COMBUSTION CHAMBER COMPRISING SECONDARY INJECTION SYSTEMS, AND FUEL SUPPLY METHOD

A combustion chamber for an aircraft turbomachine includes an annular chamber end wall structure, an annular row of main injection systems mounted in the chamber end wall structure and configured to deliver a sheet of fuel, including a central recirculation region and a corner recirculation region a...

Ausführliche Beschreibung

Gespeichert in:

Bibliographische Detailangaben
Hauptverfasser:	MUSAEFENDIC, Haris, CABRE, Jean-François, LUNEL, Romain Nicolas, LEPAROUX, Julien Marc Matthieu
Format:	Patent
Sprache:	eng
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION APPARATUS COMBUSTION ENGINES COMBUSTION PROCESSES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS GAS-TURBINE PLANTS GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS 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	MUSAEFENDIC, Haris CABRE, Jean-François LUNEL, Romain Nicolas LEPAROUX, Julien Marc Matthieu
description	A combustion chamber for an aircraft turbomachine includes an annular chamber end wall structure, an annular row of main injection systems mounted in the chamber end wall structure and configured to deliver a sheet of fuel, including a central recirculation region and a corner recirculation region around the central recirculation region, and secondary injection systems each configured to inject an additional flow of air and fuel directly into a corresponding corner recirculation region.
format	Patent
fullrecord	<record><control><sourceid>epo_EVB</sourceid><recordid>TN_cdi_epo_espacenet_US2022275941A1</recordid><sourceformat>XML</sourceformat><sourcesystem>PC</sourcesystem><sourcerecordid>US2022275941A1</sourcerecordid><originalsourceid>FETCH-epo_espacenet_US2022275941A13</originalsourceid><addsrcrecordid>eNrjZAh09vd1Cg0O8fT3U3D2cPR1cg1SAAoFBHkGe_q5KwS7Ovv7uTgGRSp4-nm5OoOVBUcGh7j6BusoOPq5KLiFuvooBIcGBPhEKvi6hnj4u_AwsKYl5hSn8kJpbgZlN9cQZw_d1IL8-NTigsTk1LzUkvjQYCMDIyMjc1NLE0NHQ2PiVAEAkVgwnA</addsrcrecordid><sourcetype>Open Access Repository</sourcetype><iscdi>true</iscdi><recordtype>patent</recordtype></control><display><type>patent</type><title>COMBUSTION CHAMBER COMPRISING SECONDARY INJECTION SYSTEMS, AND FUEL SUPPLY METHOD</title><source>esp@cenet</source><creator>MUSAEFENDIC, Haris ; CABRE, Jean-François ; LUNEL, Romain Nicolas ; LEPAROUX, Julien Marc Matthieu</creator><creatorcontrib>MUSAEFENDIC, Haris ; CABRE, Jean-François ; LUNEL, Romain Nicolas ; LEPAROUX, Julien Marc Matthieu</creatorcontrib><description>A combustion chamber for an aircraft turbomachine includes an annular chamber end wall structure, an annular row of main injection systems mounted in the chamber end wall structure and configured to deliver a sheet of fuel, including a central recirculation region and a corner recirculation region around the central recirculation region, and secondary injection systems each configured to inject an additional flow of air and fuel directly into a corresponding corner recirculation region.</description><language>eng</language><subject>AIR INTAKES FOR JET-PROPULSION PLANTS ; BLASTING ; COMBUSTION APPARATUS ; COMBUSTION ENGINES ; COMBUSTION PROCESSES ; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ; GAS-TURBINE PLANTS ; GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS ; HEATING ; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS ; LIGHTING ; MECHANICAL ENGINEERING ; WEAPONS</subject><creationdate>2022</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=20220901&DB=EPODOC&CC=US&NR=2022275941A1$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,780,885,25564,76547</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20220901&DB=EPODOC&CC=US&NR=2022275941A1$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>MUSAEFENDIC, Haris</creatorcontrib><creatorcontrib>CABRE, Jean-François</creatorcontrib><creatorcontrib>LUNEL, Romain Nicolas</creatorcontrib><creatorcontrib>LEPAROUX, Julien Marc Matthieu</creatorcontrib><title>COMBUSTION CHAMBER COMPRISING SECONDARY INJECTION SYSTEMS, AND FUEL SUPPLY METHOD</title><description>A combustion chamber for an aircraft turbomachine includes an annular chamber end wall structure, an annular row of main injection systems mounted in the chamber end wall structure and configured to deliver a sheet of fuel, including a central recirculation region and a corner recirculation region around the central recirculation region, and secondary injection systems each configured to inject an additional flow of air and fuel directly into a corresponding corner recirculation region.</description><subject>AIR INTAKES FOR JET-PROPULSION PLANTS</subject><subject>BLASTING</subject><subject>COMBUSTION APPARATUS</subject><subject>COMBUSTION ENGINES</subject><subject>COMBUSTION PROCESSES</subject><subject>CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS</subject><subject>GAS-TURBINE PLANTS</subject><subject>GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS</subject><subject>HEATING</subject><subject>HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS</subject><subject>LIGHTING</subject><subject>MECHANICAL ENGINEERING</subject><subject>WEAPONS</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2022</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZAh09vd1Cg0O8fT3U3D2cPR1cg1SAAoFBHkGe_q5KwS7Ovv7uTgGRSp4-nm5OoOVBUcGh7j6BusoOPq5KLiFuvooBIcGBPhEKvi6hnj4u_AwsKYl5hSn8kJpbgZlN9cQZw_d1IL8-NTigsTk1LzUkvjQYCMDIyMjc1NLE0NHQ2PiVAEAkVgwnA</recordid><startdate>20220901</startdate><enddate>20220901</enddate><creator>MUSAEFENDIC, Haris</creator><creator>CABRE, Jean-François</creator><creator>LUNEL, Romain Nicolas</creator><creator>LEPAROUX, Julien Marc Matthieu</creator><scope>EVB</scope></search><sort><creationdate>20220901</creationdate><title>COMBUSTION CHAMBER COMPRISING SECONDARY INJECTION SYSTEMS, AND FUEL SUPPLY METHOD</title><author>MUSAEFENDIC, Haris ; CABRE, Jean-François ; LUNEL, Romain Nicolas ; LEPAROUX, Julien Marc Matthieu</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_US2022275941A13</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng</language><creationdate>2022</creationdate><topic>AIR INTAKES FOR JET-PROPULSION PLANTS</topic><topic>BLASTING</topic><topic>COMBUSTION APPARATUS</topic><topic>COMBUSTION ENGINES</topic><topic>COMBUSTION PROCESSES</topic><topic>CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS</topic><topic>GAS-TURBINE PLANTS</topic><topic>GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS</topic><topic>HEATING</topic><topic>HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS</topic><topic>LIGHTING</topic><topic>MECHANICAL ENGINEERING</topic><topic>WEAPONS</topic><toplevel>online_resources</toplevel><creatorcontrib>MUSAEFENDIC, Haris</creatorcontrib><creatorcontrib>CABRE, Jean-François</creatorcontrib><creatorcontrib>LUNEL, Romain Nicolas</creatorcontrib><creatorcontrib>LEPAROUX, Julien Marc Matthieu</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>MUSAEFENDIC, Haris</au><au>CABRE, Jean-François</au><au>LUNEL, Romain Nicolas</au><au>LEPAROUX, Julien Marc Matthieu</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>COMBUSTION CHAMBER COMPRISING SECONDARY INJECTION SYSTEMS, AND FUEL SUPPLY METHOD</title><date>2022-09-01</date><risdate>2022</risdate><abstract>A combustion chamber for an aircraft turbomachine includes an annular chamber end wall structure, an annular row of main injection systems mounted in the chamber end wall structure and configured to deliver a sheet of fuel, including a central recirculation region and a corner recirculation region around the central recirculation region, and secondary injection systems each configured to inject an additional flow of air and fuel directly into a corresponding corner recirculation region.</abstract><oa>free_for_read</oa></addata></record>
fulltext	fulltext_linktorsrc
identifier
ispartof
issn
language	eng
recordid	cdi_epo_espacenet_US2022275941A1
source	esp@cenet
subjects	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION APPARATUS COMBUSTION ENGINES COMBUSTION PROCESSES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS GAS-TURBINE PLANTS GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS
title	COMBUSTION CHAMBER COMPRISING SECONDARY INJECTION SYSTEMS, AND FUEL SUPPLY METHOD
url	https://sfx.bib-bvb.de/sfx_tum?ctx_ver=Z39.88-2004&ctx_enc=info:ofi/enc:UTF-8&ctx_tim=2025-01-01T06%3A07%3A39IST&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=MUSAEFENDIC,%20Haris&rft.date=2022-09-01&rft_id=info:doi/&rft_dat=%3Cepo_EVB%3EUS2022275941A1%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