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1.发明申请High Temperature Pressure Sensor Element, Particularly for Measuring Pressures Inside Jet Engines, Method for the Production Thereof and Component for Jet Engines 有权高温压力传感器元件，特别是用于喷射发动机内部的测量压力，其生产方法和喷射发动机部件公开(公告)号：US20090183573A1
公开(公告)日：2009-07-23
申请号：US12281946
申请日：2007-03-01
申请人： Soeren Fricke , Gerhard Mueller , Alois Friedberger , Eberhard Rose , Thomas Ziemann , Ulrich Schmid , Dimitri Telitschkin , Stefan Ziegenhagen
发明人： Soeren Fricke , Gerhard Mueller , Alois Friedberger , Eberhard Rose , Thomas Ziemann , Ulrich Schmid , Dimitri Telitschkin , Stefan Ziegenhagen
CPC分类号： G01L9/0051 , G01L19/04 , G01L23/18 , Y10T29/49826
摘要： A high-temperature pressure sensor element for power units includes a substrate, in which an interior space is developed, a deformable membrane, which separates the interior space from the exterior space in order to deform when the exterior pressure changes, and a strain measuring element, which is arranged on the membrane, for measuring the deformation of the membrane. The substrate, the membrane, and the strain measuring element are manufactured from the same high-temperature-stable material, such as an alloy. By way of example a nickel base alloy may be used. A component for a power unit, such as a turbine blade for an airplane or rocket engine, includes an integrated high-temperature pressure sensor element of this type.
摘要翻译： 用于动力单元的高温压力传感器元件包括其中内部空间被展开的基板，可变形的膜，其将内部空间与外部空间分离以在外部压力变化时变形，并且应变测量元件 ，其布置在膜上，用于测量膜的变形。 基板，膜和应变测量元件由相同的高温稳定材料如合金制造。 作为示例，可以使用镍基合金。 用于动力单元的部件，例如用于飞机或火箭发动机的涡轮机叶片，包括这种类型的集成的高温压力传感器元件。
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公开(公告)号：US08407980B2
公开(公告)日：2013-04-02
申请号：US12068261
申请日：2008-02-05
IPC分类号： F03H1/00
CPC分类号： F02K9/62 , F05D2250/82 , Y10T29/49346
摘要： Microthruster includes a combustion chamber comprising a substrate material, a fuel inlet, and a gas outlet. A first resistance heater is arranged in the combustion chamber. A catalyst is structured and arranged to decompose fuel entering the combustion chamber. First substrate material sections are heated by the first resistance heater to at least one of a predetermined temperature and a predetermined temperature range.
摘要翻译： 微型推进器包括燃烧室，其包括基材，燃料入口和气体出口。 第一电阻加热器布置在燃烧室中。 催化剂被构造和布置成分解进入燃烧室的燃料。 第一基板材料部分被第一电阻加热器加热到预定温度和预定温度范围中的至少一个。
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3.发明授权High temperature pressure sensor element, particularly for measuring pressures inside jet engines, method for the production thereof and component for jet engines 有权高温压力传感器元件，特别用于测量喷气发动机内部的压力，其生产方法和喷气发动机部件公开(公告)号：US08001844B2
公开(公告)日：2011-08-23
申请号：US12281946
申请日：2007-03-01
申请人： Soeren Fricke , Gerhard Mueller , Alois Friedberger , Eberhard Rose , Thomas Ziemann , Ulrich Schmid , Dimitri Telitschkin , Stefan Ziegenhagen
发明人： Soeren Fricke , Gerhard Mueller , Alois Friedberger , Eberhard Rose , Thomas Ziemann , Ulrich Schmid , Dimitri Telitschkin , Stefan Ziegenhagen
IPC分类号： G01L13/02
CPC分类号： G01L9/0051 , G01L19/04 , G01L23/18 , Y10T29/49826
摘要： A high-temperature pressure sensor element for power units includes a substrate, in which an interior space is developed, a deformable membrane, which separates the interior space from the exterior space in order to deform when the exterior pressure changes, and a strain measuring element, which is arranged on the membrane, for measuring the deformation of the membrane. The substrate, the membrane, and the strain measuring element are manufactured from the same high-temperature-stable material, such as an alloy. By way of example a nickel base alloy may be used. A component for a power unit, such as a turbine blade for an airplane or rocket engine, includes an integrated high-temperature pressure sensor element of this type.
摘要翻译： 用于动力单元的高温压力传感器元件包括其中内部空间被展开的基板，可变形的膜，其将内部空间与外部空间分离以在外部压力变化时变形，并且应变测量元件 ，其布置在膜上，用于测量膜的变形。 基板，膜和应变测量元件由相同的高温稳定材料如合金制造。 作为示例，可以使用镍基合金。 用于动力单元的部件，例如用于飞机或火箭发动机的涡轮机叶片，包括这种类型的集成的高温压力传感器元件。
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4.发明申请Microthruster, in particular for use as a position adjustment thruster, thruster and method for producing a microthruster 有权微型推进器，特别用作位置调整推进器，推进器和用于产生微型推进器的方法公开(公告)号：US20090120056A1
公开(公告)日：2009-05-14
申请号：US12068261
申请日：2008-02-05
CPC分类号： F02K9/62 , F05D2250/82 , Y10T29/49346
摘要： Microthruster includes a combustion chamber comprising a substrate material, a fuel inlet, and a gas outlet. A first resistance heater is arranged in the combustion chamber. A catalyst is structured and arranged to decompose fuel entering the combustion chamber. First substrate material sections are heated by the first resistance heater to at least one of a predetermined temperature and a predetermined temperature range. This Abstract is not intended to define the invention disclosed in the specification, nor intended to limit the scope of the invention in any way.
摘要翻译： 微型推进器包括燃烧室，其包括基材，燃料入口和气体出口。 第一电阻加热器布置在燃烧室中。 催化剂被构造和布置成分解进入燃烧室的燃料。 第一基板材料部分被第一电阻加热器加热到预定温度和预定温度范围中的至少一个。 本摘要不旨在限定说明书中公开的发明，也不旨在以任何方式限制本发明的范围。
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