# US 10,309,419 B2 · Turbomachine centre blade comprising a curved portion

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- Number: US 10,309,419 B2
- Document ID: US10309419B2
- Status: Granted
- Kind: B2
- Application number: 14/349,000
- Filed: 2012-10-11
- Published: 2014-09-04
- Granted: 2019-06-04
- Earliest claimed: 2011-10-13
- Assignees: Safran Aircarft Engines
- Applicants: Safran Aircarft Engines
- Inventors: Damien Cellier; Alicia Lise Julia Dufresne; Philippe Pierre Marcel Marie Pelletrau; Vincent Paul Gabriel Perrot; Jean-Francois Antoine Christian Rios; Laurent Christophe Francis Villaines
- Web page: https://patentgrep.com/patent/US10309419B2

## CPC

- F04D 29/661: {especially adapted for elastic fluid pumps}
- F01D 5/141: {Shape, i.e. outer, aerodynamic form (F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147)}
- F01D 5/16: for counteracting blade vibration
- F01D 9/041: {using blades (F01D5/148 takes precedence)}
- F04D 29/324: {Blades}
- F04D 29/403: {especially adapted for elastic fluid pumps}
- F05D 2260/96: Preventing, counteracting or reducing vibration or noise
- F04D: NON-POSITIVE-DISPLACEMENT PUMPS (engine fuel-injection pumps F02M; ion pumps H01J41/12; electrodynamic pumps H02K44/02)
- 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 turbomachine compressor blade of main radial orientation with respect to a main axis of the turbomachine. The blade includes a radially internal root portion, a radially external tip portion, a radially intermediate portion, a curved portion tangentially in a direction, and at least one straight portion on the root portion and/or on the tip portion.

## Claims

### Claim 1

A turbomachine compressor blade of main radial orientation with respect to a main axis of the turbomachine, the blade comprising:
a radially internal root portion;
a radially external tip portion;
a radially intermediate portion;
a curved portion perpendicularly to a main axial plane of the blade in a direction; and
at least one straight portion on at least one of the root portion and the tip portion,
wherein a tangential amplitude of the curved portion is between 1% and 5% of a radial length of the blade, and
wherein, when the blade is at rest, the straight portion is inclined by a non-zero angle less than or equal to 30° with respect to a main radial direction of the blade.

### Claim 2 (depends on 1)

A blade as claimed in claim 1, wherein a radial length of the curved portion is between 30% and 60% of the radial length of the blade.

### Claim 3 (depends on 1)

A blade as claimed in claim 1, wherein the curved portion is positioned radially on the root portion.

### Claim 4

A blade according to 1, wherein the curved portion is positioned radially on the tip portion.

### Claim 5 (depends on 1)

A blade according to claim 1, wherein the curved portion is positioned radially on the intermediate portion.

### Claim 6 (depends on 1)

A blade as claimed in claim 1, wherein the curved portion is tangentially curved in a direction of intrados of the blade.

### Claim 7 (depends on 1)

A turbomachine compressor stator comprising:
radial blades distributed around the main axis of the turbomachine,
wherein each blade is a blade as claimed in claim 1.

### Claim 8 (depends on 7)

A turbomachine comprising a stator that comprises blades as claimed in claim 7.