COMBUSTOR HOT STREAK ALIGNMENT FOR GAS TURBINE ENGINE
A method and apparatus to reduce the average and maximum temperatures to which the nozzles in the hot-section of gas-turbine engine are subjected is described. The method relates to the circumferential alignment of fuel nozzles and downstream turbine nozzles in a gas turbine engine. This situates th...
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 | MUSIOL RICHARD J DUDEBOUT RODOLPHE MORRIS MARK C HOWE WILLIAM J RIAHI ARDESHIR MCKEEVER CRAIG W FREIBERG DOUGLAS P |
| description | A method and apparatus to reduce the average and maximum temperatures to which the nozzles in the hot-section of gas-turbine engine are subjected is described. The method relates to the circumferential alignment of fuel nozzles and downstream turbine nozzles in a gas turbine engine. This situates the hot-streak emerging from each fuel nozzle in between the like-numbered turbine nozzle airfoils. The most severe operating condition for reducing the durability of nozzle airfoils is the one generating hot operating temperature conditions. By identifying the temperature profile passing through downstream nozzle airfoils, airfoils in static stages can be selectively spaced around the circumference of the ring attached to the casing of the gas turbine engine to avoid high temperature exposure to the airfoils. This method and apparatus mitigates the worst oxidation and thermo-mechanical fatigue damage in the airfoils by allowing the hot gas regions to pass through the path in between two adjacent airfoils. |
| format | Patent |
| fullrecord | <record><control><sourceid>epo_EVB</sourceid><recordid>TN_cdi_epo_espacenet_US2003002975A1</recordid><sourceformat>XML</sourceformat><sourcesystem>PC</sourcesystem><sourcerecordid>US2003002975A1</sourcerecordid><originalsourceid>FETCH-epo_espacenet_US2003002975A13</originalsourceid><addsrcrecordid>eNrjZDB19vd1Cg0O8Q9S8PAPUQgOCXJ19FZw9PF09_N19QtRcANKuDsGK4SEBjl5-rkquPq5AykeBta0xJziVF4ozc2g7OYa4uyhm1qQH59aXJCYnJqXWhIfGmxkYGBsYGBkaW7qaGhMnCoAjs8oiw</addsrcrecordid><sourcetype>Open Access Repository</sourcetype><iscdi>true</iscdi><recordtype>patent</recordtype></control><display><type>patent</type><title>COMBUSTOR HOT STREAK ALIGNMENT FOR GAS TURBINE ENGINE</title><source>esp@cenet</source><creator>MUSIOL RICHARD J ; DUDEBOUT RODOLPHE ; MORRIS MARK C ; HOWE WILLIAM J ; RIAHI ARDESHIR ; MCKEEVER CRAIG W ; FREIBERG DOUGLAS P</creator><creatorcontrib>MUSIOL RICHARD J ; DUDEBOUT RODOLPHE ; MORRIS MARK C ; HOWE WILLIAM J ; RIAHI ARDESHIR ; MCKEEVER CRAIG W ; FREIBERG DOUGLAS P</creatorcontrib><description>A method and apparatus to reduce the average and maximum temperatures to which the nozzles in the hot-section of gas-turbine engine are subjected is described. The method relates to the circumferential alignment of fuel nozzles and downstream turbine nozzles in a gas turbine engine. This situates the hot-streak emerging from each fuel nozzle in between the like-numbered turbine nozzle airfoils. The most severe operating condition for reducing the durability of nozzle airfoils is the one generating hot operating temperature conditions. By identifying the temperature profile passing through downstream nozzle airfoils, airfoils in static stages can be selectively spaced around the circumference of the ring attached to the casing of the gas turbine engine to avoid high temperature exposure to the airfoils. This method and apparatus mitigates the worst oxidation and thermo-mechanical fatigue damage in the airfoils by allowing the hot gas regions to pass through the path in between two adjacent airfoils.</description><edition>7</edition><language>eng</language><subject>BLASTING ; CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TOTRANSPORTATION ; ENGINE PLANTS IN GENERAL ; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC ; GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS ; HEATING ; LIGHTING ; MACHINES OR ENGINES IN GENERAL ; MECHANICAL ENGINEERING ; NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES ; STEAM ENGINES ; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS ; TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINSTCLIMATE CHANGE ; WEAPONS</subject><creationdate>2003</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=20030102&DB=EPODOC&CC=US&NR=2003002975A1$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,776,881,25542,76289</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20030102&DB=EPODOC&CC=US&NR=2003002975A1$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>MUSIOL RICHARD J</creatorcontrib><creatorcontrib>DUDEBOUT RODOLPHE</creatorcontrib><creatorcontrib>MORRIS MARK C</creatorcontrib><creatorcontrib>HOWE WILLIAM J</creatorcontrib><creatorcontrib>RIAHI ARDESHIR</creatorcontrib><creatorcontrib>MCKEEVER CRAIG W</creatorcontrib><creatorcontrib>FREIBERG DOUGLAS P</creatorcontrib><title>COMBUSTOR HOT STREAK ALIGNMENT FOR GAS TURBINE ENGINE</title><description>A method and apparatus to reduce the average and maximum temperatures to which the nozzles in the hot-section of gas-turbine engine are subjected is described. The method relates to the circumferential alignment of fuel nozzles and downstream turbine nozzles in a gas turbine engine. This situates the hot-streak emerging from each fuel nozzle in between the like-numbered turbine nozzle airfoils. The most severe operating condition for reducing the durability of nozzle airfoils is the one generating hot operating temperature conditions. By identifying the temperature profile passing through downstream nozzle airfoils, airfoils in static stages can be selectively spaced around the circumference of the ring attached to the casing of the gas turbine engine to avoid high temperature exposure to the airfoils. This method and apparatus mitigates the worst oxidation and thermo-mechanical fatigue damage in the airfoils by allowing the hot gas regions to pass through the path in between two adjacent airfoils.</description><subject>BLASTING</subject><subject>CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TOTRANSPORTATION</subject><subject>ENGINE PLANTS IN GENERAL</subject><subject>GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC</subject><subject>GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS</subject><subject>HEATING</subject><subject>LIGHTING</subject><subject>MACHINES OR ENGINES IN GENERAL</subject><subject>MECHANICAL ENGINEERING</subject><subject>NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES</subject><subject>STEAM ENGINES</subject><subject>TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS</subject><subject>TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINSTCLIMATE CHANGE</subject><subject>WEAPONS</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2003</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZDB19vd1Cg0O8Q9S8PAPUQgOCXJ19FZw9PF09_N19QtRcANKuDsGK4SEBjl5-rkquPq5AykeBta0xJziVF4ozc2g7OYa4uyhm1qQH59aXJCYnJqXWhIfGmxkYGBsYGBkaW7qaGhMnCoAjs8oiw</recordid><startdate>20030102</startdate><enddate>20030102</enddate><creator>MUSIOL RICHARD J</creator><creator>DUDEBOUT RODOLPHE</creator><creator>MORRIS MARK C</creator><creator>HOWE WILLIAM J</creator><creator>RIAHI ARDESHIR</creator><creator>MCKEEVER CRAIG W</creator><creator>FREIBERG DOUGLAS P</creator><scope>EVB</scope></search><sort><creationdate>20030102</creationdate><title>COMBUSTOR HOT STREAK ALIGNMENT FOR GAS TURBINE ENGINE</title><author>MUSIOL RICHARD J ; DUDEBOUT RODOLPHE ; MORRIS MARK C ; HOWE WILLIAM J ; RIAHI ARDESHIR ; MCKEEVER CRAIG W ; FREIBERG DOUGLAS P</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_US2003002975A13</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng</language><creationdate>2003</creationdate><topic>BLASTING</topic><topic>CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TOTRANSPORTATION</topic><topic>ENGINE PLANTS IN GENERAL</topic><topic>GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC</topic><topic>GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS</topic><topic>HEATING</topic><topic>LIGHTING</topic><topic>MACHINES OR ENGINES IN GENERAL</topic><topic>MECHANICAL ENGINEERING</topic><topic>NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES</topic><topic>STEAM ENGINES</topic><topic>TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS</topic><topic>TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINSTCLIMATE CHANGE</topic><topic>WEAPONS</topic><toplevel>online_resources</toplevel><creatorcontrib>MUSIOL RICHARD J</creatorcontrib><creatorcontrib>DUDEBOUT RODOLPHE</creatorcontrib><creatorcontrib>MORRIS MARK C</creatorcontrib><creatorcontrib>HOWE WILLIAM J</creatorcontrib><creatorcontrib>RIAHI ARDESHIR</creatorcontrib><creatorcontrib>MCKEEVER CRAIG W</creatorcontrib><creatorcontrib>FREIBERG DOUGLAS P</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>MUSIOL RICHARD J</au><au>DUDEBOUT RODOLPHE</au><au>MORRIS MARK C</au><au>HOWE WILLIAM J</au><au>RIAHI ARDESHIR</au><au>MCKEEVER CRAIG W</au><au>FREIBERG DOUGLAS P</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>COMBUSTOR HOT STREAK ALIGNMENT FOR GAS TURBINE ENGINE</title><date>2003-01-02</date><risdate>2003</risdate><abstract>A method and apparatus to reduce the average and maximum temperatures to which the nozzles in the hot-section of gas-turbine engine are subjected is described. The method relates to the circumferential alignment of fuel nozzles and downstream turbine nozzles in a gas turbine engine. This situates the hot-streak emerging from each fuel nozzle in between the like-numbered turbine nozzle airfoils. The most severe operating condition for reducing the durability of nozzle airfoils is the one generating hot operating temperature conditions. By identifying the temperature profile passing through downstream nozzle airfoils, airfoils in static stages can be selectively spaced around the circumference of the ring attached to the casing of the gas turbine engine to avoid high temperature exposure to the airfoils. This method and apparatus mitigates the worst oxidation and thermo-mechanical fatigue damage in the airfoils by allowing the hot gas regions to pass through the path in between two adjacent airfoils.</abstract><edition>7</edition><oa>free_for_read</oa></addata></record> |
| fulltext | fulltext_linktorsrc |
| identifier | |
| ispartof | |
| issn | |
| language | eng |
| recordid | cdi_epo_espacenet_US2003002975A1 |
| source | esp@cenet |
| subjects | BLASTING CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TOTRANSPORTATION ENGINE PLANTS IN GENERAL GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS HEATING LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINSTCLIMATE CHANGE WEAPONS |
| title | COMBUSTOR HOT STREAK ALIGNMENT FOR GAS TURBINE ENGINE |
| url | https://sfx.bib-bvb.de/sfx_tum?ctx_ver=Z39.88-2004&ctx_enc=info:ofi/enc:UTF-8&ctx_tim=2025-02-08T17%3A43%3A38IST&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=MUSIOL%20RICHARD%20J&rft.date=2003-01-02&rft_id=info:doi/&rft_dat=%3Cepo_EVB%3EUS2003002975A1%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 |