# US 10,767,491 B2 · Blade comprising a trailing edge having three distinct cooling regions

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- Number: US 10,767,491 B2
- Document ID: US10767491B2
- Status: Granted
- Kind: B2
- Application number: 15/765,334
- Filed: 2016-10-04
- Published: 2018-10-25
- Granted: 2020-09-08
- Earliest claimed: 2015-10-06
- Assignees: Safran Aircraft Engines
- Applicants: Safran Aircraft Engines
- Inventors: Patrice Eneau; Sebastien Serge Francis Congratel; Charlotte Marie Dujol; Philippe Picot
- Web page: https://patentgrep.com/patent/US10767491B2

## CPC

- F01D 5/186: {Film cooling (F01D5/187 takes precedence)}
- B22C 9/103: {Multipart cores}
- F01D 5/187: {Convection cooling}
- F05D 2230/21: by casting
- F05D 2240/122: related to the trailing edge of a stator vane
- 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)
- B22C: FOUNDRY MOULDING (moulding refractory materials in general B28B)
- 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 blade including a root bearing an aerofoil extending in a direction of span and ending in a tip, this aerofoil including a leading edge and a trailing edge which are connected by a pressure face wall and a suction face wall, the trailing edge including on the pressure face side cooling slots. The trailing edge includes one or more first slots close to the root, which are supplied via a lower cavity; one or more last slots near the tip which are supplied via an upper cavity; intermediate slots situated between the first slots and the last slots supplied with air via a downstream line set; and wherein the lower cavities and upper cavities and the downstream line set are supplied distinctly at the level of the root.

## Claims

### Claim 1

A vane of a turbomachine turbine, the vane comprising:
a root carrying a blade extending along a span direction ending in an apex, the blade comprising a leading edge and a trailing edge located downstream of the leading edge, the blade comprising a pressure face wall and a suction face wall each connecting the leading edge to the trailing edge, the trailing edge including on the pressure face side, a series of through slots configured to be supplied with cooling air,
wherein the slots include:
one or more first slots which are closest to the root and which are supplied distinctly and independently by a lower cavity of the vane;
one or more last slots which are closest to the apex and which are supplied distinctly and independently by an upper cavity of the vane; and
intermediate slots located between the first slots and the last slots and which are supplied distinctly and independently by an intermediate cavity of the blade;
the lower cavity being closest to the root, the upper cavity being closest to the apex, and the intermediate cavity being arranged between the lower cavity and the upper cavity,
wherein the lower cavity, the upper cavity and the intermediate cavity are distinctly supplied with air at the root of the vane; and
wherein the vane comprises an intermediate duct for supplying the intermediate cavity with air, the intermediate duct being connected to the intermediate cavity by a series of holes to provide calibrated supply to the intermediate cavity,
the vane further comprising a central duct and a pressure face side cavity located between the central duct and the pressure face wall of the blade to form a heat screen protecting the central duct, and
the vane further comprising a suction face side cavity located between the central duct and the suction face wall of the blade to form a heat screen protecting the central duct.

### Claim 2 (depends on 1)

The vane according to claim 1, wherein the lower cavity and the intermediate cavity for cooling the intermediate slots extend along a same direction parallel to the span direction of the blade.

### Claim 3 (depends on 1)

The vane according to claim 1, comprising at least one of a single first slot or a single last slot.

### Claim 4 (depends on 1)

The vane according to claim 1, wherein the upper cavity is located at the apex of the vane by being arranged to cool the apex.

### Claim 5 (depends on 1)

A moulding means for manufacturing a vane according to claim 1, comprising a core for delimiting at least one part of an inner space of the vane when manufactured by moulding.

### Claim 6 (depends on 1)

A turbomachine turbine comprising a vane according to claim 1.

### Claim 7 (depends on 6)

A The turbomachine comprising the turbomachine turbine according to claim 6.

### Claim 8 (depends on 1)

The vane according to claim 1, wherein a length of the intermediate duct in the span direction is less than a length of the central duct in the span direction, and a free end of the intermediate duct is located facing the upper cavity.