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1.发明公开
公开(公告)号：EP1412618A1
公开(公告)日：2004-04-28
申请号：EP02751160.9
申请日：2002-07-24
发明人： REICHERT, Arnd
CPC分类号： F01D9/023 , F01D11/005 , F16J15/0893 , F16J15/121 , Y02T50/675
摘要： The invention pertains to a seal element (1) for sealing a gap (5), in particular within a turbo-machinery, between a first component (2) and a second components (3) spaced apart from each other, said first component (2) having a first surface (9) and said second component (3) having an opposing second surfaces (10). The seal element (1) comprises a support structure (4) and a sealing structure (6) covering at least partially said support structure (4). The support structure (4) comprises at least two contacting members (8), each contacting member (8) serves for putting a portion of the sealing structure (6) in contact with one of the surfaces (9, 10) and being capable of following a deformation of said surface (9, 10). The invention further pertains to a combustion turbine (22), wherein a gap (5) is formed between a first surface (9) and a second surface (10), which gap (5) is sealed off by said seal element (1).
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公开(公告)号：EP1084327B1
公开(公告)日：2003-11-05
申请号：EP99936381.5
申请日：1999-06-01
发明人： REICHERT, Arnd
CPC分类号： F01D25/12 , F01D5/081 , F01D5/18 , Y02T50/676
摘要： The invention relates to a gas turbine (4) with a turbine stage (24) having a vane (26) and an admission (32) for cooling air (K) with a cooling air outlet (34). The turbine stage (24) can be cooled by means of the cooling air (K), whereby the cooling air admission (32) has means so that a predetermined pressure of the cooling air (K) on the cooling air outlet (34) can be regulated.
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3.发明公开
公开(公告)号：EP1131537A1
公开(公告)日：2001-09-12
申请号：EP99959231.4
申请日：1999-11-02
发明人： REICHERT, Arnd , BECKER, Bernard
CPC分类号： F16C32/0692 , F01D11/22 , F01D25/166 , F05D2240/53 , F16C17/04 , F16C25/02 , F16C32/067 , F16C32/0696
摘要： The invention relates to shaft bearing (1) for the rotor (2) of a turbo-machine (19) which extends along a rotor pin (3). Said shaft bearing (1) has a bearing element (5) with a bearing surface (15). Said bearing surface (15) supports an associated rotor surface (7) and the bearing element (5) can be axially displaced. The invention further relates to a turbo-machine (19) and to a method for operating said turbo-machine (19).
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公开(公告)号：EP1706597B1
公开(公告)日：2009-03-11
申请号：EP05701049.8
申请日：2005-01-19
发明人： STÖCKER, Bernd , REICHERT, Arnd
CPC分类号： F01D11/02 , F01D11/22 , F04D29/052 , F04D29/164 , F05D2250/312 , F05D2250/314
摘要： The invention relates to a compressor (5), which is axially flowed through, for a gas turbine (1) having an axially displaceable rotor (3). An annular flow channel (24), which narrows in an axial direction, is formed between a rotationally fixed outer delimiting surface (37) and an inner delimiting surface (36) on the rotor (3). A stationary ring (15) comprised of guide profiles (28) and at least one ring (17) comprised of moving profiles (27) attached to the rotor are placed inside said annular flow channel. The end of each moving or guide blade (14, 16) is located opposite an axial section (A) of one of both delimiting surfaces (36, 37) while forming a radial gap (23). The aim of the invention is to provide a non-positive-displacement machine having an axially displaceable rotor whose velocity losses are at least not increased during an axial displacement of the rotor. To this end, the invention provides that the size of the radial gap (23) between the end of each moving or guide blade (14, 16) and the opposite axial section (A) of the delimiting surface (36, 37) is constant at least over the path of displacement of the rotor (3), and the radial gap (23) extends parallel to the rotation axis (2) of the rotor (3).
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5.发明公开VORRICHTUNG UND VERFAHREN ZUR REGELUNG EINES KÜHLLUFTSTROMS EINER GASTURBINE, SOWIE EINE KÜHLLUFTDURCHSTRÖMTE GASTURBINE 有权装置和方法用于控制燃气涡轮机的冷却空气流和冷却空气通过其流动的燃气涡轮
公开(公告)号：EP1200744A1
公开(公告)日：2002-05-02
申请号：EP00953106.2
申请日：2000-07-27
发明人： REICHERT, Arnd , LIESER, Dirk
摘要： The invention relates to a device for controlling a cooling air flow (1) according to needs, especially a gas turbine cooling air flow (1'), with low maintenance means, whereby the cooling air flow flows through a flow channel (2) and a control fluid flow (30) is introduced into the flow channel (2) in said cooling air flow (1) with a flow component (9) which is perpendicular to the flow direction (35) of said cooling air flow (1). The flow rate of the cooling air flow (1) can therefore be adjusted on the basis of control parameters of the control fluid flow (30) and/or other parameters.
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6.发明授权VORRICHTUNG UND VERFAHREN ZUR REGELUNG EINES KÜHLLUFTSTROMS EINER GASTURBINE, SOWIE EINE KÜHLLUFTDURCHSTRÖMTE GASTURBINE 有权装置和方法用于控制燃气涡轮机的冷却空气流和冷却空气通过其流动的燃气涡轮
公开(公告)号：EP1200744B1
公开(公告)日：2005-04-06
申请号：EP00953106.2
申请日：2000-07-27
发明人： REICHERT, Arnd , LIESER, Dirk
摘要： The invention relates to a device for controlling a cooling air flow (1) according to needs, especially a gas turbine cooling air flow (1'), with low maintenance means, whereby the cooling air flow flows through a flow channel (2) and a control fluid flow (30) is introduced into the flow channel (2) in said cooling air flow (1) with a flow component (9) which is perpendicular to the flow direction (35) of said cooling air flow (1). The flow rate of the cooling air flow (1) can therefore be adjusted on the basis of control parameters of the control fluid flow (30) and/or other parameters.
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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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公开(公告)号：EP3396114A1
公开(公告)日：2018-10-31
申请号：EP17168744.5
申请日：2017-04-28
发明人： REICHERT, Arnd
CPC分类号： F01D11/02 , F01D11/001 , F01D11/127 , F01D11/18 , F01D11/22 , F05D2250/232
摘要： The invention relates to a turbomachinery, in particular a gas turbine, having a casing through which a working fluid flows during operation in a direction of flow (F), an axially displaceable rotor arranged in the casing and an annular seal (8). In order to minimize the leakage mass flows of the working fluid in the turbomachinery during operation, the annular seal (8) comprises an inner seal member (8a) having a plurality of axially spaced, radially projecting seal elements (10), wherein the inner seal member (8a) is attached to a rotor component (2), and an outer seal member (8b) consisting of a plurality of seal segments (12), each seal segment (12) having a conical shape with a diameter increasing in the direction of flow (F), wherein the outer seal member (8b) is attached to a casing component (4).
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9.发明授权
公开(公告)号：EP1412618B1
公开(公告)日：2009-01-07
申请号：EP02751160.9
申请日：2002-07-24
发明人： REICHERT, Arnd
CPC分类号： F01D9/023 , F01D11/005 , F16J15/0893 , F16J15/121 , Y02T50/675
摘要： The invention pertains to a seal element (1) for sealing a gap (5), in particular within a turbo-machinery, between a first component (2) and a second components (3) spaced apart from each other, said first component (2) having a first surface (9) and said second component (3) having an opposing second surfaces (10). The seal element (1) comprises a support structure (4) and a sealing structure (6) covering at least partially said support structure (4). The support structure (4) comprises at least two contacting members (8), each contacting member (8) serves for putting a portion of the sealing structure (6) in contact with one of the surfaces (9, 10) and being capable of following a deformation of said surface (9, 10). The invention further pertains to a combustion turbine (22), wherein a gap (5) is formed between a first surface (9) and a second surface (10), which gap (5) is sealed off by said seal element (1).
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公开(公告)号：EP1706597A1
公开(公告)日：2006-10-04
申请号：EP05701049.8
申请日：2005-01-19
发明人： STÖCKER, Bernd , REICHERT, Arnd
CPC分类号： F01D11/02 , F01D11/22 , F04D29/052 , F04D29/164 , F05D2250/312 , F05D2250/314
摘要： The invention relates to a compressor (5), which is axially flowed through, for a gas turbine (1) having an axially displaceable rotor (3). An annular flow channel (24), which narrows in an axial direction, is formed between a rotationally fixed outer delimiting surface (37) and an inner delimiting surface (36) on the rotor (3). A stationary ring (15) comprised of guide profiles (28) and at least one ring (17) comprised of moving profiles (27) attached to the rotor are placed inside said annular flow channel. The end of each moving or guide blade (14, 16) is located opposite an axial section (A) of one of both delimiting surfaces (36, 37) while forming a radial gap (23). The aim of the invention is to provide a non-positive-displacement machine having an axially displaceable rotor whose velocity losses are at least not increased during an axial displacement of the rotor. To this end, the invention provides that the size of the radial gap (23) between the end of each moving or guide blade (14, 16) and the opposite axial section (A) of the delimiting surface (36, 37) is constant at least over the path of displacement of the rotor (3), and the radial gap (23) extends parallel to the rotation axis (2) of the rotor (3).
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