FR3095230B1 - Dispositif de degivrage - Google Patents

Dispositif de degivrage Download PDF

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Publication number
FR3095230B1
FR3095230B1 FR1904065A FR1904065A FR3095230B1 FR 3095230 B1 FR3095230 B1 FR 3095230B1 FR 1904065 A FR1904065 A FR 1904065A FR 1904065 A FR1904065 A FR 1904065A FR 3095230 B1 FR3095230 B1 FR 3095230B1
Authority
FR
France
Prior art keywords
annular wall
inner annular
baffle
cavity
radial
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
FR1904065A
Other languages
English (en)
Other versions
FR3095230A1 (fr
Inventor
Damien Daniel Sylvain Lourit
Adrien Jacques Philippe Fabre
Pierre Jean-Baptiste Metge
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 FR1904065A priority Critical patent/FR3095230B1/fr
Priority to US17/604,170 priority patent/US11982195B2/en
Priority to CN202080034311.3A priority patent/CN113795650B/zh
Priority to EP20716855.0A priority patent/EP3956547B1/fr
Priority to PCT/EP2020/060453 priority patent/WO2020212344A1/fr
Publication of FR3095230A1 publication Critical patent/FR3095230A1/fr
Application granted granted Critical
Publication of FR3095230B1 publication Critical patent/FR3095230B1/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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/02—De-icing means for engines having icing phenomena
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • 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
    • 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
    • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
    • 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
    • F05D2230/30—Manufacture with deposition of material
    • 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
    • F05D2230/30—Manufacture with deposition of material
    • F05D2230/31—Layer deposition
    • 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
    • F05D2230/50—Building or constructing in particular ways
    • F05D2230/53—Building or constructing in particular ways by integrally manufacturing a component, e.g. by milling from a billet or one piece construction
    • 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
    • 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
    • F05D2240/128—Nozzles

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 concerne un bec (1) de séparation entre un flux primaire et un flux secondaire d’une turbomachine à double flux. Le bec (1) comprend une paroi annulaire extérieure (12), une paroi annulaire intérieure (13), une paroi annulaire radiale (14) et un déflecteur annulaire interne (16), définissant une première cavité (17) entre la paroi annulaire extérieure (12) et le déflecteur annulaire interne (16), et une deuxième cavité (18) entre la paroi annulaire intérieure (13), la paroi annulaire radiale (14) et le déflecteur annulaire interne (16). Figure pour l’abrégé : Fig. 1
FR1904065A 2019-04-16 2019-04-16 Dispositif de degivrage Active FR3095230B1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
FR1904065A FR3095230B1 (fr) 2019-04-16 2019-04-16 Dispositif de degivrage
US17/604,170 US11982195B2 (en) 2019-04-16 2020-04-14 Separation nozzle for aeronautic turbomachine
CN202080034311.3A CN113795650B (zh) 2019-04-16 2020-04-14 用于航空涡轮机的分离喷嘴
EP20716855.0A EP3956547B1 (fr) 2019-04-16 2020-04-14 Bec de separation de turbomachine aeronautique
PCT/EP2020/060453 WO2020212344A1 (fr) 2019-04-16 2020-04-14 Bec de separation de turbomachine aeronautique

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1904065 2019-04-16
FR1904065A FR3095230B1 (fr) 2019-04-16 2019-04-16 Dispositif de degivrage

Publications (2)

Publication Number Publication Date
FR3095230A1 FR3095230A1 (fr) 2020-10-23
FR3095230B1 true FR3095230B1 (fr) 2021-03-19

Family

ID=67956957

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1904065A Active FR3095230B1 (fr) 2019-04-16 2019-04-16 Dispositif de degivrage

Country Status (5)

Country Link
US (1) US11982195B2 (fr)
EP (1) EP3956547B1 (fr)
CN (1) CN113795650B (fr)
FR (1) FR3095230B1 (fr)
WO (1) WO2020212344A1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3131939B1 (fr) 2022-01-18 2024-01-12 Safran Aircraft Engines Bec de séparation de turbomachine axiale comprenant un passage de débit d’air de dégivrage s’étandant jusqu’au redresseur

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4860534A (en) * 1988-08-24 1989-08-29 General Motors Corporation Inlet particle separator with anti-icing means
US6561760B2 (en) * 2001-08-17 2003-05-13 General Electric Company Booster compressor deicer
US6725645B1 (en) * 2002-10-03 2004-04-27 General Electric Company Turbofan engine internal anti-ice device
US8205426B2 (en) * 2006-07-31 2012-06-26 General Electric Company Method and apparatus for operating gas turbine engines
US9309781B2 (en) * 2011-01-31 2016-04-12 General Electric Company Heated booster splitter plenum
EP2505789B1 (fr) * 2011-03-30 2016-12-28 Safran Aero Boosters SA Séparateur de flux gazeux avec dispositif de dégivrage par pont thermique
CN104675524B (zh) * 2013-11-27 2017-01-18 中航商用航空发动机有限责任公司 分流环、发动机防冰装置以及涡扇发动机
BE1022957B1 (fr) * 2015-04-20 2016-10-21 Techspace Aero S.A. Bec de separation degivrant de compresseur de turbomachine axiale
BE1023289B1 (fr) * 2015-07-17 2017-01-24 Safran Aero Boosters S.A. Bec de separation de compresseur basse pression de turbomachine axiale avec conduit annulaire de degivrage
BE1023354B1 (fr) * 2015-08-13 2017-02-13 Safran Aero Boosters S.A. Bec de separation degivrant de compresseur de turbomachine axiale
BE1023531B1 (fr) * 2015-10-15 2017-04-25 Safran Aero Boosters S.A. Dispositif degivrant de bec de separation de compresseur de turbomachine axiale
FR3051016B1 (fr) * 2016-05-09 2020-03-13 Safran Aircraft Engines Dispositif de degivrage d'un bec de separation de turbomachine aeronautique
BE1024684B1 (fr) * 2016-10-21 2018-05-25 Safran Aero Boosters S.A. Bec degivrant de compresseur de turbomachine axiale
GB201705734D0 (en) * 2017-04-10 2017-05-24 Rolls Royce Plc Flow splitter

Also Published As

Publication number Publication date
WO2020212344A1 (fr) 2020-10-22
US20220205366A1 (en) 2022-06-30
FR3095230A1 (fr) 2020-10-23
CN113795650A (zh) 2021-12-14
CN113795650B (zh) 2023-04-07
EP3956547A1 (fr) 2022-02-23
EP3956547B1 (fr) 2023-06-07
US11982195B2 (en) 2024-05-14

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