FR3111393B1 - Turbomachine comprenant un organe de séparation d’un flux d’air amovible - Google Patents

Turbomachine comprenant un organe de séparation d’un flux d’air amovible Download PDF

Info

Publication number
FR3111393B1
FR3111393B1 FR2006143A FR2006143A FR3111393B1 FR 3111393 B1 FR3111393 B1 FR 3111393B1 FR 2006143 A FR2006143 A FR 2006143A FR 2006143 A FR2006143 A FR 2006143A FR 3111393 B1 FR3111393 B1 FR 3111393B1
Authority
FR
France
Prior art keywords
air flow
separation member
turbomachine
internal
vein
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
FR2006143A
Other languages
English (en)
Other versions
FR3111393A1 (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 FR2006143A priority Critical patent/FR3111393B1/fr
Publication of FR3111393A1 publication Critical patent/FR3111393A1/fr
Application granted granted Critical
Publication of FR3111393B1 publication Critical patent/FR3111393B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • 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
    • F01D5/005—Repairing methods or devices
    • 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
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/72—Maintenance
    • 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
    • F05D2230/80—Repairing, retrofitting or upgrading methods
    • 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
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/36—Retaining components in desired mutual position by a form fit connection, e.g. by interlocking
    • 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
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/37—Retaining components in desired mutual position by a press fit connection
    • 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
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/38—Retaining components in desired mutual position by a spring, i.e. spring loaded or biased towards a certain position

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

Turbomachine (10) d’axe longitudinal (X-X’) comprenant une veine interne (VI), une veine externe (VE) et un organe de séparation (20) configuré pour séparer un flux d’air principal (F) en un flux d’air primaire (F1) circulant dans la veine interne (VI) et un flux d’air secondaire (F2) circulant dans la veine externe (VE), la veine externe (VE) comprenant au moins un aubage (18) comprenant une plateforme interne (18a) et une pluralité d’aubes directrices de sortie (18c) s’étendant radialement en saillie de ladite plateforme interne (18a) et configurées pour redresser le flux secondaire (F2) en un flux secondaire redressé. L’organe de séparation (20) est distinct de l’aubage (18) et fixé de manière amovible par crochetage sur une extrémité amont (18d) de la plateforme interne (18a) dudit aubage (18). Figure pour l’abrégé : Fig 2
FR2006143A 2020-06-12 2020-06-12 Turbomachine comprenant un organe de séparation d’un flux d’air amovible Active FR3111393B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR2006143A FR3111393B1 (fr) 2020-06-12 2020-06-12 Turbomachine comprenant un organe de séparation d’un flux d’air amovible

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2006143 2020-06-12
FR2006143A FR3111393B1 (fr) 2020-06-12 2020-06-12 Turbomachine comprenant un organe de séparation d’un flux d’air amovible

Publications (2)

Publication Number Publication Date
FR3111393A1 FR3111393A1 (fr) 2021-12-17
FR3111393B1 true FR3111393B1 (fr) 2022-07-22

Family

ID=72266564

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2006143A Active FR3111393B1 (fr) 2020-06-12 2020-06-12 Turbomachine comprenant un organe de séparation d’un flux d’air amovible

Country Status (1)

Country Link
FR (1) FR3111393B1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11692481B1 (en) * 2022-04-29 2023-07-04 Pratt & Whitney Canada Corp. Inertial particle separator duct assembly with splitter

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE1022482B1 (fr) * 2014-10-21 2016-05-02 Techspace Aero S.A. Bec de separation a degivrage plasma pour compresseur de turbomachine axiale
US10156243B2 (en) * 2015-05-04 2018-12-18 Safran Aero Boosters Sa Composite splitter lip for axial turbomachine compressor
FR3047042B1 (fr) * 2016-01-22 2018-02-16 Safran Aircraft Engines Dispositif de degivrage d'un bec de separation et d'aubes directrices d'entree d'une turbomachine aeronautique
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

Also Published As

Publication number Publication date
FR3111393A1 (fr) 2021-12-17

Similar Documents

Publication Publication Date Title
US10436038B2 (en) Turbine engine with an airfoil having a tip shelf outlet
US10415392B2 (en) End wall configuration for gas turbine engine
US9103217B2 (en) Turbine blade tip with tip shelf diffuser holes
RU2012158292A (ru) Устройство охлаждения платформы рабочей лопатки турбины и способ создания этого устройства охлаждения
FR3111393B1 (fr) Turbomachine comprenant un organe de séparation d’un flux d’air amovible
US10267214B2 (en) Compressor inlet recirculation system for a turbocharger
CA2935758A1 (fr) Jambe de force et buse integrees a cordons axiaux de buse inegaux
US10669854B2 (en) Impeller
KR20170135754A (ko) 배기 디퓨저
FR3100268B1 (fr) Turbomachine a double flux pour un aeronef
CA3082693A1 (fr) Conduit diffuseur avec sortie a orientation axiale
US11143201B2 (en) Impeller tip cavity
US20180051572A1 (en) Airfoil for a turbine engine
EP3098383A1 (fr) Aubage compresseur présentant un profil de bord d'attaque composé
EP3418496A3 (fr) Pale de rotor de turbomachine
US20200240276A1 (en) Turbine blade and corresponding method of servicing
FR3111394B1 (fr) Turbomachine comprenant un organe de séparation d’un flux d’air et un organe de redressement du flux d’air séparé.
US10844735B2 (en) Turbomachine guide vanes with improved vane profile
KR101901682B1 (ko) 제이 타입 캔틸레버드 베인 및 이를 포함하는 가스터빈
US2261463A (en) Impeller
FR3085993B1 (fr) Aube mobile pour une roue d'une turbomachine
US11286951B2 (en) Diffuser pipe with exit scallops
US11136993B2 (en) Diffuser pipe with asymmetry
FR3116592B1 (fr) Vrille pour dispositif d’injection étagé de turbomachine
CN110121588B (zh) 包括由排放翅片形成的排放流引导通道的中间壳体毂部

Legal Events

Date Code Title Description
PLFP Fee payment

Year of fee payment: 2

PLSC Publication of the preliminary search report

Effective date: 20211217

PLFP Fee payment

Year of fee payment: 3

PLFP Fee payment

Year of fee payment: 4