Combustion chamber of an aeronautical turbine engine with combustion holes having different configurations

A combustion chamber for an aviation turbine engine, the combustion chamber being annular about a longitudinal axis and including an outer side wall, an inner side wall, and an annular chamber end wall connecting one end of the outer side wall to one end of the inner side wall. The outer side wall i...

Ausführliche Beschreibung

Gespeichert in:

Bibliographische Detailangaben
Hauptverfasser:	COMMARET PATRICE ANDRE, NOEL THOMAS OLIVIER MARIE
Format:	Patent
Sprache:	eng
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	COMMARET PATRICE ANDRE NOEL THOMAS OLIVIER MARIE
description	A combustion chamber for an aviation turbine engine, the combustion chamber being annular about a longitudinal axis and including an outer side wall, an inner side wall, and an annular chamber end wall connecting one end of the outer side wall to one end of the inner side wall. The outer side wall includes, distributed along its circumference, spark plugs, primary holes, and dilution holes situated downstream from the primary holes in the direction of the longitudinal axis. The primary holes situated in each of the adjacent zones adjacent to one of the spark plugs present a configuration that is different from the configuration of the primary holes situated outside the zones, such that the supply of air in the adjacent zones is different from the supply of air outside the zones.
format	Patent
fullrecord	<record><control><sourceid>epo_EVB</sourceid><recordid>TN_cdi_epo_espacenet_US9279588B2</recordid><sourceformat>XML</sourceformat><sourcesystem>PC</sourcesystem><sourcerecordid>US9279588B2</sourcerecordid><originalsourceid>FETCH-epo_espacenet_US9279588B23</originalsourceid><addsrcrecordid>eNqNyz0OwjAMQOEsDAi4gy_AUoRoVyoQOzBXTnAaV6lT5QeuD5WQWJne8r2lGtow6pIyBwHjcNQUIVhAAaQYBEtmgx5yiZqFgKSf8-LswPxOFzwlcPhk6eHB1lIkyR8hlvsScUZprRYWfaLNtysF59OtvWxpCh2lCQ0J5e5-bapDs6_rY7X7g7wBjLBB_A</addsrcrecordid><sourcetype>Open Access Repository</sourcetype><iscdi>true</iscdi><recordtype>patent</recordtype></control><display><type>patent</type><title>Combustion chamber of an aeronautical turbine engine with combustion holes having different configurations</title><source>esp@cenet</source><creator>COMMARET PATRICE ANDRE ; NOEL THOMAS OLIVIER MARIE</creator><creatorcontrib>COMMARET PATRICE ANDRE ; NOEL THOMAS OLIVIER MARIE</creatorcontrib><description>A combustion chamber for an aviation turbine engine, the combustion chamber being annular about a longitudinal axis and including an outer side wall, an inner side wall, and an annular chamber end wall connecting one end of the outer side wall to one end of the inner side wall. The outer side wall includes, distributed along its circumference, spark plugs, primary holes, and dilution holes situated downstream from the primary holes in the direction of the longitudinal axis. The primary holes situated in each of the adjacent zones adjacent to one of the spark plugs present a configuration that is different from the configuration of the primary holes situated outside the zones, such that the supply of air in the adjacent zones is different from the supply of air outside the zones.</description><language>eng</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>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=20160308&DB=EPODOC&CC=US&NR=9279588B2$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,780,885,25564,76547</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20160308&DB=EPODOC&CC=US&NR=9279588B2$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>COMMARET PATRICE ANDRE</creatorcontrib><creatorcontrib>NOEL THOMAS OLIVIER MARIE</creatorcontrib><title>Combustion chamber of an aeronautical turbine engine with combustion holes having different configurations</title><description>A combustion chamber for an aviation turbine engine, the combustion chamber being annular about a longitudinal axis and including an outer side wall, an inner side wall, and an annular chamber end wall connecting one end of the outer side wall to one end of the inner side wall. The outer side wall includes, distributed along its circumference, spark plugs, primary holes, and dilution holes situated downstream from the primary holes in the direction of the longitudinal axis. The primary holes situated in each of the adjacent zones adjacent to one of the spark plugs present a configuration that is different from the configuration of the primary holes situated outside the zones, such that the supply of air in the adjacent zones is different from the supply of air outside the zones.</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>2016</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNqNyz0OwjAMQOEsDAi4gy_AUoRoVyoQOzBXTnAaV6lT5QeuD5WQWJne8r2lGtow6pIyBwHjcNQUIVhAAaQYBEtmgx5yiZqFgKSf8-LswPxOFzwlcPhk6eHB1lIkyR8hlvsScUZprRYWfaLNtysF59OtvWxpCh2lCQ0J5e5-bapDs6_rY7X7g7wBjLBB_A</recordid><startdate>20160308</startdate><enddate>20160308</enddate><creator>COMMARET PATRICE ANDRE</creator><creator>NOEL THOMAS OLIVIER MARIE</creator><scope>EVB</scope></search><sort><creationdate>20160308</creationdate><title>Combustion chamber of an aeronautical turbine engine with combustion holes having different configurations</title><author>COMMARET PATRICE ANDRE ; NOEL THOMAS OLIVIER MARIE</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_US9279588B23</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng</language><creationdate>2016</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>COMMARET PATRICE ANDRE</creatorcontrib><creatorcontrib>NOEL THOMAS OLIVIER MARIE</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>COMMARET PATRICE ANDRE</au><au>NOEL THOMAS OLIVIER MARIE</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>Combustion chamber of an aeronautical turbine engine with combustion holes having different configurations</title><date>2016-03-08</date><risdate>2016</risdate><abstract>A combustion chamber for an aviation turbine engine, the combustion chamber being annular about a longitudinal axis and including an outer side wall, an inner side wall, and an annular chamber end wall connecting one end of the outer side wall to one end of the inner side wall. The outer side wall includes, distributed along its circumference, spark plugs, primary holes, and dilution holes situated downstream from the primary holes in the direction of the longitudinal axis. The primary holes situated in each of the adjacent zones adjacent to one of the spark plugs present a configuration that is different from the configuration of the primary holes situated outside the zones, such that the supply of air in the adjacent zones is different from the supply of air outside the zones.</abstract><oa>free_for_read</oa></addata></record>
fulltext	fulltext_linktorsrc
identifier
ispartof
issn
language	eng
recordid	cdi_epo_espacenet_US9279588B2
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	Combustion chamber of an aeronautical turbine engine with combustion holes having different configurations
url	https://sfx.bib-bvb.de/sfx_tum?ctx_ver=Z39.88-2004&ctx_enc=info:ofi/enc:UTF-8&ctx_tim=2024-12-21T08%3A32%3A36IST&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=COMMARET%20PATRICE%20ANDRE&rft.date=2016-03-08&rft_id=info:doi/&rft_dat=%3Cepo_EVB%3EUS9279588B2%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