FR3107924B1 - Movable ring for a turbomachine turbine, comprising an axial bearing end provided with differential cooling grooves - Google Patents

Movable ring for a turbomachine turbine, comprising an axial bearing end provided with differential cooling grooves Download PDF

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Publication number
FR3107924B1
FR3107924B1 FR2002175A FR2002175A FR3107924B1 FR 3107924 B1 FR3107924 B1 FR 3107924B1 FR 2002175 A FR2002175 A FR 2002175A FR 2002175 A FR2002175 A FR 2002175A FR 3107924 B1 FR3107924 B1 FR 3107924B1
Authority
FR
France
Prior art keywords
flange
bearing end
axial bearing
movable ring
end provided
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
FR2002175A
Other languages
French (fr)
Other versions
FR3107924A1 (en
Inventor
Jérôme Claude George Lemonnier
Franck Davy Boisnault
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 FR2002175A priority Critical patent/FR3107924B1/en
Publication of FR3107924A1 publication Critical patent/FR3107924A1/en
Application granted granted Critical
Publication of FR3107924B1 publication Critical patent/FR3107924B1/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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates
    • 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
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/181—Two-dimensional patterned ridged
    • 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
    • F05D2250/20—Three-dimensional
    • F05D2250/29—Three-dimensional machined; miscellaneous
    • F05D2250/294—Three-dimensional machined; miscellaneous grooved

Abstract

L’invention se rapporte à une bride (80) de maintien en position axiale d’un anneau de retenue d’aubes d’une roue mobile de turbine. La bride (80) comprend des rainures (81) circonférentielles configurées pour augmenter le refroidissement d’une extrémité axiale d’appui (84) de cette bride (80) de manière à favoriser le phénomène de mise en tonneau d’un anneau (85) de cette bride (80). De telles rainures (81) permettent de préserver le contact de la bride (80) contre l’anneau de retenue lors du fonctionnement de la turbine et de faciliter le montage à froid de la bride (80). Figure pour l’abrégé : Fig. 3The invention relates to a flange (80) for holding in axial position a retaining ring for the blades of a moving turbine wheel. The flange (80) includes circumferential grooves (81) configured to increase cooling of an axial bearing end (84) of the flange (80) so as to promote barrel rolling of a ring (85 ) of this flange (80). Such grooves (81) help to preserve the contact of the flange (80) against the retaining ring during operation of the turbine and to facilitate the cold mounting of the flange (80). Figure for abstract: Fig. 3

FR2002175A 2020-03-04 2020-03-04 Movable ring for a turbomachine turbine, comprising an axial bearing end provided with differential cooling grooves Active FR3107924B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR2002175A FR3107924B1 (en) 2020-03-04 2020-03-04 Movable ring for a turbomachine turbine, comprising an axial bearing end provided with differential cooling grooves

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2002175 2020-03-04
FR2002175A FR3107924B1 (en) 2020-03-04 2020-03-04 Movable ring for a turbomachine turbine, comprising an axial bearing end provided with differential cooling grooves

Publications (2)

Publication Number Publication Date
FR3107924A1 FR3107924A1 (en) 2021-09-10
FR3107924B1 true FR3107924B1 (en) 2022-12-23

Family

ID=71784149

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2002175A Active FR3107924B1 (en) 2020-03-04 2020-03-04 Movable ring for a turbomachine turbine, comprising an axial bearing end provided with differential cooling grooves

Country Status (1)

Country Link
FR (1) FR3107924B1 (en)

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5984636A (en) * 1997-12-17 1999-11-16 Pratt & Whitney Canada Inc. Cooling arrangement for turbine rotor
JP4675638B2 (en) * 2005-02-08 2011-04-27 本田技研工業株式会社 Secondary air supply device for gas turbine engine
FR2993599B1 (en) * 2012-07-18 2014-07-18 Snecma TURBOMACHINE LABYRINTH DISK
US10072585B2 (en) * 2013-03-14 2018-09-11 United Technologies Corporation Gas turbine engine turbine impeller pressurization
FR3019584B1 (en) 2014-04-07 2019-05-17 Safran Aircraft Engines SYSTEM FOR VENTILATION OF A TURBINE USING CROSSING ORIFICES AND LUNULES

Also Published As

Publication number Publication date
FR3107924A1 (en) 2021-09-10

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