Turbine vane with load shield

Patent metadata

Field	Value
Publication number	US-10060272-B2
Application number	US-201615007991-A
Country	US
Kind code	B2
Filing date	Jan 27, 2016
Priority date	Jan 30, 2015
Publication date	Aug 28, 2018
Grant date	Aug 28, 2018

Abstract

A turbine vane for use in a gas turbine engine is disclosed. The turbine vane includes an inner platform, an outer platform spaced from the inner platform, and an airfoil that extends from the inner platform to the outer platform. The airfoil includes a ceramic-containing web that forms a portion of the airfoil and a metallic load shield that forms another portion of the airfoil.

First claim

What is claimed is:

1. A turbine vane for use in a gas turbine engine, the turbine vane comprising
an inner platform,
an outer platform spaced from the inner platform, and
an airfoil that extends from the inner platform to the outer platform, the airfoil including a ceramic-containing web that forms a suction side of the airfoil and a metallic load shield that forms a pressure side of the airfoil,
wherein the metallic load shield is arranged adjacent to the ceramic-containing web to form a cooling channel between the ceramic-containing web and the metallic load shield that extends over the entire distance from the inner platform to the outer platform and from a leading edge of the airfoil to a trailing edge of the airfoil.

2. The turbine vane of claim 1 , wherein the metallic load shield is formed to include a first cooling air inlet port defined by a first thinned section of the metallic load shield that extends from at least one of the inner platform and the outer platform to the cooling channel and sized to conduct cooling air to the cooling channel during use of the turbine vane.

3. The turbine vane of claim 2 , wherein the first cooling air inlet port is arranged in a midspan region of the airfoil between the leading edge and the trailing edge of the airfoil at a location exposed to high temperatures when the turbine vane is used.

4. The turbine vane of claim 3 , wherein the metallic load shield includes cooling features arranged in the first cooling air inlet port that increase surface area of the metallic load shield along the first cooling air inlet port so that heat is dissipated through the cooling features by cooling air flowing through the first cooling air inlet port.

5. The turbine vane of claim 4 , wherein the cooling features include at least one of ribs, pins, slots, and bumps.

6. The turbine vane of claim 2 , wherein the metallic load shield is formed to include a second cooling air inlet port, spaced apart from the first cooling air inlet port, defined by a second thinned section of the metallic load shield that extends from at least one of the inner platform and the outer platform to the cooling channel and sized to conduct cooling air to the cooling channel during use of the turbine vane.

7. The turbine vane of claim 6 , wherein the first cooling air inlet port and the second cooling air inlet port are arranged in a midspan region of the airfoil between the leading edge and the trailing edge of the airfoil at locations exposed to high temperatures when the turbine vane is used.

8. The turbine vane of claim 7 , wherein the metallic load shield includes cooling features arranged in the first cooling air inlet port and in the second cooling air inlet port that increase surface area of the metallic load shield along the first and the second cooling air inlet ports so that heat is dissipated through the cooling features by cooling air flowing through the first and the second cooling air inlet ports.

9. The turbine vane of claim 6 , further comprising a restrictor plate arranged at the end of the first cooling air inlet port and the second cooling air inlet port adjacent to the inner platform or the outer platform, the restrictor plate formed to include a first restriction port in fluid communication with the first cooling air inlet port and sized to cause a first pressure to be established within the first cooling air inlet port by cooling air supplied to the first cooling air inlet port, and the restrictor plate formed to include a second restriction port in fluid communication with the second cooling air inlet port and sized to cause a second pressure to be established within the second cooling air inlet port by cooling air supplied to the second cooling air inlet port.

10. The turbine vane of claim 1 , wherein a leading edge interface of the metallic load shield and the ceramic-containing web is arranged to discharge cooling air from the cooling channel at a location that creates a cooling air film along at least a portion of the suction side of the airfoil during use of the turbine vane in the gas turbine engine.

11. The turbine vane of claim 10 , wherein a trailing edge interface of the metallic load shield and the ceramic-containing web is arranged to discharge cooling air from the cooling channel along the trailing edge of the airfoil during use of the turbine vane in the gas turbine engine.

12. The turbine vane of claim 1 , wherein the metallic load shield is formed to include bleed holes that extend from the cooling channel to the pressure side of the airfoil to conduct cooling air out of the cooling channel during use of the turbine vane in the gas turbine engine.

13. An airfoil adapted for use in a gas turbine engine, the airfoil comprising
a ceramic-containing web that forms a suction side of the airfoil, and
a metallic load shield that forms a pressure side of the airfoil,
wherein the metallic load shield is arranged adjacent to the ceramic-containing web to form a cooling channel between the ceramic-containing web and the metallic load shield that extends from a leading edge of the airfoil to a trailing edge of the airfoil.

14. The airfoil of claim 13 , wherein the metallic load shield is formed to include a first cooling air inlet port defined by a first thinned section of the metallic load shield that extends from at least one of an inner platform and an outer platform to the cooling channel and sized to conduct cooling air to the cooling channel.

15. The airfoil of claim 14 , wherein the first cooling air inlet port is arranged in a midspan region of the airfoil between the leading edge and the trailing edge of the airfoil at a location exposed to high temperatures when the turbine vane is used.

16. The airfoil of claim 14 , wherein the metallic load shield is formed to include a second cooling air inlet port, spaced apart from the first cooling air inlet port, defined by a second thinned section of the metallic load shield that extends from at least one of the inner platform and the outer platform to the cooling channel and sized to conduct cooling air to the cooling channel during use of the turbine vane.

17. The airfoil of claim 16 , wherein the first cooling air inlet port and the second cooling air inlet port are arranged in a midspan region of the airfoil between the leading edge and the trailing edge of the airfoil at locations exposed to high temperatures when the turbine vane is used.

18. The airfoil of claim 17 , wherein the metallic load shield includes cooling features arranged in the first cooling air inlet port and in the second cooling air inlet port that increase surface area of the metallic load shield along the first and the second cooling air inlet ports so that heat is dissipated through the cooling features by cooling air flowing through the first and the second cooling air inlet ports.

19. A method of assembling a turbine vane for use in a gas turbine engine, the method comprising
arranging a ceramic-containing web adjacent to a metallic load shield so that the ceramic-containing web and the metallic load shield cooperate to form an airfoil, and
coupling the airfoil to an inner platform and an outer platform so that the airfoil extends across a gas path defined between the inner platform and the outer platform,
wherein the metallic load shield is arranged relative to the ceramic-containing web to form a cooling channel between the ceramic-containing web and the metallic load shield that extends over the entire distance from the inner platform to the outer platform and from a leading edge of

Assignees

• Rolls Royce Corp

Inventors

• Jennings Aaron P

Classifications

• F01D5/147

  Construction, i.e. structural features, e.g. of weight-saving hollow blades (F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18) · CPC title

• F05D2240/124

  related to the suction side of a stator vane · CPC title

• F05D2300/20

  Oxide or non-oxide ceramics · CPC title

• F05D2240/123

  related to the pressure side of a stator vane · CPC title

• F01D5/284 Primary

  Selection of ceramic materials · CPC title