FR3061699B1 - ENGINE ASSEMBLY FOR AIRCRAFT - Google Patents

ENGINE ASSEMBLY FOR AIRCRAFT Download PDF

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Publication number
FR3061699B1
FR3061699B1 FR1750275A FR1750275A FR3061699B1 FR 3061699 B1 FR3061699 B1 FR 3061699B1 FR 1750275 A FR1750275 A FR 1750275A FR 1750275 A FR1750275 A FR 1750275A FR 3061699 B1 FR3061699 B1 FR 3061699B1
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FR
France
Prior art keywords
engine assembly
aircraft
rigid structure
movable part
fixed rigid
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
FR1750275A
Other languages
French (fr)
Other versions
FR3061699A1 (en
Inventor
Antoine Elie Hellegouarch
Benoit Marc Michel Fauvelet
Laurent Jean Guibert
Adrien Jean-Mickael Leguet
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
Safran Aircraft Engines SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Priority to FR1750275A priority Critical patent/FR3061699B1/en
Publication of FR3061699A1 publication Critical patent/FR3061699A1/en
Application granted granted Critical
Publication of FR3061699B1 publication Critical patent/FR3061699B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
    • B64D27/02—Aircraft characterised by the type or position of power plant
    • B64D27/10—Aircraft characterised by the type or position of power plant of gas-turbine type
    • B64D27/12—Aircraft characterised by the type or position of power plant of gas-turbine type within or attached to wing
    • B64D27/40—
    • B64D27/402—
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/72—Maintenance

Abstract

L'invention concerne un ensemble moteur (1) pour aéronef et un procédé de maintenance d'un tel ensemble moteur. L'ensemble moteur (1) comprend un dispositif d'accrochage (3) d'un turbopropulseur (2) sous une voilure d'aéronef comportant une structure rigide fixe (4) destinée à être fixée à la voilure. Selon l'invention, le dispositif d'accrochage (3) comprend une partie mobile (5) supportant le turbopropulseur (2). La partie mobile (5) est mobile par rapport à la structure rigide fixe (4) entre une position escamotée dans laquelle la partie mobile (5) est logée dans la structure rigide fixe (4) et une position déployée dans laquelle la partie mobile (5) est au moins partiellement en dehors de la structure rigide fixe (4).The invention relates to an engine assembly (1) for an aircraft and a method of maintaining such an engine assembly. The engine assembly (1) comprises a device (3) for attaching a turboprop engine (2) under an aircraft wing comprising a fixed rigid structure (4) intended to be fixed to the wing. According to the invention, the attachment device (3) comprises a movable part (5) supporting the turboprop (2). The movable part (5) is movable relative to the fixed rigid structure (4) between a retracted position in which the movable part (5) is housed in the fixed rigid structure (4) and an deployed position in which the movable part ( 5) is at least partially outside the fixed rigid structure (4).

FR1750275A 2017-01-12 2017-01-12 ENGINE ASSEMBLY FOR AIRCRAFT Active FR3061699B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1750275A FR3061699B1 (en) 2017-01-12 2017-01-12 ENGINE ASSEMBLY FOR AIRCRAFT

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1750275 2017-01-12
FR1750275A FR3061699B1 (en) 2017-01-12 2017-01-12 ENGINE ASSEMBLY FOR AIRCRAFT

Publications (2)

Publication Number Publication Date
FR3061699A1 FR3061699A1 (en) 2018-07-13
FR3061699B1 true FR3061699B1 (en) 2024-02-02

Family

ID=58455265

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1750275A Active FR3061699B1 (en) 2017-01-12 2017-01-12 ENGINE ASSEMBLY FOR AIRCRAFT

Country Status (1)

Country Link
FR (1) FR3061699B1 (en)

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6340135B1 (en) * 2000-05-30 2002-01-22 Rohr, Inc. Translating independently mounted air inlet system for aircraft turbofan jet engine
FR2906568B1 (en) * 2006-10-02 2012-01-06 Aircelle Sa DEPOSITABLE AIR INTAKE STRUCTURE FOR TURBOJET NACELLE.
FR2916736B1 (en) * 2007-06-04 2009-09-04 Airbus France Sa APPARATUS FOR HANDLING AN AIRCRAFT TURBOPROPULSER COMPRISING HYDRAULIC FASTENING MEANS.
FR3016662B1 (en) * 2014-01-23 2016-02-12 Snecma NON-CARNETIC PROPELLER TURBOMOTEUR HAVING A REINFORCING ENVELOPE INCORPORATING PIPES OF PIPES

Also Published As

Publication number Publication date
FR3061699A1 (en) 2018-07-13

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