Aircraft turbomachine with reduction gearset

Patent metadata

Field	Value
Publication number	US-2021087977-A1
Application number	US-201816954355-A
Country	US
Kind code	A1
Filing date	Dec 20, 2018
Priority date	Dec 22, 2017
Publication date	Mar 25, 2021
Grant date	—

Abstract

An aircraft turbomachine with a reduction gear has a first shaft and a second shaft having one same axis of rotation, the second shaft being rotationally driven by the first shaft via the reduction gear, the first shaft having elastically deformable means having bellows section(s) and being connected to the reduction gear by a connecting system likewise having elastically deformable means involving a hairpin or bellows section(s).

First claim

1 . An aircraft turbomachine with a reduction gear, comprising: a first shaft and a second shaft having a same axis of rotation, the second shaft being driven in rotation via the reduction gear by the first shaft, the first shaft comprising first elastically deformable means comprising at least one first annular bellows extending around the axis of rotation, wherein the first shaft comprises a portion coupled to the reduction gear by a connecting system comprising an input shaft, the input shaft comprising first splines for coupling to the reduction gear and second splines ( 19 ) for coupling to third splines complementary to the portion of the first shaft, the portion of the first shaft having a tubular shape around the axis of rotation, and comprising a downstream part comprising the at least one first bellows and a cylindrical upstream part which is surrounded by the input shaft, the input shaft comprising at least one annular part which extends around the axis and which has a U- or C-shaped cross-section and defines an annular opening around the axis, the annular part forming second elastically deformable means.

2 . The turbomachine according to claim 1 , wherein the at least one annular part with a U- or C-shaped cross-section defines an annular opening which opens in a direction of the axis of rotation.

3 . The turbomachine according to claim 1 , wherein the at least one first bellows extends radially between a first diameter equal to that of the third splines and a second diameter equal to that of the first splines.

4 . The turbomachine according to claim 1 , wherein the input shaft comprises an external annular leg for coupling to the reduction gear, and an internal annular leg for coupling to the cylindrical upstream part of the first shaft.

5 . The turbomachine according to claim 4 , wherein the internal and external annular legs are connected to each other by an annular web having a thinning in thickness at its connection to the external leg.

6 . The turbomachine according to claim 4 , wherein the external annular leg has at least one of a downstream end located near an upstream end of the at least one first bellows, or a diameter which is greater than an external diameter of the at least one first bellows.

7 . The turbomachine according to claim 4 , wherein at least one part of the at least one first bellows is surrounded by the external annular leg.

8 . The turbomachine according to claim 4 , wherein the inner annular leg extends upstream beyond a web and carries external annular sealing elements which cooperate by labyrinth effect with an inner periphery of an annular cowl carried by the second shaft.

9 . The turbomachine according to claim 1 , the at least one first bellows is includes greater first bellows.

10 . The turbomachine according to claim 1 , wherein the at least one annular part with a U- or C-shaped cross-section defines an annular opening which opens radially inwards, the at least one annular part forming a second bellows.

11 . The turbomachine according to claim 10 , wherein the at least one first bellows is located downstream of the reduction gear, and the second bellows is located upstream of the reduction gear.

12 . The turbomachine according to claim 10 , wherein the at least one annular part is an intermediate axial part of the input shaft which comprises an upstream cylindrical part comprising the second splines and a downstream cylindrical part comprising the first splines.

13 . The turbomachine according to claim 1 , wherein at least some of the first, second, or third splines have truncated longitudinal ends.

14 . The turbomachine according to claim 1 , wherein at least some of the first, second, or third splines comprise curved side faces.

15 . The turbomachine according to claim 1 , wherein the first bellows comprises an annular bottom which comprises a plurality of oil passage orifices.

16 . The turbomachine according to claim 1 , wherein the first shaft is a low pressure compressor shaft.

17 . A method of mounting the aircraft turbomachine according to claim 1 , comprising:
connecting the second shaft, which is a fan shaft, to an output shaft of the reduction gear and axially engaging on fan shaft bearings and supports of the fan shaft bearings; engaging an input shaft axially inside the reduction gear until the first splines of the input shaft cooperate with splines of a sun gear of the reduction gear; securing the fan shaft, the output shaft, and the input shaft in an intermediate casing; mounting means for supplying oil to the fan shaft bearings, and engaging the first shaft by axial translation in the input shaft until they are coupled by the second and third splines and fixing the supports of the fan shaft bearings to the intermediate casing.

Assignees

• Safran Aircraft Engines

Inventors

• Becoulet Julien Fabien Patrick
• Tan-Kim Alexandre Jean-Marie
• Pommier Nicolas Auguste Marcel
• Negri Arnaud Nicolas
• Brault Michel Gilbert Roland

Classifications

• F02C7/06

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

• F02C7/36 Primary

  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) · CPC title

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• F02K3/06

  with front fan · CPC title

• F01D5/026

  Shaft to shaft connections · CPC title