Gas turbine engines and related systems involving air-cooled vanes

Patent metadata

Field	Value
Publication number	US-10156143-B2
Application number	US-95157307-A
Country	US
Kind code	B2
Filing date	Dec 6, 2007
Priority date	Dec 6, 2007
Publication date	Dec 18, 2018
Grant date	Dec 18, 2018

Abstract

Gas turbine engines and related systems involving air-cooled vanes are provided. In this regard, a representative vane for a gas turbine engine includes: an airfoil having a leading edge, a pressure surface, a trailing edge and a suction surface; and a cooling air channel; the suction surface being formed by an exterior surface of a first wall portion and an exterior surface of a second wall portion, the first wall portion spanning a length of the suction surface between the second wall portion and the trailing edge; the cooling air channel being defined, at least in part, by an interior surface of the first wall portion, the first wall portion exhibiting a thickness that is thinner than a thickness exhibited by the second wall portion.

First claim

The invention claimed is:

1. A vane for a gas turbine engine comprising:
an airfoil having a leading edge, a pressure wall having an interior pressure wall surface and an exterior pressure wall surface, a trailing edge and a suction wall having an interior suction wall surface and an exterior suction wall surface;
a cooling air channel;
the exterior suction wall surface being formed by an exterior surface of a first wall portion and an exterior surface of a second wall portion, the first wall portion spanning a length of the suction wall between the second wall portion and the trailing edge;
the cooling air channel being defined, at least in part, by an interior surface of the first wall portion, the first wall portion exhibiting a thickness that is thinner than a thickness exhibited by the second wall portion,
a rib extending between the interior suction wall surface and the interior pressure wall surface;
a cooling air passage, the cooling air passage being isolated from the cooling air channel, at least in part, by a wall segment disposed between the interior pressure wall surface and the interior suction wall surface, the wall segment being spaced from the interior surface of the first wall portion and spaced from the interior pressure wall surface, wherein there are no direct connections between the first wall portion and the wall segment, wherein the wall segment is supported between the pressure wall and the suction wall by at least one partial rib, and wherein the wall segment is closer to the interior suction side surface than the interior pressure side surface.

2. The vane of claim 1 , wherein the thickness of the first wall portion is between approximately 0.020 inches (0.508 millimeters)′ and approximately 0.040 inches (1.016 millimeters)′.

3. The vane of claim 2 , wherein the thickness of the first wall portion is between approximately 0.030 inches (0.762 millimeters)′ and approximately 0.040 inches (1.016 millimeters)′.

4. The vane of claim 1 , wherein the first wall portion lacks cooling holes communicating between the exterior surface and the cooling air channel.

5. The vane of claim 1 , wherein the second wall portion extends between the leading edge and the rib.

6. The vane of claim 1 , wherein: the airfoil extends between a root and a tip; and the airfoil exhibits a uniform cross-section from a vicinity of the root to a vicinity of the tip.

7. The vane of claim 1 , wherein: the pressure surface is formed by the exterior surface of a pressure wall; and the vane further comprises a partial rib extending between an interior surface of the pressure wall and the wall segment such that the partial rib divides the passage into a first passageway and a second passageway.

8. The vane of claim 1 , further comprising: a first platform attached to a root of the airfoil; and a second platform attached to a tip of the airfoil.

9. The vane of claim 1 , wherein said at least one partial rib is connected at a first end to said wall segment and at a second end to an interior surface of said pressure surface.

10. The vane of claim 1 , wherein the pressure wall has a uniform thickness from the leading edge to the trailing edge.

11. A turbine section for a gas turbine engine comprising:
a turbine stage having stationary vanes and rotatable blades;
a first of the vanes having a cooling air channel and an airfoil with a leading edge, a pressure wall having an interior pressure wall surface and an exterior pressure wall surface, a trailing edge and a suction wall having an interior suction wall surface and an exterior suction wall surface;
the exterior suction wall surface being formed by an exterior surface of a first wall portion and an exterior surface of a second wall portion, the first wall portion spanning a length of the suction wall between the second wall portion and the trailing edge;
the cooling air channel being defined, at least in part, by an interior surface of the first wall portion, the first wall portion exhibiting a thickness that is thinner than a thickness exhibited by the second wall portion,
a rib extending between the interior suction wall surface and the interior pressure wall surface;
the first wall portion extends between the trailing edge and the rib;
a cooling air passage, the cooling air passage being isolated from the cooling air channel, at least in part, by a wall segment disposed between the interior pressure wall surface and the interior suction wall surface, the wall segment being spaced from the interior surface of the first wall portion and spaced from the interior pressure wall surface, wherein there are no there are no connectors extending across the cooling air passage between the first wall portion and the wall segment, wherein the wall segment is supported between the pressure wall and the suction wall by at least one partial rib, and wherein the wall segment is closer to the interior suction side surface than the interior pressure side surface.

12. The turbine of claim 11 , wherein: the first of the vanes is associated with a second stage vane assembly; and the turbine further comprises a first stage vane assembly located upstream of the second stage vane assembly.

13. The vane of claim 11 , wherein the turbine is a high-pressure turbine.

14. The vane of claim 11 wherein there are no connectors extending across an intermediate portion of the cooling air channel.

15. A gas turbine engine comprising:
a compressor section; a combustion section located downstream of the compressor section;
a turbine section located downstream of the combustion section and having vanes;
a first of the vanes having a cooling air channel and an airfoil with a leading edge, a pressure wall having an interior pressure wall surface and an exterior pressure wall surface, a trailing edge and a suction wall having an interior suction wall surface and an exterior suction wall surface;
the exterior suction wall surface being formed by an exterior surface of a first wall portion and an exterior surface of a second wall portion, the first wall portion spanning a length of the suction surface between the second wall portion and the trailing edge;
the cooling air channel being defined, at least in part, by an interior surface of the first wall portion, the first wall portion exhibiting a thickness that is thinner than a thickness exhibited by the second wall portion,
a rib extending between the suction wall and the pressure wall;
the first wall portion extends between the trailing edge and the rib;
a cooling air passage, the cooling air passage being separated from the cooling air channel, at least in part, by a wall segment disposed between the interior pressure wall surface and the interior suction wall surface, the wall segment being spaced from the interior surface of the first wall portion and spaced from the interior pressure wall surface, wherein there are no direct connections between the first wall portion and the wall segment, wherein the wall segment is supported between the pressure surface and the suction surface by at least one partial rib, and wherein the wall segment is closer to the interior suction side surface than the interior pressure side surface.

16. The gas turbine engine of claim 15 , wherein the first wall portion lacks cooling holes communicating between the exterior surface and the cooling air channel.

17. The gas turbine engine of claim 15 , wherein: the first of the vanes is associated with a second stage vane assembly; and the turbine section further comprises a first stage vane assembly located upstream of the second stage vane

Assignees

• Fisk Benjamin T
• United Technologies Corp

Inventors

• Fisk Benjamin T

Classifications

• F01D5/187 Primary

  Convection cooling · CPC title