FR3106617B1 - STATOR BLADED SECTOR WITH IMPROVED PERFORMANCES - Google Patents

STATOR BLADED SECTOR WITH IMPROVED PERFORMANCES Download PDF

Info

Publication number
FR3106617B1
FR3106617B1 FR2000699A FR2000699A FR3106617B1 FR 3106617 B1 FR3106617 B1 FR 3106617B1 FR 2000699 A FR2000699 A FR 2000699A FR 2000699 A FR2000699 A FR 2000699A FR 3106617 B1 FR3106617 B1 FR 3106617B1
Authority
FR
France
Prior art keywords
improved performances
sector
bladed sector
blades
platform
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
FR2000699A
Other languages
French (fr)
Other versions
FR3106617A1 (en
Inventor
Jean Cahen
Cyril Léo Benoit
Romain Noselli
Jean-Philippe Mallat-Desmortiers
Gomez Mireya Sanchez
Etienne Léon Francois
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 FR2000699A priority Critical patent/FR3106617B1/en
Publication of FR3106617A1 publication Critical patent/FR3106617A1/en
Application granted granted Critical
Publication of FR3106617B1 publication Critical patent/FR3106617B1/en
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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/321—Application in turbines in gas turbines for a special turbine stage
    • F05D2220/3215—Application in turbines in gas turbines for a special turbine stage the last stage of the turbine
    • 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
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • 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
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • 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
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise
    • F05D2260/961—Preventing, counteracting or reducing vibration or noise by mistuning rotor blades or stator vanes with irregular interblade spacing, airfoil shape
    • 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)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L’invention concerne un secteur aubagé statorique (23) monobloc de turbomachine comprenant une première et une deuxième plateformes (24 ; 26) s’étendant suivant une direction circonférentielle (AY) et destinées chacune à délimiter une portion d’une veine d’écoulement fluide (Vp), et des pales (22) qui relient chacune la première plateforme (24) à la deuxième plateforme (26) en étant espacées les unes des autres suivant la direction circonférentielle, dans lequel au moins deux pales (22) ont des épaisseurs différentes. Figure pour l’abrégé : Figure 3The invention relates to a one-piece turbine engine bladed stator sector (23) comprising first and second platforms (24; 26) extending in a circumferential direction (AY) and each intended to delimit a portion of a flow path fluid (Vp), and blades (22) which each connect the first platform (24) to the second platform (26) while being spaced from each other in the circumferential direction, in which at least two blades (22) have different thicknesses. Figure for the abstract: Figure 3

FR2000699A 2020-01-24 2020-01-24 STATOR BLADED SECTOR WITH IMPROVED PERFORMANCES Active FR3106617B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR2000699A FR3106617B1 (en) 2020-01-24 2020-01-24 STATOR BLADED SECTOR WITH IMPROVED PERFORMANCES

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2000699 2020-01-24
FR2000699A FR3106617B1 (en) 2020-01-24 2020-01-24 STATOR BLADED SECTOR WITH IMPROVED PERFORMANCES

Publications (2)

Publication Number Publication Date
FR3106617A1 FR3106617A1 (en) 2021-07-30
FR3106617B1 true FR3106617B1 (en) 2022-10-14

Family

ID=69903668

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2000699A Active FR3106617B1 (en) 2020-01-24 2020-01-24 STATOR BLADED SECTOR WITH IMPROVED PERFORMANCES

Country Status (1)

Country Link
FR (1) FR3106617B1 (en)

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2928962B1 (en) * 2008-03-19 2013-10-18 Snecma TURBINE DISPENSER WITH HOLLOW BLADES.
US8043063B2 (en) * 2009-03-26 2011-10-25 Pratt & Whitney Canada Corp. Intentionally mistuned integrally bladed rotor
ITTO20120517A1 (en) * 2012-06-14 2013-12-15 Avio Spa AERODYNAMIC PROFILE PLATE FOR A GAS TURBINE SYSTEM
FR3079871B1 (en) * 2018-04-10 2020-05-08 Safran Aircraft Engines TURBINE DISTRIBUTOR EQUIPPED WITH A HOLDING JUNK

Also Published As

Publication number Publication date
FR3106617A1 (en) 2021-07-30

Similar Documents

Publication Publication Date Title
US6851932B2 (en) Vibration damper assembly for the buckets of a turbine
KR102314454B1 (en) System for cooling seal rails of tip shroud of turbine blade
CN1840860B (en) Steam turbine blade, steam turbine rotor, steam turbine with those blades and rotors, and power plant with the turbines
CN101037947B (en) Damper cooled turbine blade
US8105039B1 (en) Airfoil tip shroud damper
US8851847B2 (en) Rotor for a turbo machine
JP2005214207A (en) Rotor blade for rotary machine
US20070053778A1 (en) Shroud honeycomb cutter
GB2353826A (en) Aerofoil to platform transition in gas turbine blade/vane
EP1826360A2 (en) Turbine bucket platform cooling circuit and method
EP1658923A9 (en) Method for making a repaired turbine engine stationary vane assembly and repaired assembly
EP1734229A3 (en) Bipedal damper turbine blade
EP1914384A3 (en) Part span shrouded fan blisk
KR960034690A (en) Closed loop steam cooling bucket
JP2005214206A (en) Rotor blade for rotary machine
EP1816353A3 (en) Compressor stator bleed system
US10934849B2 (en) Endwall contouring for a turbomachine
US20160333704A1 (en) Turbine blade damper system having pin with slots
DE774049T1 (en) SHOVEL FOR A TURBINE ROTOR AND MEANS FOR POSITIONING DAMPING ELEMENTS
FR3099520B1 (en) Turbomachine wheel
IL157989A (en) Integral swirl knife edge injection assembly
FR3106617B1 (en) STATOR BLADED SECTOR WITH IMPROVED PERFORMANCES
US10704392B2 (en) Tip shroud fillets for turbine rotor blades
EP2977548A1 (en) Axial turbomachine compressor blade with branches
DE69815731D1 (en) Impeller for turbine pumps equipped with blades with an improved profile

Legal Events

Date Code Title Description
PLFP Fee payment

Year of fee payment: 2

PLSC Publication of the preliminary search report

Effective date: 20210730

PLFP Fee payment

Year of fee payment: 3

PLFP Fee payment

Year of fee payment: 4

PLFP Fee payment

Year of fee payment: 5