Patent application number | Description | Published |
20130193127 | COMBUSTION TURBINE INLET ANTI-ICING RESISTIVE HEATING SYSTEM - A resistive heating system for a combustion turbine susceptible to inlet air filter house component and compressor icing includes a plurality of heating panels (bundles) arranged in a substantially-planar array, adapted to be located on or adjacent to the turbine's inlet air filter house. Each heating panel is provided with one or more electrically-resistive heating elements; and a controller for selectively activating the resistive heating elements on each of the plurality of heating panels. | 08-01-2013 |
20130318965 | Supercharged Combined Cycle System With Air Flow Bypass To HRSG And Hydraulically Coupled Fan - A supercharging system for a gas turbine system having a compressor, a combustor, a turbine and a shaft includes a prime mover and a fan assembly that provides an air stream at an air stream flow rate. A hydraulic coupler is coupled to the prime mover and the fan assembly and a second torque converter may couple the supercharger prime mover to an electrical generator. The supercharging system also includes a subsystem for conveying a first portion of the air stream to the compressor, and a bypass subsystem for optionally conveying a second portion of the air stream to other uses. | 12-05-2013 |
20130318987 | SUPERCHARGED COMBINED CYCLE SYSTEM WITH AIR FLOW BYPASS TO HRSG AND FAN - A supercharging system includes a fan providing an air flow, and a prime mover that drives the fan. A duct directs a first portion of the air flow to a gas turbine system, a main bypass subsystem diverts a second portion of the air flow to a heat recovery steam generator; and a drive bypass subsystem that diverts a third portion of the air flow to the prime mover. The prime mover may be one of an aeroderivative gas turbine, a gas turbine, a reciprocating engine, a steam turbine and an induction motor and a variable frequency drive. | 12-05-2013 |
20130330172 | METHOD, SYSTEM AND APPARATUS FOR ENHANCED OFF LINE COMPRESSOR AND TURBINE CLEANING - Methods, systems and apparatus for cleaning turbines, such as power generation turbines, are disclosed. Supplemental piping is connected to existing compressor air extraction and turbine nozzle cooling air piping, to supply water and/or cleaning agents into areas of a turbine not ordinarily accessible by injection of water and/or cleaning agents into the bellmouth of the turbine alone. Pressure and flow sensors, pumps, valving, and a control system to regulate the operation of the pumps and valving are provided to control the introduction of water and/or cleaning agents into the turbine. | 12-12-2013 |
20130340439 | Systems and Methods for De-Icing a Gas Turbine Engine Inlet Screen and Dehumidifying Inlet Air Filters - A system for de-icing a gas turbine engine is provided. A manifold is coupled to an inlet screen. A first conduit is coupled to a stage of the compressor and a first input of a mixing component. A second conduit is coupled to the exhaust and a second input of the mixing component. The second conduit being adapted to extract exhaust gases without increasing the pressure at the exhaust. A third conduit is coupled to the output of the mixing component and the manifold. A method for de-icing a gas turbine engine inlet screen includes determining a current temperature at the inlet screen, and determining a desired temperature at the inlet screen. If the current temperature at the inlet screen is less than the desired temperature at the inlet screen first flow rate of an air-exhaust mixture necessary to achieve the desired inlet screen temperature is calculated. The method also includes extracting an amount of exhaust gas from a turbine exhaust subsystem without increasing a pressure at the turbine exhaust subsystem, extracting an amount of air from a compressor stage, and mixing the amount of exhaust gas with the amount of air to generate an air-exhaust mixture that is conveyed to the inlet screen. | 12-26-2013 |
20140060061 | Systems and Methods for Removing Impurities from Heavy Fuel Oil - The present application provides a fuel delivery system for use with a flow of heavy fuel oil for a gas turbine engine. The fuel delivery system may include one or more fuel lines in communication with the gas turbine engine and a magnesium mixing system positioned upstream of the one or more fuel lines. The magnesium mixing system may include a flow of magnesium and a flow of a carrier fluid, a carrier mixing chamber to mix the flow of magnesium and the flow of the carrier fluid to form a mixed carrier flow, and a heavy fuel oil mixing chamber to mix the flow of heavy fuel oil and the mixed carrier flow. | 03-06-2014 |
20140079538 | REPLACEABLE SEALS FOR TURBINE ENGINE COMPONENTS AND METHODS FOR INSTALLING THE SAME - An assembly and method are provided for sealing a compressor in a gas turbine engine. The method comprises forming an annular groove in a compressor casing such that the groove extends circumferentially about a rotor that is housed within the casing. The compressor casing is then coupled to the rotor such that the compressor casing extends circumferentially about the rotor. A plurality of arcuate seal segments are then inserted into the annular groove without removing the rotor from the compressor casing such that the plurality of seal segments extend circumferentially about the rotor to facilitate sealing a gap that is defined between the rotor and the compressor casing. | 03-20-2014 |
20140090354 | TURBINE EXHAUST PLUME MITIGATION SYSTEM - Various embodiments include an exhaust plume mitigation system for a turbine and systems incorporating the exhaust plume mitigation system. In some embodiments, the exhaust plume mitigation system includes: a first conduit fluidly connecting a compressor to an exhaust chamber of the turbine; a first control valve operably connected with the first conduit for regulating flow of compressor air through the first conduit; and a fluid inductor including: a first inlet fluidly connected with the first conduit; a second inlet fluidly connected with ambient; and an outlet fluidly connected with the exhaust chamber. | 04-03-2014 |
20140096827 | GAS TURBINE ENGINE WITH A MULTIPLE FUEL DELIVERY SYSTEM - The present application provides a multiple fuel delivery system for use with a gas turbine engine. The multiple fuel delivery system may include a first fuel tank with a first fuel therein, a second fuel tank with a second fuel therein, a mixing chamber, and a flow divider downstream of the mixing chamber. The first fuel tank may be in communication with the mixing chamber via a first fuel pump and the second fuel tank may be in communication with the mixing chamber via a second fuel pump. | 04-10-2014 |
20140102179 | TURBINE LEAK DETECTION SYSTEM - Various embodiments include a leak detection system for a turbine compartment. In some embodiments, the leak detection system includes: a tracer fluid system fluidly connected with the turbine compartment, the tracer fluid system configured to provide an optically detectable fluid to a fluid supply of the turbine compartment; an optical detection system operably connected to the turbine compartment, the optical detection system configured to detect the presence of the optically detectable fluid in at least one location of the turbine compartment; and a control system operably connected to the tracer fluid system and the optical detection system, the control system configured to obtain data about the presence of the optically detectable fluid in the at least one location, and provide an indicator indicating a potential leak location based upon the data about the presence of the optically detectable fluid in the at least one location. | 04-17-2014 |
20140123666 | System to Improve Gas Turbine Output and Hot Gas Path Component Life Utilizing Humid Air for Nozzle Over Cooling - A system to improve gas turbine output and extend the life of hot gas path components includes a subsystem for estimating an amount of water or steam to be added to the flow of air to achieve the desired hot gas path temperature. The system includes a water or steam injection component adapted to inject the amount of water or steam to the flow of air to generate a flow of humid air and an injection subsystem adapted to inject the flow of humid air into a nozzle at the turbine stage are also included. The system includes a temperature sensor disposed at a turbine stage, and a subsystem for determining a desired hot gas path temperature at the turbine stage. An extraction conduit is coupled to a compressor stage and is adapted to extract a flow of air. | 05-08-2014 |
20140123853 | OFFLINE WATER WASH SYSTEM FOR INLET FILTERS AND FILTER HOUSE - A filter house and cleaning system arrangement for a turbine system and an associated method. The arrangement includes a filter house and filter elements within the filter house. The arrangement includes nozzles that spray a fluid on the filter elements to provide cleaning of the filter elements. The nozzles have structure that permits the nozzles to move within the filter house to adjust where on the filter elements the fluid is sprayed. The arrangement includes a detection device configured to detect a level of cleanliness and provide an output that indicates the level of cleanliness. | 05-08-2014 |
20140124007 | OFFLINE COMPRESSOR WASH SYSTEMS AND METHODS - The present application thus provides a wash system for use with a compressor having a bellmouth and one or more extraction pipes. The wash system may include a water source, a first fluid source, a mixing chamber in communication with the water source and the first fluid source, a bellmouth line in communication with the mixing chamber and the bellmouth, and a stage line in communication with one of the extraction pipes. | 05-08-2014 |
20140126991 | SYSTEMS AND METHODS FOR ACTIVE COMPONENT LIFE MANAGEMENT FOR GAS TURBINE ENGINES - The present application thus provides an active cooling system for a compressor and a turbine of a gas turbine engine. The active cooling system may include an air extraction pipe extending from the compressor to the turbine, a heat exchanger positioned about the air extraction pipe, and an external air cooling system in communication with the air extraction pipe. | 05-08-2014 |
20140174163 | Systems and Methods For Measuring Fouling in a Turbine System - Systems and methods for measuring fouling in a gas turbine compressor include a conductivity resistance sensor disposed in a compressor inlet mouth. The degree of compressor fouling is correlated to changes in resistance measured by the conductivity resistance sensor. Measurements of resistance changes are converted to an indicia of fouling and used to trigger cleaning of the compressor. | 06-26-2014 |
20140174474 | SYSTEMS AND METHODS FOR WASHING A GAS TURBINE COMPRESSOR - A method is provided for washing a compressor in a gas turbine. The method includes establishing a compressor fouling set point and sensing a fouling level in the compressor with a sensor. The fouling level is communicated to a control subsystem that determines a wash initiation instruction based on the fouling level and the compressor fouling set point. The wash initiation instruction is executed by initiating a wash with a fluid. A system is also disclosed including a compressor, an on-line wash system coupled to the compressor, and a compressor fouling sensor that senses a compressor fouling level. A source of washing fluid is provided, and a control subsystem that initiates a wash with washing fluid from the source of washing fluid based on a compressor fouling level. | 06-26-2014 |
20140202334 | FILTER SYSTEM AND METHOD FOR LEAK IDENTIFICATION - A filter system and method utilizing a plurality of filters each with an electrically conductive material portion for conducting an electric current while the filter maintains a tight seal and for not conducting the electric current when the filter does not maintain the tight seal. | 07-24-2014 |
20140208755 | Gas Turbine Air Mass Flow Measuring System and Methods for Measuring Air Mass Flow in a Gas Turbine Inlet Duct - A method and system for measuring a mass flow rate in a portion of a flow path in an inlet duct of a gas turbine engine is provided. The system includes a sensor assembly attached to the inlet duct. The sensor assembly includes a tube with a longitudinal axis disposed in a substantially laminar flow region of the inlet duct, and a flow conditioner disposed in the tube. A hot wire sensor disposed in the tube is also provided. | 07-31-2014 |
20140208759 | APPARATUS AND METHOD FOR REDUCING OIL MIST INGESTION IN A HEAVY DUTY GAS TURBINE ENGINE - A lubrication system for a heavy duty gas turbine includes a bearing lubrication assembly coupled to the bearing and an oil and vapor extraction assembly disposed in a cavity defined by a bell mouth hood in an air inlet duct. A high volume vacuum blower is coupled to the oil and vapor extraction assembly to provide a relative negative pressure. An oil and vapor separator is disposed downstream from the high volume vacuum blower. The lubrication system also includes a control subsystem that maintains a cavity pressure lower than an air inlet pressure. | 07-31-2014 |
20140208764 | SYSTEMS AND METHODS FOR MEASURING A FLOW PROFILE IN A TURBINE ENGINE FLOW PATH - A method and system for measuring a flow profile in a portion of a flow path in a turbine engine is provided. The system includes a mass flow sensor assembly having a plurality of hot wire mass flow sensors, the mass flow sensor assembly disposed in the portion of the flow path at a location where the flow profile is to be measured. The system also includes a controller that converts signals from the temperature sensor, the pressure sensor and the plurality of hot wire mass flow sensors to flow profile measurements. | 07-31-2014 |
20140208765 | Systems And Methods To Extend Gas Turbine Hot Gas Path Parts With Supercharged Air Flow Bypass - A system and method for supercharging a combined cycle system includes a forced draft fan providing a variable air flow. At least a first portion of the air flow is directed to a compressor and a second portion of the airflow is diverted to a heat recovery steam generator. A control system controls the airflows provided to the compressor and the heat recovery steam generator. The system allows a combined cycle system to be operated at a desired operating state, balancing cycle efficiency and component life, by controlling the flow of air from the forced draft fan to the compressor and the heat recovery steam generator. | 07-31-2014 |
20140208942 | Method, Apparatus, And System For Air Filter Cleaning - Disclosed are methods, apparatuses, and systems for generating an alert message based on a determined crossing of a weight threshold of a filter. | 07-31-2014 |
20140210217 | Gas Turbine Under Frequency Response Improvement System and Method - A system and method is provided that improves the under frequency response of gas turbines by providing a fast-response power augmentation system. The system includes a tank storing a blended mixture of motive fuel such as ethanol or methanol and demineralized water in a predetermined ratio that is provided as a diluent to be injected into the compressor bellmouth, the Compressor Discharge Chamber (CDC), and/or the combustion system via one to three dedicated circuits. To achieve the instantaneous injection of the diluent at the correct pressure and for the appropriate duration to meet the needs of the gas turbine Grid compliance mandate, an accumulator is used as the motive force to drive the augmentation fluid in the dedicated circuits. The injected diluent is microprocessor controlled to either be simultaneous into all three circuits or is sequenced based on a determination of the best turbine control and performance. | 07-31-2014 |
20140210984 | System, Apparatus, And Method For Gas Turbine Leak Detection - Disclosed are systems, apparatuses, and methods for monitoring fluid passage. In an embodiment, a device may receive a thermographic image of a region comprising a fluid passage. Subsequently the device may determine that the thermographic image comprises an image pattern indicative of a degraded portion of the fluid passage. | 07-31-2014 |
20140286766 | Compressor Casing Assembly Providing Access To Compressor Blade Sealing Assembly - A compressor casing assembly includes a forward compressor casing, a removable cover and a seal assembly. A midcompressor casing is provided with a cavity adapted to receive the seal assembly, and a cover groove adapted to receive the removable cover. The removable cover secures the seal assembly. | 09-25-2014 |
20150044031 | AIR DISRUPTION SYSTEM FOR AN ENCLOSURE - An air disruption system for an enclosure includes an air delivery system, at least one plenum including an inlet fluidically connected to the air delivery system and at least one outlet, and a controller operatively connected to the air delivery system. The controller is configured and disposed to selectively cause one or more discrete amounts of air to pass into the at least one plenum and flow through the outlet creating a localized air disruption. | 02-12-2015 |
20150056066 | COMPRESSOR WASH SYSTEM WITH SPHEROIDS - 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. | 02-26-2015 |
20150056912 | SYSTEM ENCLOSURE VENTILATION MONITORING SYSTEM - A system enclosure ventilation monitoring system includes a controller having an enclosure temperature input configured to receive signals indicating internal temperatures of the system enclosure, an air circulating device speed input configured to receive signals indicating operating speed of at least one air circulating device, and a damper position input configured to receive a damper position signal and an output. The controller is configured and disposed to set damper position through the output based on at least one of the air circulating device speed input and the enclosure temperature input. | 02-26-2015 |
20150075170 | METHOD AND SYSTEM FOR AUGMENTING THE DETECTION RELIABILITY OF SECONDARY FLAME DETECTORS IN A GAS TURBINE - Systems and methods for operating a gas turbine combustion system by generating a flame detection signal are provided. A set of modeled parameters expected when there is a flame in a secondary combustion zone is calculated. A set of measured gas turbine parameters is measured. A flame validation signal based on the set of measured parameters and the set of modeled parameters is generated. The systems include a subsystem that calculates a set of modeled parameters expected when there is a flame in the secondary combustion zone and a subsystem that measures a set of measured parameters. A subsystem generates a flame validation signal based on the set of measured parameters and the set of modeled parameters. | 03-19-2015 |
20150076821 | System And Method To Minimize Grid Spinning Reserve Losses By Pre-Emptively Sequencing Power Generation Equipment To Offset Wind Generation Capacity Based On Geospatial Regional Wind Conditions - A system and method to preemptively adjust power generation of one or more non-wind power generators based on near term wind generation capability, spinning reserve margin, and/or power grid spinning reserve forecast requirements to offset wind power generation based on geospatial regional wind conditions. | 03-19-2015 |
20150081124 | System And Method To Minimize Grid Spinning Reserve Losses By Pre-Emptively Sequencing Power Generation Equipment To Offset Solar Generation Capacity Based On Geospatial Regional Solar And Cloud Conditions - A system and method to preemptively adjust power generation of one or more non-solar power generators based on near term solar generation capability, spinning reserve margin, and/or power grid spinning reserve forecast requirements to offset solar power generation based on geospatial regional solar conditions. | 03-19-2015 |
20150099429 | REFURBISHING SYSTEM - A system for refurbishing at least one article attached to an assembly includes a refurbishing vessel that contains at least one wall and at least one open portion; means for providing an abrasive media to the vessel, wherein the abrasive media is caused to flow around the surfaces of the at least one article when the vessel is positioned on the at least one article; means for conformably sealing the at least one open portion against the flow of abrasive media, wherein a seal is created that conforms to the contours of the at least one article and prevents the abrasive media from escaping between the at least one article and the at least one wall; and means for removing the abrasive media from the vessel. | 04-09-2015 |
20150101401 | Method And System For Determining Wind Turbine Reliability - Disclosed are methods and systems to determine a reliability forecast for a wind turbine. In an embodiment, a method may comprise obtaining an environmental factor of a wind turbine based on geospatial data of a first area and location data of a second area, obtaining an operating factor of the wind turbine, and determining a reliability forecast based on the environmental factor and the operating factor. | 04-16-2015 |
20150106059 | Method And System For Determining Power Plant Machine Reliability - Disclosed are methods and systems to determine a power plant machine reliability forecast. In an embodiment, a method may comprise obtaining an environmental factor of a power plant machine based on geospatial data of a first area and location data of a second area, obtaining an operating factor of the power plant machine, and determining a reliability forecast based on the obtained environmental factor and the obtained operating factor. | 04-16-2015 |
20150107254 | Method and System for Improving the Efficiency of a Simple Cycle Gas Turbine System With a Closed Circuit Fuel Heating System - A closed circuit fuel heating system is provided for heating at least two types of fuel. The heating system includes a heat transfer subsystem disposed in a gas turbine system exhaust. A first heat exchange subsystem is coupled to a first fuel source and the heat transfer subsystem. The first heat exchange subsystem is provided with a control component for controlling a flow of a working fluid through the first heat exchange subsystem. A second heat exchange subsystem may be coupled to a second fuel source and the heat transfer subsystem. The second heat exchange subsystem is provided with a control component for controlling a flow of the working fluid through the second exchange subsystem. A subsystem for controlling the temperature of the working fluid is also provided. | 04-23-2015 |
20150114221 | Gas Turbine Inlet Air Filter Cleaning Control - A gas turbine inlet air filter house control system may obtain geospatial data for an area in which a gas turbine is located. The gas turbine inlet air filter house control system may determine filter cleaning parameters for the gas turbine based on the geospatial data and control the initiation and duration of the inlet air filter cleaning process. | 04-30-2015 |
20150121888 | GAS TURBINE ONLINE WASH CONTROL - A gas turbine online wash control system may obtain geospatial data for an area in which a gas turbine is located. The gas turbine online wash control system may determine wash control parameters for the gas turbine based on the geospatial data. | 05-07-2015 |
20150159505 | GAS TURBINE ORGANIC ACID BASED INTER-RINSE - A gas turbine wash control system may perform a wash and a rinse of a gas turbine that is offline. An inter-rinse solution may be injected into the gas turbine. The gas turbine may be agitated and the inter-rinse solution drained. A second rinse of the gas turbine may be performed followed by the injection of an anticorrosive solution into the gas turbine. | 06-11-2015 |
20150159506 | GAS TURBINE PERACETIC ACID SOLUTION INTER-RINSE - A gas turbine wash control system may perform a wash and a rinse of a gas turbine that is offline. An peracetic acid inter-rinse solution may be injected into the gas turbine. The gas turbine may be agitated and the peracetic acid inter-rinse solution drained. A second rinse of the gas turbine may be performed followed by the injection of an anticorrosive solution into the gas turbine. | 06-11-2015 |
20150159558 | Method And System For Dispensing Gas Turbine Anticorrosion Fluid - Disclosed herein are methods and systems for dispensing turbine engine anticorrosive protection. In an embodiment, a method may include selecting an anticorrosion fluid for a gas turbine engine and applying the anticorrosion fluid to the gas turbine engine. | 06-11-2015 |
20150159559 | Method and System for Compressor On Line Water Washing With Anticorrosive Solution - Methods and systems may dispense turbine engine anticorrosive protection. In an embodiment, a method may include determining a condition of a gas turbine engine while the gas turbine engine is online, wherein the condition includes the power output level of the gas turbine engine and applying, based on the condition, an anticorrosion fluid to the gas turbine engine while the gas turbine engine is online. | 06-11-2015 |
20150197712 | APPARATUS, METHOD, AND SOLVENT FOR CLEANING TURBINE COMPONENTS - A cleaning method and a cleaning fluid are provided. The cleaning method includes accessing a plurality of turbine components attached to a turbine assembly, the turbine assembly being a portion of a turbomachine, positioning at least one cleaning vessel over at least one of the turbine components, forming a liquid seal with a sealing bladder, providing a cleaning fluid to the cleaning vessel, and draining the cleaning fluid from the cleaning vessel. The cleaning fluid includes a carrier fluid and a solvent additive for removing fouling material from the turbine component. An alternative cleaning method is also provided. | 07-16-2015 |
20150198059 | GAS TURBINE MANUAL CLEANING AND PASSIVATION - A gas turbine engine may be manually cleaned by removing a compressor casing and a turbine casing from the gas turbine engine, cleaning stator vanes of the gas turbine engine, and applying an organic acid solution to metallic surfaces of the gas turbine engine. The organic acid solution may be rinsed from the gas turbine engine and an anticorrosive solution may be applied to the metallic surfaces of the gas turbine engine. | 07-16-2015 |