JP2004257392A5 - - Google Patents

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Publication number
JP2004257392A5
JP2004257392A5 JP2004050708A JP2004050708A JP2004257392A5 JP 2004257392 A5 JP2004257392 A5 JP 2004257392A5 JP 2004050708 A JP2004050708 A JP 2004050708A JP 2004050708 A JP2004050708 A JP 2004050708A JP 2004257392 A5 JP2004257392 A5 JP 2004257392A5
Authority
JP
Japan
Prior art keywords
airfoil
rib
extending
turbine nozzle
segment
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
JP2004050708A
Other languages
English (en)
Japanese (ja)
Other versions
JP2004257392A (ja
JP4000121B2 (ja
Filing date
Publication date
Priority claimed from US10/375,585 external-priority patent/US6969233B2/en
Application filed filed Critical
Publication of JP2004257392A publication Critical patent/JP2004257392A/ja
Publication of JP2004257392A5 publication Critical patent/JP2004257392A5/ja
Application granted granted Critical
Publication of JP4000121B2 publication Critical patent/JP4000121B2/ja
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

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JP2004050708A 2003-02-27 2004-02-26 二分割空洞を有する単一の中空ベーンを備えたガスタービンエンジンのタービンノズルセグメント Expired - Fee Related JP4000121B2 (ja)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US10/375,585 US6969233B2 (en) 2003-02-27 2003-02-27 Gas turbine engine turbine nozzle segment with a single hollow vane having a bifurcated cavity

Publications (3)

Publication Number Publication Date
JP2004257392A JP2004257392A (ja) 2004-09-16
JP2004257392A5 true JP2004257392A5 (cg-RX-API-DMAC10.html) 2007-04-12
JP4000121B2 JP4000121B2 (ja) 2007-10-31

Family

ID=32771465

Family Applications (1)

Application Number Title Priority Date Filing Date
JP2004050708A Expired - Fee Related JP4000121B2 (ja) 2003-02-27 2004-02-26 二分割空洞を有する単一の中空ベーンを備えたガスタービンエンジンのタービンノズルセグメント

Country Status (5)

Country Link
US (1) US6969233B2 (cg-RX-API-DMAC10.html)
EP (1) EP1452689B1 (cg-RX-API-DMAC10.html)
JP (1) JP4000121B2 (cg-RX-API-DMAC10.html)
CN (1) CN100347411C (cg-RX-API-DMAC10.html)
DE (1) DE602004001069T2 (cg-RX-API-DMAC10.html)

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US7740066B2 (en) * 2008-01-25 2010-06-22 Halliburton Energy Services, Inc. Additives for high alumina cements and associated methods
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US8511969B2 (en) * 2009-10-01 2013-08-20 Pratt & Whitney Canada Corp. Interturbine vane with multiple air chambers
CN102182519B (zh) * 2011-03-24 2013-11-06 西安交通大学 汽轮机静叶自射流二次流控制结构
US8651799B2 (en) 2011-06-02 2014-02-18 General Electric Company Turbine nozzle slashface cooling holes
US8978388B2 (en) * 2011-06-03 2015-03-17 General Electric Company Load member for transition duct in turbine system
EP2626519A1 (en) * 2012-02-09 2013-08-14 Siemens Aktiengesellschaft Turbine assembly, corresponding impingement cooling tube and gas turbine engine
US9024226B2 (en) * 2012-02-15 2015-05-05 United Technologies Corporation EDM method for multi-lobed cooling hole
US9151164B2 (en) 2012-03-21 2015-10-06 Pratt & Whitney Canada Corp. Dual-use of cooling air for turbine vane and method
US20140075947A1 (en) * 2012-09-18 2014-03-20 United Technologies Corporation Gas turbine engine component cooling circuit
CN103775136B (zh) * 2012-10-23 2015-06-10 中航商用航空发动机有限责任公司 一种叶片
ITCO20120059A1 (it) * 2012-12-13 2014-06-14 Nuovo Pignone Srl Metodi per produrre pale cave sagomate in 3d di turbomacchine mediante produzione additiva, pale cave di turbomacchina e turbomacchine
US9057276B2 (en) 2013-02-06 2015-06-16 Siemens Aktiengesellschaft Twisted gas turbine engine airfoil having a twisted rib
US9120144B2 (en) 2013-02-06 2015-09-01 Siemens Aktiengesellschaft Casting core for twisted gas turbine engine airfoil having a twisted rib
US10822976B2 (en) * 2013-06-03 2020-11-03 General Electric Company Nozzle insert rib cap
US20140356155A1 (en) 2013-06-03 2014-12-04 General Electric Company Nozzle Insert Rib Cap
WO2015047698A1 (en) * 2013-09-24 2015-04-02 United Technologies Corporation Bonded multi-piece gas turbine engine component
US10253986B2 (en) * 2015-09-08 2019-04-09 General Electric Company Article and method of forming an article
US10428659B2 (en) 2015-12-21 2019-10-01 United Technologies Corporation Crossover hole configuration for a flowpath component in a gas turbine engine
US20170350597A1 (en) * 2016-06-07 2017-12-07 General Electric Company Heat transfer device, turbomachine casing and related storage medium
US10669861B2 (en) * 2017-02-15 2020-06-02 Raytheon Technologies Corporation Airfoil cooling structure
GB2559739A (en) * 2017-02-15 2018-08-22 Rolls Royce Plc Stator vane section
JP6906332B2 (ja) * 2017-03-10 2021-07-21 川崎重工業株式会社 タービン翼の冷却構造
US10655485B2 (en) * 2017-08-03 2020-05-19 General Electric Company Stress-relieving pocket in turbine nozzle with airfoil rib
US10422236B2 (en) * 2017-08-03 2019-09-24 General Electric Company Turbine nozzle with stress-relieving pocket
US10865650B2 (en) * 2017-09-12 2020-12-15 Raytheon Technologies Corporation Stator vane support with anti-rotation features
US10837293B2 (en) 2018-07-19 2020-11-17 General Electric Company Airfoil with tunable cooling configuration
US11078844B2 (en) * 2018-11-21 2021-08-03 Raytheon Technologies Corporation Thermal gradient reducing device for gas turbine engine component
US11187092B2 (en) * 2019-05-17 2021-11-30 Raytheon Technologies Corporation Vane forward rail for gas turbine engine assembly
US11359502B2 (en) * 2020-02-18 2022-06-14 General Electric Company Nozzle with slash face(s) with swept surfaces with joining line aligned with stiffening member
RU199563U1 (ru) * 2020-03-04 2020-09-08 Федеральное государственное бюджетное образовательное учреждение высшего образования "Рыбинский государственный авиационный технический университет имени П.А. Соловьева" Блок охлаждаемых лопаток турбины ГТД с охлаждаемой несимметричной торцевой полкой
US11994293B2 (en) 2020-08-31 2024-05-28 General Electric Company Impingement cooling apparatus support structure and method of manufacture
FR3116861B1 (fr) * 2020-11-27 2022-10-21 Safran Aircraft Engines Dispositif et procede de controle des secteurs pour l’assemblage de distributeurs d’une turbine
JP7460510B2 (ja) * 2020-12-09 2024-04-02 三菱重工航空エンジン株式会社 静翼セグメント
WO2023147119A1 (en) 2022-01-28 2023-08-03 Raytheon Technologies Corporation Cooled vane with forward rail for gas turbine engine
US12297752B2 (en) 2022-01-28 2025-05-13 Rtx Corporation Vane forward rail for gas turbine engine assembly
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