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公开(公告)号：US20170074289A1
公开(公告)日：2017-03-16
申请号：US14855902
申请日：2015-09-16
Applicant: General Electric Company
Inventor： Laxmikant Merchant , Javeed Iqbaluddin Mohammed , Valery Ivanovich Ponyavin , Dinesh Venugopal Setty , Hua Zhang
Abstract: A silencer duct that may be part of, for example, a turbomachine inlet and may include a duct body, and a silencer element extending axially through the duct body. A first portion of a coupler may extend axially from a first side of the duct body. A second portion of a coupler may extend axially from a second side of the duct body. At least one of the first portion of the coupler and the second portion of the coupler are configured to couple to at least one of an adjacent silencer duct and an inlet.
Abstract translation: 可以是例如涡轮机入口的一部分的消音器管道，并且可以包括管道主体和沿轴向延伸穿过管道主体的消音器元件。 耦合器的第一部分可以从导管主体的第一侧轴向延伸。 耦合器的第二部分可以从导管主体的第二侧轴向延伸。 耦合器的第一部分和耦合器的第二部分中的至少一个被配置成耦合到相邻的消声器导管和入口中的至少一个。
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公开(公告)号：US20160258357A1
公开(公告)日：2016-09-08
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
IPC: F02C7/045
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.
Abstract translation: 公开了一种用于燃气轮机入口系统管道的消声器装置。 入口管道包含一个主消音器和一个预消声器，以及位于消音器之间的入口泄放热（“IBH”）。 预消声器降低了来自涡轮压缩机的噪音水平，使气流/温度曲线更加均匀。 主消声器将IBH的噪音和压缩机的噪音降低到适当的水平。 主消声器包括沿燃气轮机入口管道中的气流方向设置的第一组多个吸声分离器。 预消音器由在气体涡轮机入口管道中沿着气体流动方向设置的第二多个吸声分离器组成，但是相对于第一多个分离器交错，从而阻挡用于噪声声波的直线行进 从压缩机在入口管道中与气体流动方向相反地行进。
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公开(公告)号：US11459951B2
公开(公告)日：2022-10-04
申请号：US17131280
申请日：2020-12-22
Applicant: General Electric Company
Inventor： Francisco Gomez , Laxmikant Merchant
Abstract: An anti-icing system for a gas turbine system includes multiple nozzles, wherein each nozzle of the multiple nozzles includes one or more outlets that are configured to inject a heated fluid into an airflow within an air intake conduit. The anti-icing system also includes multiple plates disposed upstream of the one or more outlets, wherein each plate of the multiple plates extends laterally across the air intake conduit and is vertically spaced apart from one or more adjacent plates to define one or more vertically-extending gaps. The multiple plates are configured to direct the airflow through the one or more vertically-extending gaps to spread the airflow upstream of the one or more outlets to facilitate mixing of the heated fluid and the airflow.
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公开(公告)号：US11248610B2
公开(公告)日：2022-02-15
申请号：US16883536
申请日：2020-05-26
Applicant: General Electric Company
Inventor： Laxmikant Merchant , Valery Ivanovich Ponyavin , Jeffrey Patrick Mills , Divya Reddy Kothakapu , Weilun Yu , Joshua Adam Bagwell
Abstract: A liquid injection apparatus for use with a compressor having a rotor shaft and a casing part is provided. The liquid injection apparatus includes at least one conduit and at least one nozzle coupled to the conduit(s). The liquid injection apparatus is panel-shaped and has a first panel segment, a second panel segment, and at least one of: a passage defined between the first panel segment and the second panel segment, the passage sized to receive at least one of the rotor shaft and the casing part; and a third panel segment positioned between the first panel segment and the second panel segment. The third panel segment is at least in part detachable from the first panel segment and/or the second panel segment for receiving at least one of the rotor shaft and the casing part between the first panel segment and the second panel segment.
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公开(公告)号：US20210025326A1
公开(公告)日：2021-01-28
申请号：US17067539
申请日：2020-10-09
Applicant: General Electric Company
Inventor： Valery Ivanovich Ponyavin , Bradly Aaron Kippel , Laxmikant Merchant , Hua Zhang , Naveen Parmeshwar
Abstract: An inlet bleed heat (IBH) system for use in a turbine engine including a silencer assembly. The inlet bleed heat (IBH) system includes a feed pipe for delivering compressor discharge air. The feed pipe includes a plurality of orifices along at least a portion of a length of the feed pipe, and each orifice of the plurality of orifices extends through a wall of the feed pipe for allowing the compressor discharge air to exit the feed pipe. The system also includes a heat shielding component that extends across the feed pipe, wherein the heat shielding component is configured to reduce heat transfer between the feed pipe and the silencer assembly of the turbine engine.
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Patent Agency Ranking
公开(公告)号：US10883387B2
公开(公告)日：2021-01-05
申请号：US15062958
申请日：2016-03-07
Applicant: General Electric Company
Inventor： Hua Zhang , Laxmikant Merchant , Bradly Aaron Kippel , Valery Ivanovich Ponyavin
Abstract: A gas turbine system includes an exhaust processing system that may process exhaust gas generated by a gas turbine engine, the exhaust processing system includes an exhaust diffuser that may receive the exhaust gas from a turbine of the gas turbine engine and having an annular passage disposed between an inner annular wall and an outer annular wall, and an air injection assembly disposed within the exhaust diffuser. The air injection assembly includes one or more air injection conduits disposed within the annular passage of the exhaust diffuser and including fluid injection holes that may direct a cooling fluid into a first mixing region of the exhaust diffuser.
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公开(公告)号：US20200284193A1
公开(公告)日：2020-09-10
申请号：US16294621
申请日：2019-03-06
Applicant: General Electric Company
Inventor： Laxmikant Merchant
IPC: F02C7/047
Abstract: An anti-icing system for a gas turbine system includes multiple nozzles arranged in a grid and configured to inject fluid within an air intake system of the gas turbine system upstream of a filter to keep ice from forming on the filter. Each nozzle of the multiple nozzles includes multiple orifices for injecting the fluid via jets. The anti-icing system also includes a nozzle head coupled to a nozzle of the multiple nozzles. The nozzle head is disposed over the multiple orifices and is configured to rotate relative to the nozzle. The nozzle head includes at least one outlet for injecting the fluid from the jets via at least one jet.
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公开(公告)号：US10670018B2
公开(公告)日：2020-06-02
申请号：US15584558
申请日：2017-05-02
Applicant: General Electric Company
Inventor： Laxmikant Merchant , Valery Ivanovich Ponyavin , Jeffrey Patrick Mills , Divya Reddy Kothakapu , Weilun Yu , Joshua Adam Bagwell
Abstract: A liquid injection apparatus for use with a compressor having a rotor shaft and a casing part is provided. The liquid injection apparatus includes at least one conduit and at least one nozzle coupled to the conduit(s). The liquid injection apparatus is panel-shaped and has a first panel segment, a second panel segment, and at least one of: a passage defined between the first panel segment and the second panel segment, the passage sized to receive at least one of the rotor shaft and the casing part; and a third panel segment positioned between the first panel segment and the second panel segment. The third panel segment is at least in part detachable from the first panel segment and/or the second panel segment for receiving at least one of the rotor shaft and the casing part between the first panel segment and the second panel segment.
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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：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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