Rotor blade with air flow passages
A rotor blade 2 for a turbo machine, such as a gas turbine engine, comprising an aerofoil 6 having pressure and suction surfaces 8,10, leading and trailing edges 12, 14, and an array of passages 20 at a tip region 18 of the aerofoil, where the passages extend from the pressure surface to the suction...
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| creator | STEPHANE MICHEL MARCEL BARALON NEIL WILLIAM HARVEY |
| description | A rotor blade 2 for a turbo machine, such as a gas turbine engine, comprising an aerofoil 6 having pressure and suction surfaces 8,10, leading and trailing edges 12, 14, and an array of passages 20 at a tip region 18 of the aerofoil, where the passages extend from the pressure surface to the suction surface and are disposed so that the array creates a jet of gas issuing from the suction surface that is inclined outwardly from the suction surface and towards the tip in the direction from the leading edge to the trailing edge. Preferably the passage outlets are situated a distance of between 1% and 25% of the span of the aerofoil from the tip and not more than a distance of 25% of the chord of the aerofoil from the leading edge. A rotor assembly is also claimed. |
| format | Patent |
| fullrecord | <record><control><sourceid>epo_EVB</sourceid><recordid>TN_cdi_epo_espacenet_GB2481822A</recordid><sourceformat>XML</sourceformat><sourcesystem>PC</sourcesystem><sourcerecordid>GB2481822A</sourcerecordid><originalsourceid>FETCH-epo_espacenet_GB2481822A3</originalsourceid><addsrcrecordid>eNrjZFAKyi_JL1JIyklMSVUozyzJUEjMLFJIy8kvVyhILC5OTE8t5mFgTUvMKU7lhdLcDPJuriHOHrqpBfnxqcUFicmpeakl8e5ORiYWhhZGRo7GhFUAAADWJOA</addsrcrecordid><sourcetype>Open Access Repository</sourcetype><iscdi>true</iscdi><recordtype>patent</recordtype></control><display><type>patent</type><title>Rotor blade with air flow passages</title><source>esp@cenet</source><creator>STEPHANE MICHEL MARCEL BARALON ; NEIL WILLIAM HARVEY</creator><creatorcontrib>STEPHANE MICHEL MARCEL BARALON ; NEIL WILLIAM HARVEY</creatorcontrib><description>A rotor blade 2 for a turbo machine, such as a gas turbine engine, comprising an aerofoil 6 having pressure and suction surfaces 8,10, leading and trailing edges 12, 14, and an array of passages 20 at a tip region 18 of the aerofoil, where the passages extend from the pressure surface to the suction surface and are disposed so that the array creates a jet of gas issuing from the suction surface that is inclined outwardly from the suction surface and towards the tip in the direction from the leading edge to the trailing edge. Preferably the passage outlets are situated a distance of between 1% and 25% of the span of the aerofoil from the tip and not more than a distance of 25% of the chord of the aerofoil from the leading edge. A rotor assembly is also claimed.</description><language>eng</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 ; NON-POSITIVE DISPLACEMENT PUMPS ; POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS ; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS ; STEAM ENGINES ; WEAPONS</subject><creationdate>2012</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=20120111&DB=EPODOC&CC=GB&NR=2481822A$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,776,881,25542,76516</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20120111&DB=EPODOC&CC=GB&NR=2481822A$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>STEPHANE MICHEL MARCEL BARALON</creatorcontrib><creatorcontrib>NEIL WILLIAM HARVEY</creatorcontrib><title>Rotor blade with air flow passages</title><description>A rotor blade 2 for a turbo machine, such as a gas turbine engine, comprising an aerofoil 6 having pressure and suction surfaces 8,10, leading and trailing edges 12, 14, and an array of passages 20 at a tip region 18 of the aerofoil, where the passages extend from the pressure surface to the suction surface and are disposed so that the array creates a jet of gas issuing from the suction surface that is inclined outwardly from the suction surface and towards the tip in the direction from the leading edge to the trailing edge. Preferably the passage outlets are situated a distance of between 1% and 25% of the span of the aerofoil from the tip and not more than a distance of 25% of the chord of the aerofoil from the leading edge. A rotor assembly is also claimed.</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>NON-POSITIVE DISPLACEMENT PUMPS</subject><subject>POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS</subject><subject>PUMPS FOR LIQUIDS OR ELASTIC FLUIDS</subject><subject>STEAM ENGINES</subject><subject>WEAPONS</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2012</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZFAKyi_JL1JIyklMSVUozyzJUEjMLFJIy8kvVyhILC5OTE8t5mFgTUvMKU7lhdLcDPJuriHOHrqpBfnxqcUFicmpeakl8e5ORiYWhhZGRo7GhFUAAADWJOA</recordid><startdate>20120111</startdate><enddate>20120111</enddate><creator>STEPHANE MICHEL MARCEL BARALON</creator><creator>NEIL WILLIAM HARVEY</creator><scope>EVB</scope></search><sort><creationdate>20120111</creationdate><title>Rotor blade with air flow passages</title><author>STEPHANE MICHEL MARCEL BARALON ; NEIL WILLIAM HARVEY</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_GB2481822A3</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng</language><creationdate>2012</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>NON-POSITIVE DISPLACEMENT PUMPS</topic><topic>POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS</topic><topic>PUMPS FOR LIQUIDS OR ELASTIC FLUIDS</topic><topic>STEAM ENGINES</topic><topic>WEAPONS</topic><toplevel>online_resources</toplevel><creatorcontrib>STEPHANE MICHEL MARCEL BARALON</creatorcontrib><creatorcontrib>NEIL WILLIAM HARVEY</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>STEPHANE MICHEL MARCEL BARALON</au><au>NEIL WILLIAM HARVEY</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>Rotor blade with air flow passages</title><date>2012-01-11</date><risdate>2012</risdate><abstract>A rotor blade 2 for a turbo machine, such as a gas turbine engine, comprising an aerofoil 6 having pressure and suction surfaces 8,10, leading and trailing edges 12, 14, and an array of passages 20 at a tip region 18 of the aerofoil, where the passages extend from the pressure surface to the suction surface and are disposed so that the array creates a jet of gas issuing from the suction surface that is inclined outwardly from the suction surface and towards the tip in the direction from the leading edge to the trailing edge. Preferably the passage outlets are situated a distance of between 1% and 25% of the span of the aerofoil from the tip and not more than a distance of 25% of the chord of the aerofoil from the leading edge. A rotor assembly is also claimed.</abstract><oa>free_for_read</oa></addata></record> |
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| language | eng |
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| subjects | BLASTING ENGINE PLANTS IN GENERAL HEATING LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES NON-POSITIVE DISPLACEMENT PUMPS POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS PUMPS FOR LIQUIDS OR ELASTIC FLUIDS STEAM ENGINES WEAPONS |
| title | Rotor blade with air flow passages |
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