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公开(公告)号：EP1180197A1
公开(公告)日：2002-02-20
申请号：EP00938559.2
申请日：2000-05-15
发明人： TIEMANN, Peter
IPC分类号： F01D11/00
CPC分类号： F01D11/008 , F01D11/006
摘要： The invention relates to a turbo engine (1), especially a gas turbine, with a rotor (25) that extends along an axis of rotation (15). Said rotor (25) comprises a peripheral surface (31) that is defined by the outer radial delimiting surface of the rotor (25) and a receiving structure (33) and a first rotor blade (13A) and a second rotor blade (13B) which have each a blade root (43A, 43B) and a blade platform (17A, 17B). The blade platform (17A) of the first rotor blade (13A) and the blade platform (17B) of the second rotor blade (13B) adjoin. The blade platforms (17A, 17B) and the peripheral surface (31) define between them an intermediate space (49). A sealing system (51) is provided on the peripheral surface (31) in the intermediate space (49), said sealing system being of the labyrinth box type.
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62.发明公开DICHTUNG ZUR ABDICHTUNG EINES SPALTES, INSBESONDERE IN EINER TURBINE, UND TURBINE 有权密封件密封尤其是GAP在涡轮机和涡轮
公开(公告)号：EP1177367A1
公开(公告)日：2002-02-06
申请号：EP00938634.3
申请日：2000-05-11
发明人： TIEMANN, Peter
CPC分类号： F16J15/0806 , F01D11/005 , F16J15/0887
摘要： The invention relates to a seal (51) for sealing a gap (36). The seal (51) has temperature-dependent expansion properties, so that above a working temperature, the gap (36) is sealed more tightly, as the temperature increases. The gap is sealed by a curved, convex surface of the seal. The invention also relates to a turbine (1), in particular a gas turbine, in which gaps between components (17, 13, 39, 61) are closed by a seal (51).
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公开(公告)号：EP1656493B1
公开(公告)日：2010-11-17
申请号：EP04741140.0
申请日：2004-07-19
发明人： TIEMANN, Peter
CPC分类号： F01D5/3015 , F01D11/001 , F01D11/006 , F01D11/02 , F16J15/4476 , Y10T29/49323
摘要： The invention relates to a segmented inner ring for holding guide blades. According to the invention, a lateral wall opposing the front side of the inner ring and pertaining to a shaft shoulder formed on the rotor shaft extends radially, and respectively one half of a labyrinth seal is formed on the front side of the inner ring and on the shaft shoulder. The aim of the invention is to apply an arrangement of stacked labyrinth seals (28), known from aeroplane turbines, to a stationary gas turbine (1) having a separation plane (61). To this end, a method is used to mount an inner ring (30) of a gas turbine (1). The invention also relates to a stationary gas turbine comprising a segmented inner ring (30).
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公开(公告)号：EP1656523B1
公开(公告)日：2010-09-01
申请号：EP04741085.7
申请日：2004-07-16
发明人： TIEMANN, Peter
CPC分类号： F23R3/04 , F01D25/12 , F23R3/26 , Y02T50/675
摘要： The invention relates to a gas turbine (1), for energy generation, with a compressor (7), arranged coaxially to a rotor (5), mounted such as to rotate, for the compression of an inlet gaseous fluid, at least partly serving for combustion of a fuel in a subsequent annular combustion chamber (9), with generation of a hot working medium (19), with an annular diffuser (15), arranged coaxially to the rotor (5), between the compressor and the annular combustion chamber (9), for distribution and deflection of the fluid (F), whereby a part of the fluid is diverted as cooling fluid for the turbine stages after the combustion chamber, by means of a dividing element (35), arranged in the fluid flow. According to the invention, a compact diffuser (15) and an economical gas turbine (1) with an improved flow for the diversion of cooling air may be achieved, whereby the annular dividing element (35), arranged coaxially to the rotor (5), comprises at least one opening, facing the fluid flow and the dividing element (35) is supported on the diffuser (15), by means of several hollow rib-like support elements (53, 55), by means of which the cooling fluid, diverted through the opening, is first directed towards the rotor (5).
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公开(公告)号：EP1529181B1
公开(公告)日：2008-04-09
申请号：EP03753347.8
申请日：2003-08-01
发明人： TIEMANN, Peter
摘要： A gas turbine combustion chamber (4) comprises a manhole (27) as access to a combustion chamber interior (24), which may be sealed with a manhole cover (28). The manhole (27) comprises an inner cooling chamber and may thus take particularly high thermal loads.
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公开(公告)号：EP1423586B1
公开(公告)日：2007-02-21
申请号：EP02797639.8
申请日：2002-08-28
发明人： TIEMANN, Peter
IPC分类号： F01D9/02
CPC分类号： F01D9/023 , Y02T50/675
摘要： The invention relates to a gas turbine (1) having a combustion chamber arrangement and a turbine chamber (2) connected downstream of said combustion chamber arrangement, wherein the combustion chamber arrangement includes a plurality of individual combustion chambers (3) formed by input areas (4) and transition areas (5) converging in an annular gap leading to the turbine chamber and wherein the longitudinal axes (B) of the individual combustion chambers are placed at an angle relative to an engine axis (M) that is defined by the axial extension of the turbine chamber (2). In order to improve said gas turbine by visibly reducing the thermal and mechanical loads of the individual combustion chambers in the transition area so that cooling requirements can be lowered in said area, the transition area (5) of at least one individual combustion chamber (3) and a corresponding input area (9) of the turbine chamber (2) are embodied in such a way that the gas flow running from the at least one individual combustion chamber (3) into the turbine chamber (2) is deflected in the direction of the engine axis (M) and substantially in the input area (9) of the turbine chamber (2).
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67.发明授权VERFAHREN ZUR HERSTELLUNG EINES EINKRISTALLINEN BAUTEILS KOMPLEXER FORMSTRUKTUR 有权用于生产复杂结构形式的单晶COMPONENT
公开(公告)号：EP1417358B1
公开(公告)日：2007-01-24
申请号：EP02754933.6
申请日：2002-07-24
发明人： TIEMANN, Peter
CPC分类号： C30B11/003 , C30B11/00 , C30B29/52
摘要： The invention relates to a method for producing a monocrystalline component (1), having a complex moulded structure with different structure parts (2, 3), from a molten metal. According to the method, said molten metal is located in a negative mould, corresponding to the moulding structure and said negative mould moves with the formation of a solidification front on a temperature drop, which is adapted to the crystallization speed of the molten metal and which includes the melting point. Said method is characterized in that at least one of the structure parts (2, 3) of the moulded structure experiences an individual temperature drop. If the solidification front has to grow through a structure part (2,3), which is inappropriately oriented in relation to the solidification front (7), said structure part (2,3) or zone can experience an individual temperature drop. This enables monocrystalline components (1), having a complex moulded structure, to be produced in a reliable and economical manner.
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68.发明授权
公开(公告)号：EP1656497B1
公开(公告)日：2006-11-02
申请号：EP04741084.0
申请日：2004-07-16
摘要： The invention relates to a gas turbine (1), comprising an annular combustion chamber (4) and an upstream diffuser (27), with a throughflow essentially parallel to a turbine longitudinal axis (9), at a distance from said axis at least partly less than the annular combustion chamber, in which a compressed gas (K) may be divided into several partial flows (Ki, Ka) at a branching point (36), whereby at least one of the partial flows (Ki, Ka) is a cooling gas flow. A main deflection region (30) is provided in said diffuser (27), directed at an angle to the turbine longitudinal axis (9) towards the annular combustion chamber (4).
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公开(公告)号：EP1656523A2
公开(公告)日：2006-05-17
申请号：EP04741085.7
申请日：2004-07-16
发明人： TIEMANN, Peter
CPC分类号： F23R3/04 , F01D25/12 , F23R3/26 , Y02T50/675
摘要： The invention relates to a gas turbine (1), for energy generation, with a compressor (7), arranged coaxially to a rotor (5), mounted such as to rotate, for the compression of an inlet gaseous fluid, at least partly serving for combustion of a fuel in a subsequent annular combustion chamber (9), with generation of a hot working medium (19), with an annular diffuser (15), arranged coaxially to the rotor (5), between the compressor and the annular combustion chamber (9), for distribution and deflection of the fluid (F), whereby a part of the fluid is diverted as cooling fluid for the turbine stages after the combustion chamber, by means of a dividing element (35), arranged in the fluid flow. According to the invention, a compact diffuser (15) and an economical gas turbine (1) with an improved flow for the diversion of cooling air may be achieved, whereby the annular dividing element (35), arranged coaxially to the rotor (5), comprises at least one opening, facing the fluid flow and the dividing element (35) is supported on the diffuser (15), by means of several hollow rib-like support elements (53, 55), by means of which the cooling fluid, diverted through the opening, is first directed towards the rotor (5).
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70.发明公开DIFFUSOR ZWISCHEN VERDICHTER UND BRENNKAMMER EINER GASTURBINE ANGEORDNET 有权DIFFUSOR ZWISCHEN VERDICHTER UND BRENNKAMMER EINER GASURBINE ANGEORDNET
公开(公告)号：EP1656497A1
公开(公告)日：2006-05-17
申请号：EP04741084.0
申请日：2004-07-16
摘要： The invention relates to a gas turbine (1), comprising an annular combustion chamber (4) and an upstream diffuser (27), with a throughflow essentially parallel to a turbine longitudinal axis (9), at a distance from said axis at least partly less than the annular combustion chamber, in which a compressed gas (K) may be divided into several partial flows (Ki, Ka) at a branching point (36), whereby at least one of the partial flows (Ki, Ka) is a cooling gas flow. A main deflection region (30) is provided in said diffuser (27), directed at an angle to the turbine longitudinal axis (9) towards the annular combustion chamber (4).
摘要翻译： 本发明涉及一种燃气涡轮机（1），其包括环形燃烧室（4）和上游扩散器（27），其具有基本平行于涡轮机纵向轴线（9）的通流部，距离所述轴线至少部分地 小于环形燃烧室，其中压缩气体（K）可在分支点（36）处分成若干分流（Ki，Ka），由此至少一个分流（Ki，Ka）为 冷却气流。 在所述扩散器（27）中设置主偏转区域（30），所述主偏转区域（30）与涡轮纵向轴线（9）成角度地朝向环形燃烧室（4）。
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