FR3051825B1 - TURBOMACHINE RECTIFIER, AND METHOD FOR CHANGING THE BLADE SETTING - Google Patents

TURBOMACHINE RECTIFIER, AND METHOD FOR CHANGING THE BLADE SETTING Download PDF

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Publication number
FR3051825B1
FR3051825B1 FR1654771A FR1654771A FR3051825B1 FR 3051825 B1 FR3051825 B1 FR 3051825B1 FR 1654771 A FR1654771 A FR 1654771A FR 1654771 A FR1654771 A FR 1654771A FR 3051825 B1 FR3051825 B1 FR 3051825B1
Authority
FR
France
Prior art keywords
blade
notch
tail
changing
blade setting
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
FR1654771A
Other languages
French (fr)
Other versions
FR3051825A1 (en
Inventor
Yves Heinry Pierre
Aline Bourdais
Eric Dousseaud Sylvain
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.)
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Publication date
Application filed by Safran Aircraft Engines SAS, SNECMA SAS filed Critical Safran Aircraft Engines SAS
Priority to FR1654771A priority Critical patent/FR3051825B1/en
Publication of FR3051825A1 publication Critical patent/FR3051825A1/en
Application granted granted Critical
Publication of FR3051825B1 publication Critical patent/FR3051825B1/en
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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
    • F01D9/042—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
    • 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

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

Une cale (22) destinée à bloquer le pivotement d'une queue (4) d'une aube dépendant d'une virole de support (2) comporte une entaille (26) dans laquelle la queue de l'aube est engagée, et deux flancs encadrant cette entaille, dont l'un (27) est en appui entre un épaulement (31) de la virole (2) et un méplat (6) de la queue (4) de l'aube, alors que l'autre flanc (28) est libre, environné de jeux (35, 36). Cette disposition permet un montage isostatique qui se prête au libre choix de l'angle de calage de l'aube d'après la direction de l'entaille (26). Le montage et le démontage sont facilités par l'isostaticité de cet assemblage.A wedge (22) intended to block the pivoting of a tail (4) of a blade dependent on a support ring (2) comprises a notch (26) in which the tail of the blade is engaged, and two flanks framing this notch, one of which (27) is supported between a shoulder (31) of the ferrule (2) and a flat (6) of the tail (4) of the blade, while the other flank (28) is free, surrounded by games (35, 36). This arrangement allows isostatic mounting which lends itself to the free choice of the setting angle of the blade according to the direction of the notch (26). The assembly and disassembly are facilitated by the isostaticity of this assembly.

FR1654771A 2016-05-27 2016-05-27 TURBOMACHINE RECTIFIER, AND METHOD FOR CHANGING THE BLADE SETTING Active FR3051825B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1654771A FR3051825B1 (en) 2016-05-27 2016-05-27 TURBOMACHINE RECTIFIER, AND METHOD FOR CHANGING THE BLADE SETTING

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1654771A FR3051825B1 (en) 2016-05-27 2016-05-27 TURBOMACHINE RECTIFIER, AND METHOD FOR CHANGING THE BLADE SETTING
FR1654771 2016-05-27

Publications (2)

Publication Number Publication Date
FR3051825A1 FR3051825A1 (en) 2017-12-01
FR3051825B1 true FR3051825B1 (en) 2020-02-28

Family

ID=57396514

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1654771A Active FR3051825B1 (en) 2016-05-27 2016-05-27 TURBOMACHINE RECTIFIER, AND METHOD FOR CHANGING THE BLADE SETTING

Country Status (1)

Country Link
FR (1) FR3051825B1 (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3127533A1 (en) * 2021-09-28 2023-03-31 Safran Aircraft Engines Wedging system for articulated turbomachine blade, turbomachine blade equipped with this wedging system and method of mounting such wedging system on an articulated blade

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1720754A (en) * 1926-09-09 1929-07-16 Westinghouse Electric & Mfg Co Turbine-blade shrouding
FR1542561A (en) * 1967-07-07 Snecma Turbomachinery blade attachment device
FR2995934B1 (en) * 2012-09-24 2018-06-01 Safran Aircraft Engines AUBE FOR TURBOMACHINE RECTIFIER

Also Published As

Publication number Publication date
FR3051825A1 (en) 2017-12-01

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