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公开(公告)号：US10260418B2
公开(公告)日：2019-04-16
申请号：US15463902
申请日：2017-03-20
Applicant: General Electric Company
Inventor： Hua Zhang , Naveen Ghattadhahalli Parmeshwar , Christopher Conrad Frese , Valery Ivanovich Ponyavin , Bradly Aaron Kippel
Abstract: The present application provides a method of evaluating media effectiveness in a gas turbine engine. The method may include the steps of receiving a baseline media effectiveness rating, receiving a media replacement cost, receiving a number of operating parameters from a number of sensors, based at least in part on the operating parameters and the baseline media effectiveness rating, determining a media effectiveness model, based at least in part of the media effectiveness model, determining a loss in evaporative benefit cost over time, determining a time t when the loss in evaporative benefit cost exceeds the media replacement cost, and scheduling media replacement at time t.
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公开(公告)号：US10092878B2
公开(公告)日：2018-10-09
申请号：US15060161
申请日：2016-03-03
Applicant: General Electric Company
Inventor： Hua Zhang , Laxmikant Merchant , Bradly Aaron Kippel , Valery Ivanovich Ponyavin
Abstract: A simple-cycle gas turbine system includes an injection system including a plurality of injection tubes that may inject a fluid into a duct of an exhaust processing system that may process exhaust gas generated by a gas turbine engine. The exhaust processing system includes a selective catalytic reduction (SCR) system that may reduce a level of nitrogen oxides (NOx) within the exhaust gas; and a mixing system positioned adjacent to the plurality of injection tubes and within the exhaust processing system. The mixing system includes a mixing module having a plurality of turbulators that may swirl the fluid, or the exhaust gas, or both, in a first swirl direction to encourage turbulent flow along an axis of the exhaust processing system and thereby facilitate mixing between the fluid and the exhaust gas.
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公开(公告)号：US20180266325A1
公开(公告)日：2018-09-20
申请号：US15463807
申请日：2017-03-20
Applicant: General Electric Company
Inventor： Naveen Ghattadhahalli PARMESHWAR , Hua Zhang , Christopher Conrad Frese , Valery Ivanovich Ponyavin , Bradly Aaron Kippel
CPC classification number: F02C7/18 , F01D25/12 , F02C7/185 , F05D2260/207 , F05D2260/212 , F05D2300/43
Abstract: The present application provides a gas turbine engine. The gas turbine engine may include a compressor, a turbine, one or more hot gas path components positioned downstream of the turbine, an extraction from the compressor to the one or more hot gas path components, and an extraction cooling system in communication with the extraction. The extraction cooling system may include an evaporative cooling media.
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公开(公告)号：US20180266317A1
公开(公告)日：2018-09-20
申请号：US15463711
申请日：2017-03-20
Applicant: General Electric Company
Inventor： Hua ZHANG , Naveen Ghattadhahalli Parmeshwar , Christopher Conrad Frese , Valery Ivanovich Ponyavin , Bradly Aaron Kippel
Abstract: The present application provides a gas turbine engine. The gas turbine engine may include a compressor and an inlet air system positioned upstream of the compressor. The inlet air system may include a wetted media pad for evaporative cooling. The wetted media pad may include a number of synthetic media sheets with a number of micro-channels therein.
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Patent Agency Ranking
公开(公告)号：US09951646B2
公开(公告)日：2018-04-24
申请号：US13932467
申请日：2013-07-01
Applicant: General Electric Company
Inventor： Doug Scott Byrd , Gilbert Otto Kraemer , Hua Zhang , Jianmin Zhang , Valery Ivanovich Ponyavin
CPC classification number: F01D25/002 , B08B7/00 , F05D2270/172
Abstract: An on-line wash system for a compressor including: a nozzle including a flow passage for wash liquid, wherein the flow passage is configured to be coupled to a source of a wash liquid and includes a discharge outlet arranged to project the wash liquid into a stream of working fluid for the turbomachine; an electrode proximate to the flow passage of the nozzle, wherein the electrode is configured to form an electrical field sufficient to charge the wash liquid flowing through the passage and the charge applied to the wash liquid is of a first polarity, and a surface of the compressor charged with the first polarity, wherein the surface is exposed to the stream of working fluid and downstream of the nozzle.
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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：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：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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