# US 10,871,083 B2 · Turbine vane for gas turbine engine

> Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt

- Number: US 10,871,083 B2
- Document ID: US10871083B2
- Status: Granted
- Kind: B2
- Application number: 15/933,986
- Filed: 2018-03-23
- Published: 2019-09-26
- Granted: 2020-12-22
- Earliest claimed: 2018-03-23
- Assignees: Raytheon Technologies Corporation
- Applicants: United Technologies Corporation
- Inventors: Christopher Cosher; Alex J. Schneider; Bret M. Teller
- Web page: https://patentgrep.com/patent/US10871083B2

## CPC

- F01D 9/065: {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)}
- F01D 25/12: Cooling
- F01D 9/041: {using blades (F01D5/148 takes precedence)}
- F01D 5/143: {Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour}
- F05D 2220/3213: an intermediate stage of the turbine
- F05D 2240/12: Fluid guiding means, e.g. vanes
- F05D 2240/121: related to the leading edge of a stator vane
- F05D 2240/81: Cooled platforms
- F05D 2250/74: given by a set or table of xyz-coordinates
- F05D 2260/202: by film cooling
- Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft
- F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D)
- F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION

## 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.

## Claims

### Claim 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.

### Claim 2 (depends on 1)

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

### Claim 3 (depends on 1)

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

### Claim 4 (depends on 1)

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.

### Claim 5 (depends on 1)

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.

### Claim 6 (depends on 5)

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.

### Claim 7 (depends on 1)

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.

### Claim 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.

### Claim 9 (depends on 8)

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

### Claim 10 (depends on 9)

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.

### Claim 11 (depends on 8)

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.

### Claim 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.

### Claim 13 (depends on 12)

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

### Claim 14 (depends on 12)

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.

### Claim 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.

### Claim 16 (depends on 15)

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.

### Claim 17 (depends on 15)

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.

### Claim 18 (depends on 15)

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.