# US 11,441,438 B2 · Bleed air extraction device for a gas turbine engine

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- Number: US 11,441,438 B2
- Document ID: US11441438B2
- Status: Granted
- Kind: B2
- Application number: 16/855,503
- Filed: 2020-04-22
- Published: 2020-12-10
- Granted: 2022-09-13
- Earliest claimed: 2019-04-26
- Assignees: Rolls-Royce Deutschland Ltd & Co KG
- Applicants: Rolls-Royce Deutschland Ltd & Co KG
- Inventors: Bernd Becker
- Web page: https://patentgrep.com/patent/US11441438B2

## CPC

- F01D 9/06: Fluid supply conduits to nozzles or the like
- F01D 9/041: {using blades (F01D5/148 takes precedence)}
- F02C 6/08: the gas being bled from the gas-turbine compressor
- F04D 27/0215: {Arrangements therefor, e.g. bleed or by-pass valves}
- F04D 29/542: {Bladed diffusers (fixing blades to stators F01D9/042)}
- F02C 9/18: by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages {(F02C3/113 takes precedence)}
- F04D 27/023: {Details or means for fluid extraction}
- F05D 2220/3217: for the first stage of a compressor or a low pressure compressor
- F05D 2220/323: for aircraft propulsion, e.g. jet engines
- F05D 2240/12: Fluid guiding means, e.g. vanes
- F05D 2240/80: Platforms for stationary or moving blades
- 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)
- 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

The invention relates to a bleed air extraction device for a turbomachine, which has: an axial compressor, formed in a flow path and having at least one compressor stage, which comprises a rotor and a stator, and a bleed air duct, which is provided and designed to guide a bleed air flow branched off from the flow path of the axial compressor. In this case, the bleed air duct comprises an inlet opening, which is formed downstream of a stator of the axial compressor in the radially outer flow path boundary, an axially forward wall adjoining the inlet opening, and an axially rearward wall adjoining the inlet opening. Guide means are provided, which are provided and designed for the purpose of guiding at least a portion of the bleed air flow branched off from the flow path in the direction of the axially forward wall of the bleed air duct.

## Claims

### Claim 1

A bleed air extraction device for a turbomachine, comprising:
an axial compressor, formed in a flow path and having at least one compressor stage, which comprises a rotor and a stator, wherein the flow path is bounded radially on an inside by a radially inner flow path boundary and radially on an outside by a radially outer flow path boundary,
a bleed air duct configured to guide a bleed air flow branched off from the flow path of the axial compressor, wherein the bleed air duct includes:
an inlet opening, which is formed downstream of the rotor or the stator of the axial compressor in the radially outer flow path boundary,
an axially forward wall adjoining the inlet opening, and
an axially rearward wall adjoining the inlet opening,
a guide mechanism configured to guide at least a portion of the bleed air flow increasingly in a direction of the axially forward wall of the bleed air duct;
the guide mechanism including flow-guiding bodies shaped as ribs and positioned on the axially rearward wall of the bleed air duct, the ribs being aligned in the longitudinal direction of the bleed air duct and deflecting the bleed air flow in the bleed air duct increasingly in the direction of the axially forward wall of the bleed air duct, wherein the ribs extend from the axially rearward wall only partially into the bleed air duct and do not extend to the axially forward wall.

### Claim 2 (depends on 1)

The device according to claim 1, wherein the guide mechanism is configured to guide the portion of the bleed air flow increasingly in the direction of the axially forward wall of the bleed air duct in such a way that a low-momentum zone which is formed adjoining the inlet opening at the axially forward wall is reduced or dispersed by the portion of the bleed air flow.

### Claim 3 (depends on 1)

The device according to claim 1, wherein the guide mechanism is configured to guide the portion of the bleed air flow increasingly in the direction of the axially forward wall of the bleed air duct in such a way that a portion of the portion of the bleed air flow adjacent to the axially forward wall flows parallel to the axially forward.

### Claim 4 (depends on 1)

The device according to claim 1, wherein the ribs extend from the axially rearward wall into the bleed air duct and, at the same time, are profiled in such a way that the bleed air flow in the bleed air duct undergoes a greater deflection adjacent to the axially rearward wall than at tips of the ribs.

### Claim 5 (depends on 4)

The device according to claim 4, wherein the ribs are profiled in such a way that the bleed air flow in the bleed air duct undergoes no deflection or a relatively slight deflection at the tips of the ribs.

### Claim 6 (depends on 1)

The device according to claim 1, wherein the bleed air duct is shaped as an annular gap.