# US 9,435,210 B2 · Cooled turbine blade for gas turbine engine

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- Number: US 9,435,210 B2
- Document ID: US9435210B2
- Status: Granted
- Kind: B2
- Application number: 13/693,649
- Filed: 2012-12-04
- Published: 2013-06-06
- Granted: 2016-09-06
- Earliest claimed: 2011-12-06
- Assignees: Snecma
- Applicants: Snecma
- Inventors: Jean-Luc Bacha; Emmanuel Berche; Tangi Brusq
- Web page: https://patentgrep.com/patent/US9435210B2

## CPC

- F01D 5/147: {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)}
- F01D 5/20: Specially-shaped blade tips to seal space between tips and stator {(F01D5/225 takes precedence)}
- F01D 25/12: Cooling
- F05D 2250/314: the axes being inclined in relation to each other
- F05D 2250/70: Shape
- F05D 2260/201: by impingement of a fluid
- F05D 2260/221: Improvement of heat transfer
- 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 cooled turbine blade for a gas turbine engine including a pressure surface wall, a suction surface wall and a distal wall connecting the pressure surface wall and the suction surface wall, arranged so as to create in the region of the distal end of the blade at least one external cavity forming a bathtub-shaped cavity and at least one internal cavity separated by the distal wall, the blade having at least one opening for the introduction of a flow of cooling air into the external cavity, wherein, on the one hand, at least one part of the distal wall is inclined relative to the verticals of the pressure surface wall and, on the other hand, the opening is created in the vicinity of the distal wall so that the flow of cooling air is directed towards the distal end of the pressure surface wall.

## Claims

### Claim 1

A cooled turbine blade for a gas turbine engine comprising:
a pressure surface wall;
a suction surface wall; and
a distal wall connecting the pressure surface wall and the suction surface wall, arranged so as to create in a region of a distal end of the blade at least one external cavity forming a bathtub-shaped cavity delimited by the pressure surface wall, the suction surface wall, and the distal wall, and at least one internal cavity separated by the distal wall,
wherein the blade includes at least me opening for the introduction of a flow of cooling air into the external cavity,
wherein a portion of the distal wall is inclined relative to verticals of the pressure surface wall,
wherein the opening is provided in the distal wall so that the flow of cooling air is directed towards a distal end of the pressure surface wall, the distal end of the pressure surface wall being a free end, and
wherein a first end of the distal wall connected to the pressure surface wall is lower than a second end of the distal wall connected to the suction surface wall.

### Claim 2 (depends on 1)

The blade according to claim 1, wherein the opening is created in the distal wall so that the flow of cooling air is not directed towards a distal end of the suction surface wall.

### Claim 3 (depends on 2)

The blade according to claim 2, wherein the opening is created in the distal wall so that an entire flow of cooling air is directed towards the distal end of the pressure surface wall.

### Claim 4 (depends on 1)

The blade according to claim 1, wherein the opening is created in the distal wall so that an entire flow of cooling air is directed towards the distal end of the pressure surface wall and passes along said pressure surface wall.

### Claim 5 (depends on 1)

The blade according to claim 1, wherein an axis of the opening is at least substantially inclined relative to the verticals of the pressure surface wall.

### Claim 6 (depends on 1)

The blade according to claim 1, wherein the entire distal wall is inclined relative to the pressure surface wall.

### Claim 7 (depends on 1)

The blade according to claim 1, wherein another portion of the distal wall is located in a plane at least substantially at right angles to the pressure surface wall.

### Claim 8

A gas turbine engine comprising at least one turbine blade according to one of the preceding claims.