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公开(公告)号：US09695696B2
公开(公告)日：2017-07-04
申请号：US13955679
申请日：2013-07-31
Applicant: General Electric Company
Inventor： Mark Andrew Jones , Bradley Taylor Boyer , Robert Alan Brittingham , Gregory Thomas Foster , Christopher William Kester
CPC classification number: F01D5/16 , B22C9/10 , B22C9/24 , B23P15/04 , F01D5/147 , F01D5/18 , F01D5/186 , F01D5/187 , F05D2240/304 , F05D2240/305 , F05D2240/306 , F05D2260/2212 , F05D2260/2214 , F05D2260/22141 , F05D2260/961 , Y10T29/49337
Abstract: A turbine blade is provided and includes pressure and suction surfaces connected to define an interior through which coolant is passable and first and second pedestal arrays, each of the first and second pedestal arrays including 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 pedestals of the second pedestal array by gaps respectively defined therebetween.
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公开(公告)号：US20160245097A1
公开(公告)日：2016-08-25
申请号：US15142640
申请日：2016-04-29
Applicant: General Electric Company
Inventor： Mark Andrew Jones , Aaron Ezekiel Smith
CPC classification number: F01D5/187 , F01D9/041 , F01D25/12 , F05D2220/32 , F05D2240/304 , F05D2260/202
Abstract: An airfoil includes a pressure side, a suction side opposed to the pressure side, a cavity inside the airfoil between the pressure and suction sides, and a trailing edge downstream from the cavity between the pressure and suction sides. A first set of cooling passages through the trailing edge provide fluid communication from the cavity through the trailing edge. A first divider across each cooling passage in the first set of cooling passages extends from the pressure side to the suction side at the trailing edge.
Abstract translation: 翼型件包括压力侧，与压力侧相对的吸入侧，在压力侧和吸力侧之间的翼型内的空腔，以及在压力侧和吸力侧之间的空腔下游的后缘。 通过后缘的第一组冷却通道提供从空腔到后缘的流体连通。 第一组冷却通道中的每个冷却通道的第一分隔件从后侧的压力侧延伸到吸入侧。
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公开(公告)号：US20150110617A1
公开(公告)日：2015-04-23
申请号：US14061169
申请日：2013-10-23
Applicant: General Electric Company
Inventor： Alexander Stein , Lee Larned Brozyna , Mark Andrew Jones
CPC classification number: F01D5/20 , F01D5/141 , F01D9/041 , F05D2240/307 , Y02T50/673
Abstract: A turbine blade can include a root configured to connect to a turbine and supporting an airfoil configured to extend into a flowpath of the turbine. The airfoil can include a tip disposed substantially opposite the root and a first tip fillet disposed proximate the tip that can extend substantially perpendicular to a local flow direction at points along a surface of the turbine blade over the extremity of the first tip fillet. The tip fillet can enhance performance of the turbine by beneficially altering flow through a stage in which the blade is included.
Abstract translation: 涡轮叶片可以包括构造成连接到涡轮机并且支撑构造成延伸到涡轮机的流动路径中的翼型件的根部。 翼型件可以包括基本上与根部相对设置的尖端，以及设置在尖端附近的第一末端圆角，其可沿着沿着涡轮叶片的表面的点在第一尖端圆角的末端处基本上垂直于局部流动方向延伸。 尖端圆角可以通过有益地改变通过其中包括叶片的阶段的流动来增强涡轮机的性能。
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公开(公告)号：US10472974B2
公开(公告)日：2019-11-12
申请号：US15432117
申请日：2017-02-14
Applicant: General Electric Company
Inventor： Mark Andrew Jones , James Tyson Balkcum, III
Abstract: In one aspect, the present disclosure is directed to a rotor blade for a turbomachine. The rotor blade includes an airfoil defining at least one cooling passage. The rotor blade also includes a tip shroud coupled to the airfoil. The tip shroud and the airfoil define a core fluidly coupled to the cooling passage. A maximum radial depth of the core is at least six times greater than a minimum hydraulic diameter of a largest cooling passage of the at least one cooling passage.
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公开(公告)号：US10436034B2
公开(公告)日：2019-10-08
申请号：US15594704
申请日：2017-05-15
Applicant: General Electric Company
Inventor： Lee Larned Brozyna , Mark Andrew Jones , Matthew Lutz , Srinivasa Govardhan Jayana
IPC: F01D5/14
Abstract: A turbine rotor blade is provided including an airfoil having an airfoil shape. The airfoil shape having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein 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, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the airfoil profile sections at Z distances being joined smoothly with one another to form a complete airfoil shape.
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Patent Agency Ranking
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：US20190003318A1
公开(公告)日：2019-01-03
申请号：US15638603
申请日：2017-06-30
Applicant: General Electric Company
Inventor： Robert Alan Brittingham , Mark Andrew Jones
CPC classification number: F01D5/187 , F01D5/147 , F01D5/18 , F01D5/20 , F01D5/225 , F05D2240/24 , F05D2240/301 , F05D2240/307 , F05D2240/81 , F05D2260/202
Abstract: The present disclosure is directed to a rotor blade for a turbomachine. The rotor blade includes an airfoil having a trailing edge surface and defining a cooling passage. The rotor blade also includes a tip shroud coupled to the airfoil. The tip shroud includes a radially inner surface. The tip shroud defines a cooling core fluidly coupled to the cooling passage. The cooling core includes at least one of a first outlet aperture having a first opening defined by the radially inner surface or a second outlet aperture having a second opening defined by the trailing edge surface of the airfoil. The first or second outlet apertures eject coolant from the cooling core in a direction of a local flow of combustion gases external to the tip shroud.
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公开(公告)号：US20180340428A1
公开(公告)日：2018-11-29
申请号：US15426170
申请日：2017-02-07
Applicant: General Electric Company
Inventor： Mark Andrew Jones
Abstract: The present disclosure is directed to a rotor blade for a turbomachine. The rotor blade includes an airfoil and a tip shroud coupled to the airfoil. The tip shroud defines a core. The tip shroud includes a rib positioned within the core and a radially outer wall. The rib separates a first portion of the core and a second portion of the core. The airfoil, the rib, and the radially outer wall partially define a first cooling passage fluidly isolated from the core.
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公开(公告)号：US20180328178A1
公开(公告)日：2018-11-15
申请号：US15594704
申请日：2017-05-15
Applicant: General Electric Company
Inventor： Lee Larned Brozyna , Mark Andrew Jones , Matthew Lutz , Srinivasa Govardhan Jayana
IPC: F01D5/14
CPC classification number: F01D5/141 , F05D2250/74
Abstract: A turbine rotor blade is provided including an airfoil having an airfoil shape. The airfoil shape having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein 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, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the airfoil profile sections at Z distances being joined smoothly with one another to form a complete airfoil shape.
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公开(公告)号：US20170241269A1
公开(公告)日：2017-08-24
申请号：US15046469
申请日：2016-02-18
Applicant: General Electric Company
Inventor： Mark Andrew Jones , Lee Larned Brozyna
CPC classification number: F01D5/16 , B23P15/02 , F01D5/141 , F01D5/147 , F01D5/26 , F01D25/06 , F05D2220/32 , F05D2230/20 , F05D2240/30 , F05D2260/96 , F05D2260/961
Abstract: A method for producing a rotating turbine blade and tuning the natural frequencies of the blade is disclosed that changes the second effective beam length of the blade thereby changing the separation between the first natural frequency and the second natural frequency of the blade.
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