COOLING-AIR INJECTION CASING FOR A TURBOMACHINE TURBINE

The present invention relates to a cooling-air injection casing (2) for cooling a bladed rotor disc of a turbine, in particular a high-pressure turbine, of a turbomachine, this casing extending around a longitudinal axis (X-X′) and being traversed by at least one channel (20) forming an air injector...

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Bibliographische Detailangaben
Hauptverfasser:	BOISNAULT, Franck Davy, LEMONNIER, Jérôme Claude George, VAN NOORT, Antoine Bruno
Format:	Patent
Sprache:	eng
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	The present invention relates to a cooling-air injection casing (2) for cooling a bladed rotor disc of a turbine, in particular a high-pressure turbine, of a turbomachine, this casing extending around a longitudinal axis (X-X′) and being traversed by at least one channel (20) forming an air injector, the channel (20) comprising an inlet mouth (201) and an outlet mouth (202). This casing is noteworthy in that the channel (20) comprises a primary section (203) which extends in an axial plane (P) from the inlet mouth (201) to an elbow (206), and a secondary section (207) which extends from this elbow (206) to the outlet mouth (202), the secondary section (207) having a progressive variation of its orientation with a tangential component between the elbow (206) and the outlet mouth (202), in that the channel (20) has a reduction in cross section between the inlet mouth (201) and a neck (204), and in that the channel (20) has at least one corrugation (205) in its primary section (203), such that the outlet mouth (202) is situated closer to the longitudinal axis (X-X′) than the inlet mouth (201).