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公开(公告)号：US20180073386A1
公开(公告)日：2018-03-15
申请号：US15263019
申请日：2016-09-12
Applicant: General Electric Company
Inventor： Hua Zhang , Bradly Kippel , David Trayhan , Iris Hu
CPC classification number: F01D21/003 , B01D46/0068 , B01D46/008 , B01D46/0086 , B01D46/442 , B01D46/446 , B01D46/448 , F01D25/002 , F02C7/055 , F05D2230/72 , F05D2260/607 , F05D2260/80 , G01M15/14 , G05B23/0283
Abstract: In one embodiment, a turbine system includes an intake section including a filter house, the filter house including at least one filtration stage, each of the at least one filtration stage, including a filter. The turbine system also includes one or more sensors disposed in the intake section, and a processor configured to receive performance data related to testing conditions of the intake section, sensor data from the one or more sensors, local conditions data, or some combination thereof, predict a filter degradation rate for the filter using a filter degradation prediction model that provides a function of performance of the filter based on the performance data, the sensor data, the local conditions data, or some combination thereof, and perform one or more preventative actions based on the filter degradation rate prediction.
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公开(公告)号：US09890713B2
公开(公告)日：2018-02-13
申请号：US14638472
申请日：2015-03-04
Applicant: General Electric Company
Inventor： Hua Zhang , Dinesh Venugopal Setty , Laxmikant Merchant , Valery Ivanovich Ponyavin
CPC classification number: F02C7/045 , B64D29/00 , F02C3/30 , F02C7/047 , F05D2260/96
Abstract: A silencer apparatus for a gas turbine inlet system ducting is disclosed. The inlet ducting contains a main silencer and a pre-silencer, and Inlet Bleed Heat (“IBH”) located between the silencers. The pre-silencer decreases the noise level from the turbine compressor and makes the air flow/temperature profiles more uniform. The main silencer reduces noise from the IBH and the remaining noise from the compressor to an appropriate level. The main silencer is comprised of a first plurality of sound-absorbing splitters disposed along the gas flow direction in the gas turbine inlet ducting. The pre-silencer is comprised of a second plurality of sound-absorbing splitters disposed along the gas flow direction in the gas turbine inlet ducting, but staggered with respect to the first plurality of splitters to thereby block a direct line of travel for noise acoustical waves from the compressor travelling opposite the gas flow direction in the inlet ducting.
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公开(公告)号：US20180023398A1
公开(公告)日：2018-01-25
申请号：US15217033
申请日：2016-07-22
Applicant: General Electric Company
Inventor： Jeffrey Clarence Jones , Thomas James Brunt , Jason Anton Byers , Adam John Fredmonski , Hua Zhang
CPC classification number: F01D5/145 , F01D5/186 , F01D5/188 , F05D2220/30 , F05D2240/303 , F05D2240/304 , F05D2250/61 , F05D2250/711 , F05D2250/712 , F05D2260/201 , Y02T50/673 , Y02T50/676
Abstract: A blade includes an airfoil body defined by a concave pressure side outer wall and a convex suction side outer wall that connect along leading and trailing edges and, therebetween, form a radially extending chamber for receiving the flow of a coolant. The airfoil body has an inner surface facing the radially extending chamber and an outer surface, a first corrugated surface on a portion of the outer surface, and a second corrugated surface on the inner surface paralleling the first corrugated surface. The corrugated surface on the outer surface of the airfoil provides wake mixing. The blade may also include an integrally formed impingement cooling structure having a third corrugated surface parallel to the second corrugated surface, which is made possible through additive manufacturing. The impingement cooling structure so formed provides improved cooling of the blade.
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公开(公告)号：US09771865B2
公开(公告)日：2017-09-26
申请号：US14525494
申请日：2014-10-28
Applicant: General Electric Company
Inventor： Laxmikant Merchant , Richard Lynn Loud , Valery Ivanovich Ponyavin , Dinesh Venugopal Setty , Hua Zhang
Abstract: An inlet bleed heat (IBH) system manifold for a compressor inlet housing is provided. The manifold includes: a plurality of feed pipes for delivering a compressor discharge air, each feed pipe extending across a duct of the compressor inlet housing. Each feed pipe includes: an elongated inner feed pipe for delivering the compressor discharge air, the inner feed pipe including a plurality of orifices along at least a portion of a length of the inner feed pipe, each orifice extending through a wall of the inner feed pipe allowing the compressor discharge air to exit the inner feed pipe; and a noise attenuating material disposed about the inner feed pipe and the plurality of orifices, the noise attenuating material configured to attenuate noise created by the compressor discharge air exiting the plurality of orifices.
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公开(公告)号：US20170204786A1
公开(公告)日：2017-07-20
申请号：US14997319
申请日：2016-01-15
Applicant: General Electric Company
Inventor： Hua Zhang , Parag Prakash Kulkarni , Bradly Aaron Kippel
CPC classification number: F02C7/18 , F01D25/305 , F02C7/052 , F02C9/16 , F05D2270/082 , F05D2270/3062
Abstract: A gas turbine system includes a gas turbine engine, an exhaust processing system disposed downstream of and fluidly coupled to the gas turbine engine, and an air delivery system that may supply treated air to the gas turbine engine and the exhaust processing system. The air delivery system includes a main air duct fluidly coupled to the gas turbine engine and that may supply a first portion of the treated air to the gas turbine engine, an auxiliary air duct fluidly coupled to the main air duct and the exhaust processing system and that may supply a second portion of the treated air to the exhaust processing system, and an air treatment unit fluidly coupled to the main air duct and that may generate the treated air.
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Patent Agency Ranking
公开(公告)号：US20170204771A1
公开(公告)日：2017-07-20
申请号：US15001823
申请日：2016-01-20
Applicant: General Electric Company
Inventor： Hua Zhang , Parag Prakash Kulkarni , Bradly Aaron Kippel
IPC: F01N9/00
CPC classification number: F01N9/00 , F01D25/305 , F01N3/05 , F01N3/2066 , F01N3/22 , F01N3/2892 , F01N3/30 , F01N3/32 , F01N11/002 , F01N13/009 , F01N2240/20 , F01N2270/02 , F01N2270/10 , F01N2550/00 , F01N2610/02 , F01N2610/08 , F01N2900/0416 , F01N2900/1404 , F05D2270/082 , Y02T10/24 , Y02T10/47
Abstract: A system includes a system includes an exhaust section which receives an exhaust flow of a gas turbine, where the exhaust section includes a catalyst assembly. The system includes an exhaust duct coupled to the diffuser section upstream of the catalyst assembly, where the exhaust duct extracts a return portion of the exhaust flow. The system includes a filter house coupled to the exhaust duct, where the filter house is receives a combined flow of an ambient air flow and the return portion. The system includes a return conduit coupled to the filter house and the exhaust section, where the return conduit is coupled to the exhaust section upstream of the exhaust duct. The return conduit directs the combined flow to the exhaust section, and the catalyst assembly receives a mixed flow including the exhaust flow and the combined flow.
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公开(公告)号：US09046005B2
公开(公告)日：2015-06-02
申请号：US13855907
申请日：2013-04-03
Applicant: General Electric Company
Inventor： Hua Zhang , Douglas Scott Byrd , Laxmikant Merchant , Valery Ivanovich Ponyavin
CPC classification number: F01D25/30 , F01D25/305 , F02C6/18 , F02K1/822 , F05D2250/232 , F05D2250/25
Abstract: A gas turbine exhaust diffuser includes a frustoconical portion that defines an interior surface and an axial centerline. In particular embodiments, the interior surface may have a slope greater than 6 degrees, 10 degrees, or 20 degrees with respect to the axial centerline to define an axial cross-sectional area of at least 200 square feet, 240 square feet, or 260 square feet. In other particular embodiments, the interior surface may have an axial length of less than 25 feet or less than 10 feet. A helical turbulator on the interior surface of the frustoconical portion may reduce flow separation between exhaust gases and the interior surface to enhance recovery of potential energy from the exhaust gases.
Abstract translation: 燃气轮机排气扩散器包括限定内表面和轴向中心线的截头圆锥形部分。 在特定实施例中，内表面可以具有相对于轴向中心线大于6度，10度或20度的斜率，以限定至少200平方英尺，240平方英尺或260平方的轴向横截面积 脚。 在其它具体实施例中，内表面可以具有小于25英尺或小于10英尺的轴向长度。 在截头圆锥形部分的内表面上的螺旋形紊流器可以减少废气和内表面之间的流动分离，以增强来自废气的势能回收。
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公开(公告)号：US20140298771A1
公开(公告)日：2014-10-09
申请号：US13855907
申请日：2013-04-03
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Hua Zhang , Douglas Scott Byrd , Laxmikant Merchant , Valery Ivanovich Ponyavin
IPC: F01D25/30
CPC classification number: F01D25/30 , F01D25/305 , F02C6/18 , F02K1/822 , F05D2250/232 , F05D2250/25
Abstract: A gas turbine exhaust diffuser includes a frustoconical portion that defines an interior surface and an axial centerline. In particular embodiments, the interior surface may have a slope greater than 6 degrees, 10 degrees, or 20 degrees with respect to the axial centerline to define an axial cross-sectional area of at least 200 square feet, 240 square feet, or 260 square feet. In other particular embodiments, the interior surface may have an axial length of less than 25 feet or less than 10 feet. A helical turbulator on the interior surface of the frustoconical portion may reduce flow separation between exhaust gases and the interior surface to enhance recovery of potential energy from the exhaust gases.
Abstract translation: 燃气轮机排气扩散器包括限定内表面和轴向中心线的截头圆锥形部分。 在特定实施例中，内表面可以具有相对于轴向中心线大于6度，10度或20度的斜率，以限定至少200平方英尺，240平方英尺或260平方的轴向横截面积 脚。 在其它具体实施例中，内表面可以具有小于25英尺或小于10英尺的轴向长度。 在截头圆锥形部分的内表面上的螺旋形紊流器可以减少废气与内表面之间的流动分离，以增强来自废气的势能回收。
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公开(公告)号：US20140123674A1
公开(公告)日：2014-05-08
申请号：US13669478
申请日：2012-11-06
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Yongjiang Hao , Douglas Scott Byrd , Hua Zhang , Bradly Aaron Kippel , Jianmin Zhang
CPC classification number: F01D25/08 , F01D25/10 , F02C6/06 , F02C7/04 , F02C7/045 , F02C7/057 , F05D2260/96
Abstract: The present application provides an inlet bleed heat system for supplying a flow of bleed air to a flow of incoming air into a compressor of a gas turbine engine. The inlet bleed heat system may include an air knife and a silencer panel. The air knife may include a compressor bleed air port in communication with the flow of bleed air and a discharge gap to discharge the flow of bleed air into the flow of incoming air. The air knife may and the silencer panel may form an integrated air knife/silencer panel.
Abstract translation: 本申请提供了一种入口放气加热系统，用于将进气流输送到燃气涡轮发动机的压缩机中。 入口放气加热系统可以包括气刀和消声器面板。 气刀可以包括与排放气流连通的压缩机排气口和排放间隙，以将排出的空气流进入进入的空气流中。 气刀可以和消音器面板可以形成一体的气刀/消声器面板。
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公开(公告)号：US11208959B2
公开(公告)日：2021-12-28
申请号：US15346973
申请日：2016-11-09
Applicant: General Electric Company
Inventor： Yimin Huang , Manuel Cardenas , Hua Zhang
Abstract: A system includes a gas turbine system having a first compressor, a combustor, and a turbine, where the first compressor provides a first portion of a discharge air directly to the combustor. The system includes a fluid circuit which receives a fluid comprising a second portion of the discharge air from the first compressor or a combustible fluid and provides the second portion of the discharge air to fuel at a location upstream of the combustor to alter a chemical and physical characteristic of the fuel in an air-fuel mixture that is provided to the combustor.
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