Aircraft turbine engine with planetary or epicyclic gear train

Patent metadata

Field	Value
Publication number	US-2018073384-A1
Application number	US-201615560464-A
Country	US
Kind code	A1
Filing date	Mar 22, 2016
Priority date	Mar 26, 2015
Publication date	Mar 15, 2018
Grant date	—

Abstract

Aircraft turbine engine comprising a low-pressure spool that comprises a low-pressure shaft ( 24 ), means ( 44 ) for taking off power from said low-pressure shaft, and a fan ( 28 ) that is driven by said low-pressure shaft by means of a reduction gear ( 32 ), said reduction gear comprising at least one first element ( 50 ) that is connected to said low-pressure shaft for conjoint rotation, at least one second element ( 56 ) that is connected to said fan for conjoint rotation, and at least one third element ( 52 ) that is connected to a stator casing of the turbine engine, characterised in that said at least one third element is connected to said stator casing by disengageable connection means ( 60 ), and comprising at least one member that can move from a first position in which said at least one third element is fixedly connected to said stator casing into a second position in which said at least one third element is separated from said stator casing and is free to rotate about said longitudinal axis.

First claim

1 . An aircraft turbine engine comprising a low-pressure spool that comprises a low-pressure shaft that connects a rotor of a low-pressure compressor to a rotor of a low-pressure turbine, and a high-pressure spool that comprises a high-pressure shaft that connects a rotor of a high-pressure compressor to a rotor of a high-pressure turbine, the low-pressure and high-pressure shafts extending along the same longitudinal axis (A), the turbine engine further comprising means for taking off power from said low-pressure shaft, and a fan that is driven by said low-pressure shaft by means of a planetary or epicyclic reduction gear, said reduction gear comprising at least one first element that is connected to said low-pressure shaft for conjoint rotation, at least one second element that is connected to said fan for conjoint rotation, and at least one third element that is connected to a stator casing of the turbine engine, characterised in that said at least one third element is connected to said stator casing by disengageable connection means, and comprising at least one member that can move from a first position in which said at least one third element is fixedly connected to said stator casing into a second position in which said at least one third element is separated from said stator casing and is free to rotate about said longitudinal axis.

2 . The aircraft turbine engine according to claim 1 , wherein said third element is an external ring gear of the reduction gear.

3 . The aircraft turbine engine according to claim 1 , wherein said third element is a planet carrier of the reduction gear.

4 . The aircraft turbine engine according to claim 1 , wherein said connection means comprise an annular flange that is supported by said third element, said at least one member being movably mounted in at least one stirrup that is supported by said stator casing and is mounted on said flange.

5 . The aircraft turbine engine according to claim 4 , wherein said at least one member ( 68 ), which is preferably a piston, is designed to come into abutment on the flange and to clamp said flange when said member is in the first position mentioned above.

6 . The aircraft turbine engine according to claim 5 , wherein at least one of said at least stirrup and said at least one member comprises a support plate made of a material having a high friction coefficient.

7 . The aircraft turbine engine according to claim 5 , wherein said at least one member is biased against the flange by at least one spring.

8 . The aircraft turbine engine according to claim 5 , wherein said at least one member is designed to be moved in translation by means of a screw.

9 . The aircraft turbine engine according to claim 1 , wherein said connection means are connected to least one of:
actuation means, for example hydraulic actuation means, that are connected to a computer of the turbine engine, and/or pneumatic actuation means that are connected by supply means to air offtake means in a compressor of the high-pressure spool.

10 . The aircraft turbine engine according to claim 1 , wherein said turbine engine has a bypass ratio of greater than 10, or even of greater than 12.

11 . A method for starting up an aircraft turbine engine according to claim 1 , wherein said method comprises disengaging said connection means in order to move said movable member from the first position thereof into the second position thereof.

12 . The aircraft turbine engine according to claim 6 , wherein said at least one member is biased against the flange by at least one spring.

13 . The aircraft turbine engine according to claim 6 , wherein said at least one member is designed to be moved in translation by means of a screw.

Assignees

• Safran Aircraft Engines

Inventors

• Bordoni Nils
• Kubiak Guillaume Patrice
• Lemarchand Kevin Morgane

Classifications

• F16D25/0635

  with flat friction surfaces, e.g. discs · CPC title

• F05D2260/85

  Starting · CPC title

• F02C7/277

  the starter being a {separate} turbine · CPC title

• F02C7/275

  Mechanical drives · CPC title

• F01D15/12 Primary

  Combinations with mechanical gearing (driven by multiple engines F01D13/00) · CPC title