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FR3137121B1 - Bladed assembly with inter-platform connection by interposed rolling element - Google Patents

Bladed assembly with inter-platform connection by interposed rolling element Download PDF

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Publication number
FR3137121B1
FR3137121B1 FR2206154A FR2206154A FR3137121B1 FR 3137121 B1 FR3137121 B1 FR 3137121B1 FR 2206154 A FR2206154 A FR 2206154A FR 2206154 A FR2206154 A FR 2206154A FR 3137121 B1 FR3137121 B1 FR 3137121B1
Authority
FR
France
Prior art keywords
hollow
rolling element
platform
blade
inter
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
FR2206154A
Other languages
French (fr)
Other versions
FR3137121A1 (en
Inventor
Simon Jean-Marie Bernard Cousseau
Romain Claude Gabriel Bardon
Fabrice Joël Luc Chevillot
Fabrice Marcel Noël Garin
Lucien Henri Jacques Quennehen
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
Safran Ceramics SA
Original Assignee
Safran Aircraft Engines SAS
Safran Ceramics SA
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, Safran Ceramics SA filed Critical Safran Aircraft Engines SAS
Priority to FR2206154A priority Critical patent/FR3137121B1/en
Publication of FR3137121A1 publication Critical patent/FR3137121A1/en
Application granted granted Critical
Publication of FR3137121B1 publication Critical patent/FR3137121B1/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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • 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
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/282—Selecting composite materials, e.g. blades with reinforcing filaments
    • 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
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/284—Selection of ceramic materials
    • 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
    • F05D2250/20—Three-dimensional
    • F05D2250/24—Three-dimensional ellipsoidal
    • F05D2250/241—Three-dimensional ellipsoidal spherical
    • 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
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/36—Retaining components in desired mutual position by a form fit connection, e.g. by interlocking
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • F05D2300/6033—Ceramic matrix composites [CMC]

Landscapes

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

Abstract

Un ensemble aubagé (40) pour rotor de turbomachine comprend une pluralité d’aubes (42) réparties autour d’un axe (28) et comprenant chacune une pale (44), et une plateforme (46) en bout de pale comprenant un premier creux (56) et un second creux (60), de sorte que le premier creux (56) soit disposé radialement en vis-à-vis du second creux (60) de la plateforme d’une aube circonférentiellement adjacente. Un élément roulant (70) est logé dans le premier creux (56) de la plateforme de chaque aube et le second creux (60) de la plateforme de l’aube adjacente. En fonctionnement, les points de contact entre l’élément roulant et les creux peuvent se déplacer sur la surface de l’élément roulant, induisant ainsi une non-linéarité dans le comportement dynamique de l’ensemble aubagé de nature à limiter l’amplitude de vibrations de ce dernier. Figure pour l’abrégé : Figure 4A bladed assembly (40) for a turbomachine rotor comprises a plurality of blades (42) distributed around an axis (28) and each comprising a blade (44), and a platform (46) at the end of the blade comprising a first hollow (56) and a second hollow (60), so that the first hollow (56) is arranged radially opposite the second hollow (60) of the platform of a circumferentially adjacent blade. A rolling element (70) is housed in the first hollow (56) of the platform of each blade and the second hollow (60) of the platform of the adjacent blade. In operation, the points of contact between the rolling element and the recesses can move on the surface of the rolling element, thus inducing non-linearity in the dynamic behavior of the bladed assembly such as to limit the amplitude of vibrations of the latter. Figure for abstract: Figure 4

FR2206154A 2022-06-22 2022-06-22 Bladed assembly with inter-platform connection by interposed rolling element Active FR3137121B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR2206154A FR3137121B1 (en) 2022-06-22 2022-06-22 Bladed assembly with inter-platform connection by interposed rolling element

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2206154A FR3137121B1 (en) 2022-06-22 2022-06-22 Bladed assembly with inter-platform connection by interposed rolling element
FR2206154 2022-06-22

Publications (2)

Publication Number Publication Date
FR3137121A1 FR3137121A1 (en) 2023-12-29
FR3137121B1 true FR3137121B1 (en) 2024-06-21

Family

ID=83355268

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2206154A Active FR3137121B1 (en) 2022-06-22 2022-06-22 Bladed assembly with inter-platform connection by interposed rolling element

Country Status (1)

Country Link
FR (1) FR3137121B1 (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3159626A1 (en) * 2024-02-27 2025-08-29 Safran Aircraft Engines Device for damping the bladed assembly of an aircraft turbomachine

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10342207A1 (en) * 2003-09-12 2005-04-07 Alstom Technology Ltd Blade binding of a turbomachine
FR2955142B1 (en) 2010-01-13 2013-08-23 Snecma PIONE VIBRATION SHOCK ABSORBER BETWEEN ADJACENT AUB THREADS IN COMPOSITE MATERIAL OF A TURBOMACHINE MOBILE WHEEL.
FR2955608B1 (en) 2010-01-26 2013-01-11 Snecma LAMINATED VIBRATION SHOCK ABSORBER AND SHOES BETWEEN ADJACENT BLADE HEADS IN COMPOSITE MATERIAL OF A TURBOMACHINE MOBILE WHEEL.
FR2956152B1 (en) 2010-02-09 2012-07-06 Snecma VIBRATION DAMPING DEVICE BETWEEN ADJACENT BLADE HEADS IN COMPOSITE MATERIAL OF A MOBILE TURBOMACHINE WHEEL.
US8894368B2 (en) * 2012-01-04 2014-11-25 General Electric Company Device and method for aligning tip shrouds
US9765625B2 (en) * 2013-05-23 2017-09-19 MTU Aero Engines AG Turbomachine blade
PL416301A1 (en) * 2016-02-29 2017-09-11 General Electric Company Turbine engine shrouding bandage unit
CN110671155B (en) * 2019-10-18 2021-01-19 西安交通大学 An adaptive variable working condition optimal positive pressure damping blade structure and design method

Also Published As

Publication number Publication date
FR3137121A1 (en) 2023-12-29

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