# US 11,078,801 B2 · Air-gap fins for a turbine engine compressor

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- Number: US 11,078,801 B2
- Document ID: US11078801B2
- Status: Granted
- Kind: B2
- Application number: 16/519,875
- Filed: 2019-07-23
- Published: 2020-01-30
- Granted: 2021-08-03
- Earliest claimed: 2018-07-24
- Assignees: Safran Aircraft Engines
- Applicants: Safran Aircraft Engines
- Inventors: Damien Bernard Emeric Guegan; Sébastien Claude Cochon; Pierre-Hugues Ambroise Maxime Victor Retiveau
- Web page: https://patentgrep.com/patent/US11078801B2

## CPC

- F01D 9/041: {using blades (F01D5/148 takes precedence)}
- F01D 11/001: {for sealing space between stator blade and rotor}
- F01D 5/143: {Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour}
- 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})
- F04D 29/164: {of an axial flow wheel}
- F04D 29/542: {Bladed diffusers (fixing blades to stators F01D9/042)}
- F05D 2240/50: Bearings
- F05D 2240/80: Platforms for stationary or moving blades
- F05D 2250/90: Variable geometry
- 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

A vane stage with a longitudinal axis designed to be fitted in a turbine engine compressor. The van stage has an annular row of mobile vanes arranged upstream from an annular row of stator vanes. The annular row of stator vanes has a radially internal annular platform bearing radial blades, an upstream annular portion of which is arranged upstream from the blades and is surrounded radially outwards by a downstream annular portion of an annular platform of the upstream row of mobile vanes. The upstream annular portion of the annular platform of the annular row of stator vanes has a radially external annular face from which fins extend, which are distributed around the longitudinal axis and extend radially outwards towards the downstream annular portion of the platform of the annular row of mobile vanes.

## Claims

### Claim 1

A vane stage extending around a longitudinal axis and designed to be fitted in a turbine engine compressor, the vane stage comprising an annular row of mobile vanes arranged upstream from an annular row of stator vanes, wherein the annular row of stator vanes comprises a radially internal annular platform bearing radial blades, an upstream annular portion of which is arranged upstream from said blades and is surrounded radially outwards by a downstream annular portion of an annular platform of the upstream row of mobile vanes, wherein the upstream annular portion of the annular platform of the annular row of stator vanes comprises a radially external annular face from which fins extend, said fins are distributed around the longitudinal axis and extend radially outwards towards the downstream annular portion of the platform of the annular row of mobile vanes, characterised in that the fins each comprise an intrados face and an extrados face oriented circumferentially in an identical manner to the intrados faces and extrados faces of the blades of the stator vanes.

### Claim 2 (depends on 1)

The vane stage of claim 1, wherein an angle between the longitudinal axis and the tangent to the mean camber line at the leading edge of the fins is between 45° and 90°.

### Claim 3 (depends on 1)

The vane stage of claim 1, wherein an angle between the longitudinal axis and the tangent to the mean camber line at the trailing edge of the fins is on the order of the leading angle between the longitudinal axis and the tangent to the mean camber line at the leading edge of a blade in the row of stator vanes.

### Claim 4 (depends on 3)

The vane stage of claim 3, wherein the angle is between 10° and 75°.

### Claim 5 (depends on 1)

The vane stage of claim 1, wherein the external annular face of the upstream annular portion is tapered with a section increasing in the downstream direction.

### Claim 6 (depends on 5)

The vane stage of claim 5, wherein said annular face is inclined by an alpha angle relative to the longitudinal axis of between 0° and 90°.

### Claim 7 (depends on 1)

The vane stage of claim 1, wherein the relative pitch defined by the ratio S/C is between 0.3 and 0.9, where S is the distance between two leading edges of two circumferentially adjacent fins and C is the string of a fin.

### Claim 8 (depends on 1)

A turbine engine compressor comprising at least one stage of claim 1, wherein a downstream annular row of mobile vanes is arranged axially downstream from the annular row of stator vanes and is connected to the annular row of mobile vanes upstream by means of an annular shroud extending radially inside the annular row of stator vanes and bearing lips sealedly interacting with a ring of abradable material borne by a radially internal annular platform of the annular row of stator vanes.

### Claim 9 (depends on 8)

A turbine engine comprising the compressor of claim 8.

### Claim 10 (depends on 1)

The vane stage of claim 1, wherein the angle between the longitudinal axis and the tangent to the mean camber line at the leading edge of the fins is on the order of 85°.

### Claim 11 (depends on 3)

The vane stage of claim 3, wherein the angle is on the order of 55°.

### Claim 12 (depends on 5)

The vane stage of claim 5, wherein said annular face is inclined by an alpha angle relative to the longitudinal axis of the order of 30°.