Isostatic suspension of a turbojet by rear double support

Patent metadata

Field	Value
Publication number	US-2016200443-A1
Application number	US-201414914349-A
Country	US
Kind code	A1
Filing date	Aug 21, 2014
Priority date	Aug 28, 2013
Publication date	Jul 14, 2016
Grant date	—

Abstract

The invention relates to a bypass turbojet comprising an exhaust housing having a central hub ( 13 ) and connecting means ( 11 ) that can transmit the forces generated by the turbojet to the structure of the aircraft that it propels, said connection means being two arms extending radially from the central hub in order to cross the cold flow of said turbojet and being characterised in that they are secured to said central hub and positioned in a diametrically opposed manner in relation to each other. An additional connection means ( 14 ) extends between the hub ( 13 ) and the area ( 9 ) for securing the exhaust housing to the structure ( 12 ) of the aircraft in order to transmit the exceptional dimensioning loads, said connection means being on standby during normal use, without any transmission of force between said hub and said area.

First claim

1 . Exhaust casing of a bypass turbojet engine for an aircraft, which casing is equipped with a support means which is intended to be attached to the structure of the aircraft, said exhaust casing, which is cylindrical, comprising a central hub supported by said support means 8 by connection means
characterised in that said connection means are arms which are rigidly connected to said central hub and extend therefrom, passing through a secondary air flow of the bypass turbojet engine, said arms being designed to transmit to said support means the stresses generated in the region of said central hub by the turbojet engine in normal use without transmitting them to a cold-flow channel, in which said secondary air flow of the turbojet engine is guided.

2 . Equipped exhaust casing according to claim 1 , wherein the connection arms are radial arms, of which there are two, which are positioned diametrically opposite one another.

3 . Equipped exhaust casing according to claim 1 , wherein the outer end of each arm is designed to be attached to the support means by a connection of the sliding pivot type or annular linear type.

4 . Equipped exhaust casing according to claim 1 , wherein the support means is a suspension hoop to which the outer ends of the arms are attached and which comprises an attachment zone which is capable of transmitting the stresses transmitted by said exhaust casing to the structure of the aircraft.

5 . Equipped exhaust casing according to claim 4 , wherein the suspension hoop is circular and surrounds the cold-flow channel of the turbojet engine.

6 . Equipped exhaust casing according to claim 5 , wherein the suspension hoop is semi-circular, there being two connection arms, which are positioned along a diameter which is perpendicular to the radius passing through the attachment zone.

7 . Equipped exhaust casing according to claim 4 , further comprising an additional connection means which extends between its hub and said attachment zone, said additional connection means being in a standby position, in normal use, without transmitting stress between said hub and said attachment zone and being capable of transmitting stresses between said hub and said attachment zone when stresses arise in said suspension hoop which exceed a particular threshold.

8 . Equipped exhaust casing according to claim 7 , wherein said additional connection means is a connecting rod which is dimensioned so as to withstand stresses which are abnormally high, referred to as ultimate stresses, causing potentially large movements of the exhaust casing.

9 . Equipped exhaust casing according to claim 8 , wherein said connecting rod is oriented radially with respect to the attachment zone and freely mounted in rotation in a radial plane about yokes respectively positioned on said hub and on said attachment zone, said connecting rod comprising a radially oriented slot at least one of its ends, through which slot the shaft of the corresponding yoke passes.

10 . Equipped exhaust casing according to claim 7 , wherein the additional connection means passes through the cold-flow channel by a hole without contact.

11 . Bypass turbojet engine comprising an exhaust casing according to any of claim 1 .

12 . Bypass turbojet engine according to claim 11 , wherein the connection arms pass through the cold-flow channel.

13 . Bypass turbojet engine according to claim 12 , wherein the connection arms ( 11 ) pass through the cold-flow channel in the region of a support ring of the cold-flow channel.

14 . Bypass turbojet engine according to claim 13 , wherein each arm of the exhaust casing passes through a hole made in the support ring.

15 . Bypass turbojet engine according to claim 13 , wherein the cold-flow channel is retained by the connection arms ( 11 ) by means of fastening means connecting the support ring to the connection arms, said fastening means not participating in transmitting stresses between the exhaust casing and the structure of the aircraft.

Assignees

• Snecma

Inventors

• Bellabal Francois Robert
• Gallet Francois
• Poisson Mathieu Ange

Classifications

• B64D27/404

  Suspension arrangements specially adapted for supporting vertical loads · CPC title

• B64D27/40 Primary

  Arrangements for mounting power plants in aircraft · CPC title

• B64D27/16

  of jet type · CPC title

• F05D2220/323

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

• F02K1/04

  Mounting of an exhaust cone in the jet pipe · CPC title