# US 10,370,983 B2 · Endwall cooling system

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- Number: US 10,370,983 B2
- Document ID: US10370983B2
- Status: Granted
- Kind: B2
- Application number: 15/663,462
- Filed: 2017-07-28
- Published: 2019-01-31
- Granted: 2019-08-06
- Earliest claimed: 2017-07-28
- Assignees: ROLLS-ROYCE plc
- Applicants: Rolls-Royce Corporation
- Inventors: John A. Weaver; Tony A. Lambert
- Web page: https://patentgrep.com/patent/US10370983B2

## CPC

- F01D 5/188: {with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall}
- F01D 5/145: {Means for influencing boundary layers or secondary circulations (for compressors F04D29/68)}
- F01D 5/187: {Convection cooling}
- F01D 9/041: {using blades (F01D5/148 takes precedence)}
- F01D 25/12: Cooling
- F04D 29/2255: {flow-channels with a special cross-section contour, e.g. ejecting, throttling or diffusing effect}
- F04D 29/2272: {for influencing flow or boundary layer}
- F04D 29/5846: {cooling by injection}
- F05D 2240/81: Cooled platforms
- F05D 2250/12: rectangular
- F05D 2250/141: circular
- F05D 2260/20: Heat transfer, e.g. cooling
- F05D 2260/22141: using fins or ribs
- 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)
- F04D: NON-POSITIVE-DISPLACEMENT PUMPS (engine fuel-injection pumps F02M; ion pumps H01J41/12; electrodynamic pumps H02K44/02)
- 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

An air distribution system for cooling a component in a heated gas environment may be provided, where the air distribution system includes a wall and a plate. The wall includes an inner surface, an outer surface configured to be exposed to the heated gas environment, and a protrusion extending from the inner surface of the wall. The plate is fixedly coupled to the protrusion and is space apart from the inner surface of the wall. The plate includes an outer edge. A passage is defined between the plate and the inner surface of the wall. The inlet of the passage is defined by the outer edge of the plate.

## Claims

### Claim 1

An air distribution system for cooling a component in a heated gas environment of a gas turbine engine, comprising:
a wall comprising an inner surface, an outer surface configured to be exposed to the heated gas environment, and a protrusion extending from the inner surface of the wall; and
a plate spaced apart from the inner surface of the wall, the plate comprising an outer edge, the plate fixedly coupled to the protrusion, wherein a passage is defined between the plate and the inner surface of the wall, and wherein an inlet of the passage is defined by the outer edge of the plate.

### Claim 2 (depends on 1)

The air distribution system of claim 1, wherein the wall comprises an opening extending between the inner surface and the outer surface of the wall, the opening defining an outlet of the passage.

### Claim 3 (depends on 2)

The air distribution system of claim 2, wherein the opening of the wall is arranged proximate to the protrusion.

### Claim 4 (depends on 2)

The air distribution system of claim 2, wherein the opening is positioned on the wall so as to maximize distance between the outer edge of the plate and the opening of the wall.

### Claim 5 (depends on 1)

The air distribution system of claim 1, wherein the protrusion is fixedly coupled to a center of the plate.

### Claim 6 (depends on 1)

The air distribution system of claim 1, wherein the protrusion is fixedly coupled to a portion of the outer edge of the plate.

### Claim 7 (depends on 1)

The air distribution system of claim 1, wherein one of the wall or the plate comprises a rib extending into the passage, wherein the rib is configured to direct air flow from the inlet of the passage to an outlet of the passage.

### Claim 8 (depends on 1)

The air distribution system of claim 1, wherein the plate comprises an intact surface extending from a first outer edge of the plate to an opposing second outer edge of the plate.

### Claim 9 (depends on 1)

The air distribution system of claim 1, wherein one of the wall or the plate comprises a plurality of pins extending in the passage, and wherein the plurality of pins are shaped and arranged to create turbulence in a fluid that passes through the passage.

### Claim 10 (depends on 1)

The air distribution system of claim 1, comprising a plurality of plates and a plurality of protrusions, wherein each plate is coupled one of the plurality of protrusions, wherein each of the plurality of plates is spaced apart from each another, and wherein the inlet of the passage is at least partially defined by a gap between the respective outer edges of at least two of the plurality of plates.

### Claim 11

A turbine vane comprising:
a wall comprising an inner surface, an outer surface, and a protrusion extending from the inner surface of the wall;
a plate spaced apart from the inner surface of the wall, the plate comprising an outer edge, wherein the plate is fixedly coupled to the protrusion; and
an airfoil extending outwardly from the outer surface of the wall, wherein a passage is defined between the plate and the inner surface of the wall, and wherein an inlet of the passage is defined by the outer edge of the plate.

### Claim 12 (depends on 11)

The turbine vane of claim 11, wherein a perimeter of the plate defined by the outer edge of the plate is greater than a perimeter of the protrusion which is fixedly coupled to the plate.

### Claim 13 (depends on 11)

The turbine vane of claim 11, further comprising a cavity within the airfoil, the passage having an outlet which is in fluid communication with the cavity of the airfoil.

### Claim 14 (depends on 13)

The turbine vane of claim 13, wherein the airfoil comprises a boss which extends inwardly from the inner surface of the wall, wherein the outlet of the passage is defined by an opening in the boss.

### Claim 15 (depends on 14)

The turbine vane of claim 14, wherein the protrusion is the boss of the airfoil.

### Claim 16 (depends on 15)

The turbine vane of claim 15, wherein the plate encircles the boss of the airfoil.

### Claim 17 (depends on 16)

The turbine vane of claim 16, wherein the wall comprises a raised element extending transversely to and aligned with the outer edge of the plate, wherein the inlet of the passage is at least partially defined by a gap between the raised element of the wall and the outer edge of the plate.

### Claim 18

A method of cooling a component of a turbine vane comprising:
supplying cooling air to a passage, wherein the passage is defined by a wall of the turbine vane and a plate spaced apart from the wall, wherein the plate is fixedly coupled to a protrusion which extends between the plate and the wall, and wherein an inlet of the passage is defined by an outer edge of the plate; and
releasing the cooling air from the passage through an outlet of the passage.

### Claim 19 (depends on 18)

The method of claim 18, wherein the cooling air is released through an opening in the wall to an outer surface of the wall.

### Claim 20 (depends on 18)

The method of claim 18, wherein the cooling air is released into a cavity of an airfoil of the turbine vane.