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1. 发明授权

US10087762B2 Scallop curvature for radial turbine wheel 有权
公开(公告)号：US10087762B2
公开(公告)日：2018-10-02
申请号：US13179634
申请日：2011-07-11
申请人： Loc Quang Duong , Xiaolan Hu , Gao Yang , Anthony C. Jones
发明人： Loc Quang Duong , Xiaolan Hu , Gao Yang , Anthony C. Jones
IPC分类号： F01D5/04
摘要： A turbine wheel is disposed about an axis and has a back face including a plurality of lobes disposed about a periphery of the back face. The lobes define scalloped areas therebetween. The scalloped areas are further defined by a radius BR2 that blends into a first lobe and into a radius BR1 that also blends into a flat area.

2. 发明授权

US08936439B2 Radial turbine backface curvature stress reduction 有权
标题翻译：径向涡轮机背面曲率应力减小
公开(公告)号：US08936439B2
公开(公告)日：2015-01-20
申请号：US13179611
申请日：2011-07-11
申请人： Loc Quang Duong , Xiaolan Hu , Gao Yang , Anthony C. Jones
发明人： Loc Quang Duong , Xiaolan Hu , Gao Yang , Anthony C. Jones
IPC分类号： F01D5/22 , F01D5/04
CPC分类号： F01D5/048 , F05D2260/941
摘要： A turbine wheel is disposed about an axis and has a back having a separator disposed thereon, an inner undercut disposed between the separator and the axis, and an outer undercut disposed between the separator and an outer periphery of the back face. The inner undercut is defined by a first radius blending toward the axis and into a first flat section, and further defined by a second radius blending into the first flat section and into the separator.
摘要翻译：涡轮机叶轮围绕轴线设置，并且具有设置在其上的分离器的背面，设置在分离器和轴线之间的内部底切部，以及设置在分离器和背面的外周之间的外部底切部。内底切口由朝向轴线的第一半径和第一平坦部分限定，并且进一步由第二半径限定在第一平坦部分中并进入分离器。

3. 发明申请

US20130017091A1 RADIAL TURBINE BACKFACE CURVATURE STRESS REDUCTION 有权
标题翻译：径向涡轮机背面弯曲应力减小
公开(公告)号：US20130017091A1
公开(公告)日：2013-01-17
申请号：US13179611
申请日：2011-07-11
申请人： Loc Quang Duong , Xiaolan Hu , Gao Yang , Anthony C. Jones
发明人： Loc Quang Duong , Xiaolan Hu , Gao Yang , Anthony C. Jones
IPC分类号： F01D5/22
CPC分类号： F01D5/048 , F05D2260/941
摘要： A turbine wheel is disposed about an axis and has a back having a separator disposed thereon, an inner undercut disposed between the separator and the axis, and an outer undercut disposed between the separator and an outer periphery of the back face. The inner undercut is defined by a first radius blending toward the axis and into a first flat section, and further defined by a second radius blending into the first flat section and into the separator.
摘要翻译：涡轮机叶轮围绕轴线设置，并且具有设置在其上的分离器的背面，设置在分离器和轴线之间的内部底切部，以及设置在分离器和背面的外周之间的外部底切部。内底切口由朝向轴线的第一半径和第一平坦部分限定，并且进一步由第二半径限定在第一平坦部分中并进入分离器。

4. 发明申请

US20130017090A1 SCALLOP CURVATURE FOR RADIAL TURBINE WHEEL 审中-公开
标题翻译：用于径向涡轮轮的扫射曲线
公开(公告)号：US20130017090A1
公开(公告)日：2013-01-17
申请号：US13179634
申请日：2011-07-11
申请人： Loc Quang Duong , Xiaolan Hu , Gao Yang , Anthony C. Jones
发明人： Loc Quang Duong , Xiaolan Hu , Gao Yang , Anthony C. Jones
IPC分类号： F01D5/22
CPC分类号： F01D5/048 , F05D2260/941
摘要： A turbine wheel is disposed about an axis and has a back face including a plurality of lobes disposed about a periphery of the back face. The lobes define scalloped areas therebetween. The scalloped areas are further defined by a radius BR2 that blends into a first lobe and into a radius BR1 that also blends into a flat area.
摘要翻译：涡轮机叶轮围绕轴线设置并且具有包括围绕背面的周边设置的多个叶片的背面。裂片在其间限定扇形区域。扇形区域进一步由半径BR2限定，该半径BR2共混成第一个凸角，并进入也融合到平坦区域的半径BR1。

5. 发明申请

US20120288373A1 ROTOR WITH ASYMMETRIC BLADE SPACING 审中-公开
标题翻译：具有不对称叶片间距的转子
公开(公告)号：US20120288373A1
公开(公告)日：2012-11-15
申请号：US13107374
申请日：2011-05-13
申请人： Loc Quang Duong , Xiaolan Hu , Nagamany Thayalakhandan , Bo Zheng , Benjamin E. Fishler , Gao Yang , Anthony C. Jones , James C. Napier , Jay M. Francisco
发明人： Loc Quang Duong , Xiaolan Hu , Nagamany Thayalakhandan , Bo Zheng , Benjamin E. Fishler , Gao Yang , Anthony C. Jones , James C. Napier , Jay M. Francisco
IPC分类号： F01D5/22
CPC分类号： F04D29/284 , F01D5/048 , F01D5/141 , F01D5/16 , F04D29/30 , F04D29/666 , F05D2250/30 , F05D2260/961 , Y02T50/672 , Y02T50/673
摘要： A turbine apparatus comprises a rotor with a hub section defined about a rotational axis and a plurality of blades attached to the hub section. The plurality of blades comprises a first group having a first angular spacing in a first circumferential sector of the rotor, and a second group having a second angular spacing in a second circumferential sector of the rotor. The first angular spacing is different from the second angular spacing, and the rotor blades are asymmetric about the rotational axis.
摘要翻译：涡轮机装置包括转子，其具有围绕旋转轴线限定的毂部分以及附接到轮毂部分的多个叶片。多个叶片包括在转子的第一圆周扇形区域中具有第一角度间隔的第一组和在转子的第二圆周部分中具有第二角度间隔的第二组。第一角度间隔与第二角度间隔不同，并且转子叶片围绕旋转轴线是不对称的。

6. 发明申请

US20130034446A1 TURBINE BLADE POCKET PIN STRESS RELIEF 有权
标题翻译：涡轮叶片口袋紧固件
公开(公告)号：US20130034446A1
公开(公告)日：2013-02-07
申请号：US13198808
申请日：2011-08-05
申请人： Loc Quang Duong , Xiaolan Hu , Anthony C. Jones
发明人： Loc Quang Duong , Xiaolan Hu , Anthony C. Jones
IPC分类号： F01D5/14 , B23P15/04
CPC分类号： F01D5/147 , F01D5/18 , F05D2260/941 , Y10T29/49336
摘要： A turbine blade comprises an airfoil having a pressure side and a suction side, and extending from a leading edge to a trailing edge. The airfoil has a tip remote from a mounting root, and a pocket extending inwardly of the tip. The pocket has spaced walls with one wall associated with the pressure side of the airfoil, and an opposed wall associated with the suction side. A pin extends across the pocket and connects the opposed walls. A slot is formed in the pin at a location intermediate ends of the pin which connect to the opposed walls. A method for identifying a location for the pin along a distance between a leading edge and a trailing edge of the pocket utilizes a modal analysis, and seeks to find a location where both a reaction force and a moment are lower than they might be at other locations.
摘要翻译：涡轮叶片包括具有压力侧和吸力侧并从前缘延伸到后缘的翼型件。翼型件具有远离安装根部的尖端和从尖端向内延伸的口袋。口袋具有间隔壁，其中一个壁与翼型的压力侧相关联，以及与吸力侧相关联的相对的壁。销延伸穿过口袋并连接相对的墙壁。在销的中间端处连接到相对的壁的位置处，在销中形成槽。用于识别销口沿着口袋的前缘和后缘之间的距离的位置的方法利用模态分析，并寻求找到反作用力和力矩都低于它们可能在其它位置的位置位置。

7. 发明授权

US08876484B2 Turbine blade pocket pin stress relief 有权
标题翻译：涡轮叶片袋针应力消除
公开(公告)号：US08876484B2
公开(公告)日：2014-11-04
申请号：US13198808
申请日：2011-08-05
申请人： Loc Quang Duong , Xiaolan Hu , Anthony C. Jones
发明人： Loc Quang Duong , Xiaolan Hu , Anthony C. Jones
IPC分类号： F04D29/32 , F01D5/18 , F01D5/14
CPC分类号： F01D5/147 , F01D5/18 , F05D2260/941 , Y10T29/49336
摘要： A turbine blade comprises an airfoil having a pressure side and a suction side, and extending from a leading edge to a trailing edge. The airfoil has a tip remote from a mounting root, and a pocket extending inwardly of the tip. The pocket has spaced walls with one wall associated with the pressure side of the airfoil, and an opposed wall associated with the suction side. A pin extends across the pocket and connects the opposed walls. A slot is formed in the pin at a location intermediate ends of the pin which connect to the opposed walls. A method for identifying a location for the pin along a distance between a leading edge and a trailing edge of the pocket utilizes a modal analysis, and seeks to find a location where both a reaction force and a moment are lower than they might be at other locations.
摘要翻译：涡轮叶片包括具有压力侧和吸力侧并从前缘延伸到后缘的翼型件。翼型件具有远离安装根部的尖端和从尖端向内延伸的口袋。口袋具有间隔壁，其中一个壁与翼型的压力侧相关联，以及与吸力侧相关联的相对的壁。销延伸穿过口袋并连接相对的墙壁。在销的中间端处连接到相对的壁的位置处，在销中形成槽。用于识别销口沿着口袋的前缘和后缘之间的距离的位置的方法利用模态分析，并寻求找到反作用力和力矩都低于它们可能在其它位置的位置位置。

8. 发明申请

US20130236326A1 BLADE POCKET DESIGN 有权
标题翻译：刀片设计
公开(公告)号：US20130236326A1
公开(公告)日：2013-09-12
申请号：US13415005
申请日：2012-03-08
申请人： Loc Quang Duong , Xiaolan Hu , Nagamany Thayalakhandan , Gao Yang
发明人： Loc Quang Duong , Xiaolan Hu , Nagamany Thayalakhandan , Gao Yang
IPC分类号： F01D5/14 , B23P15/02
CPC分类号： F01D5/14 , F01D5/18
摘要： An airfoil includes a blade having a pocket recess therein and one or more features disposed within the pocket recess. The one or more features are configured to disrupt pressure oscillations within the pocket recess. In another embodiment, a blade is disclosed having a first wall and a second wall. The first wall is disposed on a suction side of the blade and the second wall is disposed on a pressure side of the blade. The second wall is connected to the first wall at a leading edge of the blade. Together the first wall and the second wall form a portion of a pocket recess and the pocket recess is disposed asymmetrically with respect to a camber line of the blade.
摘要翻译：翼型件包括其中具有凹穴凹部的叶片，以及设置在凹槽内的一个或多个特征。该一个或多个特征被配置为破坏袋凹部内的压力振荡。在另一个实施例中，公开了一种具有第一壁和第二壁的叶片。第一壁设置在叶片的吸力侧，第二壁设置在叶片的压力侧。第二壁在叶片的前缘连接到第一壁。第一壁和第二壁一起形成凹部凹部的一部分，并且凹部凹部相对于叶片的弧形线不对称地设置。

9. 发明授权

US08926289B2 Blade pocket design 有权
标题翻译：刀口袋设计
公开(公告)号：US08926289B2
公开(公告)日：2015-01-06
申请号：US13415005
申请日：2012-03-08
申请人： Loc Quang Duong , Xiaolan Hu , Nagamany Thayalakhandan , Gao Yang
发明人： Loc Quang Duong , Xiaolan Hu , Nagamany Thayalakhandan , Gao Yang
IPC分类号： F01D5/18
CPC分类号： F01D5/14 , F01D5/18
摘要： An airfoil includes a blade having a pocket recess therein and one or more features disposed within the pocket recess. The one or more features are configured to disrupt pressure oscillations within the pocket recess. In another embodiment, a blade is disclosed having a first wall and a second wall. The first wall is disposed on a suction side of the blade and the second wall is disposed on a pressure side of the blade. The second wall is connected to the first wall at a leading edge of the blade. Together the first wall and the second wall form a portion of a pocket recess and the pocket recess is disposed asymmetrically with respect to a camber line of the blade.
摘要翻译：翼型件包括其中具有凹穴凹部的叶片，以及设置在凹槽内的一个或多个特征。该一个或多个特征被配置为破坏袋凹部内的压力振荡。在另一个实施例中，公开了一种具有第一壁和第二壁的叶片。第一壁设置在叶片的吸力侧，第二壁设置在叶片的压力侧。第二壁在叶片的前缘连接到第一壁。第一壁和第二壁一起形成凹部凹部的一部分，并且凹部凹部相对于叶片的弧形线不对称地设置。

10. 发明授权

US08694285B2 Turbine blade base load balancing 有权
标题翻译：涡轮叶片基座负载平衡
公开(公告)号：US08694285B2
公开(公告)日：2014-04-08
申请号：US13098651
申请日：2011-05-02
申请人： Loc Quang Duong , Xiaolan Hu
发明人： Loc Quang Duong , Xiaolan Hu
IPC分类号： G06F17/50
CPC分类号： F01D5/3007 , F05D2250/32 , F05D2250/70 , F05D2260/81 , G06F17/50
摘要： An example method of designing blade lobes of a turbomachine blade and corresponding disk lobes includes determining contact areas between the blade lobes on a blade model and the disk loads on a disk model when the turbomachine blade is in a loaded position. The method adjusts the blade lobes, the disk lobes, or both, so that gaps are established between the blade lobes and the disk lobes at the contact areas when the turbomachine blade is in an unloaded position. The size of the gaps varies.
摘要翻译：设计涡轮机叶片和对应的叶片的叶片叶片的示例性方法包括确定叶片模型上的叶片叶片之间的接触面积和当涡轮机叶片处于加载位置时盘片模型上的盘载荷。该方法调节叶片叶片，叶片瓣或两者，使得当涡轮机叶片处于卸载位置时，在叶片瓣和接触区域的叶片叶片之间建立间隙。间隙的大小有所不同。

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