METHOD OF MANUFACTURING TURBINE BLADE AND TURBINE BLADE

To efficiently manufacture a turbine blade.SOLUTION: A method includes a blade split body formation process in which a blade split body constituting a blade body of a turbine blade is formed by a three-dimensional laminate method, a shroud split body formation process in which a plurality of shroud...

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Bibliographische Detailangaben
Hauptverfasser:	ATSUMI HIDEKATSU, MOTOYAMA NOBUHIKO, TANIGAWA HIDETSUGU
Format:	Patent
Sprache:	eng ; jpn
Schlagworte:	ADDITIVE MANUFACTURING TECHNOLOGY ADDITIVE MANUFACTURING, i.e. MANUFACTURING OFTHREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVEAGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING,STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING CLADDING OR PLATING BY SOLDERING OR WELDING COMBUSTION ENGINES 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 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:	To efficiently manufacture a turbine blade.SOLUTION: A method includes a blade split body formation process in which a blade split body constituting a blade body of a turbine blade is formed by a three-dimensional laminate method, a shroud split body formation process in which a plurality of shroud split bodies constituting a shroud of the turbine blade are individually formed for each of the shroud split bodies by a three-dimensional laminate method, and a blade body joining process in which the blade split body and the shroud split bodies are joined.SELECTED DRAWING: Figure 6 【課題】タービン翼を効率的に製造する。【解決手段】タービン翼の翼体を構成する翼体分割体を三次元積層法により形成する翼体分割体形成工程と、タービン翼のシュラウドを構成する複数のシュラウド分割体を三次元積層法によりシュラウド分割体ごとに個別に形成するシュラウド分割体形成工程と、シュラウド分割体同士を接合するシュラウド接合工程と、翼体分割体とシュラウド分割体とを接合する翼体接合工程とを含む。【選択図】図６