公开(公告)号：US20190048799A1

公开(公告)日：2019-02-14

申请号：US16076422

申请日：2017-03-02

申请人： Mitsubishi Hitachi Power Systems, Ltd.

发明人： Hiroaki KISHIDA

IPC分类号： F02C7/18 ,  F23R3/42 ,  F23R3/00

摘要： A combustor panel having a plurality of cooling flow paths formed between the outer surface and the inner surface of the combustor panel. The cooling flow paths have inlets that open at the outer surface and introduce a cooling medium into their interior, and outlets that open at the inner surface and discharge the cooling medium flowing through their interior. Among the plurality of cooling flow paths, each of plurality of cooling flow paths extending from a position along the edge of an aperture of the combustor panel forms an aperture-vicinity flow path. Among the plurality of aperture-vicinity flow paths, each of the aperture-vicinity flow paths for which the inlet is formed closer to the aperture than the outlet forms an aperture-side inlet flow path. The number of the aperture-side inlet flow paths is greater than one-half of the all of the aperture-vicinity flow paths.

公开(公告)号：US20180209282A1

公开(公告)日：2018-07-26

申请号：US15327442

申请日：2015-08-19

申请人： MITSUBISHI HITACHI POWER SYSTEMS, LTD.

发明人： Yasuro SAKAMOTO ,  Satoshi MIZUKAMI ,  Keisuke MATSUYAMA ,  Satoshi TANIMURA ,  Masanori YURI ,  Shunsuke TORII ,  Hiroaki KISHIDA

IPC分类号： F01D9/02 ,  F23R3/46 ,  F01D9/04 ,  F01D25/12

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.

公开(公告)号：US20180347385A1

公开(公告)日：2018-12-06

申请号：US15757745

申请日：2016-09-01

申请人： Mitsubishi Hitachi Power Systems, Ltd.

发明人： Hiroaki KISHIDA ,  Norihiko NAGAI

IPC分类号： F01D11/00 ,  F02C3/04

CPC分类号： F01D11/00 ,  F01D25/00 ,  F02C7/00 ,  F02C7/28 ,  F16J15/04

摘要： A seal member assembly structure and assembly method, a seal member, and a gas turbine, wherein, in a state where first flange parts provided on a combustor transition piece are fitted into first fitting parts provided in seal members, protruding parts provided on the first flange parts are inserted into recessed parts provided in the first fitting parts.

公开(公告)号：US20170370235A1

公开(公告)日：2017-12-28

申请号：US15544384

申请日：2016-01-25

申请人： MITSUBISHI HITACHI POWER SYSTEMS, LTD.

发明人： Tetsu KONISHI ,  Hiroaki KISHIDA ,  Kentaro TOKUYAMA ,  Hiroki SHIBATA ,  Akihiro MURAKAMI

IPC分类号： F01D9/02 ,  F02C7/18 ,  F02C3/04 ,  F01D25/24 ,  F01D5/08 ,  F23R3/28 ,  F01D25/12

CPC分类号： F01D9/023 ,  F01D5/082 ,  F01D25/12 ,  F01D25/24 ,  F02C3/04 ,  F02C7/18 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2260/20 ,  F23R3/06 ,  F23R3/28 ,  F23R3/42

摘要： A plurality of cooling passages extending in an axial direction are formed in a transition piece so as to be aligned in a circumferential direction and the axial direction. One or more downstream side passages are formed in a downstream side region (Rd) within one circumferential region. One or more upstream side passages are formed in an upstream side region Ru within the circumferential region. The total cross-sectional area per unit circumferential length of the one or more downstream side passages is larger than the total cross-sectional area per unit circumferential length of the one or more upstream side passages.