JP2012172588A5 - - Google Patents

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Publication number
JP2012172588A5
JP2012172588A5 JP2011035305A JP2011035305A JP2012172588A5 JP 2012172588 A5 JP2012172588 A5 JP 2012172588A5 JP 2011035305 A JP2011035305 A JP 2011035305A JP 2011035305 A JP2011035305 A JP 2011035305A JP 2012172588 A5 JP2012172588 A5 JP 2012172588A5
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JP
Japan
Prior art keywords
blade
pressure difference
secondary flow
load
boundary layer
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JP2011035305A
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JP2012172588A (ja
JP5603800B2 (ja
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Priority to JP2011035305A priority Critical patent/JP5603800B2/ja
Priority claimed from JP2011035305A external-priority patent/JP5603800B2/ja
Priority to US13/396,798 priority patent/US20120210715A1/en
Priority to EP12156171.6A priority patent/EP2492440B1/en
Publication of JP2012172588A publication Critical patent/JP2012172588A/ja
Publication of JP2012172588A5 publication Critical patent/JP2012172588A5/ja
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Publication of JP5603800B2 publication Critical patent/JP5603800B2/ja
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Description

端面近傍で発達する二次流れと翼負荷分布の関係を説明する。図４を見て分かるように、端面境界層の内部の遅い流体は、翼の背側と腹側の圧力差により、腹側から背側へ向かって流れることになる。この二次流れは、翼の腹側と背側の圧力差（すなわち翼負荷）が大きいほど強くなり、また、その圧力差が上流側で起こるほど強くなる傾向にある。つまり、翼の上流側の圧力差（翼負荷）が小さい、後半負荷型の翼の方が端面境界層の巻き上がりが小さくなり、二次流れ損失が減少する。二次流れ損失低減の観点からは、後半負荷分布の方が性能上、有利である。

JP2011035305A 2011-02-22 2011-02-22 タービン静翼、およびそれを用いた蒸気タービン設備 Active JP5603800B2 (ja)

Priority Applications (3)

Application Number Priority Date Filing Date Title
JP2011035305A JP5603800B2 (ja) 2011-02-22 2011-02-22 タービン静翼、およびそれを用いた蒸気タービン設備
US13/396,798 US20120210715A1 (en) 2011-02-22 2012-02-15 Turbine Nozzle Blade and Steam Turbine Equipment Using Same
EP12156171.6A EP2492440B1 (en) 2011-02-22 2012-02-20 Turbine nozzle blade and steam turbine equipment using same

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP2011035305A JP5603800B2 (ja) 2011-02-22 2011-02-22 タービン静翼、およびそれを用いた蒸気タービン設備

Publications (3)

Publication Number Publication Date
JP2012172588A JP2012172588A (ja) 2012-09-10
JP2012172588A5 true JP2012172588A5 (ja) 2013-03-28
JP5603800B2 JP5603800B2 (ja) 2014-10-08

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ID=45656180

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JP2011035305A Active JP5603800B2 (ja) 2011-02-22 2011-02-22 タービン静翼、およびそれを用いた蒸気タービン設備

Country Status (3)

Country Link
US (1) US20120210715A1 (ja)
EP (1) EP2492440B1 (ja)
JP (1) JP5603800B2 (ja)

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EP2921647A1 (en) 2014-03-20 2015-09-23 Alstom Technology Ltd Gas turbine blade comprising bended leading and trailing edges
US10060263B2 (en) * 2014-09-15 2018-08-28 United Technologies Corporation Incidence-tolerant, high-turning fan exit stator
US9995166B2 (en) * 2014-11-21 2018-06-12 General Electric Company Turbomachine including a vane and method of assembling such turbomachine
US20170138202A1 (en) * 2015-11-16 2017-05-18 General Electric Company Optimal lift designs for gas turbine engines
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WO2017168646A1 (ja) * 2016-03-30 2017-10-05 三菱重工業株式会社 可変容量型ターボチャージャ
FR3059353B1 (fr) * 2016-11-29 2019-05-17 Safran Aircraft Engines Aube directrice de sortie pour turbomachine d'aeronef, comprenant une zone coudee de passage de lubrifiant presentant une conception amelioree
EP3358134B1 (en) * 2017-02-02 2021-07-14 General Electric Company Steam turbine with rotor blade
US10982549B2 (en) * 2017-04-17 2021-04-20 General Electric Company Stator vanes including curved trailing edges
CN107489461A (zh) * 2017-09-15 2017-12-19 哈尔滨汽轮机厂有限责任公司 一种用于汽轮机叶片的高效宽负荷叶型
US20190106989A1 (en) * 2017-10-09 2019-04-11 United Technologies Corporation Gas turbine engine airfoil
CN108194150B (zh) * 2018-02-11 2023-06-09 杭州汽轮动力集团股份有限公司 一种工业汽轮机大负荷高效调节级静叶片
EP3569817B1 (en) * 2018-05-14 2020-10-14 ArianeGroup GmbH Guide vane arrangement for use in a turbine
EP3816397B1 (en) * 2019-10-31 2023-05-10 General Electric Company Controlled flow turbine blades
CN111259559B (zh) * 2020-02-02 2023-03-24 上海交通大学 悬臂静子叶片前加载设计减小损失的流动控制方法
CN112610283B (zh) * 2020-12-17 2023-01-06 哈尔滨工业大学 一种采用端壁分区造型设计的涡轮叶栅

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