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公开(公告)号：EP1292760B1
公开(公告)日：2010-11-03
申请号：EP01949387.3
申请日：2001-06-08
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , B22C9/10 , F05D2260/20 , F05D2260/22141
摘要： The invention relates to a turbine blade (1) through which cooling liquid flows and which comprises several flow channels (4, 5, 6) that are adjacently arranged in the flowing-off direction (2) of the working fluid (3). Said flow channels (4, 5, 6) extend between inflow openings (7, 8, 9), which are located on a radially inner blade foot (10), and outflow openings (11, 12, 13), which are situated opposite the blade foot in a more radially outer manner. The flow channels (4, 5, 6) extend such that the local radial flow components (15) of the resulting cooling fluid stream (14) are directed outward in a, for the most part, predominantly radial manner. A flow channel (4), which is in the front when viewing in the flowing-off direction (2), is provided whose outflow openings (11) are placed inside a touching edge (16) of the turbine blade (1). In addition, at least one rear edge channel (5, 6) is provided whose associated resulting cooling fluid stream (14) additionally comprises local cross-flow components (17) and whose outflow openings (12, 13) are placed inside a rear edge (16) of the turbine blade (1).
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公开(公告)号：EP1292760A1
公开(公告)日：2003-03-19
申请号：EP01949387.3
申请日：2001-06-08
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , B22C9/10 , F05D2260/20 , F05D2260/22141
摘要： The invention relates to a turbine blade (1) through which cooling liquid flows and which comprises several flow channels (4, 5, 6) that are adjacently arranged in the flowing-off direction (2) of the working fluid (3). Said flow channels (4, 5, 6) extend between inflow openings (7, 8, 9), which are located on a radially inner blade foot (10), and outflow openings (11, 12, 13), which are situated opposite the blade foot in a more radially outer manner. The flow channels (4, 5, 6) extend such that the local radial flow components (15) of the resulting cooling fluid stream (14) are directed outward in a, for the most part, predominantly radial manner. A flow channel (4), which is in the front when viewing in the flowing-off direction (2), is provided whose outflow openings (11) are placed inside a touching edge (16) of the turbine blade (1). In addition, at least one rear edge channel (5, 6) is provided whose associated resulting cooling fluid stream (14) additionally comprises local cross-flow components (17) and whose outflow openings (12, 13) are placed inside a rear edge (16) of the turbine blade (1).
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公开(公告)号：EP1309773B1
公开(公告)日：2005-12-21
申请号：EP01962905.4
申请日：2001-08-03
IPC分类号： F01D5/18
摘要： The invention relates to a turbine vane (1), especially a turbine vane of the last stages, respectively comprising a lower area (2) which is radially and externally arranged, an upper area (3) which is radially and internally arranged, and a radial cooling air channel (4) extending between the upper area and the lower area. Cooling air (23) can be introduced into said channel via an inlet (36) in the lower area, and can be at least partially discharged via an outlet (35) in the upper area. The cooling air channel comprises a radial inner channel through which the cooling air flows from the lower area to the upper area, and an outer channel (9) which is adjacent to the inner channel and which at least partially surrounds the inner channel on the circumferential side thereof. Said outer channel communicates with the inner channel and comprises an outlet (12) which is arranged in the lower area. Part of the cooling air (41) flows back in the direction of the lower area via the outer channel and emerges via the outlet.
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公开(公告)号：EP1180196B1
公开(公告)日：2005-02-16
申请号：EP00925282.6
申请日：2000-05-12
IPC分类号： F01D11/00
CPC分类号： F01D11/006
摘要： The invention relates to a turbo-machine (1) comprising a rotor (25) that extends along a rotational axis (15). Said rotor (25) has a peripheral surface (31) which is defined by the outer radial delimitation surface of the rotor (25) and has a receiving structure (33) as well as a first moving blade (13A) and a second moving blade (13B). Each moving blade comprises a blade footing (43A, 43B) and a blade platform (17A, 17B). The blade platform (17A) of the first moving blade (13A) and the blade platform (17B) of the second moving blade (13B) border one another, and a gap (49) is formed between the blade platforms (17A, 17B) and the peripheral surface (31). A sealing system (51) is provided in the gap (49) on the peripheral surface (31).
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5.发明授权HEISSGASBEAUFSCHLAGBARES BAUTEIL, INSBESONDERE TURBINENSCHAUFEL 有权HEISSGASBEAUFSCHLAGBARES部分，特别是涡轮叶片
公开(公告)号：EP1192333B1
公开(公告)日：2003-06-04
申请号：EP00942078.7
申请日：2000-06-15
发明人： TIEMANN, Peter , SCHEURLEN, Michael , ANDING, Dirk , BOLMS, Hans-Thomas , STRASSBERGER, Michael
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2260/2212
摘要： The invention relates to a component (10) that can be subjected to a hot gas, especially a turbine blade. At least one channel (13) is provided. Said channel can be subjected to a cooling fluid and is delimited by two first walls (16, 17), which face each other and have turbulators (20, 21) with the same direction of inclination. The turbulators (20) of the first wall (16) have a different angle of inclination (α) in relation to a direction of flow (22) of the cooling fluid to the turbulators (21) of the second wall (17) in order to avoid constrictions (23).
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公开(公告)号：EP1309773A1
公开(公告)日：2003-05-14
申请号：EP01962905.4
申请日：2001-08-03
IPC分类号： F01D5/18
摘要： The invention relates to a turbine vane (1), especially a turbine vane of the last stages, respectively comprising a lower area (2) which is radially and externally arranged, an upper area (3) which is radially and internally arranged, and a radial cooling air channel (4) extending between the upper area and the lower area. Cooling air (23) can be introduced into said channel via an inlet (36) in the lower area, and can be at least partially discharged via an outlet (35) in the upper area. The cooling air channel comprises a radial inner channel through which the cooling air flows from the lower area to the upper area, and an outer channel (9) which is adjacent to the inner channel and which at least partially surrounds the inner channel on the circumferential side thereof. Said outer channel communicates with the inner channel and comprises an outlet (12) which is arranged in the lower area. Part of the cooling air (41) flows back in the direction of the lower area via the outer channel and emerges via the outlet.
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公开(公告)号：EP1180196A1
公开(公告)日：2002-02-20
申请号：EP00925282.6
申请日：2000-05-12
IPC分类号： F01D11/00
CPC分类号： F01D11/006
摘要： The invention relates to a turbo-machine (1) comprising a rotor (25) that extends along a rotational axis (15). Said rotor (25) has a peripheral surface (31) which is defined by the outer radial delimitation surface of the rotor (25) and has a receiving structure (33) as well as a first moving blade (13A) and a second moving blade (13B). Each moving blade comprises a blade footing (43A, 43B) and a blade platform (17A, 17B). The blade platform (17A) of the first moving blade (13A) and the blade platform (17B) of the second moving blade (13B) border one another, and a gap (49) is formed between the blade platforms (17A, 17B) and the peripheral surface (31). A sealing system (51) is provided in the gap (49) on the peripheral surface (31).
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公开(公告)号：EP1257732B1
公开(公告)日：2004-10-06
申请号：EP01913779.3
申请日：2001-02-01
CPC分类号： F01D5/081 , F01D5/147 , F01D5/187 , F01D5/3007
摘要： The invention relates to a moving turbine blade comprising a blade profile (1) with inner cooling which extends out from a blade platform (2) adjoined by a blade foot (4), said blade foot engaging with a turbine disk (3) and having a radial cross-section with an area (5) whose width (6') increases towards the blade platform (2). The aim of the invention is to configure a moving turbine blade of this type in such a way as to enable the moving blade profile to be lengthened. To this end, the blade foot (4) has a hollowed-out section (7) which opens out in the direction facing away from the platform, which comes to a dead end on the platform side and which has a widened cross section in the area (5) of the blade foot (4) whose width (6´) increases.
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公开(公告)号：EP1254301A2
公开(公告)日：2002-11-06
申请号：EP01905702.5
申请日：2001-01-29
CPC分类号： F01D11/008 , F01D5/3007
摘要： The invention relates to a turbine blade arrangement consisting of rotating blades (4) respectively provided with a leg (8) which can be respectively inserted into a groove (9) on the outer circumference (2) of a turbine disk in a radial, positive fit and which are respectively provided with a profiled section (5) which has a lateral platform (6) located in an end area on the side of the disk. According to the invention, at least one part (10) of the platform is joined to the turbine disk by means of a retaining element (11) which is independent from the leg (8) of the blades in order to extend the profiled sections of the rotating blades.
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10.发明公开HEISSGASBEAUFSCHLAGBARES BAUTEIL, INSBESONDERE TURBINENSCHAUFEL 有权HEISSGASBEAUFSCHLAGBARES部分，特别是涡轮叶片
公开(公告)号：EP1192333A1
公开(公告)日：2002-04-03
申请号：EP00942078.7
申请日：2000-06-15
发明人： TIEMANN, Peter , SCHEURLEN, Michael , ANDING, Dirk , BOLMS, Hans-Thomas , STRASSBERGER, Michael
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2260/2212
摘要： The invention relates to a component (10) that can be subjected to a hot gas, especially a turbine blade. At least one channel (13) is provided. Said channel can be subjected to a cooling fluid and is delimited by two first walls (16, 17), which face each other and have turbulators (20, 21) with the same direction of inclination. The turbulators (20) of the first wall (16) have a different angle of inclination (α) in relation to a direction of flow (22) of the cooling fluid to the turbulators (21) of the second wall (17) in order to avoid constrictions (23).
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