FR3095234B1 - Ensemble de turbomachine comprenant un dispositif de limitation de temperature pour fond d’alveole non refroidi - Google Patents

Ensemble de turbomachine comprenant un dispositif de limitation de temperature pour fond d’alveole non refroidi Download PDF

Info

Publication number
FR3095234B1
FR3095234B1 FR1904211A FR1904211A FR3095234B1 FR 3095234 B1 FR3095234 B1 FR 3095234B1 FR 1904211 A FR1904211 A FR 1904211A FR 1904211 A FR1904211 A FR 1904211A FR 3095234 B1 FR3095234 B1 FR 3095234B1
Authority
FR
France
Prior art keywords
alveole
uncooled
assembly including
limitation device
temperature limitation
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
FR1904211A
Other languages
English (en)
Other versions
FR3095234A1 (fr
Inventor
Pierre Vincent
Simon José Pierre Amoedo
Josselin Luc Florent Sicard
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 FR1904211A priority Critical patent/FR3095234B1/fr
Publication of FR3095234A1 publication Critical patent/FR3095234A1/fr
Application granted granted Critical
Publication of FR3095234B1 publication Critical patent/FR3095234B1/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
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • 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
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • 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

Dans un agencement de rotor (1) comprenant un disque (8) dont la périphérie est formée de dents alternant avec des alvéoles recevant des pieds (14) d’aubes (3) et où des canaux de ventilation (27) sont délimitées entre les faces inférieures (35) des pieds et les fonds des alvéoles (36) et parcourus par des débits de gaz chauds (E2) pouvant comprendre un débit de fuite originaire de la veine d’écoulement (10) ; la section des canaux n’est pas uniforme mais très différente entre une partie calibrante (31 ou 32) et une partie débitante (30), beaucoup plus large et plus longue pour diminuer la vitesse des gaz et les échanges de chaleur nuisibles avec le disque (8) et les pieds (14) des aubes (3). Figure pour l’abrégé : fig. 2.
FR1904211A 2019-04-19 2019-04-19 Ensemble de turbomachine comprenant un dispositif de limitation de temperature pour fond d’alveole non refroidi Active FR3095234B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1904211A FR3095234B1 (fr) 2019-04-19 2019-04-19 Ensemble de turbomachine comprenant un dispositif de limitation de temperature pour fond d’alveole non refroidi

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1904211A FR3095234B1 (fr) 2019-04-19 2019-04-19 Ensemble de turbomachine comprenant un dispositif de limitation de temperature pour fond d’alveole non refroidi
FR1904211 2019-04-19

Publications (2)

Publication Number Publication Date
FR3095234A1 FR3095234A1 (fr) 2020-10-23
FR3095234B1 true FR3095234B1 (fr) 2021-07-09

Family

ID=68072571

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1904211A Active FR3095234B1 (fr) 2019-04-19 2019-04-19 Ensemble de turbomachine comprenant un dispositif de limitation de temperature pour fond d’alveole non refroidi

Country Status (1)

Country Link
FR (1) FR3095234B1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3126141A1 (fr) * 2021-08-11 2023-02-17 Safran Aircraft Engines Rotor de turbine a ventilation amelioree

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2485632B1 (fr) * 1980-06-30 1985-07-05 Snecma Perfectionnement aux systemes de ventilation des aubes et disques de turbines
FR2905139B1 (fr) * 2006-08-25 2012-09-28 Snecma Aube de rotor d'une turbomachine
US8210821B2 (en) * 2008-07-08 2012-07-03 General Electric Company Labyrinth seal for turbine dovetail
FR2969209B1 (fr) * 2010-12-21 2019-06-21 Safran Aircraft Engines Etage de turbine pour turbomachine d'aeronef, presentant une etancheite amelioree entre le flasque aval et les aubes de la turbine
FR2995003B1 (fr) * 2012-09-03 2014-08-15 Snecma Rotor de turbine pour une turbomachine

Also Published As

Publication number Publication date
FR3095234A1 (fr) 2020-10-23

Similar Documents

Publication Publication Date Title
GB2475448A8 (en) Gas turbine exhaust diffuser
FR2402060A1 (fr) Aube de turbomachine a dispositif de refroidissement perfectionne
EP1593813A1 (fr) Dispositif de refroidissement pour anneau fixe de turbine à gaz
FR3095234B1 (fr) Ensemble de turbomachine comprenant un dispositif de limitation de temperature pour fond d’alveole non refroidi
CN107849931B (zh) 静叶及具备该静叶的燃气涡轮
FR2385900A1 (fr) Aube mobile refroidie pour moteur a turbine a gaz
JP5496469B2 (ja) ターボ機械内で冷却流体をリアルタイムに調節するための方法及びシステム
FR2417639A1 (fr) Dispositif refrigerant pour aube de distributeur de moteur a turbine a gaz
EP3960992A3 (fr) Amortisseur de flux de galet d'étanchéité
JP6639514B2 (ja) 軸流タービン
RU2330994C2 (ru) Центробежный компрессор
FR3103012B1 (fr) Rangée annulaire sectorisée d’aubes fixes
RU138296U1 (ru) Турбина газотурбинного двигателя
FR3107307B1 (fr) Système de récupération de chaleur pour système propulsif
JP2016031032A (ja) 内燃機関のシリンダヘッド
GB609028A (en) Improvements in or relating to cooling devices for the casings of gas turbine plant
FR3093540B1 (fr) Turbomachine double flux a gaz a bras echangeur thermique
RU2252315C1 (ru) Концевое уплотнение цилиндра паровой турбины
RU163785U1 (ru) Сопловой аппарат турбины газотурбинного двигателя
FR3082926B1 (fr) Echangeur thermique
FR3038363B1 (fr) Chambre annulaire de combustion a diaphragme fixe, pour une turbine a gaz
RU2260748C2 (ru) Камера сгорания газотурбинного двигателя
RU136092U1 (ru) Охлаждаемая лопатка турбины
FR3101665B1 (fr) Distributeur de turbine à aubage en composite à matrice céramique traversé par un circuit de ventilation métallique
FR3104692B1 (fr) Echangeur de chaleur comportant une paroi inter-aubes pourvue de générateurs de turbulence creux

Legal Events

Date Code Title Description
PLFP Fee payment

Year of fee payment: 2

PLSC Publication of the preliminary search report

Effective date: 20201023

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