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1. 发明授权

US10427213B2 Turbine blade with sectioned pins and method of making same 有权
公开(公告)号：US10427213B2
公开(公告)日：2019-10-01
申请号：US15432055
申请日：2017-02-14
申请人： General Electric Company
发明人： Tyler Walton Kasperski , Mark Andrew Jones , Jason Adam Neville
IPC分类号： F01D5/18 , B22C9/10 , B22C9/24
摘要： A turbine blade includes pressure and suction surfaces connected to define an interior through which coolant is passable. First and second pedestal arrays, each include pedestals respectively coupled to radially outboard portions of respective interior faces of one of the pressure and suction surfaces. The pedestals of the first pedestal array are separated from and directly opposed to pedestals of the second pedestal array by gaps respectively defined therebetween.

2. 发明申请

US20170356297A1 Lockwire Tab Backcut For Blade Stress Reduction (9E.04) 审中-公开
公开(公告)号：US20170356297A1
公开(公告)日：2017-12-14
申请号：US15180842
申请日：2016-06-13
申请人： General Electric Company
发明人： Jason Adam Neville , William Scott Zemitis , Nicholas Alvin Hogberg , Mohankumar Banakar
IPC分类号： F01D5/30 , F01D5/18
CPC分类号： F01D5/3007 , F01D5/187 , F01D5/326 , F05D2220/32 , F05D2230/10 , F05D2260/81 , F05D2260/941 , Y02T50/673
摘要： The present application thus provides a method for reducing stress on a turbine blade wherein each of the turbine blades includes a dovetail with lockwire tab. The method may include the steps of (a) determining a starting line for a backcut relative to a lockwire tab end, (b) determining a cut angle for the backcut, and (c) removing material from the lockwire tab according to the starting line and the cut angle to form the dovetail backcut. The starting line may be positioned about 0.6 inches (about 15.24 millimeters), plus or minus 0.065 inches (about 1.65 millimeters) from the lockwire tab end along the dovetail axis.

3. 发明申请

US20210115944A1 Turbine Nozzle Airfoil Profile 有权
公开(公告)号：US20210115944A1
公开(公告)日：2021-04-22
申请号：US16654496
申请日：2019-10-16
申请人： General Electric Company
发明人： Sylvain Pierre , Brendon James Leary , Jason Adam Neville
IPC分类号： F04D29/44 , F01D5/32 , F01D25/24 , F04D29/26
摘要： The present application provides a turbine nozzle including an airfoil shape. The airfoil shape may have a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The airfoil profile sections at Z distances may be joined smoothly with one another to form a complete airfoil shape.

4. 发明授权

US09957805B2 Turbomachine and turbine blade therefor 有权
公开(公告)号：US09957805B2
公开(公告)日：2018-05-01
申请号：US14973894
申请日：2015-12-18
申请人： General Electric Company
发明人： Sumeet Soni , Ross James Gustafson , Rohit Chouhan , Jason Adam Neville
IPC分类号： F01D5/14 , F04D29/32 , F01D5/20
CPC分类号： F01D5/141 , F01D5/145 , F01D5/20 , F04D29/324 , F05D2220/32 , F05D2240/122 , F05D2240/301 , F05D2250/71 , F05D2250/74
摘要： A blade has an airfoil, and the blade is configured for use with a turbomachine. The airfoil has a throat distribution measured at a narrowest region in a pathway between adjacent blades, at which adjacent blades extend across the pathway between opposing walls to aerodynamically interact with fluid flow. The airfoil defines the throat distribution, and the throat distribution reduces aerodynamic loss and improves aerodynamic loading on the airfoil. The airfoil has a linear trailing edge profile.

5. 发明授权

US11306735B2 Turbine nozzle airfoil profile 有权
公开(公告)号：US11306735B2
公开(公告)日：2022-04-19
申请号：US16654496
申请日：2019-10-16
申请人： General Electric Company
发明人： Sylvain Pierre , Brendon James Leary , Jason Adam Neville
IPC分类号： F04D29/44 , F04D29/26 , F01D25/24 , F01D5/32 , F01D5/14 , F01D9/04
摘要： A turbine nozzle includes an airfoil shape. The airfoil shape may have a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The airfoil profile sections at Z distances may be joined smoothly with one another to form a complete airfoil shape.

6. 发明申请

US20170175530A1 TURBOMACHINE AND TURBINE BLADE THEREFOR 有权
公开(公告)号：US20170175530A1
公开(公告)日：2017-06-22
申请号：US14973894
申请日：2015-12-18
申请人： General Electric Company
发明人： Sumeet Soni , Ross James Gustafson , Rohit Chouhan , Jason Adam Neville
IPC分类号： F01D5/14 , F04D29/32
CPC分类号： F01D5/141 , F01D5/145 , F01D5/20 , F04D29/324 , F05D2220/32 , F05D2240/122 , F05D2240/301 , F05D2250/71 , F05D2250/74
摘要： A blade has an airfoil, and the blade is configured for use with a turbomachine. The airfoil has a throat distribution measured at a narrowest region in a pathway between adjacent blades, at which adjacent blades extend across the pathway between opposing walls to aerodynamically interact with fluid flow. The airfoil defines the throat distribution, and the throat distribution reduces aerodynamic loss and improves aerodynamic loading on the airfoil. The airfoil has a linear trailing edge profile.

7. 发明申请

US20150345303A1 ROTOR BLADE COOLING 有权
标题翻译：转子叶片冷却
公开(公告)号：US20150345303A1
公开(公告)日：2015-12-03
申请号：US14288748
申请日：2014-05-28
申请人： General Electric Company
发明人： Zhirui Dong , Xiuzhang James Zhang , Jason Adam Neville
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F01D5/085 , F01D5/187 , F05D2260/202 , F05D2260/2212 , Y02T50/676
摘要： A rotor blade includes a mounting portion comprising a mounting body that is formed to receive a coolant therein. An airfoil portion extends substantially radially outwardly from the mounting body and includes an airfoil body. The mounting body and the airfoil body define a plurality of primary cooling passages that extend substantially radially therein for routing the coolant through the airfoil body. Each of the primary cooling passages includes a cooling flow outlet that is formed along a tip portion of the airfoil body. The airfoil body further defines a plurality of trailing edge cooling passages, each having a coolant outlet that is formed along a trailing edge portion of the airfoil body. At least a portion of the trailing edge cooling passages are formed along a radially outer portion of the trailing edge proximate to the tip portion of the airfoil body.
摘要翻译：转子叶片包括安装部分，其包括形成为在其中容纳冷却剂的安装体。机翼部分从安装体基本上径向向外延伸并且包括翼型体。安装体和翼型体限定了多个基本上径向延伸的主冷却通道，用于使冷却剂穿过翼型体。每个主冷却通道包括沿翼型本体的尖端部分形成的冷却流出口。翼型体还限定多个后缘冷却通道，每个后缘冷却通道具有沿翼型本体的后缘部分形成的冷却剂出口。尾缘冷却通道的至少一部分沿靠近翼型本体的尖端部分的后缘的径向外部部分形成。

8. 发明授权

US10513934B2 Z-notch shape for a turbine blade tip shroud 有权
公开(公告)号：US10513934B2
公开(公告)日：2019-12-24
申请号：US15410061
申请日：2017-01-19
申请人： General Electric Company
发明人： William Scott Zemitis , Antonio Rodriguez , Jason Adam Neville
IPC分类号： F01D5/22 , F01D5/20
摘要： A turbine blade includes an airfoil having a tip shroud. The tip shroud has an edge, and the edge has a profile substantially in accordance with values of X and Y in a Cartesian coordinate system set forth in Table 1 at points 1-30. The X and Y values represent distances that may be proportionally scaled by a common multiplier which, once scaled and connected, define the profile of the edge of the tip shroud. The profile of the edge lies in an envelope within +/−20%, +/−10% or +/−0% in a direction normal to any location along the edge set forth by the points in Table 1.

9. 发明申请

US20160245095A1 TURBINE ROTOR BLADE 审中-公开
标题翻译：涡轮转子叶片
公开(公告)号：US20160245095A1
公开(公告)日：2016-08-25
申请号：US14631409
申请日：2015-02-25
申请人： General Electric Company
发明人： Rohit Chouhan , Sumeet Soni , Jason Adam Neville
IPC分类号： F01D5/18 , F02C3/04 , F02C7/18 , F01D5/14
CPC分类号： F01D5/187 , F01D5/141 , F01D5/146 , F01D5/20 , F02C3/04 , F02C7/18 , F05D2220/32 , F05D2240/304 , F05D2240/307 , F05D2260/20
摘要： A turbine rotor blade includes a tip portion having a pressure tip wall and a suction tip wall, a tip leading edge and a tip trailing edge, wherein the pressure tip wall and the suction tip wall define a trailing edge tip thickness. Also included is a squealer cavity at least partially defined by the pressure tip wall and the suction tip wall, the squealer cavity including a trench extending fully to the tip trailing edge to form an open flow path out of the tip trailing edge. Further included is a suction side wall and a pressure side wall extending from a root portion of the turbine rotor blade to the tip portion, wherein the suction side wall and the pressure side wall define a trailing edge blade thickness, the trailing edge tip thickness being greater than the trailing edge blade thickness.
摘要翻译：涡轮转子叶片包括具有压力顶端壁和吸入端壁，尖端前缘和尖端后缘的尖端部分，其中压力尖端壁和吸力端壁限定了后缘尖端厚度。还包括一个至少部分地由压力尖端壁和吸力端壁限定的尖叫声腔，该尖声腔包括一个完全延伸到尖端后缘的沟槽，以形成一个从尖端后缘开出的开放流路。进一步包括从涡轮转子叶片的根部延伸到顶端部分的吸力侧壁和压力侧壁，其中吸力侧壁和压力侧壁限定后缘叶片厚度，后缘尖端厚度为大于后缘叶片厚度。

10. 发明授权

US09151587B2 Bucket tip shroud measurement fixture and method of measuring bucket tip shroud orientation 有权
标题翻译：斗尖护罩测量夹具和测量铲斗顶端护罩方向的方法
公开(公告)号：US09151587B2
公开(公告)日：2015-10-06
申请号：US14076558
申请日：2013-11-11
申请人： General Electric Company
发明人： John David Ward, Jr. , Juan Pablo Cilia , James Ryan Connor , Jason Adam Neville , Christopher Allen Nafis , Neil Robert Peddar , Antonio Rodriguez , Daniel Howard Tragesser
IPC分类号： G01B5/008 , G01B5/20 , G01B5/00 , F01D11/00
CPC分类号： G01B5/008 , F01D11/00 , F01D25/285 , F05D2260/83 , G01B5/0002 , G01B5/0004 , G01B5/205
摘要： A bucket tip shroud measurement fixture includes a frame extending from a first end to a second end through an intermediate portion having a first surface and an opposing second surface, a first tip shroud fixing member extending from the second surface of the frame at the first end, and a second tip shroud fixing member extending from the second surface of the frame at the second end. The first and second tip shroud fixing members are configured and disposed to retain and establish an orientation of a bucket tip shroud relative the frame. A plurality of reference points are provided on the frame. The plurality of reference points are configured and disposed to receive a coordinate measuring machine (CMM) probe.
摘要翻译：铲斗顶部护罩测量夹具包括：框架，其从第一端延伸到第二端，通过具有第一表面和相对的第二表面的中间部分;第一末端护罩固定件，在第一端从框架的第二表面延伸; 以及在第二端处从框架的第二表面延伸的第二顶端罩固定构件。第一和第二末端罩固定构件被构造和设置成保持并建立相对于框架的铲斗顶部护罩的取向。在框架上设置多个参考点。多个参考点被配置和设置成接收坐标测量机（CMM）探针。

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