Lobe lance for a gas turbine combustor
A lobe lance (21) for a gas turbine combustor comprises a plurality of N (N ¥ 4) lobe fingers (22a-d), whereby each of said lobe fingers (22a-d) is configured as a streamlined body which has a streamlined cross-sectional profile, whereby said body has two lateral surfaces essentially parallel to a...
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| creator | YANG, YANG DÜSING, MICHAEL |
| description | A lobe lance (21) for a gas turbine combustor comprises a plurality of N (N ¥ 4) lobe fingers (22a-d), whereby each of said lobe fingers (22a-d) is configured as a streamlined body which has a streamlined cross-sectional profile, whereby said body has two lateral surfaces essentially parallel to a direction (32) of hot gas flow, whereby said lateral surfaces are joined at their upstream side by a leading edge (23) and joined at their downstream side forming a trailing edge (24), whereby a plurality of nozzles (27) for injecting a gaseous and/or liquid fuel mixed with air is distributed along said trailing edge (24), and whereby lobes (28) running between said nozzles (27) are provided at said trailing edge (24) for improving the mixing quality and reducing pressure loss in said combustor. The mixing is improved by the lobes (28) of each lobe finger (22a-d) having one of two opposite orientations with respect to said flow direction (32), and the lobes (28) of all lobe fingers (22a-d) following a predetermined pattern of orientation across the lobe fingers (22a-d), and that at least one pair of neighboring lobe fingers (22a-d) has the same lobe orientation resulting in a grouped lobe arrangement (...LL...or...RR...) such that at least two of the vortices generated by the lobe shape downstream of said lobe fingers (22a-d) combine. |
| format | Patent |
| fullrecord | <record><control><sourceid>epo_EVB</sourceid><recordid>TN_cdi_epo_espacenet_EP3023696A1</recordid><sourceformat>XML</sourceformat><sourcesystem>PC</sourcesystem><sourcerecordid>EP3023696A1</sourcerecordid><originalsourceid>FETCH-epo_espacenet_EP3023696A13</originalsourceid><addsrcrecordid>eNrjZFDzyU9KVchJzEtOVUjLL1JIVEhPLFYoKS1KysxLVUjOz00qLS7JL-JhYE1LzClO5YXS3AwKbq4hzh66qQX58anFBYnJqXmpJfGuAcYGRsZmlmaOhsZEKAEA5rcmrg</addsrcrecordid><sourcetype>Open Access Repository</sourcetype><iscdi>true</iscdi><recordtype>patent</recordtype></control><display><type>patent</type><title>Lobe lance for a gas turbine combustor</title><source>esp@cenet</source><creator>YANG, YANG ; DÜSING, MICHAEL</creator><creatorcontrib>YANG, YANG ; DÜSING, MICHAEL</creatorcontrib><description>A lobe lance (21) for a gas turbine combustor comprises a plurality of N (N ¥ 4) lobe fingers (22a-d), whereby each of said lobe fingers (22a-d) is configured as a streamlined body which has a streamlined cross-sectional profile, whereby said body has two lateral surfaces essentially parallel to a direction (32) of hot gas flow, whereby said lateral surfaces are joined at their upstream side by a leading edge (23) and joined at their downstream side forming a trailing edge (24), whereby a plurality of nozzles (27) for injecting a gaseous and/or liquid fuel mixed with air is distributed along said trailing edge (24), and whereby lobes (28) running between said nozzles (27) are provided at said trailing edge (24) for improving the mixing quality and reducing pressure loss in said combustor. The mixing is improved by the lobes (28) of each lobe finger (22a-d) having one of two opposite orientations with respect to said flow direction (32), and the lobes (28) of all lobe fingers (22a-d) following a predetermined pattern of orientation across the lobe fingers (22a-d), and that at least one pair of neighboring lobe fingers (22a-d) has the same lobe orientation resulting in a grouped lobe arrangement (...LL...or...RR...) such that at least two of the vortices generated by the lobe shape downstream of said lobe fingers (22a-d) combine.</description><language>eng ; fre ; ger</language><subject>BLASTING ; COMBUSTION APPARATUS ; COMBUSTION PROCESSES ; ENGINE PLANTS IN GENERAL ; GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS ; HEATING ; LIGHTING ; MACHINES OR ENGINES IN GENERAL ; MECHANICAL ENGINEERING ; NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES ; STEAM ENGINES ; WEAPONS</subject><creationdate>2016</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=20160525&DB=EPODOC&CC=EP&NR=3023696A1$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,776,881,25542,76290</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20160525&DB=EPODOC&CC=EP&NR=3023696A1$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>YANG, YANG</creatorcontrib><creatorcontrib>DÜSING, MICHAEL</creatorcontrib><title>Lobe lance for a gas turbine combustor</title><description>A lobe lance (21) for a gas turbine combustor comprises a plurality of N (N ¥ 4) lobe fingers (22a-d), whereby each of said lobe fingers (22a-d) is configured as a streamlined body which has a streamlined cross-sectional profile, whereby said body has two lateral surfaces essentially parallel to a direction (32) of hot gas flow, whereby said lateral surfaces are joined at their upstream side by a leading edge (23) and joined at their downstream side forming a trailing edge (24), whereby a plurality of nozzles (27) for injecting a gaseous and/or liquid fuel mixed with air is distributed along said trailing edge (24), and whereby lobes (28) running between said nozzles (27) are provided at said trailing edge (24) for improving the mixing quality and reducing pressure loss in said combustor. The mixing is improved by the lobes (28) of each lobe finger (22a-d) having one of two opposite orientations with respect to said flow direction (32), and the lobes (28) of all lobe fingers (22a-d) following a predetermined pattern of orientation across the lobe fingers (22a-d), and that at least one pair of neighboring lobe fingers (22a-d) has the same lobe orientation resulting in a grouped lobe arrangement (...LL...or...RR...) such that at least two of the vortices generated by the lobe shape downstream of said lobe fingers (22a-d) combine.</description><subject>BLASTING</subject><subject>COMBUSTION APPARATUS</subject><subject>COMBUSTION PROCESSES</subject><subject>ENGINE PLANTS IN GENERAL</subject><subject>GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS</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>2016</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZFDzyU9KVchJzEtOVUjLL1JIVEhPLFYoKS1KysxLVUjOz00qLS7JL-JhYE1LzClO5YXS3AwKbq4hzh66qQX58anFBYnJqXmpJfGuAcYGRsZmlmaOhsZEKAEA5rcmrg</recordid><startdate>20160525</startdate><enddate>20160525</enddate><creator>YANG, YANG</creator><creator>DÜSING, MICHAEL</creator><scope>EVB</scope></search><sort><creationdate>20160525</creationdate><title>Lobe lance for a gas turbine combustor</title><author>YANG, YANG ; DÜSING, MICHAEL</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_EP3023696A13</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng ; fre ; ger</language><creationdate>2016</creationdate><topic>BLASTING</topic><topic>COMBUSTION APPARATUS</topic><topic>COMBUSTION PROCESSES</topic><topic>ENGINE PLANTS IN GENERAL</topic><topic>GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS</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>YANG, YANG</creatorcontrib><creatorcontrib>DÜSING, MICHAEL</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>YANG, YANG</au><au>DÜSING, MICHAEL</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>Lobe lance for a gas turbine combustor</title><date>2016-05-25</date><risdate>2016</risdate><abstract>A lobe lance (21) for a gas turbine combustor comprises a plurality of N (N ¥ 4) lobe fingers (22a-d), whereby each of said lobe fingers (22a-d) is configured as a streamlined body which has a streamlined cross-sectional profile, whereby said body has two lateral surfaces essentially parallel to a direction (32) of hot gas flow, whereby said lateral surfaces are joined at their upstream side by a leading edge (23) and joined at their downstream side forming a trailing edge (24), whereby a plurality of nozzles (27) for injecting a gaseous and/or liquid fuel mixed with air is distributed along said trailing edge (24), and whereby lobes (28) running between said nozzles (27) are provided at said trailing edge (24) for improving the mixing quality and reducing pressure loss in said combustor. The mixing is improved by the lobes (28) of each lobe finger (22a-d) having one of two opposite orientations with respect to said flow direction (32), and the lobes (28) of all lobe fingers (22a-d) following a predetermined pattern of orientation across the lobe fingers (22a-d), and that at least one pair of neighboring lobe fingers (22a-d) has the same lobe orientation resulting in a grouped lobe arrangement (...LL...or...RR...) such that at least two of the vortices generated by the lobe shape downstream of said lobe fingers (22a-d) combine.</abstract><oa>free_for_read</oa></addata></record> |
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| language | eng ; fre ; ger |
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| subjects | BLASTING COMBUSTION APPARATUS COMBUSTION PROCESSES ENGINE PLANTS IN GENERAL GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS HEATING LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS |
| title | Lobe lance for a gas turbine combustor |
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