FR3084696B1 - IMPROVED BALANCING SYSTEM FOR AIRCRAFT TURBOMACHINE - Google Patents

IMPROVED BALANCING SYSTEM FOR AIRCRAFT TURBOMACHINE Download PDF

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Publication number
FR3084696B1
FR3084696B1 FR1857171A FR1857171A FR3084696B1 FR 3084696 B1 FR3084696 B1 FR 3084696B1 FR 1857171 A FR1857171 A FR 1857171A FR 1857171 A FR1857171 A FR 1857171A FR 3084696 B1 FR3084696 B1 FR 3084696B1
Authority
FR
France
Prior art keywords
balancing system
aircraft turbomachine
improved balancing
annular row
mounting holes
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
FR1857171A
Other languages
French (fr)
Other versions
FR3084696A1 (en
Inventor
Nadege Pauline Audrey Hugon
Thomas Giraudeau
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 FR1857171A priority Critical patent/FR3084696B1/en
Priority to FR1908695A priority patent/FR3084697B1/en
Priority to US16/527,445 priority patent/US10975720B2/en
Publication of FR3084696A1 publication Critical patent/FR3084696A1/en
Application granted granted Critical
Publication of FR3084696B1 publication Critical patent/FR3084696B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/027—Arrangements for balancing
    • 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
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • 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)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Testing Of Balance (AREA)

Abstract

L'invention se rapporte à un système d'équilibrage (40) de turbomachine d'aéronef comprenant une première rangée annulaire (44a) de premiers orifices de montage (42a) d'organes d'équilibrage, et une seconde rangée annulaire (44b) de seconds orifices de montage (42b) d'organes d'équilibrage décalée axialement de la première rangée annulaire (44a), le nombre et les positions angulaires des premiers orifices de montage (42a) étant identiques au nombre et aux positions angulaires des seconds orifices de montage (42b).The invention relates to an aircraft turbomachine balancing system (40) comprising a first annular row (44a) of first mounting holes (42a) of balancing members, and a second annular row (44b) second mounting holes (42b) of balancing members axially offset from the first annular row (44a), the number and angular positions of the first mounting holes (42a) being identical to the number and angular positions of the second holes mounting bracket (42b).

FR1857171A 2018-07-31 2018-07-31 IMPROVED BALANCING SYSTEM FOR AIRCRAFT TURBOMACHINE Active FR3084696B1 (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
FR1857171A FR3084696B1 (en) 2018-07-31 2018-07-31 IMPROVED BALANCING SYSTEM FOR AIRCRAFT TURBOMACHINE
FR1908695A FR3084697B1 (en) 2018-07-31 2019-07-30 Improved balancing system for aircraft turbine engine
US16/527,445 US10975720B2 (en) 2018-07-31 2019-07-31 Balancing system for an aircraft turbomachine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1857171 2018-07-31
FR1857171A FR3084696B1 (en) 2018-07-31 2018-07-31 IMPROVED BALANCING SYSTEM FOR AIRCRAFT TURBOMACHINE

Publications (2)

Publication Number Publication Date
FR3084696A1 FR3084696A1 (en) 2020-02-07
FR3084696B1 true FR3084696B1 (en) 2021-06-04

Family

ID=63722628

Family Applications (2)

Application Number Title Priority Date Filing Date
FR1857171A Active FR3084696B1 (en) 2018-07-31 2018-07-31 IMPROVED BALANCING SYSTEM FOR AIRCRAFT TURBOMACHINE
FR1908695A Active FR3084697B1 (en) 2018-07-31 2019-07-30 Improved balancing system for aircraft turbine engine

Family Applications After (1)

Application Number Title Priority Date Filing Date
FR1908695A Active FR3084697B1 (en) 2018-07-31 2019-07-30 Improved balancing system for aircraft turbine engine

Country Status (1)

Country Link
FR (2) FR3084696B1 (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3119647B1 (en) * 2021-02-11 2023-01-13 Safran Aircraft Engines Turbomachine rotor flange repair process

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS6185501A (en) * 1984-10-03 1986-05-01 Ngk Insulators Ltd Balance adjusting method of ceramics rotor and adjusting jig available thereof
FR2943726B1 (en) * 2009-03-31 2014-04-25 Snecma ROTATING INPUT COVER FOR TURBOMACHINE, COMPRISING AN EXTREMITY BEFORE EXCENTREE
FR2986046B1 (en) * 2012-01-24 2016-01-08 Snecma ASSEMBLY FOR A TURBOMACHINE BLOWER ROTOR
US9388697B2 (en) * 2012-07-17 2016-07-12 Solar Turbines Incorporated First stage compressor disk configured for balancing the compressor rotor assembly
FR2996255B1 (en) * 2012-10-03 2018-05-25 Safran Aircraft Engines MOTOR BALANCING DEVICE FOR TURBOMACHINE INPUT HOOD

Also Published As

Publication number Publication date
FR3084697B1 (en) 2023-04-28
FR3084697A1 (en) 2020-02-07
FR3084696A1 (en) 2020-02-07

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