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FR3124824B1 - RIBBED TAB FOIL - Google Patents

RIBBED TAB FOIL Download PDF

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Publication number
FR3124824B1
FR3124824B1 FR2107139A FR2107139A FR3124824B1 FR 3124824 B1 FR3124824 B1 FR 3124824B1 FR 2107139 A FR2107139 A FR 2107139A FR 2107139 A FR2107139 A FR 2107139A FR 3124824 B1 FR3124824 B1 FR 3124824B1
Authority
FR
France
Prior art keywords
base
central tongue
ribbed
foil
connection
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
FR2107139A
Other languages
French (fr)
Other versions
FR3124824A1 (en
Inventor
Arnaud Martine
Pierre Marie Mulheim
Nicolas Daniel Delaporte
Antoine Giguet
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 FR2107139A priority Critical patent/FR3124824B1/en
Publication of FR3124824A1 publication Critical patent/FR3124824A1/en
Application granted granted Critical
Publication of FR3124824B1 publication Critical patent/FR3124824B1/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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3092—Protective layers between blade root and rotor disc surfaces, e.g. anti-friction layers
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3084—Fixing blades to rotors; Blade roots ; Blade spacers the blades being made of ceramics
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/30—Manufacture with deposition of material
    • F05D2230/31—Layer deposition
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/50—Building or constructing in particular ways
    • F05D2230/54—Building or constructing in particular ways by sheet metal manufacturing
    • 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)
  • Chemical & Material Sciences (AREA)
  • Ceramic Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

CLINQUANT A LANGUETTE NERVURÉE L’invention concerne un clinquant (1) destiné à être monté sur un pied d’aube (21) d’une aube (2) d’un rotor (3) de turbomachine comprenant : une base (11),une première et une deuxième branches latérales (12c, 12d) reliées entre elles par la base (11) et distantes l’une de l’autre,des bords latéraux (15) opposés s’étendant chacun sur la base (11) et les branches (12c, 12d),au moins une languette centrale (17) liée à la base (11) par une liaison (14) et s’étendant perpendiculairement à partir de la base (11), la languette centrale (17) est droite et comprend une nervure (13) située sur la liaison (14) entre la base (11) et la languette centrale (17). Figure à publier avec l’abrégé : Figure 1FILING WITH RIBBED TAB The invention relates to a foil (1) intended to be mounted on a blade root (21) of a blade (2) of a rotor (3) of a turbomachine comprising: a base (11), a first and a second side branches (12c, 12d) connected together by the base (11) and spaced apart from each other, opposite side edges (15) each extending on the base (11) and the branches (12c, 12d), at least one central tongue (17) linked to the base (11) by a connection (14) and extending perpendicularly from the base (11), the central tongue (17) is straight and comprises a rib (13) located on the connection (14) between the base (11) and the central tongue (17). Figure to be published with the abstract: Figure 1

FR2107139A 2021-07-01 2021-07-01 RIBBED TAB FOIL Active FR3124824B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR2107139A FR3124824B1 (en) 2021-07-01 2021-07-01 RIBBED TAB FOIL

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2107139 2021-07-01
FR2107139A FR3124824B1 (en) 2021-07-01 2021-07-01 RIBBED TAB FOIL

Publications (2)

Publication Number Publication Date
FR3124824A1 FR3124824A1 (en) 2023-01-06
FR3124824B1 true FR3124824B1 (en) 2023-12-15

Family

ID=78212177

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2107139A Active FR3124824B1 (en) 2021-07-01 2021-07-01 RIBBED TAB FOIL

Country Status (1)

Country Link
FR (1) FR3124824B1 (en)

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2890684B1 (en) 2005-09-15 2007-12-07 Snecma CLINKING FOR TURBOREACTOR BLADE
FR2921409B1 (en) 2007-09-25 2009-12-18 Snecma CLINKING FOR TURBOMACHINE DAWN.
DE102019210699A1 (en) * 2019-07-19 2021-01-21 MTU Aero Engines AG Intermediate element for a blade-rotor disk connection in a rotor of a turbomachine and a rotor for a turbomachine

Also Published As

Publication number Publication date
FR3124824A1 (en) 2023-01-06

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