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1. 发明专利

DE112013003971T5 Nickelbasierte einkristalline Superlegierung 未知
公开(公告)号：DE112013003971T5
公开(公告)日：2015-06-25
申请号：DE112013003971
申请日：2013-07-30
申请人： MITSUBISHI HEAVY IND LTD , NAT INST FOR MATERIALS SCIENCE
发明人： KAWAGISHI KYOKO , HARADA HIROSHI , YOKOKAWA TADAHARU , KOIZUMI YUTAKA , SAKAMOTO MASAO , YUYAMA MICHINARI , TANEIKI MASAKI , OKADA IKUO , SHIMOHATA SACHIO , OGUMA HIDETAKA , OKIMOTO RYOTA , TSUKAGOSHI KEIZO , UEMURA YOSHITAKA , MASADA JUNICHIRO , TORII SHUNSUKE , KOBAYASHI TOSHIHARU
IPC分类号： C22C19/05 , C22F1/00 , C22F1/10 , F01D5/28 , F01D25/00 , F02C7/00
摘要： Eine nickelbasierte einkristalline Superlegierung wird offenbart, die Folgendes aufweist: 6 oder mehr Massen-% und 12 oder weniger Massen-% Cr, 0,4 oder mehr Massen-% und 3,0 oder weniger Massen-% Mo, 6 oder mehr Massen-% und 10 oder weniger Massen-% W, 4,0 oder mehr Massen-% und 6,5 oder weniger Massen-% Al, 0 oder mehr Massen-% und 1 oder weniger Massen-% Nb, 8 oder mehr Massen-% und 12 oder weniger Massen-% Ta, 0 oder mehr Massen-% und 0,15 oder weniger Massen-% Hf, 0,01 oder mehr Massen-% und 0,2 oder weniger Massen-% Si, und 0 oder mehr Massen-% und 0,04 oder weniger Massen-% Zr, und optional wenigstens ein Element, welches aus B, C; Y, La, Ce und V ausgewählt ist, wobei der Rest Ni und unvermeidbare Verunreinigungen ist.

2. 发明公开

EP2037081A4 PLATFORM COOLING STRUCTURE OF GAS TURBINE ROTOR BLADE 有权转让
标题翻译：平台冷却结构的燃气轮机叶片
公开(公告)号：EP2037081A4
公开(公告)日：2013-05-01
申请号：EP07849990
申请日：2007-11-27
申请人： MITSUBISHI HEAVY IND LTD
发明人： TORII SHUNSUKE , KUWABARA MASAMITSU , ITO EISAKU
IPC分类号： F01D5/18 , F02C7/18
CPC分类号： F01D5/187 , F01D5/18 , F01D25/12 , F05D2240/81

3. 发明公开

EP2182169A4 BLADE COOLING STRUCTURE OF GAS TURBINE 有权转让
标题翻译： SCHAUFELKÜHLUNGSSTRUKTUREINER GASTURBINE
公开(公告)号：EP2182169A4
公开(公告)日：2012-12-19
申请号：EP07806358
申请日：2007-08-30
申请人： MITSUBISHI HEAVY IND LTD
发明人： FUJIMURA DAIGO , SUGISHITA HIDEAKI , MATSUURA MASAAKI , YAMAMOTO HIROYUKI , TORII SHUNSUKE , HADA SATOSHI
IPC分类号： F01D5/18 , F01D9/02
CPC分类号： F01D5/187 , F05D2240/127 , F05D2250/185 , F05D2260/2212 , F05D2260/22141 , Y02T50/676

4. 发明专利

DE60113892D1 未知
公开(公告)号：DE60113892D1
公开(公告)日：2006-02-23
申请号：DE60113892
申请日：2001-02-13
申请人： MITSUBISHI HEAVY IND LTD
发明人： TOMITA YASUOKI , HASHIMOTO YUKIHIRO , SUENAGA KIYOSHI , ARIMURA HISATO , TORII SHUNSUKE , KUBOTA JUN , SHIROTA AKIHIKO , AOKI SUNAO , ISHIGURO TATSUO
IPC分类号： F01D5/18 , F02C7/18
摘要： A gas turbine moving blade is improved so as to prevent occurrence of cracks caused by thermal stresses due to temperature differences between a blade (101) and a platform (102) to which the blade is fitted. The moving blade comprises a blade serpentine cooling passage (106a-106c,107a-107c), a platform cooling passage provided in each of blade ventral and dorsal side end portions of the platform, and cooling air blow holes (108,109,110a-110c,111,112) provided in and around the blade. The blade serpentine cooling passage comprises a flow path (107) constructed such that cooling air (183) entering a central portion of a blade root portion (117) flows toward a blade trailing edge side. The blade fitting portion is formed having an exterior (104a,104b) with a curved surface. A recessed portion (103b) is provided, extending in a direction orthogonal to a turbine axial direction, in an end face portion of a rear side portion of the platform near the blade fitting portion on the blade trailing edge side. The cooling air blow holes include a plurality of cooling holes provided in the platform and being arranged along the platform cooling passage on the blade dorsal side and each having one end communicating with the platform cooling passage on the blade dorsal side and the other end opening at an end face on the blade dorsal side of the platform.

5. 发明专利

DE60113796D1 未知
公开(公告)号：DE60113796D1
公开(公告)日：2005-11-10
申请号：DE60113796
申请日：2001-12-20
申请人： MITSUBISHI HEAVY IND LTD
发明人： TOMITA YASUOKI , KUWABARA MASAMITSU , TORII SHUNSUKE
IPC分类号： F01D11/02 , F01D9/04 , F01D11/00
摘要： A base plate and honeycomb member disposed at the inner circumference side of an inside shroud are fixed to the inside shroud, at a phase deviation in the peripheral direction, with respect to the inside shroud, so as to plug the missing range of seal member, out of gaps between adjacent inside shrouds, and therefore leak of purge air from the missing range of seal member is prevented without adding new constituent members.

6. 发明专利

CA2366726C COOLING STRUCTURE FOR A GAS TURBINE 未知
公开(公告)号：CA2366726C
公开(公告)日：2005-07-26
申请号：CA2366726
申请日：2002-01-08
申请人： MITSUBISHI HEAVY IND LTD
发明人： TORII SHUNSUKE , KUWABARA MASAMITSU , KUBOTA JUN , TOMITA YASUOKI , AOKI HIROYUKI
IPC分类号： F01D5/18 , F01D9/02 , F01D25/12
摘要： In a cooling structure for a gas turbine, cooling air diffusion holes are formed from inner surface to outer surface of a platform so as to open from high pressure side blade surface of a moving blade offset in a direction toward low pressure side blade surface of adjacent moving blade confronting the high pressure side blade surface, in a direction of primary flow.

7. 发明专利

DE102004002888A1 未知
公开(公告)号：DE102004002888A1
公开(公告)日：2004-08-12
申请号：DE102004002888
申请日：2004-01-20
申请人： MITSUBISHI HEAVY IND LTD
发明人： SOECHTING FRIEDRICH , TOMITA YASUOKI , TORII SHUNSUKE
IPC分类号： F02C7/28 , F01D9/02 , F01D9/04 , F01D11/00 , F02C1/00 , F02C7/00 , F02C7/18 , F02G3/00 , F23R3/42

8. 发明专利

DE60123492T2 未知
公开(公告)号：DE60123492T2
公开(公告)日：2007-06-14
申请号：DE60123492
申请日：2001-02-13
申请人： MITSUBISHI HEAVY IND LTD
发明人： TOMITA YASUOKI , HASHIMOTO YUKIHIRO , SUENAGA KIYOSHI , ARIMURA HISATO , TORII SHUNSUKE , KUBOTA JUN , SHIROTA AKIHIKO , AOKI SUNAO , ISHIGURO TATSUO
IPC分类号： F01D5/18 , F02C7/18
摘要： A gas turbine moving blade is improved so as to prevent occurrence of cracks caused by thermal stresses due to temperature differences between a blade (101) and a platform (102) to which the blade is fitted. The moving blade comprises a blade serpentine cooling passage (106a-106c,107a-107c), a platform cooling passage provided in each of blade ventral and dorsal side end portions of the platform, and cooling air blow holes (108,109,110a-110c,111,112) provided in and around the blade. The blade serpentine cooling passage comprises a flow path (107) constructed such that cooling air (183) entering a central portion of a blade root portion (117) flows toward a blade trailing edge side. The blade fitting portion is formed having an exterior (104a,104b) with a curved surface. A recessed portion (103b) is provided, extending in a direction orthogonal to a turbine axial direction, in an end face portion of a rear side portion of the platform near the blade fitting portion on the blade trailing edge side. The cooling air blow holes include a plurality of cooling holes provided in the platform and being arranged along the platform cooling passage on the blade dorsal side and each having one end communicating with the platform cooling passage on the blade dorsal side and the other end opening at an end face on the blade dorsal side of the platform.

9. 发明专利

DE60127804D1 未知
公开(公告)号：DE60127804D1
公开(公告)日：2007-05-24
申请号：DE60127804
申请日：2001-11-29
申请人： MITSUBISHI HEAVY IND LTD
发明人： FUJIKAWA TATSUAKI , TOMITA YASUOKI , TORII SHUNSUKE , MAGOSHI RYOTARO , KUWABARA MASAMITSU , INOUE SHINICHI
IPC分类号： F01D11/08 , F01D25/24 , F01D9/00 , F01D11/18
摘要： A gas turbine shroud segment (1) has an outer surface (1b) with radial (10b) and axial (10a) reinforcing ribs (10), forming a waffle grid where the axial ribs (10a) are higher than the radial ribs (10b) to reduce heat deformation of the shroud segment (1) which can influence tip clearance.

10. 发明专利

DE102004002888B4 未知
公开(公告)号：DE102004002888B4
公开(公告)日：2006-03-02
申请号：DE102004002888
申请日：2004-01-20
申请人： MITSUBISHI HEAVY IND LTD
发明人： SOECHTING FRIEDRICH , TOMITA YASUOKI , TORII SHUNSUKE
IPC分类号： F02C7/28 , F01D9/02 , F01D9/04 , F01D11/00 , F02C1/00 , F02C7/00 , F02C7/18 , F02G3/00 , F23R3/42

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