprises a plate disposed at an angle within the interior volume relative to an axis of each mixing tube of the plurality of mixing tubes; and
a combustor cap face removably coupled to the support structure.

16. The system of claim 15 , wherein the plurality of mixing tubes is at least partially supported within the interior volume by the air distributor, and each of the plurality of mixing tubes is individually removable from the air distributor.

17. The system of claim 15 , wherien the combustor cap face is coupled to the support structure with a radial spring.

Assignees

• Gen Electric

Inventors

• Westmoreland James Harold
• Boardman Gregory Allen
• Melton Patrick Benedict

Classifications

• Y02T50/675

  Cross-Sectional Technologies · mapped topic

• F23R3/10

  for primary air (F23R3/06, F23R3/045 take precedence) · CPC title

• F23R3/286 Primary

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

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title