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公开(公告)号：US10107108B2
公开(公告)日：2018-10-23
申请号：US14699321
申请日：2015-04-29
Applicant: General Electric Company
Inventor： Jeffrey Clarence Jones , Xiuzhang James Zhang , Mitchell Allan Merrill
Abstract: A rotor blade includes an airfoil having a blade tip and a tip cavity formed at the blade tip. The tip cavity includes a tip cap that is recessed radially inwardly from the tip and surrounded continuously by pressure and suction side walls of the airfoil. The tip cap further includes an aperture that extends through the tip cap and provides for fluid communication between an internal cavity defined within the airfoil and the tip cavity. An exhaust port provides for fluid communication out the tip cavity through one of the pressure side wall, the suction side wall or the trailing edge. A portion of at least one of the suction side wall and the pressure side wall that defines the tip cavity extends obliquely outwardly from the tip cavity with respect to a radial direction.
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公开(公告)号：US10125632B2
公开(公告)日：2018-11-13
申请号：US14887988
申请日：2015-10-20
Applicant: General Electric Company
Inventor： Matthew Peter Scoffone , Jason Edward Albert , Michael Robert Berry , Mitchell Allan Merrill
Abstract: Cooling air extracted from a gas turbine engine compressor is sent to a nozzle vane cooling passage inlet, through the cooling passage, and to a purge tube of the vane. A mixing chamber formed in a diaphragm cavity receives fluid from the purge tube and directs it through exit passage(s) formed through a side wall of the mixing chamber and/or diaphragm cavity to a diametral surface of the diaphragm. The exit passage(s) can be inclined to induce a fluid velocity component substantially parallel to the diametral surface and/or in a rotation direction of a turbine wheel adjacent the diaphragm.
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公开(公告)号：US10132195B2
公开(公告)日：2018-11-20
申请号：US14918005
申请日：2015-10-20
Applicant: General Electric Company
Inventor： Matthew Peter Scoffone , Jason Edward Albert , Michael Robert Berry , Mitchell Allan Merrill
Abstract: Cooling air extracted from a gas turbine engine compressor is sent to nozzle vane cooling passage inlets, through the cooling passages, and to purge tubes of a set of two or more vanes. A mixing chamber formed between the purge tubes in a diaphragm cavity receives fluid from the purge tubes and directs it through exit passage(s) formed through a wall of the mixing chamber to a surface of the diaphragm. The exit passage(s) can be inclined to induce a fluid velocity component substantially parallel to the surface and/or in a rotation direction of a turbine wheel.
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公开(公告)号：US20170107850A1
公开(公告)日：2017-04-20
申请号：US14887988
申请日：2015-10-20
Applicant: General Electric Company
Inventor： Matthew Peter Scoffone , Jason Edward Albert , Michael Robert Berry , Mitchell Allan Merrill
CPC classification number: F01D25/12 , F01D5/189 , F01D9/02 , F01D9/06 , F01D25/08 , F05D2240/128 , F05D2260/20 , F05D2260/232
Abstract: Cooling air extracted from a gas turbine engine compressor is sent to a nozzle vane cooling passage inlet, through the cooling passage, and to a purge tube of the vane. A mixing chamber formed in a diaphragm cavity receives fluid from the purge tube and directs it through exit passage(s) formed through a side wall of the mixing chamber and/or diaphragm cavity to a diametral surface of the diaphragm. The exit passage(s) can be inclined to induce a fluid velocity component substantially parallel to the diametral surface and/or in a rotation direction of a turbine wheel adjacent the diaphragm.
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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：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：US20170107853A1
公开(公告)日：2017-04-20
申请号：US14918005
申请日：2015-10-20
Applicant: General Electric Company
Inventor： Matthew Peter Scoffone , Jason Edward Albert , Michael Robert Berry , Mitchell Allan Merrill
CPC classification number: F01D25/14 , F01D9/02 , F01D9/065 , F01D25/12 , F02C7/18 , F05D2240/10 , F05D2240/128 , F05D2260/202 , F05D2260/232 , Y02T50/676
Abstract: Cooling air extracted from a gas turbine engine compressor is sent to nozzle vane cooling passage inlets, through the cooling passages, and to purge tubes of a set of two or more vanes. A mixing chamber formed between the purge tubes in a diaphragm cavity receives fluid from the purge tubes and directs it through exit passage(s) formed through a wall of the mixing chamber to a surface of the diaphragm. The exit passage(s) can be inclined to induce a fluid velocity component substantially parallel to the surface and/or in a rotation direction of a turbine wheel.
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公开(公告)号：US20160319673A1
公开(公告)日：2016-11-03
申请号：US14699321
申请日：2015-04-29
Applicant: General Electric Company
Inventor： Jeffrey Clarence Jones , Xiuzhang James Zhang , Mitchell Allan Merrill
CPC classification number: F01D5/187 , F01D5/20 , F02C3/04 , F02C7/18 , F05D2220/32 , F05D2240/304 , F05D2240/307 , F05D2240/35 , F05D2250/294 , F05D2250/324 , F05D2260/202
Abstract: A rotor blade includes an airfoil having a blade tip and a tip cavity formed at the blade tip. The tip cavity includes a tip cap that is recessed radially inwardly from the tip and surrounded continuously by pressure and suction side walls of the airfoil. The tip cap further includes an aperture that extends through the tip cap and provides for fluid communication between an internal cavity defined within the airfoil and the tip cavity. An exhaust port provides for fluid communication out the tip cavity through one of the pressure side wall, the suction side wall or the trailing edge. A portion of at least one of the suction side wall and the pressure side wall that defines the tip cavity extends obliquely outwardly from the tip cavity with respect to a radial direction.
Abstract translation: 转子叶片包括具有形成在叶片尖端处的叶片尖端和尖端腔的翼型件。 尖端腔包括从尖端径向向内凹入并且被翼型的压力和吸力侧壁连续围绕的顶盖。 尖端帽还包括一个孔，其延伸穿过顶端帽，并提供在翼型内限定的内腔与尖端腔之间的流体连通。 排气口提供通过压力侧壁，吸力侧壁或后缘中的一个流体连通出口腔。 限定尖端腔的吸入侧壁和压力侧壁中的至少一个的一部分相对于径向方向从尖端腔倾斜向外延伸。
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公开(公告)号：US20150345332A1
公开(公告)日：2015-12-03
申请号：US14287717
申请日：2014-05-27
Applicant: General Electric Company
CPC classification number: F01D25/243 , F01D9/041 , F04D17/122 , F04D19/02 , F04D29/522 , F04D29/624 , F04D29/644 , F05D2230/64 , Y10T29/49321 , Y10T403/7075
Abstract: A horizontal joint of a rotary machine barrel includes first and second section mating surfaces that extend axially adjacent to the joint, and a plurality of gaps and a plurality of tangs disposed axially along the first and second section mating surfaces, respectively. Each tang has an axially extending tang aperture defined therethrough. Each gap is sized and axially spaced to receive a corresponding tang. Additionally, the joint includes a plurality of mating surface segments defined along the first section mating surface. Each segment extends axially between a corresponding pair of gaps and has an axially extending segment aperture defined therethrough. The tang apertures and segment apertures align to form a generally continuous axial pin aperture when the second section mating surface is positioned against the first section mating surface.
Abstract translation: 旋转机筒的水平接头包括分别沿轴向相对于接头延伸的第一和第二部分配合表面，以及分别沿第一和第二部分配合表面轴向设置的多个间隙和多个柄脚。 每个脚具有穿过其限定的轴向延伸的脚孔。 每个间隙的尺寸和轴向间隔开以接收相应的柄脚。 另外，接头包括沿着第一部分配合表面限定的多个配合表面段。 每个段在相应的一对间隙之间轴向延伸并且具有通过其限定的轴向延伸的节段孔。 当第二部分配合表面抵靠第一部分配合表面定位时，柄部孔和节段孔对齐以形成大致连续的轴向销孔。
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