Front enclosure which is sealed during the modular dismantling of a turbojet with reduction gear

Patent metadata

Field	Value
Publication number	US-2016298639-A1
Application number	US-201415037151-A
Country	US
Kind code	A1
Filing date	Nov 13, 2014
Priority date	Nov 21, 2013
Publication date	Oct 13, 2016
Grant date	—

Abstract

The invention relates to a turbofan engine comprising a fan driven, via a fan shaft supported by at least two first bearings, by a turbine shaft supported by at least one second bearing comprising a stationary ring and a movable ring, said turbine shaft driving said fan shaft through a device for reducing the speed of rotation, said device for reducing the speed of rotation and said first and second bearings being housed in a lubrication enclosure in which the shell comprises stationary portions and movable portions connected to one another by sealing means, said reducing device comprising an inducer shaped so as to receive the torque transmitted by said turbine shaft via driving means connected to said movable ring, wherein the lubrication enclosure forms a coaxial ring with the turbine shaft and said driving means comprise a girth gear which is part of the movable sealing walls of the shell of the lubrication enclosure.

First claim

1 . Bypass turbojet engine comprising a fan which is driven, by a fan shaft which is supported by at least two first bearings, by a turbine shaft which is supported by at least one second bearing having a fixed ring and a movable ring, said turbine shaft driving said fan shaft through a device for reducing the rotational speed, said device for reducing the rotational speed and said first and second bearings being received in a lubrication vessel, the casing of which comprises fixed portions and movable portions which are interconnected by sealing means, said device for reducing speed having an input wheel which is shaped so as to receive the torque transmitted by said turbine shaft by drive means which are connected to said movable ring, wherein the lubrication vessel forms a ring which is coaxial with the turbine shaft, and said drive means have a drive ring forming a portion of the movable sealing walls of the casing of the lubrication vessel.

2 . Turbojet engine according to claim 1 , wherein said movable portions of the casing of the lubrication vessel comprise the fan shaft, a downstream extension casing of said fan shaft supporting the sealing means between the fan shaft and said drive means, and said drive means.

3 . Turbojet engine according to claim 1 , wherein said drive means comprise an end portion which is positioned radially between said movable ring and said turbine shaft, and an opposite end portion supporting the sealing means.

4 . Turbojet engine according to claim 1 , wherein the drive means are formed by two shafts which are coaxial with said turbine shaft: a first drive shaft being connected to said movable ring and comprising drive means of a second drive shaft forming said drive ring of the input wheel of the reduction device.

5 . Turbojet engine according to claim 4 , wherein said first drive shaft comprises a portion which is shaped so as to cooperate with the turbine shaft and receive the torque to be transmitted to the reduction device, said portion being positioned between said movable ring and said turbine shaft.

6 . Turbojet engine according to claim 5 , further comprising, axially in the region of said second bearing, a journal supporting a rotor of the turbojet engine, wherein said portion of the first drive shaft is positioned between said movable ring and said journal.

7 . Turbojet engine according to claim 1 , wherein said lubrication vessel comprises two sealing means of the rotor/stator type in the region of one of the first bearings and the second bearing and a sealing means of the rotor/rotor type which is positioned lengthwise between said turbine shaft and said fan shaft.

8 . Turbojet engine according to claim 7 , wherein the means which ensure the rotor/rotor-type seal are supported, firstly, by a downstream extension casing of said fan shaft and, secondly, by one of said drive means.

9 . Turbojet engine according to claim 7 , wherein the rotor/rotor-type seal comprises a movable labyrinth seal.

10 . Turbojet engine according to claim 1 , wherein the internal diameter of each of the elements of the movable portions of said vessel is greater than that of the turbine shaft .

Assignees

• Snecma

Inventors

• Brault Michel Gilbert Roland
• Nowakowski Nathalie

Classifications

• F02K3/06

  with front fan · CPC title

• F01D25/18 Primary

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

• F02C7/36

  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) · CPC title

• F05D2260/40311

  of the epicyclical, planetary or differential type · CPC title

• F02C3/067

  having counter-rotating rotors (F02C3/073 takes precedence) · CPC title