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1. 发明授权

US5662418A High temperature probe 失效
标题翻译：高温探头
公开(公告)号：US5662418A
公开(公告)日：1997-09-02
申请号：US496412
申请日：1995-06-29
申请人： Anton F. Deak , Dieter Glaser , Caroline Marchmont , Ung-Lap Ngo-Beelmann
发明人： Anton F. Deak , Dieter Glaser , Caroline Marchmont , Ung-Lap Ngo-Beelmann
IPC分类号： G01K1/08 , F02C7/00 , G01K7/02 , G01K13/02
CPC分类号： G01K13/02
摘要： In a high temperature probe (10), in particular for use in the hot gas stream of a gas turbine at temperatures of up to 1200.degree. C., which high temperature probe (10) comprises a metallic probe tube (11) having an internal drilled hole (12, 13) running in the direction of the tube axis of the probe tube (11) and a measurement space arranged at the lower end, which measurement space is separated from the internal drilled hole (12, 13) by a constriction (16a, b) and is in contact with the surroundings of the probe tube (11), and which high temperature probe (10) furthermore comprises at least one thermocouple (31, 32) which is conducted downwards in an insulated manner in the internal drilled hole (12, 13) and through the constriction (16a, b) into the measurement space, a high accuracy at a low time constant is achieved by the measurement space being configured as a flow-through channel (15) for the hot gases to be measured, which channel is oriented at right angles to the direction of the tube axis and runs through the probe tube (11) with one internal width (W), and by the thermocouple (31, 32), of which there is at least one, being arranged with its connection point (47) within the flow-through channel (15).
摘要翻译：在高温探针（10）中，特别是在高达1200℃的温度下用于燃气轮机的热气流中，该高温探针（10）包括具有内部的金属探针管（11）在探针管（11）的管轴方向上延伸的钻孔（12,13）和设置在下端的测量空间，该测量空间通过收缩与内钻孔（12,13）分离（16a，b）并且与探针管（11）的周围接触，并且该高温探头（10）还包括至少一个热电偶（31,32），该热电偶以内绝缘的方式向下传导钻孔（12,13）并且通过收缩部（16a，b）进入测量空间，通过测量空间被配置为用于热气体的流通通道（15），实现了低时间常数的高精度要测量，哪个通道与方向成直角所述管轴线穿过具有一个内部宽度（W）的所述探针管（11），并且通过所述热电偶（31,32）至少具有一个，其连接点（47）布置在所述流体内通过通道（15）。

2. 发明授权

US5812588A Temperature probe 失效
标题翻译：温度探头
公开(公告)号：US5812588A
公开(公告)日：1998-09-22
申请号：US743935
申请日：1996-11-05
申请人： Anton Deak , Caroline Marchmont , Ung-Lap Ngo-Beelmann
发明人： Anton Deak , Caroline Marchmont , Ung-Lap Ngo-Beelmann
IPC分类号： G01K1/12 , G01K7/02 , H01L35/02
CPC分类号： G01K1/12
摘要： In a temperature probe, in particular for use in the waste-gas diffusor of a gas turbine, a probe tube (1) projecting into the hot-gas region of the waste-gas diffusor is provided with an inner bore running in the direction of the tube axis of the probe tube (1). At the same time, the probe tube (1) is provided over its length with a number of throughflow ducts running transversely relative to the tube axis and in which are located a number of thermocouples (22), the connecting points (23) of which are arranged in the throughflow ducts. The thermocouples (22) are connected to a compensating line (13) in a terminal box (14). Each thermocouple (22) is arranged in a solely heat-movably guided manner in a protective tube (18) which is fixed relative to the inner bore of the probe tube (1).
摘要翻译：特别是在燃气轮机的废气扩散器中使用的温度探头中，向废气扩散器的热气体区域突出的探针管（1）设置有沿着探针管（1）的管轴。同时，探针管（1）在其长度上设置有相对于管轴线横向延伸的多个通流管，并且其中定位有多个热电偶（22），其中的连接点（23）布置在通流管道中。热电偶（22）连接到接线盒（14）中的补偿线（13）。每个热电偶（22）以仅仅热可移动的方式布置在相对于探针管（1）的内孔固定的保护管（18）中。

3. 发明申请

US20110223036A1 BLADE FOR A GAS TURBINE 有权
标题翻译：燃气轮机叶片
公开(公告)号：US20110223036A1
公开(公告)日：2011-09-15
申请号：US13071219
申请日：2011-03-24
申请人： Thomas Wilhelm , Caroline Marchmont , Sergei Riazantsev
发明人： Thomas Wilhelm , Caroline Marchmont , Sergei Riazantsev
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/225
摘要： The blade for a gas turbine includes a blade airfoil having a leading edge and a trailing edge and extending in the blade longitudinal direction up to a blade tip, and at the blade tip the blade airfoil merges into a shroud segment, wherein on the shroud segment a first rib, projecting upwards, is arranged in the flow direction, extending transversely to the flow direction, and upstream of the first rib, in the region of the leading edge of the blade airfoil, a winglet is formed on the shroud segment for guiding of the hot gas flow in this region. With such a blade, a longer service life is achieved by provision being made for direct cooling of the winglet.
摘要翻译：用于燃气涡轮的叶片包括具有前缘和后缘并且在叶片纵向方向上延伸直到叶片尖端的叶片翼型件，并且在叶片尖端处，叶片翼型件合并成护罩段，其中在护罩段向上突出的第一肋沿流动方向布置，横向于流动方向延伸，并且在第一肋的上游处在叶片翼型的前缘的区域中，在护罩段上形成小翼以用于引导的热气流在这个地区。利用这种叶片，通过提供用于小翼的直接冷却来实现更长的使用寿命。

4. 发明授权

US08764395B2 Blade for a gas turbine 有权
标题翻译：燃气轮机叶片
公开(公告)号：US08764395B2
公开(公告)日：2014-07-01
申请号：US13071219
申请日：2011-03-24
申请人： Thomas Wilhelm , Caroline Marchmont , Sergei Riazantsev
发明人： Thomas Wilhelm , Caroline Marchmont , Sergei Riazantsev
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/225
摘要： The blade for a gas turbine includes a blade airfoil having a leading edge and a trailing edge and extending in the blade longitudinal direction up to a blade tip, and at the blade tip the blade airfoil merges into a shroud segment, wherein on the shroud segment a first rib, projecting upwards, is arranged in the flow direction, extending transversely to the flow direction, and upstream of the first rib, in the region of the leading edge of the blade airfoil, a winglet is formed on the shroud segment for guiding of the hot gas flow in this region. With such a blade, a longer service life is achieved by provision being made for direct cooling of the winglet.
摘要翻译：用于燃气涡轮的叶片包括具有前缘和后缘并且在叶片纵向方向上延伸直到叶片尖端的叶片翼型件，并且在叶片尖端处，叶片翼型件合并成护罩段，其中在护罩段向上突出的第一肋沿流动方向布置，横向于流动方向延伸，并且在第一肋的上游处在叶片翼型的前缘的区域中，在护罩段上形成小翼以用于引导的热气流在这个地区。利用这种叶片，通过提供用于小翼的直接冷却来实现更长的使用寿命。

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