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公开(公告)号：US20230018703A1
公开(公告)日：2023-01-19
申请号：US17379052
申请日：2021-07-19
Applicant: General Electric Company
IPC: F02C3/14
Abstract: A system includes an annular track that surrounds the turbomachine. The annular track includes an upper rail portion and a lower rail portion removably coupled to one another. The system further includes a drive assembly operably coupled to the annular track. The drive assembly includes a drive chain that extends along the annular track. The system further includes a plurality of carts rotatably coupled to the annular track and connected to the drive chain such that operation of the drive assembly alters a circumferential position of the plurality of carts with respect to an axial centerline of the turbomachine. The system further includes a plurality of combustion can cradle assemblies each coupled to a respective cart of the plurality of carts. Each combustion can cradle assembly of the plurality of combustion can cradle assemblies is configured to removably couple to a combustion can of the one or more combustion cans.
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2.发明授权公开(公告)号：US10544739B2
公开(公告)日：2020-01-28
申请号：US15049674
申请日：2016-02-22
Applicant: General Electric Company
Inventor： Alston Ilford Scipio , Michael Anthony Cocca , Thomas John Freeman , Michael Wesley Yarnold , Ryan Eric Obenhoff , Sanji Ekanayake , Douglas Corbin Warwick , Joseph Philip Klosinski
IPC: F02C6/08 , F02C9/18 , F02C3/34 , F02C9/22 , F02C9/26 , F01K23/10 , F02C3/13 , F02C9/28 , F23R3/26
Abstract: A gas turbine system includes a compressor protection subsystem; a hibernation mode subsystem; and a control subsystem that controls the compressor subsystem and the hibernation subsystem. At partial loads on the turbine system, the compressor protection subsystem maintains an air flow through a compressor at an airflow coefficient for the partial load above a minimum flow rate coefficient where aeromechanical stresses occur in the compressor. The air fuel ratio in a combustor is maintained where exhaust gas emission components from the turbine are maintained below a predetermined component emission level while operating at partial loads.
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公开(公告)号：US10344677B2
公开(公告)日：2019-07-09
申请号：US14290608
申请日：2014-05-29
Applicant: General Electric Company
Inventor： Sanji Ekanayake , Alston Ilford Scipio , Joseph Klosinski , William Theadore Fisher
Abstract: Systems and methods for preheating fuel in a gas turbine engine are provided. In one embodiment, a system may include a gas turbine engine, a fuel line in fluid communication with the gas turbine engine, a gas turbine compartment disposed about the gas turbine engine, and a first conduit in fluid communication with the gas turbine compartment. The first conduit may include ventilation discharge air from the gas turbine compartment. The system also may include a first heat exchanger in communication with the fuel line and the first conduit. The first heat exchanger may be configured to exchange heat between the fuel and the ventilation discharge air from the gas turbine compartment.
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公开(公告)号：US10253652B2
公开(公告)日：2019-04-09
申请号：US14969051
申请日：2015-12-15
Applicant: General Electric Company
Inventor： George Vargese Mathai , Alston Ilford Scipio , Harold Lamar Jordan, Jr. , Sanji Ekanayake , Joseph Philip Klosinski
Abstract: A system for controlling gas turbine output for a gas turbine power plant is disclosed herein. The power plant includes a gas turbine including a combustor downstream from a compressor, a turbine downstream from the combustor and an exhaust duct downstream from the outlet of the turbine. The exhaust duct receives exhaust gas from the turbine outlet. The system further includes an exhaust damper operably connected to a downstream end of the exhaust duct. The exhaust damper increases backpressure at the turbine outlet and restricts axial exit velocity of the exhaust gas exiting the turbine outlet when the exhaust damper is partially closed. A method for controlling gas turbine output is also provided herein.
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公开(公告)号：US20180216499A1
公开(公告)日：2018-08-02
申请号：US15420776
申请日：2017-01-31
Applicant: General Electric Company
Inventor： George Vargese Mathai , Joseph Philip Klosinski , Sanji Ekanayake , Alston Ilford Scipio , William Theadore Fisher
CPC classification number: F01K13/025 , F01D25/10 , F01K13/003 , F01K17/025 , F01K23/10 , F02C6/06 , F02C6/18 , F05D2220/72 , Y02E20/14 , Y02E20/16
Abstract: The present application provides a power generation system. The power generation system may include a gas turbine engine, a steam turbine, and a steam turbine preheating system. The steam turbine preheating system may include a steam generator that creates a flow of steam to preheat the steam turbine from an extraction of the gas turbine engine.
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Patent Agency Ranking
公开(公告)号：US10036321B2
公开(公告)日：2018-07-31
申请号：US14290580
申请日：2014-05-29
Applicant: General Electric Company
Inventor： Sanji Ekanayake , Alston Ilford Scipio , Joseph Klosinski , Pierre Antoine Semel
CPC classification number: F02C7/08 , F01D25/145 , F02C1/08 , F02C7/047 , F02C9/18
Abstract: Systems and methods for utilizing gas turbine compartment ventilation discharge air. In one embodiment, a system may include a gas turbine engine having a compressor. The system also may include a gas turbine compartment disposed about the gas turbine engine. Moreover, the system may include an inlet bleed heat (IBH) manifold in fluid communication with the compressor. The gas turbine compartment may be in fluid communication with the IBH manifold for providing the IBH manifold with ventilation discharge air from the gas turbine compartment.
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公开(公告)号：US20180073440A1
公开(公告)日：2018-03-15
申请号：US15264058
申请日：2016-09-13
Applicant: General Electric Company
Inventor： George Vargese Mathai , William Theadore Fisher , Joseph Philip Klosinski , Alston Ilford Scipio
CPC classification number: F02C9/48 , F01D11/14 , F01D11/22 , F01D11/24 , F01D25/24 , F02C6/18 , F05D2220/32 , F05D2220/72 , F05D2240/128 , F05D2240/307 , F05D2270/101 , F05D2270/30 , F05D2270/54 , F05D2270/60 , Y02E20/14
Abstract: This disclosure provides systems, methods, and storage medium for storing code related to controlling turbine shroud clearance for operational protection. The disclosure includes a multi-stage turbine and a protection system. The multi-stage turbine includes a stage of airfoils with a distal shroud, a casing adjacent the distal shroud and defining a clearance distance between the distal shroud and the casing, and a clearance control mechanism that controllably adjusts the clearance distance based upon receiving a clearance control signal. The protection system has an operational limit value related to a failure mode and provides the clearance control signal to the clearance control mechanism. The protection system receives operational data related to the multi-stage turbine and modifies the clearance control signal based on the operational limit value to increase the clearance distance.
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公开(公告)号：US20170342900A1
公开(公告)日：2017-11-30
申请号：US15167283
申请日：2016-05-27
Applicant: General Electric Company
Inventor： Alston Ilford Scipio , Jason Brian Schaffer , Joseph Philip Klosinski , David Clayton Poole , George Vargese Mathai
CPC classification number: F04D29/563 , F02C3/34 , F02C6/18 , F02C7/057 , F04D29/522 , F05D2260/601 , Y02E20/14 , Y02E20/16
Abstract: A system includes a controller configured to control a heated flow discharged from an outlet of an eductor to an inlet control system to control a temperature of an intake flow through a compressor inlet of a compressor of a gas turbine system. The controller is configured to control a turbine extraction gas (TEG) flow to a suction inlet of the eductor. The controller is configured to control a motive flow to a motive inlet of the eductor. The TEG flow is extracted through a turbine casing. The heated flow includes the TEG flow and the motive flow.
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公开(公告)号：US09816391B2
公开(公告)日：2017-11-14
申请号：US14493378
申请日：2014-09-23
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Sanji Ekanayake , Alston Ilford Scipio , Julio Enrique Mestroni , Timothy Joseph Rehg
CPC classification number: F01D25/002 , B05B7/0892 , B08B3/02 , B08B9/00
Abstract: The present application thus provides a cleaning system for use with a compressor of a turbine engine. The cleaning system may include a wash nozzle positioned about the compressor and a spheroid injection port to inject a number of spheroids therein.
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公开(公告)号：US20170218852A1
公开(公告)日：2017-08-03
申请号：US15012473
申请日：2016-02-01
Applicant: General Electric Company
Inventor： Joseph Philip Klosinski , Alston Ilford Scipio , Alex Clinton Solomon , Sanji Ekanayake , Hannah Louise Dombek
CPC classification number: F02C9/18 , F02C7/047 , F05D2220/32 , F05D2260/232 , F05D2270/101
Abstract: An inlet bleed heat system for use with a turbine assembly includes a first discharge line coupled in flow communication between a compressor and an intake manifold assembly. A first control valve that is coupled to the first discharge line and operable to control a first discharge flow through the first discharge line from the compressor to the intake manifold assembly during a first operational mode. A second discharge line that is coupled in flow communication between the compressor and the intake manifold assembly and a second control valve that is coupled to the second discharge line and operable to control a second discharge flow through the second discharge line from the compressor to the intake manifold assembly during a second operational mode.
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