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FR3077601B1 - DAWN OF AIRCRAFT TURBOMACHINE - Google Patents

DAWN OF AIRCRAFT TURBOMACHINE Download PDF

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Publication number
FR3077601B1
FR3077601B1 FR1851069A FR1851069A FR3077601B1 FR 3077601 B1 FR3077601 B1 FR 3077601B1 FR 1851069 A FR1851069 A FR 1851069A FR 1851069 A FR1851069 A FR 1851069A FR 3077601 B1 FR3077601 B1 FR 3077601B1
Authority
FR
France
Prior art keywords
blade
bowl
edge
lateral edges
coating
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
FR1851069A
Other languages
French (fr)
Other versions
FR3077601A1 (en
Inventor
Marc-Etienne Loisel Bruno
Aline Marie Deflandre Stephanie
Jacques Delcoigne Eric
Denis Daniel Limousin Franck
Nicole Person Laetitia
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 FR1851069A priority Critical patent/FR3077601B1/en
Publication of FR3077601A1 publication Critical patent/FR3077601A1/en
Application granted granted Critical
Publication of FR3077601B1 publication Critical patent/FR3077601B1/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
    • F01D5/22—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
    • F01D5/288—Protective coatings for blades

Landscapes

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

Abstract

Aube de rotor (10) pour une turbomachine d'aéronef, cette aube présentant un axe (A) de rotation une fois solidaire d'un rotor et un axe d'empilement (X) et comportant une pale (16) s'étendant entre une plateforme interne (19) et une plateforme externe (20) qui porte au moins une léchette (31, 32) en saillie, ladite pale comportant un intrados (16a) et un extrados et ladite plateforme externe comportant, du côté desdits intrados et extrados, des bords latéraux (21, 22) configurés pour coopérer par complémentarité avec des bords latéraux (22, 21) complémentaires d'aubes adjacentes, ces bords latéraux comportant chacun un revêtement (36) anti-usure situé dans une cuvette (38) du bord latéral correspondant, cette cuvette (38) comprenant une paroi de fond (39) s'étendant entre deux parois latérales (40a, 40b) bordant ladite cuvette, une première (40a) desdites parois latérales faisant partie d'une portion saillante du bord latéral correspondant, et une seconde (40b) desdites parois latérales faisant partie d'une portion en creux de ce bord latéral, chaque revêtement étant destiné à prendre appui dans un plan d'appui (P) sur un revêtement d'une aube adjacente du rotor portant une pluralité de ces aubes, caractérisée en ce que ladite première paroi latérale (40a) de chaque bord latéral est reliée directement à une paroi incurvée convexe (44) du bord latéral, qui est située en dehors de la cuvette et qui définit au moins en partie un sommet de ladite portion saillante, cette paroi incurvée convexe comportant une extrémité (44a) tangente audit plan d'appui (P) et une extrémité (44b) opposée en retrait par rapport à ce plan.Rotor blade (10) for an aircraft turbomachine, this blade having an axis (A) of rotation once secured to a rotor and a stacking axis (X) and comprising a blade (16) extending between an internal platform (19) and an external platform (20) which carries at least one protruding wiper (31, 32), said blade comprising a lower surface (16a) and an upper surface and said external platform comprising, on the side of said lower surface and upper surface , lateral edges (21, 22) configured to cooperate by complementarity with lateral edges (22, 21) complementary to adjacent blades, these lateral edges each comprising an anti-wear coating (36) situated in a bowl (38) of the corresponding side edge, this bowl (38) comprising a bottom wall (39) extending between two side walls (40a, 40b) bordering said bowl, a first (40a) of said side walls forming part of a projecting portion of the edge corresponding side, and a second (40b) d Said side walls forming part of a hollow portion of this lateral edge, each coating being intended to bear in a support plane (P) on a coating of an adjacent blade of the rotor carrying a plurality of these blades, characterized in that said first side wall (40a) of each side edge is connected directly to a convex curved wall (44) of the side edge, which is located outside the bowl and which defines at least in part a top of said projecting portion , this convex curved wall comprising an end (44a) tangent to said support plane (P) and an opposite end (44b) set back relative to this plane.

FR1851069A 2018-02-08 2018-02-08 DAWN OF AIRCRAFT TURBOMACHINE Active FR3077601B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1851069A FR3077601B1 (en) 2018-02-08 2018-02-08 DAWN OF AIRCRAFT TURBOMACHINE

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1851069 2018-02-08
FR1851069A FR3077601B1 (en) 2018-02-08 2018-02-08 DAWN OF AIRCRAFT TURBOMACHINE

Publications (2)

Publication Number Publication Date
FR3077601A1 FR3077601A1 (en) 2019-08-09
FR3077601B1 true FR3077601B1 (en) 2020-01-17

Family

ID=61913417

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1851069A Active FR3077601B1 (en) 2018-02-08 2018-02-08 DAWN OF AIRCRAFT TURBOMACHINE

Country Status (1)

Country Link
FR (1) FR3077601B1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3129685A1 (en) 2021-11-29 2023-06-02 Safran Aircraft Engines Aircraft engine blade including stub with puzzle assembly

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2860741B1 (en) * 2003-10-10 2007-04-13 Snecma Moteurs PROCESS FOR THE REPAIR OF METALLIC PARTS, ESPECIALLY TURBINE BLADES OF GAS TURBINE ENGINES
US7934315B2 (en) * 2006-08-11 2011-05-03 United Technologies Corporation Method of repairing shrouded turbine blades with cracks in the vicinity of the outer shroud notch
FR2970999B1 (en) * 2011-02-02 2015-03-06 Snecma CURRENT TURBOMACHINE AUBES, MOBILE TURBOMACHINE WHEEL AND TURBOMACHINE COMPRISING THE SAME, AND PROCESS FOR THEIR MANUFACTURE
FR2985759B1 (en) * 2012-01-17 2014-03-07 Snecma MOBILE AUB OF TURBOMACHINE

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3129685A1 (en) 2021-11-29 2023-06-02 Safran Aircraft Engines Aircraft engine blade including stub with puzzle assembly

Also Published As

Publication number Publication date
FR3077601A1 (en) 2019-08-09

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