Isostatic suspension of a turbojet by rear double support

Patent metadata

Field	Value
Publication number	US-9863273-B2
Application number	US-201414914349-A
Country	US
Kind code	B2
Filing date	Aug 21, 2014
Priority date	Aug 28, 2013
Publication date	Jan 9, 2018
Grant date	Jan 9, 2018

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 characterized 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

The invention claimed is:

1. An exhaust casing for a bypass turbojet engine for an aircraft, said casing comprising:
a support for attaching to a structure of the aircraft, said exhaust casing being cylindrical and comprising a central hub supported by said support by a connection, wherein said connection comprises connection arms rigidly connected to said central hub and extending radially through a secondary aft flow of the bypass turbojet engine, said connection arms passing through a cold-flow channel having an outer fan duct in which said secondary air flow is guided,
wherein the fan duct surrounds the central hub in a radially outward direction, said connection arms are configured to transmit to said support stresses generated in the region of said central hub by the turbojet engine without transmitting the stresses to the cold-flow channel,
wherein the support is a suspension hoop, the outer ends of the connection arms being attached to the suspension hoop, wherein the suspension hoop surrounds the outer fan duct in the radially outward direction, and
wherein the connection arms are two radial arms, which are positioned diametrically opposite one another relative to the center of the exhaust casing.

2. The exhaust casing according to claim 1 , wherein each connection arm comprises an outer end, said outer end being configured to be attached to the support by a connection of the sliding pivot type or annular linear type.

3. The exhaust casing according to claim 1 , wherein said suspension hoop comprises an attachment zone for transmitting stresses transmitted by said exhaust casing to the structure of the aircraft.

4. The exhaust casing according to claim 3 , wherein the suspension hoop is circular and surrounds the cold-flow channel of the turbojet engine.

5. The exhaust casing according to claim 4 , wherein the suspension hoop is semi-circular, there being two connection arms positioned along a diameter, said diameter being perpendicular to the radius passing through the attachment zone.

6. The exhaust casing according to claim 3 , further comprising an additional connection extending between the central hub and said attachment zone, said additional connection being in a standby position, without transmitting stress between said central hub and said attachment zone for transmitting stresses between said central hub and said attachment zone when stresses arise in said suspension hoop which exceed a predetermined threshold.

7. The exhaust casing according to claim 6 , wherein said additional connection is a connecting rod dimensioned so as to withstand ultimate stresses.

8. The exhaust casing according to claim 7 , 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 central hub and on said attachment zone, at least one radially oriented slot disposed on at least one end of the connecting rods, wherein at least one corresponding yoke of the yokes passes through a corresponding radially oriented slot of the at least one radially oriented slot.

9. The exhaust casing according to claim 6 , wherein the additional connection passes through the cold-flow channel by a hole without contact to the cold flow channel.

10. A bypass turbojet engine comprising the exhaust casing according to claim 1 .

11. The bypass turbojet engine according to claim 10 , wherein the connection arms pass through the cold-flow channel in the region of a support ring of the cold-flow channel.

12. The bypass turbojet engine according to claim 11 , wherein each arm of the exhaust casing passes through a hole made in the support ring.

13. The bypass turbojet engine according to claim 11 , wherein the suspension hoop is retained by the connection arms by a fastener connecting the suspension hoop to the connection arms, said support ring 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

• Y02T50/672

  Cross-Sectional Technologies · mapped topic

• F02K1/04

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

• B64D27/26

  Operations & Transport · mapped topic

• B64D2027/266

  Operations & Transport · mapped topic