Nothing Special   »   [go: up one dir, main page]

FR3091552B1 - Rotor disc socket intended to receive a turbomachine blade - Google Patents

Rotor disc socket intended to receive a turbomachine blade Download PDF

Info

Publication number
FR3091552B1
FR3091552B1 FR1900202A FR1900202A FR3091552B1 FR 3091552 B1 FR3091552 B1 FR 3091552B1 FR 1900202 A FR1900202 A FR 1900202A FR 1900202 A FR1900202 A FR 1900202A FR 3091552 B1 FR3091552 B1 FR 3091552B1
Authority
FR
France
Prior art keywords
receive
rotor disc
bearing surface
intended
bearing
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
FR1900202A
Other languages
French (fr)
Other versions
FR3091552A1 (en
Inventor
Joao Antonio Amorim
Richaud Quentin De
Nicolas Xavier Trappier
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 FR1900202A priority Critical patent/FR3091552B1/en
Publication of FR3091552A1 publication Critical patent/FR3091552A1/en
Application granted granted Critical
Publication of FR3091552B1 publication Critical patent/FR3091552B1/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
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type

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

L’invention concerne un disque (1) de rotor s’étendant circonférentiellement autour d’un axe, comportant au moins un alvéole destiné à recevoir au moins une aube (3) de turbomachine, l’alvéole (2) comportant au moins deux portées situées circonférentiellement de part et d’autre d’un plan radial médian (P) de l’alvéole (2), chaque portée comportant une surface d’appui (9a,9b) destinée à coopérer avec une surface d’appui (9a,9b) complémentaire de l’aube (3), caractérisé en ce que l’alvéole (2) comporte pour chaque portée un ressaut (10) radialement interne et/ou un ressaut radialement externe, à l’une des extrémités respectivement interne et/ou externe de la surface d’appui (9a,9b), chaque ressaut (10, 11) comprenant une surface concave.The invention relates to a rotor disc (1) extending circumferentially around an axis, comprising at least one cavity intended to receive at least one turbine engine blade (3), the cavity (2) comprising at least two bearing surfaces. located circumferentially on either side of a radial median plane (P) of the cell (2), each bearing surface comprising a bearing surface (9a, 9b) intended to cooperate with a bearing surface (9a, 9b) complementary to the blade (3), characterized in that the cell (2) comprises for each bearing a radially internal projection (10) and / or a radially external projection, at one of the respectively internal ends and / or external of the bearing surface (9a, 9b), each projection (10, 11) comprising a concave surface.

FR1900202A 2019-01-09 2019-01-09 Rotor disc socket intended to receive a turbomachine blade Active FR3091552B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1900202A FR3091552B1 (en) 2019-01-09 2019-01-09 Rotor disc socket intended to receive a turbomachine blade

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1900202A FR3091552B1 (en) 2019-01-09 2019-01-09 Rotor disc socket intended to receive a turbomachine blade

Publications (2)

Publication Number Publication Date
FR3091552A1 FR3091552A1 (en) 2020-07-10
FR3091552B1 true FR3091552B1 (en) 2021-05-21

Family

ID=67514713

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1900202A Active FR3091552B1 (en) 2019-01-09 2019-01-09 Rotor disc socket intended to receive a turbomachine blade

Country Status (1)

Country Link
FR (1) FR3091552B1 (en)

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19728085A1 (en) * 1997-07-02 1999-01-07 Asea Brown Boveri Joint connection between two joining partners and their use
US6183202B1 (en) * 1999-04-30 2001-02-06 General Electric Company Stress relieved blade support
JP5227241B2 (en) * 2009-04-17 2013-07-03 株式会社日立製作所 Turbine rotor, turbine rotor blade coupling structure, steam turbine and power generation equipment
EP2546465A1 (en) * 2011-07-14 2013-01-16 Siemens Aktiengesellschaft Blade root, corresponding blade, rotor disc, and turbomachine assembly

Also Published As

Publication number Publication date
FR3091552A1 (en) 2020-07-10

Similar Documents

Publication Publication Date Title
FR2585069A1 (en) DEVICE FOR LIMITING THE ANGULAR DEBATMENT OF AUBES MOUNTED ON A TURBOMACHINE ROTOR DISK
FR3050689B3 (en) ADAPTER FOR ROLLING ASSEMBLY AND ROLLING ASSEMBLY COMPRISING SAME
FR3066552B1 (en) ASSEMBLY ON A TURBOMACHINE SHAFT OF A MONOBLOC BLADE DISC AND A LOW PRESSURE COMPRESSOR ROTOR WITH AT LEAST TWO STAGES OF MOBILE BLADES
FR3085714B1 (en) TURBOMACHINE ROTOR INCLUDING MEANS LIMITING THE MOVEMENTS OF THE DAWN IN THE ROTOR DISC
FR3029960B1 (en) BLADDER WHEEL WITH RADIAL SEAL FOR A TURBOMACHINE TURBINE
FR3091552B1 (en) Rotor disc socket intended to receive a turbomachine blade
EP3147525A1 (en) Friction disc, in particular for motor vehicle
FR3091553B1 (en) Blade intended to be mounted on a rotor disk of a turbomachine
FR3097904B1 (en) Inter-vane platform with sacrificial box
FR3078100B1 (en) BLADED CROWN FOR TURBOMACHINE STATOR OF WHICH THE BLADES ARE CONNECTED TO THE EXTERNAL RUBBER BY CONICAL SUPPORT AND FRANGIBLE PIONE
CH337264A (en) Eddy current apparatus
FR3091725B1 (en) TOGETHER FOR A TURBOMACHINE
FR3035447B1 (en) TURBOMOTEUR FOR AN AIRCRAFT EQUIPPED WITH AN AUTOMATIC ACTIVATION CENTER
FR2922588A1 (en) Rotor disk or drum i.e. booster drum, for e.g. turbojet engine of airplane, has flange including orifice for mounting bolt, where rim of bolt cooperates with edges of reinforcement of flange for immobilizing bolt in orifice
US20160305259A1 (en) Turbine blade retention configuration
FR3055145B1 (en) ANGULAR AREA OF TURBOMACHINE STATOR BLADE
FR3100563B1 (en) Polyspherical turbomachine hub for variable pitch blades
FR3070422B1 (en) DAGGER ATTACHMENT WITH STRAIGHTENER VANE SEAL
FR3100835B1 (en) ROTOR BLADE FOR A TURBOMACHINE
FR3041714A1 (en) TURBOMACHINE COMPRESSOR, ESPECIALLY AIRCRAFT TURBOPROPULSER OR AIRCRAFT TURBINEACTOR
JP2017534795A (en) Screw bolt, turbine casing, turbine, and method for assembling a turbine casing
EP4368845A3 (en) Articulated component and mechanical system comprising such a component
FR3074518B1 (en) CONNECTION BETWEEN A CERAMIC MATRIX COMPOSITE DISTRIBUTOR AND A METAL SUPPORT OF A TURBOMACHINE TURBINE
FR3009593A1 (en) VIBRATION DAMPING DEVICE
FR3103855B1 (en) Improved blade leading edge structure.

Legal Events

Date Code Title Description
PLFP Fee payment

Year of fee payment: 2

PLSC Publication of the preliminary search report

Effective date: 20200710

PLFP Fee payment

Year of fee payment: 3

PLFP Fee payment

Year of fee payment: 4

PLFP Fee payment

Year of fee payment: 5

PLFP Fee payment

Year of fee payment: 6