FR3125505B1 - TURBOMACHINE PROPELLER BLADE PITCH CHANGE SYSTEM - Google Patents

TURBOMACHINE PROPELLER BLADE PITCH CHANGE SYSTEM Download PDF

Info

Publication number
FR3125505B1
FR3125505B1 FR2107924A FR2107924A FR3125505B1 FR 3125505 B1 FR3125505 B1 FR 3125505B1 FR 2107924 A FR2107924 A FR 2107924A FR 2107924 A FR2107924 A FR 2107924A FR 3125505 B1 FR3125505 B1 FR 3125505B1
Authority
FR
France
Prior art keywords
blade
root
axis
propeller blade
blade pitch
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
FR2107924A
Other languages
French (fr)
Other versions
FR3125505A1 (en
Inventor
Christophe Marcel Lucien Perdrigeon
Clément Cottet
Régis Eugène Henri Servant
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 FR2107924A priority Critical patent/FR3125505B1/en
Publication of FR3125505A1 publication Critical patent/FR3125505A1/en
Application granted granted Critical
Publication of FR3125505B1 publication Critical patent/FR3125505B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • 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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • 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
    • B64C11/02—Hub construction
    • B64C11/04—Blade mountings
    • B64C11/06—Blade mountings for variable-pitch 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
    • B64C11/30—Blade pitch-changing mechanisms
    • 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
    • B64C11/30—Blade pitch-changing mechanisms
    • B64C11/32—Blade pitch-changing mechanisms mechanical
    • 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
    • B64C11/30—Blade pitch-changing mechanisms
    • B64C11/32—Blade pitch-changing mechanisms mechanical
    • B64C11/325—Blade pitch-changing mechanisms mechanical comprising feathering, braking or stopping systems
    • 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
    • B64C11/30—Blade pitch-changing mechanisms
    • B64C11/38—Blade pitch-changing mechanisms fluid, e.g. hydraulic
    • 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
    • B64C11/30—Blade pitch-changing mechanisms
    • B64C11/38—Blade pitch-changing mechanisms fluid, e.g. hydraulic
    • B64C11/385—Blade pitch-changing mechanisms fluid, e.g. hydraulic comprising feathering, braking or stopping systems
    • 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
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/36—Application in turbines specially adapted for the fan of turbofan engines
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/14—Two-dimensional elliptical
    • 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
    • F05D2260/50—Kinematic linkage, i.e. transmission of position
    • F05D2260/56—Kinematic linkage, i.e. transmission of position using cams or eccentrics

Abstract

L’invention concerne un système (30) de changement de pas d’une pale d’une hélice, pour une turbomachine d’aéronef, caractérisé en ce qu’il comprend un support (40) de pied (25) de pale comportant une paroi annulaire (42) s’étendant autour d’un axe (A) destiné à être un axe de calage de la pale, cette paroi annulaire comportant une extrémité axiale inférieure fermée par une paroi de fond (44) et une extrémité axiale supérieure ouverte et configurée pour autoriser le montage d’un pied de pale, la paroi de fond (44) comportant une face supérieure configurée pour coopérer par complémentarité de forme avec une extrémité libre du pied de façon à ce que le support soit solidarisé en rotation avec le pied autour dudit axe (A) et une face inférieure opposée à la face supérieure comprenant un prolongement transversal (48), le prolongement transversal ayant une extrémité fixée solidairement à une chape (49) formant excentrique (50) configurée pour coopérer avec un mécanisme de changement de pas. Figure pour l'abrégé : Figure 9The invention relates to a system (30) for changing the pitch of a blade of a propeller, for an aircraft turbine engine, characterized in that it comprises a support (40) for the root (25) of the blade comprising a annular wall (42) extending around an axis (A) intended to be a wedging axis of the blade, this annular wall comprising a lower axial end closed by a bottom wall (44) and an open upper axial end and configured to allow the mounting of a blade root, the bottom wall (44) comprising an upper face configured to cooperate by shape complementarity with a free end of the root so that the support is integral in rotation with the foot around said axis (A) and a lower face opposite the upper face comprising a transverse extension (48), the transverse extension having one end fixed integrally to a yoke (49) forming an eccentric (50) configured to cooperate with a mechanism of step change. Figure for abstract: Figure 9

FR2107924A 2021-07-22 2021-07-22 TURBOMACHINE PROPELLER BLADE PITCH CHANGE SYSTEM Active FR3125505B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR2107924A FR3125505B1 (en) 2021-07-22 2021-07-22 TURBOMACHINE PROPELLER BLADE PITCH CHANGE SYSTEM

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2107924A FR3125505B1 (en) 2021-07-22 2021-07-22 TURBOMACHINE PROPELLER BLADE PITCH CHANGE SYSTEM
FR2107924 2021-07-22

Publications (2)

Publication Number Publication Date
FR3125505A1 FR3125505A1 (en) 2023-01-27
FR3125505B1 true FR3125505B1 (en) 2023-07-21

Family

ID=77519347

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2107924A Active FR3125505B1 (en) 2021-07-22 2021-07-22 TURBOMACHINE PROPELLER BLADE PITCH CHANGE SYSTEM

Country Status (1)

Country Link
FR (1) FR3125505B1 (en)

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4021142A (en) * 1974-10-09 1977-05-03 United Technologies Corporation Pitch-change apparatus for a ducted thrust fan
US4718823A (en) * 1987-02-24 1988-01-12 United Technologies Corporation Pitch changing mechanism for fan blades
FR2908451B1 (en) 2006-11-09 2009-03-20 Snecma Sa TURBOPROPULSEUR COMPRISING AN ADJUSTABLE ORIENTATION BLADE ASSEMBLY
FR2980770B1 (en) 2011-10-03 2014-06-27 Snecma AIRBORNE TURBINE ENGINE (S) FOR AIRCRAFT WITH SYSTEM FOR CHANGING THE PROPELLER STEP.
US20160009373A1 (en) * 2014-03-31 2016-01-14 Aerovate Inc. Variable Blade Pitch Propeller Assembly

Also Published As

Publication number Publication date
FR3125505A1 (en) 2023-01-27

Similar Documents

Publication Publication Date Title
FR3082230B1 (en) NON-HOODED ROTOR AIRCRAFT ENGINE WITH STATOR VANE ADAPTATION
FR3083207B1 (en) POWERTRAIN ASSEMBLY FOR AN AIRCRAFT INCLUDING A NON-HOODED ROTOR
FR3125505B1 (en) TURBOMACHINE PROPELLER BLADE PITCH CHANGE SYSTEM
FR3091551B1 (en) DEFLECTOR FOR THE FAIRING OF A TURBOMACHINE PINION, ASSOCIATED GEAR HOUSING AND TURBOMACHINE
FR3112820B1 (en) AIRCRAFT TURBOMACHINE WITH VARIABLE-PITCHED PROPELLER BLADE
FR3072425A1 (en) DOUBLE FLOW TURBOMACHINE AND LUBRICANT RESERVOIR
FR2958977B1 (en) PISTON FOR DIESEL ENGINE COMBUSTION CHAMBER
FR3061741B1 (en) TURBINE FOR TURBOMACHINE
FR3072422B1 (en) COMBUSTION CHAMBER MODULE FOR A TURBOMACHINE
FR3123696B1 (en) PROPELLER BLADE ANGULAR PITCH CONTROL SYSTEM FOR AN AIRCRAFT TURBOMACHINE
FR3104197B1 (en) TURBINE ROTOR WHEEL FOR AN AIRCRAFT TURBOMACHINE
FR3023591A1 (en) "INTERNAL COMBUSTION ENGINE HAVING A MOTOR BLOCK WITH AN OIL DEFLECTOR"
FR3055002B1 (en) PITCH CHANGE SYSTEM EQUIPPED WITH FLUID SUPPLY MEANS OF A CONTROL MEANS AND CORRESPONDING TURBOMACHINE
FR3113419B1 (en) DISTRIBUTOR OF A TURBOMACHINE TURBINE
FR3097260B1 (en) Turbojet fan housing
FR3116306B1 (en) Exhaust cone with resonators for a turbomachine
FR3120660B1 (en) PROPELLER BLADE ANGULAR PITCH CONTROL SYSTEM FOR AN AIRCRAFT TURBOMACHINE
FR3084699B1 (en) THERMAL EXCHANGER FOR TURBOMACHINE AND ASSOCIATED MANUFACTURING PROCESS
FR3096561B1 (en) Carrying strap equipped with a conformation frame
FR3121477B1 (en) AIRCRAFT TURBOMACHINE WITH VARIABLE-PITCHED PROPELLER BLADE
FR3131731B1 (en) SYSTEM FOR CONTROLLING THE ANGULAR PITCHING OF A PROPELLER BLADE FOR AN AIRCRAFT TURBOMACHINE
FR3107717B1 (en) Degassing tube for a turbomachine
FR3097903B1 (en) CASING FOR AN AIRCRAFT TURBOMACHINE
FR3099798B1 (en) Set for a turbomachine turbine
FR3097028B1 (en) Method of manufacturing a flame tube for a turbomachine

Legal Events

Date Code Title Description
PLFP Fee payment

Year of fee payment: 2

PLFP Fee payment

Year of fee payment: 3