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1. 发明公开

EP1990552A4 BOLT AND METHOD FOR MANUFACTURING BOLT 有权
标题翻译：插头和制造方法BOLT
公开(公告)号：EP1990552A4
公开(公告)日：2012-06-27
申请号：EP07707395
申请日：2007-01-25
申请人： MITSUBISHI HEAVY IND LTD
发明人： TEZUKA NORIKAZU , HIROKAWA KAZUHARU , IHARA KEISUKE , OSAWA KEI , ISHIKAWA HIROSHI , TORIGOE TAIJI , YAMAMOTO RYUICHI , HASHIMOTO YUKIHIRO , IZUTSU NOBUYUKI , TAKAHASHI KOJI
IPC分类号： F16B33/06 , B23G9/00 , B23P9/04 , B24C1/10 , B64C1/10
CPC分类号： B24C1/10 , B23G9/001 , B23P9/04 , B23P15/00 , C21D9/0093 , F01D5/066 , F05D2230/311 , F05D2230/90 , F05D2260/941 , F05D2300/211 , F05D2300/2112 , F05D2300/2261 , F16B33/06 , Y10T29/479

2. 发明公开

EP0931910A4 GAS TURBINE COOLING BLADE 失效
标题翻译：冷却的气体涡轮叶片
公开(公告)号：EP0931910A4
公开(公告)日：2001-02-28
申请号：EP98924593
申请日：1998-06-12
申请人： MITSUBISHI HEAVY IND LTD
发明人： FUKUNO HIROKI , TOMITA YASUOKI , MAEDA SHIGEYUKI , HASHIMOTO YUKIHIRO , SUENAGA KIYOSHI
IPC分类号： F01D5/18 , F02C7/18
CPC分类号： F01D5/186 , F01D5/18
摘要： A gas turbine cooling blade wherein the thermal stress in, especially, the portions thereof which are around shower head cooling air blowout holes in a front edge section thereof is reduced to prevent the occurrence of cracks therein, wherein a front edge section (2) of a cooling blade (1) is provided with air blowout holes (4), from which the cooling air flowing in a cooling air passage (15) in the interior of the cooling blade is blown out onto a blade surface of the front edge section (2) of the cooling blade (1) to shower-head cool the surface. Conventional air blowout holes (14) are provided diagonally with respect to a front edge section (2), so that acute angle portions (30) are formed in outlets and inlets of these air blowout holes (14), thermal stress causing cracks to occur around the air blowout holes (14). The air blowout holes (4) in the present invention are made so as to cross at substantially right angles the outer surface of the front edge section of the cooling blade (1) to eliminate the above-mentioned acute angle portions, and this enables the thermal stress to be reduced and the occurrence of cracks to be avoided.

3. 发明公开

EP0927813A4 AIR SEPARATOR FOR GAS TURBINES 失效
标题翻译：除氧器燃气涡轮机
公开(公告)号：EP0927813A4
公开(公告)日：2001-01-17
申请号：EP98928538
申请日：1998-06-18
申请人： MITSUBISHI HEAVY IND LTD
发明人： AI TOSHISHIGE , IWASAKI YOICHI , AOKI SUNAO , HASHIMOTO YUKIHIRO , SUENAGA KIYOSHI
IPC分类号： F01D5/08 , F01D11/02 , F01D5/18
CPC分类号： F01D11/02 , F01D5/081 , F01D5/085
摘要： An air separator (20) for gas turbines, capable of preventing the fretting fatigue, which causes cracks to occur, of a flange thereof, and easily replacing a conventional air separator, wherein the air separator (20) has a cylindrical shape and a divided structure comprising a part (20-1) fixed to a rotor (1) and a part (20-2) fixed to a disc (7) on the side of a rotor blade (2) by bolts (28) inserted into bolt holes (23) in a flange (22), the cooling air (30) being sent out of a compressor, entering a space (6) through a duct (5) and passing through a clearance (33), and a passage (32) being supplied to air supply ports (43) in the disc (7) and radial holes (44), thereby preventing the occurrence of cracks due to the fretting fatigue encountered in a conventional air separator having an overhung structure fixed by bolts (8), with a flange on the side of a rotor blade (1) being kept only in a contacting condition. The air separator according to the present invention can be substituted for an air separator in an existing plant by forming air holes (50) in the flange (22) as circumferentially elongated holes to cover the radial holes and enable the cooling air to be supplied uniformly.

4. 发明公开

EP0945594A4 COOLED MOVING BLADE FOR GAS TURBINES 失效
标题翻译：冷藏气，涡轮叶片
公开(公告)号：EP0945594A4
公开(公告)日：2001-12-05
申请号：EP98924595
申请日：1998-06-12
申请人： MITSUBISHI HEAVY IND LTD
发明人： FUKUNO HIROKI , TOMITA YASUOKI , MAEDA SHIGEYUKI , HASHIMOTO YUKIHIRO , SUENAGA KIYOSHI
IPC分类号： F01D5/08 , F01D5/14 , F01D5/18 , F01D5/28 , F02C7/18
CPC分类号： F01D5/147 , F01D5/141 , F01D5/18 , F01D5/187 , F01D5/28 , F05D2240/80
摘要： A cooled moving blade for a gas turbine, formed to such a shape that it can reduce thermal stress in a base portion of the moving blade and prevent the occurrence of cracks therein, in view of the fact that a high-temperature combustion gas, which has come to be used recently for heightening the efficiency of a gas turbine, increases the frequency of occurrence of cracks in the base portion of the moving blade, in which a large thermal stress occurs, wherein a moving blade (1) is fixed to a platform (2) with cooling air passages (3) which form a serpentine flow passage provided in an inner portion of the moving blade, the moving blade being cooled with cooling air, a surface of the base portion of the moving blade is formed of an elliptic curved portion (11), and a linear portion (12) provided on a hub section in which thermal stress is large, the linear portion (12) in comparison with an inwardly bulging arcuate elliptic fillet (R) which forms a base portion of a conventional moving blade increasing a cross-sectional area of the moving blade according to the present invention, whereby the heat capacity of the moving blade becomes higher than that of the conventional moving blade, so that a temperature difference occurring due to thermal stress becomes smaller, thus enabling the thermal stress in the moving blade to be reduced to a level lower than that of the thermal stress in the conventional moving blade.

5. 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.

6. 发明专利

HK1063343A1 FLANGED HOLLOW STRUCTURE 未知
公开(公告)号：HK1063343A1
公开(公告)日：2004-12-24
申请号：HK04106119
申请日：2004-08-16
申请人： MITSUBISHI HEAVY IND LTD
发明人： SHIMIZU HIROSHI , KONDO MITSURU , HAKODA HIRONOBU , HASHIMOTO YUKIHIRO , TANAKA KATSUNORI , NAKAMURA SOUSUKE
IPC分类号： F23R3/42 , F01D20060101 , F01D9/02 , F02C7/00 , F16L20060101 , F16L23/00 , F16L23/24 , F23R20060101
摘要： The present invention provides a hollow structure with at least one flange which can eliminate the possibility of creating crackings due to the thermal fatigue, thereby improving the durability thereof. A hollow structure with an flange according to the present invention includes at least one annular flange fixedly attached around the hollow structure which has a temperature gradient in the direction of the thickness of the wall thereof, wherein said at least one annular flange including an outer portion formed of a metal material having a coefficient of linear expansion greater than that of the metal material forming another portion of said at least one annular flange.

7. 发明专利

CA2283862C ROTATIONAL SPEED CONTROL METHOD IN GAS TURBINE STOPPING PROCESS 未知
公开(公告)号：CA2283862C
公开(公告)日：2002-03-19
申请号：CA2283862
申请日：1998-12-28
申请人： MITSUBISHI HEAVY IND LTD
发明人： SUENAGA KIYOSHI , HASHIMOTO YUKIHIRO , TOMITA YASUOKI
IPC分类号： F02C9/00 , F01D21/06 , F02C9/46
摘要： Stress occurring in moving blade in gas turbine stopping process is decreased. Where time t1 is load decrease start or fuel throttling start, time t2 is no load operation start, time t3 is fuel. shut-off and time t4 is time of largest stress, (a) 4/4 load until t1 decreases gradually to 0/4 load at t2 to be kept until t3 and then decreases further, (b) rotational speed is rated one until t2 to be then controlled to be decreased gradually to about 60% of the rated rotational speed at t3, (c) metal temperature with differential temperature between moving blade point A and platform point B is constant until t1 to be then decreased slightly between t1 and t2 and between t2 and t3, and differential temperature .DELTA. t , which is largest after t3, occurs at t4, and (d) stress occurring in moving blade, while decreasing between t1 and t3, becomes largest at t4 by effect of centrifugal force and thermal stress, but as the rotational speed is decreased to about 60% of the rated rotational speed at t3 and the metal temperature is also decreased as compared with prior art, influence of centrifugal force and differential temperature is decreased, thereby stress occurring in the moving blade is mitigated.

8. 发明公开

EP1400755A4 FLANGED HOLLOW STRUCTURE 有权
标题翻译：法兰空心
公开(公告)号：EP1400755A4
公开(公告)日：2007-05-09
申请号：EP02738898
申请日：2002-07-01
申请人： MITSUBISHI HEAVY IND LTD
发明人： SHIMIZU HIROSHI , KONDO MITSURU , HAKODA HIRONOBU , HASHIMOTO YUKIHIRO , TANAKA KATSUNORI , NAKAMURA SOUSUKE
IPC分类号： F23R3/42 , F01D9/02 , F02C7/00 , F16L23/00 , F16L23/24
CPC分类号： F01D9/023 , F05D2260/94 , F05D2260/941 , F05D2300/50212 , F16L23/00 , F16L23/24 , F23R2900/00005 , Y10T403/64
摘要： A flanged hollow structure capable of increasing a structural integrity by preventing cracking due to thermal fatigue from occurring around a flange, comprising the annular flange fixed to the outer peripheral surface thereof causing a temperature difference in the direction of plate thickness thereof, wherein the annular flange is characterized in that a metal material having a linear expansion coefficient larger than the linear expansion coefficient of the metal material around the inner edge of the annular flange is provided along the outer edge of the annular flange.

9. 发明公开

EP0979933A4 REVOLUTION SPEED CONTROL METHOD IN GAS TURBINE SHUTDOWN PROCESS 有权
标题翻译：速度控制的燃气涡轮机的SHUTDOWN
公开(公告)号：EP0979933A4
公开(公告)日：2002-01-30
申请号：EP98961628
申请日：1998-12-28
申请人： MITSUBISHI HEAVY IND LTD
发明人： SUENAGA KIYOSHI , HASHIMOTO YUKIHIRO , TOMITA YASUOKI
IPC分类号： F02C9/00 , F01D21/06 , F02C9/46 , F01D21/00 , F02C9/26
CPC分类号： F02C9/46 , F01D21/06 , F05D2270/02 , F05D2270/091 , F05D2270/112
摘要： A revolution speed control method in a gas turbine shutdown process for reducing a stress on a moving vane. (a) A load is maintained at a 4/4 load up to time t1 at which a fuel begins to be throttled, is decreased to be set to a 0/4 load at time t2, is maintained at no load up to time t3 at which the fuel is shutoff, and is further decreased thereafter. (b) A revolution speed is maintained at a rated level up to time t2 at which a 0/4 load is reached, is decreased starting at time t2, and is controlled to decrease to about 60 % of the rated level at time t3. (c) Metal temperatures at a point A of a platform and a point B of the moving vane, which are slightly different from each other, are kept constant up to time t1, decrease somewhat between time t2 and time t3, and give a maximum temperature difference DELTA t at time t4 in the course of decrease after time t3. (d) A stress on a moving vane decreases between time t1, and time t3, peaks at a maximum level at time t4 due to a centrifugal force and a thermal stress, but is relieved thereafter because of a centrifugal force that has decreased according to a revolution speed decrease to 60 % between t2 and t3, the temperature decreases and a resulting maximum stress decrease.

10. 发明专利

CA2393911C STATIONARY BLADE OF INTEGRATED SEGMENT CONSTRUCTION AND MANUFACTURING METHOD THEREFOR 未知
公开(公告)号：CA2393911C
公开(公告)日：2007-03-13
申请号：CA2393911
申请日：2002-07-16
申请人： MITSUBISHI HEAVY IND LTD
发明人： HASHIMOTO YUKIHIRO , KATAOKA MASAHITO , TERAZAKI MASAO
IPC分类号： F01D5/14 , F01D9/04
摘要： The present invention provides a stationary blade of integrated segment construction, in which a thermal barrier coating can be applied to the whole blade surface and excessive stress can be avoided in a shroud. A plate seat connector is provided at each end face portion of an inside shroud and an outside shroud attached to outside and inside ends of gas turbine stationary blade. Several stationary blades are integrated by joining the plate seat connectors of the adjacent shrouds by means of bolts and nuts to provide a stationary blade of integrated segment construction.

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