Method of fabricating a rocket engine nozzle using pressure brazing
A method of fabrication of a rocket engine nozzle assembly using pressure brazing generally includes initially assembling a rocket engine nozzle liner into a rocket engine nozzle jacket for a rocket engine nozzle assembly. The rocket engine nozzle assembly may then be sealed. Prior to pressure brazi...
Gespeichert in:
| Hauptverfasser: | , , , , , , , |
|---|---|
| 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 | Fint, Jeffry A Hankins, Michael B Jew, Myron L Ulmer, Donald G Wherley, Brian L Romine, William D Kuck, Frederick M Ades, Douglas S |
| description | A method of fabrication of a rocket engine nozzle assembly using pressure brazing generally includes initially assembling a rocket engine nozzle liner into a rocket engine nozzle jacket for a rocket engine nozzle assembly. The rocket engine nozzle assembly may then be sealed. Prior to pressure brazing the rocket engine nozzle assembly, pressure brazing parameters may be determined. The pressure brazing may be performed with the determined pressure brazing parameters to complete the fabrication of the rocket engine nozzle. The rocket engine nozzle assembly may include a rocket engine nozzle jacket and a rocket engine nozzle liner having a plurality of channels, with the space between each channel defining a land, and the rocket engine nozzle liner having at least a pair of endlands disposed at each end thereof. The rocket engine nozzle liner is bonded to the rocket engine nozzle jacket by the endlands being bonded to the nozzle jacket and the lands being pressure brazed to the nozzle jacket. |
| format | Patent |
| fullrecord | <record><control><sourceid>uspatents_EFH</sourceid><recordid>TN_cdi_uspatents_grants_08127443</recordid><sourceformat>XML</sourceformat><sourcesystem>PC</sourcesystem><sourcerecordid>08127443</sourcerecordid><originalsourceid>FETCH-uspatents_grants_081274433</originalsourceid><addsrcrecordid>eNrjZHD2TS3JyE9RyE9TSEtMKspMTizJzEtXSFQoyk_OTi1RSM1Lz8xLVcjLr6rKSVUoLQZJFhSlFheXFqUqJBUlVgEFeBhY0xJzilN5oTQ3g4Kba4izh25pcUFiSWpeSXF8elEiiDKwMDQyNzExNiZCCQBBSDNv</addsrcrecordid><sourcetype>Open Access Repository</sourcetype><iscdi>true</iscdi><recordtype>patent</recordtype></control><display><type>patent</type><title>Method of fabricating a rocket engine nozzle using pressure brazing</title><source>USPTO Issued Patents</source><creator>Fint, Jeffry A ; Hankins, Michael B ; Jew, Myron L ; Ulmer, Donald G ; Wherley, Brian L ; Romine, William D ; Kuck, Frederick M ; Ades, Douglas S</creator><creatorcontrib>Fint, Jeffry A ; Hankins, Michael B ; Jew, Myron L ; Ulmer, Donald G ; Wherley, Brian L ; Romine, William D ; Kuck, Frederick M ; Ades, Douglas S ; United Technologies Corporation</creatorcontrib><description>A method of fabrication of a rocket engine nozzle assembly using pressure brazing generally includes initially assembling a rocket engine nozzle liner into a rocket engine nozzle jacket for a rocket engine nozzle assembly. The rocket engine nozzle assembly may then be sealed. Prior to pressure brazing the rocket engine nozzle assembly, pressure brazing parameters may be determined. The pressure brazing may be performed with the determined pressure brazing parameters to complete the fabrication of the rocket engine nozzle. The rocket engine nozzle assembly may include a rocket engine nozzle jacket and a rocket engine nozzle liner having a plurality of channels, with the space between each channel defining a land, and the rocket engine nozzle liner having at least a pair of endlands disposed at each end thereof. The rocket engine nozzle liner is bonded to the rocket engine nozzle jacket by the endlands being bonded to the nozzle jacket and the lands being pressure brazed to the nozzle jacket.</description><language>eng</language><creationdate>2012</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/8127443$$EPDF$$P50$$Guspatents$$Hfree_for_read</linktopdf><link.rule.ids>230,308,776,798,881,64016</link.rule.ids><linktorsrc>$$Uhttps://image-ppubs.uspto.gov/dirsearch-public/print/downloadPdf/8127443$$EView_record_in_USPTO$$FView_record_in_$$GUSPTO$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>Fint, Jeffry A</creatorcontrib><creatorcontrib>Hankins, Michael B</creatorcontrib><creatorcontrib>Jew, Myron L</creatorcontrib><creatorcontrib>Ulmer, Donald G</creatorcontrib><creatorcontrib>Wherley, Brian L</creatorcontrib><creatorcontrib>Romine, William D</creatorcontrib><creatorcontrib>Kuck, Frederick M</creatorcontrib><creatorcontrib>Ades, Douglas S</creatorcontrib><creatorcontrib>United Technologies Corporation</creatorcontrib><title>Method of fabricating a rocket engine nozzle using pressure brazing</title><description>A method of fabrication of a rocket engine nozzle assembly using pressure brazing generally includes initially assembling a rocket engine nozzle liner into a rocket engine nozzle jacket for a rocket engine nozzle assembly. The rocket engine nozzle assembly may then be sealed. Prior to pressure brazing the rocket engine nozzle assembly, pressure brazing parameters may be determined. The pressure brazing may be performed with the determined pressure brazing parameters to complete the fabrication of the rocket engine nozzle. The rocket engine nozzle assembly may include a rocket engine nozzle jacket and a rocket engine nozzle liner having a plurality of channels, with the space between each channel defining a land, and the rocket engine nozzle liner having at least a pair of endlands disposed at each end thereof. The rocket engine nozzle liner is bonded to the rocket engine nozzle jacket by the endlands being bonded to the nozzle jacket and the lands being pressure brazed to the nozzle jacket.</description><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2012</creationdate><recordtype>patent</recordtype><sourceid>EFH</sourceid><recordid>eNrjZHD2TS3JyE9RyE9TSEtMKspMTizJzEtXSFQoyk_OTi1RSM1Lz8xLVcjLr6rKSVUoLQZJFhSlFheXFqUqJBUlVgEFeBhY0xJzilN5oTQ3g4Kba4izh25pcUFiSWpeSXF8elEiiDKwMDQyNzExNiZCCQBBSDNv</recordid><startdate>20120306</startdate><enddate>20120306</enddate><creator>Fint, Jeffry A</creator><creator>Hankins, Michael B</creator><creator>Jew, Myron L</creator><creator>Ulmer, Donald G</creator><creator>Wherley, Brian L</creator><creator>Romine, William D</creator><creator>Kuck, Frederick M</creator><creator>Ades, Douglas S</creator><scope>EFH</scope></search><sort><creationdate>20120306</creationdate><title>Method of fabricating a rocket engine nozzle using pressure brazing</title><author>Fint, Jeffry A ; Hankins, Michael B ; Jew, Myron L ; Ulmer, Donald G ; Wherley, Brian L ; Romine, William D ; Kuck, Frederick M ; Ades, Douglas S</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-uspatents_grants_081274433</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng</language><creationdate>2012</creationdate><toplevel>online_resources</toplevel><creatorcontrib>Fint, Jeffry A</creatorcontrib><creatorcontrib>Hankins, Michael B</creatorcontrib><creatorcontrib>Jew, Myron L</creatorcontrib><creatorcontrib>Ulmer, Donald G</creatorcontrib><creatorcontrib>Wherley, Brian L</creatorcontrib><creatorcontrib>Romine, William D</creatorcontrib><creatorcontrib>Kuck, Frederick M</creatorcontrib><creatorcontrib>Ades, Douglas S</creatorcontrib><creatorcontrib>United Technologies Corporation</creatorcontrib><collection>USPTO Issued Patents</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>Fint, Jeffry A</au><au>Hankins, Michael B</au><au>Jew, Myron L</au><au>Ulmer, Donald G</au><au>Wherley, Brian L</au><au>Romine, William D</au><au>Kuck, Frederick M</au><au>Ades, Douglas S</au><aucorp>United Technologies Corporation</aucorp><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>Method of fabricating a rocket engine nozzle using pressure brazing</title><date>2012-03-06</date><risdate>2012</risdate><abstract>A method of fabrication of a rocket engine nozzle assembly using pressure brazing generally includes initially assembling a rocket engine nozzle liner into a rocket engine nozzle jacket for a rocket engine nozzle assembly. The rocket engine nozzle assembly may then be sealed. Prior to pressure brazing the rocket engine nozzle assembly, pressure brazing parameters may be determined. The pressure brazing may be performed with the determined pressure brazing parameters to complete the fabrication of the rocket engine nozzle. The rocket engine nozzle assembly may include a rocket engine nozzle jacket and a rocket engine nozzle liner having a plurality of channels, with the space between each channel defining a land, and the rocket engine nozzle liner having at least a pair of endlands disposed at each end thereof. The rocket engine nozzle liner is bonded to the rocket engine nozzle jacket by the endlands being bonded to the nozzle jacket and the lands being pressure brazed to the nozzle jacket.</abstract><oa>free_for_read</oa></addata></record> |
| fulltext | fulltext_linktorsrc |
| identifier | |
| ispartof | |
| issn | |
| language | eng |
| recordid | cdi_uspatents_grants_08127443 |
| source | USPTO Issued Patents |
| title | Method of fabricating a rocket engine nozzle using pressure brazing |
| url | https://sfx.bib-bvb.de/sfx_tum?ctx_ver=Z39.88-2004&ctx_enc=info:ofi/enc:UTF-8&ctx_tim=2025-01-23T03%3A20%3A01IST&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=Fint,%20Jeffry%20A&rft.aucorp=United%20Technologies%20Corporation&rft.date=2012-03-06&rft_id=info:doi/&rft_dat=%3Cuspatents_EFH%3E08127443%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 |