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1. WO2020193912 - TURBINE ENGINE VANE EQUIPPED WITH A COOLING CIRCUIT AND LOST-WAX METHOD FOR MANUFACTURING SUCH A VANE

Publication Number WO/2020/193912
Publication Date 01.10.2020
International Application No. PCT/FR2020/050564
International Filing Date 16.03.2020
IPC
F01D 5/18 2006.01
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
DNON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
5Blades; Blade-carrying members; Heating, heat-insulating, cooling, or antivibration means on the blades or the members
12Blades
14Form or construction
18Hollow blades; Heating, heat-insulating, or cooling means on blades
CPC
F01D 5/187
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
5Blades; Blade-carrying members
12Blades
14Form or construction
18Hollow blades, ; i.e. blades with cooling or heating channels or cavities
187Convection cooling
F05D 2260/941
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
2260Function
94Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
941particularly aimed at mechanical or thermal stress reduction
Applicants
  • SAFRAN [FR]/[FR]
  • SAFRAN AIRCRAFT ENGINES [FR]/[FR]
Inventors
  • CARIOU, Romain, Pierre
  • PELLETERAT DE BORDE, Myriam
  • SIMON, Vianney
  • ROLLINGER, Adrien, Bernard, Vincent
Agents
  • BARBE, Laurent
  • DELAHAYE, Jean-Baptiste
  • ALEXANDRINE, Nathalie
Priority Data
190301922.03.2019FR
Publication Language French (FR)
Filing Language French (FR)
Designated States
Title
(EN) TURBINE ENGINE VANE EQUIPPED WITH A COOLING CIRCUIT AND LOST-WAX METHOD FOR MANUFACTURING SUCH A VANE
(FR) AUBE DE TURBOMACHINE EQUIPEE D'UN CIRCUIT DE REFROIDISSEMENT ET PROCEDE DE FABRICATION A CIRE PERDUE D'UNE TELLE AUBE
Abstract
(EN)
The invention relates to a turbine engine vane (20) comprising a blade (21) extending along a radial axis and a first cooling circuit (28) arranged inside the blade, the first cooling circuit (28) comprising a first cavity (34) and a second cavity (35) disposed downstream of the first cavity in a direction of circulation of a coolant in the blade, the first and second cavities radially extending inside the blade and being at least partly separated by a first radial partition (36) having a radially internal free end (37), which at least partly demarcates a first coolant passage (40) connecting the first and second cavities. According to the invention, the radially internal free end (37) is enlarged by having a general transverse section substantially in the form of a keyhole.
(FR)
L'invention concerne une aube (20) de turbomachine comprenant une pale (21) s'étendant suivant un axe radial et un premier circuit de refroidissement (28) agencé à l'intérieur de la pale, le premier circuit de refroidissement (28) comportant une première cavité (34) et une deuxième cavité (35) disposée en aval de la première cavité suivant un sens de circulation d'un fluide de refroidissement dans la pale, les première et deuxième cavités s'étendant radialement à l'intérieur de la pale et étant séparées au moins en partie par une première cloison radiale (36) ayant une extrémité libre radialement interne (37) qui délimite au moins en partie un premier passage (40) de fluide de refroidissement reliant les première et deuxième cavités. Selon l'invention, l'extrémité libre radialement interne (37) est élargie en ayant une section transversale générale sensiblement en forme de trou de serrure.
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