WO2012066262A3 - Pale pour une helice de turbomachine - Google Patents

Pale pour une helice de turbomachine Download PDF

Info

Publication number
WO2012066262A3
WO2012066262A3 PCT/FR2011/052707 FR2011052707W WO2012066262A3 WO 2012066262 A3 WO2012066262 A3 WO 2012066262A3 FR 2011052707 W FR2011052707 W FR 2011052707W WO 2012066262 A3 WO2012066262 A3 WO 2012066262A3
Authority
WO
WIPO (PCT)
Prior art keywords
blade
turbine engine
engine propeller
length
blade body
Prior art date
Application number
PCT/FR2011/052707
Other languages
English (en)
Other versions
WO2012066262A2 (fr
Inventor
François Gallet
Original Assignee
Snecma
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 Snecma filed Critical Snecma
Publication of WO2012066262A2 publication Critical patent/WO2012066262A2/fr
Publication of WO2012066262A3 publication Critical patent/WO2012066262A3/fr

Links

Classifications

    • 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
    • B64C11/16—Blades
    • B64C11/20—Constructional features
    • B64C11/26—Fabricated blades
    • 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
    • B64C11/16—Blades
    • B64C11/20—Constructional features
    • B64C11/24—Hollow blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/02—De-icing means for engines having icing phenomena
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/10—Heating, e.g. warming-up before starting
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/324—Blades
    • 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
    • B64D2027/005—Aircraft with an unducted turbofan comprising contra-rotating rotors, e.g. contra-rotating open rotors [CROR]
    • 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
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/303—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the leading edge of a rotor blade
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • 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)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Architecture (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne une pale pour une hélice de turbomachine qui com- porte: -un corps de pale (15A) solidaire d'un pied de pale (15B); et -au moins un canal (19) d'écoulement d'un flux de gaz chaud (F) qui s'étend le long de son bord d'attaque (15C), caractérisée par le fait qu'elle comporte une pièce d'extrémité (20) qui en- toure, au moins partiellement, le bord amont (15D) du corps de pale (15A), de telle façon que le canal d'écoulement (19) soit ménagé entre le bord amont dudit corps et ladite pièce, le long du corps de pale depuis le pied de pale.
PCT/FR2011/052707 2010-11-19 2011-11-18 Pale pour une helice de turbomachine WO2012066262A2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1059548A FR2967646B1 (fr) 2010-11-19 2010-11-19 Pale pour une helice de turbomachine
FR1059548 2010-11-19

Publications (2)

Publication Number Publication Date
WO2012066262A2 WO2012066262A2 (fr) 2012-05-24
WO2012066262A3 true WO2012066262A3 (fr) 2013-08-08

Family

ID=44202043

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/FR2011/052707 WO2012066262A2 (fr) 2010-11-19 2011-11-18 Pale pour une helice de turbomachine

Country Status (2)

Country Link
FR (1) FR2967646B1 (fr)
WO (1) WO2012066262A2 (fr)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10808550B2 (en) * 2018-12-13 2020-10-20 Raytheon Technologies Corporation Fan blade with integral metering device for controlling gas pressure within the fan blade
FR3116573B1 (fr) * 2020-11-20 2023-03-24 Safran Aircraft Engines Aube comprenant un bouclier ayant une conduite de passage d’air de dégivrage
US12017787B2 (en) * 2021-09-07 2024-06-25 Experimental Vehicle Engineering Ltd. Aircraft propeller blade radiator
FR3138468A1 (fr) * 2022-07-29 2024-02-02 Safran Aircraft Engines Bouclier de bord d’attaque metallique pour aube de turbomachine, aube de turbomachine, procede de fabrication et d’utilisation

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR767674A (fr) * 1934-07-20
US2440115A (en) * 1948-04-20 Deiging system foi
US2503451A (en) * 1944-01-11 1950-04-11 Curtiss Wright Corp Deicing system for aircraft surfaces
US2586054A (en) * 1948-08-21 1952-02-19 Northrop Aircraft Inc Pusher turboprop exhaust system
FR2635824A1 (fr) * 1988-08-25 1990-03-02 Mtu Muenchen Gmbh Turbomoteur a turbine a gaz entrainant par un reducteur des rotors a helices ou des rotors de soufflante
FR2942513A1 (fr) * 2009-02-20 2010-08-27 Airbus France Aube pour recepteur de turbomachine, comprenant une partie pale integrant un fusible mecanique
WO2010128240A2 (fr) * 2009-05-05 2010-11-11 Airbus Operations (S.A.S) Dispositif de dégivrage pour pales de propulseur de type propfan

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR767674A (fr) * 1934-07-20
US2440115A (en) * 1948-04-20 Deiging system foi
US2503451A (en) * 1944-01-11 1950-04-11 Curtiss Wright Corp Deicing system for aircraft surfaces
US2586054A (en) * 1948-08-21 1952-02-19 Northrop Aircraft Inc Pusher turboprop exhaust system
FR2635824A1 (fr) * 1988-08-25 1990-03-02 Mtu Muenchen Gmbh Turbomoteur a turbine a gaz entrainant par un reducteur des rotors a helices ou des rotors de soufflante
FR2942513A1 (fr) * 2009-02-20 2010-08-27 Airbus France Aube pour recepteur de turbomachine, comprenant une partie pale integrant un fusible mecanique
WO2010128240A2 (fr) * 2009-05-05 2010-11-11 Airbus Operations (S.A.S) Dispositif de dégivrage pour pales de propulseur de type propfan

Also Published As

Publication number Publication date
FR2967646B1 (fr) 2015-03-06
WO2012066262A2 (fr) 2012-05-24
FR2967646A1 (fr) 2012-05-25

Similar Documents

Publication Publication Date Title
EP3106621A3 (fr) Couvercle d'orientation de flux pour composant de moteur
WO2011053513A3 (fr) Corps de turbine d'un turbocompresseur de gaz d'échappement
WO2014077922A3 (fr) Admission de déflecteur de nacelle
WO2013130181A3 (fr) Bord de fuite de plateforme de profil à faible perte
GB2436708B (en) Auxiliary gas turbine engine assembly, aircraft component and controller
GB201112001D0 (en) Turbine blade assembly including a damper
EP2500519A3 (fr) Aube rotorique de turbine
WO2014028095A3 (fr) Joint d'étanchéité vis-à-vis de l'air externe de pale avec passages évidés
EP2149679A3 (fr) Carter de soufflante pour une turbine à gaz
EP2592232A3 (fr) Joint plat pour conduit de transition dans un système de turbine
EP2325439A3 (fr) Noyau de refroidissement d'une plate-forme d'aube de turbine
WO2010043887A3 (fr) Turbine à écoulement tourbillonnaire
WO2011157398A3 (fr) Turbomachine à réduction de bruit
WO2011015193A3 (fr) Aube
WO2010106337A3 (fr) Ensemble turbine
EP2592231A3 (fr) Joint métallique flexible pour conduit de transition dans un système de turbine
EP2410165A3 (fr) Turbine à gaz dotée zone de carénage variable d'atténuation du bruit
EP2527742A3 (fr) Système et procédé pour le contrôle de l'écoulement dans un moteur de turbine à gaz
EP2511482A3 (fr) Système de refroidissement d'un segment d'anneau de turbine et procédé
EP2354452A3 (fr) Rangée d'aubes statoriques de compresseur
WO2015134005A8 (fr) Profil aérodynamique de turbine
WO2011128551A3 (fr) Dispositif redresseur pour turbomachine
WO2012066262A3 (fr) Pale pour une helice de turbomachine
WO2015175073A3 (fr) Surface portante de moteur à turbine à gaz
EP2559849A3 (fr) Ensemble joint de moteur à turbine à gaz ayant un tube à passage de flux

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 11802483

Country of ref document: EP

Kind code of ref document: A2

122 Ep: pct application non-entry in european phase

Ref document number: 11802483

Country of ref document: EP

Kind code of ref document: A2