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公开(公告)号：US20210115944A1
公开(公告)日：2021-04-22
申请号：US16654496
申请日：2019-10-16
Applicant: General Electric Company
Inventor： Sylvain Pierre , Brendon James Leary , Jason Adam Neville
Abstract: 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.
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公开(公告)号：US09957805B2
公开(公告)日：2018-05-01
申请号：US14973894
申请日：2015-12-18
Applicant: General Electric Company
Inventor： Sumeet Soni , Ross James Gustafson , Rohit Chouhan , Jason Adam Neville
CPC classification number: F01D5/141 , F01D5/145 , F01D5/20 , F04D29/324 , F05D2220/32 , F05D2240/122 , F05D2240/301 , F05D2250/71 , F05D2250/74
Abstract: 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.
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公开(公告)号：US10427213B2
公开(公告)日：2019-10-01
申请号：US15432055
申请日：2017-02-14
Applicant: General Electric Company
Inventor： Tyler Walton Kasperski , Mark Andrew Jones , Jason Adam Neville
Abstract: 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.
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公开(公告)号：US20170356297A1
公开(公告)日：2017-12-14
申请号：US15180842
申请日：2016-06-13
Applicant: General Electric Company
CPC classification number: F01D5/3007 , F01D5/187 , F01D5/326 , F05D2220/32 , F05D2230/10 , F05D2260/81 , F05D2260/941 , Y02T50/673
Abstract: 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.
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公开(公告)号：US11306735B2
公开(公告)日：2022-04-19
申请号：US16654496
申请日：2019-10-16
Applicant: General Electric Company
Inventor： Sylvain Pierre , Brendon James Leary , Jason Adam Neville
Abstract: 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.
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Patent Agency Ranking
公开(公告)号：US20170175530A1
公开(公告)日：2017-06-22
申请号：US14973894
申请日：2015-12-18
Applicant: General Electric Company
Inventor： Sumeet Soni , Ross James Gustafson , Rohit Chouhan , Jason Adam Neville
CPC classification number: F01D5/141 , F01D5/145 , F01D5/20 , F04D29/324 , F05D2220/32 , F05D2240/122 , F05D2240/301 , F05D2250/71 , F05D2250/74
Abstract: 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.
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公开(公告)号：US20150345303A1
公开(公告)日：2015-12-03
申请号：US14288748
申请日：2014-05-28
Applicant: General Electric Company
Inventor： Zhirui Dong , Xiuzhang James Zhang , Jason Adam Neville
IPC: F01D5/18
CPC classification number: F01D5/186 , F01D5/085 , F01D5/187 , F05D2260/202 , F05D2260/2212 , Y02T50/676
Abstract: 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.
Abstract translation: 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。
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公开(公告)号：US20180202298A1
公开(公告)日：2018-07-19
申请号：US15410061
申请日：2017-01-19
Applicant: General Electric Company
Inventor： William Scott Zemitis , Antonio Rodriguez , Jason Adam Neville
CPC classification number: F01D5/225 , F01D5/20 , F05D2230/80 , F05D2250/74 , F05D2250/75 , Y02T50/671 , Y02T50/673
Abstract: 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.
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公开(公告)号：US09810072B2
公开(公告)日：2017-11-07
申请号：US14288748
申请日：2014-05-28
Applicant: General Electric Company
Inventor： Zhirui Dong , Xiuzhang James Zhang , Jason Adam Neville
CPC classification number: F01D5/186 , F01D5/085 , F01D5/187 , F05D2260/202 , F05D2260/2212 , Y02T50/676
Abstract: 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.
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公开(公告)号：US20170152748A1
公开(公告)日：2017-06-01
申请号：US15432055
申请日：2017-02-14
Applicant: General Electric Company
Inventor： Tyler Walton Kasperski , Mark Andrew Jones , Jason Adam Neville
CPC classification number: B22C9/10 , B22C9/24 , F01D5/187 , F05D2240/304 , F05D2240/305 , F05D2240/306 , F05D2250/18 , F05D2260/2212 , F05D2260/2214 , F05D2260/22141 , Y10T29/49337
Abstract: 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.
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