BLADE FOR A TURBOMACHINE, BLADE ASSEMBLY, AND TURBINE
A blade for turbo machine, in particular for a turbine, includes an airfoil body extending in a radial direction and comprising a suction side surface and a pressure side surface opposite to the suction side surface with regard to a circumferential direction that extends transverse to the radial dir...
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| creator | BEAUMONT, Wade HOFFMANN, Willy H KRUECKELS, Joerg TSYPKAYKIN, Igor MARTIN, Stefan Emanuel |
| description | A blade for turbo machine, in particular for a turbine, includes an airfoil body extending in a radial direction and comprising a suction side surface and a pressure side surface opposite to the suction side surface with regard to a circumferential direction that extends transverse to the radial direction, and a snubber structure. The snubber structure includes a first snubber element protruding, along the circumferential direction, from the suction side surface of the airfoil body, and a second snubber element protruding, along the circumferential direction, from the pressure side surface of the airfoil body wherein the first snubber element is connected to the suction side surface of the airfoil body by a concave curved first transition portion having a first radius, and wherein the second snubber element is connected to the pressure side surface of the airfoil body by a concave curved second transition portion having a second radius. The first radius is smaller than the second radius to reduce aerodynamic losses. |
| format | Patent |
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The snubber structure includes a first snubber element protruding, along the circumferential direction, from the suction side surface of the airfoil body, and a second snubber element protruding, along the circumferential direction, from the pressure side surface of the airfoil body wherein the first snubber element is connected to the suction side surface of the airfoil body by a concave curved first transition portion having a first radius, and wherein the second snubber element is connected to the pressure side surface of the airfoil body by a concave curved second transition portion having a second radius. The first radius is smaller than the second radius to reduce aerodynamic losses.</description><language>eng ; fre ; ger</language><subject>BLASTING ; ENGINE PLANTS IN GENERAL ; HEATING ; LIGHTING ; MACHINES OR ENGINES IN GENERAL ; MECHANICAL ENGINEERING ; NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES ; STEAM ENGINES ; WEAPONS</subject><creationdate>2023</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=20230104&DB=EPODOC&CC=EP&NR=4112884A1$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,776,881,25542,76516</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20230104&DB=EPODOC&CC=EP&NR=4112884A1$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>BEAUMONT, Wade</creatorcontrib><creatorcontrib>HOFFMANN, Willy H</creatorcontrib><creatorcontrib>KRUECKELS, Joerg</creatorcontrib><creatorcontrib>TSYPKAYKIN, Igor</creatorcontrib><creatorcontrib>MARTIN, Stefan Emanuel</creatorcontrib><title>BLADE FOR A TURBOMACHINE, BLADE ASSEMBLY, AND TURBINE</title><description>A blade for turbo machine, in particular for a turbine, includes an airfoil body extending in a radial direction and comprising a suction side surface and a pressure side surface opposite to the suction side surface with regard to a circumferential direction that extends transverse to the radial direction, and a snubber structure. The snubber structure includes a first snubber element protruding, along the circumferential direction, from the suction side surface of the airfoil body, and a second snubber element protruding, along the circumferential direction, from the pressure side surface of the airfoil body wherein the first snubber element is connected to the suction side surface of the airfoil body by a concave curved first transition portion having a first radius, and wherein the second snubber element is connected to the pressure side surface of the airfoil body by a concave curved second transition portion having a second radius. The first radius is smaller than the second radius to reduce aerodynamic losses.</description><subject>BLASTING</subject><subject>ENGINE PLANTS IN GENERAL</subject><subject>HEATING</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>STEAM ENGINES</subject><subject>WEAPONS</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2023</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZDB18nF0cVVw8w9ScFQICQ1y8vd1dPbw9HPVUYDIOAYHu_o6-UTqKDj6uYBVACV5GFjTEnOKU3mhNDeDgptriLOHbmpBfnxqcUFicmpeakm8a4CJoaGRhYWJo6ExEUoAUyEmmQ</recordid><startdate>20230104</startdate><enddate>20230104</enddate><creator>BEAUMONT, Wade</creator><creator>HOFFMANN, Willy H</creator><creator>KRUECKELS, Joerg</creator><creator>TSYPKAYKIN, Igor</creator><creator>MARTIN, Stefan Emanuel</creator><scope>EVB</scope></search><sort><creationdate>20230104</creationdate><title>BLADE FOR A TURBOMACHINE, BLADE ASSEMBLY, AND TURBINE</title><author>BEAUMONT, Wade ; HOFFMANN, Willy H ; KRUECKELS, Joerg ; TSYPKAYKIN, Igor ; MARTIN, Stefan Emanuel</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_EP4112884A13</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng ; fre ; ger</language><creationdate>2023</creationdate><topic>BLASTING</topic><topic>ENGINE PLANTS IN GENERAL</topic><topic>HEATING</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>STEAM ENGINES</topic><topic>WEAPONS</topic><toplevel>online_resources</toplevel><creatorcontrib>BEAUMONT, Wade</creatorcontrib><creatorcontrib>HOFFMANN, Willy H</creatorcontrib><creatorcontrib>KRUECKELS, Joerg</creatorcontrib><creatorcontrib>TSYPKAYKIN, Igor</creatorcontrib><creatorcontrib>MARTIN, Stefan Emanuel</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>BEAUMONT, Wade</au><au>HOFFMANN, Willy H</au><au>KRUECKELS, Joerg</au><au>TSYPKAYKIN, Igor</au><au>MARTIN, Stefan Emanuel</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>BLADE FOR A TURBOMACHINE, BLADE ASSEMBLY, AND TURBINE</title><date>2023-01-04</date><risdate>2023</risdate><abstract>A blade for turbo machine, in particular for a turbine, includes an airfoil body extending in a radial direction and comprising a suction side surface and a pressure side surface opposite to the suction side surface with regard to a circumferential direction that extends transverse to the radial direction, and a snubber structure. The snubber structure includes a first snubber element protruding, along the circumferential direction, from the suction side surface of the airfoil body, and a second snubber element protruding, along the circumferential direction, from the pressure side surface of the airfoil body wherein the first snubber element is connected to the suction side surface of the airfoil body by a concave curved first transition portion having a first radius, and wherein the second snubber element is connected to the pressure side surface of the airfoil body by a concave curved second transition portion having a second radius. The first radius is smaller than the second radius to reduce aerodynamic losses.</abstract><oa>free_for_read</oa></addata></record> |
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| language | eng ; fre ; ger |
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| source | esp@cenet |
| subjects | BLASTING ENGINE PLANTS IN GENERAL HEATING LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS |
| title | BLADE FOR A TURBOMACHINE, BLADE ASSEMBLY, AND TURBINE |
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