# US 10,767,512 B2 · Particle-trapping device for a turbomachine and turbomachine with such a device

> Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt

- Number: US 10,767,512 B2
- Document ID: US10767512B2
- Status: Granted
- Kind: B2
- Application number: 15/758,337
- Filed: 2016-09-08
- Published: 2018-09-20
- Granted: 2020-09-08
- Earliest claimed: 2015-09-10
- Assignees: Safran Helicopter Engines
- Applicants: Safran Helicopter Engines
- Inventors: Amaury Paillard; Stephane Pascaud
- Web page: https://patentgrep.com/patent/US10767512B2

## CPC

- F01D 25/32: Collecting of condensation water; Drainage {; Removing solid particles}
- F02C 3/145: {the combustion chamber being in the reverse flow-type}
- F02C 7/052: with dust-separation devices
- F23R 3/04: Air inlet arrangements
- F23R 3/54: Reverse-flow combustion chambers
- F05D 2220/329: in helicopters
- F05D 2240/35: Combustors or associated equipment
- F05D 2260/607: Preventing clogging or obstruction of flow paths by dirt, dust, or foreign particles
- Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft
- Y02T 50/678: Aviation using fuels of non-fossil origin
- F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D)
- F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00)
- F23R: GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS (fluidised bed combustion apparatus specially adapted for operation at superatmospheric pressures F23C10/16)
- 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

The invention relates to a particle-trapping device (2) for a turbomachine, said particles being contained in an air stream flowing inside a turbomachine, in particular the air stream flowing in the bypass region (17) of the combustion chamber (13) of said turbomachine. The device is characterized in that it comprises: —at least two particle deflectors (3, 3a, 3b, 3c), —a member (5) for collecting and storing the particles deflected by said deflector, —and means (6) for attaching said trapping device (2) to a part of the turbomachine.

## Claims

### Claim 1

A turbomachine comprising a combustion chamber and a bypass area provided between a wall of said combustion chamber and an outer casing of said turbomachine, wherein the turbomachine is equipped with a particle-trapping device disposed inside said bypass area, said particle-trapping device comprising:
at least two particle deflectors for deflecting grains of sand or dust particles, contained in an air flow circulating inside the bypass area of the combustion chamber of said turbomachine,
at least one support frame,
an element for collecting and storing particles deflected by the at least two particle deflectors,
means for attaching said trapping device on a portion of the turbomachine,
said particle deflectors having an annular shape and being attached to the at least one support frame so as to be coaxial, to be radially aligned and to be spaced radially from one another or from each other, said deflectors being inclined in the same direction with respect to their axes of revolution (X-X′) so as to be turned toward said element for collecting and storing particles.

### Claim 2 (depends on 1)

The turbomachine according to claim 1, wherein said support frame is a ring which extends in a plane perpendicular or substantially perpendicular to the axis of revolution (X-X′) of the deflectors, in that the deflectors of a pair of contiguous deflectors are attached respectively along the outer circular edge and the inner circular edge of said annular support frame and in that this support frame is perforated with openings for passage of the air flow.

### Claim 3 (depends on 1)

The turbomachine according to claim 1, wherein the inner face of a deflector has an angle of inclination (α,β) with respect to said axis of revolution (X-X′) greater than the angle of inclination (β, γ) with respect to this same axis of revolution (X-X′) of the inner face of a deflector disposed radially further inside the device.

### Claim 4 (depends on 1)

The turbomachine according to claim 1, wherein the inner radius (R1) of an outermost deflector of a pair of contiguous deflectors is less than or equal to the outer radius (R2) of a deflector located further inside.

### Claim 5

The turbomachine according to wherein it comprises three deflectors.

### Claim 6 (depends on 1)

The turbomachine according to claim 1, wherein at least one of said deflectors has a rectilinear cross section.

### Claim 7 (depends on 1)

The turbomachine according to claim 1, wherein at least one of said deflectors has a curved cross section, the concavity whereof is turned toward the particle collecting and storing element.

### Claim 8 (depends on 1)

The turbomachine according to claim 1, wherein the collecting and storing element comprises a solid ring coaxial with the axis of revolution (X-X′) of the deflectors and which extends in a plane perpendicular or substantially perpendicular to this axis, this ring being continued in the direction of said deflector by a solid outer annular edge and by a solid inner annular edge, said collecting and storing element being disposed facing the deflector.

### Claim 9 (depends on 1)

The turbomachine according to claim 1, wherein said attachment means comprise a planar annular flange coaxial with the axis of revolution (X-X′) of the deflectors and perpendicular to it, and which is continued in the direction of the particle collecting and storing element by a cylinder with a longitudinal axis coaxial with said axis of revolution (X-X′), in that said cylinder is perforated with several openings for passage of the air flow and in that said annular flange is perforated with several openings for passage of attachment members.