FR3049000B1 - TURBINE DISPENSER COMPRISING A MONOBLOC INTERNAL CROWN - Google Patents

TURBINE DISPENSER COMPRISING A MONOBLOC INTERNAL CROWN Download PDF

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Publication number
FR3049000B1
FR3049000B1 FR1652340A FR1652340A FR3049000B1 FR 3049000 B1 FR3049000 B1 FR 3049000B1 FR 1652340 A FR1652340 A FR 1652340A FR 1652340 A FR1652340 A FR 1652340A FR 3049000 B1 FR3049000 B1 FR 3049000B1
Authority
FR
France
Prior art keywords
monobloc
ring
turbine
turbomachine
internal crown
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
FR1652340A
Other languages
French (fr)
Other versions
FR3049000A1 (en
Inventor
Jeremy Phorla Lao
Olivier BELMONTE
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
SNECMA 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, SNECMA SAS filed Critical Safran Aircraft Engines SAS
Priority to FR1652340A priority Critical patent/FR3049000B1/en
Publication of FR3049000A1 publication Critical patent/FR3049000A1/en
Application granted granted Critical
Publication of FR3049000B1 publication Critical patent/FR3049000B1/en
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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements

Landscapes

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

Abstract

L'invention concerne un distributeur d'une turbine et un redresseur d'un compresseur pour une turbomachine (1) comprenant une pluralité d'aubages (12) disposés radialement par rapport à un axe (X) de rotation de la turbomachine (1) reliant une couronne annulaire radialement interne (14) et une couronne annulaire radialement externe (16). La couronne externe (16) est sectorisée et comprend au moins deux secteurs d'anneau (17) s'étendant coaxialement avec l'axe (X) de rotation de la turbomachine (1) et la couronne interne (14) est monobloc.The invention relates to a distributor of a turbine and a rectifier of a compressor for a turbomachine (1) comprising a plurality of blades (12) arranged radially with respect to an axis (X) of rotation of the turbomachine (1). connecting a radially inner annular ring (14) and a radially outer annular ring (16). The outer ring (16) is sectorized and comprises at least two ring sectors (17) extending coaxially with the axis (X) of rotation of the turbomachine (1) and the inner ring (14) is monobloc.

FR1652340A 2016-03-18 2016-03-18 TURBINE DISPENSER COMPRISING A MONOBLOC INTERNAL CROWN Active FR3049000B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1652340A FR3049000B1 (en) 2016-03-18 2016-03-18 TURBINE DISPENSER COMPRISING A MONOBLOC INTERNAL CROWN

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1652340 2016-03-18
FR1652340A FR3049000B1 (en) 2016-03-18 2016-03-18 TURBINE DISPENSER COMPRISING A MONOBLOC INTERNAL CROWN

Publications (2)

Publication Number Publication Date
FR3049000A1 FR3049000A1 (en) 2017-09-22
FR3049000B1 true FR3049000B1 (en) 2019-05-10

Family

ID=55863079

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1652340A Active FR3049000B1 (en) 2016-03-18 2016-03-18 TURBINE DISPENSER COMPRISING A MONOBLOC INTERNAL CROWN

Country Status (1)

Country Link
FR (1) FR3049000B1 (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3139858A1 (en) * 2022-09-15 2024-03-22 Safran Aircraft Engines DISTRIBUTOR FOR A TURBINE OF AN AIRCRAFT TURBOMACHINE

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5248240A (en) * 1993-02-08 1993-09-28 General Electric Company Turbine stator vane assembly
EP1510654A1 (en) * 2003-08-25 2005-03-02 Siemens Aktiengesellschaft Unitary turbine blade array and method to produce the unitary turbine blade array.
FR2902843A1 (en) * 2006-06-23 2007-12-28 Snecma Sa COMPRESSOR RECTIFIER AREA OR TURBOMACHINE DISTRIBUTOR SECTOR
FR2984427B1 (en) * 2011-12-15 2018-04-27 Safran Aircraft Engines RECTIFIER AREA FOR A TURBOMACHINE COMPRESSOR MADE BY BRATING A PLATFORM OF ITS AUBES ON A VIROLE.

Also Published As

Publication number Publication date
FR3049000A1 (en) 2017-09-22

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