Fuel injection for integral combustor and turbine vane

Patent metadata

Field	Value
Publication number	US-11788723-B2
Application number	US-202217854342-A
Country	US
Kind code	B2
Filing date	Jun 30, 2022
Priority date	Nov 26, 2019
Publication date	Oct 17, 2023
Grant date	Oct 17, 2023

Abstract

A system includes a combustor. The combustor has a combustor wall with a combustor dome at an upstream end of the combustor wall, and an outlet at a downstream end of the combustor wall opposite the upstream end. The combustor wall includes an inner wall portion and an outer wall portion defining an interior of the combustor therebetween. Each of the inner wall portion and outer wall portion extends from the combustor dome to the downstream end of the combustor wall. The combustor wall includes an air cooling passage embedded inside at least one of the inner wall portion and the outer wall portion. The air cooling passage extends from the upstream end of the combustor wall to the downstream end of the combustor wall.

First claim

What is claimed is:

1. A system comprising:
an annular combustor including a combustor wall with a combustor dome at an upstream end of the combustor wall, and an outlet at a downstream end of the combustor wall opposite the upstream end, wherein the combustor wall includes an inner wall portion and an outer wall portion defining a full annular interior of the combustor therebetween, each of the inner wall portion and outer wall portion extending from the combustor dome to the downstream end of the combustor wall, wherein the combustor wall includes an air cooling passage embedded inside at least one of the inner wall portion and the outer wall portion, extending from the upstream end of the combustor wall, to the downstream end of the combustor wall; and
a multipoint fuel injection system in the combustor dome, wherein the multipoint fuel injection system includes a plurality of fuel injectors with air passages extending through the combustor dome for communication of compressor discharge air through the combustor dome into the combustor for combustion, wherein the multipoint fuel injection system includes a fuel manifold in fluid communication with the fuel injectors for injecting fuel with the compressor discharge air for atomization of the fuel for combustion in the combustor, wherein the manifold, the combustor wall, and a turbine inlet stator vane are together a single monolithic construction.

2. The system as recited in claim 1 , further comprising the turbine inlet stator vane in the outlet of the combustor, wherein the air cooling passage has an outlet positioned downstream of the turbine inlet stator vane.

3. The system as recited in claim 1 , wherein the air cooling passage is one of a plurality of circumferentially spaced apart cooling passages through the combustor wall, wherein the plurality of circumferentially spaced apart cooling passages through the combustor wall are embedded in the inner wall portion of the combustor wall and in the outer wall portion of the combustor wall.

4. The system as recited in claim 3 , wherein each of the cooling passages has a respective inlet at the upstream end of the combustor wall and a respective outlet at the downstream end of the combustor wall, and does not include any other inlets or outlets.

5. The system as recited in claim 3 , wherein the cooling passages follow a helical pattern around the combustor wall.

6. The system as recited in claim 3 , further comprising an ignition boss defined in the combustor wall for passage of an ignitor though the combustor wall, wherein the cooling passages conform around the ignitor boss.

7. The system as recited in claim 1 , further comprising a plurality of circumferentially spaced apart turbine inlet stator vanes in the outlet of the combustor.

8. The system as recited in claim 1 , wherein the manifold is a multistage manifold with a plurality of fluidly isolated fuel circuits defined therein for staging flow to the injectors.

9. The system as recited in claim 1 , wherein the manifold is mounted to a cowl extending upstream of the combustor dome.

10. The system as recited in claim 1 , further comprising a high pressure engine case, wherein the manifold, the combustor dome, the combustor wall, and the turbine inlet stator vane are all within the high pressure engine case.

11. The system as recited in claim 10 , wherein the high pressure engine case includes an inlet for supplying compressor discharge air, and wherein the combustor wall is spaced apart from both an inner case wall of the high pressure engine case radially inward from the combustor wall, and a radially outer case wall of the high pressure engine case radially outward from the combustor wall.

12. The system as recited in claim 11 , wherein the combustor wall defines integral internal fins for conducting heat from an inner surface of the combustor wall to an outer surface of the combustor wall for heat transfer from the combustor wall to a space between the combustor wall and the radially inner and outer case walls.

13. A system comprising:
an annular combustor including a combustor wall with a combustor dome at an upstream end of the combustor wall, and an outlet at a downstream end of the combustor wall opposite the upstream end, wherein the combustor wall includes an inner wall portion and an outer wall portion defining a full annular interior of the combustor therebetween, each of the inner wall portion and outer wall portion extending from the combustor dome to the downstream end of the combustor wall, wherein the combustor wall includes an air cooling passage embedded inside at least one of the inner wall portion and the outer wall portion, extending from the upstream end of the combustor wall, to the downstream end of the combustor wall; and
a multipoint fuel injection system in the combustor dome, wherein the multipoint fuel injection system includes a plurality of fuel injectors with air passages extending through the combustor dome for communication of compressor discharge air through the combustor dome into the combustor for combustion, wherein the multipoint fuel injection system includes a fuel manifold in fluid communication with the fuel injectors for injecting fuel with the compressor discharge air for atomization of the fuel for combustion in the combustor, further comprising a high pressure engine case, wherein the manifold, the combustor dome, the combustor wall, and a turbine inlet stator vane are all within the high pressure engine case.

14. The system as recited in claim 13 , wherein the high pressure engine case includes an inlet for supplying compressor discharge air, and wherein the combustor wall is spaced apart from both an inner case wall of the high pressure engine case radially inward from the combustor wall, and a radially outer case wall of the high pressure engine case radially outward from the combustor wall.

15. The system as recited in claim 14 , wherein the combustor wall defines integral internal fins for conducting heat from an inner surface of the combustor wall to an outer surface of the combustor wall for heat transfer from the combustor wall to a space between the combustor wall and the radially inner and outer case walls.

Assignees

• Collins Engine Nozzles Inc

Inventors

• Prociw Lev A
• Ryon Jason

Classifications

• F23R3/002 Primary

  Wall structures (F23R3/02 and F23R3/007 take precedence) · CPC title

• F23R3/005 Primary

  Combined with pressure or heat exchangers · CPC title

• F02C7/12

  Cooling of plants (of component parts, see the relevant subclasses, e.g. F01D; cooling of engines in general F01P) · CPC title

• F02C7/222

  Fuel flow conduits, e.g. manifolds · CPC title

• F05D2260/204

  by the use of microcircuits · CPC title