FR3096727B1 - Aube de turbine dotée d’une cavité de fragilisation d’une section frangible - Google Patents

Aube de turbine dotée d’une cavité de fragilisation d’une section frangible Download PDF

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Publication number
FR3096727B1
FR3096727B1 FR1905588A FR1905588A FR3096727B1 FR 3096727 B1 FR3096727 B1 FR 3096727B1 FR 1905588 A FR1905588 A FR 1905588A FR 1905588 A FR1905588 A FR 1905588A FR 3096727 B1 FR3096727 B1 FR 3096727B1
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FR
France
Prior art keywords
stilt
blade
turbine blade
embrittlement
cavity
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
FR1905588A
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English (en)
Other versions
FR3096727A1 (fr
Inventor
Matthieu Claude Jean Denaux
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 Helicopter Engines SAS
Original Assignee
Safran Helicopter 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
Priority to FR1905588A priority Critical patent/FR3096727B1/fr
Application filed by Safran Helicopter Engines SAS filed Critical Safran Helicopter Engines SAS
Priority to CN202080040046.XA priority patent/CN113891983B/zh
Priority to CA3139054A priority patent/CA3139054A1/fr
Priority to EP20726420.1A priority patent/EP3976931B1/fr
Priority to US17/614,039 priority patent/US11846206B2/en
Priority to PL20726420.1T priority patent/PL3976931T3/pl
Priority to PCT/EP2020/063781 priority patent/WO2020239490A1/fr
Publication of FR3096727A1 publication Critical patent/FR3096727A1/fr
Application granted granted Critical
Publication of FR3096727B1 publication Critical patent/FR3096727B1/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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • 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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/02—Shutting-down responsive to overspeed
    • 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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of rotor
    • 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
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow 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
    • 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
    • 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
    • F05D2250/20—Three-dimensional
    • F05D2250/29—Three-dimensional machined; miscellaneous
    • F05D2250/294—Three-dimensional machined; miscellaneous grooved
    • 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
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • F05D2250/712—Shape curved concave
    • 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
    • F05D2270/02—Purpose of the control system to control rotational speed (n)
    • F05D2270/021—Purpose of the control system to control rotational speed (n) to prevent overspeed

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)

Abstract

Cette aube de turbine d'une turbomachine comporte une pale (11) et un pied (12), ledit pied comprenant une échasse (13) présentant des flancs latéraux à profil curviligne, ladite échasse comprenant une zone frangible adaptée pour subir une rupture de l’échasse si des efforts radiaux supérieurs à un seuil sont exercés sur l’aube, en particuler des efforts centrifuges lors d’un état de survitesse de la turbine. La zone frangible comprend au moins une cavité oblongue (17) de frangibilité pratiquée sur au moins l’un des flancs latéraux de l’échasse, ladite cavité oblongue s’étendant dans une direction axiale de l’échasse selon un axe longitudinal (X-X’) parallèle à ou compris dans un plan de section minimale (P) dans lequel se situe une section transversale minimale de l’échasse. Figure pour l’abrégé : Fig 6
FR1905588A 2019-05-27 2019-05-27 Aube de turbine dotée d’une cavité de fragilisation d’une section frangible Active FR3096727B1 (fr)

Priority Applications (7)

Application Number Priority Date Filing Date Title
FR1905588A FR3096727B1 (fr) 2019-05-27 2019-05-27 Aube de turbine dotée d’une cavité de fragilisation d’une section frangible
CA3139054A CA3139054A1 (fr) 2019-05-27 2020-05-18 Aube de turbine dotee d'une cavite de fragilisation d'une section frangible
EP20726420.1A EP3976931B1 (fr) 2019-05-27 2020-05-18 Aube de turbine dotée d'une cavité de fragilisation d'une section frangible
US17/614,039 US11846206B2 (en) 2019-05-27 2020-05-18 Turbine vane provided with a recess for embrittlement of a frangible section
CN202080040046.XA CN113891983B (zh) 2019-05-27 2020-05-18 设置有用于易碎段脆化的凹部的涡轮叶片
PL20726420.1T PL3976931T3 (pl) 2019-05-27 2020-05-18 Łopatka turbiny mająca osłabione wgłębienie o przekroju łamliwym
PCT/EP2020/063781 WO2020239490A1 (fr) 2019-05-27 2020-05-18 Aube de turbine dotée d'une cavité de fragilisation d'une section frangible

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1905588A FR3096727B1 (fr) 2019-05-27 2019-05-27 Aube de turbine dotée d’une cavité de fragilisation d’une section frangible
FR1905588 2019-05-27

Publications (2)

Publication Number Publication Date
FR3096727A1 FR3096727A1 (fr) 2020-12-04
FR3096727B1 true FR3096727B1 (fr) 2021-06-25

Family

ID=68138342

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1905588A Active FR3096727B1 (fr) 2019-05-27 2019-05-27 Aube de turbine dotée d’une cavité de fragilisation d’une section frangible

Country Status (7)

Country Link
US (1) US11846206B2 (fr)
EP (1) EP3976931B1 (fr)
CN (1) CN113891983B (fr)
CA (1) CA3139054A1 (fr)
FR (1) FR3096727B1 (fr)
PL (1) PL3976931T3 (fr)
WO (1) WO2020239490A1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR20230081267A (ko) * 2021-11-30 2023-06-07 두산에너빌리티 주식회사 터빈 블레이드, 이를 포함하는 터빈 및 가스터빈

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB881850A (en) 1959-05-05 1961-11-08 Gen Electric Improvements in turbine speed limiting arrangement
US5435694A (en) * 1993-11-19 1995-07-25 General Electric Company Stress relieving mount for an axial blade
US10458257B2 (en) * 2013-12-23 2019-10-29 Safran Aircraft Engines Blade comprising a shank, provided with a depressed portion
FR3015553B1 (fr) * 2013-12-23 2019-05-31 Safran Aircraft Engines Aube comprenant une echasse, munie d'une seule portion en depression
FR3025553B1 (fr) * 2014-09-08 2019-11-29 Safran Aircraft Engines Aube a becquet amont
FR3067625B1 (fr) * 2017-06-16 2019-12-27 Safran Aircraft Engines Procede de fabrication d’une aube de rotor pour une turbomachine d’aeronef
CN109139123B (zh) * 2018-08-09 2019-08-23 南京航空航天大学 一种涡轮叶片的飞脱断裂位置和飞脱断裂转速的定制方法

Also Published As

Publication number Publication date
US20220235665A1 (en) 2022-07-28
US11846206B2 (en) 2023-12-19
EP3976931A1 (fr) 2022-04-06
WO2020239490A1 (fr) 2020-12-03
EP3976931B1 (fr) 2023-08-09
CA3139054A1 (fr) 2020-12-03
CN113891983B (zh) 2023-12-22
FR3096727A1 (fr) 2020-12-04
CN113891983A (zh) 2022-01-04
PL3976931T3 (pl) 2023-12-04

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