Method for defining the shape of a turbomachine convergent-divergent nozzle, and corresponding convergent-divergent nozzle

Method for defining the shape of a turbomachine convergent-divergent nozzle, and corresponding convergent-divergent nozzle

According to the invention, the method for defining the shape of a convergent-divergent nozzle of longitudinal axis L-L comprising a convergent part connected, at a throat, to a divergent part the downstream free end of which comprises scallops delimiting noise-reducing chevrons distributed in the c...

Ausführliche Beschreibung

Gespeichert in:
Bibliographische Detailangaben
Hauptverfasser: Jonathan Langridge, Julien Szydlowski, Guillaume Bodard, Matthieu Leyko
Format: Patent
Sprache:eng
Schlagworte:
BLASTING
COMBUSTION ENGINES
HEATING
HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
JET-PROPULSION 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 Jonathan Langridge
Julien Szydlowski
Guillaume Bodard
Matthieu Leyko
description According to the invention, the method for defining the shape of a convergent-divergent nozzle of longitudinal axis L-L comprising a convergent part connected, at a throat, to a divergent part the downstream free end of which comprises scallops delimiting noise-reducing chevrons distributed in the circumferential direction, comprises defining beforehand the divergent part of the nozzle using a divergent first portion, a divergent second portion and a convergent portion, attributing an initial value to dimensional parameters defining the chevrons and the three portions, calculating performance criteria and checking that the calculated performance criteria satisfy predefined performance conditions.
format Patent
fullrecord <record><control><sourceid>epo_EVB</sourceid><recordid>TN_cdi_epo_espacenet_GB2500466B</recordid><sourceformat>XML</sourceformat><sourcesystem>PC</sourcesystem><sourcerecordid>GB2500466B</sourcerecordid><originalsourceid>FETCH-epo_espacenet_GB2500466B3</originalsourceid><addsrcrecordid>eNqFzDsOwjAQhGE3FAg4A3sAIkU8coAgHg0dfWTscWwp7Ea2ocjpCVJqqGaKT_9cDTdkL5acRLJwgQO3lD0oed2DxJGm_IoPeWrjA4OM8BuxBefChukRyzB02JBmO4IYkXph-0394Es1c7pLWE27UOvz6X68FuilGQvagJGbS709lOW-qurdf_EBk5VHEg</addsrcrecordid><sourcetype>Open Access Repository</sourcetype><iscdi>true</iscdi><recordtype>patent</recordtype></control><display><type>patent</type><title>Method for defining the shape of a turbomachine convergent-divergent nozzle, and corresponding convergent-divergent nozzle</title><source>esp@cenet</source><creator>Jonathan Langridge ; Julien Szydlowski ; Guillaume Bodard ; Matthieu Leyko</creator><creatorcontrib>Jonathan Langridge ; Julien Szydlowski ; Guillaume Bodard ; Matthieu Leyko</creatorcontrib><description>According to the invention, the method for defining the shape of a convergent-divergent nozzle of longitudinal axis L-L comprising a convergent part connected, at a throat, to a divergent part the downstream free end of which comprises scallops delimiting noise-reducing chevrons distributed in the circumferential direction, comprises defining beforehand the divergent part of the nozzle using a divergent first portion, a divergent second portion and a convergent portion, attributing an initial value to dimensional parameters defining the chevrons and the three portions, calculating performance criteria and checking that the calculated performance criteria satisfy predefined performance conditions.</description><language>eng</language><subject>BLASTING ; COMBUSTION ENGINES ; HEATING ; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS ; JET-PROPULSION PLANTS ; 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=20190529&amp;DB=EPODOC&amp;CC=GB&amp;NR=2500466B$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,776,881,25542,76290</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&amp;date=20190529&amp;DB=EPODOC&amp;CC=GB&amp;NR=2500466B$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>Jonathan Langridge</creatorcontrib><creatorcontrib>Julien Szydlowski</creatorcontrib><creatorcontrib>Guillaume Bodard</creatorcontrib><creatorcontrib>Matthieu Leyko</creatorcontrib><title>Method for defining the shape of a turbomachine convergent-divergent nozzle, and corresponding convergent-divergent nozzle</title><description>According to the invention, the method for defining the shape of a convergent-divergent nozzle of longitudinal axis L-L comprising a convergent part connected, at a throat, to a divergent part the downstream free end of which comprises scallops delimiting noise-reducing chevrons distributed in the circumferential direction, comprises defining beforehand the divergent part of the nozzle using a divergent first portion, a divergent second portion and a convergent portion, attributing an initial value to dimensional parameters defining the chevrons and the three portions, calculating performance criteria and checking that the calculated performance criteria satisfy predefined performance conditions.</description><subject>BLASTING</subject><subject>COMBUSTION ENGINES</subject><subject>HEATING</subject><subject>HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS</subject><subject>JET-PROPULSION PLANTS</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>eNqFzDsOwjAQhGE3FAg4A3sAIkU8coAgHg0dfWTscWwp7Ea2ocjpCVJqqGaKT_9cDTdkL5acRLJwgQO3lD0oed2DxJGm_IoPeWrjA4OM8BuxBefChukRyzB02JBmO4IYkXph-0394Es1c7pLWE27UOvz6X68FuilGQvagJGbS709lOW-qurdf_EBk5VHEg</recordid><startdate>20190529</startdate><enddate>20190529</enddate><creator>Jonathan Langridge</creator><creator>Julien Szydlowski</creator><creator>Guillaume Bodard</creator><creator>Matthieu Leyko</creator><scope>EVB</scope></search><sort><creationdate>20190529</creationdate><title>Method for defining the shape of a turbomachine convergent-divergent nozzle, and corresponding convergent-divergent nozzle</title><author>Jonathan Langridge ; Julien Szydlowski ; Guillaume Bodard ; Matthieu Leyko</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_GB2500466B3</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng</language><creationdate>2019</creationdate><topic>BLASTING</topic><topic>COMBUSTION ENGINES</topic><topic>HEATING</topic><topic>HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS</topic><topic>JET-PROPULSION PLANTS</topic><topic>LIGHTING</topic><topic>MECHANICAL ENGINEERING</topic><topic>WEAPONS</topic><toplevel>online_resources</toplevel><creatorcontrib>Jonathan Langridge</creatorcontrib><creatorcontrib>Julien Szydlowski</creatorcontrib><creatorcontrib>Guillaume Bodard</creatorcontrib><creatorcontrib>Matthieu Leyko</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>Jonathan Langridge</au><au>Julien Szydlowski</au><au>Guillaume Bodard</au><au>Matthieu Leyko</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>Method for defining the shape of a turbomachine convergent-divergent nozzle, and corresponding convergent-divergent nozzle</title><date>2019-05-29</date><risdate>2019</risdate><abstract>According to the invention, the method for defining the shape of a convergent-divergent nozzle of longitudinal axis L-L comprising a convergent part connected, at a throat, to a divergent part the downstream free end of which comprises scallops delimiting noise-reducing chevrons distributed in the circumferential direction, comprises defining beforehand the divergent part of the nozzle using a divergent first portion, a divergent second portion and a convergent portion, attributing an initial value to dimensional parameters defining the chevrons and the three portions, calculating performance criteria and checking that the calculated performance criteria satisfy predefined performance conditions.</abstract><oa>free_for_read</oa></addata></record>
fulltext fulltext_linktorsrc
identifier
ispartof
issn
language eng
recordid cdi_epo_espacenet_GB2500466B
source esp@cenet
subjects BLASTING
COMBUSTION ENGINES
HEATING
HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
JET-PROPULSION PLANTS
LIGHTING
MECHANICAL ENGINEERING
WEAPONS
title Method for defining the shape of a turbomachine convergent-divergent nozzle, and corresponding convergent-divergent nozzle
url https://sfx.bib-bvb.de/sfx_tum?ctx_ver=Z39.88-2004&ctx_enc=info:ofi/enc:UTF-8&ctx_tim=2025-01-29T13%3A44%3A16IST&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=Jonathan%20Langridge&rft.date=2019-05-29&rft_id=info:doi/&rft_dat=%3Cepo_EVB%3EGB2500466B%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