FR3104636B1 - IMPROVED DESIGN STATOR SECTOR FOR AIRCRAFT TURBOMACHINE - Google Patents

IMPROVED DESIGN STATOR SECTOR FOR AIRCRAFT TURBOMACHINE Download PDF

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Publication number
FR3104636B1
FR3104636B1 FR1914565A FR1914565A FR3104636B1 FR 3104636 B1 FR3104636 B1 FR 3104636B1 FR 1914565 A FR1914565 A FR 1914565A FR 1914565 A FR1914565 A FR 1914565A FR 3104636 B1 FR3104636 B1 FR 3104636B1
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FR
France
Prior art keywords
sector
improved design
stator sector
aircraft turbomachine
design stator
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
FR1914565A
Other languages
French (fr)
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FR3104636A1 (en
Inventor
Laurent Gilles Dezouche
Julien Marc Antoine Prevost
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 FR1914565A priority Critical patent/FR3104636B1/en
Publication of FR3104636A1 publication Critical patent/FR3104636A1/en
Application granted granted Critical
Publication of FR3104636B1 publication Critical patent/FR3104636B1/en
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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
    • 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
    • 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
    • F05D2240/122—Fluid guiding means, e.g. vanes related to the trailing edge of a stator vane
    • 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
    • F05D2240/125—Fluid guiding means, e.g. vanes related to the tip of a stator vane
    • 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]
    • F05D2260/941—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] particularly aimed at mechanical or thermal stress reduction
    • 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
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/11—Purpose of the control system to prolong engine life
    • F05D2270/114—Purpose of the control system to prolong engine life by limiting mechanical stresses
    • 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)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L’invention se rapporte à un secteur de stator (30) pour de turbomachine d’aéronef, le secteur comportant un premier secteur de virole (34) ainsi que des pales de stator (40), chaque pale étant solidaire du premier secteur de virole (34) au niveau d’un premier élément (42a) parmi une tête de pale et un pied de pale. Selon l’invention, le premier élément (42a) d’au moins l’une des pales de stator (40) comporte une portion de fixation (52) solidarisée au premier secteur de virole (34), ainsi qu’au moins une portion libre (54) désolidarisée du premier secteur de virole (34), ladite portion libre (54) correspondant à une extrémité du premier élément (42a) selon une direction de la corde (53) de cet élément (42a). Figure pour l’abrégé : Figure 2.The invention relates to a stator sector (30) for an aircraft turbine engine, the sector comprising a first shroud sector (34) as well as stator blades (40), each blade being integral with the first shroud sector (34) at the level of a first element (42a) among a blade tip and a blade root. According to the invention, the first element (42a) of at least one of the stator blades (40) comprises an attachment portion (52) secured to the first shell sector (34), as well as at least one free (54) detached from the first ferrule sector (34), said free portion (54) corresponding to one end of the first element (42a) in a direction of the chord (53) of this element (42a). Figure for abstract: Figure 2.

FR1914565A 2019-12-17 2019-12-17 IMPROVED DESIGN STATOR SECTOR FOR AIRCRAFT TURBOMACHINE Active FR3104636B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1914565A FR3104636B1 (en) 2019-12-17 2019-12-17 IMPROVED DESIGN STATOR SECTOR FOR AIRCRAFT TURBOMACHINE

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1914565A FR3104636B1 (en) 2019-12-17 2019-12-17 IMPROVED DESIGN STATOR SECTOR FOR AIRCRAFT TURBOMACHINE
FR1914565 2019-12-17

Publications (2)

Publication Number Publication Date
FR3104636A1 FR3104636A1 (en) 2021-06-18
FR3104636B1 true FR3104636B1 (en) 2023-01-13

Family

ID=69811243

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1914565A Active FR3104636B1 (en) 2019-12-17 2019-12-17 IMPROVED DESIGN STATOR SECTOR FOR AIRCRAFT TURBOMACHINE

Country Status (1)

Country Link
FR (1) FR3104636B1 (en)

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2929983B1 (en) * 2008-04-14 2013-05-17 Snecma TURBINE ENGINE TURBINE DISPENSER SECTOR.
DE102014203605A1 (en) * 2014-02-27 2015-08-27 Rolls-Royce Deutschland Ltd & Co Kg Blade row group
DE102014205226A1 (en) * 2014-03-20 2015-09-24 Rolls-Royce Deutschland Ltd & Co Kg Blade row group
DE102016113568A1 (en) * 2016-07-22 2018-01-25 Rolls-Royce Deutschland Ltd & Co Kg Method for producing a tandem vane segment
CN107762973B (en) * 2017-10-20 2020-06-16 哈尔滨工程大学 Compressor corner region stability-expanding blade and trailing edge groove forming method thereof
KR102048874B1 (en) * 2018-04-09 2019-11-26 두산중공업 주식회사 Turbine vane having improved flexibility

Also Published As

Publication number Publication date
FR3104636A1 (en) 2021-06-18

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