# US 2014/0191080 A1 · Aircraft propulsion system comprising an aft pylon fairing with lateral walls that are profiled for injecting cool air along a thermal protection floor

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- Number: US 2014/0191080 A1
- Document ID: US20140191080A1
- Status: Published application
- Kind: A1
- Application number: 14/137,334
- Filed: 2013-12-20
- Published: 2014-07-10
- Earliest claimed: 2013-01-09
- Assignees: Airbus Operations GmbH
- Applicants: Airbua Operations (S.A.S,)
- Inventors: Thierry Surply; Cyril BONNAUD; David Grossein; Stève BEDOIN; Amadou André Sylla; Guillaume Drochon; Marjorie Clottes
- Web page: https://patentgrep.com/patent/US20140191080A1

## CPC

- B64C 7/02: Nacelles
- B64D 27/406: {Suspension arrangements specially adapted for supporting thrust loads, e.g. thrust links}
- B64D 29/02: associated with wings
- B64D 33/04: of exhaust outlets or jet pipes
- F01D 25/14: Casings modified therefor (double casings F01D25/26)
- F02C 7/12: Cooling of plants (of component parts, see the relevant subclasses, e.g. F01D; cooling of engines in general F01P)
- F05D 2220/327: to drive shrouded, high solidity propeller
- F05D 2260/202: by film cooling
- Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft
- B64C: AEROPLANES; HELICOPTERS
- B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D)
- F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00)
- F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION

## 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

### Claim 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.

### Claim 2 (depends on 1)

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.

### Claim 3 (depends on 1)

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.

### Claim 4 (depends on 1)

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.

### Claim 5 (depends on 1)

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.

### Claim 6 (depends on 1)

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.

### Claim 7 (depends on 1)

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