Patents by Inventor Laxmikant Merchant
Laxmikant Merchant has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Patent number: 9771865Abstract: 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.Type: GrantFiled: October 28, 2014Date of Patent: September 26, 2017Assignee: General Electric CompanyInventors: Laxmikant Merchant, Richard Lynn Loud, Valery Ivanovich Ponyavin, Dinesh Venugopal Setty, Hua Zhang
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Publication number: 20170254222Abstract: 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.Type: ApplicationFiled: March 7, 2016Publication date: September 7, 2017Inventors: Hua Zhang, Laxmikant Merchant, Bradly Aaron Kippel, Valery Ivanovich Ponyavin
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Publication number: 20170252698Abstract: 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.Type: ApplicationFiled: March 3, 2016Publication date: September 7, 2017Inventors: Hua Zhang, Laxmikant Merchant, Bradly Aaron Kippel, Valery Ivanovich Ponyavin
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Publication number: 20170107907Abstract: The present application provides a gas turbine engine. The gas turbine engine may include a compressor air extraction system with a number of valves, an exhaust frame cooling system with an exhaust frame blower, and a turbine valve cooling system with one or more valve protection boxes surrounding one or more of the valves. The valve protection boxes may be in communication with a flow of air from the exhaust frame blower.Type: ApplicationFiled: October 19, 2015Publication date: April 20, 2017Inventors: Avishetti Srinivas, Laxmikant Merchant, Anil Kumar Dasoji, Ampili Kishore Kumar
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Publication number: 20170074289Abstract: 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.Type: ApplicationFiled: September 16, 2015Publication date: March 16, 2017Inventors: Laxmikant Merchant, Javeed Iqbaluddin Mohammed, Valery Ivanovich Ponyavin, Dinesh Venugopal Setty, Hua Zhang
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Publication number: 20170074288Abstract: A silencer duct that may be part of, for example, a turbomachine inlet may include a duct body. A first perforated wall extends within the duct body and substantially parallel to an interior surface of the duct body. A first acoustic absorbing material may be positioned between the duct body and the first perforated wall. A silencer element may extend axially through the duct body, the silencer element including a second perforated wall having a second acoustic absorbing material adjacent thereto.Type: ApplicationFiled: September 16, 2015Publication date: March 16, 2017Inventors: Dinesh Venugopal Setty, Dale Joel Davis, Laxmikant Merchant, Valery Ivanovich Ponyavin, Hua Zhang
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Publication number: 20170037781Abstract: An inlet system for a gas turbine includes an inlet duct, a silencer assembly disposed downstream from the inlet duct and an outlet duct disposed downstream from the silencer assembly. The silencer assembly may include a duct and a plurality of laterally spaced baffles disposed within the duct. The baffles may be arranged substantially parallel to a flow of air flowing through the inlet system. Each baffle includes a leading edge portion, a trailing edge portion that is longitudinally spaced from the leading edge portion and a pair of laterally opposing side walls that extend between the leading and trailing edges. Each baffle includes at least one acoustic panel that extends at least partially across one side wall of the pair of side walls.Type: ApplicationFiled: August 7, 2015Publication date: February 9, 2017Inventors: Valery Ivanovich Ponyavin, Hua Zhang, Dinesh Venugopal Setty, Laxmikant Merchant
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Patent number: 9551280Abstract: A silencer panel includes an acoustic absorbing material; and an enclosure surrounding the acoustic absorbing material. The enclosure includes at least one plastic, perforated side wall.Type: GrantFiled: September 16, 2015Date of Patent: January 24, 2017Assignee: General Electric CompanyInventors: Dinesh Venugopal Setty, Laxmikant Merchant, Javeed Iqbaluddin Mohammed, Valery Ivanovich Ponyavin, Hua Zhang
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Patent number: 9546582Abstract: A silencer panel section may include an acoustic absorbing material, a first enclosure surrounding the acoustic absorbing material, and a first coupler configured to couple the first enclosure to a second enclosure of an adjacent silencer panel section. A silencer panel may employ a plurality of the sections coupled together to form a single silencer panel. A silencer duct may include a frame forming a working fluid flow path, and a plurality of silencer panel mounts positioned within the frame, each silencer panel mount configured to slidingly receive a silencer panel, such as the silencer panel described herein.Type: GrantFiled: September 16, 2015Date of Patent: January 17, 2017Assignee: General Electric CompanyInventors: Hua Zhang, Laxmikant Merchant, Javeed Iqbaluddin Mohammed, Valery Ivanovich Ponyavin, Dinesh Venugopal Setty
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Patent number: 9506835Abstract: A fuel leak detection system for use in a turbine enclosure is provided. The system includes a ventilation duct extending through an interior cavity of the turbine enclosure such that an extended portion of the ventilation duct is positioned within a bottom portion of the turbine enclosure. The ventilation duct includes a plurality of openings configured to allow air from within the turbine enclosure to be drawn into the ventilation duct through the plurality of openings. The system also includes a sensor system coupled in flow communication with the air drawn into the ventilation duct, the sensor system configured to detect fuel in the air.Type: GrantFiled: April 23, 2014Date of Patent: November 29, 2016Assignee: General Electric CompanyInventors: Rajesh Reddy Konatham, Len Alan Wolf, Laxmikant Merchant, Rajakumar Alagappan, Lakshmi Bettadapura Shankar
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Publication number: 20160258357Abstract: 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.Type: ApplicationFiled: March 4, 2015Publication date: September 8, 2016Inventors: Hua Zhang, Dinesh Venugopal Setty, Laxmikant Merchant, Valery Ivanovich Ponyavin
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Patent number: 9359951Abstract: An inlet system for a gas turbine includes an inlet air duct; a silencer disposed in the inlet air duct, the silencer including a plurality of panels with spaces between the panels; and a conduit with orifices disposed to inject inlet bleed heat into each of the spaces. A method of conditioning inlet air for a gas turbine includes flowing air through spaces between panels of a silencer in an inlet air duct of the gas turbine, and injecting inlet bleed heat through orifices and into each of the spaces.Type: GrantFiled: September 6, 2013Date of Patent: June 7, 2016Assignee: General Electric CompanyInventors: Laxmikant Merchant, Srinivas Avishetti, Valery Ivanovich Ponyavin, Doug Byrd
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Publication number: 20160115870Abstract: 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.Type: ApplicationFiled: October 28, 2014Publication date: April 28, 2016Inventors: Laxmikant Merchant, Richard Lynn Loud, Valery Ivanovich Ponyavin, Dinesh Venugopal Setty, Hua Zhang
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Publication number: 20150308915Abstract: A fuel leak detection system for use in a turbine enclosure is provided. The system includes a ventilation duct extending through an interior cavity of the turbine enclosure such that an extended portion of the ventilation duct is positioned within a bottom portion of the turbine enclosure. The ventilation duct includes a plurality of openings configured to allow air from within the turbine enclosure to be drawn into the ventilation duct through the plurality of openings. The system also includes a sensor system coupled in flow communication with the air drawn into the ventilation duct, the sensor system configured to detect fuel in the air.Type: ApplicationFiled: April 23, 2014Publication date: October 29, 2015Applicant: General Electric CompanyInventors: Rajesh Reddy Konatham, Len Alan Wolf, Laxmikant Merchant, Rajakumar Alagappan, Lakshmi Bettadapura Shankar
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Patent number: 9046005Abstract: 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.Type: GrantFiled: April 3, 2013Date of Patent: June 2, 2015Assignee: GENERAL ELECTRIC COMPANYInventors: Hua Zhang, Douglas Scott Byrd, Laxmikant Merchant, Valery Ivanovich Ponyavin
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Publication number: 20150068217Abstract: An inlet system for a gas turbine includes an inlet air duct; a silencer disposed in the inlet air duct, the silencer including a plurality of panels with spaces between the panels; and a conduit with orifices disposed to inject inlet bleed heat into each of the spaces. A method of conditioning inlet air for a gas turbine includes flowing air through spaces between panels of a silencer in an inlet air duct of the gas turbine, and injecting inlet bleed heat through orifices and into each of the spaces.Type: ApplicationFiled: September 6, 2013Publication date: March 12, 2015Applicant: General Electric CompanyInventors: Laxmikant MERCHANT, Srinivas AVISHETTI, Valery Ivanovich PONYAVIN, Doug BYRD
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Publication number: 20140298771Abstract: 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.Type: ApplicationFiled: April 3, 2013Publication date: October 9, 2014Applicant: General Electric CompanyInventors: Hua Zhang, Douglas Scott Byrd, Laxmikant Merchant, Valery Ivanovich Ponyavin
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Publication number: 20140044517Abstract: An air supply and conditioning system for a turbine system includes an atomizing air system comprising at least one conditioning component configured to receive a compressor discharge air supply at an inlet at a first temperature and a first pressure, wherein the at least one conditioning component conditions the compressor discharge air supply to a second temperature and a second pressure at an outlet. Also included is an air processing unit configured to receive the compressor discharge air supply from the outlet of the atomizing air system, wherein the air processing unit further conditions the compressor discharge air supply to a third temperature and a third pressure. Further included is a filter housing having at least one filter for filtering a main inlet airstream, wherein the compressor discharge air supply is provided from the air processing unit to the at least one filter.Type: ApplicationFiled: August 10, 2012Publication date: February 13, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Rajarshi Saha, Venkateswara Rao Akana, Indrajit Mazumder, Laxmikant Merchant
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Publication number: 20130186435Abstract: The present application provides a water wash system for use with a compressor of a gas turbine engine. The water wash system may include a number of spray nozzles in communication with the compressor, a heat recovery steam generator, a flow of heating water from the heat recovery steam generator, and a tap off line in communication with the flow of heating water and the spray nozzles so as to deliver the flow of heating water to the compressor.Type: ApplicationFiled: January 23, 2012Publication date: July 25, 2013Applicant: GENERAL ELECTRIC COMPANHInventors: Rajarshi Saha, Laxmikant Merchant, Venkateswara Rao Akana
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Publication number: 20130168180Abstract: A gas turbine inlet system includes a main inlet portion, wherein an airflow is introduced to the gas turbine inlet system. Also included is a silencer assembly. The silencer assembly includes a first silencing panel, wherein the first silencing panel is oriented substantially perpendicularly to the airflow, and wherein the first silencing panel includes a first plurality of airflow apertures. The silencer assembly also includes a second silencing panel, wherein the second silencing panel is oriented substantially perpendicularly to the airflow, and wherein the second silencing panel includes a second plurality of airflow apertures.Type: ApplicationFiled: January 4, 2012Publication date: July 4, 2013Applicant: GENERAL ELECTRIC COMPANYInventors: Laxmikant Merchant, Dinesh Venugopal Setty