FR3111394B1 - Turbomachine comprenant un organe de séparation d’un flux d’air et un organe de redressement du flux d’air séparé. - Google Patents

Turbomachine comprenant un organe de séparation d’un flux d’air et un organe de redressement du flux d’air séparé. Download PDF

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Publication number
FR3111394B1
FR3111394B1 FR2006152A FR2006152A FR3111394B1 FR 3111394 B1 FR3111394 B1 FR 3111394B1 FR 2006152 A FR2006152 A FR 2006152A FR 2006152 A FR2006152 A FR 2006152A FR 3111394 B1 FR3111394 B1 FR 3111394B1
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FR
France
Prior art keywords
air flow
turbomachine
separation member
separate
blading
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
FR2006152A
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English (en)
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FR3111394A1 (fr
Inventor
Clément Raphaël Laroche
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 FR2006152A priority Critical patent/FR3111394B1/fr
Priority to PCT/FR2021/050995 priority patent/WO2021250339A1/fr
Publication of FR3111394A1 publication Critical patent/FR3111394A1/fr
Application granted granted Critical
Publication of FR3111394B1 publication Critical patent/FR3111394B1/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
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
    • 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
    • F05D2220/3216—Application in turbines in gas turbines for a special turbine stage for a special compressor stage
    • F05D2220/3217—Application in turbines in gas turbines for a special turbine stage for a special compressor stage for the first stage of a compressor or a low pressure compressor
    • 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
    • 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)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

Turbomachine d’axe longitudinal (X-X’) comprenant une soufflante délivrant un flux d’air principal (F) et un organe de séparation (20) configuré pour séparer ledit flux d’air (F) en un flux d’air primaire (F1) circulant dans une veine interne (VI) et un flux d’air secondaire (F2) circulant dans une veine externe (VE), la veine externe (VE) comprenant au moins un aubage (18) comprenant une pluralité d’aubes directrices de sortie configurées pour redresser le flux secondaire (F2) en un flux secondaire redressé (F2’’). L’organe de séparation (20) comprend un organe de redressement disposé en amont de l’aubage (18) et configuré pour redresser le flux d’air secondaire (F2) en amont dudit aubage (18). Figure pour l’abrégé : Fig 2
FR2006152A 2020-06-12 2020-06-12 Turbomachine comprenant un organe de séparation d’un flux d’air et un organe de redressement du flux d’air séparé. Active FR3111394B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
FR2006152A FR3111394B1 (fr) 2020-06-12 2020-06-12 Turbomachine comprenant un organe de séparation d’un flux d’air et un organe de redressement du flux d’air séparé.
PCT/FR2021/050995 WO2021250339A1 (fr) 2020-06-12 2021-06-02 Turbomachine comprenant un organe de séparation d'un flux d'air et un organe de redressement du flux d'air séparé

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2006152A FR3111394B1 (fr) 2020-06-12 2020-06-12 Turbomachine comprenant un organe de séparation d’un flux d’air et un organe de redressement du flux d’air séparé.
FR2006152 2020-06-12

Publications (2)

Publication Number Publication Date
FR3111394A1 FR3111394A1 (fr) 2021-12-17
FR3111394B1 true FR3111394B1 (fr) 2022-07-22

Family

ID=72266565

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2006152A Active FR3111394B1 (fr) 2020-06-12 2020-06-12 Turbomachine comprenant un organe de séparation d’un flux d’air et un organe de redressement du flux d’air séparé.

Country Status (2)

Country Link
FR (1) FR3111394B1 (fr)
WO (1) WO2021250339A1 (fr)

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2075194B1 (fr) * 2007-12-27 2017-08-16 Techspace Aero Echangeur de chaleur air-huile pour turboréacteur, turboréacteur associé et utilisation dudit échangeur
EP2339123B1 (fr) * 2009-12-23 2013-07-10 Techspace Aero S.A. Paroi intérieure annulaire de la veine secondaire d'un turboréacteur et procédé d'assemblage d'une telle paroi
FR2989734B1 (fr) * 2012-04-24 2014-04-18 Snecma Turboreacteur incorporant des generateurs thermoelectriques
BE1024081B1 (fr) * 2015-03-20 2017-11-13 Safran Aero Boosters S.A. Refroidissement de turbomachine par evaporation
FR3059735B1 (fr) * 2016-12-05 2020-09-25 Safran Aircraft Engines Piece de turbomachine a surface non-axisymetrique

Also Published As

Publication number Publication date
FR3111394A1 (fr) 2021-12-17
WO2021250339A1 (fr) 2021-12-16

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