Fuel injection assembly for a gas turbine

A gas turbine comprises a combustion unit (8), a flow sleeve (2) surrounding the combustion unit (8), wherein the flow sleeve (2) is positioned radially outward from the combustion unit (8). Further, the gas turbine includes a fuel injection assembly which is integrated with a flange means (4) which...

Ausführliche Beschreibung

Gespeichert in:
Bibliographische Detailangaben
Hauptverfasser: SINGH, RAM BAHADUR, SINGH, MANOJ, GUPTA, GAURAV, PFADLER, SEBASTIAN
Format: Patent
Sprache:eng ; fre ; ger
Schlagworte:
Online-Zugang:Volltext bestellen
Tags: Tag hinzufügen
Keine Tags, Fügen Sie den ersten Tag hinzu!
container_end_page
container_issue
container_start_page
container_title
container_volume
creator SINGH, RAM BAHADUR
SINGH, MANOJ
GUPTA, GAURAV
PFADLER, SEBASTIAN
description A gas turbine comprises a combustion unit (8), a flow sleeve (2) surrounding the combustion unit (8), wherein the flow sleeve (2) is positioned radially outward from the combustion unit (8). Further, the gas turbine includes a fuel injection assembly which is integrated with a flange means (4) which supports the combustion unit (8). The fuel injection assembly is provided with a hollow fuel supply casing having an outer wall (10). The fuel injection assembly comprises a plurality of dispensing tubes (12) coupled to the outer wall (10). The plurality of dispensing tubes (12) is adapted to discharge fuel into the annular cavity. The fuel injection assembly is disposed in the annular cavity between the flow sleeve (2) and a combustion unit (2) of the gas turbine.
format Patent
fullrecord <record><control><sourceid>epo_EVB</sourceid><recordid>TN_cdi_epo_espacenet_EP2949999A1</recordid><sourceformat>XML</sourceformat><sourcesystem>PC</sourcesystem><sourcerecordid>EP2949999A1</sourcerecordid><originalsourceid>FETCH-epo_espacenet_EP2949999A13</originalsourceid><addsrcrecordid>eNrjZNB0K03NUcjMy0pNLsnMz1NILC5OzU3KqVRIyy9SSFRITyxWKCktSsrMS-VhYE1LzClO5YXS3AwKbq4hzh66qQX58anFBYnJqXmpJfGuAUaWJpZA4GhoTIQSAJggKCk</addsrcrecordid><sourcetype>Open Access Repository</sourcetype><iscdi>true</iscdi><recordtype>patent</recordtype></control><display><type>patent</type><title>Fuel injection assembly for a gas turbine</title><source>esp@cenet</source><creator>SINGH, RAM BAHADUR ; SINGH, MANOJ ; GUPTA, GAURAV ; PFADLER, SEBASTIAN</creator><creatorcontrib>SINGH, RAM BAHADUR ; SINGH, MANOJ ; GUPTA, GAURAV ; PFADLER, SEBASTIAN</creatorcontrib><description>A gas turbine comprises a combustion unit (8), a flow sleeve (2) surrounding the combustion unit (8), wherein the flow sleeve (2) is positioned radially outward from the combustion unit (8). Further, the gas turbine includes a fuel injection assembly which is integrated with a flange means (4) which supports the combustion unit (8). The fuel injection assembly is provided with a hollow fuel supply casing having an outer wall (10). The fuel injection assembly comprises a plurality of dispensing tubes (12) coupled to the outer wall (10). The plurality of dispensing tubes (12) is adapted to discharge fuel into the annular cavity. The fuel injection assembly is disposed in the annular cavity between the flow sleeve (2) and a combustion unit (2) of the gas turbine.</description><language>eng ; fre ; ger</language><subject>BLASTING ; BURNERS ; COMBUSTION APPARATUS ; COMBUSTION PROCESSES ; GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS ; HEATING ; LIGHTING ; MECHANICAL ENGINEERING ; WEAPONS</subject><creationdate>2015</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&amp;date=20151202&amp;DB=EPODOC&amp;CC=EP&amp;NR=2949999A1$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,780,885,25564,76547</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&amp;date=20151202&amp;DB=EPODOC&amp;CC=EP&amp;NR=2949999A1$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>SINGH, RAM BAHADUR</creatorcontrib><creatorcontrib>SINGH, MANOJ</creatorcontrib><creatorcontrib>GUPTA, GAURAV</creatorcontrib><creatorcontrib>PFADLER, SEBASTIAN</creatorcontrib><title>Fuel injection assembly for a gas turbine</title><description>A gas turbine comprises a combustion unit (8), a flow sleeve (2) surrounding the combustion unit (8), wherein the flow sleeve (2) is positioned radially outward from the combustion unit (8). Further, the gas turbine includes a fuel injection assembly which is integrated with a flange means (4) which supports the combustion unit (8). The fuel injection assembly is provided with a hollow fuel supply casing having an outer wall (10). The fuel injection assembly comprises a plurality of dispensing tubes (12) coupled to the outer wall (10). The plurality of dispensing tubes (12) is adapted to discharge fuel into the annular cavity. The fuel injection assembly is disposed in the annular cavity between the flow sleeve (2) and a combustion unit (2) of the gas turbine.</description><subject>BLASTING</subject><subject>BURNERS</subject><subject>COMBUSTION APPARATUS</subject><subject>COMBUSTION PROCESSES</subject><subject>GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS</subject><subject>HEATING</subject><subject>LIGHTING</subject><subject>MECHANICAL ENGINEERING</subject><subject>WEAPONS</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2015</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZNB0K03NUcjMy0pNLsnMz1NILC5OzU3KqVRIyy9SSFRITyxWKCktSsrMS-VhYE1LzClO5YXS3AwKbq4hzh66qQX58anFBYnJqXmpJfGuAUaWJpZA4GhoTIQSAJggKCk</recordid><startdate>20151202</startdate><enddate>20151202</enddate><creator>SINGH, RAM BAHADUR</creator><creator>SINGH, MANOJ</creator><creator>GUPTA, GAURAV</creator><creator>PFADLER, SEBASTIAN</creator><scope>EVB</scope></search><sort><creationdate>20151202</creationdate><title>Fuel injection assembly for a gas turbine</title><author>SINGH, RAM BAHADUR ; SINGH, MANOJ ; GUPTA, GAURAV ; PFADLER, SEBASTIAN</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_EP2949999A13</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng ; fre ; ger</language><creationdate>2015</creationdate><topic>BLASTING</topic><topic>BURNERS</topic><topic>COMBUSTION APPARATUS</topic><topic>COMBUSTION PROCESSES</topic><topic>GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS</topic><topic>HEATING</topic><topic>LIGHTING</topic><topic>MECHANICAL ENGINEERING</topic><topic>WEAPONS</topic><toplevel>online_resources</toplevel><creatorcontrib>SINGH, RAM BAHADUR</creatorcontrib><creatorcontrib>SINGH, MANOJ</creatorcontrib><creatorcontrib>GUPTA, GAURAV</creatorcontrib><creatorcontrib>PFADLER, SEBASTIAN</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>SINGH, RAM BAHADUR</au><au>SINGH, MANOJ</au><au>GUPTA, GAURAV</au><au>PFADLER, SEBASTIAN</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>Fuel injection assembly for a gas turbine</title><date>2015-12-02</date><risdate>2015</risdate><abstract>A gas turbine comprises a combustion unit (8), a flow sleeve (2) surrounding the combustion unit (8), wherein the flow sleeve (2) is positioned radially outward from the combustion unit (8). Further, the gas turbine includes a fuel injection assembly which is integrated with a flange means (4) which supports the combustion unit (8). The fuel injection assembly is provided with a hollow fuel supply casing having an outer wall (10). The fuel injection assembly comprises a plurality of dispensing tubes (12) coupled to the outer wall (10). The plurality of dispensing tubes (12) is adapted to discharge fuel into the annular cavity. The fuel injection assembly is disposed in the annular cavity between the flow sleeve (2) and a combustion unit (2) of the gas turbine.</abstract><oa>free_for_read</oa></addata></record>
fulltext fulltext_linktorsrc
identifier
ispartof
issn
language eng ; fre ; ger
recordid cdi_epo_espacenet_EP2949999A1
source esp@cenet
subjects BLASTING
BURNERS
COMBUSTION APPARATUS
COMBUSTION PROCESSES
GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
HEATING
LIGHTING
MECHANICAL ENGINEERING
WEAPONS
title Fuel injection assembly for a gas turbine
url https://sfx.bib-bvb.de/sfx_tum?ctx_ver=Z39.88-2004&ctx_enc=info:ofi/enc:UTF-8&ctx_tim=2024-12-23T16%3A05%3A08IST&url_ver=Z39.88-2004&url_ctx_fmt=infofi/fmt:kev:mtx:ctx&rfr_id=info:sid/primo.exlibrisgroup.com:primo3-Article-epo_EVB&rft_val_fmt=info:ofi/fmt:kev:mtx:patent&rft.genre=patent&rft.au=SINGH,%20RAM%20BAHADUR&rft.date=2015-12-02&rft_id=info:doi/&rft_dat=%3Cepo_EVB%3EEP2949999A1%3C/epo_EVB%3E%3Curl%3E%3C/url%3E&disable_directlink=true&sfx.directlink=off&sfx.report_link=0&rft_id=info:oai/&rft_id=info:pmid/&rfr_iscdi=true