# US 10,502,083 B2 · Turbomachine element comprising an auxiliary sealing means, and method for testing this element

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- Number: US 10,502,083 B2
- Document ID: US10502083B2
- Status: Granted
- Kind: B2
- Application number: 15/320,937
- Filed: 2015-07-21
- Published: 2017-06-01
- Granted: 2019-12-10
- Earliest claimed: 2014-07-29
- Assignees: Safran Aircraft Engines
- Applicants: Safran Aircraft Engines
- Inventors: Florence Irène Noëlle Leutard; Thibault Jamon; Olivier Renon
- Web page: https://patentgrep.com/patent/US10502083B2

## CPC

- F01D 11/10: using sealing fluid, e.g. steam
- F01D 5/02: Blade-carrying members, e.g. rotors (rotors of non-bladed type F01D1/34; stators F01D9/00 {; selecting particular materials F01D5/28})
- F01D 5/026: {Shaft to shaft connections}
- F01D 9/04: forming ring or sector
- F01D 21/003: {Arrangements for testing or measuring (for measuring vibrations G01H)}
- F01D 25/16: Arrangement of bearings; Supporting or mounting bearings in casings (bearings per se F16C)
- F01D 25/166: {Sliding contact bearing (gas bearings F01D25/22)}
- F01D 25/186: {for sliding contact bearing}
- F02C 7/28: Arrangement of seals
- F05D 2220/30: in turbines
- F05D 2240/54: Radial bearings
- F05D 2260/83: Testing, e.g. methods, components or tools therefor
- 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)
- F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS

## Abstract

A turbomachine element includes a stator, a rotor, and a first sealing means for sealing between the rotor and the stator. The element is arranged to be active when the rotor is in the operating position of same around the axis of rotation thereof. The element includes an auxiliary pressure sealing means, sealing between the rotor and the stator and is arranged so that the two sealing means are active when the rotor is placed along the axis of rotation thereof during an assembly operation in a test position. In the test position, the rotor and the stator form an enclosure between said two sealing means.

## Claims

### Claim 1

A turbine engine element comprising a stator, a rotor, and a first sealing means between the rotor and the stator which is arranged so as to be active when the rotor is in an operating position around an axis of rotation of said rotor, wherein the turbine engine element comprises an auxiliary pressurized sealing means, between the rotor and the stator, wherein the element is arranged so that said first sealing means and said auxiliary pressurized sealing means are active when the rotor is placed along the axis of rotation of said rotor during a process of mounting in a test position, the rotor and the stator forming, in said test position, an enclosure between said first sealing means and said auxiliary pressurized sealing means, and wherein the auxiliary pressurized sealing means is arranged so as to be or become inactive when the rotor is placed in an operating position.

### Claim 2 (depends on 1)

The turbine engine element according to claim 1, wherein the auxiliary pressurized sealing means is arranged so as to be inactive before any operation of the turbine engine element.

### Claim 3 (depends on 2)

The turbine engine element according to claim 2, wherein the auxiliary pressurized sealing means comprises a pressurized sealing joint which is rigidly connected to one of the bodies among the rotor or the stator and is arranged so as to rest on a first cylindrical sealing surface when the rotor is in a test position which is axially offset by a distance which is determined with respect to the operating position and so as to be removed from said first cylindrical sealing surface when the rotor is in the operating position.

### Claim 4 (depends on 3)

The turbine engine element according to claim 3, further comprising a bearing between the stator and the rotor, said bearing comprising roller bearings between a first ring and a second ring, one of said first ring and said second ring being rigidly connected to the stator, and the other being rigidly connected to the rotor, wherein the first ring allows the rolling bearings to slide axially, and wherein the axial extension of said first ring is arranged so as to act as a surface for guiding the rotor along the axis of rotation during a movement from the operating position to the test position or inversely.

### Claim 5 (depends on 3)

The turbine engine element according to claim 3, wherein the rotor is arranged so as to be mounted in the stator in a mounting direction along the axis of rotation, and the test position is located before the operating position along said mounting direction.

### Claim 6 (depends on 1)

The turbine engine element according to claim 1, wherein the auxiliary pressurized sealing means is arranged so as to be inactive during a first operation when the rotor rotates at a speed which is at least equal to a predetermined value.

### Claim 7 (depends on 6)

The turbine engine element according to claim 6, wherein the auxiliary pressurized sealing means comprises a pressurized sealing joint which is rigidly connected to one of the bodies among the rotor or the stator and is arranged so as to rest on a second cylindrical sealing surface when the rotor is fixed in rotation with respect to the stator and so as to be removed when the rotor is set into rotation.

### Claim 8 (depends on 1)

The turbine engine element according to claim 1, wherein the stator and the rotor are arranged so as to form an enclosure for lubricating a device which is located axially between said first sealing means and said auxiliary pressurized sealing mean when the rotor is in the operating position thereof.

### Claim 9 (depends on 1)

The turbine engine element according to claim 1, wherein the first sealing means comprises a radial pressurized sealing joint, for example a segmented radial joint, which is rigidly connected to one of the bodies among the rotor or the stator and is arranged so as to rest on a third cylindrical sealing surface, which is rigidly connected to the other body, when said first means is active.

### Claim 10 (depends on 1)

A turbine engine comprising an element according to claim 1.