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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| creator | GENTILE DAVID P KINCHELOE TODD A |
| description | 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. |
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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.</description><language>eng</language><subject>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</subject><creationdate>2008</creationdate><oa>free_for_read</oa><woscitedreferencessubscribed>false</woscitedreferencessubscribed></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><linktohtml>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20080117&DB=EPODOC&CC=US&NR=2008014091A1$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,780,885,25564,76547</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20080117&DB=EPODOC&CC=US&NR=2008014091A1$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>GENTILE DAVID P</creatorcontrib><creatorcontrib>KINCHELOE TODD A</creatorcontrib><title>FREQUENCY TAILORED THICKNESS BLADE FOR A TURBOMACHINE WHEEL</title><description>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.</description><subject>AEROPLANES</subject><subject>AIRCRAFT</subject><subject>AVIATION</subject><subject>BLASTING</subject><subject>CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TOTRANSPORTATION</subject><subject>COSMONAUTICS</subject><subject>ENGINE PLANTS IN GENERAL</subject><subject>GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC</subject><subject>GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS</subject><subject>HEATING</subject><subject>HELICOPTERS</subject><subject>LIGHTING</subject><subject>MACHINES OR ENGINES IN GENERAL</subject><subject>MECHANICAL ENGINEERING</subject><subject>NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES</subject><subject>PERFORMING OPERATIONS</subject><subject>STEAM ENGINES</subject><subject>TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS</subject><subject>TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINSTCLIMATE CHANGE</subject><subject>TRANSPORTING</subject><subject>WEAPONS</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2008</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZLB2C3INDHX1c45UCHH09PEPcnVRCPHwdPb2cw0OVnDycXRxVXDzD1JwVAgJDXLy93V09vD0c1UI93B19eFhYE1LzClO5YXS3AzKbq4hzh66qQX58anFBYnJqXmpJfGhwUYGBhYGhiYGloaOhsbEqQIAeYQqEA</recordid><startdate>20080117</startdate><enddate>20080117</enddate><creator>GENTILE DAVID P</creator><creator>KINCHELOE TODD A</creator><scope>EVB</scope></search><sort><creationdate>20080117</creationdate><title>FREQUENCY TAILORED THICKNESS BLADE FOR A TURBOMACHINE WHEEL</title><author>GENTILE DAVID P ; KINCHELOE TODD A</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_US2008014091A13</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng</language><creationdate>2008</creationdate><topic>AEROPLANES</topic><topic>AIRCRAFT</topic><topic>AVIATION</topic><topic>BLASTING</topic><topic>CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TOTRANSPORTATION</topic><topic>COSMONAUTICS</topic><topic>ENGINE PLANTS IN GENERAL</topic><topic>GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC</topic><topic>GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS</topic><topic>HEATING</topic><topic>HELICOPTERS</topic><topic>LIGHTING</topic><topic>MACHINES OR ENGINES IN GENERAL</topic><topic>MECHANICAL ENGINEERING</topic><topic>NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES</topic><topic>PERFORMING OPERATIONS</topic><topic>STEAM ENGINES</topic><topic>TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS</topic><topic>TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINSTCLIMATE CHANGE</topic><topic>TRANSPORTING</topic><topic>WEAPONS</topic><toplevel>online_resources</toplevel><creatorcontrib>GENTILE DAVID P</creatorcontrib><creatorcontrib>KINCHELOE TODD A</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>GENTILE DAVID P</au><au>KINCHELOE TODD A</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>FREQUENCY TAILORED THICKNESS BLADE FOR A TURBOMACHINE WHEEL</title><date>2008-01-17</date><risdate>2008</risdate><abstract>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.</abstract><oa>free_for_read</oa></addata></record> |
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| subjects | 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 |
| title | FREQUENCY TAILORED THICKNESS BLADE FOR A TURBOMACHINE WHEEL |
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