AIRCRAFT PROPULSION SYSTEM COMPRISING AN AFT PYLON FAIRING WITH LATERAL WALLS THAT ARE PROFILED FOR INJECTING COOL AIR ALONG A THERMAL PROTECTION FLOOR

• US 20140191080A1
• Filed: 12/20/2013
• Published: 07/10/2014
• Est. Priority Date: 01/09/2013
• Status: Active Grant

• Current Assignee: Airbus Operations (European Aeronautic Defence and Space Company EADS NV)
• Original Assignee: Airbus Operations GmbH (Airbus SE)
• Inventors: Surply, Thierry, BONNAUD, Cyril, Grossein, David, BEDOIN, Stve, Andr Sylla, Amadou, Drochon, Guillaume, Clottes, Marjorie
• Granted Patent: US 9,708,071 B2
• Time in Patent Office: Days
• US Class Current: 244/54
• CPC Class Codes: B64C 7/02 Nacelles
• CPC Class Codes: B64D 27/40 Arrangements for mounting power plants in aircraft
• CPC Class Codes: B64D 27/406 Suspension arrangements specially adapted for supporting thrust loads, e.g. thrust links
• CPC Class Codes: B64D 29/02 associated with wings wings adapted for mounting power plant B64C
• CPC Class Codes: B64D 33/04 of exhaust outlets or jet pipes exhaust outlets for combustion engines in general F01N; jet pipes or nozzles for jet-propulsion plants per se F02K; plants characterised by the form or arrangement of the jet pipe or nozzle F02K ; attitude, flight direction, or altitude control by jet reaction B64C
• CPC Class Codes: F01D 25/14 Casings modified therefor double casings F01D25/26
• CPC Class Codes: F02C 7/12 Cooling of plants of component parts, see the relevant subclasses, e.g. F01D; cooling of engines in general F01P
• CPC Class Codes: F05D 2220/327 to drive shrouded, high solidity propeller
• CPC Class Codes: F05D 2260/202 by film cooling
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

The invention proposes to protect a rear part of a floor of an aft fairing of a pylon of an aircraft bypass turbojet engine using a film of cool air formed of part of a bypass flow of the jet engine which is guided under the floor by two lateral wall portions of this fairing which have been profiled for this purpose. To do that, these two lateral wall portions delimit respective air passage spaces formed between a forward part of the floor and a jetpipe of the turbojet engine and which open laterally and towards the rear.

Claims

1. Propulsion system for an aircraft, comprising a bypass turbojet engine and a pylon intended to attach the turbojet engine to an airframe of an aircraft, the pylon comprising an aft fairing comprising two lateral walls and a floor to protect the pylon from the heat of a primary flow ducted by a jetpipe of the turbojet engine,

the floor comprising two lateral floor portions positioned one on either side of a mid-plane of the aft fairing and separated from the jetpipe so that the lateral floor portions with the jetpipe respectively delimit two air passage spaces which are open laterally and towards the rear of the propulsion system,

and wherein each of the lateral walls of the aft fairing comprises, at its end facing the jetpipe, a lateral wall portion which extends rearwards and towards the mid-plane and which delimits one of the air passage spaces.

2. Propulsion system according to claim 1, wherein each of the lateral wall portions is curved and has a convex face facing towards the outside of the aft fairing when the latter is viewed in section on a plane orthogonal to the said mid-plane and parallel to an axis of the bypass turbojet engine.

3. Propulsion system according to claim 1, wherein the separation between each of the lateral floor portions and the jetpipe at a rear end of the corresponding lateral wall portion is between 2% and 15% of a maximum width of the aft fairing at a trailing edge of the jetpipe.

4. Propulsion system according to claim 1, wherein the jetpipe comprises an extension extending as a projection rearwards and facing the floor of the aft fairing.

5. Propulsion system according to claim 1, wherein the two lateral walls of the aft fairing extend respectively in the continuation of two fork walls which connect together two annular cowls which, respectively on the inside and on the outside, delimit an annular space in which a bypass stream flows through the turbojet engine.

6. Propulsion system according to claim 1, in which the floor comprises a rear part extending in line with the jetpipe to a rear end of the jetpipe and a rear part extending rearwardly from the jetpipe substantially in continuation of the rear part.

7. An aircraft comprising at least one propulsion system according to claim 1.