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1. 发明申请

US20080181767A1 Turbine seal plate locking system 有权
标题翻译：涡轮密封板锁定系统
公开(公告)号：US20080181767A1
公开(公告)日：2008-07-31
申请号：US11699801
申请日：2007-01-30
申请人： Dieter Brillert , Oran Bertsch
发明人： Dieter Brillert , Oran Bertsch
IPC分类号： F01D11/00 , F04D29/08
CPC分类号： F01D11/00 , F01D5/081 , F01D5/3015 , F01D5/326 , F01D11/006 , F05D2260/30 , Y10T29/4932 , Y10T29/49321
摘要： A seal plate assembly is provided in a rotor disc for a turbine engine. The seal plate assembly includes a radially extending flange on the disc and an annular groove defined between a radial surface on the flange and a face of the disc. An annular outer surface extends axially in facing relationship to an annular inner surface of the groove. A plate structure is supported between the inner and outer surfaces, and a lock structure is provided for holding the plate structure in place. The lock structure includes an axial leg that is adapted to be located between an inner edge of the plate structure and the inner surface of the groove, and the lock structure further includes a radial leg that is adapted to be located between the radial surface on the flange and an outwardly facing surface of the plate structure.
摘要翻译：在用于涡轮发动机的转子盘中设置有密封板组件。密封板组件包括在盘上的径向延伸的凸缘和限定在凸缘上的径向表面和盘的表面之间的环形凹槽。环形外表面以与槽的环形内表面成面对关系的方式轴向延伸。板结构支撑在内表面和外表面之间，并且提供用于将板结构保持在适当位置的锁定结构。所述锁定结构包括适于位于所述板结构的内边缘和所述槽的内表面之间的轴向支腿，并且所述锁定结构还包括径向支腿，所述径向支腿适于位于所述板结构的径向表面之间凸缘和板结构的面向外的表面。

2. 发明授权

US07566201B2 Turbine seal plate locking system 有权
标题翻译：涡轮密封板锁定系统
公开(公告)号：US07566201B2
公开(公告)日：2009-07-28
申请号：US11699801
申请日：2007-01-30
申请人： Dieter Brillert , Oran Bertsch
发明人： Dieter Brillert , Oran Bertsch
IPC分类号： F01D5/32
CPC分类号： F01D11/00 , F01D5/081 , F01D5/3015 , F01D5/326 , F01D11/006 , F05D2260/30 , Y10T29/4932 , Y10T29/49321
摘要： A seal plate assembly is provided in a rotor disc for a turbine engine. The seal plate assembly includes a radially extending flange on the disc and an annular groove defined between a radial surface on the flange and a face of the disc. An annular outer surface extends axially in facing relationship to an annular inner surface of the groove. A plate structure is supported between the inner and outer surfaces, and a lock structure is provided for holding the plate structure in place. The lock structure includes an axial leg that is adapted to be located between an inner edge of the plate structure and the inner surface of the groove, and the lock structure further includes a radial leg that is adapted to be located between the radial surface on the flange and an outwardly facing surface of the plate structure.
摘要翻译：在用于涡轮发动机的转子盘中设置有密封板组件。密封板组件包括在盘上的径向延伸的凸缘和限定在凸缘上的径向表面和盘的表面之间的环形凹槽。环形外表面以与槽的环形内表面成面对关系的方式轴向延伸。板结构支撑在内表面和外表面之间，并且提供用于将板结构保持在适当位置的锁定结构。所述锁定结构包括适于位于所述板结构的内边缘和所述槽的内表面之间的轴向支腿，并且所述锁定结构还包括径向支腿，所述径向支腿适于位于所述板结构的径向表面之间凸缘和板结构的面向外的表面。

3. 发明申请

US20080131270A1 Blade clearance system for a turbine engine 有权
标题翻译：用于涡轮发动机的叶片间隙系统
公开(公告)号：US20080131270A1
公开(公告)日：2008-06-05
申请号：US11633396
申请日：2006-12-04
申请人： Hubertus Edward Paprotna , Oran Bertsch
发明人： Hubertus Edward Paprotna , Oran Bertsch
IPC分类号： F01D11/20
CPC分类号： F01D11/20 , F01D11/22 , F01D11/24 , F05D2300/505
摘要： A blade gap control system configured to move a blade ring of a turbine engine relative to a blade assembly to reduce the gaps between the tips of the blades and the blade rings to increase the efficiency of the turbine engine is provided. The blade rings can be at an acute angle with respect to the rotational axis of the blade assembly. The axial movement of the blade ring can be done by a pressure differential supplied across the blade ring, the thermal expansion and/or contraction of a linkage or by a piston.
摘要翻译：叶片间隙控制系统构造成相对于叶片组件移动涡轮发动机的叶片环，以减小叶片和叶片环之间的间隙，以提高涡轮发动机的效率。叶片环可以相对于叶片组件的旋转轴线成锐角。叶片环的轴向运动可以通过供应在叶片环上的压力差，连杆的热膨胀和/或收缩或活塞来实现。

4. 发明授权

US07686569B2 Blade clearance system for a turbine engine 有权
标题翻译：用于涡轮发动机的叶片间隙系统
公开(公告)号：US07686569B2
公开(公告)日：2010-03-30
申请号：US11633396
申请日：2006-12-04
申请人： Hubertus Edward Paprotna , Oran Bertsch
发明人： Hubertus Edward Paprotna , Oran Bertsch
IPC分类号： F01D11/20
CPC分类号： F01D11/20 , F01D11/22 , F01D11/24 , F05D2300/505
摘要： A blade gap control system configured to move a blade ring of a turbine engine relative to a blade assembly to reduce the gaps between the tips of the blades and the blade rings to increase the efficiency of the turbine engine is provided. The blade rings can be at an acute angle with respect to the rotational axis of the blade assembly. The axial movement of the blade ring can be done by a pressure differential supplied across the blade ring, the thermal expansion and/or contraction of a linkage or by a piston.
摘要翻译：叶片间隙控制系统构造成相对于叶片组件移动涡轮发动机的叶片环，以减小叶片和叶片环之间的间隙，以提高涡轮发动机的效率。叶片环可以相对于叶片组件的旋转轴线成锐角。叶片环的轴向运动可以通过供应在叶片环上的压力差，连杆的热膨胀和/或收缩或活塞来实现。

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