FR3120909B1 - Turbomachine blade with a reinforced trailing edge - Google Patents

Turbomachine blade with a reinforced trailing edge Download PDF

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Publication number
FR3120909B1
FR3120909B1 FR2102832A FR2102832A FR3120909B1 FR 3120909 B1 FR3120909 B1 FR 3120909B1 FR 2102832 A FR2102832 A FR 2102832A FR 2102832 A FR2102832 A FR 2102832A FR 3120909 B1 FR3120909 B1 FR 3120909B1
Authority
FR
France
Prior art keywords
blade
trailing edge
face
main radial
turbomachine blade
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
FR2102832A
Other languages
French (fr)
Other versions
FR3120909A1 (en
Inventor
Ba-Phuc Tang
Josserand Jacques André Bassery
Samuel Laurent Noël Mathieu Juge
De La Fond Andrès Ostau
Léo Amar
Yann François Louis Baraton
Nils Eliasson
Morgan Merrien
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 FR2102832A priority Critical patent/FR3120909B1/en
Publication of FR3120909A1 publication Critical patent/FR3120909A1/en
Application granted granted Critical
Publication of FR3120909B1 publication Critical patent/FR3120909B1/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
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for blades
    • 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
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/304—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the trailing edge of a rotor blade
    • 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
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/13—Refractory metals, i.e. Ti, V, Cr, Zr, Nb, Mo, Hf, Ta, W
    • F05D2300/133—Titanium
    • 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
    • F05D2300/20—Oxide or non-oxide ceramics

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne une aube mobile (10) de rotor de turbomachine s'étendant selon une direction principale radiale et selon une direction longitudinale, comportant une pale (12) délimitée par : - une face d'intrados (14) située d'un premier côté transversal de la pale (12); - une face d'extrados (16) située d'un deuxième côté transversal de la pale (12) ; - un bord d'attaque (18) d'orientation principale radiale, situé à une extrémité longitudinale amont de la pale (12) ; et - un bord de fuite (20) d'orientation principale radiale, situé à une extrémité longitudinale aval de la pale (12), dans laquelle l'aube mobile (10) est réalisée en un alliage de titane caractérisée en ce qu'elle comporte une couche de matériau de revêtement (22) qui recouvre en partie chacune de la face d'intrados (14) et de la face d'extrados (16) et qui recouvre aussi le bord de fuite (20). Figure pour l’abrégé : figure 1The invention relates to a movable blade (10) of a turbomachine rotor extending in a main radial direction and in a longitudinal direction, comprising a blade (12) delimited by: - an intrados face (14) located on a first transverse side of the blade (12); - an extrados face (16) located on a second transverse side of the blade (12); - a leading edge (18) of main radial orientation, located at an upstream longitudinal end of the blade (12); and - a trailing edge (20) of main radial orientation, located at a downstream longitudinal end of the blade (12), in which the movable blade (10) is made of a titanium alloy characterized in that it comprises a layer of covering material (22) which partly covers each of the intrados face (14) and the extrados face (16) and which also covers the trailing edge (20). Figure for abstract: figure 1

FR2102832A 2021-03-22 2021-03-22 Turbomachine blade with a reinforced trailing edge Active FR3120909B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR2102832A FR3120909B1 (en) 2021-03-22 2021-03-22 Turbomachine blade with a reinforced trailing edge

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2102832 2021-03-22
FR2102832A FR3120909B1 (en) 2021-03-22 2021-03-22 Turbomachine blade with a reinforced trailing edge

Publications (2)

Publication Number Publication Date
FR3120909A1 FR3120909A1 (en) 2022-09-23
FR3120909B1 true FR3120909B1 (en) 2023-11-24

Family

ID=76283882

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2102832A Active FR3120909B1 (en) 2021-03-22 2021-03-22 Turbomachine blade with a reinforced trailing edge

Country Status (1)

Country Link
FR (1) FR3120909B1 (en)

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB0226686D0 (en) * 2002-11-15 2002-12-24 Rolls Royce Plc Method of damping vibration in metallic articles
US8118561B2 (en) * 2004-07-26 2012-02-21 General Electric Company Erosion- and impact-resistant coatings
US7186092B2 (en) * 2004-07-26 2007-03-06 General Electric Company Airfoil having improved impact and erosion resistance and method for preparing same
US9267218B2 (en) * 2011-09-02 2016-02-23 General Electric Company Protective coating for titanium last stage buckets

Also Published As

Publication number Publication date
FR3120909A1 (en) 2022-09-23

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