# US 2024/0200460 A1 · Foil for a turbomachine rotor blade, assembly for a turbomachine rotor, and turbomachine

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- Number: US 2024/0200460 A1
- Document ID: US20240200460A1
- Status: Published application
- Kind: A1
- Application number: 18/552,017
- Filed: 2022-03-22
- Published: 2024-06-20
- Earliest claimed: 2021-04-01
- Assignees: Safran Aircraft Engines
- Applicants: Safran Aircraft Engines
- Inventors: Vincent GOYON; Pierre Marie MULHEIM; Arnaud MARTINE; Antoine GIGUET; Nicolas Daniel DELAPORTE
- Web page: https://patentgrep.com/patent/US20240200460A1

## CPC

- F01D 5/3015: {with side plates}
- F01D 5/3092: {Protective layers between blade root and rotor disc surfaces, e.g. anti-friction layers (F01D5/288 takes precedence)}
- F01D 5/323: {Locking of axial insertion type blades by means of a key or the like parallel to the axis of the rotor}
- F05D 2230/54: by sheet metal manufacturing
- F05D 2250/75: given by its similarity to a letter, e.g. T-shaped
- F05D 2260/38: by a spring, i.e. spring loaded or biased towards a certain position
- 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 foil for a rotating blade of a turbomachine, configured to be mounted to a blade root of the rotating blade and including an overall U-shaped cross-section formed by two lateral legs connected through a lower surface, the lower surface covering a lower face of the blade root, the lateral legs each covering at least part of two lateral flanks of the blade root; and a blocking system for prohibiting at least some of relative movements between the blade root and the foil, the blocking system including at least one oblique tab, partially cut out of a lower surface of the foil and forming, with respect to the lower surface of the foil, a tilted plane protrusion able to be inserted into a housing formed in a lower face of the blade root.

## Claims

### Claim 1

A foil for a rotating blade of a turbomachine, configured to be mounted to a blade root of said rotating blade and comprising:
an overall U-shaped cross-section formed by two lateral legs connected through a lower surface, the lower surface covering a lower face of the blade root, the lateral legs each covering at least part of two lateral flanks of the blade root; and
blocking means for prohibiting at least some of relative movements between the blade root and said foil,
said blocking means including at least one oblique tab, partially cut out of a lower surface of the foil and forming, with respect to said lower surface of the foil, a tilted plane protrusion able to be inserted into a housing formed in a lower face of the blade root.

### Claim 2 (depends on 1)

The foil according to claim 1, wherein the oblique tab includes free edges detached from the lower surface of the foil, and a non-free edge attached to said lower surface.

### Claim 3 (depends on 1)

The foil according to claim 1, wherein the tilted plane formed by the oblique tab extends from an upstream to downstream direction.

### Claim 4 (depends on 1)

The foil according to claim 1, wherein the oblique tab is at least partially rectangular in shape and is tilted relative to the lower surface of the foil at an angle of less than 45°.

### Claim 5 (depends on 4)

The foil according to claim 4, wherein the oblique tab is tilted, relative to the lower surface of the foil, at an angle of between about 10° and 25°.

### Claim 6 (depends on 1)

The foil according to claim 1, wherein the oblique tab has the shape of a planar lamella, shaped by folding its non-free edge (305b).

### Claim 7 (depends on 1)

The foil according to claim 1, wherein the oblique tab has the shape of a lamella with an at least partially bent profile, shaped by drawing.

### Claim 8 (depends on 1)

An assembly for a turbomachine rotor, including a rotating blade configured so as to be rotatably rotating about an axis of rotation and including a vane radially extending between a heel and a blade root, said blade root including a lower face extending in a plane parallel to the axis of rotation, the assembly comprising a foil according to claim 1, mounted at least partially around the blade root, the lower face of the blade root including a recess forming a housing for the oblique tab of the foil.

### Claim 9 (depends on 8)

The assembly according to claim 8, wherein the blade root is configured so as to be mounted in an alveolus of a disc of the turbomachine, wherein a height between the lower surface of the foil and free edge of the oblique tab furthest from said lower surface is greater than a clearance between the lower face of the blade root and a bottom of the alveolus of the disc.

### Claim 10 (depends on 8)

The assembly according to claim 8, wherein the recess of the blade root includes an oblique upper wall forming a tilted plane substantially parallel to the tilted plane formed by the oblique tab.

### Claim 11 (depends on 8)

A turbomachine including a rotor comprising at least one assembly according to claim 8.