# US 12,595,743 B2 · Bladed turbomachine assembly including means for limiting vibrations between platforms

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- Number: US 12,595,743 B2
- Document ID: US12595743B2
- Status: Granted
- Kind: B2
- Application number: 18/869,432
- Filed: 2023-06-12
- Published: 2025-11-20
- Granted: 2026-04-07
- Earliest claimed: 2022-06-22
- Assignees: Safran Aircraft Engines; Safran Ceramics
- Applicants: Safran Aircraft Engines; Safran Ceramics
- Inventors: Fabrice Marcel Noël Garin; Romain Claude Gabriel Bardon; Fabrice Joël Luc Chevillot; Lucien Henri Jacques Quennehen; Simon Jean-Marie Bernard Cousseau
- Web page: https://patentgrep.com/patent/US12595743B2

## CPC

- F01D 5/225: {by shrouding}
- F05D 2220/323: for aircraft propulsion, e.g. jet engines
- F05D 2240/80: Platforms for stationary or moving blades
- F05D 2260/96: Preventing, counteracting or reducing vibration or noise
- F05D 2300/6033: Ceramic matrix composites [CMC]
- 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 bladed turbomachine assembly including at least two adjacent blades, each blade including a radial aerofoil and a platform located at a free radial end of the aerofoil, the platform of each blade of the bladed assembly being located circumferentially facing a platform of the other circumferentially adjacent blade of the bladed assembly, the bladed assembly including an insert arranged circumferentially between the platforms and which cooperates with the platforms, each platform including a circumferential bearing face against which a circumferential end of the insert is in contact, and the direction of the contact between each circumferential bearing face and the insert being oriented circumferentially with respect to the main axis (A).

## Claims

### Claim 1

A bladed turbomachine assembly extending about a main axis and including at least two circumferentially adjacent blades,
each blade comprising an airfoil extending according to a direction of radial extension with respect to said main axis and a platform located at a free radial end of the airfoil,
wherein the platform of each blade of the bladed assembly is located circumferentially facing a platform of the other circumferentially adjacent blade of the bladed assembly,
wherein the bladed assembly includes an insert arranged circumferentially between the platforms and which cooperates with the platforms,
wherein each platform includes a circumferential bearing face against which a circumferential end of the insert is in contact, and the direction of the contact between each circumferential bearing face and the insert is oriented circumferentially with respect to the main axis, and
wherein said bladed turbomachine assembly comprises means for axial retention of the insert between the two platforms that comprise at least one finger carried by the insert which protrudes circumferentially from the insert and which is received in an associated notch formed circumferentially in recess in at least one of the platforms, said at least one finger and the associated notch are designed to allow a relative movement of the insert with respect to the platforms according to the radial direction.

### Claim 2 (depends on 1)

The bladed turbomachine assembly according to claim 1, wherein at least one of the two platforms includes a groove circumferentially open towards the other of the two platforms, one face of the groove of which forms the circumferential bearing face and in which said groove a circumferential end of the insert is received.

### Claim 3 (depends on 1)

The bladed turbomachine assembly according to claim 1, wherein said circumferential bearing face is in the shape of an arc of a circle or is inclined with respect to the radial direction.

### Claim 4 (depends on 1)

The bladed turbomachine assembly according to claim 1, wherein the circumferential bearing face of a platform is parallel to a radial direction with respect to the main axis.

### Claim 5 (depends on 1)

The bladed turbomachine assembly according to claim 1, wherein the circumferential bearing face includes a groove.

### Claim 6 (depends on 1)

The bladed turbomachine assembly according to claim 1, wherein the insert includes two contact faces, each contact face of which has a shape complementary to the shape of the circumferential bearing face.

### Claim 7 (depends on 6)

The bladed turbomachine assembly according to claim 6, wherein at least one contact face of the insert is in the shape of an arc of a cylinder, an axis of which is parallel to the main direction of the insert.

### Claim 8 (depends on 7)

The bladed turbomachine assembly according to claim 7, wherein each circumferential end of the insert is received with a radial play and a circumferential play in a groove.

### Claim 9 (depends on 1)

The bladed turbomachine assembly according to claim 1, wherein each platform includes a boss having a radial thickness greater than a thickness of the rest of the platform, in which said boss a groove is formed.

### Claim 10 (depends on 1)

An aircraft turbomachine including a bladed turbomachine assembly according to claim 1.