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公开(公告)号：US09995146B2
公开(公告)日：2018-06-12
申请号：US14699607
申请日：2015-04-29
Applicant: General Electric Company
Inventor： Adebukola Oluwaseun Benson , Nicholas Alvin Hogberg , Gary Michael Itzel , Mitchell Allan Merrill , Xiuzhang James Zhang
IPC: F01D5/18
CPC classification number: F01D5/18 , F01D5/187 , F05D2240/127 , F05D2260/2212 , F05D2260/22141
Abstract: A turbine airfoil includes a leading edge and a trailing edge. Also included is a cooling channel extending in a radial direction and tapering inwardly toward the trailing edge, the cooling channel at least partially defined by a pressure side face and a suction side face. Further included is a first plurality of turbulators protruding from one of the pressure side face and the suction side face to define a first height, the first plurality of turbulators extending toward the trailing edge of the turbine airfoil and spaced radially from each other. Yet further included is a second plurality of turbulators protruding from one of the pressure side face and the suction side face to define a second height that is less than the first height, the second plurality of turbulators extending toward the trailing edge of the turbine airfoil and spaced radially from each other.
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公开(公告)号：US20170175529A1
公开(公告)日：2017-06-22
申请号：US14973875
申请日：2015-12-18
Applicant: General Electric Company
Inventor： Rohit Chouhan , Sumeet Soni , Ross James Gustafson , Nicholas Alvin Hogberg
CPC classification number: F01D5/141 , F01D5/145 , F04D29/324 , F05D2220/32 , F05D2240/301 , F05D2240/304 , F05D2250/70
Abstract: A turbomachine includes a plurality of blades, and each blade has an airfoil. The turbomachine includes opposing walls that define a pathway into which a fluid flow is receivable to flow through the pathway. A throat distribution is measured at a narrowest region in the pathway between adjacent blades, at which adjacent blades extend across the pathway between the opposing walls to aerodynamically interact with the fluid flow. The airfoil defines the throat distribution, and the throat distribution reduces aerodynamic loss and improves aerodynamic loading on each airfoil.
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公开(公告)号：US09957804B2
公开(公告)日：2018-05-01
申请号：US14973875
申请日：2015-12-18
Applicant: General Electric Company
Inventor： Rohit Chouhan , Sumeet Soni , Ross James Gustafson , Nicholas Alvin Hogberg
CPC classification number: F01D5/141 , F01D5/145 , F04D29/324 , F05D2220/32 , F05D2240/301 , F05D2240/304 , F05D2250/70
Abstract: A turbomachine includes a plurality of blades, and each blade has an airfoil. The turbomachine includes opposing walls that define a pathway into which a fluid flow is receivable to flow through the pathway. A throat distribution is measured at a narrowest region in the pathway between adjacent blades, at which adjacent blades extend across the pathway between the opposing walls to aerodynamically interact with the fluid flow. The airfoil defines the throat distribution, and the throat distribution reduces aerodynamic loss and improves aerodynamic loading on each airfoil.
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公开(公告)号：US20170234142A1
公开(公告)日：2017-08-17
申请号：US15045553
申请日：2016-02-17
Applicant: General Electric Company
Inventor： Adebukola Oluwaseun Benson , Nicholas Alvin Hogberg , Xiuzhang James Zhang , Gary Michael Itzel , Mohankumar Banakar
CPC classification number: F01D5/187 , F01D5/186 , F02C3/04 , F05D2220/32 , F05D2240/304 , F05D2240/80 , F05D2250/185 , F05D2250/314 , F05D2250/38 , F05D2250/52
Abstract: The present disclosure is directed to a rotor blade for a gas turbine engine. The rotor blade includes a platform having a radially inner surface and a radially outer surface. A connection portion extends radially inwardly from the radially inner surface of the platform. An airfoil extends radially outwardly from the radially outer surface of the platform to an airfoil tip. The airfoil includes a leading edge portion and a trailing edge portion. The platform, the airfoil, and the connection portion collectively define a cooling circuit extending from an inlet defined by the connection portion to one or more outlet passages at least partially defined by the trailing edge portion of the airfoil. At least one of the one or more outlet passages include an entrance and an exit radially inwardly offset from the entrance.
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公开(公告)号：US20170204730A1
公开(公告)日：2017-07-20
申请号：US14996498
申请日：2016-01-15
Applicant: General Electric Company
CPC classification number: F01D5/187 , F01D5/143 , F01D11/006 , F02C3/04 , F05D2220/32 , F05D2240/24 , F05D2240/81 , F05D2250/185 , F05D2260/201 , F05D2260/205
Abstract: The present disclosure is directed to a rotor blade for a gas turbine engine. The rotor blade includes a platform comprising a radially inner surface, an undulating radially outer surface, a leading edge portion, a trailing edge portion, a pressure-side slash face, and a suction-side slash face. An airfoil extends outwardly from the undulating radially outer surface of the platform to an airfoil tip. A connection portion extends radially inwardly from the radially inner surface of the platform. The platform, the airfoil, and the connection portion collectively define a cooling circuit extending from an inlet in the connection portion through the airfoil to a plurality of outlet plena in the platform. Two or more outlet plena of the plurality of outlet plena are spaced equidistant from the undulating radially outer surface of the platform.
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Patent Agency Ranking
公开(公告)号：US20160319671A1
公开(公告)日：2016-11-03
申请号：US14699607
申请日：2015-04-29
Applicant: General Electric Company
Inventor： Adebukola Oluwaseun Benson , Nicholas Alvin Hogberg , Gary Michael Itzel , Mitchell Allan Merrill , Xiuzhang James Zhang
IPC: F01D5/18
CPC classification number: F01D5/18 , F01D5/187 , F05D2240/127 , F05D2260/2212 , F05D2260/22141
Abstract: A turbine airfoil includes a leading edge and a trailing edge. Also included is a cooling channel extending in a radial direction and tapering inwardly toward the trailing edge, the cooling channel at least partially defined by a pressure side face and a suction side face. Further included is a first plurality of turbulators protruding from one of the pressure side face and the suction side face to define a first height, the first plurality of turbulators extending toward the trailing edge of the turbine airfoil and spaced radially from each other. Yet further included is a second plurality of turbulators protruding from one of the pressure side face and the suction side face to define a second height that is less than the first height, the second plurality of turbulators extending toward the trailing edge of the turbine airfoil and spaced radially from each other.
Abstract translation: 涡轮机翼片包括前缘和后缘。 还包括冷却通道，该冷却通道在径向方向上延伸并且朝向后缘向内逐渐变细，所述冷却通道至少部分地由压力侧面和吸力侧面限定。 另外包括从压力侧面和吸力侧面中的一个突出的第一多个紊流器以限定第一高度，第一多个涡流器朝向涡轮机翼型的后缘延伸并且彼此径向间隔开。 还包括第二多个涡轮，其从压力侧面和吸力侧面中的一个突出，以限定小于第一高度的第二高度，第二多个涡轮朝向涡轮机翼缘的后缘延伸， 彼此径向间隔开。
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公开(公告)号：US20140363279A1
公开(公告)日：2014-12-11
申请号：US13913920
申请日：2013-06-10
Applicant: General Electric Company
Inventor： Michael Anthony WONDRASEK , Nicholas Alvin Hogberg
CPC classification number: F01D11/006 , F01D5/3015 , F01D11/001
Abstract: A cover plate adapted to axially overlie root or shank portions of one or more buckets or blades secured to a turbomachine wheel, includes an arcuate cover plate body adapted to be secured to the turbomachine wheel so as to cover a root portion of at least one of the turbine buckets or blades; and at least one arcuate angel-wing seal segment detachably secured to one side of the arcuate cover plate body.
Abstract translation: 适于轴向覆盖固定到涡轮机轮的一个或多个铲斗或叶片的根部或柄部的盖板包括弧形盖板主体，其适于固定到涡轮机轮，以覆盖至少一个的根部部分 涡轮机叶片或叶片; 以及可拆卸地固定在弧形盖板主体的一侧的至少一个弓形天使翼密封段。
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公开(公告)号：US10196903B2
公开(公告)日：2019-02-05
申请号：US14996498
申请日：2016-01-15
Applicant: General Electric Company
Abstract: The present disclosure is directed to a rotor blade for a gas turbine engine. The rotor blade includes a platform comprising a radially inner surface, an undulating radially outer surface, a leading edge portion, a trailing edge portion, a pressure-side slash face, and a suction-side slash face. An airfoil extends outwardly from the undulating radially outer surface of the platform to an airfoil tip. A connection portion extends radially inwardly from the radially inner surface of the platform. The platform, the airfoil, and the connection portion collectively define a cooling circuit extending from an inlet in the connection portion through the airfoil to a plurality of outlet plena in the platform. Two or more outlet plena of the plurality of outlet plena are spaced equidistant from the undulating radially outer surface of the platform.
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公开(公告)号：US10138735B2
公开(公告)日：2018-11-27
申请号：US14932104
申请日：2015-11-04
Applicant: General Electric Company
Inventor： Adebukola Oluwaseun Benson , Xiuzhang James Zhang , Nicholas Alvin Hogberg , Kenneth Earl Williams
Abstract: In one aspect of the present disclosure, an airfoil for a rotor blade of a gas turbine includes a normalized pressure side wall portion thickness, a normalized suction side wall portion thickness, a normalized leading edge wall thickness, and a normalized trailing edge wall thickness. The values of theses thicknesses define the pressure side wall portion thickness, the suction side wall portion thickness, the leading edge wall thickness, and the trailing edge wall thickness, which improve heat transfer, flow distribution, and mechanical load transfer.
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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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