Structural assembly for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-2022065166-A1
Application number	US-202117382583-A
Country	US
Kind code	A1
Filing date	Jul 22, 2021
Priority date	Aug 25, 2020
Publication date	Mar 3, 2022
Grant date	—

Abstract

The invention regards a structural assembly for a gas turbine engine which includes a bearing with a statically arranged outer ring and a rotatably arranged inner ring, the bearing outer ring including a radially outer surface. The assembly further includes a housing structure supporting the statically arranged outer ring. It is provided that the housing structure forms a housing ring against which the radially outer surface of the bearing outer ring lies and which supports the bearing outer ring radially outwards.

First claim

1 . A structural assembly for a gas turbine engine comprising:
a bearing comprising a statically arranged outer ring and a rotatably arranged inner ring, the bearing outer ring comprising a radially outer surface, a housing structure supporting the statically arranged outer ring, wherein the housing structure forms a housing ring against which the radially outer surface of the bearing outer ring lies and which supports the bearing outer ring radially outwards.

2 . The assembly of claim 1 , wherein the bearing outer ring is axially supported at one axial end by a structure of the housing ring.

3 . The assembly of claim 2 , wherein the structure of the housing ring that axially supports the one axial end of the bearing outer ring comprises a wall at one end of the housing ring that extends radially inward, wherein the one axial end of the bearing outer ring lies against such wall.

4 . The assembly of claim 2 , wherein the structure of the housing ring that axially supports the one axial end of the bearing outer ring comprises a recess in the housing ring.

5 . The assembly of claim 1 , wherein the bearing outer ring is axially supported at its axial other end by a further static component.

6 . The assembly of claim 5 , wherein the further static component comprises a surface that extends in the radial direction, wherein the bearing outer ring is axially supported at its axial other end by such surface.

7 . The assembly of claim 6 , wherein the surface of the further static component comprises an anti-rotation feature.

8 . The assembly of claim 5 , wherein an axial retention is provided between the axial other end of the bearing outer ring and the further static component.

9 . The assembly of claim 5 , wherein the further static component is a ring of an oil transfer unit.

10 . The assembly of claim 5 , wherein the further static component is coupled to the housing ring by means of bolts, wherein the bolts are outside the radial load path of the bearing.

11 . The assembly of claim 5 , wherein the bearing inner ring is connected to or a part of a rotating component, wherein the further static component comprises an axially extending part that extends axially forward to be arranged to the radial inside of the rotating component, wherein the axially extending part is separated from such rotating component in the radial direction by a gap.

12 . The assembly of claim 1 , wherein the bearing outer ring contacts in the radial outward direction the housing ring with a clearance fit, a transition fit or an interference fit or by means of a squeeze film damper.

13 . The assembly of claim 1 , wherein the bearing outer ring lies with its complete radially outer surface against the radially inner surface of the housing ring.

14 . The assembly of claim 1 , wherein the housing structure is a load-bearing structure of a gas turbine engine.

15 . The assembly of claim 1 , wherein the rotatably arranged inner ring is connected to or an element of a carrier element of a planetary gearbox.

16 . The assembly of claim 15 , wherein the axially extending part is a part of the oil transfer unit, the axially extending part extending axially forward to be arranged to the radial inside of the carrier element, wherein the axially extending part is separated from the carrier element in the radial direction by a gap.

17 . The assembly of claim 1 , wherein the bearing is designed as a rolling-element bearing, wherein rolling elements are arranged between the inner ring and the outer ring.

18 . A gas turbine engine for an aircraft comprising:
an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan located upstream of the engine core, the fan comprising a plurality of fan blades; and a planetary gearbox that receives an input from the core shaft and outputs drive to the fan so as to drive the fan at a lower rotational speed than the core shaft, wherein the planetary gearbox comprises a planet carrier which is supported by means of a bearing with the features of claim 1 to a housing structure of the gas turbine engine.

19 . The gas turbine engine of claim 18 , wherein:
the turbine is a first turbine, the compressor is a first compressor, and the core shaft is a first core shaft; the engine core further comprises a second turbine, a second compressor, and a second core shaft connecting the second turbine to the second compressor; and the second turbine, second compressor, and second core shaft are arranged to rotate at a higher rotational speed than the first core shaft.

Assignees

• Rolls Royce Deutschland Ltd & Co Kg

Inventors

• Mittelstaedt Stefan
• Sacha Jiri

Classifications

• F02C7/06 Primary

  Arrangements of bearings (bearings F16C); Lubricating ({of turbo machines F01D25/18; of machines or} engines in general F01M) · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F01D25/18

  Lubricating arrangements (of machines or engines in general F01M) · CPC title

• F01D25/162 Primary

  Bearing supports · CPC title

• F05D2240/14

  Casings or housings protecting or supporting assemblies within · CPC title