# US 2024/0200468 A1 · Turbine engine assembly comprising a casing and an aerodynamic treatment member at the blade tips, and corresponding turbine engine

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- Number: US 2024/0200468 A1
- Document ID: US20240200468A1
- Status: Published application
- Kind: A1
- Application number: 18/556,803
- Filed: 2022-04-26
- Published: 2024-06-20
- Earliest claimed: 2021-04-28
- Assignees: Safran
- Applicants: Safran
- Inventors: Gabriel PEREZ; Mickael Vincent PHILIT; William Henri Joseph RIERA
- Web page: https://patentgrep.com/patent/US20240200468A1

## CPC

- F01D 25/24: Casings (modified for heating or cooling F01D25/14); Casing parts, e.g. diaphragms, casing fastenings (casings for rotary machines or engines in general F16M {; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045})
- F01D 9/041: {using blades (F01D5/148 takes precedence)}
- F04D 19/00: Axial-flow pumps (F04D21/00 takes precedence; {pump comprising axial flow and radial flow stages F04D17/025})
- F04D 29/526: {Details of the casing section radially opposing blade tips (ducts F04D29/545)}
- F04D 29/685: {Inducing localised fluid recirculation in the stator-rotor interface}
- F05D 2240/11: Shroud seal segments
- F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D)
- F04D: NON-POSITIVE-DISPLACEMENT PUMPS (engine fuel-injection pumps F02M; ion pumps H01J41/12; electrodynamic pumps H02K44/02)
- F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS

## Abstract

An assembly including a turbine engine casing, in particular for an aircraft, the turbine engine casing including an annular or cylindrical radially outer shell, provided with a radially inner surface, and an aerody-namic treatment member including a plurality of grooves distributed in a circumferential direction. The radially outer shell includes a circumferential recess in which the aerodynamic treatment member is removably mounted, the treatment member extending along at least one angular sector and having a shape that matches that of the circumferential recess, the treatment member including a circumferential opening into which the plurality of grooves open.

## Claims

### Claim 1

An assembly comprising a casing for a turbine engine, in particular for an aircraft, the turbine engine casing comprising an annular or cylindrical radially outer shell provided with a radially inner surface, and an aerodynamic treatment member comprising a plurality of grooves distributed in a circumferential direction, wherein the radially outer shell comprises a circumferential recess in which the aerodynamic treatment member is removably mounted, the treatment member extending along at least one angular sector and being complementary in shape to the circumferential recess, the treatment member comprising a circumferential opening into which the plurality of grooves opens.

### Claim 2 (depends on 1)

The assembly according to claim 1, wherein the treatment member comprises a first surface and a second surface opposite the first surface, the first surface being intended to have a surface continuity with the radially inner surface of the radially outer shell.

### Claim 3 (depends on 1)

The assembly according to claim 1, wherein the treatment member has substantially a L-shape.

### Claim 4 (depends on 1)

The assembly according to claim 1, wherein the treatment member is produced by additive manufacturing, preferably on a powder basis.

### Claim 5 (depends on 1)

The assembly according to claim 1, wherein the treatment member is made of an abradable material.

### Claim 6 (depends on 1)

The assembly according to claim 1, wherein the member is made of a metallic material or of a thermoplastic material or of a ceramic material.

### Claim 7 (depends on 2)

The assembly according to claim 2, wherein the second surface comprises a slot intended to face at least one portion of the radially inner surface, the slot forming a radial space between the bottom of the slot and the radially inner surface portion.

### Claim 8 (depends on 1)

The assembly according to claim 1, wherein each groove has an elongate shape in a main direction of orientation with a substantially straight first portion and a second portion substantially inclined with respect to the first portion.

### Claim 9 (depends on 1)

The assembly according to claim 1, wherein it comprises a wheel with blades surrounded by the casing, the aerodynamic treatment member being arranged facing the free ends of the blades so that, when the blades rotate, a flow of air circulating at the level of the free ends penetrates at least into the grooves.

### Claim 10 (depends on 1)

The assembly according to claim 1, wherein the casing is a high-pressure or low-pressure compressor casing.

### Claim 11 (depends on 1)

The assembly according to claim 1, wherein the treatment member is formed of several treatment member sectors or is annular.

### Claim 12 (depends on 1)

A turbine engine, in particular for an aircraft, comprising a turbine engine assembly according to claim 1.