FR3086701B1 - WATERPROOFING OF DAWN FOOT - Google Patents

WATERPROOFING OF DAWN FOOT Download PDF

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Publication number
FR3086701B1
FR3086701B1 FR1858930A FR1858930A FR3086701B1 FR 3086701 B1 FR3086701 B1 FR 3086701B1 FR 1858930 A FR1858930 A FR 1858930A FR 1858930 A FR1858930 A FR 1858930A FR 3086701 B1 FR3086701 B1 FR 3086701B1
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FR
France
Prior art keywords
annular
ring
blade
disc
teeth
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
FR1858930A
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French (fr)
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FR3086701A1 (en
Inventor
Clement Raphael Laroche
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.)
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Publication date
Application filed by Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Priority to FR1858930A priority Critical patent/FR3086701B1/en
Publication of FR3086701A1 publication Critical patent/FR3086701A1/en
Application granted granted Critical
Publication of FR3086701B1 publication Critical patent/FR3086701B1/en
Active legal-status Critical Current
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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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • 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)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne un ensemble rotatif pour turbomachine aéronautique, comprenant : - un disque (112) s'étendant circonférentiellement autour d'un axe (X) et présentant des alvéoles et des dents (120), - des aubes disposés dans les alvéoles, par l'intermédiaire d'un pied (116) d'aube, - un anneau mobile (28) disposé en amont du disque, - un jonc annulaire (30) d'étanchéité disposé axialement entre une face aval (34) de l'anneau mobile (28) et une face amont des dents (120) du disque (112) et des pieds (116) d'aubes, caractérisé en ce que les dents (120) et les pieds (116) d'aubes présentent chacun une saillie axiale (48a, 48b) dirigée vers l'anneau mobile (28), les saillies axiales formant conjointement une surface annulaire (49) continue qui fait radialement face au jonc annulaire (30), de façon que le jonc annulaire vienne annulairement en contact avec la surface annulaire (49) continue selon au moins une composante radiale.The invention relates to a rotary assembly for an aeronautical turbomachine, comprising: - a disc (112) extending circumferentially around an axis (X) and having cells and teeth (120), - blades arranged in the cells, by means of a root (116) of the blade, - a movable ring (28) disposed upstream of the disc, - an annular sealing ring (30) disposed axially between a downstream face (34) of the movable ring (28) and an upstream face of the teeth (120) of the disc (112) and of the blade roots (116), characterized in that the blade teeth (120) and the blade roots (116) each have a axial projection (48a, 48b) directed towards the movable ring (28), the axial projections jointly forming a continuous annular surface (49) which radially faces the annular ring (30), so that the annular ring comes into annular contact with the annular surface (49) continuous along at least one radial component.

FR1858930A 2018-09-28 2018-09-28 WATERPROOFING OF DAWN FOOT Active FR3086701B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1858930A FR3086701B1 (en) 2018-09-28 2018-09-28 WATERPROOFING OF DAWN FOOT

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1858930A FR3086701B1 (en) 2018-09-28 2018-09-28 WATERPROOFING OF DAWN FOOT

Publications (2)

Publication Number Publication Date
FR3086701A1 FR3086701A1 (en) 2020-04-03
FR3086701B1 true FR3086701B1 (en) 2021-01-01

Family

ID=64049436

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1858930A Active FR3086701B1 (en) 2018-09-28 2018-09-28 WATERPROOFING OF DAWN FOOT

Country Status (1)

Country Link
FR (1) FR3086701B1 (en)

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4523890A (en) * 1983-10-19 1985-06-18 General Motors Corporation End seal for turbine blade base
US6363610B1 (en) * 1999-10-21 2002-04-02 Allied Signal, Inc. Gas turbine rotor bimetallic ring seal and method therefor
US7052240B2 (en) * 2004-04-15 2006-05-30 General Electric Company Rotating seal arrangement for turbine bucket cooling circuits
FR3011032B1 (en) * 2013-09-25 2017-12-29 Snecma ROTARY ASSEMBLY FOR TURBOMACHINE

Also Published As

Publication number Publication date
FR3086701A1 (en) 2020-04-03

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