Suspension of a tubular element in an aircraft compartment

Patent metadata

Field	Value
Publication number	US-10301036-B2
Application number	US-201415103277-A
Country	US
Kind code	B2
Filing date	Dec 8, 2014
Priority date	Dec 16, 2013
Publication date	May 28, 2019
Grant date	May 28, 2019

Abstract

The invention relates to an assembly comprising a structure ( 2 ) and a tubular element ( 6 ), which is mounted isostatically in the structure ( 2 ), said tubular element ( 6 ) comprising a first end ( 7 ) connected to said structure by at least four connecting rods 10 a - 10 b - 10 c - 10 d , thus setting four first degrees of freedom, and a second end ( 8 ) connected to said structure ( 2 ) by an attachment means ( 20 ) that sets two second degrees of freedom, said connecting rods comprising a means for adjusting the length thereof. In particular, it relates to an exhaust suitable for an auxiliary power unit in the compartment thereof and to the mounting method for aligning them.

First claim

The invention claimed is:

1. An installation comprising an engine module comprising a gas exhaust nozzle and an assembly comprising a structure and an exhaust pipe of a turboshaft engine, which is mounted isostatically in the structure, said exhaust pipe comprising a first end connected to said structure by at least four connecting rods, thus setting four first degrees of freedom, and a second end connected to said structure by an attachment means that sets two second degrees of freedom, said connecting rods comprising a means for adjusting the length thereof, the exhaust pipe being a pipe of which an inlet is positioned to collect the exhaust gases leaving the gas exhaust nozzle, and wherein an outlet of the gas exhaust nozzle fits into the first end of the exhaust pipe, while leaving play relative to said exhaust pipe over the entirety of the periphery of said exhaust pipe.

2. The installation according to claim 1 , wherein the structure comprises a wall comprising an opening, the second end of the exhaust pipe being slidingly mounted in said opening.

3. The installation according to claim 2 , wherein the sliding mounting between the wall and the second end of the exhaust pipe is flexible in accordance with at least one of the two second degrees of freedom.

4. The installation according to claim 1 , wherein the engine module comprises an auxiliary power unit, the wall of the structure forming at least part of the wall of the compartment containing the auxiliary power unit.

5. An aircraft comprising the installation according to claim 4 , wherein said structure forms the tail cone.

6. A method for mounting an engine module comprising a gas exhaust nozzle and an exhaust pipe of a turboshaft engine in a structure so as to position a first end of said exhaust pipe relative to the engine module while keeping a second end of said exhaust pipe in contact with said structure, wherein, after having previously connected said second end to said structure by two degrees of freedom and having positioned said first end so that an outlet of the gas exhaust nozzle fits into the first end of the exhaust pipe, while leaving play relative to said exhaust pipe over the entirety of the periphery of said exhaust pipe, said first end is connected to said structure by four connecting rods of which the length is adjusted so as to maintain this position, said first end being positioned relative to the engine module that has been previously mounted in said structure.

Assignees

• Microturbo
• Safran Power Units

Inventors

• Cazenave Olivier
• Lalanne Clement
• Barneto Xavier

Classifications

• B64D2041/002

  Mounting arrangements for auxiliary power units (APU's) · CPC title

• B64D33/08

  of power plant cooling systems · CPC title

• B64D41/00 Primary

  Power installations for auxiliary purposes · CPC title

• B64D33/04

  of exhaust outlets or jet pipes · CPC title

• Y02T50/44

  Cross-Sectional Technologies · mapped topic