Cooled turbine guide vane or blade for a turbomachine

Patent metadata

Field	Value
Publication number	US-9896942-B2
Application number	US-201214352106-A
Country	US
Kind code	B2
Filing date	Oct 2, 2012
Priority date	Oct 20, 2011
Publication date	Feb 20, 2018
Grant date	Feb 20, 2018

Abstract

A turbine airfoil has a suction side wall and a pressure side wall of an airfoil cavity, through which a cooling fluid flows for cooling of the side walls. The suction side wall has one or more protrusions extending therefrom into the airfoil cavity. The protrusions are arranged such that: a number of the one or more protrusions on the suction side wall is higher than a number of protrusions on the pressure side wall; and/or a protrusion density on the suction side wall is higher than a protrusion density on the pressure side wall, and/or a total protrusion surface area on the suction side wall is larger than a total protrusion surface area on the pressure side wall, so that the heat transfer from the suction side wall to the cooling fluid is higher compared to that of the pressure side wall during operation of the turbomachine.

First claim

What is claimed is:

1. A turbine airfoil for a turbomachine, the turbine airfoil comprising:
a suction side wall and a pressure side wall bordering an airfoil cavity, which is adapted to be flowed through by a cooling fluid for cooling of the side walls,
wherein the suction side wall comprises protrusions extending therefrom inside the airfoil cavity, wherein the protrusions are arranged such that:
a number of the protrusions on the suction side wall is higher than a number of protrusions on the pressure side wall; and/or
a protrusion density on the suction side wall is higher than a protrusion density on the pressure side wall, and/or
a total protrusion surface area on the suction side wall is larger than a total protrusion surface area on the pressure side wall,
so that the heat transfer from the suction side wall to the cooling fluid is higher compared to the heat transfer from the pressure side wall to the cooling fluid during operation of the turbomachine, and
wherein the suction side wall and the pressure side wall each comprise film cooling holes and a respective diameter of the film cooling holes on the suction side wall is smaller than a respective diameter of the film cooling holes on the pressure side wall.

2. The turbine airfoil according to claim 1 , wherein at least one of the protrusions extending from the suction side wall is a turbulator for the cooling fluid flow.

3. The turbine airfoil according to claim 1 , wherein at least one of the protrusions extending from the suction side wall is a cone, a pyramid or a tetrahedron.

4. The turbine airfoil according to claim 1 , wherein at least one of the protrusions extending from the suction side wall is an elongated rib.

5. The turbine airfoil according to claim 1 , wherein at least one of the protrusions extending from the suction side wall extends from an interior surface of the suction side wall to the pressure side wall forming a pedestal around which the cooling fluid can flow.

6. The turbine airfoil according to claim 1 , wherein at least one of the one or more protrusions is located adjacent to a trailing edge of the turbine airfoil.

7. The turbine airfoil according to claim 1 , wherein the turbine airfoil comprises a trailing edge and at least one passage in the trailing edge, wherein the at least one passage is provided for outflow of the cooling fluid from the airfoil cavity.

8. The turbine airfoil according to claim 1 , wherein the turbine airfoil is film cooled.

9. The turbine airfoil according to claim 1 , wherein the film cooling holes are arranged such that:
a number of the film cooling holes on the suction side wall is smaller than a number of film cooling holes on the pressure side wall, and/or
a density of the film cooling holes on the suction side wall is smaller than a density of film cooling holes on the pressure side wall.

10. The turbine airfoil according to claim 1 , wherein at least one of the protrusions extending from the suction side wall is an elongated rib with a triangular cross section.

11. The turbine airfoil according to claim 1 , wherein the turbine airfoil comprises a trailing edge, and wherein at the trailing edge the suction side wall extends aft farther than the pressure side wall.

12. The turbine airfoil according to claim 1 , wherein the turbine airfoil comprises a trailing edge and a leading edge, wherein the airfoil cavity is disposed immediately upstream of an exit passage through the trailing edge, and wherein a direction of flow of the cooling fluid through the airfoil cavity and out the exit passage is from the leading edge toward the trailing edge.

13. A turbine airfoil for a turbomachine, the turbine airfoil comprising:
a leading edge, a trailing edge, and a suction side wall and a pressure side wall that define an airfoil cavity immediately upstream of an exit passage through the trailing edge, the turbine airfoil configured to pass a flow of cooling fluid through the airfoil cavity in a direction from the leading edge toward the trailing edge,
wherein the suction side wall comprises suction-side protrusions extending therefrom into the flow of cooling fluid,

wherein the pressure side wall comprises one or more pressure-side protrusions extending therefrom into the flow of cooling fluid, and
wherein a protrusion density of the suction-side protrusions is higher than a protrusion density of the one or more pressure-side protrusions so that the heat transfer from the suction side wall to the flow of cooling fluid is higher compared to the heat transfer from the pressure side wall to the flow of cooling fluid during operation of the turbomachine, and
suction side film cooling holes through the suction side wall and pressure side film cooling holes through the pressure side wall,
wherein a respective diameter of the suction side film cooling holes is smaller than a respective diameter of the pressure side film cooling holes.

14. The turbine airfoil according to claim 13 , wherein a number, a density, and the diameter, respectively, of the suction side film cooling holes is smaller than that of a number, a density, and the diameter, respectively, of the pressure side film cooling holes.

15. A turbine airfoil for a turbomachine, the turbine airfoil comprising:
a leading edge, a trailing edge, and a suction side wall and a pressure side wall that define an airfoil cavity immediately upstream of an exit passage through the trailing edge, the turbine airfoil configured to pass a flow of cooling fluid through the airfoil cavity in a direction from the leading edge toward the trailing edge,
wherein the suction side wall comprises protrusions extending therefrom into the flow of cooling fluid,
wherein the pressure side wall comprises one or more protrusions extending therefrom into the flow of cooling fluid,
wherein the protrusions are arranged such that:
a number of the protrusions on the suction side wall is higher than a number of the one or more protrusions on the pressure side wall; and
a protrusion density of the protrusions on the suction side wall is higher than a protrusion density of the one or more protrusions on the pressure side wall, and
a total protrusion surface area of the protrusions on the suction side wall is larger than a total protrusion surface area of the one or more protrusions on the pressure side wall,

so that the heat transfer from the suction side wall to the flow of cooling fluid is higher compared to the heat transfer from the pressure side wall to the flow of cooling fluid during operation of the turbomachine,
the turbine airfoil further comprising film cooling holes arranged such that:
a number of the film cooling holes on the suction side wall is smaller than a number of film cooling holes on the pressure side wall, and
a density of the film cooling holes on the suction side wall is smaller than a density of film cooling holes on the pressure side wall, and
a diameter of the film cooling holes on the suction side wall is smaller than a diameter of film cooling holes on the pressure side wall.

Assignees

• Siemens Ag

Inventors

• Shepherd Andrew

Classifications

• F01D9/065

  Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids (see also F01D25/16, F01D25/24 and F01D25/26) · CPC title

• F05D2260/203

  by transpiration cooling · CPC title

• F01D5/186

  Film cooling (F01D5/187 takes precedence) · CPC title

• F01D5/187 Primary

  Convection cooling · CPC title