FR3111657B1 - Rotor de turbine de turbomachine muni d’un circuit de refroidissement. - Google Patents

Rotor de turbine de turbomachine muni d’un circuit de refroidissement. Download PDF

Info

Publication number
FR3111657B1
FR3111657B1 FR2006385A FR2006385A FR3111657B1 FR 3111657 B1 FR3111657 B1 FR 3111657B1 FR 2006385 A FR2006385 A FR 2006385A FR 2006385 A FR2006385 A FR 2006385A FR 3111657 B1 FR3111657 B1 FR 3111657B1
Authority
FR
France
Prior art keywords
rotor
lunules
annular groove
downstream
rotor disc
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
FR2006385A
Other languages
English (en)
Other versions
FR3111657A1 (fr
Inventor
Hassane Amara
Jean Michel Anthime Papail
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 FR2006385A priority Critical patent/FR3111657B1/fr
Publication of FR3111657A1 publication Critical patent/FR3111657A1/fr
Application granted granted Critical
Publication of FR3111657B1 publication Critical patent/FR3111657B1/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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • F01D5/082—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades on the side of the rotor disc
    • 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
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/085—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor
    • 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

La présente invention concerne un rotor de turbine de turbomachine d’aéronef, comprenant :- un disque de rotor amont,- un disque de rotor aval comprenant à sa périphérie une pluralité d’alvéoles de réception de pieds d’aubes,- un anneau d’étanchéité (6) muni d’une bride radiale annulaire (61), sur la face aval (613) de laquelle une pluralité de lunules (614) est formée. Ce rotor est remarquable en ce que l’anneau d’étanchéité (6) comprend sur la face aval (613) de sa bride radiale (61), une gorge annulaire (616) joignant les différentes lunules (614) et une pluralité de canaux d’injection d’air (617) qui s’étendent radialement vers l’extérieur depuis ladite gorge annulaire (616), cet anneau d’étanchéité (6) étant assemblé entre le disque de rotor amont et le disque de rotor aval, de façon à former un circuit de refroidissement desdites alvéoles mettant en communication fluidique une cavité radialement interne du rotor avec lesdites alvéoles, le circuit de refroidissement comprenant lesdites lunules (614), la gorge annulaire (616) et les canaux d’injection d’air (617). Figure pour l’abrégé : Fig. 3
FR2006385A 2020-06-18 2020-06-18 Rotor de turbine de turbomachine muni d’un circuit de refroidissement. Active FR3111657B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR2006385A FR3111657B1 (fr) 2020-06-18 2020-06-18 Rotor de turbine de turbomachine muni d’un circuit de refroidissement.

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2006385A FR3111657B1 (fr) 2020-06-18 2020-06-18 Rotor de turbine de turbomachine muni d’un circuit de refroidissement.
FR2006385 2020-06-18

Publications (2)

Publication Number Publication Date
FR3111657A1 FR3111657A1 (fr) 2021-12-24
FR3111657B1 true FR3111657B1 (fr) 2022-06-03

Family

ID=72178823

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2006385A Active FR3111657B1 (fr) 2020-06-18 2020-06-18 Rotor de turbine de turbomachine muni d’un circuit de refroidissement.

Country Status (1)

Country Link
FR (1) FR3111657B1 (fr)

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2918104B1 (fr) * 2007-06-27 2009-10-09 Snecma Sa Dispositif de refroidissement des alveoles d'un disque de rotor de turbomachine a double alimentation en air.
FR2961250B1 (fr) * 2010-06-14 2012-07-20 Snecma Dispositif de refroidissement des alveoles d'un disque de rotor de turbomachine a l'aval du cone d'entrainement
FR3019584B1 (fr) * 2014-04-07 2019-05-17 Safran Aircraft Engines Systeme de ventilation d'une turbine a l'aide d'orifices traversants et de lunules
FR3062415B1 (fr) * 2017-02-02 2019-06-07 Safran Aircraft Engines Rotor de turbine de turbomachine a ventilation par lamage

Also Published As

Publication number Publication date
FR3111657A1 (fr) 2021-12-24

Similar Documents

Publication Publication Date Title
US10753219B2 (en) Internally cooled seal runner and method of cooling seal runner of a gas turbine engine
GB617475A (en) Improvements relating to gas-turbine engines
US10533444B2 (en) Turbine shroud sealing architecture
KR20170117889A (ko) 터빈 블레이드의 팁 슈라우드의 시일 레일을 냉각시키는 시스템
US9915175B2 (en) Seal runner with controlled oil lubrication
JP5561368B2 (ja) 固定翼式ターボチャージャ
CN108291721B (zh) 过渡构造
JPH02108801A (ja) タービン動翼
US10260362B2 (en) Turbine vane assembly with ceramic matrix composite airfoil and friction fit metallic attachment features
EP1927725A3 (fr) Système pour faciliter le refroidissement de film récupéré distribué selon la préférence pour un assemblage d'anneaux de turbine
KR101704986B1 (ko) 축류 터빈의 래버린스 시일 장치 및 이를 구비한 배기가스 터빈 과급기
JP2010065698A (ja) ターボ機械用のシュラウド
US10794203B2 (en) Scavenge tube for a gas turbine engine
FR3111657B1 (fr) Rotor de turbine de turbomachine muni d’un circuit de refroidissement.
US9879550B2 (en) Outer shroud with gusset
GB805545A (en) Improvements in or relating to axial-flow fluid machines for example axial-flow turbines of gas-turbine engines
JP7085402B2 (ja) ガスタービン
JP2010127240A (ja) 羽根車の取付構造
GB787666A (en) Improvements in blades for gas turbine engines
WO2019123565A8 (fr) Turbine et turbocompresseur
FR3108149B1 (fr) Module de soufflante pour une turbomachine d’aeronef
RU138296U1 (ru) Турбина газотурбинного двигателя
FR3101374B1 (fr) Structure de refroidissement d’une turbine avec coopération radiale entre anneau d’étanchéité et disque de roue mobile
JP2014199059A (ja) 端壁部材及びガスタービン
FR3096397B1 (fr) Pion amovible sur distributeur de turbomachine

Legal Events

Date Code Title Description
PLFP Fee payment

Year of fee payment: 2

PLSC Publication of the preliminary search report

Effective date: 20211224

PLFP Fee payment

Year of fee payment: 3

PLFP Fee payment

Year of fee payment: 4