Aircraft propulsion assembly with fire extinguishing system

Patent metadata

Field	Value
Publication number	US-2016368618-A1
Application number	US-201415100246-A
Country	US
Kind code	A1
Filing date	Dec 22, 2014
Priority date	Dec 24, 2013
Publication date	Dec 22, 2016
Grant date	—

Abstract

An aircraft propulsion assembly includes an engine, a nacelle surrounding the engine, and a system for extinguishing a fire that may occur in the engine and/or in the nacelle. The extinguishing system has means for supplying an extinguishant to at least one extinguishant distribution pipe which opens into a cavity of the engine and/or a cavity of the nacelle. The extinguishing system also includes means for supplying said at least one pipe with air so as to ventilate the or each cavity.

First claim

1 . An aircraft propulsion assembly comprising an engine, a nacelle surrounding the engine, and a system for extinguishing a fire which may break out in the engine and/or in the nacelle, this extinguishing system comprising means for supplying extinguishing agent to at least one pipe which is configured to dispense said extinguishing agent and leads into a cavity in the engine and/or a cavity in the nacelle, wherein said propulsion assembly further comprises means for supplying air to said at least one pipe in order to ventilate the cavity/cavities.

2 . The propulsion assembly according to claim 1 , wherein the air supply means comprise a ventilator fan.

3 . The propulsion assembly according to claim 2 , wherein the ventilator fan is an electric ventilator fan.

4 . The propulsion assembly according to claim 1 , wherein the air supply means are connected to said at least one pipe by a valve and/or a non-return flap.

5 . The propulsion assembly according to claim 1 , wherein the air supply means are housed in the nacelle.

6 . The propulsion assembly according to claim 1 , further comprising a strut for connecting the propulsion assembly to the aircraft, said air supply means being housed in the strut.

7 . The propulsion assembly according to claim 1 , wherein the air supply means are designed to output an air flow rate of between 1 and 500 g/s.

8 . The propulsion assembly according to claim 1 , wherein the pipe comprises at least one outlet which is located close to an air intake scoop of the nacelle or of the engine.

9 . A method for ventilating a cavity in an engine and/or a cavity in a nacelle of an aircraft propulsion assembly, this propulsion assembly comprising a system for extinguishing a fire which may break out in the engine and/or in the nacelle, this extinguishing system comprising means for supplying extinguishing agent to at least one pipe which is configured to dispense said extinguishing agent and leads into the cavity in the engine and/or the cavity in the nacelle, wherein said method comprises supplying air to said at least one pipe.

Assignees

• Snecma

Inventors

• Charlemagne Pierrick
• Leroux Delphine

Classifications

• F01D25/24

  Casings (modified for heating or cooling F01D25/14); Casing parts, e.g. diaphragms, casing fastenings (casings for rotary machines or engines in general F16M {; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045}) · CPC title

• B64D2045/009

  Fire detection or protection; Erosion protection, e.g. from airborne particles · CPC title

• F05D2220/323

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

• B64C7/02

  Nacelles · CPC title

• B64D45/00 Primary

  Aircraft indicators or protectors not otherwise provided for · CPC title