Patent application number | Description | Published |
20080202092 | Mixer for cooling and sealing air system of turbomachinery - A system is provided for directing air from plural compressor ports to provide cooling and/or sealing air to an associated turbine site. A first flow from a pressure stage of the compressor has a first pressure and temperature. A second flow from another pressure stage of the compressor has a second pressure and temperature. The first and second pressures/temperatures are different. An ejector has two inlets for receiving the first and second flows, and output for combining the first and second flows into a third flow. The pressure and temperature of the third flow are different from the first and second pressures and temperatures. A bypass line is connected between the first flow and the third flow, and provides a bypass flow. A mixer combines the bypass flow and the third flow into a fourth flow. The fourth flow has a pressure and temperature intermediate the pressure and temperature of the bypass flow and the third flow. The mixer comprises inner and outer sections. The inner section is generally cylindrical in cross section and has a plurality of holes therein. The angle between the direction of the bypass flow and the direction of the third flow, when the bypass flow meets the third flow in the mixer, is less than about 90 degrees. | 08-28-2008 |
20090053035 | APPARATUS AND METHOD FOR REDUCING ECCENTRICITY AND OUT-OF-ROUNDNESS IN TURBINES - A turbine includes: a plurality of turbine blades arranged within a casing, the arrangement including a clearance between tips of the blades and the casing; a plurality of manifolds disposed proximate to the casing opposite the clearance, wherein each of the manifolds includes a plurality of impingement holes in the surface thereof; a source of clearance information; and a source of cooling air for supplying cooling air through a plurality of flow control devices to selected ones of the manifolds according to the clearance information. A system and a method are also provided. | 02-26-2009 |
20090068007 | Mounting System for Impingement Cooling Manifold - A manifold mounting system for mounting an impingement cooling manifold to a casing of a turbine including a mounting pin affixed to a shroud pin of the turbine wherein the mounting pin extends through the impingement cooling manifold wherein the mounting pin comprises a securing device operable for securing the mounting pin to the impingement cooling manifold, and a leveling support leg affixed to the impingement cooling manifold wherein the mounting pin, securing device, and leveling support leg are operable for adjusting the gap distance between the impingement cooling manifold and the casing of the turbine. | 03-12-2009 |
20090277266 | METHODS AND APPARATUS FOR SENSING PARAMETERS OF ROTATING BLADES - A method for monitoring operating parameters of a rotating blade is provided. The blade includes at least one sensor thereon, the sensor operatively coupled to a data acquisition device. The method includes transferring data from the sensor to the data acquisition device, the data relating to blade acceleration measurements, transmitting a signal representative of the transferred data from the data acquisition device to a control system, and controlling blade loads using the transmitted signal. | 11-12-2009 |
20100011738 | HEAT PIPE FOR REMOVING THERMAL ENERGY FROM EXHAUST GAS - Disclosed is a turbomachine including at least one exhaust pathway along which exhaust is directed and released, and at least one exhaust processor capable of removing regulated substances from the exhaust. A plurality of heat pipes are disposed at least partially in the exhaust pathway upstream of the at least one exhaust processor. The plurality of heat pipes are capable of transferring thermal energy from the exhaust to the plurality of heat pipes thus reducing a temperature of the exhaust to increase effectiveness of the at least one exhaust processor. A method for releasing turbomachine exhaust includes urging turbomachine exhaust along at least one exhaust pathway and flowing the exhaust past a plurality of heat pipes. Thermal energy is transferred from the exhaust to the plurality of heat pipes thus reducing a temperature of the exhaust. | 01-21-2010 |
20100018180 | APPARATUS AND METHOD FOR COOLING TURBOMACHINE EXHAUST GAS - Disclosed is a turbomachine including at least one exhaust pathway along which exhaust is directed and released to ambient and at least one exhaust processor capable of removing regulated substances from the exhaust. One or more ambient air inlets are located at the at least one exhaust pathway upstream of the at least one exhaust processor. The at least one exhaust pathway is configured such that ambient air is capable of being urged into the at least one exhaust pathway through the one or more ambient air inlets by an acceleration of the exhaust along the at least one exhaust pathway. The ambient air urged into the at least one exhaust pathway reduces a temperature of the exhaust to increase effectiveness of the at least one exhaust processor. Further disclosed is a method for releasing turbomachine exhaust to ambient. | 01-28-2010 |
20100024382 | HEAT RECOVERY STEAM GENERATOR FOR A COMBINED CYCLE POWER PLANT - A combined cycle power plant includes a gas turbomachine system including a compressor and a gas turbine that extracts work from gases at a first temperature. The combined cycle power plant also includes a steam turbomachine system including at least one steam turbine that extracts work from gases at a second temperature. The combined cycle power plant further includes a heat recovery steam generator having a main housing fluidly connected to the gas turbine. The heat recovery steam generator includes a plurality of heat pipes that extend within the main housing in fluid communication with the gases at the first temperature. The plurality of heat pipes are also in fluid communication with the gases at the second temperature. The plurality of heat pipes absorb heat from the gases at the first temperature and pass the heat into the gases at the second temperature to form gases at a third temperature. | 02-04-2010 |
20100024424 | CONDENSER FOR A COMBINED CYCLE POWER PLANT - A combined cycle power plant includes a steam turbine section having an inlet section and an outlet section. The steam turbine section passes steam from the inlet section toward the outlet section. The combined cycle power plant also includes a condenser fluidly connected to the outlet section of the steam turbine section. The condenser includes a plurality of heat pipes configured to extract latent heat from steam passing from the steam turbine section to form condensed water. | 02-04-2010 |
20100024429 | APPARATUS, SYSTEM AND METHOD FOR HEATING FUEL GAS USING GAS TURBINE EXHAUST - An apparatus, a system and a method by which fuel gas to drive a heat source is heated are provided. The apparatus includes a first gas passage by which at least a portion of the fuel gas is transported from an inlet to an outlet, the outlet being fluidly coupled to the heat source, a plurality of heat pipes in thermal communication, at respective first ends thereof, with the portion of the fuel gas transported by the first gas passage, and a heating element, fluidly coupled to the heat source to receive exhaust of the heat source, through which respective second ends of the heat pipes extend to be in position to be heated by the exhaust. | 02-04-2010 |
20100025016 | APPARATUS AND METHOD EMPLOYING HEAT PIPE FOR START-UP OF POWER PLANT - An apparatus to facilitate a start-up operation of a combined cycle or rankine cycle power plant is provided and includes a plurality of heat pipes, each of which respectively includes a first portion in thermal communication with exhaust emitted from a heat source and a second portion in thermal communication with the first portion, a cooling unit to cool the second portions of the heat pipes, and a controller which is configured to control the cooling unit to cool the second portions of the heat pipes and to thereby remove heat from exhaust via the first portions of the heat pipes. | 02-04-2010 |
20100028140 | HEAT PIPE INTERCOOLER FOR A TURBOMACHINE - A turbomachine includes a compressor having an intake portion and an outlet portion. The compressor compresses air received at the intake portion to form a compressed airflow that is passed from the outlet portion. The turbomachine also includes an intercooler operatively connected downstream from the compressor. The intercooler includes a plurality of heat pipes that are configured to extract heat from the compressed airflow. | 02-04-2010 |
20100034635 | Predictive Model Based Control System for Heavy Duty Gas Turbines - A system for controlling the clearance between a turbine blade and the turbine casing that includes an impingement cooling manifold attached to a turbine casing, a temperature sensing device for determining the temperature of the turbine casing, a blower, a control system logic for determining the setting temperature of the casing, and a controller for controlling the blower, wherein the blower forces air onto the impingement cooling manifold to cool the casing towards the setting temperature and control the clearance. | 02-11-2010 |
20100040482 | EJECTORS WITH SEPARABLY SECURED NOZZLES, ADJUSTABLE SIZE NOZZLES, OR ADJUSTABLE SIZE MIXING TUBES - An ejector comprising a motive inlet, a motive nozzle separably secured to the motive inlet, a suction chamber about the motive nozzle, a suction fluid inlet to the suction chamber, a mixing tube in fluid communication with the suction chamber and the motive nozzle, a diffuser in fluid communication with the mixing tube and distal the suction chamber and the motive nozzle, and an outlet from the diffuser is provided. A nozzle comprising at least two concentric arc nozzle portions is also provided. An ejector comprising a mixing tube including a flexible layer adapted to compress or stretch, thereby allowing a mixing tube diameter to change is further provided. | 02-18-2010 |
20100043442 | DIMPLED SERRATED FINTUBE STRUCTURE - Disclosed is a fin tube for thermal energy transfer of turbomachine exhaust including a tube disposable in an exhaust stream of a turbomachine and a plurality of fins extending from an outer surface of the tube. Each fin includes a plurality of adjacent fin segments which are separated by a serration. At least one fin segment of the plurality of fin segments includes at least one dimple thereon. The at least one dimple increases a turbulence of exhaust flow across the at least one fin segment and increases a surface area of the at least one fin segment thereby increasing a thermal energy transfer capability of the fin tube. Further disclosed is a combined cycle power plant utilizing the fin tube and a method for operating the combined cycle power plant. | 02-25-2010 |
20100054926 | SYSTEM AND METHOD FOR THERMAL MANAGEMENT OF A GAS TURBINE INLET - A thermal management system includes: a turbine assembly including an inlet housing, a compressor in fluid communication with the inlet housing, a power turbine in fluid communication with the compressor, and an exhaust assembly in fluid communication with the power turbine; and at least one heat pipe having a first portion disposed in thermal communication with the inlet housing and a second portion disposed in thermal communication with the exhaust assembly, the at least one heat pipe configured to transfer thermal energy from the exhaust assembly to at least one of input gas entering the inlet housing and at least one component of the inlet housing. | 03-04-2010 |
20100064655 | SYSTEM AND METHOD FOR MANAGING TURBINE EXHAUST GAS TEMPERATURE - A system for thermal management of exhaust gas includes: a nozzle configured to be disposed in fluid communication with an exhaust of a turbomachine; a mixing conduit in fluid communication with the nozzle; at least one secondary inlet disposed around a periphery of the nozzle and extending between an exterior of the mixing conduit and an interior of the mixing conduit; a variable nozzle mechanism configured to be movable between i) a first position in which the mechanism is configured to close the at least one secondary inlet and ii) a second position in which the mechanism is configured to open the at least one secondary inlet and adjust a selected diameter of the nozzle; and an actuator configured to move the variable nozzle mechanism between the first position and the second position. | 03-18-2010 |
20100095648 | Combined Cycle Power Plant - A combined cycle power plant including a gas turbine, a steam turbine and a heat recovery generator, for thermally connecting the gas turbine and the steam turbine. The heat recovery steam generator has a duct for receiving hot exhaust gas from the gas turbine. The heat recovery steam generator is also associated with a heating system for receiving feed water for heating to steam. A heat pipe having a first end disposed within the duct operates to remove heat there from. A second end of the heat pipe disposed within the heating system operates to transfer heat to the feed water. | 04-22-2010 |
20100096474 | Gas Turbine Ejector and Method of Operation - An ejector system and method of operation for combining high and low pressure fluid flow streams is disclosed. A nozzle chamber communicates with a high pressure fluid flow stream and a suction chamber communicates with a low pressure fluid flow stream. The outlet of the nozzle chamber exit into the suction chamber and include multiple nozzles such that the high pressure flow stream exits the nozzle chamber in multiple flow streams having multiple surface areas for interlayer drag between the flows. The low pressure fluid flow stream is entrained by the high pressure fluid flow streams exiting the multiple nozzles to define an intermediate pressure flow stream. | 04-22-2010 |
20100107595 | COMBINED CYCLE POWER PLANT - A combined cycle power plant includes at least one gas turbine, at least one steam turbine and a heat recovery boiler in combination to produce electricity and/or process steam. The heat recovery boiler has a duct for receiving and confining gas turbine exhaust gas from the gas turbine. Heat transfer tubes for heating water and steam for use in the bottoming steam cycle (steam turbine and/or process steam) are disposed within the heat recovery boiler and have exterior surfaces in fluid communication with the gas turbine exhaust gas and interior surfaces in circulatory fluid communication with water and/or steam. A cellular material is attached to the exterior surfaces of the heat transfer tubes and operates to enhance heat transfer from the gas turbine exhaust gas to the water and/or steam. | 05-06-2010 |
20100118914 | EXTERNALLY ADJUSTABLE IMPINGEMENT COOLING MANIFOLD MOUNT AND THERMOCOUPLE HOUSING - A mount includes a mounting bolt attached to a casing; an internal bushing that engages the casing at a distal end of the internal bushing; and an external bushing that engages a manifold and engages the internal bushing. The internal bushing is adjustable with respect to the external bushing thereby allowing the manifold to be adjustable with respect to the casing. | 05-13-2010 |
20100154781 | SYSTEM AND METHOD FOR HEATING A FUEL USING A SOLAR HEATING SYSTEM - An embodiment of the present invention may take the form of a system and method that may use at least one solar heating system to heat the fuel consumed by a turbomachine. An embodiment of the present invention may incorporate concentrated solar power (CSP). Generally, CSP systems incorporate a plurality of lenses, mirrors, or combinations thereof and a tracking system to focus a large area of sunlight forming a small concentrated beam of light. The concentrated light may then be used as a heat source. In an embodiment of the present invention, the heat source may be used to partially or completely heat the fuel consumed by a turbomachine. CSP systems may take the form of a solar trough system, a parabolic dish system, a solar power tower system, or the like. | 06-24-2010 |
20100162708 | METHODS, APPARATUS AND/OR SYSTEMS RELATING TO FUEL DELIVERY SYSTEMS FOR INDUSTRIAL MACHINERY - An assembly for delivering a supply of liquid fuel and a supply of purge air to a gas turbine engine, the assembly comprising: an annular dual-flow check valve for controlling the flow through concentric channels that have a common outlet, the annular dual-flow check valve comprising: an outer body and an inner body that define the concentric channels, which include an outer channel and an inner channel formed therein; a spring activated annular poppet that resides in the outer channel and has a range of motion in the axial direction; and an opening through the inner body that connects the outer channel to the inner channel; wherein the axial movement of the annular poppet is regulated by the pressure of the flow upstream of the annular poppet in the outer channel; and the axial range of motion of the annular poppet includes at least two axial positions. | 07-01-2010 |
20100170265 | Variable Geometry Ejector - An ejector for a turbine engine is described herein. The ejector may include a variable geometry motive nozzle and a variable geometry mixing tube positioned downstream of the variable geometry motive nozzle. | 07-08-2010 |
20100186443 | HEAT TRANSFER TUBES - A combined cycle power plant includes a first generator driven by a gas turbine for generating electricity. The combined cycle power plant further includes a heat recovery steam generator disposed to receive exhaust gas from the gas turbine. The heat recovery steam generator includes an evaporator having tubes receptive to water flow therethrough. The tubes are disposed to be exposed to the exhaust gas, such that a flow of the exhaust gas passes around the tubes transfers heat from the exhaust gas to the tubes and thereby the water flowing through the tubes sufficient for the water to evaporate into steam. The tubes each having an outer surface with a plurality of deformations formed therein sufficient to introduce turbulence in the flow of the exhaust gas for enhancing heat transfer from the exhaust gas to the tubes. | 07-29-2010 |
20100232945 | TURBOMACHINE INLET HEATING SYSTEM - A turbomachine system includes a compressor having a compressor intake and a compressor extraction outlet, and an inlet system fluidly connected to the compressor intake and the compressor extraction outlet. The inlet system includes a plenum having a first end portion that extends to a second end portion through an intermediate portion. The inlet system also includes a heating system having a plurality of conduits extending horizontally through the intermediate portion of the plenum and arranged in a vertical relationship. Heated air from the compressor extraction outlet passes through the plurality of conduits and raises a temperature of ambient air passing through the plenum and into the compressor intake. | 09-16-2010 |
20100263350 | APPARATUS AND METHOD FOR COOLING A TURBINE USING HEAT PIPES - The turbine section of the turbine engine is provided with a flow of cooling air which is taken from a compressor section of the turbine engine. The air received from the compressor section is itself cooled before the air is delivered to the turbine. Heat is removed from the flow of air by a plurality of heat pipes which conduct heat away from the flow of air to lower the temperature of the air before it is provided to the turbine. | 10-21-2010 |
20100282456 | FINNED TUBE HEAT EXCHANGER - A heat exchanger comprises a tube and fins extending from an outer surface of the tube. The fins comprise first and second sets of fins with the first set of fins oriented in a first direction with respect to an axial direction of the tube and the second set of fins oriented in a second direction with respect to the axial direction of the tube to expose at least a portion of the first and second sets of fins to a free stream. | 11-11-2010 |
20110030331 | Ammonia Injection System - In one embodiment, a system includes an emissions reduction system including a compressor in fluid communication with a catalyst mixing tank. The compressor is configured to output an air flow configured to deliver catalyst from the catalyst mixing tank to a catalyst injection grid. A temperature of the air flow is increased by the compressor. | 02-10-2011 |
20110100020 | APPARATUS AND METHOD FOR TURBINE ENGINE COOLING - A turbine engine comprises a turbine housing, a turbine disposed in the turbine housing that is configured to receive hot combustion gas, a turbine component subject to thermal energy from the hot combustion gas and a cooling system disposed externally of the turbine housing and having a cooling medium disposed therein. A heat pipe has a high temperature end in communication with the turbine component and a low temperature end extending out of the turbine housing in communication with the cooling medium in the cooling system for transferring the thermal energy from the component to the cooling medium. | 05-05-2011 |
20110103939 | TURBINE ROTOR BLADE TIP AND SHROUD CLEARANCE CONTROL - A gas turbine engine includes a turbine shell that is configured to retain a turbine rotor shroud adjacent to a turbine rotor blade. A heat pipe has a first end in thermal communication with the turbine shell and a second end extending outwardly of the shell. A heating/cooling system is in thermal communication with the second end of the heat pipe and has a thermal medium configurable to exchange thermal energy with the second end of the heat pipe. The thermal medium is configurable to remove thermal energy from the second end of the heat pipe to remove thermal energy from the turbine shell and is configurable to add thermal energy to the second end of the heat pipe to add thermal energy to the turbine shell. | 05-05-2011 |
20110132571 | SYSTEMS RELATING TO GEOTHERMAL ENERGY AND THE OPERATION OF GAS TURBINE ENGINES - A geothermal heat exchange system for use in a gas turbine power plant that includes an inlet plenum that directs a flow of air to a compressor that compresses a flow of air that is then mixed with a fuel and combusted in a combustor such that the resulting flow of hot gas is directed through a turbine, the geothermal heat exchange system comprising means for exchanging heat between a ground and the flow of air moving through the inlet plenum. | 06-09-2011 |
20110173947 | SYSTEM AND METHOD FOR GAS TURBINE POWER AUGMENTATION - A gas turbine power augmentation system and method are provided. The system includes a chiller, a controller, a heat exchanger, and a gas turbine inlet air flow. The chiller may be operable to chill a coolant flow using energy from a heat source. The controller may be operably connected to the chiller and configured to regulate operation of the chiller in relation to at least one environmental condition. The heat exchanger may be in fluid communication with the chiller and configured to allow the coolant flow to pass through the heat exchanger. The gas turbine inlet air flow may be directed through the heat exchanger before entering a gas turbine inlet, allowing the air flow to interact with the coolant flow, thereby cooling the air flow. | 07-21-2011 |
20120031600 | TURBINE INTERCOOLER - An intercooler includes a shell with an inlet and an outlet. The shell defines a first chamber. The intercooler further includes a plurality of elongate conducting members. Each of the conducting members includes a first end section and a second end section and is disposed such that each of the first end sections is inside the first chamber of the shell and such that each of the second end sections is disposed exteriorly of the shell. Each of the second end sections is disposed in a flow path of at least one cooling medium so as to undergo evaporative cooling. | 02-09-2012 |
20120058013 | MODEL BASED TEMPERING AIR CONTROL AND ENHANCEMENT OF EXHAUST FOR SELECT CATALYTIC REDUCTION - A method and system for controlling a temperature of an exhaust gas being introduced to a catalyst is provided. Using an adjustable flow controller, an adjustable amount of tempering fluid is provided to the exhaust gas prior to the exhaust gas proceeding to the catalyst. A sensor senses a parameter indicative of a temperature of the exhaust gas being introduced to the catalyst. A computer processor uses a relationship to relate the parameter to an adjustment of the adjustable flow controller that will adjust the amount of tempering fluid provided to the exhaust gas and change the temperature of the exhaust gas being introduced to the catalyst toward a target temperature. Adjustment of the adjustable flow controller is initiated by the computer processor to change the flow of the tempering fluid, and the relationship between the parameter and the adjustment of the adjustable flow controller is updated. | 03-08-2012 |
20120102913 | APPARATUS FOR REDUCING EMISSIONS AND METHOD OF ASSEMBLY - A heat recovery steam generator (HRSG) is coupled to a gas turbine engine that discharges a flow of exhaust gases including oxides of nitrogen (NO | 05-03-2012 |
20120167547 | COMBUSTION TURBINE PURGE SYSTEM AND METHOD OF ASSEMBLING SAME - A method for assembling a rotary machine includes providing at least one combustor assembly that includes at least one fuel nozzle. The method also includes coupling at least one fuel source to the at least one combustor assembly. The method further includes coupling at least one solvent-based purge system in flow communication with the at least one combustor assembly. | 07-05-2012 |
20120305086 | SYSTEM AND METHOD FOR SUPPLYING FUEL - A system for supplying fuel includes a fuel manifold, a water manifold, and a fluid junction between the fuel manifold and the water manifold. A turbulator downstream from the fluid junction receives a fluid flow from the fluid junction. A method for supplying fuel includes flowing fuel through a fuel manifold, flowing water through a water manifold, and combining a portion of the water from the water manifold with the fuel from the fuel manifold to create emulsion fuel. The method further includes flowing the emulsion fuel through a turbulator. | 12-06-2012 |
20130097991 | SYSTEM FOR TURBINE COMBUSTOR FUEL MIXING - A system includes a mixing assembly configured to mix a liquid fuel and a water to generate a fuel mixture. The fuel mixture is configured to combust in a combustor of a gas turbine. The mixing assembly includes a liquid fuel passage disposed in an integrated housing. The liquid fuel passage is configured to flow the liquid fuel and to exclude liquid traps. The mixing assembly also includes a water passage disposed in the integrated housing. The water passage is configured to flow the water and to exclude liquid traps. The mixing assembly also includes a mixer disposed in the integrated housing and coupled to the liquid fuel passage and the water passage. The mixer is configured to mix the liquid fuel and the water to form the fuel mixture. | 04-25-2013 |
20130098040 | SYSTEM FOR TURBINE COMBUSTOR FUEL ASSEMBLY - A system includes a gas turbine engine having a combustor, a liquid fuel supply coupled to the combustor, and a water supply coupled to the liquid fuel supply. The water supply is configured to flow water through the liquid fuel supply while the liquid fuel supply is not in use to flow a liquid fuel. | 04-25-2013 |
20130098041 | SYSTEM FOR TURBINE COMBUSTOR FUEL MIXING - A system includes a plurality of interconnected mixing assemblies configured to mix a first fuel and water to generate a first mixture, and mix a second fuel and the water to generate a second mixture. The first and second fuel mixtures are configured to combust in a plurality of combustors of a gas turbine. The interconnected mixing assemblies include first and second fuel passages, a water passage, first and second mixers, first and second fuel valves, and first and second water valves disposed in an integrated housing. The first fuel valve has a first fuel flow coefficient between approximately 1.0 to 1.5, the second fuel valve has a second fuel flow coefficient between approximately 3.0 to 5.0, the first water valve has a first water flow coefficient between approximately 0.4 to 0.55, and the second water valve has a second water flow coefficient between approximately 3.5 to 5.0. | 04-25-2013 |
20130098056 | SYSTEM AND METHOD FOR TURBINE COMBUSTOR FUEL ASSEMBLY - A system includes a turbine fuel supply system. The turbine fuel supply system includes a first turbine fuel mixer configured to mix a first liquid fuel and a first deaerated water to generate a first fuel mixture. The first fuel mixture is configured to combust in a combustor of a gas turbine engine. The turbine fuel supply system also includes a deaerated water flow path configured to route the first deaerated water to the first turbine fuel mixer and a liquid fuel flow path configured to route the first liquid fuel to the first turbine fuel mixer. | 04-25-2013 |
20130104519 | AMMONIA INJECTION SYSTEMS | 05-02-2013 |
20130115061 | INLET BLEED HEAT SYSTEM - An embodiment of the present invention takes the form of an IBH system that has two conduits, which are positioned close to a downstream end of a silencer section. This arrangement may reduce the overall pressure drop associated with the inlet system. This arrangement may also promote a substantially uniform mixing between the cooler ambient air and the warmer heated air. | 05-09-2013 |
20130115062 | INLET BLEED HEAT SYSTEM - An embodiment of the present invention takes the form of an IBH system that has a single conduit, which is positioned close to a downstream end of a silencer section. This arrangement may reduce the overall pressure drop associated with the inlet system. This arrangement may also promote a substantially uniform mixing between the cooler ambient air and the warmer heated air. | 05-09-2013 |
20130192236 | Method For Transferring Fuel - A method for transferring fuel includes flowing water to at least one nozzle of a main fuel circuit. Also included is flowing oil to the at least one nozzle of the main fuel circuit. Further included is flowing liquid fuel to the at least one nozzle of the main fuel circuit, wherein flowing water to the at least one nozzle of the main fuel circuit occurs prior to flowing oil to the at least one nozzle of the main fuel circuit and flowing liquid fuel to the at least one nozzle of the main fuel circuit. | 08-01-2013 |
20130199150 | STEAM INJECTION ASSEMBLY FOR A COMBINED CYCLE SYSTEM - A steam injection assembly for a combined cycle system includes a heat recovery system having at least one superheater configured to generate a steam supply. Also included is a gas turbine system having an inlet and a compressor, wherein the inlet receives an air supply and the steam supply for combined injection into the compressor. | 08-08-2013 |
20140069076 | GAS TURBINE INLET FOGGING SYSTEM USING ELECTROHYDRODYNAMIC (EHD) ATOMIZATION - A gas turbine inlet fogging system using electrohydrodynamic (EHD) atomization is disclosed. In one embodiment, the inlet fogging system includes: a gas turbine system including an air inlet duct, and a plurality of electrohydrodynamic (EHD) nozzles coupled to a water supply, the plurality of EHD nozzles configured to provide a water-spray for reducing a temperature of inlet air drawn into the air inlet duct. In another embodiment, an inlet fogging system for a gas turbine system includes: a plurality of electrohydrodynamic (EHD) nozzles, and a water supply in fluid communication with the plurality of EHD nozzles. | 03-13-2014 |
20140123622 | Combined Cycle Power Plant with Absorption Heat Transformer - A combined cycle power plant utilizes an absorption heat transformer to improve plant efficiency. A heat recovery steam generator receives exhaust from a gas turbine and generates steam for input to a steam turbine. The heat recovery steam generator includes a low pressure economizer, an intermediate pressure economizer and a high pressure economizer. The absorption heat transformer is in fluid communication with the low pressure economizer. The absorption heat transformer includes a feed water circuit that draws exhaust water from the low pressure economizer for heating by the absorption heat transformer and directs heated water to at least one of the intermediate pressure economizer and the high pressure economizer. | 05-08-2014 |
20140298771 | GAS TURBINE EXHAUST DIFFUSER - 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. | 10-09-2014 |
20140318634 | Fuel Conditioning System - The present application provides a fuel conditioning system for delivering a flow of fuel to a nozzle in a gas turbine engine. The fuel conditioning system may include a fuel compressor to increase the pressure of the flow of fuel, a pressure reduction valve to decrease the pressure of the flow of fuel, and a heater downstream of the pressure reduction valve. The pressure reduction valve may include a rotary control valve. | 10-30-2014 |