Turbine vane for gas turbine engine

Patent metadata

Field	Value
Publication number	US-10871083-B2
Application number	US-201815933986-A
Country	US
Kind code	B2
Filing date	Mar 23, 2018
Priority date	Mar 23, 2018
Publication date	Dec 22, 2020
Grant date	Dec 22, 2020

Abstract

A turbine vane for a gas turbine engine having a plurality of cooling holes defined therein, the plurality of cooling holes provide fluid communication to a surface of the turbine vane, the plurality of cooling holes including holes noted by the following coordinates: HDA, HDB, HEA, HEB, SAA, SAB, and HCA of Table 1.

First claim

What is claimed is:

1. A turbine vane for a gas turbine engine having a plurality of cooling holes defined therein, the plurality of cooling holes provide fluid communication to a surface of the turbine vane, the plurality of cooling holes including holes noted by the following coordinates: HDA, HDB, HEA, HEB, SAA, SAB, and HCA of Table 1, wherein X, Y and Z coordinate values in Table 1 are distances given in inches from a point of origin O, which is a center point of a circular opening that is cast into a bottom surface of the vane and the coordinates of Table 1 have in average a tolerance of 0.100 inches with respect to X, Y and Z axes of the coordinates wherein for each hole, surface breakout corresponds to an intersection of a central axis of the cooling hole with an outer surface of the vane.

2. The turbine vane of claim 1 , wherein the vane is a second stage vane of a high pressure turbine of the gas turbine engine.

3. The turbine vane of claim 1 , wherein the plurality of cooling holes include holes noted by the all of the coordinates of Table 1.

4. The turbine vane of claim 1 , wherein the plurality of cooling holes include holes noted by the following coordinates of Table 1: TCA, TCB, TDA, TDB, and TDC.

5. The turbine vane of claim 1 , wherein the plurality of cooling holes include holes noted by the following coordinates of Table 1: TBA and TBE.

6. The turbine vane of claim 5 , wherein the plurality of cooling holes include holes noted by the following coordinates of Table 1: TCA, TCB, TDA, TDB, and TDC.

7. The turbine vane of claim 1 , wherein the coordinates of Table 1 have in average a tolerance of ±0.030 or 0.050 inches with respect to X, Y and Z axes of the coordinates.

8. A turbine vane for a gas turbine engine having a plurality of cooling holes defined therein, the plurality of cooling holes providing fluid communication to a surface of the turbine vane, the plurality of cooling holes including holes noted by the following coordinates: TCA, TCB, TDA, TDB, and TDC of Table 1, wherein X, Y and Z coordinate values in Table 1 are distances given in inches from a point of origin O, which is a center point of a circular opening that is cast into a bottom surface of the vane and the coordinates of Table 1 have in average a tolerance of ±0.100 inches with respect to X, Y and Z axes of the coordinates, wherein for each hole, surface breakout corresponds to an intersection of a central axis of the cooling hole with an outer surface of the vane.

9. The turbine vane of claim 8 , wherein the vane is a second stage vane of a high pressure turbine of the gas turbine engine.

10. The turbine vane of claim 9 , wherein the plurality of cooling holes include holes noted by the following coordinates of Table 1; TBA and TBE.

11. The turbine vane of claim 8 , wherein the coordinates of Table 1 have in average a tolerance of ±0.030 or 0.050 inches with respect to X, Y and Z axes of the coordinates.

12. A turbine vane for a gas turbine engine having a plurality of cooling holes defined therein, the plurality of cooling holes providing fluid communication to a surface of the turbine vane, the plurality of cooling holes including holes noted by the following coordinates: TBA and TBE of Table 1, wherein X, Y and Z coordinate values in Table 1 are distances given in inches from a point of origin O, which is a center point of a circular opening that is cast into a bottom surface of the vane and the coordinates of Table 1 have in average a tolerance of ±0.100 inches with respect to X, Y and Z axes of the coordinates wherein for each hole, surface breakout corresponds to an intersection of a central axis of the cooling hole with an outer surface of the vane.

13. The turbine vane of claim 12 , wherein the vane is a second stage vane of a high pressure turbine of the gas turbine engine.

14. The turbine vane of claim 12 , wherein the coordinates of Table 1 have in average a tolerance of ±0.030 or 0.050 inches with respect to X, Y and Z axes of the coordinates.

15. A turbine stator assembly for a gas turbine engine comprising a plurality of vanes, each vane having a plurality of cooling holes defined therein for providing fluid communication to a surface of each vane, the plurality of cooling holes including holes noted by the following coordinates: HDA, HDB, HEA, HEB, SAA, SAB and HCA of Table 1, wherein X, Y and Z coordinate values in Table 1 are distances given in inches from a point of origin O, which is a center point of a circular opening that is cast into a bottom surface of the vane and the coordinates of Table 1 have in average a tolerance of ±0.100 inches with respect to X, Y and Z axes of the coordinates wherein for each hole, surface breakout corresponds to an intersection of a central axis of the cooling hole with an outer surface of the vane.

16. The turbine stator assembly of claim 15 , wherein the plurality of cooling holes include holes noted by the all of the coordinates of Table 1.

17. The turbine stator assembly of claim 15 , wherein the plurality of cooling holes include holes noted by the following coordinates of Table 1: TCA, TCB, TDA, TDB, and TDC and/or holes noted by the following coordinates of Table 1: TBA and TBE.

18. The turbine stator assembly of claim 15 , wherein the coordinates of Table 1 have in average a tolerance of ±0.030 or 0.050 inches with respect to X, Y and Z axes of the coordinates.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Cosher Christopher
• Schneider Alex J
• Teller Bret M

Classifications

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F05D2240/12

  Fluid guiding means, e.g. vanes · CPC title

• F01D5/143

  Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour · CPC title

• F05D2220/3213

  an intermediate stage of the turbine · CPC title

• F05D2250/74

  given by a set or table of xyz-coordinates · CPC title