Volute trapped vortex combustor assembly

Patent metadata

Field	Value
Publication number	US-11906168-B2
Application number	US-202117198150-A
Country	US
Kind code	B2
Filing date	Mar 10, 2021
Priority date	Oct 25, 2017
Publication date	Feb 20, 2024
Grant date	Feb 20, 2024

Abstract

A combustor assembly is generally provided. The combustor assembly includes a volute wall extended annularly around a combustor centerline. The volute wall is extended at least partially as a spiral curve from a circumferential reference line around the combustor centerline. The volute wall defines a combustion chamber therewithin. An annular inner wall is extended at least partially along a lengthwise direction from the volute wall. An annular outer wall is extended at least partially along the lengthwise direction from the volute wall. The inner wall and the outer wall are each separated along a radial direction from the combustor centerline. A primary flow passage is defined between the inner wall and the outer wall in fluid communication from the combustion chamber.

First claim

What is claimed is:

1. A combustor assembly, the combustor assembly comprising:
a volute wall extended annularly around a combustor centerline, and wherein the volute wall is extended at least partially as a spiral curve from a circumferential reference line around the combustor centerline such that a portion of the volute wall curves from a first radially outer location to a first radially inward location, the first radially inward location located forward of the first radially outer location, and wherein the volute wall defines an annular volute combustion chamber therewithin;
an annular inner wall extended at least partially along a lengthwise direction from the volute wall;
an annular outer wall extended at least partially along the lengthwise direction from the volute wall, wherein the annular inner wall and the annular outer wall are separated along a radial direction from the combustor centerline and a portion of the annular outer wall curves from a second radially outer location to a second radially inward location, the second radially inward location located forward of the second radially outer location, and wherein a primary flow passage is defined between the annular inner wall and the annular outer wall in fluid communication with the annular volute combustion chamber, the annular volute combustion chamber being radially outward of the primary flow passage relative to the combustor centerline;
at least one secondary flow passage defined by the portion of the volute wall and the portion of the annular outer wall, the at least one secondary flow passage having:
a secondary inlet opening defined through the annular outer wall at the second radially outer location of the annular outer wall and at the first radially outer location of the portion of the volute wall; and
a secondary outlet opening adjacent to and in fluid communication with the annular volute combustion chamber, the secondary outlet opening defined by the first radially inward location of the portion of the volute wall and the second radially inward location of the portion of the annular outer wall, the secondary outlet opening located axially forward of and radially inward of the secondary inlet opening such that a flow of fluid is introduced into the annular volute combustion chamber in a direction that is radially inward and forward of the annular volute combustion chamber,

wherein the volute wall extends from a first location disposed at the secondary outlet opening to a second location disposed at the annular inner wall.

2. The combustor assembly of claim 1 , wherein the at least one secondary flow passage curves radially inward toward the combustor centerline from the secondary inlet opening.

3. The combustor assembly of claim 1 , wherein the at least one secondary flow passage defines a decreasing cross-sectional area from the secondary inlet opening to the secondary outlet opening.

4. The combustor assembly of claim 3 , wherein the decreasing cross-sectional area defines a nozzle configured to accelerate a flow of fluid through the at least one secondary flow passage to the annular volute combustion chamber.

5. The combustor assembly of claim 1 , wherein the volute wall extends as the spiral curve to the secondary outlet opening.

6. The combustor assembly of claim 1 , wherein the secondary outlet opening opens into and is in fluid communication with the annular volute combustion chamber defined within the volute wall.

7. The combustor assembly of claim 1 , wherein the secondary outlet opening is in fluid communication with the at least one secondary flow passage and the primary flow passage.

8. The combustor assembly of claim 1 , further comprising a tertiary opening defined through the annular outer wall adjacent to the primary flow passage; and a tertiary fuel injector extended at least partially through the tertiary opening at the annular outer wall.

9. The combustor assembly of claim 1 , wherein the volute wall extends from a first radius disposed approximately at the secondary outlet opening to a second radius disposed approximately at the annular inner wall, and wherein the first radius is greater than the second radius.

10. The combustor assembly of claim 1 , wherein the secondary outlet opening is tangential to the volute wall and the combustor centerline.

11. The combustor assembly of claim 1 , wherein the at least one secondary flow passage curves from the secondary inlet opening toward the circumferential reference line.

12. The combustor assembly of claim 1 , wherein the at least one secondary flow passage is extended at least partially annularly relative to the combustor centerline.

13. The combustor assembly of claim 1 , the at least one secondary flow passage comprising two or more discrete secondary flow passages in adjacent circumferential arrangement around the combustor centerline.

14. The combustor assembly of claim 1 , further comprising a primary fuel injector, wherein the volute wall defines one or more fuel injection openings through which the primary fuel injector is extended at least partially into the annular volute combustion chamber and a secondary fuel injector extended at least partially into the secondary flow passage through the secondary inlet opening.

15. The combustor assembly of claim 1 , wherein the at least one secondary flow passage is configured to provide a flow of an oxidizer to the annular volute combustion chamber to drive a trapped vortex in a primary combustion zone of the annular volute combustion chamber.

16. The combustor assembly of claim 1 , wherein the annular volute combustion chamber is at least partially partitioned from the primary flow passage via the portion of the volute wall and the portion of the annular outer wall that both define the at least one secondary flow passage.

17. The combustor assembly of claim 1 , wherein the volute wall defines one or more volute wall openings therethrough in fluid communication with the annular volute combustion chamber.

18. The combustor assembly of claim 17 , wherein the volute wall defines a volute wall passage extended to the one or more volute wall openings, the volute wall passage extended from a pressure plenum surrounding the volute wall, the annular inner wall, and the annular outer wall.

19. The combustor assembly of claim 1 , further comprising a second inner wall disposed inward of the annular inner wall along the radial direction, wherein the second inner wall is extended at least partially along the lengthwise direction, and wherein an inner cooling flow passage is defined therebetween; and
a second outer wall disposed outward of the annular outer wall along the radial direction, wherein the second outer wall is extended at least partially along the lengthwise direction, and wherein an outer cooling flow passage is defined therebetween.

Assignees

• Gen Electric

Inventors

• Boardman Gregory Allen
• Naik Pradeep
• Zelina Joseph
• Cooper Clayton Stuart

Classifications

• F23R3/286 Primary

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

• F02C3/14

  characterised by the arrangement of the combustion chamber in the plant (combustion chambers per se F23R; F02C3/205 takes precedence) · CPC title

• F23R3/346

  for staged combustion · CPC title

• F23R3/42 Primary

  characterised by the arrangement or form of the flame tubes or combustion chambers · CPC title

• F23R3/58

  Cyclone or vortex type combustion chambers · CPC title