TURBOMACHINE COMPONENT, PARTICULARLY A GAS TURBINE ENGINE COMPONENT, WITH A COOLED WALL AND A METHOD OF MANUFACTURING

The invention is directed to a turbomachine component (10), particularly a gas turbine engine component, comprising at least one part (2) built in parts from a curved or planar panel (11), particularly a sheet metal, the part (2) comprising a plurality of cooling channels (3) via which a cooling flu...

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Bibliographische Detailangaben
Hauptverfasser:	LORSTAD, DANIEL, OFVERSTEDT, TOMAS
Format:	Patent
Sprache:	eng ; fre
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING CLADDING OR PLATING BY SOLDERING OR WELDING COMBUSTION APPARATUS COMBUSTION ENGINES COMBUSTION PROCESSES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MACHINE TOOLS MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING METAL-WORKING NOT OTHERWISE PROVIDED FOR NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES PERFORMING OPERATIONS SOLDERING OR UNSOLDERING STEAM ENGINES TRANSPORTING WEAPONS WELDING WORKING BY LASER BEAM
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Beschreibung
Zusammenfassung:	The invention is directed to a turbomachine component (10), particularly a gas turbine engine component, comprising at least one part (2) built in parts from a curved or planar panel (11), particularly a sheet metal, the part (2) comprising a plurality of cooling channels (3) via which a cooling fluid (5), particularly air, is guidable, wherein at least one of the plurality of cooling channels (3) has a continuously tapered section (8). The at least one of the plurality of cooling channels (3) has a single inlet port (1) from a first surface (15) of the panel (11) and a single outlet port (7) for the cooling fluid (5) to another surface (16), particularly a surface opposite to the first surface (15), or to the first surface (15). Further the panel (11) is built via laser sintering or laser melting or direct laser deposition. The invention furthermore is directed to a gas turbine engine equipped with such a component and a method of manufacturing.