METHOD FOR ASSISTING A TURBOSHAFT ENGINE IN STANDBY OF A MULTI-ENGINE HELICOPTER AND ARCHITECTURE OF A PROPULSION SYSTEM OF A HELICOPTER COMPRISING AT LEAST ONE TURBOSHAFT ENGINE THAT CAN BE IN STANDBY

METHOD FOR ASSISTING A TURBOSHAFT ENGINE IN STANDBY OF A MULTI-ENGINE HELICOPTER AND ARCHITECTURE OF A PROPULSION SYSTEM OF A HELICOPTER COMPRISING AT LEAST ONE TURBOSHAFT ENGINE THAT CAN BE IN STANDBY

The invention relates to an architecture of a propulsion system of a multiple-engine helicopter comprising turboshaft engines (5, 6), characterised in that it comprises: at least one hybrid turboshaft engine (5) that is capable of operating in at least one standby mode during a stable flight of the...

Ausführliche Beschreibung

Gespeichert in:
Bibliographische Detailangaben
Hauptverfasser: DESCUBES, OLIVIER PIERRE, BEDRINE, OLIVIER
Format: Patent
Sprache:eng ; pol
Schlagworte:
AIR INTAKES FOR JET-PROPULSION PLANTS
BLASTING
COMBUSTION ENGINES
CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
GAS-TURBINE PLANTS
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 DESCUBES, OLIVIER PIERRE
BEDRINE, OLIVIER
description The invention relates to an architecture of a propulsion system of a multiple-engine helicopter comprising turboshaft engines (5, 6), characterised in that it comprises: at least one hybrid turboshaft engine (5) that is capable of operating in at least one standby mode during a stable flight of the helicopter, the other turboshaft engines (6) operating alone during this stable flight; an air turbine (30) that is mechanically connected to the gas generator (17) of the hybrid turboshaft engine (5) and is suitable for rotating said gas generator (17); means for withdrawing pressurised air from the gas generator (27) of a running turboshaft engine (6); and a duct (31) for routing this withdrawn air to said air turbine (30).
format Patent
fullrecord <record><control><sourceid>epo_EVB</sourceid><recordid>TN_cdi_epo_espacenet_PL3123012TT3</recordid><sourceformat>XML</sourceformat><sourcesystem>PC</sourcesystem><sourcerecordid>PL3123012TT3</sourcerecordid><originalsourceid>FETCH-epo_espacenet_PL3123012TT33</originalsourceid><addsrcrecordid>eNqNjkEKAjEMRWfjQtQ7xAMI6pyg08nYQKcpTWbhSkTqSlTQS3ori7oQ3LgKJO-__HH16FEdt9BxAiNCohQ2YECH1LA40ylg2FBAoACiJrTNFrgrRD94pcXn6NCT5ahYLKEFk6wjRVss-KZj4jh4IS6WrSj27_VXznIfE8nrvYJHIwpc1L9N1BXAmgDNd6tpNTruT7c8-8xJNe9QrVvk62WXb9f9IZ_zfRd9vVrXy9Vata7_YZ4VnE_x</addsrcrecordid><sourcetype>Open Access Repository</sourcetype><iscdi>true</iscdi><recordtype>patent</recordtype></control><display><type>patent</type><title>METHOD FOR ASSISTING A TURBOSHAFT ENGINE IN STANDBY OF A MULTI-ENGINE HELICOPTER AND ARCHITECTURE OF A PROPULSION SYSTEM OF A HELICOPTER COMPRISING AT LEAST ONE TURBOSHAFT ENGINE THAT CAN BE IN STANDBY</title><source>esp@cenet</source><creator>DESCUBES, OLIVIER PIERRE ; BEDRINE, OLIVIER</creator><creatorcontrib>DESCUBES, OLIVIER PIERRE ; BEDRINE, OLIVIER</creatorcontrib><description>The invention relates to an architecture of a propulsion system of a multiple-engine helicopter comprising turboshaft engines (5, 6), characterised in that it comprises: at least one hybrid turboshaft engine (5) that is capable of operating in at least one standby mode during a stable flight of the helicopter, the other turboshaft engines (6) operating alone during this stable flight; an air turbine (30) that is mechanically connected to the gas generator (17) of the hybrid turboshaft engine (5) and is suitable for rotating said gas generator (17); means for withdrawing pressurised air from the gas generator (27) of a running turboshaft engine (6); and a duct (31) for routing this withdrawn air to said air turbine (30).</description><language>eng ; pol</language><subject>AIR INTAKES FOR JET-PROPULSION PLANTS ; BLASTING ; COMBUSTION ENGINES ; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ; GAS-TURBINE PLANTS ; HEATING ; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS ; LIGHTING ; MECHANICAL ENGINEERING ; WEAPONS</subject><creationdate>2020</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=20200727&amp;DB=EPODOC&amp;CC=PL&amp;NR=3123012T3$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,780,885,25564,76547</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&amp;date=20200727&amp;DB=EPODOC&amp;CC=PL&amp;NR=3123012T3$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>DESCUBES, OLIVIER PIERRE</creatorcontrib><creatorcontrib>BEDRINE, OLIVIER</creatorcontrib><title>METHOD FOR ASSISTING A TURBOSHAFT ENGINE IN STANDBY OF A MULTI-ENGINE HELICOPTER AND ARCHITECTURE OF A PROPULSION SYSTEM OF A HELICOPTER COMPRISING AT LEAST ONE TURBOSHAFT ENGINE THAT CAN BE IN STANDBY</title><description>The invention relates to an architecture of a propulsion system of a multiple-engine helicopter comprising turboshaft engines (5, 6), characterised in that it comprises: at least one hybrid turboshaft engine (5) that is capable of operating in at least one standby mode during a stable flight of the helicopter, the other turboshaft engines (6) operating alone during this stable flight; an air turbine (30) that is mechanically connected to the gas generator (17) of the hybrid turboshaft engine (5) and is suitable for rotating said gas generator (17); means for withdrawing pressurised air from the gas generator (27) of a running turboshaft engine (6); and a duct (31) for routing this withdrawn air to said air turbine (30).</description><subject>AIR INTAKES FOR JET-PROPULSION PLANTS</subject><subject>BLASTING</subject><subject>COMBUSTION ENGINES</subject><subject>CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS</subject><subject>GAS-TURBINE PLANTS</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>2020</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNqNjkEKAjEMRWfjQtQ7xAMI6pyg08nYQKcpTWbhSkTqSlTQS3ori7oQ3LgKJO-__HH16FEdt9BxAiNCohQ2YECH1LA40ylg2FBAoACiJrTNFrgrRD94pcXn6NCT5ahYLKEFk6wjRVss-KZj4jh4IS6WrSj27_VXznIfE8nrvYJHIwpc1L9N1BXAmgDNd6tpNTruT7c8-8xJNe9QrVvk62WXb9f9IZ_zfRd9vVrXy9Vata7_YZ4VnE_x</recordid><startdate>20200727</startdate><enddate>20200727</enddate><creator>DESCUBES, OLIVIER PIERRE</creator><creator>BEDRINE, OLIVIER</creator><scope>EVB</scope></search><sort><creationdate>20200727</creationdate><title>METHOD FOR ASSISTING A TURBOSHAFT ENGINE IN STANDBY OF A MULTI-ENGINE HELICOPTER AND ARCHITECTURE OF A PROPULSION SYSTEM OF A HELICOPTER COMPRISING AT LEAST ONE TURBOSHAFT ENGINE THAT CAN BE IN STANDBY</title><author>DESCUBES, OLIVIER PIERRE ; BEDRINE, OLIVIER</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_PL3123012TT33</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng ; pol</language><creationdate>2020</creationdate><topic>AIR INTAKES FOR JET-PROPULSION PLANTS</topic><topic>BLASTING</topic><topic>COMBUSTION ENGINES</topic><topic>CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS</topic><topic>GAS-TURBINE PLANTS</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>DESCUBES, OLIVIER PIERRE</creatorcontrib><creatorcontrib>BEDRINE, OLIVIER</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>DESCUBES, OLIVIER PIERRE</au><au>BEDRINE, OLIVIER</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>METHOD FOR ASSISTING A TURBOSHAFT ENGINE IN STANDBY OF A MULTI-ENGINE HELICOPTER AND ARCHITECTURE OF A PROPULSION SYSTEM OF A HELICOPTER COMPRISING AT LEAST ONE TURBOSHAFT ENGINE THAT CAN BE IN STANDBY</title><date>2020-07-27</date><risdate>2020</risdate><abstract>The invention relates to an architecture of a propulsion system of a multiple-engine helicopter comprising turboshaft engines (5, 6), characterised in that it comprises: at least one hybrid turboshaft engine (5) that is capable of operating in at least one standby mode during a stable flight of the helicopter, the other turboshaft engines (6) operating alone during this stable flight; an air turbine (30) that is mechanically connected to the gas generator (17) of the hybrid turboshaft engine (5) and is suitable for rotating said gas generator (17); means for withdrawing pressurised air from the gas generator (27) of a running turboshaft engine (6); and a duct (31) for routing this withdrawn air to said air turbine (30).</abstract><oa>free_for_read</oa></addata></record>
fulltext fulltext_linktorsrc
identifier
ispartof
issn
language eng ; pol
recordid cdi_epo_espacenet_PL3123012TT3
source esp@cenet
subjects AIR INTAKES FOR JET-PROPULSION PLANTS
BLASTING
COMBUSTION ENGINES
CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
GAS-TURBINE PLANTS
HEATING
HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
LIGHTING
MECHANICAL ENGINEERING
WEAPONS
title METHOD FOR ASSISTING A TURBOSHAFT ENGINE IN STANDBY OF A MULTI-ENGINE HELICOPTER AND ARCHITECTURE OF A PROPULSION SYSTEM OF A HELICOPTER COMPRISING AT LEAST ONE TURBOSHAFT ENGINE THAT CAN BE IN STANDBY
url https://sfx.bib-bvb.de/sfx_tum?ctx_ver=Z39.88-2004&ctx_enc=info:ofi/enc:UTF-8&ctx_tim=2025-01-02T18%3A56%3A21IST&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=DESCUBES,%20OLIVIER%20PIERRE&rft.date=2020-07-27&rft_id=info:doi/&rft_dat=%3Cepo_EVB%3EPL3123012TT3%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