FREQUENCY TAILORED THICKNESS BLADE FOR A TURBOMACHINE WHEEL

A method is provided for determining a blade topology that reduces the effects of vibratory stress on a turbomachine blade having a plurality of discrete locations, wherein each discrete location has a thickness. The method includes the steps of creating a computational model of the blade, using the...

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Bibliographische Detailangaben
Hauptverfasser:	GENTILE DAVID P, KINCHELOE TODD A
Format:	Patent
Sprache:	eng
Schlagworte:	AEROPLANES AIRCRAFT AVIATION BLASTING CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TOTRANSPORTATION COSMONAUTICS ENGINE PLANTS IN GENERAL GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS HEATING HELICOPTERS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES PERFORMING OPERATIONS STEAM ENGINES TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINSTCLIMATE CHANGE TRANSPORTING WEAPONS
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Beschreibung
Zusammenfassung:	A method is provided for determining a blade topology that reduces the effects of vibratory stress on a turbomachine blade having a plurality of discrete locations, wherein each discrete location has a thickness. The method includes the steps of creating a computational model of the blade, using the computational model to modify the thickness of at least one of the discrete locations a predetermined amount, determining a combination of a discrete location and predetermined thickness amount that reduces vibratory stress on the blade, and applying the determined combination to the computational model to create a revised blade. A turbomachine including a blade having the determined blade topology is also provided.