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公开(公告)号：US10724377B2
公开(公告)日：2020-07-28
申请号：US15188157
申请日：2016-06-21
Applicant: General Electric Company
Inventor： Jamie Dean Lumpkin , Thomas Robbins Tipton , Kelvin Rono Aaron
Abstract: An article of manufacture includes a rotor blade configured for use with a turbomachine. The blade is configured for attachment to a rotor wheel. The blade is configured to substantially reduce the possibility of attachment with an undesired rotor wheel by modification of at least one characteristic of the blade, so that the modification of the characteristic is matched by a complementary characteristic of the rotor wheel. The characteristic of the blade is, neck width, platform length, platform angle, platform height, tang height, or circumferential width. The blade and the wheel comprise a first stage of the turbomachine. The undesired rotor wheel is in a second stage of the turbomachine, where the first stage is different from the second stage. The complementary characteristic of the wheel is, slot opening width, platform opening depth, slot neck width, slot neck angle, slot tang depth, or slot tang width.
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公开(公告)号：US10196908B2
公开(公告)日：2019-02-05
申请号：US15019379
申请日：2016-02-09
Applicant: General Electric Company
Inventor： Craig Allen Bielek , Kelvin Rono Aaron , Michael David McDufford
Abstract: Various embodiments of the invention include turbine buckets and systems employing such buckets. Various particular embodiments include a turbine bucket having: an airfoil having: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; a pair of part-span connectors extending from the airfoil at the suction side and the pressure side, respectively, wherein each of the pair of part-span connectors is located between approximately 40 percent and approximately 70 percent of a radial span measured from the base to a radial tip of the airfoil; and a base connected with a first end of the airfoil along the suction side, pressure side, trailing edge and the leading edge.
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Patent Agency Ranking
公开(公告)号：US20170226872A1
公开(公告)日：2017-08-10
申请号：US15019379
申请日：2016-02-09
Applicant: General Electric Company
Inventor： Craig Allen Bielek , Kelvin Rono Aaron , Michael David McDufford
CPC classification number: F01D5/225 , F05D2250/74 , Y02T50/673
Abstract: Various embodiments of the invention include turbine buckets and systems employing such buckets. Various particular embodiments include a turbine bucket having: an airfoil having: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; a pair of part-span connectors extending from the airfoil at the suction side and the pressure side, respectively, wherein each of the pair of part-span connectors is located between approximately 40 percent and approximately 70 percent of a radial span measured from the base to a radial tip of the airfoil; and a base connected with a first end of the airfoil along the suction side, pressure side, trailing edge and the leading edge.
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公开(公告)号：US20140147283A1
公开(公告)日：2014-05-29
申请号：US13685950
申请日：2012-11-27
Applicant: GENERAL ELECTRIC COMPANY
Inventor： John David Ward, Jr. , Kelvin Rono Aaron , James Ryan Connor , Melbourne James Myers , Brad Wilson VanTassel
CPC classification number: F01D5/005 , F01D5/225 , F05D2230/80 , F05D2240/307 , F05D2260/94 , F05D2260/941 , F05D2270/332 , Y10T29/49234 , Y10T83/04
Abstract: According to one aspect of the invention, a method is provided for modifying an airfoil shroud located at a tip of an airfoil of a airfoil, the airfoil shroud having a first end edge, a second end edge, a leading edge and a trailing edge. The method includes locating a reference location in the first end edge of the airfoil shroud, the reference location being proximate a seal rail extending circumferentially from the substantially horizontal surface and forming a relief cut in the airfoil shroud to remove the reference location, wherein a modifying of the airfoil shroud is complete following forming of the relief cut.
Abstract translation: 根据本发明的一个方面，提供了一种用于修改位于翼型的翼型的尖端处的翼型护罩的方法，所述翼型护罩具有第一端边缘，第二端边缘，前缘和后缘。 该方法包括将参考位置定位在翼型护罩的第一端边缘中，参考位置靠近从基本水平的表面周向延伸的密封轨道，并在翼型护罩中形成浮雕切口以移除参考位置，其中修改 的翼型护罩在形成浮雕切割后完成。
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公开(公告)号：US20160362988A1
公开(公告)日：2016-12-15
申请号：US15245985
申请日：2016-08-24
Applicant: General Electric Company
Inventor： John David Ward , Kelvin Rono Aaron , James Ryan Connor , Melbourne James Myers , Brad Wilson VanTassel
IPC: F01D5/22
CPC classification number: F01D5/225 , F01D5/005 , F05D2220/32 , F05D2230/10 , F05D2230/50 , F05D2230/80 , F05D2260/94 , F05D2270/332 , Y10T29/49234 , Y10T83/04
Abstract: A method is provided for modifying an airfoil shroud located at a tip of a blade of an airfoil, the airfoil shroud having a first end edge, a second end edge, a leading edge, and a trailing edge. The method includes locating a reference location in the first end edge of the airfoil shroud, the reference location including a portion of a seal rail extending circumferentially from a radially outer surface of the airfoil shroud, and a fillet extending from the radially outer surface and positioned directly adjacent to the seal rail. The method further includes forming a relief cut in the seal rail and fillet without performing a weld process on the airfoil shroud to remove the reference location, and installing the airfoil shroud in a turbomachine directly following forming the relief cut, wherein modifying the airfoil shroud is complete following forming the relief cut.
Abstract translation: 提供了一种用于改变位于翼型件的叶片的尖端处的翼型护罩的方法，翼型护罩具有第一端边缘，第二端边缘，前缘和后缘。 该方法包括将参考位置定位在翼型护罩的第一端边缘中，参考位置包括从翼型护罩的径向外表面周向延伸的密封轨道的一部分，以及从径向外表面延伸的圆角， 直接靠近密封轨。 该方法还包括在密封导轨和圆角上形成浮雕切口，而不对翼型护罩进行焊接处理以去除参考位置，并且在形成浮雕切割之后将翼型件护罩直接安装在涡轮机中，其中修改翼型护罩是 完成以后形成救济切割。
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公开(公告)号：US20160298461A1
公开(公告)日：2016-10-13
申请号：US15188157
申请日：2016-06-21
Applicant: General Electric Company
Inventor： Jamie Dean Lumpkin , Thomas Robbins Tipton , Kelvin Rono Aaron
Abstract: An article of manufacture includes a rotor blade configured for use with a turbomachine. The blade is configured for attachment to a rotor wheel. The blade is configured to substantially reduce the possibility of attachment with an undesired rotor wheel by modification of at least one characteristic of the blade, so that the modification of the characteristic is matched by a complementary characteristic of the rotor wheel. The characteristic of the blade is, neck width, platform length, platform angle, platform height, tang height, or circumferential width. The blade and the wheel comprise a first stage of the turbomachine. The undesired rotor wheel is in a second stage of the turbomachine, where the first stage is different from the second stage. The complementary characteristic of the wheel is, slot opening width, platform opening depth, slot neck width, slot neck angle, slot tang depth, or slot tang width.
Abstract translation: 制造品包括被配置为与涡轮机一起使用的转子叶片。 叶片被构造成附接到转子轮。 叶片被构造成通过修改叶片的至少一个特性来大大降低与不需要的转子轮的连接的可能性，使得特性的修改由转子轮的互补特性来匹配。 刀片的特点是颈部宽度，平台长度，平台角度，平台高度，刀柄高度或圆周宽度。 叶片和轮子包括涡轮机的第一级。 不期望的转子轮处于涡轮机的第二阶段，其中第一级与第二级不同。 车轮的互补特征是槽开口宽度，平台开口深度，槽颈宽度，槽颈角度，槽口深度或槽口宽度。
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公开(公告)号：US20160024930A1
公开(公告)日：2016-01-28
申请号：US14340059
申请日：2014-07-24
Applicant: General Electric Company
Inventor： Kelvin Rono Aaron , Craig Allen Bielek , Ross James Gustafson , Ariel Caesar Prepena Jacala , Spencer Aaron Kareff , Matthew Robert Piersall , John Franklin Ryman
IPC: F01D5/14
CPC classification number: F01D5/16 , F01D5/141 , F05D2240/305 , F05D2250/711 , F05D2260/941 , Y02T50/673
Abstract: A turbomachine airfoil includes a base portion and a blade portion extending from the base portion to a tip portion defining a radial span dimension. The blade portion includes a leading edge, a trailing edge, a pressure side and a suction side. An axial chord dimension is defined between the leading edge and the trailing edge. At least one protuberance is provided on the pressure side. The at least one protuberance extends from about 10% of the axial chord dimension to about 90% of the axial chord dimension.
Abstract translation: 涡轮机翼型包括基部和从基部延伸到限定径向跨度尺寸的尖端部的叶片部分。 叶片部分包括前缘，后缘，压力侧和吸力侧。 在前缘和后缘之间限定轴向弦的尺寸。 在压力侧设置至少一个凸起。 至少一个突起从轴向弦尺寸的约10％延伸到轴向弦尺寸的约90％。
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