# US 8,540,483 B2 · Turbine engine rotating cavity anti-vortex cascade

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- Number: US 8,540,483 B2
- Document ID: US8540483B2
- Status: Granted
- Kind: B2
- Application number: 13/416,414
- Filed: 2012-03-09
- Published: 2012-07-05
- Granted: 2013-09-24
- Earliest claimed: 2009-04-17
- Assignees: United Technologies Corporation
- Applicants: Matthew E. Bintz; Peter T. Schutte; Anthony R. Bifulco; Eric W. Malmborg
- Inventors: Matthew E. Bintz; Peter T. Schutte; Anthony R. Bifulco; Eric W. Malmborg
- Web page: https://patentgrep.com/patent/US8540483B2

## CPC

- F02C 6/08: the gas being bled from the gas-turbine compressor
- F01D 5/087: {in the radial passages of the rotor disc}
- F04D 29/321: {for axial flow compressors}
- 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)
- 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)

## Abstract

A gas turbine engine rotor drum includes spaced apart discs providing a cavity between the discs. The discs are configured to rotate in a rotational direction about an axis. An annular support is mounted on at least one of the discs and within the cavity. A cascade of relatively short anti-vortex members is mounted circumferentially on the annular support. The anti-vortex members include an outer end having a concave surface extending within the cavity radially outward from the annular support. The concave surface faces the rotational direction and promotes swirl as the rotor drum rotates.

## Claims

### Claim 1

An anti-vortex cascade for a gas turbine engine comprising:
an annular support arranged about a rotational axis and including a rotational direction in which the annular support is configured to rotate;
multiple anti-vortex members mounted circumferentially on the annular support, the anti-vortex members including an outer end having a concave surface extending from the axis radially outward from the annular support; and
wherein the annular support includes an aperture arranged between the anti-vortex members configured to permit conditioning air radially inward through the annular support.

### Claim 2 (depends on 1)

The anti-vortex cascade according to claim 1, wherein the concave surface faces opposite the rotational direction.

### Claim 3 (depends on 2)

The anti-vortex cascade according to claim 2, wherein the anti-vortex members are airfoil-shaped and oriented generally radially relative to the rotational axis.

### Claim 4 (depends on 2)

The anti-vortex cascade according to claim 2, wherein anti-vortex members are bent or curved tubes supported in circumferentially spaced openings in the annular support.