GAS TURBINE COMBUSTOR HAVING LINER COOLING GUIDE VANES

GAS TURBINE COMBUSTOR HAVING LINER COOLING GUIDE VANES

The present disclosure is directed to a combustor having an annularly shaped liner that at least partially defines a hot gas path of the combustor. A flow sleeve (54) circumferentially surrounds at least a portion of the liner. The flow sleeve (54) is radially spaced from the liner to form a cooling...

Ausführliche Beschreibung

Gespeichert in:
Bibliographische Detailangaben
Hauptverfasser: GODFREY, Andrew Grady, PORZIO, David Philip, CIHLAR, David William, WILLIS, Christopher Paul
Format: Patent
Sprache:eng ; fre ; ger
Schlagworte:
BLASTING
COMBUSTION APPARATUS
COMBUSTION PROCESSES
GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
HEATING
LIGHTING
MECHANICAL ENGINEERING
WEAPONS
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 GODFREY, Andrew Grady
PORZIO, David Philip
CIHLAR, David William
WILLIS, Christopher Paul
description The present disclosure is directed to a combustor having an annularly shaped liner that at least partially defines a hot gas path of the combustor. A flow sleeve (54) circumferentially surrounds at least a portion of the liner. The flow sleeve (54) is radially spaced from the liner to form a cooling flow annulus (56) there-between. A bluff body extends radially between the flow sleeve (54) and the liner through the cooling flow annulus (56). A guide vane (68) is disposed within the cooling flow annulus (56) and extends between the flow sleeve (54) and the liner downstream and proximate to the bluff body.
format Patent
fullrecord <record><control><sourceid>epo_EVB</sourceid><recordid>TN_cdi_epo_espacenet_EP3220049B1</recordid><sourceformat>XML</sourceformat><sourcesystem>PC</sourcesystem><sourcerecordid>EP3220049B1</sourcerecordid><originalsourceid>FETCH-epo_espacenet_EP3220049B13</originalsourceid><addsrcrecordid>eNrjZDBzdwxWCAkNcvL0c1Vw9vd1Cg0O8Q9S8HAM8_RzV_ABigYBhf19QDz3UE8XV4UwRz_XYB4G1rTEnOJUXijNzaDg5hri7KGbWpAfn1pckJicmpdaEu8aYGxkZGBgYulkaEyEEgDDHSdu</addsrcrecordid><sourcetype>Open Access Repository</sourcetype><iscdi>true</iscdi><recordtype>patent</recordtype></control><display><type>patent</type><title>GAS TURBINE COMBUSTOR HAVING LINER COOLING GUIDE VANES</title><source>esp@cenet</source><creator>GODFREY, Andrew Grady ; PORZIO, David Philip ; CIHLAR, David William ; WILLIS, Christopher Paul</creator><creatorcontrib>GODFREY, Andrew Grady ; PORZIO, David Philip ; CIHLAR, David William ; WILLIS, Christopher Paul</creatorcontrib><description>The present disclosure is directed to a combustor having an annularly shaped liner that at least partially defines a hot gas path of the combustor. A flow sleeve (54) circumferentially surrounds at least a portion of the liner. The flow sleeve (54) is radially spaced from the liner to form a cooling flow annulus (56) there-between. A bluff body extends radially between the flow sleeve (54) and the liner through the cooling flow annulus (56). A guide vane (68) is disposed within the cooling flow annulus (56) and extends between the flow sleeve (54) and the liner downstream and proximate to the bluff body.</description><language>eng ; fre ; ger</language><subject>BLASTING ; 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>2019</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=20190605&amp;DB=EPODOC&amp;CC=EP&amp;NR=3220049B1$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,776,881,25542,76289</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&amp;date=20190605&amp;DB=EPODOC&amp;CC=EP&amp;NR=3220049B1$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>GODFREY, Andrew Grady</creatorcontrib><creatorcontrib>PORZIO, David Philip</creatorcontrib><creatorcontrib>CIHLAR, David William</creatorcontrib><creatorcontrib>WILLIS, Christopher Paul</creatorcontrib><title>GAS TURBINE COMBUSTOR HAVING LINER COOLING GUIDE VANES</title><description>The present disclosure is directed to a combustor having an annularly shaped liner that at least partially defines a hot gas path of the combustor. A flow sleeve (54) circumferentially surrounds at least a portion of the liner. The flow sleeve (54) is radially spaced from the liner to form a cooling flow annulus (56) there-between. A bluff body extends radially between the flow sleeve (54) and the liner through the cooling flow annulus (56). A guide vane (68) is disposed within the cooling flow annulus (56) and extends between the flow sleeve (54) and the liner downstream and proximate to the bluff body.</description><subject>BLASTING</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>2019</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZDBzdwxWCAkNcvL0c1Vw9vd1Cg0O8Q9S8HAM8_RzV_ABigYBhf19QDz3UE8XV4UwRz_XYB4G1rTEnOJUXijNzaDg5hri7KGbWpAfn1pckJicmpdaEu8aYGxkZGBgYulkaEyEEgDDHSdu</recordid><startdate>20190605</startdate><enddate>20190605</enddate><creator>GODFREY, Andrew Grady</creator><creator>PORZIO, David Philip</creator><creator>CIHLAR, David William</creator><creator>WILLIS, Christopher Paul</creator><scope>EVB</scope></search><sort><creationdate>20190605</creationdate><title>GAS TURBINE COMBUSTOR HAVING LINER COOLING GUIDE VANES</title><author>GODFREY, Andrew Grady ; PORZIO, David Philip ; CIHLAR, David William ; WILLIS, Christopher Paul</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_EP3220049B13</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng ; fre ; ger</language><creationdate>2019</creationdate><topic>BLASTING</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>GODFREY, Andrew Grady</creatorcontrib><creatorcontrib>PORZIO, David Philip</creatorcontrib><creatorcontrib>CIHLAR, David William</creatorcontrib><creatorcontrib>WILLIS, Christopher Paul</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>GODFREY, Andrew Grady</au><au>PORZIO, David Philip</au><au>CIHLAR, David William</au><au>WILLIS, Christopher Paul</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>GAS TURBINE COMBUSTOR HAVING LINER COOLING GUIDE VANES</title><date>2019-06-05</date><risdate>2019</risdate><abstract>The present disclosure is directed to a combustor having an annularly shaped liner that at least partially defines a hot gas path of the combustor. A flow sleeve (54) circumferentially surrounds at least a portion of the liner. The flow sleeve (54) is radially spaced from the liner to form a cooling flow annulus (56) there-between. A bluff body extends radially between the flow sleeve (54) and the liner through the cooling flow annulus (56). A guide vane (68) is disposed within the cooling flow annulus (56) and extends between the flow sleeve (54) and the liner downstream and proximate to the bluff body.</abstract><oa>free_for_read</oa></addata></record>
fulltext fulltext_linktorsrc
identifier
ispartof
issn
language eng ; fre ; ger
recordid cdi_epo_espacenet_EP3220049B1
source esp@cenet
subjects BLASTING
COMBUSTION APPARATUS
COMBUSTION PROCESSES
GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
HEATING
LIGHTING
MECHANICAL ENGINEERING
WEAPONS
title GAS TURBINE COMBUSTOR HAVING LINER COOLING GUIDE VANES
url https://sfx.bib-bvb.de/sfx_tum?ctx_ver=Z39.88-2004&ctx_enc=info:ofi/enc:UTF-8&ctx_tim=2025-02-12T13%3A31%3A43IST&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=GODFREY,%20Andrew%20Grady&rft.date=2019-06-05&rft_id=info:doi/&rft_dat=%3Cepo_EVB%3EEP3220049B1%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