专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明授权

US08152463B2 Method for impingement air cooling for gas turbines 有权
标题翻译：燃气轮机冲击空气冷却方法
公开(公告)号：US08152463B2
公开(公告)日：2012-04-10
申请号：US12071156
申请日：2008-02-15
申请人： Frank Haselbach , Erik Janke , Jens Taege , Timm Janetzke , Wolfgang Nitsche , Matthias Reyer
发明人： Frank Haselbach , Erik Janke , Jens Taege , Timm Janetzke , Wolfgang Nitsche , Matthias Reyer
IPC分类号： F01D5/18
CPC分类号： F01D25/12 , F01D5/187 , F05D2260/201 , F23R2900/03044
摘要： In impingement air cooling of gas turbine components, cooling air velocity packs of a certain amplitude and a given frequency are applied to impingement air openings, with intervallic annular swirl structures being formed which penetrate a cross-flow and hit a component to be cooled with high intensity, thus providing for efficient cooling. In order to obtain annular swirl structures with optimum cooling effect, the Strouhal number, which is determined by a ratio of amplitude, frequency of the velocity packs and size of impingement air cooling openings, ranges between 0.2 and 2.0, and preferably between 0.8 and 1.2.
摘要翻译：在燃气轮机部件的冲击空气冷却中，将一定幅度和给定频率的冷却空气速度组件施加到冲击空气开口，形成贯穿横流的金属间环形涡流结构，并以高的速度撞击要冷却的部件强度，从而提供有效的冷却。为了获得具有最佳冷却效果的环形涡旋结构，由振幅，速度包的频率和冲击空气冷却开口的尺寸确定的Strouhal数范围在0.2和2.0之间，优选在0.8和1.2之间。

2. 发明授权

US4934197A Method of measuring pressures and forces acting on arbitrarily shaped bodies 失效
标题翻译：测量作用在任意成形体上的压力和力的方法
公开(公告)号：US4934197A
公开(公告)日：1990-06-19
申请号：US241325
申请日：1988-09-06
申请人： Wolfgang Nitsche
发明人： Wolfgang Nitsche
IPC分类号： G01L1/16
CPC分类号： G01L1/16
摘要： An indication is given of a method, and simultaneously of an apparatus, for measuring pressures and forces acting on arbitrarily shaped bodies. Employed in this connection is a piezoelectric film, which is provided on both sides with a metal coating. The piezoelectric film is bonded onto the body, and a charge variation of the piezoelectric film is evaluated in an evaluation unit, and employed as measure for the force acting on the body, or for the pressure. The metal coating (5) is partially removed from one side of the piezoelectric film (2) to form individual sensors (3, 4). Each individual sensor (3, 4) is coupled to the evaluation unit (10) via an electrical connection (8, 9). The other side of the piezoelectric film (2) with the continuous metal coating (5) serves as electronic shield and is connected to earth (7). The charge variation of each individual sensor (3, 4) serves as measure for the local force or the local pressure.
摘要翻译：给出了一种用于测量作用在任意形状的体上的压力和力的装置的方法和方法。在这方面所用的是一种压电薄膜，它在两侧设置有金属涂层。将压电膜接合到主体上，并且在评估单元中评估压电膜的电荷变化，并且用作作用于身体或作用于压力的力的量度。从压电膜（2）的一侧部分地去除金属涂层（5）以形成单独的传感器（3,4）。每个单独的传感器（3,4）经由电连接（8,9）耦合到评估单元（10）。具有连续金属涂层（5）的压电膜（2）的另一侧用作电子屏蔽并连接到地（7）。每个传感器（3,4）的充电变化用作局部力或局部压力的量度。

3. 发明授权

US09014877B2 Aircraft with a control device 有权
标题翻译：具有控制装置的飞机
公开(公告)号：US09014877B2
公开(公告)日：2015-04-21
申请号：US13525282
申请日：2012-06-16
申请人： Burkhard Gölling , Frank Haucke , Matthias Bauer , Wolfgang Nitsche , Inken Peltzer
发明人： Burkhard Gölling , Frank Haucke , Matthias Bauer , Wolfgang Nitsche , Inken Peltzer
IPC分类号： B64C15/00 , B64C29/00 , B64C23/00
CPC分类号： B64C23/005 , B64C9/16 , B64C9/38 , B64C13/18 , B64C21/04 , B64C29/0025 , Y02T50/166
摘要： An aircraft with aerofoils including a main wing and a control flap that includes an adjustment flap. The aircraft includes an actuator for the control flap, as well as a sensor device for acquiring the position of the control flap, an arrangement of flow-influencing devices for influencing the fluid that flows over a segment of the main wing, and flow-state sensor devices for measuring the flow state. The aircraft includes a flight control device connected to the sensor device for acquiring the position of the control flap and to the flow-state sensor devices, and connected to the actuator and flow-influencing devices for transmitting actuating commands, and a flight-state sensor device connected to the flight control device for transmitting flight states. The flight control device includes a function that selects the flow-influencing devices that are operated for optimizing local lift coefficients on the aerofoil, depending on the flight state.
摘要翻译：具有机翼的飞机包括主翼和包括调节翼片的控制翼片。飞机包括用于控制翼片的致动器，以及用于获取控制翼片的位置的传感器装置，用于影响流过主翼片段的流体的流动影响装置的布置，以及流动状态用于测量流动状态的传感器装置。飞机包括连接到传感器装置的飞行控制装置，用于获取控制翼片和流动状态传感器装置的位置，并连接到用于传送致动指令的致动器和流量影响装置，以及飞行状态传感器连接到飞行控制装置的装置用于传送飞行状态。飞行控制装置包括根据飞行状态选择用于优化机翼上的局部升力系数的流量影响装置的功能。

4. 发明申请

US20130035808A1 AIRCRAFT WITH A CONTROL DEVICE 有权
标题翻译：具有控制装置的飞机
公开(公告)号：US20130035808A1
公开(公告)日：2013-02-07
申请号：US13525282
申请日：2012-06-16
申请人： Burkhard GÖLLING , Frank HAUCKE , Matthias BAUER , Wolfgang NITSCHE , Inken PELTZER
发明人： Burkhard GÖLLING , Frank HAUCKE , Matthias BAUER , Wolfgang NITSCHE , Inken PELTZER
IPC分类号： B64C13/16 , B64C9/00 , B64C21/00 , B64C13/24
CPC分类号： B64C23/005 , B64C9/16 , B64C9/38 , B64C13/18 , B64C21/04 , B64C29/0025 , Y02T50/166
摘要： An aircraft with aerofoils including a main wing and a control flap that includes an adjustment flap. The aircraft includes an actuator for the control flap, as well as a sensor device for acquiring the position of the control flap, an arrangement of flow-influencing devices for influencing the fluid that flows over a segment of the main wing, and flow-state sensor devices for measuring the flow state. The aircraft includes a flight control device connected to the sensor device for acquiring the position of the control flap and to the flow-state sensor devices, and connected to the actuator and flow-influencing devices for transmitting actuating commands, and a flight-state sensor device connected to the flight control device for transmitting flight states. The flight control device includes a function that selects the flow-influencing devices that are operated for optimising local lift coefficients on the aerofoil, depending on the flight state.
摘要翻译：具有机翼的飞机包括主翼和包括调节翼片的控制翼片。飞机包括用于控制翼片的致动器，以及用于获取控制翼片的位置的传感器装置，用于影响流过主翼片段的流体的流动影响装置的布置，以及流动状态用于测量流动状态的传感器装置。飞机包括连接到传感器装置的飞行控制装置，用于获取控制翼片和流动状态传感器装置的位置，并连接到用于传送致动指令的致动器和流量影响装置，以及飞行状态传感器连接到飞行控制装置的装置用于传送飞行状态。飞行控制装置包括根据飞行状态选择用于优化机翼上的局部升力系数的流量影响装置的功能。

5. 发明申请

US20080226441A1 Method for impingement air cooling for gas turbines 有权
标题翻译：燃气轮机冲击空气冷却方法
公开(公告)号：US20080226441A1
公开(公告)日：2008-09-18
申请号：US12071156
申请日：2008-02-15
申请人： Frank Haselbach , Erik Janke , Jens Taege , Timm Janetzke , Wolfgang Nitsche , Matthias Reyer
发明人： Frank Haselbach , Erik Janke , Jens Taege , Timm Janetzke , Wolfgang Nitsche , Matthias Reyer
IPC分类号： F01D25/08
CPC分类号： F01D25/12 , F01D5/187 , F05D2260/201 , F23R2900/03044
摘要： In impingement air cooling of gas turbine components, cooling air velocity packs of a certain amplitude and a given frequency are applied to impingement air openings, with intervallic annular swirl structures being formed which penetrate a cross-flow and hit a component to be cooled with high intensity, thus providing for efficient cooling. In order to obtain annular swirl structures with optimum cooling effect, the Strouhal number, which is determined by a ratio of amplitude, frequency of the velocity packs and size of impingement air cooling openings, ranges between 0.2 and 2.0, and preferably between 0.8 and 1.2.
摘要翻译：在燃气轮机部件的冲击空气冷却中，将一定幅度和给定频率的冷却空气速度组件施加到冲击空气开口，形成贯穿横流的金属间环形涡流结构，并以高的速度撞击要冷却的部件强度，从而提供高效的冷却。为了获得具有最佳冷却效果的环形涡旋结构，由振幅，速度包的频率和冲击空气冷却开口的尺寸确定的Strouhal数范围在0.2和2.0之间，优选在0.8和1.2之间。

6. 发明授权

US08645007B2 Aircraft with an arrangement of flow-influencing devices 有权
标题翻译：具有流量影响装置布置的飞机
公开(公告)号：US08645007B2
公开(公告)日：2014-02-04
申请号：US13491629
申请日：2012-06-08
申请人： Burkhard Gölling , Rudibert King , Ulrich Notger Heinz , Wolfgang Nitsche
发明人： Burkhard Gölling , Rudibert King , Ulrich Notger Heinz , Wolfgang Nitsche
IPC分类号： B64C19/00
CPC分类号： B64C21/025 , B64C21/08 , B64C2230/02 , Y02T50/166
摘要： An aircraft, which has a respective arrangement of flow-influencing devices in at least one surface segment of each wing extending in the wingspan direction in order to influence the fluid flow over the surface segment, and of flow condition sensor devices for measuring the flow condition on the respective segment, and a flight control device, wherein the flight control device has a flow-influencing target parameter setting device connected with the arrangement of flow-influencing devices for generating target parameters for the flow-influencing devices of the at least one surface segment, wherein the flow-influencing devices are designed in such a way as to use the target parameters to change the local lift coefficients or correlations between the drag and lift coefficients in the segment where respectively located.
摘要翻译：一种飞机，其在每个机翼的至少一个表面段中具有相应的流量影响装置的布置，其在翼展方向上延伸以便影响表面段上的流体流动，以及用于测量流动状态的流动状态传感器装置在飞行控制装置上，其中所述飞行控制装置具有流量影响目标参数设定装置，该流量影响目标参数设定装置与所述流量影响装置的装置连接，用于产生所述至少一个表面的流量影响装置的目标参数其中所述流量影响装置被设计成使用所述目标参数来改变所述局部升力系数或在分别位于所述段的所述牵引系数和升力系数之间的相关性。

7. 发明授权

US2827062A Conveying apparatus 失效
标题翻译：输送装置
公开(公告)号：US2827062A
公开(公告)日：1958-03-18
申请号：US49406155
申请日：1955-03-14
申请人： WOLFGANG NITSCHE KARL PAUL
发明人： WOLFGANG NITSCHE KARL PAUL
IPC分类号： B65G27/00
CPC分类号： B65G27/00 , B65G2812/0392

8. 发明申请

US20130166110A1 AIRCRAFT WITH AN ARRANGEMENT OF FLOW-INFLUENCING DEVICES 有权
标题翻译：具有流量流动装置安排的飞机
公开(公告)号：US20130166110A1
公开(公告)日：2013-06-27
申请号：US13491629
申请日：2012-06-08
申请人： Burkhard Gölling , Rudibert KING , Ulrich Notger HEINZ , Wolfgang NITSCHE
发明人： Burkhard Gölling , Rudibert KING , Ulrich Notger HEINZ , Wolfgang NITSCHE
IPC分类号： B64C19/00
CPC分类号： B64C21/025 , B64C21/08 , B64C2230/02 , Y02T50/166
摘要： An aircraft, which has a respective arrangement of flow-influencing devices in at least one surface segment of each wing extending in the wingspan direction in order to influence the fluid flow over the surface segment, and of flow condition sensor devices for measuring the flow condition on the respective segment, and a flight control device, wherein the flight control device has a flow-influencing target parameter setting device connected with the arrangement of flow-influencing devices for generating target parameters for the flow-influencing devices of the at least one surface segment, wherein the flow-influencing devices are designed in such a way as to use the target parameters to change the local lift coefficients or correlations between the drag and lift coefficients in the segment where respectively located.
摘要翻译：一种飞机，其在每个机翼的至少一个表面段中具有相应的流量影响装置的布置，其在翼展方向上延伸以便影响表面段上的流体流动，以及用于测量流动状态的流动状态传感器装置在飞行控制装置上，其中所述飞行控制装置具有流量影响目标参数设定装置，该流量影响目标参数设定装置与所述流量影响装置的装置连接，用于产生所述至少一个表面的流量影响装置的目标参数其中所述流量影响装置被设计成使用所述目标参数来改变所述局部升力系数或在分别位于所述段的所述牵引系数和升力系数之间的相关性。

9. 发明授权

US2888939A Apparatus for cleaning or similar treatment of metallic articles 失效
标题翻译：用于清洁或类似处理金属制品的装置
公开(公告)号：US2888939A
公开(公告)日：1959-06-02
申请号：US49402755
申请日：1955-03-14
申请人： WOLFGANG NITSCHE KARL PAUL
发明人： WOLFGANG NITSCHE KARL PAUL
IPC分类号： B08B3/12
CPC分类号： B08B3/12

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式