FR3102148B1 - PROPULSION SYSTEM FOR AN AIRCRAFT - Google Patents

PROPULSION SYSTEM FOR AN AIRCRAFT Download PDF

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Publication number
FR3102148B1
FR3102148B1 FR1911524A FR1911524A FR3102148B1 FR 3102148 B1 FR3102148 B1 FR 3102148B1 FR 1911524 A FR1911524 A FR 1911524A FR 1911524 A FR1911524 A FR 1911524A FR 3102148 B1 FR3102148 B1 FR 3102148B1
Authority
FR
France
Prior art keywords
axis
aircraft
rotor
walls
propulsion system
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
FR1911524A
Other languages
French (fr)
Other versions
FR3102148A1 (en
Inventor
Jean-Louis Robert Guy Besse
Ye-Bonne Karina Maldonado
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 Helicopter Engines SAS
Safran SA
Original Assignee
Safran Helicopter Engines SAS
Safran SA
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 Helicopter Engines SAS, Safran SA filed Critical Safran Helicopter Engines SAS
Priority to FR1911524A priority Critical patent/FR3102148B1/en
Priority to PCT/FR2020/051798 priority patent/WO2021074514A1/en
Publication of FR3102148A1 publication Critical patent/FR3102148A1/en
Application granted granted Critical
Publication of FR3102148B1 publication Critical patent/FR3102148B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/04—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C15/00—Attitude, flight direction, or altitude control by jet reaction
    • B64C15/02—Attitude, flight direction, or altitude control by jet reaction the jets being propulsion jets
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/16—Aircraft characterised by the type or position of power plants of jet type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/002—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto with means to modify the direction of thrust vector
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/06—Varying effective area of jet pipe or nozzle
    • F02K1/10—Varying effective area of jet pipe or nozzle by distorting the jet pipe or nozzle
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/001—Shrouded propellers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/20—Rotorcraft characterised by having shrouded rotors, e.g. flying platforms
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/04—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
    • B64D33/06—Silencing exhaust or propulsion jets
    • 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
    • F05D2220/00—Application
    • F05D2220/90—Application in vehicles adapted for vertical or short take off and landing (v/stol vehicles)
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/505—Shape memory behaviour
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Wind Motors (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L’invention concerne un système propulsif (1, 1’) pour un aéronef, comprenant un rotor (2) et un carénage (3) de nacelle s’étendant autour dudit rotor par rapport à un axe (X) et comprenant un tronçon aval (20) dont une extrémité aval (21) forme une section de sortie (BF) du carénage (3) de nacelle ; et caractérisé en ce que le tronçon aval (20) comprend des parois radialement interne (20a) et externe (20b), dont au moins une partie de l’une desdites parois est réalisée dans un matériau à mémoire de forme thermo-déformable, cette paroi étant munie d’éléments chauffants (23a, 23c) s’étendant dans des secteurs angulaires consécutifs différents autour dudit axe (X), chaque élément chauffant étant actionnable indépendamment et configuré pour déformer cette paroi dans une direction radiale audit axe (X) et centrée angulairement par rapport à son secteur angulaire, sous l’effet d’une commande de tension prédéterminée. Figure pour l'abrégé : Figure 3The invention relates to a propulsion system (1, 1') for an aircraft, comprising a rotor (2) and a nacelle fairing (3) extending around said rotor with respect to an axis (X) and comprising a downstream section (20) of which a downstream end (21) forms an outlet section (BF) of the nacelle fairing (3); and characterized in that the downstream section (20) comprises radially internal (20a) and external (20b) walls, of which at least part of one of the said walls is made of a thermo-deformable shape memory material, this wall being provided with heating elements (23a, 23c) extending in different consecutive angular sectors around said axis (X), each heating element being independently operable and configured to deform this wall in a direction radial to said axis (X) and angularly centered relative to its angular sector, under the effect of a predetermined voltage command. Figure for abstract: Figure 3

FR1911524A 2019-10-16 2019-10-16 PROPULSION SYSTEM FOR AN AIRCRAFT Active FR3102148B1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
FR1911524A FR3102148B1 (en) 2019-10-16 2019-10-16 PROPULSION SYSTEM FOR AN AIRCRAFT
PCT/FR2020/051798 WO2021074514A1 (en) 2019-10-16 2020-10-12 Propulsion system for an aircraft

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1911524A FR3102148B1 (en) 2019-10-16 2019-10-16 PROPULSION SYSTEM FOR AN AIRCRAFT
FR1911524 2019-10-16

Publications (2)

Publication Number Publication Date
FR3102148A1 FR3102148A1 (en) 2021-04-23
FR3102148B1 true FR3102148B1 (en) 2022-07-01

Family

ID=69572096

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1911524A Active FR3102148B1 (en) 2019-10-16 2019-10-16 PROPULSION SYSTEM FOR AN AIRCRAFT

Country Status (2)

Country Link
FR (1) FR3102148B1 (en)
WO (1) WO2021074514A1 (en)

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
NL98695C (en) * 1952-07-25
US6718752B2 (en) * 2002-05-29 2004-04-13 The Boeing Company Deployable segmented exhaust nozzle for a jet engine
GB0414869D0 (en) * 2004-07-02 2004-08-04 Rolls Royce Plc Shape memory material actuation
US20070018035A1 (en) * 2005-07-20 2007-01-25 Saiz Manuel M Lifting and Propulsion System For Aircraft With Vertical Take-Off and Landing
GB0603285D0 (en) * 2006-02-18 2006-03-29 Rolls Royce Plc A gas turbine engine
US8157207B2 (en) * 2006-08-09 2012-04-17 The Boeing Company Jet engine nozzle exit configurations, including projections oriented relative to pylons, and associated systems and methods
WO2008045081A1 (en) * 2006-10-12 2008-04-17 United Technologies Corporation Variable fan nozzle using shape memory material
GB2448320B (en) * 2007-04-10 2012-04-11 Pericles Pilidis Aircraft engine variable nozzle for silencing and performance enhancement
US7716932B2 (en) * 2008-07-24 2010-05-18 Spirit Aerosystems, Inc. Dilating fan duct nozzle
GB0820175D0 (en) * 2008-11-05 2008-12-10 Rolls Royce Plc A gas turbine engine variable area exhuast nozzle
US8434293B2 (en) * 2009-08-06 2013-05-07 The Boeing Company High stiffness shape memory alloy actuated aerostructure
US8613398B2 (en) * 2011-06-17 2013-12-24 General Electric Company Apparatus and methods for linear actuation of flow altering components of jet engine nozzle
GB201220378D0 (en) * 2012-11-13 2012-12-26 Rolls Royce Plc A gas turbine engine exhaust nozzle
DE102013226496A1 (en) * 2013-12-18 2015-07-02 Rolls-Royce Deutschland Ltd & Co Kg Aircraft gas turbine with adjustable discharge nozzle of the bypass duct

Also Published As

Publication number Publication date
WO2021074514A1 (en) 2021-04-22
FR3102148A1 (en) 2021-04-23

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