[go: up one dir, main page]
More Web Proxy on the site http://driver.im/

FR3020407B1 - Ensemble rotatif a double anneau en appui pour turbomachine - Google Patents

Ensemble rotatif a double anneau en appui pour turbomachine Download PDF

Info

Publication number
FR3020407B1
FR3020407B1 FR1453716A FR1453716A FR3020407B1 FR 3020407 B1 FR3020407 B1 FR 3020407B1 FR 1453716 A FR1453716 A FR 1453716A FR 1453716 A FR1453716 A FR 1453716A FR 3020407 B1 FR3020407 B1 FR 3020407B1
Authority
FR
France
Prior art keywords
radially
platforms
annular
turbomachine
downstream
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
FR1453716A
Other languages
English (en)
Other versions
FR3020407A1 (fr
Inventor
Pierre Guillaume Blanchard Stephane
Olivier Ito-Lardeau Youki
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
SNECMA 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, SNECMA SAS filed Critical Safran Aircraft Engines SAS
Priority to FR1453716A priority Critical patent/FR3020407B1/fr
Publication of FR3020407A1 publication Critical patent/FR3020407A1/fr
Application granted granted Critical
Publication of FR3020407B1 publication Critical patent/FR3020407B1/fr
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
    • 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
    • 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
    • F05D2240/55—Seals
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/14—Two-dimensional elliptical
    • F05D2250/141—Two-dimensional elliptical circular
    • 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
    • F05D2250/00—Geometry
    • F05D2250/40—Movement of components
    • F05D2250/41—Movement of components with one degree of freedom
    • 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)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne un ensemble rotatif pour turbomachine, comprenant un disque rotatif, des aubes, des plates-formes, un flasque (63) d'étanchéité s'étendant radialement entre les plates-formes (30) et le disque (16), en face aval de l'échasse (32) et du pied. Le flasque comprend radialement une partie sensiblement annulaire interne (66) et une partie sensiblement annulaire externe (64) en appui axial et radial l'une contre l'autre dans une zone du flasque radialement intermédiaire entre : - un bord périphérique radialement externe où la partie sensiblement annulaire externe (64) est engagée dans une gorge annulaire radiale des plates-formes (30), et - un bord périphérique radialement interne où la partie sensiblement annulaire interne (66) est axialement serrée entre, en amont, les dents du disque et les pieds d'aubes et, en aval, un anneau aval d'étanchéité (52).
FR1453716A 2014-04-24 2014-04-24 Ensemble rotatif a double anneau en appui pour turbomachine Active FR3020407B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1453716A FR3020407B1 (fr) 2014-04-24 2014-04-24 Ensemble rotatif a double anneau en appui pour turbomachine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1453716 2014-04-24
FR1453716A FR3020407B1 (fr) 2014-04-24 2014-04-24 Ensemble rotatif a double anneau en appui pour turbomachine

Publications (2)

Publication Number Publication Date
FR3020407A1 FR3020407A1 (fr) 2015-10-30
FR3020407B1 true FR3020407B1 (fr) 2019-05-10

Family

ID=51261039

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1453716A Active FR3020407B1 (fr) 2014-04-24 2014-04-24 Ensemble rotatif a double anneau en appui pour turbomachine

Country Status (1)

Country Link
FR (1) FR3020407B1 (fr)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2018110581A1 (fr) * 2016-12-13 2018-06-21 三菱日立パワーシステムズ株式会社 Procédé de démontage/assemblage de turbine à gaz, ensemble plaque d'étanchéité et rotor de turbine à gaz
TWI705182B (zh) 2016-12-13 2020-09-21 日商三菱日立電力系統股份有限公司 燃氣渦輪機的分解組裝方法、密封板組裝體及燃氣渦輪機輥
EP3536907B1 (fr) 2016-12-13 2021-03-31 Mitsubishi Power, Ltd. Procédé de désassemblage/assemblage de turbine à gaz, rotor de turbine à gaz et turbine à gaz
USD975135S1 (en) 2018-05-23 2023-01-10 Mitsubishi Heavy Industries, Ltd. Seal plate for rotary machine
USD960833S1 (en) 2018-05-23 2022-08-16 Mitsubishi Power, Ltd. Seal plate for rotary machine
FR3093131B1 (fr) * 2019-02-22 2021-10-01 Safran Aircraft Engines Ensemble pour turbomachine
FR3127255A1 (fr) 2021-09-23 2023-03-24 Safran Aircraft Engines Ensemble rotatif pour turbomachine

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2694046B1 (fr) * 1992-07-22 1994-09-23 Snecma Dispositif d'étanchéité et de rétention pour un rotor entaillé de brochages recevant des pieds d'aubes.
FR2960589B1 (fr) * 2010-05-28 2014-05-02 Snecma Roue a aubes pour une turbomachine, telle qu'un turboreacteur ou un turbopropulseur d'avion
US9181810B2 (en) * 2012-04-16 2015-11-10 General Electric Company System and method for covering a blade mounting region of turbine blades
JP5881523B2 (ja) * 2012-05-08 2016-03-09 三菱重工業株式会社 タービンロータ、ガスタービン、及びタービンロータにおけるシールアッセンブリの組立方法

Also Published As

Publication number Publication date
FR3020407A1 (fr) 2015-10-30

Similar Documents

Publication Publication Date Title
FR3020407B1 (fr) Ensemble rotatif a double anneau en appui pour turbomachine
FR3022944B1 (fr) Ensemble rotatif pour turbomachine
JP2014055588A5 (fr)
EP4279119A3 (fr) Pompe à sang
RU2016142470A (ru) Компрессор газотурбинного двигателя, содержащий лопатки с изменяемым углом установки
EP2302174A3 (fr) Turbine à gaz avec un joint à labyrinthe de la virole
WO2016179608A3 (fr) Joint d'étanchéité inter-arbres avec bague d'étanchéité asymétrique
FR2930595B1 (fr) Rotor de soufflante d'une turbomachine ou d'un moteur d'essai
JP2016079904A5 (fr)
FR3011032B1 (fr) Ensemble rotatif pour turbomachine
MY196921A (en) Impeller assembly for centrifugal pumps
FR3019584B1 (fr) Systeme de ventilation d'une turbine a l'aide d'orifices traversants et de lunules
RU2015115261A (ru) Стопорное кольцо лопаток для внутреннего кожуха компрессора осевой турбомашины
WO2015149732A3 (fr) Couronne d'aubes fixes, bague intérieure et turbomachine
RU2016115551A (ru) Рабочее колесо для осевой воздуходувки
RU2015146074A (ru) Внутренний бандаж для компрессора осевой турбомашины
MX2022010853A (es) Montaje de sello de eje.
EA201992173A1 (ru) Способ и устройство для уменьшения окружного дисбаланса давления в боковой полости рабочего колеса турбомашин
MX2016009570A (es) Soplador.
MX2015009575A (es) Sello de salida de caja de engranes.
FR3029960B1 (fr) Roue a aubes avec joint radial pour une turbine de turbomachine
RU2014125101A (ru) Барабан компрессора осевой турбомашины с двойным средством для фиксации лопаток
FR3075869B1 (fr) Roue mobile de turbine pour turbomachine d'aeronef, comprenant un anneau d'etancheite retenu radialement par des excroissances sur l'echasse des aubes
FR3026430B1 (fr) Roue de turbine dans une turbomachine
RU2014127525A (ru) Разблокируемое устройство для стопорения в осевом направлении уплотнительного кольца, с которым рабочее колесо ротора модуля турбомашины летательного аппарата осуществляет контакт

Legal Events

Date Code Title Description
PLFP Fee payment

Year of fee payment: 2

PLSC Publication of the preliminary search report

Effective date: 20151030

PLFP Fee payment

Year of fee payment: 3

PLFP Fee payment

Year of fee payment: 4

CD Change of name or company name

Owner name: SAFRAN AIRCRAFT ENGINES, FR

Effective date: 20170719

PLFP Fee payment

Year of fee payment: 5

PLFP Fee payment

Year of fee payment: 6

PLFP Fee payment

Year of fee payment: 7

PLFP Fee payment

Year of fee payment: 8

PLFP Fee payment

Year of fee payment: 9

PLFP Fee payment

Year of fee payment: 10

PLFP Fee payment

Year of fee payment: 11