# US 10,502,080 B2 · Rotating labyrinth M-seal

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- Number: US 10,502,080 B2
- Document ID: US10502080B2
- Status: Granted
- Kind: B2
- Application number: 14/684,035
- Filed: 2015-04-10
- Published: 2016-10-13
- Granted: 2019-12-10
- Earliest claimed: 2015-04-10
- Assignees: United Technologies Corporation
- Applicants: United Technologies Corporation
- Inventors: David E. Gambardella; Nicholas W. Oren
- Web page: https://patentgrep.com/patent/US10502080B2

## CPC

- F01D 11/02: by non-contact sealings, e.g. of labyrinth type (for sealing space between rotor blade tips and stator F01D11/08)
- F01D 5/225: {by shrouding}
- F04D 29/083: {especially adapted for elastic fluid pumps}
- F04D 29/321: {for axial flow compressors}
- F16J 15/447: Labyrinth packings
- F05D 2220/32: in gas turbines
- F05D 2240/55: Seals
- F05D 2250/183: zigzag
- F05D 2250/232: conical
- F05D 2250/75: given by its similarity to a letter, e.g. T-shaped
- F05D 2260/941: particularly aimed at mechanical or thermal stress reduction
- Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft
- 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)
- F16J: PISTONS {(specially adapted for dampers F16F9/32)}; CYLINDERS; SEALINGS
- F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION

## Abstract

Aspects of the disclosure are directed to a seal associated with an engine of an aircraft. The seal includes a plurality of lands, and a barrel coupled to the lands and formed from a plurality of segments, where the segments are coupled to one another such that the barrel is substantially non-linear.

## Claims

### Claim 1

A seal for a gas turbine engine, comprising:
a plurality of lands;
a barrel coupled to the lands and formed from a plurality of segments; and
a plurality of knife edge seals coupled to the plurality of segments, the plurality of knife edge seals extending in a first radial direction so that at least one knife edge seal of the plurality of knife edge seals is disposed radially above at least one land of the plurality of lands,
where the segments are coupled to one another such that the barrel is substantially non-linear,
wherein a first of the plurality of segments and a second of the plurality of segments between the knife edge seals together form a ‘V’-shape, the ‘V’-shape extending in a second radial direction so that a peak of the ‘V’-shape is disposed radially below at least one land of the plurality of lands, and where the barrel is substantially ‘M’-shaped, and
wherein the seal is configured to open on both of a first end and an opposing second end of the seal when the seal rotates.

### Claim 2 (depends on 1)

The seal of claim 1, wherein at least one of the segments is of a non-uniform width.

### Claim 3 (depends on 1)

The seal of claim 1, wherein at least one of the segments is tapered in terms of width.

### Claim 4 (depends on 1)

The seal of claim 1, wherein the barrel is substantially symmetrical in terms of shape.

### Claim 5 (depends on 1)

The seal of claim 1, wherein the barrel is substantially asymmetrical in terms of shape.

### Claim 6 (depends on 5)

The seal of claim 5, wherein a first length associated with a first of the segments is different from a second length associated with a second of the segments.

### Claim 7 (depends on 5)

The seal of claim 5, wherein a first orientation associated with a first of the segments is different from a second orientation associated with a second of the segments.

### Claim 8 (depends on 1)

The seal of claim 1, wherein the segments form a plurality of non-linear portions.

### Claim 9 (depends on 1)

The seal of claim 1, wherein the lands are configured to interface a first section of the engine to a second section of the engine.

### Claim 10 (depends on 9)

The seal of claim 9, wherein the seal interfaces a low pressure turbine section and a high pressure turbine section.

### Claim 11 (depends on 9)

The seal of claim 9, wherein the seal interfaces a low pressure compressor section and a high pressure compressor section.

### Claim 12 (depends on 1)

The seal of claim 1, wherein a ratio of a diameter of at least one of the lands to a length of the seal is within a range of 4:1 to 14:1.

### Claim 13 (depends on 12)

The seal of claim 12, wherein a ratio of a diameter of at least one of the lands to a thickness of at least one of the segments is within a range of 240:1 to 500:1.

### Claim 14 (depends on 1)

The seal of claim 1, wherein a ratio of a length of the seal to a height of at least one of the segments is within a range of 3:1 to 12:1.

### Claim 15 (depends on 1)

The seal of claim 1, wherein a ratio of a length of the seal to a radius is within a range of 6:1 to 60:1.

### Claim 16 (depends on 1)

The seal of claim 1, wherein a V-angle associated with the seal assumes a value within a range of forty degrees and one-hundred twenty degrees.

### Claim 17 (depends on 1)

The seal of claim 1, wherein the gas turbine engine has an axial centerline, and wherein the seal opens axially with respect to the centerline on the first end of the seal when the seal rotates.

### Claim 18 (depends on 1)

The seal of claim 1, wherein the seal springs open when the seal rotates.

### Claim 19 (depends on 14)

The seal of claim 14, wherein a ratio of a length of the seal to a radius is within a range of 6:1 to 60:1.