FR3118990B1 - Rotor de turbine pour une turbomachine. - Google Patents

Rotor de turbine pour une turbomachine. Download PDF

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Publication number
FR3118990B1
FR3118990B1 FR2100570A FR2100570A FR3118990B1 FR 3118990 B1 FR3118990 B1 FR 3118990B1 FR 2100570 A FR2100570 A FR 2100570A FR 2100570 A FR2100570 A FR 2100570A FR 3118990 B1 FR3118990 B1 FR 3118990B1
Authority
FR
France
Prior art keywords
blade
rotor
lip
platform
tooth
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
FR2100570A
Other languages
English (en)
Other versions
FR3118990A1 (fr
Inventor
Julian Nicolas Girardeau
Benoit Guillaume Silet
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 FR2100570A priority Critical patent/FR3118990B1/fr
Priority to EP22705421.0A priority patent/EP4281652B1/fr
Priority to CN202280010978.9A priority patent/CN116783369A/zh
Priority to PCT/FR2022/050095 priority patent/WO2022157448A1/fr
Priority to US18/271,893 priority patent/US12270307B2/en
Publication of FR3118990A1 publication Critical patent/FR3118990A1/fr
Application granted granted Critical
Publication of FR3118990B1 publication Critical patent/FR3118990B1/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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
    • 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
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • 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
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/307—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the tip of a rotor blade
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/11—Two-dimensional triangular
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/12—Two-dimensional rectangular
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/182—Two-dimensional patterned crenellated, notched
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/183—Two-dimensional patterned zigzag
    • 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

La présente invention concerne un rotor (2) d'une turbine s'étendant autour d’un axe longitudinal (X-X'), comprenant au moins un disque de rotor (21) supportant à sa périphérie au moins une aube (20) de rotor, chaque aube (20) comprenant une pale (22) pourvue à son extrémité radialement externe d'une plateforme (26) munie d'une léchette amont (27) et d'une léchette aval (28), la plateforme (26) présentant un bord latéral avant (260) et un bord latéral arrière (261) par rapport au sens de rotation normal du rotor (2) autour de l'axe longitudinal (X-X'), et une portion extrados (264) qui s'étend dudit bord latéral avant (260) jusqu'à l'extrados de la pale (22). Cette aube est remarquable en ce que la léchette amont (27) et la léchette aval (28) comprennent chacune des découpes en dent de scie de façon à former une dent avant (271, 281) et une dent arrière (272, 282) contigües, en ce que la dent arrière (272, 282) présente un bord de coupe et en ce que la dent avant (271, 281) de chaque léchette (27, 28) est disposée sur la portion extrados (264) de la plateforme (26). Figure pour l’abrégé : Fig. 2
FR2100570A 2021-01-21 2021-01-21 Rotor de turbine pour une turbomachine. Active FR3118990B1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
FR2100570A FR3118990B1 (fr) 2021-01-21 2021-01-21 Rotor de turbine pour une turbomachine.
EP22705421.0A EP4281652B1 (fr) 2021-01-21 2022-01-18 Rotor de turbine pour une turbomachine
CN202280010978.9A CN116783369A (zh) 2021-01-21 2022-01-18 用于涡轮机的涡轮转子
PCT/FR2022/050095 WO2022157448A1 (fr) 2021-01-21 2022-01-18 Rotor de turbine pour une turbomachine
US18/271,893 US12270307B2 (en) 2021-01-21 2022-01-18 Turbine rotor for a turbomachine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2100570 2021-01-21
FR2100570A FR3118990B1 (fr) 2021-01-21 2021-01-21 Rotor de turbine pour une turbomachine.

Publications (2)

Publication Number Publication Date
FR3118990A1 FR3118990A1 (fr) 2022-07-22
FR3118990B1 true FR3118990B1 (fr) 2023-09-15

Family

ID=74860236

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2100570A Active FR3118990B1 (fr) 2021-01-21 2021-01-21 Rotor de turbine pour une turbomachine.

Country Status (5)

Country Link
US (1) US12270307B2 (fr)
EP (1) EP4281652B1 (fr)
CN (1) CN116783369A (fr)
FR (1) FR3118990B1 (fr)
WO (1) WO2022157448A1 (fr)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3153633A1 (fr) 2023-10-02 2025-04-04 Safran Aircraft Engines Léchette d’aube de turbomachine, turbomachine et procédé de fabrication
FR3153850A1 (fr) * 2023-10-05 2025-04-11 Safran Aircraft Engines Aube de rotor pour une turbomachine d’aeronef

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US23330A (en) * 1859-03-22 Improved construction of saw-teeth
US1046718A (en) 1910-02-18 1912-12-10 Lunkenheimer Co Exhaust-pressure regulator.
DE4015206C1 (fr) * 1990-05-11 1991-10-17 Mtu Muenchen Gmbh
DE4432998C1 (de) * 1994-09-16 1996-04-04 Mtu Muenchen Gmbh Anstreifbelag für metallische Triebwerkskomponente und Herstellungsverfahren
DE10047307A1 (de) * 2000-09-25 2002-08-01 Alstom Switzerland Ltd Dichtungsanordnung
US6805530B1 (en) * 2003-04-18 2004-10-19 General Electric Company Center-located cutter teeth on shrouded turbine blades
WO2014189875A1 (fr) * 2013-05-21 2014-11-27 Siemens Energy, Inc. Enveloppe de bout d'aube de turbine
US10648346B2 (en) * 2016-07-06 2020-05-12 General Electric Company Shroud configurations for turbine rotor blades
FR3072121B1 (fr) * 2017-10-06 2021-07-30 Safran Aircraft Engines Dispositif d'etancheite entre rotor et stator de turbomachine
FR3072716B1 (fr) * 2017-10-20 2019-09-27 Safran Aircraft Engines Aube de rotor de turbomachine, turbomachine associee
FR3077600B1 (fr) * 2018-02-08 2020-03-06 Safran Aircraft Engines Aube de turbomachine d'aeronef
FR3079868B1 (fr) * 2018-04-05 2020-11-06 Safran Aircraft Engines Lechette d'etancheite entre rotor et stator et turbine ainsi equipee

Also Published As

Publication number Publication date
US20240117750A1 (en) 2024-04-11
US12270307B2 (en) 2025-04-08
EP4281652A1 (fr) 2023-11-29
WO2022157448A1 (fr) 2022-07-28
EP4281652B1 (fr) 2024-10-23
CN116783369A (zh) 2023-09-19
FR3118990A1 (fr) 2022-07-22

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