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FR3123696B1 - PROPELLER BLADE ANGULAR PITCH CONTROL SYSTEM FOR AN AIRCRAFT TURBOMACHINE - Google Patents

PROPELLER BLADE ANGULAR PITCH CONTROL SYSTEM FOR AN AIRCRAFT TURBOMACHINE Download PDF

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Publication number
FR3123696B1
FR3123696B1 FR2105788A FR2105788A FR3123696B1 FR 3123696 B1 FR3123696 B1 FR 3123696B1 FR 2105788 A FR2105788 A FR 2105788A FR 2105788 A FR2105788 A FR 2105788A FR 3123696 B1 FR3123696 B1 FR 3123696B1
Authority
FR
France
Prior art keywords
bowl
blade
angular pitch
propeller blade
control 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
FR2105788A
Other languages
French (fr)
Other versions
FR3123696A1 (en
Inventor
Clément Cottet
Vivien Mickaël Courtier
Vincent Joudon
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 FR2105788A priority Critical patent/FR3123696B1/en
Priority to PCT/FR2021/051315 priority patent/WO2022018358A1/en
Priority to CN202180051532.6A priority patent/CN115989178A/en
Priority to EP21755512.7A priority patent/EP4185523B1/en
Priority to US18/006,285 priority patent/US11981418B2/en
Publication of FR3123696A1 publication Critical patent/FR3123696A1/en
Application granted granted Critical
Publication of FR3123696B1 publication Critical patent/FR3123696B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • 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
    • F04D29/322—Blade mountings
    • F04D29/323—Blade mountings adjustable
    • 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
    • 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
    • F04D29/60—Mounting; Assembling; Disassembling
    • F04D29/64—Mounting; Assembling; Disassembling of axial pumps
    • F04D29/644—Mounting; Assembling; Disassembling of axial pumps especially adapted for elastic fluid pumps

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Système (34) de commande du calage angulaire d’une aube (10) d’hélice, pour une turbomachine d’aéronef, caractérisé en ce qu’il comprend : - une aube (10) comportant une pale (12) reliée à un pied (14), - un bol (58) comportant une paroi annulaire (58a) s’étendant autour d’un axe (A) de calage de l’aube (10) et une extrémité axiale inférieure fermée par une paroi de fond (58b), - une bague d’immobilisation (52) qui s’étend autour du pied (14) et à l’intérieur du bol (58), et un élément de sécurité (110, 110’) qui assure la retenue du pied (14) vis-à-vis du bol (58), ledit au moins un élément de sécurité (110, 110’) ayant une forme générale allongée et traversant des orifices (112, 114, 126) alignés de la paroi de fond (58b) du bol (58) ainsi que de l’extrémité libre (28) du pied (14). Figure pour l'abrégé : Figure 18System (34) for controlling the angular pitch of a propeller blade (10), for an aircraft turbine engine, characterized in that it comprises: - a blade (10) comprising a blade (12) connected to a root (14), - a bowl (58) comprising an annular wall (58a) extending around an axis (A) for wedging the blade (10) and a lower axial end closed by a bottom wall ( 58b), - an immobilization ring (52) which extends around the foot (14) and inside the bowl (58), and a safety element (110, 110') which ensures the retention of the foot (14) vis-à-vis the bowl (58), said at least one safety element (110, 110') having a generally elongated shape and passing through orifices (112, 114, 126) aligned in the bottom wall ( 58b) of the bowl (58) as well as the free end (28) of the foot (14). Figure for abstract: Figure 18

FR2105788A 2020-07-24 2021-06-02 PROPELLER BLADE ANGULAR PITCH CONTROL SYSTEM FOR AN AIRCRAFT TURBOMACHINE Active FR3123696B1 (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
FR2105788A FR3123696B1 (en) 2021-06-02 2021-06-02 PROPELLER BLADE ANGULAR PITCH CONTROL SYSTEM FOR AN AIRCRAFT TURBOMACHINE
PCT/FR2021/051315 WO2022018358A1 (en) 2020-07-24 2021-07-15 System for controlling the pitch setting of a propeller blade for an aircraft turbine engine
CN202180051532.6A CN115989178A (en) 2020-07-24 2021-07-15 System for controlling the pitch setting of propeller blades of an aircraft turbine engine
EP21755512.7A EP4185523B1 (en) 2020-07-24 2021-07-15 System for controlling the pitch setting of a propeller blade for an aircraft turbine engine
US18/006,285 US11981418B2 (en) 2020-07-24 2021-07-15 System for controlling the pitch setting of a propeller vane for an aircraft turbine engine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2105788A FR3123696B1 (en) 2021-06-02 2021-06-02 PROPELLER BLADE ANGULAR PITCH CONTROL SYSTEM FOR AN AIRCRAFT TURBOMACHINE
FR2105788 2021-06-02

Publications (2)

Publication Number Publication Date
FR3123696A1 FR3123696A1 (en) 2022-12-09
FR3123696B1 true FR3123696B1 (en) 2023-04-21

Family

ID=76601464

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2105788A Active FR3123696B1 (en) 2020-07-24 2021-06-02 PROPELLER BLADE ANGULAR PITCH CONTROL SYSTEM FOR AN AIRCRAFT TURBOMACHINE

Country Status (1)

Country Link
FR (1) FR3123696B1 (en)

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1573000A (en) * 1921-07-20 1926-02-16 Heath Spencer Propeller-blade mounting
DE4203205C2 (en) * 1992-02-05 1995-12-07 Muehlbauer Luftfahrttechn Gmbh Propeller blade storage
FR3017163B1 (en) 2014-02-04 2016-02-12 Snecma DEVICE FOR A NON-CAREED PROPELLER HAVING A VARIABLE SHIFT OF A TURBOMACHINE
FR3021030B1 (en) * 2014-05-14 2018-01-05 Ratier Figeac SECURED ANCHOR BLADE IN RADIAL TRANSLATION, PROPELLER, TURBOMACHINE AND AIRCRAFT
FR3080322B1 (en) 2018-04-20 2020-03-27 Safran Aircraft Engines BLADE COMPRISING A COMPOSITE MATERIAL STRUCTURE AND MANUFACTURING METHOD THEREOF

Also Published As

Publication number Publication date
FR3123696A1 (en) 2022-12-09

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