FR2974865B1 - Rotor haute pression pour turbomachine d'aeronef, comprenant des moyens de detrompage associes a des boulons de prefixation de module de turbine - Google Patents

Rotor haute pression pour turbomachine d'aeronef, comprenant des moyens de detrompage associes a des boulons de prefixation de module de turbine

Info

Publication number
FR2974865B1
FR2974865B1 FR1153824A FR1153824A FR2974865B1 FR 2974865 B1 FR2974865 B1 FR 2974865B1 FR 1153824 A FR1153824 A FR 1153824A FR 1153824 A FR1153824 A FR 1153824A FR 2974865 B1 FR2974865 B1 FR 2974865B1
Authority
FR
France
Prior art keywords
disk
high pressure
bolts
auxiliary
detromping
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
FR1153824A
Other languages
English (en)
Other versions
FR2974865A1 (fr
Inventor
Cecile Alirot
Stephane Pierre Guillaume Blanchard
Fabrice Marcel Noel Garin
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
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 SNECMA SAS filed Critical SNECMA SAS
Priority to FR1153824A priority Critical patent/FR2974865B1/fr
Publication of FR2974865A1 publication Critical patent/FR2974865A1/fr
Application granted granted Critical
Publication of FR2974865B1 publication Critical patent/FR2974865B1/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
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • F01D5/066—Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00—Function
    • F05B2260/30—Retaining components in desired mutual position
    • F05B2260/301—Retaining bolts or nuts
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • 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)
  • Structures Of Non-Positive Displacement Pumps (AREA)
FR1153824A 2011-05-04 2011-05-04 Rotor haute pression pour turbomachine d'aeronef, comprenant des moyens de detrompage associes a des boulons de prefixation de module de turbine Active FR2974865B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1153824A FR2974865B1 (fr) 2011-05-04 2011-05-04 Rotor haute pression pour turbomachine d'aeronef, comprenant des moyens de detrompage associes a des boulons de prefixation de module de turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1153824A FR2974865B1 (fr) 2011-05-04 2011-05-04 Rotor haute pression pour turbomachine d'aeronef, comprenant des moyens de detrompage associes a des boulons de prefixation de module de turbine

Publications (2)

Publication Number Publication Date
FR2974865A1 FR2974865A1 (fr) 2012-11-09
FR2974865B1 true FR2974865B1 (fr) 2013-07-05

Family

ID=44550491

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1153824A Active FR2974865B1 (fr) 2011-05-04 2011-05-04 Rotor haute pression pour turbomachine d'aeronef, comprenant des moyens de detrompage associes a des boulons de prefixation de module de turbine

Country Status (1)

Country Link
FR (1) FR2974865B1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102013216377A1 (de) 2013-08-19 2015-03-12 Rolls-Royce Deutschland Ltd & Co Kg Verfahren zum Auswuchten und zur Montage eines Turbinenrotors

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2885167B1 (fr) * 2005-04-29 2007-06-29 Snecma Moteurs Sa Module de turbine pour moteur a turbine a gaz
FR2938292B1 (fr) * 2008-11-07 2010-12-24 Snecma Bride annulaire de fixation d'un element de rotor ou de stator dans une turbomachine

Also Published As

Publication number Publication date
FR2974865A1 (fr) 2012-11-09

Similar Documents

Publication Publication Date Title
WO2012068068A3 (fr) Système de manipulation de fluide comprenant un turbogénérateur egr dédié
WO2013147969A3 (fr) Système tampon de bâti de milieu de turbine
EP4411128A3 (fr) Agencement de système de propulsion pour moteur à turbine à gaz à double flux
EP2479383A3 (fr) Ensemble d'aube de stator de moteur de turbine à gaz
WO2015057310A3 (fr) Noyau de refroidissement de plate-forme pour aube de rotor de turbine à gaz
WO2012087420A3 (fr) Procédé pour équilibrer un ensemble tournant d'un moteur à turbine à gaz
EP2573329A3 (fr) Architecture de système d'air pour un module de cadre de turbine intermédiaire
WO2015071070A3 (fr) Boulon, système d'étanchéité et turbine à gaz
ATE552407T1 (de) Dichtungsvorrichtung eines abgasturboladers
WO2013154640A3 (fr) Collecteur interne permettant de tourner la distribution du flux d'un cadre de turbine intermédiaire
UA92447C2 (uk) Пристрій для з'єднання кільцевих фланців разом, зокрема, у турбомашині
EP2574845A3 (fr) Système de combustion et son procédé d'assemblage
EP3779167A3 (fr) Architecture de turbine à gaz avec compresseur de basse pression entre les paliers de butée des rotors d'haute et basse pression
EP4350125A3 (fr) Ensemble d'étanchéité sans contact pour moteur à turbine à gaz
WO2010111357A3 (fr) Systèmes centrifuges de compression de gaz hydrogène à haut débit, procédés et composants associés
EP2511482A3 (fr) Système de refroidissement d'un segment d'anneau de turbine et procédé
EP2706241A3 (fr) Pale de ventilateur
MY188544A (en) System and method for startup of a power production plant
WO2015069338A3 (fr) Système de régulation thermique d'élément d'étanchéité à l'air extérieur d'aube de moteur à turbine à gaz
EP2613014A3 (fr) Étage de moteur à turbine à gaz et procédé associé de modification
EP2538022A3 (fr) Bouclier thermique TOBI fixé de manière non mécanique
BRPI0912030B8 (pt) união de elementos de rotor ou de estator de uma turbomáquina e turbomáquina, tal como um turborreator ou um turbopropulsor
EP2075436A3 (fr) Cône d'entrée pour une turbine à gaz
RU2012130351A (ru) Ступень турбины в турбомашине
FR2961554B1 (fr) Secteur angulaire de redresseur pour compresseur de turbomachine, redresseur de turbomachine et turbomachine comprenant un tel secteur

Legal Events

Date Code Title Description
PLFP Fee payment

Year of fee payment: 6

PLFP Fee payment

Year of fee payment: 7

PLFP Fee payment

Year of fee payment: 8

CD Change of name or company name

Owner name: SAFRAN AIRCRAFT ENGINES, FR

Effective date: 20170719

PLFP Fee payment

Year of fee payment: 9

PLFP Fee payment

Year of fee payment: 10

PLFP Fee payment

Year of fee payment: 11

PLFP Fee payment

Year of fee payment: 12

PLFP Fee payment

Year of fee payment: 13

PLFP Fee payment

Year of fee payment: 14