Doublet vane assembly for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-10533425-B2
Application number	US-201715856182-A
Country	US
Kind code	B2
Filing date	Dec 28, 2017
Priority date	Dec 28, 2017
Publication date	Jan 14, 2020
Grant date	Jan 14, 2020

Abstract

A vane assembly for a gas turbine engine includes an inner diameter platform, an outer diameter platform, and an airfoil shaped vane spanning from the inner diameter platform to the outer diameter platform. The airfoil shaped vane includes an internal cooling passage having a first inlet at the inner diameter platform and a second inlet at the outer diameter platform. An outer diameter platform cover is disposed radially outward of the outer diameter platform, relative to a radius of an arc defined by an arc of the outer diameter platform. The outer diameter platform includes at least one coolant cover inlet hole, the at least one coolant cover inlet hole being aligned with a corresponding second inlet.

First claim

The invention claimed is:

1. A vane assembly for a gas turbine engine comprising:
an inner diameter platform;
an outer diameter platform;
an airfoil shaped vane spanning from the inner diameter platform to the outer diameter platform, the airfoil shaped vane including an internal cooling passage having a first inlet at said inner diameter platform and a second inlet at said outer diameter platform; and
an outer diameter platform cover disposed radially outward of the outer diameter platform, relative to a radius of an arc defined by an arc of the outer diameter platform, the outer diameter platform including at least one coolant cover inlet hole, the at least one coolant cover inlet hole being aligned with a corresponding second inlet and a cross sectional shape of the second inlet and a cross sectional shape of the at least one cooling cover inlet hole is the same.

2. The vane assembly of claim 1 , further comprising a baffle plate disposed between said outer diameter platform and said outer diameter platform cover.

3. The vane assembly of claim 2 , wherein the baffle plate includes at least one baffle plate inlet hole, the at least one baffle plate inlet hole being aligned with a corresponding second inlet and a corresponding coolant cover inlet.

4. The vane assembly of claim 3 , wherein the baffle plate inlet hole is identically sized with the corresponding coolant cover inlet.

5. The vane assembly of claim 3 , wherein the baffle plate inlet hole is identically shaped with the corresponding coolant cover inlet.

6. The vane assembly of claim 1 , further comprising a second vane spanning from the inner diameter platform to the outer diameter platform, the second vane being substantially identical to the airfoil shaped vane.

7. The vane assembly of claim 6 , wherein the at least one coolant cover inlet hole includes a first coolant cover inlet corresponding to the second inlet of said airfoil shaped vane, and a second coolant cover inlet corresponding to the second inlet of the second vane.

8. The vane assembly of claim 1 , wherein the airfoil shaped vane includes a plurality of film cooling holes configured as coolant outlets for the internal coolant passage.

9. The vane assembly of claim 1 , wherein the vane assembly is a first stage turbine vane assembly for a gas turbine engine.

10. A vane assembly for a gas turbine engine comprising:
an inner diameter platform;
an outer diameter platform;
an airfoil shaped vane spanning from the inner diameter platform to the outer diameter platform, the airfoil shaped vane including an internal cooling passage having a first inlet at said inner diameter platform and a second inlet at said outer diameter platform;
an outer diameter platform cover disposed radially outward of the outer diameter platform, relative to a radius of an arc defined by an arc of the outer diameter platform, the outer diameter platform including at least one coolant cover inlet hole, the at least one coolant cover inlet hole being aligned with a corresponding second inlet; and
wherein a cross sectional shape of the second inlet and a cross sectional shape of the at least one cooling cover inlet hole is the same and the cross sectional shape of the at least one cooling cover inlet hole is scaled down relative to the cross sectional shape of the second inlet by a scaling factor.

11. The vane assembly of claim 10 , wherein the scaling factor is at least 39%.

12. A method for improving a vane assembly comprising:
creating at least a first coolant cover inlet hole in an outer diameter platform cover of a vane assembly, the first coolant cover inlet hole being aligned with a corresponding first airfoil inlet, and the vane assembly including:
an inner diameter platform;
an outer diameter platform;
an airfoil shaped vane spanning from the inner diameter platform to the outer diameter platform, the airfoil shaped vane including an internal cooling passage having a first inlet at said outer diameter platform and a second inlet at said inner diameter platform;
the outer diameter platform cover being disposed radially outward of the outer diameter platform, relative to a radius of an arc defined by an arc of the outer diameter platform; and
wherein the first cooling cover inlet hole is the same shape as the first airfoil inlet.

13. The method of claim 12 , wherein creating the first coolant cover inlet hole in the outer diameter platform cover of the vane assembly further includes creating a first baffle plate inlet hole in a corresponding baffle plate.

14. The method of claim 13 , wherein creating the first coolant cover inlet hole and the first baffle plate inlet hole is performed in a single material removal operation.

15. The method of claim 12 , further comprising creating a second coolant cover inlet hole in the outer diameter platform cover of the vane assembly, the second coolant cover inlet hole being aligned with the corresponding first airfoil inlet.

16. A method for improving a vane assembly comprising:
creating at least a first coolant cover inlet hole in an outer diameter platform cover of a vane assembly, the first coolant cover inlet hole being aligned with a corresponding first airfoil inlet, and the vane assembly including:
an inner diameter platform;
an outer diameter platform;
an airfoil shaped vane spanning from the inner diameter platform to the outer diameter platform, the airfoil shaped vane including an internal cooling passage having a first inlet at said outer diameter platform and a second inlet at said inner diameter platform;
the outer diameter platform cover being disposed radially outward of the outer diameter platform, relative to a radius of an arc defined by an arc of the outer diameter platform; and

wherein the first cooling cover inlet hole is the same shape as the first airfoil inlet, and wherein a size of the first cooling cover inlet hole is scaled relative to a size of the first airfoil inlet such that the first cooling cover inlet hole is smaller than the first airfoil inlet.

Assignees

• United Technologies Corp

Inventors

• Mcmahon Shawn M
• Whitfield Christopher
• Loricco Nicholas M
• Gautschi Steven Bruce
• Simms Vincent E
• Aniello Justin M
• Allwood Thomas
• Salzillo Richard M
• Hembree Sr Jeffery Scott

Classifications

• F05D2260/202

  by film cooling · CPC title

• F05D2240/81

  Cooled platforms · CPC title

• F01D9/041 Primary

  using blades (F01D5/148 takes precedence) · CPC title

• F05D2260/201

  by impingement of a fluid · CPC title

• 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