# US 10,371,173 B2 · Liner for a gas turbine engine

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- Number: US 10,371,173 B2
- Document ID: US10371173B2
- Status: Granted
- Kind: B2
- Application number: 14/706,259
- Filed: 2015-05-07
- Published: 2016-11-10
- Granted: 2019-08-06
- Earliest claimed: 2015-05-07
- Assignees: United Technologies Corporation
- Applicants: United Technologies Corporation
- Inventors: Michaela M. Logue; Oliver V. Atassi
- Web page: https://patentgrep.com/patent/US10371173B2

## CPC

- F04D 29/668: {damping or preventing mechanical vibrations}
- F01D 25/04: Antivibration arrangements
- F01D 25/162: {Bearing supports}
- F02C 7/045: having provisions for noise suppression
- F02K 1/08: by axially moving or transversely deforming an internal member, e.g. the exhaust cone
- F02K 1/827: {Sound absorbing structures or liners}
- F02K 3/06: with front fan
- F04D 29/526: {Details of the casing section radially opposing blade tips (ducts F04D29/545)}
- F04D 29/541: {Specially adapted for elastic fluid pumps (F04D29/56 takes precedence)}
- F05D 2220/36: specially adapted for the fan of turbofan engines
- F05D 2240/12: Fluid guiding means, e.g. vanes
- F05D 2250/283: honeycomb
- F05D 2260/96: Preventing, counteracting or reducing vibration or noise
- F05D 2260/963: by Helmholtz resonators
- 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)
- 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)
- F02K: JET-PROPULSION PLANTS (features of jet-propulsion plants common to gas-turbine plants, air intakes or fuel supply control of air-breathing jet-propulsion plants F02C7/00, F02C9/00)
- F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS

## Abstract

A gas turbine engine is provided having a fan case and a translating sleeve positioned downstream from the fan case. A flow channel extends between the fan case and the translating sleeve. The flow channel includes an inner diameter and an outer diameter. A structural guide vane is positioned within the flow channel and extends from the inner diameter to the outer diameter. A liner is positioned between an aft end of the fan case and an aft end of the translating sleeve to reduce vibratory stress on the structural guide vane.

## Claims

### Claim 1

A gas turbine engine comprising:
a fan case, a translating sleeve positioned downstream in a direction of flow from the fan case,
a flow channel extending axially between the fan case and the translating sleeve, the flow channel including a plurality of walls including an inner diameter wall and an outer diameter wall, and a structural guide vane positioned within the flow channel and extending from the inner diameter wall to the outer diameter wall; and
a plurality of liner patches on one or both of the plurality of walls for covering a discrete portion of the one or both of the plurality of walls, the plurality of liner patches being mutually independent and individual vibration attenuating liner patches, the plurality of liner patches positioned aft of the fan case, proximate in the direction of flow to the structural guide vane and distal in the direction of flow to the fan case and the translating sleeve, and the plurality of liner patches being mutually spaced in the direction of flow along the flow channel so that the plurality of liner patches are mutually nonabutting, and
wherein the plurality of liner patches reduce vibratory stress on the structural guide vane, the liner having a thickness capable of attenuating vibrations having a frequency of less than 1,000 Hertz.

### Claim 2 (depends on 1)

The gas turbine engine of claim 1, wherein at least one of the plurality of liner patches is positioned upstream of the structural guide vane and along the outer diameter of the flow channel.

### Claim 3 (depends on 1)

The gas turbine engine of claim 1, wherein at least one of the plurality of liner patches is positioned downstream of the structural guide vane and along the inner diameter of the flow channel adjacent to the structural guide vane.

### Claim 4 (depends on 1)

The gas turbine engine of claim 1, wherein at least one of the plurality of liner patches is positioned upstream or downstream of the structural guide vane and along the outer diameter of the flow channel adjacent to the structural guide vane.

### Claim 5 (depends on 1)

The gas turbine engine of claim 1, wherein the inner diameter of the flow channel includes an inner diameter splitter, at least one of the plurality of liner patches is positioned upstream of the structural guide vane and along the inner diameter splitter.

### Claim 6 (depends on 1)

The gas turbine engine of claim 1, wherein at least one of the plurality of liner patches is positioned downstream of the structural guide vane, upstream of the translating sleeve and along the outer diameter of the flow channel.

### Claim 7 (depends on 1)

The gas turbine engine of claim 1, further comprising an inner fixed structure extending along the inner diameter of the flow channel, and wherein at least one of the plurality of liner patches is positioned downstream of the structural guide vane and along the inner fixed structure.

### Claim 8

A method of reducing vibratory stress on a structural guide vane in a gas turbine engine,
wherein the gas turbine engine includes:
a fan case, a translating sleeve positioned downstream in a direction of flow from the fan case,
a flow channel extending axially between the fan case and the translating sleeve, the flow channel including a plurality of walls including an inner diameter wall and an outer diameter wall, and the structural guide vane positioned within the flow channel and extending from the inner diameter wall to the outer diameter wall; and
the structural guide vane extending between an inner diameter and outer diameter of a flow channel, the flow channel extending axially between a fan case and a translating sleeve,
the method comprising:
positioning a plurality of liner patches on one or both of the plurality of walls for covering a discrete portion of the one or both of the plurality of walls, the plurality of liner patches being mutually independent and individual vibration attenuating liner patches, the plurality of liner patches positioned aft of the fan case, proximate in the direction of flow to the structural guide vane and distal in the direction of flow to the fan case and the translating sleeve, and the plurality of liner patches being mutually spaced in the direction of flow along the flow channel so that the plurality of liner patches are mutually nonabutting, and
wherein the plurality of liner patches reduce vibratory stress on the structural guide vane, the liner having a thickness capable of attenuating vibrations having a frequency of less than 1.000 Hertz.

### Claim 9 (depends on 8)

The method of claim 8, wherein the method further comprises positioning the at least one of the plurality of liner patches upstream of the structural guide vane and along the outer diameter of the flow channel.

### Claim 10 (depends on 8)

The method of claim 8, wherein the method further comprises positioning at least one of the plurality of the liner patches downstream of and adjacent to the structural guide vane and along the inner diameter of the flow channel.

### Claim 11 (depends on 8)

The method of claim 8, wherein the method further comprises positioning at least one of the plurality of the liner patches upstream or downstream of, and adjacent to the structural guide vane and along the outer diameter of the flow channel.

### Claim 12 (depends on 8)

The method of claim 8, wherein the inner diameter of the flow channel includes an inner diameter splitter, the method further comprising positioning at least one of the plurality of the liner patches upstream of the structural guide vane and along the inner diameter splitter.

### Claim 13 (depends on 8)

The method of claim 8, wherein the method further comprises positioning at least one of the plurality of liner patches downstream of the structural guide vane, upstream of the translating sleeve and along the outer diameter of the flow channel.

### Claim 14 (depends on 8)

The method of claim 8, wherein the gas turbine engine includes an inner fixed structure extending along the inner diameter of the flow channel, and the method further comprises positioning at least one of the plurality of liner patches downstream of the structural guide vane and along the inner fixed structure.