# US 11,905,889 B2 · Aircraft turbomachine with reducer

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- Number: US 11,905,889 B2
- Document ID: US11905889B2
- Status: Granted
- Kind: B2
- Application number: 17/278,617
- Filed: 2019-09-19
- Published: 2022-02-10
- Granted: 2024-02-20
- Earliest claimed: 2018-09-24
- Assignees: Safran Aircraft Engines
- Applicants: Safran Aircraft Engines
- Inventors: Marion Jeanne Pierrette Verdier; Yanis Benslama; Michel Gilbert Roland Brault; Romain Guillaume Cuvillier; Serge René Morreale
- Web page: https://patentgrep.com/patent/US11905889B2

## CPC

- F02C 7/36: Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user ({F02C3/107 - F02C3/13 and} F02C7/32 take precedence; couplings for transmitting rotation F16D; gearing in general F16H)
- F01D 15/12: Combinations with mechanical gearing (driven by multiple engines F01D13/00)
- F02K 3/06: with front fan
- F01D 5/026: {Shaft to shaft connections}
- F01D 25/16: Arrangement of bearings; Supporting or mounting bearings in casings (bearings per se F16C)
- F02C 3/10: with another turbine driving an output shaft but not driving the compressor
- F02C 3/107: with two or more rotors connected by power transmission
- F02C 3/113: with variable power transmission between rotors
- F02C 7/06: Arrangements of bearings (bearings F16C); Lubricating ({of turbo machines F01D25/18; of machines or} engines in general F01M)
- F05D 2220/30: in turbines
- F05D 2240/50: Bearings
- F05D 2240/54: Radial bearings
- F05D 2240/60: Shafts
- F05D 2250/36: in inner-outer relationship, e.g. shaft-bearing arrangements
- F05D 2260/40311: of the epicyclical, planetary or differential type
- F05D 2270/023: of different spools or shafts
- 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)
- F02K: JET-PROPULSION PLANTS (features of jet-propulsion plants common to gas-turbine plants, air intakes or fuel supply control of air-breathing jet-propulsion plants F02C7/00, F02C9/00)
- F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS

## Abstract

A turbomachine includes a single ducted fan including a first shaft rotated by a second shaft via a speed reduction gearset, the second shaft being rotated by a third shaft of a turbine, the first shaft being guided in rotation with respect to a fixed structure via a first bearing and a second bearing placed upstream of the speed reduction gearset. The second shaft is guided in rotation with respect to the first shaft via a rolling bearing placed upstream of the speed reduction gearset, the rolling bearing comprising an outer ring housed in the first shaft, an inner ring connected to the second shaft and rolling elements arranged between the inner and outer rings.

## Claims

### Claim 1

A turbomachine with an axis of rotation, comprising: a single ducted fan comprising a first shaft carrying blades and driven in rotation by a second shaft via a speed reducer, said second shaft being driven in rotation by a third shaft of a turbine, said first, second and third shafts sharing the axis of rotation, said first shaft being guided in rotation with respect to a fixed structure of the turbomachine via a first bearing and a second bearing located upstream of said speed reducer, wherein the second shaft is guided in rotation with respect to the first shaft via a third rolling bearing located upstream of said speed reducer, said third rolling bearing comprising an outer ring housed in said first shaft, an inner ring attached to said second shaft, and rolling elements disposed between said inner and outer rings.

### Claim 2 (depends on 1)

The turbomachine according to claim 1, further comprising sealing means located upstream of said third bearing and configured to ensure tightness between said first shaft and said second shaft.

### Claim 3 (depends on 2)

The turbomachine according to claim 2, wherein said sealing means comprise a first member and a second member, said first member comprising at least one annular lip in radial contact with an abradable ring of said second member.

### Claim 4 (depends on 3)

The turbomachine according to claim 3, wherein the first member comprises a collar attached to said second shaft, said collar being disposed axially between axial holding means and either said inner ring or a ledge made in said second shaft.

### Claim 5 (depends on 3)

The turbomachine according to claim 3, wherein the second member comprises a flange located in a housing of said first shaft between said outer ring and a shoulder made in said housing.

### Claim 6 (depends on 1)

The turbomachine according to claim 1, wherein said second shaft is rotationally coupled to said speed reducer via first coupling means, said second shaft being rotationally coupled to a fourth shaft of a compressor via second coupling means disposed downstream of said speed reducer, said fourth shaft being rotationally coupled to said third shaft.

### Claim 7 (depends on 6)

The turbomachine according to claim 6, wherein said second shaft comprises an inner portion and an outer portion centred on the axis of rotation, the inner portion and the outer portion being rotationally coupled to each other via third coupling means disposed upstream of said third bearing, said outer portion being rotationally coupled to said speed reducer via the first coupling means, said inner ring being attached to said outer portion, said inner portion being rotationally coupled to the fourth shaft via the second coupling means.

### Claim 8 (depends on 7)

The turbomachine according to claim 7, wherein said third coupling means have an angular deflection.

### Claim 9 (depends on 1)

The turbomachine according to claim 1, wherein said second shaft comprises elastically deformable means axially disposed downstream of said speed reducer.

### Claim 10 (depends on 9)

The turbomachine according to claim 9, wherein said elastically deformable means comprise a first elastically deformable device and a second elastically deformable device located in series.

### Claim 11 (depends on 1)

The turbomachine according to claim 1, further comprising a nozzle disposed downstream of said speed reducer, said nozzle comprising an outlet for injecting a liquid lubricant into an internal cavity formed in said second shaft, the turbomachine further comprising conveying means of said lubricant configured to convey said lubricant from said cavity to the third bearing.

### Claim 12 (depends on 1)

The turbomachine according to claim 1, wherein said first and second bearings each comprise an inner ring connected to said first shaft, an outer ring connected to said fixed structure of the turbomachine, and rolling elements between said inner and outer rings.