# US 2013/0156598 A1 · Blade for a turbo machine

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- Number: US 2013/0156598 A1
- Document ID: US20130156598A1
- Status: Published application
- Kind: A1
- Application number: 13/818,121
- Filed: 2011-08-08
- Published: 2013-06-20
- Earliest claimed: 2010-08-30
- Assignees: Siemens Aktiengesellschaft
- Inventors: Anthony Davis
- Web page: https://patentgrep.com/patent/US20130156598A1

## CPC

- F01D 5/082: {on the side of the rotor disc}
- F01D 25/12: Cooling
- F01D 5/187: {Convection cooling}
- F01D 11/04: using sealing fluid, e.g. steam
- F05D 2240/81: Cooled platforms
- F05D 2260/201: by impingement of a fluid
- 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

## Abstract

A blade for a turbomachine, for example a gas turbine, is provided. The blade is arranged on a turbine rotor of the gas turbine. The blade includes a root portion having two narrow sides and two broad sides, a cooling air supply passage in the root portion, and a cooling air bleed which is arranged in the root portion and is in fluid connection with the cooling air supply passage. The cooling air bleed includes a nozzle on one of the narrow sides of the root portion, wherein the nozzle is formed by a hole and wherein an axial direction of the hole is inclined upward between 92° and 135° with respect to a longitudinal direction of the blade.

## Claims

### Claim at position 1

1-13. (canceled)

### Claim 14

Blade for a turbomachine, comprising:
a root portion with two narrow sides and two broad sides;
a cooling air supply passage in the root portion; and
a cooling air bleed arranged in the root portion and in fluid connection with the cooling air supply passage;
wherein the cooling air bleed comprises a nozzle on one of the narrow sides of the root portion, and wherein the nozzle is formed by a hole,
wherein the blade further comprises an upper blade platform and a lower blade platform,
wherein the upper blade platform and the lower blade platform are embodied as parts of a labyrinth-sealing when assembled in the turbomachine, and
wherein the nozzle is arranged between the upper blade platform and the lower blade platform, and
wherein an axial direction of the hole is inclined upward between 92° and 135° with respect to a longitudinal direction of the blade.

### Claim 15 (depends on 14)

The blade according to claim 14, wherein the hole of the nozzle is machined into the root portion.

### Claim 16 (depends on 14)

The blade according to claim 14, wherein the nozzle is arranged on a front surface of the blade.

### Claim 17 (depends on 14)

The blade according to claim 14, wherein the nozzle is arranged for generating an air flow which is directed towards a platform region of an adjacent nozzle guide vane when assembled in the turbomachine.

### Claim 18 (depends on 17)

The blade according to claim 17, wherein the air flow is directed towards a rim and/or tip of the platform region, and wherein the rim and/or tip are directed towards the blade when assembled in the turbomachine.

### Claim 19 (depends on 17)

The blade according to claim 17, wherein the rim and/or tip are part of the labyrinth-sealing when assembled in the turbomachine.

### Claim 20 (depends on 14)

The blade according to claim 14, wherein the cooling air bleed comprises a plurality of nozzles on one of the narrow sides of the root portion.

### Claim 21 (depends on 14)

A turbomachine, comprising:
a turbine rotor with at least one blade according to claim 14.

### Claim 22 (depends on 21)

The turbomachine according to claim 21, further comprising:
a plurality of nozzle guide vanes being arranged upstream of the turbine rotor, wherein the nozzle arranged in the root portion of the at least one blade is directed towards a platform region of the nozzle guide vanes.

### Claim 23 (depends on 22)

The turbomachine according to claim 22, wherein the nozzle is directed to an edge, which is embodied as a rim and/or tip, of the platform region of the nozzle guide vane.

### Claim 24 (depends on 22)

The turbomachine according to claim 22, wherein the platform regions of the nozzle guide vane together with an upper blade platform and a lower blade platform of the at least one blade form the labyrinth-sealing.

### Claim 25 (depends on 24)

The turbomachine according to claim 24, wherein the labyrinth-sealing separates inner regions of the gas turbine from a channel filled with a hot gas.

### Claim 26 (depends on 21)

The turbomachine according to claim 21, wherein an axial direction of the hole of the cooling air bleed, lies at least essentially in a radial plane of the turbine rotor.

### Claim 27 (depends on 21)

The turbomachine according to claim 21, wherein an axial direction of the hole of the cooling air bleed is inclined with respect to a radial plane of the turbine rotor, and wherein the axial direction of the hole has a same direction as a direction of rotation of the blade.