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公开(公告)号：US20180016902A1
公开(公告)日：2018-01-18
申请号：US15207750
申请日：2016-07-12
Applicant: General Electric Company
Inventor： Dennis Scott Holloway , Adebukola Oluwaseun Benson , Melbourne James Myers , Peter Paul Pirolla , William Scott Zemitis
CPC classification number: F01D5/141 , F01D5/145 , F05D2250/74 , Y02E20/16 , Y02T50/673
Abstract: Various embodiments of the invention include turbine blades and systems employing such blades. Various particular embodiments include a turbine blade 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, wherein the trailing edge defines a radial throat distribution between the airfoil and an adjacent 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：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：US20170122111A1
公开(公告)日：2017-05-04
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
IPC: F01D5/18
CPC classification number: F01D5/188 , F01D5/147 , F05D2260/201
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：US10247006B2
公开(公告)日：2019-04-02
申请号：US15207750
申请日：2016-07-12
Applicant: General Electric Company
Inventor： Dennis Scott Holloway , Adebukola Oluwaseun Benson , Melbourne James Myers , Peter Paul Pirolla , William Scott Zemitis
Abstract: Various embodiments of the invention include turbine blades and systems employing such blades. Various particular embodiments include a turbine blade 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, wherein the trailing edge defines a radial throat distribution between the airfoil and an adjacent 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：US10001013B2
公开(公告)日：2018-06-19
申请号：US14198659
申请日：2014-03-06
Applicant: General Electric Company
Inventor： Brad Wilson VanTassel , James Ryan Connor , Bryan David Lewis , Adebukola Oluwaseun Benson
CPC classification number: F01D5/082 , B23P15/02 , F01D5/187 , F01D11/24 , F05D2240/11 , F05D2240/81 , F05D2260/201 , Y02T50/676 , Y10T29/49341
Abstract: Platform cooling arrangements in a turbine rotor blade include a feedhole that extends from the suction side slash face to the interior cooling passage, and, one or more branch holes that each extends from the feedhole to the suction side slash face such that coolant flows from the interior cooling passage, through the feedhole to the one or more branch holes and exits the platform along the suction side slash face.
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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：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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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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