# US 10,865,650 B2 · Stator vane support with anti-rotation features

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- Number: US 10,865,650 B2
- Document ID: US10865650B2
- Status: Granted
- Kind: B2
- Application number: 15/702,564
- Filed: 2017-09-12
- Published: 2019-03-14
- Granted: 2020-12-15
- Earliest claimed: 2017-09-12
- Assignees: Raytheon Technologies Corporation
- Applicants: United Technologies Corporation
- Inventors: Michael S. Stevens; Tomasz Pelic
- Web page: https://patentgrep.com/patent/US10865650B2

## CPC

- F01D 9/042: {fixing blades to stators (fixing stator-rings in the casing or to each other F01D25/246)}
- F01D 9/041: {using blades (F01D5/148 takes precedence)}
- F01D 25/246: {Fastening of diaphragms or stator-rings}
- F05D 2220/32: in gas turbines
- F05D 2230/642: using maintaining alignment while permitting differential dilatation
- F05D 2240/12: Fluid guiding means, e.g. vanes
- F05D 2260/30: Retaining components in desired mutual position
- 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 stator vane support with anti-rotation features is provided. The stator vane support may comprise an inner diameter surface opposite an outer diameter surface. The stator vane support may comprise an anti-rotation lug defining a protrusion extending inward from the inner diameter surface. The stator vane support may have a first recess defining a first void on the inner diameter surface proximate a first surface of the anti-rotation lug. The stator vane support may have a second recess defining a second void on the inner diameter surface proximate a second surface of the anti-rotation lug. The anti-rotation lug may be configured to interface with a stator vane to at least partially limit circumferential movement, and each recess may be configured to allow the stator vane to thermally expand during gas turbine engine operation.

## Claims

### Claim 1

A turbine assembly, comprising:
a plurality of stator vanes, each stator vane in the plurality of stator vanes being monolithic, each stator vane in the plurality of stator vanes comprising:
a base coupled to an inner engine structure;
a vane; and
an anti-rotation end disposed radially outward from the base, the vane extending from the base to the anti-rotation end, the anti-rotation end defining a radially outer surface, the anti-rotation end comprising a first protrusion extending radially outward from the radially outer surface, a second protrusion extending radially outward from the radially outer surface and disposed circumferentially adjacent to each first protrusion, and an anti-rotation recess defining an anti-rotation void, the anti-rotation recess disposed between, and defined by, each first protrusion and each second protrusion; and
a vane support, comprising:
an inner diameter surface opposite an outer diameter surface;
a plurality of anti-rotation lugs, each anti-rotation lug defining a protrusion extending from the inner diameter surface, wherein each anti-rotation lug comprises a first surface opposite a second surface, wherein each anti-rotation lug is configured to interface with the anti-rotation end of an adjacent stator vane in the plurality of stator vanes, and wherein each anti-rotation lug is disposed within the anti-rotation recess of the adjacent stator vane and between each first protrusion and each second protrusion of the adjacent stator vane;
a plurality of first recesses, each first recess defining a first void on the inner diameter surface proximate the first surface of an adjacent anti-rotation lug in the plurality of anti-rotation lugs, each first recess having a first inner surface; and
a plurality of second recesses, each second recess defining a second void on the inner diameter surface proximate the second surface of the adjacent anti-rotation lug in the plurality of anti-rotation lugs, each second recess having a second inner surface, wherein:
the first inner surface of each first recess and the second inner surface of each second recess comprise a hemispherical shaped surface relative to the inner diameter surface, and
each stator vane in the plurality of stator vanes is configured to thermally expand in a radial direction relative to the base and reduce a gap between the anti-rotation void of each stator vane in the plurality of stator vanes and an adjacent anti-rotation lug.

### Claim 2 (depends on 1)

The turbine assembly of claim 1, wherein each anti-rotation lug of the vane support is configured to interface with each anti-rotation void of each stator vane to at least partially limit rotation of each stator vane relative to the vane support.

### Claim 3 (depends on 2)

The turbine assembly of claim 2, wherein in response to each anti-rotation lug interfacing with each anti-rotation void, each first protrusion is configured to interface with each first recess and each second protrusion is configured to interface with each second recess.

### Claim 4 (depends on 1)

The turbine assembly of claim 1, wherein the vane support comprises a first support recess thickness defining a first distance from the first inner surface of each first recess to the outer diameter surface, and wherein the first support recess thickness comprises at least a minimum thickness.

### Claim 5 (depends on 4)

The turbine assembly of claim 4, wherein each first recess is sized and shaped to maintain the minimum thickness of the first support recess thickness.

### Claim 6 (depends on 1)

The turbine assembly of claim 1, wherein the vane support comprises a second support recess thickness defining a second distance from the second inner surface of each second recess to the outer diameter surface, and wherein the second support recess thickness comprises at least a minimum thickness.

### Claim 7 (depends on 6)

The turbine assembly of claim 6, wherein each second recess is sized and shaped to maintain the minimum thickness of the second support recess thickness.

### Claim 8

A gas turbine engine, comprising:
a compressor section; and
a turbine section, wherein the turbine section comprises:
a plurality of stator vanes, each stator vane in the plurality of stator vanes being monolithic, each stator vane in the plurality of stator vanes comprising:
a base coupled to an inner engine structure;
a vane;
an anti-rotation end disposed radially outward from the base, the vane extending from the base to the anti-rotation end, the anti-rotation end defining a radially outer surface, the anti-rotation end comprising a first protrusion extending radially outward from the radially outer surface, a second protrusion extending radially outward from the radially outer surface and disposed circumferentially adjacent to each first protrusion, and an anti-rotation recess defining an anti-rotation void, the anti-rotation recess disposed between, and defined by, each first protrusion and each second protrusion; and
a vane support, comprising:
an inner diameter surface opposite an outer diameter surface;
a plurality of anti-rotation lugs, each anti-rotation lug defining a protrusion extending from the inner diameter surface, wherein each anti-rotation lug comprises a first surface opposite a second surface, wherein each anti-rotation lug is configured to interface with the anti-rotation end of an adjacent stator vane in the plurality of stator vanes, and wherein each anti-rotation lug is disposed within the anti-rotation recess of the adjacent stator vane and between each first protrusion and each second protrusion of the adjacent stator vane;
a plurality of first recesses, each first recess defining a first void on the inner diameter surface proximate the first surface of an adjacent anti-rotation lug in the plurality of anti-rotation lugs, each first recess having a first inner surface; and
a plurality of second recesses, each second recess defining a second void on the inner diameter surface proximate the second surface of the adjacent anti-rotation lug, each second recess having a second inner surface, wherein:
the first inner surface of each first recess and the second inner surface of each second recess comprise a hemispherical shaped surface relative to the inner diameter surface, and
each stator vane in the plurality of stator vanes is configured to thermally expand in a radial direction relative to the base and reduce a gap between the anti-rotation void of each stator vane in the plurality of stator vanes and an adjacent anti-rotation lug.

### Claim 9 (depends on 8)

The gas turbine engine of claim 8, wherein each anti-rotation lug of the vane support is configured to interface with each anti-rotation void of each stator vane to at least partially limit rotation of each stator vane relative to the vane support.

### Claim 10 (depends on 9)

The gas turbine engine of claim 9, wherein in response to each anti-rotation lug interfacing with each anti-rotation void, each first protrusion is configured to interface with each first recess and each second protrusion is configured to interface with each second recess.