FR3062682B1 - Partie de turbomachine comprenant une paroi de separation de deux cavites pourvue de bossages - Google Patents

Partie de turbomachine comprenant une paroi de separation de deux cavites pourvue de bossages Download PDF

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Publication number
FR3062682B1
FR3062682B1 FR1700131A FR1700131A FR3062682B1 FR 3062682 B1 FR3062682 B1 FR 3062682B1 FR 1700131 A FR1700131 A FR 1700131A FR 1700131 A FR1700131 A FR 1700131A FR 3062682 B1 FR3062682 B1 FR 3062682B1
Authority
FR
France
Prior art keywords
bosses
air inlet
air outlet
radially
cavities
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
FR1700131A
Other languages
English (en)
Other versions
FR3062682A1 (fr
Inventor
Tewfik Boudebiza
Antoine Jean-Philippe BEAUJARD
Romain Bordoni Nils Edouard
Catherine PIKOVSKY
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 FR1700131A priority Critical patent/FR3062682B1/fr
Publication of FR3062682A1 publication Critical patent/FR3062682A1/fr
Application granted granted Critical
Publication of FR3062682B1 publication Critical patent/FR3062682B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D5/02—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
    • 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
    • F01D25/125—Cooling of bearings
    • 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
    • F01D5/087—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor in the radial passages of the rotor disc
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
    • 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)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

Une partie de turbomachine comprend un disque de rotor (32), un espace annulaire délimité extérieurement par le disque de rotor, et une paroi de séparation (76) qui partage l'espace annulaire en une cavité radialement interne (78) et une cavité radialement externe (80). La cavité radialement interne comporte une première entrée d'air (82) et une première sortie d'air (84), et la cavité radialement externe comporte une deuxième entrée d'air (86) et une deuxième sortie d'air (88). La paroi de séparation comporte une rangée annulaire de bossages (94) en saillie radialement vers l'extérieur espacés les uns des autres de sorte que les bossages délimitent des premiers canaux (96) débouchant dans, ou formant partiellement, la première entrée d'air ou la première sortie d'air, et de sorte que les bossages délimitent entre eux des deuxièmes canaux débouchant dans, ou formant partiellement, la deuxième entrée d'air ou la deuxième sortie d'air.
FR1700131A 2017-02-07 2017-02-07 Partie de turbomachine comprenant une paroi de separation de deux cavites pourvue de bossages Active FR3062682B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1700131A FR3062682B1 (fr) 2017-02-07 2017-02-07 Partie de turbomachine comprenant une paroi de separation de deux cavites pourvue de bossages

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1700131A FR3062682B1 (fr) 2017-02-07 2017-02-07 Partie de turbomachine comprenant une paroi de separation de deux cavites pourvue de bossages
FR1700131 2017-02-07

Publications (2)

Publication Number Publication Date
FR3062682A1 FR3062682A1 (fr) 2018-08-10
FR3062682B1 true FR3062682B1 (fr) 2019-04-19

Family

ID=59520950

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1700131A Active FR3062682B1 (fr) 2017-02-07 2017-02-07 Partie de turbomachine comprenant une paroi de separation de deux cavites pourvue de bossages

Country Status (1)

Country Link
FR (1) FR3062682B1 (fr)

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5555721A (en) * 1994-09-28 1996-09-17 General Electric Company Gas turbine engine cooling supply circuit
JP4091874B2 (ja) * 2003-05-21 2008-05-28 本田技研工業株式会社 ガスタービンエンジンの二次エア供給装置
FR2904036B1 (fr) * 2006-07-19 2008-08-29 Snecma Sa Systeme de ventilation d'une cavite aval de rouet de compresseur centrifuge
FR2937371B1 (fr) * 2008-10-20 2010-12-10 Snecma Ventilation d'une turbine haute-pression dans une turbomachine
FR2955152B1 (fr) * 2010-01-11 2012-05-11 Snecma Turbomachine a circulation de flux d'air de purge amelioree

Also Published As

Publication number Publication date
FR3062682A1 (fr) 2018-08-10

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