Gas turbine nozzle segment and process therefor

Gas turbine nozzle segment and process therefor

A gas turbine engine nozzle segment and process for producing such a nozzle segment to exhibit improved durability and aerodynamic performance. The process produces a nozzle segment having at least one vane between and interconnecting a pair of platforms. The nozzle segment is cast from a gamma prim...

Ausführliche Beschreibung

Gespeichert in:
Bibliographische Detailangaben
Hauptverfasser: Farmer, Andrew David, Nagaraj, Bangalore Aswatha, Lu, Wenfeng, Lee, Ching-Pang, Guentert, Joseph Michael
Format: Patent
Sprache:eng
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 Farmer, Andrew David
Nagaraj, Bangalore Aswatha
Lu, Wenfeng
Lee, Ching-Pang
Guentert, Joseph Michael
description A gas turbine engine nozzle segment and process for producing such a nozzle segment to exhibit improved durability and aerodynamic performance. The process produces a nozzle segment having at least one vane between and interconnecting a pair of platforms. The nozzle segment is cast from a gamma prime-strengthened nickel-base superalloy, on whose surface is thermal sprayed an environmental coating formed of a MCrAlX-type coating material. The surface of the environmental coating is then worked to cause the coating to have a surface finish of less than 2.0 micrometers Ra. Cooling holes are then drilled in the nozzle segment, after which an oxidation-resistant coating is applied on the smoothed surface of the nozzle segment so as to maintain an outermost surface on the nozzle segment having surface finish of less than 2.0 micrometers Ra.
format Patent
fullrecord <record><control><sourceid>uspatents_EFH</sourceid><recordid>TN_cdi_uspatents_grants_07341427</recordid><sourceformat>XML</sourceformat><sourcesystem>PC</sourcesystem><sourcerecordid>07341427</sourcerecordid><originalsourceid>FETCH-uspatents_grants_073414273</originalsourceid><addsrcrecordid>eNrjZNB3TyxWKCktSsrMS1XIy6-qyklVKE5Nz03NK1FIzEtRKCjKT04tBirJSC1KTcsv4mFgTUvMKU7lhdLcDApuriHOHrqlxQWJJUBdxfHpRYkgysDc2MTQxMjcmAglABDVK_Y</addsrcrecordid><sourcetype>Open Access Repository</sourcetype><iscdi>true</iscdi><recordtype>patent</recordtype></control><display><type>patent</type><title>Gas turbine nozzle segment and process therefor</title><source>USPTO Issued Patents</source><creator>Farmer, Andrew David ; Nagaraj, Bangalore Aswatha ; Lu, Wenfeng ; Lee, Ching-Pang ; Guentert, Joseph Michael</creator><creatorcontrib>Farmer, Andrew David ; Nagaraj, Bangalore Aswatha ; Lu, Wenfeng ; Lee, Ching-Pang ; Guentert, Joseph Michael ; General Electric Company</creatorcontrib><description>A gas turbine engine nozzle segment and process for producing such a nozzle segment to exhibit improved durability and aerodynamic performance. The process produces a nozzle segment having at least one vane between and interconnecting a pair of platforms. The nozzle segment is cast from a gamma prime-strengthened nickel-base superalloy, on whose surface is thermal sprayed an environmental coating formed of a MCrAlX-type coating material. The surface of the environmental coating is then worked to cause the coating to have a surface finish of less than 2.0 micrometers Ra. Cooling holes are then drilled in the nozzle segment, after which an oxidation-resistant coating is applied on the smoothed surface of the nozzle segment so as to maintain an outermost surface on the nozzle segment having surface finish of less than 2.0 micrometers Ra.</description><language>eng</language><creationdate>2008</creationdate><oa>free_for_read</oa><woscitedreferencessubscribed>false</woscitedreferencessubscribed></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><linktopdf>$$Uhttps://image-ppubs.uspto.gov/dirsearch-public/print/downloadPdf/7341427$$EPDF$$P50$$Guspatents$$Hfree_for_read</linktopdf><link.rule.ids>230,308,780,802,885,64038</link.rule.ids><linktorsrc>$$Uhttps://image-ppubs.uspto.gov/dirsearch-public/print/downloadPdf/7341427$$EView_record_in_USPTO$$FView_record_in_$$GUSPTO$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>Farmer, Andrew David</creatorcontrib><creatorcontrib>Nagaraj, Bangalore Aswatha</creatorcontrib><creatorcontrib>Lu, Wenfeng</creatorcontrib><creatorcontrib>Lee, Ching-Pang</creatorcontrib><creatorcontrib>Guentert, Joseph Michael</creatorcontrib><creatorcontrib>General Electric Company</creatorcontrib><title>Gas turbine nozzle segment and process therefor</title><description>A gas turbine engine nozzle segment and process for producing such a nozzle segment to exhibit improved durability and aerodynamic performance. The process produces a nozzle segment having at least one vane between and interconnecting a pair of platforms. The nozzle segment is cast from a gamma prime-strengthened nickel-base superalloy, on whose surface is thermal sprayed an environmental coating formed of a MCrAlX-type coating material. The surface of the environmental coating is then worked to cause the coating to have a surface finish of less than 2.0 micrometers Ra. Cooling holes are then drilled in the nozzle segment, after which an oxidation-resistant coating is applied on the smoothed surface of the nozzle segment so as to maintain an outermost surface on the nozzle segment having surface finish of less than 2.0 micrometers Ra.</description><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2008</creationdate><recordtype>patent</recordtype><sourceid>EFH</sourceid><recordid>eNrjZNB3TyxWKCktSsrMS1XIy6-qyklVKE5Nz03NK1FIzEtRKCjKT04tBirJSC1KTcsv4mFgTUvMKU7lhdLcDApuriHOHrqlxQWJJUBdxfHpRYkgysDc2MTQxMjcmAglABDVK_Y</recordid><startdate>20080311</startdate><enddate>20080311</enddate><creator>Farmer, Andrew David</creator><creator>Nagaraj, Bangalore Aswatha</creator><creator>Lu, Wenfeng</creator><creator>Lee, Ching-Pang</creator><creator>Guentert, Joseph Michael</creator><scope>EFH</scope></search><sort><creationdate>20080311</creationdate><title>Gas turbine nozzle segment and process therefor</title><author>Farmer, Andrew David ; Nagaraj, Bangalore Aswatha ; Lu, Wenfeng ; Lee, Ching-Pang ; Guentert, Joseph Michael</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-uspatents_grants_073414273</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng</language><creationdate>2008</creationdate><toplevel>online_resources</toplevel><creatorcontrib>Farmer, Andrew David</creatorcontrib><creatorcontrib>Nagaraj, Bangalore Aswatha</creatorcontrib><creatorcontrib>Lu, Wenfeng</creatorcontrib><creatorcontrib>Lee, Ching-Pang</creatorcontrib><creatorcontrib>Guentert, Joseph Michael</creatorcontrib><creatorcontrib>General Electric Company</creatorcontrib><collection>USPTO Issued Patents</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>Farmer, Andrew David</au><au>Nagaraj, Bangalore Aswatha</au><au>Lu, Wenfeng</au><au>Lee, Ching-Pang</au><au>Guentert, Joseph Michael</au><aucorp>General Electric Company</aucorp><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>Gas turbine nozzle segment and process therefor</title><date>2008-03-11</date><risdate>2008</risdate><abstract>A gas turbine engine nozzle segment and process for producing such a nozzle segment to exhibit improved durability and aerodynamic performance. The process produces a nozzle segment having at least one vane between and interconnecting a pair of platforms. The nozzle segment is cast from a gamma prime-strengthened nickel-base superalloy, on whose surface is thermal sprayed an environmental coating formed of a MCrAlX-type coating material. The surface of the environmental coating is then worked to cause the coating to have a surface finish of less than 2.0 micrometers Ra. Cooling holes are then drilled in the nozzle segment, after which an oxidation-resistant coating is applied on the smoothed surface of the nozzle segment so as to maintain an outermost surface on the nozzle segment having surface finish of less than 2.0 micrometers Ra.</abstract><oa>free_for_read</oa></addata></record>
fulltext fulltext_linktorsrc
identifier
ispartof
issn
language eng
recordid cdi_uspatents_grants_07341427
source USPTO Issued Patents
title Gas turbine nozzle segment and process therefor
url https://sfx.bib-bvb.de/sfx_tum?ctx_ver=Z39.88-2004&ctx_enc=info:ofi/enc:UTF-8&ctx_tim=2025-01-10T11%3A15%3A56IST&url_ver=Z39.88-2004&url_ctx_fmt=infofi/fmt:kev:mtx:ctx&rfr_id=info:sid/primo.exlibrisgroup.com:primo3-Article-uspatents_EFH&rft_val_fmt=info:ofi/fmt:kev:mtx:patent&rft.genre=patent&rft.au=Farmer,%20Andrew%20David&rft.aucorp=General%20Electric%20Company&rft.date=2008-03-11&rft_id=info:doi/&rft_dat=%3Cuspatents_EFH%3E07341427%3C/uspatents_EFH%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