Hybrid nozzle segment assemblies for a gas turbine engine
A nozzle segment assembly for a gas turbine engine may generally include inner and outer ring support segments and a nozzle fairing positioned between the inner and outer ring support segments. The nozzle fairing may be formed from a ceramic matrix composite (CMC) material and may include both an ou...
Saved in:
Main Author | |
---|---|
Format | Patent |
Language | English |
Published |
09.01.2018
|
Subjects | |
Online Access | Get full text |
Cover
Loading…
Abstract | A nozzle segment assembly for a gas turbine engine may generally include inner and outer ring support segments and a nozzle fairing positioned between the inner and outer ring support segments. The nozzle fairing may be formed from a ceramic matrix composite (CMC) material and may include both an outer endwall and an inner endwall. In addition, the nozzle fairing may include a strut vane extending between the inner and outer endwalls. The nozzle segment assembly may also include a metallic strut extending through the strut vane between the outer and inner ring supports and at least one secondary vane configured to be received through at least one of the outer endwall or the inner endwall of the nozzle fairing such that the at least one secondary vane extends between the inner and outer endwalls at a location adjacent to the strut vane. |
---|---|
AbstractList | A nozzle segment assembly for a gas turbine engine may generally include inner and outer ring support segments and a nozzle fairing positioned between the inner and outer ring support segments. The nozzle fairing may be formed from a ceramic matrix composite (CMC) material and may include both an outer endwall and an inner endwall. In addition, the nozzle fairing may include a strut vane extending between the inner and outer endwalls. The nozzle segment assembly may also include a metallic strut extending through the strut vane between the outer and inner ring supports and at least one secondary vane configured to be received through at least one of the outer endwall or the inner endwall of the nozzle fairing such that the at least one secondary vane extends between the inner and outer endwalls at a location adjacent to the strut vane. |
Author | Weaver Matthew Mark |
Author_xml | – fullname: Weaver Matthew Mark |
BookMark | eNrjYmDJy89L5WSw9KhMKspMUcjLr6rKSVUoTk3PTc0rUUgsLk7NTcrJTC1WSMsvUkhUSE8sVigpLUrKzEtVSM1LB1I8DKxpiTnFqbxQmptBwc01xNlDN7UgPz61uCAxOTUvtSQ-NNjSwszYyMzAyciYCCUA6x0wJQ |
ContentType | Patent |
DBID | EVB |
DatabaseName | esp@cenet |
DatabaseTitleList | |
Database_xml | – sequence: 1 dbid: EVB name: esp@cenet url: http://worldwide.espacenet.com/singleLineSearch?locale=en_EP sourceTypes: Open Access Repository |
DeliveryMethod | fulltext_linktorsrc |
Discipline | Medicine Chemistry Sciences |
ExternalDocumentID | US9863260B2 |
GroupedDBID | EVB |
ID | FETCH-epo_espacenet_US9863260B23 |
IEDL.DBID | EVB |
IngestDate | Fri Jul 19 15:09:03 EDT 2024 |
IsOpenAccess | true |
IsPeerReviewed | false |
IsScholarly | false |
Language | English |
LinkModel | DirectLink |
MergedId | FETCHMERGED-epo_espacenet_US9863260B23 |
Notes | Application Number: US201514672380 |
OpenAccessLink | https://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20180109&DB=EPODOC&CC=US&NR=9863260B2 |
ParticipantIDs | epo_espacenet_US9863260B2 |
PublicationCentury | 2000 |
PublicationDate | 20180109 |
PublicationDateYYYYMMDD | 2018-01-09 |
PublicationDate_xml | – month: 01 year: 2018 text: 20180109 day: 09 |
PublicationDecade | 2010 |
PublicationYear | 2018 |
RelatedCompanies | General Electric Company |
RelatedCompanies_xml | – name: General Electric Company |
Score | 3.132235 |
Snippet | A nozzle segment assembly for a gas turbine engine may generally include inner and outer ring support segments and a nozzle fairing positioned between the... |
SourceID | epo |
SourceType | Open Access Repository |
SubjectTerms | AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS |
Title | Hybrid nozzle segment assemblies for a gas turbine engine |
URI | https://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20180109&DB=EPODOC&locale=&CC=US&NR=9863260B2 |
hasFullText | 1 |
inHoldings | 1 |
isFullTextHit | |
isPrint | |
link | http://utb.summon.serialssolutions.com/2.0.0/link/0/eLvHCXMwfV3dS8MwED_GFPVNp-L8Ig_St2JL03Z9KML6QRH2gVtlb6Np0jGY3bAVcX-9l9BNX_QtJHBcAnf3u0vuF4AHlyEOsAr54KmgOrW5qbPc5DrNHeoWLs0M1cU_GDpJSp9n9qwFy10vjOIJ_VTkiGhROdp7rfz15qeIFaq3ldUjW-LU-ime-qHWZMdmT970aGHfj8ajcBRoQeCnE2344ns9B4GK0UdvfSBRtKTZj177sill8zuixKdwOEZhZX0GLVF24DjYfbzWgaNBc9-Nw8b0qnPwki_ZXEXK9Xa7EqQSC1nXI4h9xRtqKCqC8JNkZJFVBMMIJryCCEU2eAEkjqZBoqMO8_1-5-lkr611Ce1yXYorIK7LDeZJ3k6eU4Nxz2bSniyLcY6og3Wh-6eY63_WbuBEHpwqK3i30K7fP8QdBtqa3asj-gYeiYJe |
link.rule.ids | 230,309,786,891,25594,76904 |
linkProvider | European Patent Office |
linkToHtml | http://utb.summon.serialssolutions.com/2.0.0/link/0/eLvHCXMwfV1bS8MwFD6MKc43nYrzmgfpW7Gl2bo-FGG9UHU33CZ7K0uTjsHshq2I-_WehG76om8hgXASODnfuX0BuLMZ4gArlQVPKdVpk5s6S0yu06RF7dSmM0N18ff6rWhCn6bNaQUW214YxRP6qcgRUaMS1PdCvdfrnyCWr2or83u2wKnVQzh2fa30js22zPRofscNhgN_4Gme505GWv_FddotBCpGB1_rPRs9QkmzH7x2ZFPK-rdFCY9gf4ibZcUxVERWh5q3_XitDge9Mt-Nw1L18hNwoi_ZXEWy1WazFCQXcxnXI4h9xRtKKHKC8JPMyHyWEzQj6PAKIhTZ4CmQMBh7kY4yxLvzxpPRTlrrDKrZKhPnQGybG8yRvJ08oQbjTpNJfbIsxjmiDtaAxp_bXPyzdgu1aNzrxt3H_vMlHMpLVCEG5wqqxfuHuEajW7AbdV3fXSGFSQ |
openUrl | ctx_ver=Z39.88-2004&ctx_enc=info%3Aofi%2Fenc%3AUTF-8&rfr_id=info%3Asid%2Fsummon.serialssolutions.com&rft_val_fmt=info%3Aofi%2Ffmt%3Akev%3Amtx%3Apatent&rft.title=Hybrid+nozzle+segment+assemblies+for+a+gas+turbine+engine&rft.inventor=Weaver+Matthew+Mark&rft.date=2018-01-09&rft.externalDBID=B2&rft.externalDocID=US9863260B2 |