Mesh cooled conduit for conveying combustion gases

Patent metadata

Field	Value
Publication number	US-8959886-B2
Application number	US-83212410-A
Country	US
Kind code	B2
Filing date	Jul 8, 2010
Priority date	Jul 8, 2010
Publication date	Feb 24, 2015
Grant date	Feb 24, 2015

Abstract

A conduit through which hot combustion gases pass in a gas turbine engine. The conduit includes a wall structure having an inner surface, an outer surface, a region, an inlet, and an outlet. The inner surface defines an inner volume of the conduit. The region extends between the inner and outer surfaces and includes cooling fluid structure defining a plurality of cooling passageways. The inlet extends inwardly from the outer surface and provides fluid communication between the inlet and the passageways. The outlet extends from the passageways to the inner surface to provide fluid communication between the passageways and the inner volume. At least one first cooling passageway intersects with at least one second cooling passageway such that cooling fluid flowing through the first cooling passageway interacts with cooling fluid flowing through the second cooling passageway.

First claim

What is claimed is:

1. A conduit through which hot combustion gases pass in a can-annular gas turbine engine, the conduit comprising:
a wall structure having a central axis, said wall structure second instance being one of a liner and transition duct between a combustion section and a turbine section in the can-annular gas turbine, the wall structure comprising:
an inner surface defining an inner volume of the conduit;
an outer boundary defining an outermost surface of the conduit;
a region extending between said inner and outermost surfaces, said region comprising cooling fluid structure defining a plurality of cooling passageways;
an inlet extending inwardly from said outermost surface to said passageways to allow cooling fluid to pass through said inlet and enter said passageways, wherein said inlet includes a circumferential groove extending about substantially an entire circumference of said outermost surface and extending radially inwardly continuously through said outermost surface to said region, said circumferential groove extending in a direction oriented transverse to said central axis for receiving said cooling fluid in the direction oriented transverse to said central axis; and
an outlet extending from said passageways to said inner surface to allow cooling fluid to exit said passageways and enter said inner volume; and

wherein at least one first cooling passageway intersects with at least one second cooling passageway such that cooling fluid flowing through said first cooling passageway interacts with cooling fluid flowing through said second cooling passageway, and wherein said cooling fluid flows through said cooling passageways having a component of the flow in a direction parallel to said central axis.

2. The conduit according to claim 1 , wherein said outlet comprises at least one exit passage formed in said wall structure and extending at an angle such that the cooling fluid passing into the inner volume of the conduit through said at least one exit passage includes an axial component of a velocity vector in the same direction as the direction of flow of the hot combustion gases passing through the conduit.

3. The conduit according to claim 2 , wherein said outlet further comprises an exit manifold formed in said wall structure and in communication with said passageways in said region and said at least one exit passage.

4. The conduit according to claim 1 , wherein said cooling fluid structure defines a mesh arrangement of cooling passageways, wherein each of two or more of said cooling passageways intersects with a plurality of other ones of said cooling passageways such that the cooling fluid flowing through each of said two or more cooling passageways interacts with cooling fluid flowing through said other ones of said cooling passageways, causing turbulent air flows and pressure drops in said passageways.

5. The conduit according to claim 1 , wherein said inlet is located axially upstream from said outlet such that the cooling fluid flowing through said cooling passageways flows axially downstream from said inlet to said outlet.

6. The conduit according to claim 1 , wherein said circumferential groove is in fluid communication with at least two of said cooling passageways defined by said cooling fluid structure.

7. The conduit according to claim 1 , wherein said plurality of cooling passageways are defined by a plurality of diamond-shaped nodes.

8. The conduit according to claim 1 , wherein said outlet comprises an annular manifold formed in said wall structure, said annular manifold in fluid communication with each of said cooling passageways defined by said cooling fluid structure.

9. The conduit according to claim 8 , wherein said outlet further comprises a plurality of passages formed in said wall structure, each said passage in fluid communication with said annular manifold.

10. A conduit through which hot combustion gases pass in a can-annular gas turbine engine, the conduit comprising:
a wall structure having a central axis, said wall structure second instance being one of a liner and transition duct between a combustion section and a turbine section in the can-annular gas turbine, the wall structure comprising:
an inner surface defining an inner volume of the conduit;
an outer boundary defining an outermost surface of the conduit;
a region extending between said inner and outermost surfaces, said region comprising cooling fluid structure defining a plurality of cooling passageways;
an inlet extending inwardly from said outermost surface to said passageways to allow cooling fluid to pass through said inlet and enter said passageways, wherein said inlet includes a circumferential groove extending about substantially an entire circumference of said outermost surface and extending radially inwardly continuously through said outermost surface to said region, said circumferential groove extending in a direction oriented transverse to said central axis for receiving said cooling fluid in the direction oriented transverse to said central axis; and
an outlet extending from said passageways to said inner surface to allow cooling fluid to exit said passageways and enter said inner volume; and
wherein said cooling fluid structure defines a mesh arrangement of cooling passageways, wherein each of two or more of said cooling passageways intersects with a plurality of other ones of said cooling passageways such that the cooling fluid flowing through each of said two or more cooling passageways interacts with cooling fluid flowing through said other ones of said cooling passageways, and wherein said cooling fluid flows through said cooling passageways having a component of the flow in a direction parallel to said central axis.

11. The conduit according to claim 10 , wherein said outlet comprises at least one exit passage formed in said wall structure and extending at an angle such that the cooling fluid passing into the inner volume of the conduit through said at least one exit passage includes an axial component of a velocity vector in the same direction as the direction of flow of the hot combustion gases passing through the conduit.

12. The conduit according to claim 11 , wherein said outlet further comprises an exit manifold formed in said wall structure and in communication with said passageways in said region and said at least one exit passage.

13. The conduit according to claim 10 , wherein said circumferential groove is in fluid communication with each of said cooling passageways defined by said cooling fluid structure.

14. The conduit according to claim 10 , wherein said plurality of cooling passageways are defined by a plurality of diamond-shaped nodes.

15. A conduit through which hot combustion gases pass in a can-annular gas turbine engine, the conduit comprising:
a wall structure having a central axis, said wall structure second instance being one of a liner and transition duct between a combustion section and a turbine section in the can-annular gas turbine, the wall structure comprising:
an inner surface defining an inner volume of the conduit;
an outer boundary defining an outermost surface of the conduit;
a region extending between said inner and outermost surfaces, said region comprising cooling fluid structure defining a plurality of cooling passageways;
an inlet extending inwardly from said outermost surface to said passageways to allow cooling fluid to pass through said inlet and enter said passageways, wherein said inlet includes a circumferential groove extending about substantially an entire circumference of said outermost surface and extending radially inwardly continuo

Assignees

• Lee Ching-Pang
• Zuniga Humberto A
• Morrison Jay A
• Siemens Energy Inc
• Mikro Systems Inc

Inventors

• Lee Ching-Pang
• Zuniga Humberto A
• Morrison Jay A

Classifications

• F23R2900/03042

  Film cooled combustion chamber walls or domes · CPC title

• F23R2900/03045

  Convection cooled combustion chamber walls provided with turbolators or means for creating turbulences to increase cooling · CPC title

• F23R3/06

  Arrangement of apertures along the flame tube · CPC title

• F01D9/023

  Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings · CPC title

• F23R3/005 Primary

  Combined with pressure or heat exchangers · CPC title