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FR3108947B1 - REDUCER MODULE FOR AN AIRCRAFT TURBOMACHINE - Google Patents

REDUCER MODULE FOR AN AIRCRAFT TURBOMACHINE Download PDF

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Publication number
FR3108947B1
FR3108947B1 FR2003278A FR2003278A FR3108947B1 FR 3108947 B1 FR3108947 B1 FR 3108947B1 FR 2003278 A FR2003278 A FR 2003278A FR 2003278 A FR2003278 A FR 2003278A FR 3108947 B1 FR3108947 B1 FR 3108947B1
Authority
FR
France
Prior art keywords
drive shaft
input shaft
section
reducer
aircraft turbomachine
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
FR2003278A
Other languages
French (fr)
Other versions
FR3108947A1 (en
Inventor
Xavier Jean Yves Alain Agneray
Didier Gabriel Bertrand Desombre
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 FR2003278A priority Critical patent/FR3108947B1/en
Publication of FR3108947A1 publication Critical patent/FR3108947A1/en
Application granted granted Critical
Publication of FR3108947B1 publication Critical patent/FR3108947B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • 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
    • F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
    • 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
    • F05D2240/60—Shafts
    • F05D2240/62—Flexible
    • 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
    • F05D2260/40—Transmission of power
    • F05D2260/403—Transmission of power through the shape of the drive components
    • F05D2260/4031—Transmission of power through the shape of the drive components as in toothed gearing
    • F05D2260/40311—Transmission of power through the shape of the drive components as in toothed gearing of the epicyclical, planetary or differential type

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • General Details Of Gearings (AREA)
  • Retarders (AREA)

Abstract

Module de turbomachine (1) pour un aéronef, comportant : un réducteur mécanique (7), un arbre d’entraînement (4, 15) relié à un arbre d’entrée (8) qui entraîne en rotation un solaire (7a) du réducteur, cet arbre d’entraînement comportant au moins un premier tronçon (4a) élastiquement déformable, caractérisé en ce que l’arbre d’entraînement est accouplé à l’arbre d’entrée par une pièce annulaire (30) intermédiaire qui comprend des cannelures externes (30a) d’accouplement avec l’arbre d’entrée et des cannelures internes (30b) d’accouplement avec l’arbre d’entraînement, la pièce intermédiaire comportant une première paroi annulaire (40c) formant un premier flanc transversal d’un second tronçon (32) élastiquement déformable, et ledit arbre d’entrée comportant une seconde paroi annulaire (8c) sensiblement radiale formant un second flanc transversal de ce second tronçon. Figure pour l'abrégé : Figure 4Turbomachine module (1) for an aircraft, comprising: a mechanical reducer (7), a drive shaft (4, 15) connected to an input shaft (8) which rotates a sun gear (7a) of the reducer , this drive shaft comprising at least a first elastically deformable section (4a), characterized in that the drive shaft is coupled to the input shaft by an intermediate annular part (30) which comprises external splines (30a) for coupling with the input shaft and internal splines (30b) for coupling with the drive shaft, the intermediate part comprising a first annular wall (40c) forming a first transverse flank of a elastically deformable second section (32), and said input shaft comprising a second substantially radial annular wall (8c) forming a second transverse flank of this second section. Figure for abstract: Figure 4

FR2003278A 2020-04-01 2020-04-01 REDUCER MODULE FOR AN AIRCRAFT TURBOMACHINE Active FR3108947B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR2003278A FR3108947B1 (en) 2020-04-01 2020-04-01 REDUCER MODULE FOR AN AIRCRAFT TURBOMACHINE

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2003278A FR3108947B1 (en) 2020-04-01 2020-04-01 REDUCER MODULE FOR AN AIRCRAFT TURBOMACHINE
FR2003278 2020-04-01

Publications (2)

Publication Number Publication Date
FR3108947A1 FR3108947A1 (en) 2021-10-08
FR3108947B1 true FR3108947B1 (en) 2022-08-05

Family

ID=70804814

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2003278A Active FR3108947B1 (en) 2020-04-01 2020-04-01 REDUCER MODULE FOR AN AIRCRAFT TURBOMACHINE

Country Status (1)

Country Link
FR (1) FR3108947B1 (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3146658A1 (en) * 2023-03-16 2024-09-20 Safran Aircraft Engines Assembly comprising a shaft section guided by a flexibly held bearing

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2979121B1 (en) 2011-08-18 2013-09-06 Snecma MECHANICAL TRANSMISSION DEVICE FOR THE ROTATION DRIVE OF THE CONTRAROTATIVE PROPELLERS OF A DOUBLE PROPELLER TURBOPROPULSOR.
FR3075874B1 (en) * 2017-12-22 2019-11-22 Safran Aircraft Engines REDUCING TURBOMACHINE FOR AN AIRCRAFT

Also Published As

Publication number Publication date
FR3108947A1 (en) 2021-10-08

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