# US 10,502,081 B2 · Turbomachine bearing housing

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- Number: US 10,502,081 B2
- Document ID: US10502081B2
- Status: Granted
- Kind: B2
- Application number: 15/110,905
- Filed: 2015-01-15
- Published: 2016-11-24
- Granted: 2019-12-10
- Earliest claimed: 2014-01-23
- Assignees: Safran Aircraft Engines
- Applicants: Snecma
- Inventors: Jérémy Lucien Jacques Bioud; Sébastien Bourget; Gaël Evain; Eddy Stéphane Joël Fontanel; Florence Irène Noëlle Leutard; Christophe Lima; Giuliana Elisa Rossi
- Web page: https://patentgrep.com/patent/US10502081B2

## CPC

- F01D 11/04: using sealing fluid, e.g. steam
- F01D 9/02: Nozzles; Nozzle boxes; Stator blades; Guide conduits {, e.g. individual nozzles (nozzle boxes F01D9/047)}
- F01D 25/162: {Bearing supports}
- F01D 25/183: {Sealing means}
- F02C 7/06: Arrangements of bearings (bearings F16C); Lubricating ({of turbo machines F01D25/18; of machines or} engines in general F01M)
- F05D 2220/32: in gas turbines
- F05D 2240/12: Fluid guiding means, e.g. vanes
- F05D 2240/50: Bearings
- F05D 2240/55: Seals
- F05D 2240/60: Shafts
- F05D 2240/80: Platforms for stationary or moving blades
- F05D 2250/283: honeycomb
- 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 bearing housing comprising a fixed wall, a rotating shaft, first and second seals between the wall and the shaft, and a chamber between the fixed wall and a stator element supplied with air via an opening close to the shaft. An air guide is arranged along the surface of the wall of the housing, outside same, such that at least a portion of the air exiting the guide passes between the first seal and the shaft, the air guide being supplied with air by an air intake separated radially from the shaft, the air from the air intake being at a higher pressure than at the shaft.

## Claims

### Claim 1

A bearing enclosure of a turbine engine, comprising:
a fixed wall;
a rotating shaft;
a first seal and a second seal between the fixed wall and the rotating shaft;
a stator element disposed around the rotating shaft and comprising a first opening positioned adjacent the rotating shaft;
a first chamber disposed between the fixed wall and the stator element, the first chamber being supplied with intake air through the first opening;
an air guide arranged along an external surface of the fixed wall, the air guide defining a pathway supplied with intake air through an orifice positioned in the first chamber in such a way that at least some of the intake air supplied to the orifice exits the air guide through the first seal,
wherein the orifice is arranged at a first distance radially outwardly from the rotating shaft and the first opening so that the intake air supplying the pathway is at a higher pressure than the intake air passing through the first opening.

### Claim 2 (depends on 1)

The enclosure according to claim 1, wherein the air guide comprises a plate which is arranged radially along and at a distance from the fixed wall.

### Claim 3 (depends on 2)

The enclosure according to claim 2, wherein a clearance is provided between the plate and the rotating shaft.

### Claim 4 (depends on 1)

The enclosure according to claim 1, wherein a spacer is disposed between the air guide and a wall portion upstream to the fixed wall, the spacer extending perpendicularly to the rotating shaft, the spacer being in the form of a ring which is perforated by radial holes, is provided with a honeycomb structure, or is provided with fins.

### Claim 5 (depends on 1)

The enclosure according to claim 1, wherein the first seal is a segmented radial seal.

### Claim 6 (depends on 1)

The enclosure according to claim 1, wherein the second seal is a labyrinth seal.

### Claim 7 (depends on 1)

The enclosure according to claim 1, wherein the orifice is positioned in a vortex compression portion of the first chamber.

### Claim 8 (depends on 1)

The enclosure according to claim 1, wherein the first opening is disposed in a lower portion of the first chamber, and the orifice is disposed in an upper portion of the first chamber.

### Claim 9 (depends on 1)

The enclosure according to claim 1, wherein the pathway extends radially between the rotating shaft and an annular output duct, the annular output duct being disposed in an upper portion of the first chamber.

### Claim 10

A turbine engine comprising:
a bearing enclosure, the bearing enclosure including:
a fixed wall;
a rotating shaft;
a first seal and a second seal between the fixed wall and the rotating shaft;
a stator element disposed around the rotating shaft and comprising a first opening positioned adjacent the rotating shaft;
a first chamber disposed between the fixed wall and the stator element, the first chamber being supplied with intake air through the first opening;
an air guide arranged along an external surface of the fixed wall, the air guide defining a pathway supplied with intake air through an orifice positioned in the first chamber in such a way that at least some of the intake air supplied to the orifice exits the air guide through the first seal,
wherein the orifice is arranged at a first distance radially outwardly from the rotating shaft and the first opening so that the intake air supplying the pathway is at a higher pressure than the intake air passing through the first opening, and
wherein the first chamber being located upstream of the fixed wall, and having a second discharge opening which is arranged radially at a distance from the rotating shaft, said orifice being arranged at a second distance from said second discharge opening.

### Claim 11 (depends on 10)

The turbine engine according to claim 10, comprising an annular, second chamber downstream of the fixed wall, which is supplied with intake air from the first chamber.

### Claim 12 (depends on 10)

The turbine engine according to claim 10, wherein the second distance of the second discharge opening is radially farther from the rotating shaft than the orifice.