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1.发明申请公开(公告)号：US20180306037A1
公开(公告)日：2018-10-25
申请号：US15771257
申请日：2016-11-04
发明人： Yoshimasa TAKAOKA , Shunsuke TORII , Hidemichi KOYABU , Saki MATSUO , Yasuoki TOMITA , Satoshi HADA , Yoshifumi OKAJIMA
CPC分类号： F01D5/187 , F01D5/18 , F01D5/181 , F01D9/02 , F02C7/00 , F02C7/18 , F05D2230/21 , F05D2240/12 , F05D2240/122 , F05D2240/301 , F05D2240/304 , F05D2260/201
摘要： Provided are a turbine blade, a gas turbine, an intermediate product of the turbine blade, and a method of manufacturing the turbine blade. This turbine blade has a blade body having hollow shape, cavities provided inside the blade body, and a cooling passage that opens from the cavities to the rear end portion of the blade body. The cooling passage includes: a first passage provided on the third cavity side and having a width that becomes narrower from the third cavity side toward the rear end portion of the blade body; and a second passage provided on the rear end portion side of the blade body and having a width that is constant from the third cavity side toward the rear end portion of the blade body.
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公开(公告)号：US20180209282A1
公开(公告)日：2018-07-26
申请号：US15327442
申请日：2015-08-19
发明人： Yasuro SAKAMOTO , Satoshi MIZUKAMI , Keisuke MATSUYAMA , Satoshi TANIMURA , Masanori YURI , Shunsuke TORII , Hiroaki KISHIDA
CPC分类号： F01D9/023 , F01D9/041 , F01D25/12 , F05D2220/3212 , F05D2240/35 , F23R3/42 , F23R3/46 , Y02T50/675
摘要： A gas turbine combustor and a gas turbine; wherein inclined surfaces are provided on inner surfaces of side walls neighboring in a circumferential direction at downstream end portions of transition pieces of combustors, the inclined surfaces being configured to increase a passage area of the transition pieces, a ratio (S/P) is from 0 to 0.2, where (P) is a pitch dimension of first stage vanes, and (S) is a circumferential dimension from an intermediate point between neighboring transition pieces to an upstream end of a first stage vane closest in the circumferential direction; and a ratio (L/P) is from 0.3 to 0.55, where (P) is the pitch dimension, and (L) is an axial dimension from a downstream end of the transition piece to the upstream end of the first stage vane.
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公开(公告)号：US20210140329A1
公开(公告)日：2021-05-13
申请号：US16618431
申请日：2018-05-22
发明人： Kentaro TOKUYAMA , Kenji SATO , Keisuke MATSUYAMA , Takaya KODA , Shunsuke TORII , Tetsuya SHIMMYO , Shinya HASHIMOTO , Akihiro MURAKAMI
IPC分类号： F01D9/02
摘要： A first-stage stator vane for a gas turbine includes: a first portion partially forming an airfoil which includes a pressure surface, a suction surface, and a trailing edge; and a second portion positioned at a leading-edge side of the airfoil with respect to the first portion, the second portion having a recess portion or a protruding portion. The recess portion or the protruding portion of the second portion has a pair of side wall surfaces, and an angle formed between the pair of side wall surfaces is less than 90 angular degrees.
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公开(公告)号：US20170198594A1
公开(公告)日：2017-07-13
申请号：US15315471
申请日：2015-06-24
发明人： Keita TAKAMURA , Shunsuke TORII , Masanori YURI
摘要： A turbine vane (3) includes: a vane body (21); a plate-like inner shroud (22) provided at a radially inner end of the vane body (21); and a plate-like outer shroud (23) provided at a radially outer end of the vane body (21). The vane body (21) includes a serpentine channel (30) which is formed so as to meander inside the vane body (21) in the radial direction and through which a cooling medium flows. The inner shroud (22) includes a cooling path (40) which has one end open at the downstream end side of the serpentine channel (30) and the other end open at a trailing edge (22D) of the inner shroud (22) and through which the serpentine channel (30) communicates with the outside of the inner shroud (22).
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