# US 7,743,598 B2 · Sealing system for the rear lubricating chamber of a jet engine

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- Number: US 7,743,598 B2
- Document ID: US7743598B2
- Status: Granted
- Kind: B2
- Application number: 11/461,614
- Filed: 2006-08-01
- Published: 2007-02-08
- Granted: 2010-06-29
- Earliest claimed: 2005-08-02
- Assignees: Snecma
- Inventors: Jacques Rene Bart; Stephane Rousselin
- Web page: https://patentgrep.com/patent/US7743598B2

## CPC

- F01D 25/18: Lubricating arrangements (of machines or engines in general F01M)
- F01D 25/16: Arrangement of bearings; Supporting or mounting bearings in casings (bearings per se F16C)
- F01D 25/183: {Sealing means}
- F05D 2240/56: Brush seals
- F05D 2260/602: Drainage
- F05D 2260/6022: of leakage having past a seal
- 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)
- 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

A jet engine with a system for recovering oil around the lubricating chamber of the rear rolling bearing of the shaft of the jet engine. The shaft is supported by a rolling bearing situated in a lubricating chamber surrounded by a single recovery chamber having a seal situated downstream from the rotor of the turbine driving the shaft.

## Claims

### Claim 1

A jet engine comprising: a shaft driven by a low pressure turbine superimposed coaxially outside said shaft, said shaft being supported, at a rear, by a rolling bearing situated between said shaft and said low pressure turbine and housed in a lubricating chamber in which an oil mist is receivable, said lubricating chamber comprising an inner rotating part linked to the shaft and an outer fixed part separated by a first annular seal, and
a pressurized recovery chamber, arranged outside said first seal and comprising two parts, a fixed part and a moveable part separated by said first seal, wherein said recovery chamber is a single one and has a second seal, situated radially externally in relation to said first seal and wherein said second seal is situated downstream from the rotor of said turbine, and wherein an oil discharge orifice is provided in the lower part of said recovery chamber.

### Claim 2 (depends on 1)

The jet engine as claimed in claim 1, in which said low pressure turbine comprises a rotor provided with a plurality of axially spaced discs, each having a reinforcing ring in its radially most inner part, wherein said second seal is situated at a radial distance that is greater than that where the ring of the disc that is most downstream in said turbine is situated.

### Claim 3 (depends on 2)

The jet engine as claimed in claim 2, wherein said second seal is located at a radial distance that is greater than a radial distance of a bore of the most downstream ring.

### Claim 4 (depends on 1)

The jet engine as claimed in claim 1, wherein said recovery chamber is the only recovery chamber surrounding the lubricating chamber and said shaft.

### Claim 5 (depends on 2)

The jet engine as claimed in claim 2, wherein said first seal is located radially inward relative to said ring of the disc that is most downstream in said turbine.

### Claim 6 (depends on 1)

The jet engine as claimed in claim 1, wherein said low pressure turbine comprises a rotor provided with a plurality of axially spaced discs, each having a reinforcing ring in its radially most inner part, wherein said first seal is located radially inward relative to a ring of the disc that is most downstream in said turbine.