Combustion device of a gas turbine including a plurality of passages and chambers defining helmholtz resonators
A combustion device for a gas turbine that includes a portion having first and second walls that defines an inside of the combustion device, a zone between the first and second walls and an outside of the combustion device. A plurality of first passages connect the inside of the combustion device to...
Gespeichert in:
| Hauptverfasser: | , , , , |
|---|---|
| Format: | Patent |
| Sprache: | eng |
| Schlagworte: | |
| 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 | REINERT FELIX SCHUERMANS BRUNO LAUFFER DIANE SCHNELL ALEXANDER NOIRAY NICOLAS |
| description | A combustion device for a gas turbine that includes a portion having first and second walls that defines an inside of the combustion device, a zone between the first and second walls and an outside of the combustion device. A plurality of first passages connect the inside of the combustion device to the zone between the first and second walls and a plurality of second passages connect the zone between the first and second walls to the outside of the combustion device. A plurality of chambers are defined within the zone between the first and second walls, each chamber being connected with one first passage and at least one second passage. Each chamber defining a Helmholtz damper. |
| format | Patent |
| fullrecord | <record><control><sourceid>epo_EVB</sourceid><recordid>TN_cdi_epo_espacenet_US8839624B2</recordid><sourceformat>XML</sourceformat><sourcesystem>PC</sourcesystem><sourcerecordid>US8839624B2</sourcerecordid><originalsourceid>FETCH-epo_espacenet_US8839624B23</originalsourceid><addsrcrecordid>eNqNzEEKwjAQheFuXIh6h7mAm1akbi2Ke3Vdpum0DSQzIZMIenpb8ACuHvx8vHUhjfgua7LC0NPLGgIZAGFEhZRjZ5nAsnG5tzzOPbgc0dn0XlhAVRxJAbkHM6HvKOp8M1he9ETOT-LSByKpMCaJui1WAzql3W83BVwvj-a2pyAtaUBDTKl93uu6Oh3Lw7ms_iBfmnJDKA</addsrcrecordid><sourcetype>Open Access Repository</sourcetype><iscdi>true</iscdi><recordtype>patent</recordtype></control><display><type>patent</type><title>Combustion device of a gas turbine including a plurality of passages and chambers defining helmholtz resonators</title><source>esp@cenet</source><creator>REINERT FELIX ; SCHUERMANS BRUNO ; LAUFFER DIANE ; SCHNELL ALEXANDER ; NOIRAY NICOLAS</creator><creatorcontrib>REINERT FELIX ; SCHUERMANS BRUNO ; LAUFFER DIANE ; SCHNELL ALEXANDER ; NOIRAY NICOLAS</creatorcontrib><description>A combustion device for a gas turbine that includes a portion having first and second walls that defines an inside of the combustion device, a zone between the first and second walls and an outside of the combustion device. A plurality of first passages connect the inside of the combustion device to the zone between the first and second walls and a plurality of second passages connect the zone between the first and second walls to the outside of the combustion device. A plurality of chambers are defined within the zone between the first and second walls, each chamber being connected with one first passage and at least one second passage. Each chamber defining a Helmholtz damper.</description><language>eng</language><subject>AIR INTAKES FOR JET-PROPULSION PLANTS ; BLASTING ; CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FORCOMBUSTION CHAMBERS, e.g. FIREBRIDGES ; COMBUSTION APPARATUS ; COMBUSTION ENGINES ; COMBUSTION PROCESSES ; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDEDFOR ; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS INCOMBUSTION CHAMBERS ; 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 ; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTIONAPPARATUS ; WEAPONS</subject><creationdate>2014</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=20140923&DB=EPODOC&CC=US&NR=8839624B2$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,780,885,25564,76547</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20140923&DB=EPODOC&CC=US&NR=8839624B2$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>REINERT FELIX</creatorcontrib><creatorcontrib>SCHUERMANS BRUNO</creatorcontrib><creatorcontrib>LAUFFER DIANE</creatorcontrib><creatorcontrib>SCHNELL ALEXANDER</creatorcontrib><creatorcontrib>NOIRAY NICOLAS</creatorcontrib><title>Combustion device of a gas turbine including a plurality of passages and chambers defining helmholtz resonators</title><description>A combustion device for a gas turbine that includes a portion having first and second walls that defines an inside of the combustion device, a zone between the first and second walls and an outside of the combustion device. A plurality of first passages connect the inside of the combustion device to the zone between the first and second walls and a plurality of second passages connect the zone between the first and second walls to the outside of the combustion device. A plurality of chambers are defined within the zone between the first and second walls, each chamber being connected with one first passage and at least one second passage. Each chamber defining a Helmholtz damper.</description><subject>AIR INTAKES FOR JET-PROPULSION PLANTS</subject><subject>BLASTING</subject><subject>CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FORCOMBUSTION CHAMBERS, e.g. FIREBRIDGES</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>DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDEDFOR</subject><subject>DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS INCOMBUSTION CHAMBERS</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>SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTIONAPPARATUS</subject><subject>WEAPONS</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2014</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNqNzEEKwjAQheFuXIh6h7mAm1akbi2Ke3Vdpum0DSQzIZMIenpb8ACuHvx8vHUhjfgua7LC0NPLGgIZAGFEhZRjZ5nAsnG5tzzOPbgc0dn0XlhAVRxJAbkHM6HvKOp8M1he9ETOT-LSByKpMCaJui1WAzql3W83BVwvj-a2pyAtaUBDTKl93uu6Oh3Lw7ms_iBfmnJDKA</recordid><startdate>20140923</startdate><enddate>20140923</enddate><creator>REINERT FELIX</creator><creator>SCHUERMANS BRUNO</creator><creator>LAUFFER DIANE</creator><creator>SCHNELL ALEXANDER</creator><creator>NOIRAY NICOLAS</creator><scope>EVB</scope></search><sort><creationdate>20140923</creationdate><title>Combustion device of a gas turbine including a plurality of passages and chambers defining helmholtz resonators</title><author>REINERT FELIX ; SCHUERMANS BRUNO ; LAUFFER DIANE ; SCHNELL ALEXANDER ; NOIRAY NICOLAS</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_US8839624B23</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng</language><creationdate>2014</creationdate><topic>AIR INTAKES FOR JET-PROPULSION PLANTS</topic><topic>BLASTING</topic><topic>CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FORCOMBUSTION CHAMBERS, e.g. FIREBRIDGES</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>DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDEDFOR</topic><topic>DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS INCOMBUSTION CHAMBERS</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>SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTIONAPPARATUS</topic><topic>WEAPONS</topic><toplevel>online_resources</toplevel><creatorcontrib>REINERT FELIX</creatorcontrib><creatorcontrib>SCHUERMANS BRUNO</creatorcontrib><creatorcontrib>LAUFFER DIANE</creatorcontrib><creatorcontrib>SCHNELL ALEXANDER</creatorcontrib><creatorcontrib>NOIRAY NICOLAS</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>REINERT FELIX</au><au>SCHUERMANS BRUNO</au><au>LAUFFER DIANE</au><au>SCHNELL ALEXANDER</au><au>NOIRAY NICOLAS</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>Combustion device of a gas turbine including a plurality of passages and chambers defining helmholtz resonators</title><date>2014-09-23</date><risdate>2014</risdate><abstract>A combustion device for a gas turbine that includes a portion having first and second walls that defines an inside of the combustion device, a zone between the first and second walls and an outside of the combustion device. A plurality of first passages connect the inside of the combustion device to the zone between the first and second walls and a plurality of second passages connect the zone between the first and second walls to the outside of the combustion device. A plurality of chambers are defined within the zone between the first and second walls, each chamber being connected with one first passage and at least one second passage. Each chamber defining a Helmholtz damper.</abstract><oa>free_for_read</oa></addata></record> |
| fulltext | fulltext_linktorsrc |
| identifier | |
| ispartof | |
| issn | |
| language | eng |
| recordid | cdi_epo_espacenet_US8839624B2 |
| source | esp@cenet |
| subjects | AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FORCOMBUSTION CHAMBERS, e.g. FIREBRIDGES COMBUSTION APPARATUS COMBUSTION ENGINES COMBUSTION PROCESSES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDEDFOR DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS INCOMBUSTION CHAMBERS 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 SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTIONAPPARATUS WEAPONS |
| title | Combustion device of a gas turbine including a plurality of passages and chambers defining helmholtz resonators |
| url | https://sfx.bib-bvb.de/sfx_tum?ctx_ver=Z39.88-2004&ctx_enc=info:ofi/enc:UTF-8&ctx_tim=2024-12-22T12%3A15%3A13IST&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=REINERT%20FELIX&rft.date=2014-09-23&rft_id=info:doi/&rft_dat=%3Cepo_EVB%3EUS8839624B2%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 |