| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 060774000 | Multiple expansion | 51 |
| 20120067056 | SYSTEM AND METHOD FOR HIGH EFFICIENCY POWER GENERATION USING A NITROGEN GAS WORKING FLUID - A method of power production using a high pressure/low pressure ratio Brayton Power cycle with predominantly N | 03-22-2012 |
| 20120137698 | COGENERATION PLANT AND COGENERATION METHOD - A cogeneration plant is provided that includes a gas turbine, a heat recovery steam generator, a steam turbine and a cooler/condenser. A division module is provided at a division point, via which downstream the heat recovery steam generator the combustion gas is cooled and dehumidified in the cooler/condenser and then divided into a first combustion gas flow and a second combustion gas flow. A second condenser is provided for receiving the second combustion gas flow to separate contained carbon dioxide from contained water by condensation of the water. The cogeneration plant further includes a heater and a compressor for receiving the first combustion gas flow, which is heated, compressed and partly extracted to by-pass the combustor for cooling of the gas turbine before it enters the combustor and mix with the flow of oxygen and fuel to be burned in the gas turbine. | 06-07-2012 |
| 20120151935 | GAS TURBINE ENGINE AND METHOD OF OPERATING THEREOF - A method for operating a gas turbine engine includes compressing an air stream in a compressor and generating a post combustion gas by combusting a compressed air stream exiting from the compressor in a combustor. The post combustion gas is expanded in a first turbine. The expanded combustion gas exiting from the first turbine is split into a first stream and a second stream. The first stream of the expanded combustion gas is combusted in a reheat combustor. The reheat combustor is cooled using the second stream of the expanded combustion gas. | 06-21-2012 |
| 20120174593 | BLADES IN A TURBINE SECTION OF A GAS TURBINE ENGINE - An exemplary gas turbine engine includes a turbine section operative to impart rotational energy to a compressor section. The turbine section includes at least a low-pressure turbine and a high-pressure turbine, and a number of stages in the low pressure turbine is from three to five. | 07-12-2012 |
| 20120260665 | REHEAT COMBUSTOR FOR A GAS TURBINE ENGINE - A reheat combustor for a gas turbine engine includes a fuel/gas mixer for mixing fuel, air and combustion gases produced by a primary combustor and expanded through a high pressure turbine. Fuel injectors inject fuel into the mixer together with spent cooling air previously used for convectively cooling the reheat combustor. The fuel mixture is burnt in an annular reheat combustion chamber prior to expansion through low pressure turbine inlet guide vanes. The fuel/gas mixer and optionally the combustion chamber define cooling paths through which cooling air flows to convectively cool their walls. The fuel injectors are also convectively cooled by the cooling air after it has passed through the fuel/gas mixer cooling paths. The low pressure turbine inlet guide vanes may also define convective cooling paths in series with the combustion chamber cooling paths. | 10-18-2012 |
| 20130098055 | GAS TURBINE ENGINE WITH INTERCOOLING TURBINE SECTION AND INTERCOOLING TURBINE SECTION BYPASS - A gas turbine engine includes an intercooling turbine section to at least partially drive one of a low spool and a high spool. An intercooling turbine section bypass to selectively bypass at least a portion of a core flow through an intercooling turbine section bypass path around the intercooling turbine section. | 04-25-2013 |
| 20130145771 | SYSTEM AND METHOD USING LOW EMISSIONS GAS TURBINE CYCLE WITH PARTIAL AIR SEPARATION - A system and method of reducing gas turbine nitric oxide emissions includes a first combustion stage configured to burn air vitiated with diluents to generate first combustion stage products. A second combustion stage is configured to burn the first combustion stage products in combination with enriched oxygen to generate second combustion stage products having a lower level of nitric oxide emissions than that achievable through combustion with vitiated air alone or through combustion staging alone. | 06-13-2013 |
| 20130152598 | SYSTEM AND METHOD FOR THERMAL CONTROL IN A GAS TURBINE ENGINE - A system includes a gas turbine engine that includes a compressor section configured to generate compressed air and a combustor coupled to the compressor section. The combustor is configured to combust a first mixture comprising the compressed air and a first fuel to generate a first combustion gas. The gas turbine engine also includes a turbine section coupled to the combustor. The turbine section is configured to expand the first combustion gas to generate an exhaust gas. The gas turbine engine also includes a boiler coupled to the turbine section. The boiler is configured to combust a second mixture comprising a portion of the first combustion gas and a second fuel to generate a second combustion gas that is routed to the turbine section. In addition, the boiler generates a first steam from heat exchange with the second combustion gas. | 06-20-2013 |
| 20130213050 | COMBUSTOR WITH A SINGLE LIMITED FUEL-AIR MIXING BURNER AND RECUPERATED MICRO GAS TURBINE - A recuperated micro gas turbine combustor has a casing, liner, fuel injector and a flame stabilization device. This flame stabilization device is characterized by a swirl strength and air passage geometry as such that the pressure loss over the device is less than 1.5%. The flame stabilization device and the fuel injector form together with the liner inlet/head hardware a single burner. | 08-22-2013 |
| 20130219907 | GEARED TURBOFAN ARCHITECTURE FOR IMPROVED THRUST DENSITY - A turbine engine includes a fan, a compressor section having a low pressure compressor section and a high pressure compressor section, a combustor in fluid communication with the compressor section and a turbine section in fluid communication with the combustor. The turbine section includes a low pressure turbine section and a high pressure turbine section. The low pressure compressor section, the low pressure turbine section and the fan rotate in a first direction whereas the high pressure compressor section and the high pressure turbine section rotate in a second direction opposite the first direction. | 08-29-2013 |
| 20130219908 | GEARED TURBOFAN ARCHITECTURE FOR IMPROVED THRUST DENSITY - A turbine engine includes a fan, a compressor section having a low pressure compressor section and a high pressure compressor section, a combustor in fluid communication with the compressor section and a turbine section in fluid communication with the combustor. The turbine section includes a low pressure turbine section and a high pressure turbine section. The low pressure compressor section, the low pressure turbine section and the fan rotate in a first direction whereas the high pressure compressor section and the high pressure turbine section rotate in a second direction opposite the first direction. | 08-29-2013 |
| 20130298568 | Process Utilizing High Performance Air-Cooled Combined Cycle Power Plant With Dual Working Fluid Bottoming Cycle and Integrated Capacity Control - A combined cycle power plant system and methods of operation so as to minimize consumption of cooling water utilizes exhaust from a combustion turbine to generate steam for power generation in a steam turbine topping cycle. The exhaust steam from the steam turbine topping cycle is utilized to vaporize an organic working fluid in an organic working fluid bottoming cycle, where vaporized organic working fluid expanded across a turbine generates additional power. Exhaust gas from the organic working fluid bottoming cycle is condensed utilizing an air-cooled heat exchanger. Heat exchange bundles of the air-cooled heat exchanger are preferably arranged horizontally relative to the ground to maximize efficiency. Turbine inlet cooling is employed at the combustion turbine to recapture energy lost in the system. A thermal energy storage tank may be utilized in conjunction with the turbine inlet cooling to supply chilling water to the system. | 11-14-2013 |
| 20130318991 | Combustor With Multiple Combustion Zones With Injector Placement for Component Durability - A combustion system including a combustor; a combustor liner disposed within the combustor is provided. At least one primary fuel nozzle is provided to provide fuel to a primary combustion zone disposed proximate to the upstream end of the combustor liner. A transition duct is coupled to the downstream end of the combustor liner. A secondary nozzle assembly is disposed proximate to the downstream end of the combustor to provide fuel to a secondary combustion zone at locations predetermined to reduce peak thermal loads on the surface area of the transition duct. | 12-05-2013 |
| 20140096532 | SYSTEM AND METHOD FOR UREA DECOMPOSITION TO AMMONIA IN A SIDE STREAM FOR SELECTIVE CATALYTIC REDUCTION - A method for reducing NOx emissions in the exhaust of a combined cycle gas turbine equipped with a heat recovery boiler and a catalyst effective for NOx reduction, wherein a slip stream of hot flowing exhaust gases is withdrawn from the primary gas flow after the catalyst at a temperature of 500° F. to 900° F. and directed through a fan to a continuous duct into which an aqueous based reagent is injected for decomposition to ammonia gas and the outlet of the continuous duct is connected to an injection grid positioned in the primary exhaust for injection of ammonia gas into the primary exhaust stream at a location upstream of the catalyst. | 04-10-2014 |
| 20140123665 | REHEAT BURNER ARRANGEMENT - A reheat burner arrangement including a center body, an annular duct with a cross-section area, an intermediate fuel injection plane located along the center body and being actively connected to the cross section area of the annular duct, wherein the center body is located upstream of a combustion chamber, wherein the structure of the reheat burner arrangement is defined by various parameters and the structure of the reheat burner arrangement is defined by various dependencies. | 05-08-2014 |
| 20140150443 | Gas Turbine Engine with Integrated Bottoming Cycle System - The present application provides an integrated bottoming cycle system for use with a gas turbine engine. The integrated bottoming cycle system described herein may include a compressor/pump, a cooling circuit downstream of the compressor/pump, a bottoming cycle heat exchanger, a heating circuit downstream of the bottoming cycle heat exchanger, and a number of turbine components in communication with the cooling circuit and/or the heating circuit to maximize the overall plant efficiency and economics. | 06-05-2014 |
| 20140182299 | SYSTEM AND METHOD FOR REHEAT IN GAS TURBINE WITH EXHAUST GAS RECIRCULATION - A system includes a turbine having an exhaust flow path through a plurality of turbine stages, wherein the plurality of turbine stages is driven by combustion products flowing through the exhaust flow path, at least one main combustor disposed upstream from the turbine, wherein the at least one main combustor is configured to combust a fuel with a first oxidant and an exhaust gas to generate the combustion products, at least one reheat combustor disposed in or between turbine stages of the turbine, wherein the at least one reheat combustor is configured to reheat the combustion products by adding a second oxidant to react with unburnt fuel in the combustion products, and an exhaust gas compressor, wherein the exhaust gas compressor is configured to compress and route the exhaust gas from the turbine to the at least one main combustor along an exhaust recirculation path. | 07-03-2014 |
| 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 |
| 20140216047 | Two-Shaft Gas Turbine - A two-shaft gas turbine having high operability is provided. The two-shaft gas turbine includes: a gas generator having a compressor, a combustor and a high pressure turbine; a power turbine having a low pressure turbine; a load connected to the power turbine; a motor/generator capable of rotatably driving the gas generator and capable of extracting power from the gas generator; electric equipment controlling the rotational driving and the power extraction by delivering electric power between the electric equipment and the motor/generator; and a control device controlling the electric equipment, wherein the combustor has a plurality of combustion regions to which a fuel is supplied through fuel adjustment means which are independent from each other, and the control device controls a delivery amount of the electric power delivered by the electric equipment corresponding to the number of combustion regions to which the fuel is supplied. | 08-07-2014 |
| 20140250903 | COGEN HEAT LOAD MATCHING THROUGH REHEAT AND CAPACITY MATCH - One example of a gas turbine engine may include a gas generator, a reheat combustor that is disposed downstream of the gas generator, and a power turbine that is disposed downstream of the reheat combustor and includes a plurality of nozzle guide vanes. The reheat combustor is configured to increase a fuel flow so as to increase a temperature of the reheat combustor and match a required exhaust temperature. The nozzle guide vanes are configured to increase a real capacity at a power turbine inlet in proportion with the required exhaust temperature. A constant apparent capacity at a gas generator exit upstream of the reheat combustor remains constant, in response to proportionately increasing the temperature and the real capacity with respect to one another. | 09-11-2014 |
| 20140250904 | CAPACITY CONTROL OF TURBINE BY THE USE OF A REHEAT COMBUSTOR IN MULTI SHAFT ENGINE - One example of a gas turbine engine can include a first compressor and a first turbine connected to the first compressor by a first shaft. The engine can include a reheat combustor, which is disposed downstream of the first turbine, and a second turbine, which is disposed downstream of the reheat combustor. The engine can further include a second compressor, which is connected to the second turbine by a second shaft and is disposed upstream of the first compressor. The first and second turbines can be disconnected from one another, and the first and second compressors can be disconnected from one another. The second compressor may have an outlet including a flow to the first compressor, such that the first and second turbines provide a shaft worksplit. The reheat combustor can be configured to receive fuel and generate a reheat exit temperature, so as to control an apparent capacity of the second turbine based on a plurality of parameters of the second compressor. | 09-11-2014 |
| 20140260295 | GAS TURBINE ENGINE WITH TRANSMISSION AND METHOD OF ADJUSTING ROTATIONAL SPEED - A method of adjusting a rotational speed of the low pressure compressor rotor(s) of a gas turbine engine, including rotating the high pressure compressor rotor(s) with the high pressure turbine rotor(s) through the high pressure spool, rotating the low pressure turbine rotor(s) with a flow of exhaust gases from the high pressure turbine, rotating the low pressure spool with the low pressure turbine rotor(s), rotating a load of the engine with the low pressure spool, driving a rotation of the low pressure compressor rotor(s) with the low pressure spool through a variable transmission defining a variable transmission ratio between rotational speeds of the compressor rotor(s) and the low pressure spool, and adjusting the transmission ratio to obtain a desired rotational speed for the low pressure compressor rotor(s). A method of adjusting rotational speeds of a gas turbine engine and a gas turbine engine are also described. | 09-18-2014 |
| 20140338352 | ELECTRICAL GENERATION ARRANGEMENT FOR AN AIRCRAFT - This invention relates to a multi-spool gas turbine engine, including: a first generator for providing electrical power to an electrical system, the generator being driveably connected to a first spool; a second generator for providing electrical power to the electrical system, the generator being driveably connected to a second spool; a disconnection device for disconnecting the second generator from the second spool; and, a controller configured to selectively operate the disconnection device under predetermined powered engine conditions. | 11-20-2014 |
| 20140352319 | GAS TURBINE ENGINE AND METHOD OF OPERATING THEREOF - A gas turbine engine and method for operating a gas turbine engine includes compressing an air stream in a compressor and generating a post combustion gas by combusting a compressed air stream exiting from the compressor in a combustor. The post combustion gas is expanded in a first turbine. The expanded combustion gas exiting from the first turbine is split into a first stream, a second stream and a third stream. The first stream of the expanded combustion gas is combusted in a reheat combustor. An outer liner and flame stabilizer of the reheat combustor are cooled using the second stream of the expanded combustion gas. An inner liner of the reheat combustor is cooled using the third stream of the expanded combustion gas and a portion of the second stream of the expanded combustion gas passing through the one or more flame stabilizers. | 12-04-2014 |
| 20140352320 | Two-Shaft Gas Turbine - A two-shaft gas turbine is provided that can raise an inlet temperature of a high-pressure turbine and the air quantity of a compressor to respective rated values at any atmospheric temperature without using a variable stator vane in the initial stage of a low-pressure turbine. | 12-04-2014 |
| 20140366550 | GAS TURBINE ENGINE AND METHOD OF OPERATING THEREOF - A gas turbine engine and method for operating a gas turbine engine includes compressing an air stream in a compressor and combusting the compressed air stream to generate a post combustion gas. The post combustion gas is expanded in a first turbine. The expanded combustion gas exiting the first turbine is split into a first stream, a second stream and a third stream in a splitting zone including one or more aerodynamically shaped flow diverters. The first stream of the expanded combustion gas is combusted in a reheat combustor. An outer liner and flame stabilizer of the reheat combustor are cooled using the second stream of the expanded combustion gas. An inner liner of the reheat combustor is cooled using the third stream of the expanded combustion gas and a portion of the second stream of the expanded combustion gas passing through the one or more flame stabilizers. | 12-18-2014 |
| 20150047364 | BURNER ARRANGEMENT AND METHOD FOR OPERATING A BURNER ARRANGEMENT - The invention relates to a burner arrangement for using in a single combustion chamber or in a can-combustor comprising a center body burner located upstream of a combustion zone, an annular duct with a cross section area, intermediate lobes which are arranged in circumferential direction and in longitudinal direction of the center body. The lobes being actively connected to the cross section area of the annular duct, wherein a cooling air is guided through a number of pipes within the lobes to the center body and cools beforehand at least the front section of the center body based on impingement cooling. Subsequently, the impingement cooling air cools the middle and back face of the center body based on convective and/or effusion cooling. At least the back face of the center body includes on the inside at least one damper. | 02-19-2015 |
| 20150075173 | COMPRESSED-AIR ENERGY-STORAGE SYSTEM - A compressed-air energy-storage system, comprising: a variable-nozzle expander configured to receive an airflow at a first pressure and partially expand said airflow at a second pressure, said second pressure being lower than said first pressure, expansion of said airflow in said variable-nozzle expander producing useful mechanical power; a heat generator component configured to receive a fuel and a partially expanded airflow from the variable-nozzle expander; and a turbine configured to receive combustion gas from the heat generator component and expand the combustion gas producing useful mechanical power. | 03-19-2015 |
| 20150101340 | SYSTEM AND METHOD FOR IMPROVING EFFICIENCY OF A GAS TURBINE ENGINE - A gas turbine engine is presented. The gas turbine engine includes a control unit having a first bypass channel that is coupled between an outlet of a first turbine and an inlet of a second turbine. Further, the control unit includes a second bypass channel coupled between a first outlet of a compressor unit and the inlet of the second turbine. Additionally, the control unit includes a first control valve coupled to the first bypass channel and configured to direct at least a first portion of exhaust gas from the first turbine to the inlet of the second turbine via the first bypass channel. Furthermore, the control unit includes a second control valve coupled to the second bypass channel and configured to direct at least a first portion of compressed air from the compressor unit to the inlet of the second turbine via the second bypass channel. | 04-16-2015 |
| 20150101341 | METHOD FOR A PART LOAD CO REDUCTION OPERATION FOR A SEQUENTIAL GAS TURBINE - The invention concerns a method for a part load CO reduction operation and a low-CO emissions operation of a gas turbine with sequential combustion. The gas turbine essentially includes at least one compressor, a first combustor which is connected downstream to the compressor. The hot gases of the first combustor are admitted at least to an intermediate turbine or directly or indirectly to a second combustor. The hot gases of the second combustor are admitted to a further turbine or directly or indirectly to an energy recovery. At least one combustor runs under a caloric combustion path having a can-architecture, and wherein the air ratio (λ) of the combustion at least of the second combustor is kept below a maximum air ratio (λ | 04-16-2015 |
| 20150121893 | ADAPTIVE FAN REVERSE CORE GEARED TURBOFAN ENGINE WITH SEPARATE COLD TURBINE - A turbine engine includes a first fan including a plurality of fan blades rotatable about an axis and a reverse flow core engine section including a core turbine axially forward of a combustor and compressor. The core turbine drives the compressor about the axis and a transmission system. A geared architecture is driven by the transmission system to drive the first fan at a speed less than that of the core turbine. A second fan is disposed axially aft of the first fan and forwarded of the core engine and a second turbine is disposed between the second fan and the core engine for driving the second fan when not coupled to the transmission. | 05-07-2015 |
| 20150135722 | SYSTEM AND METHOD OF CONTROLLING A TWO-SHAFT GAS TURBINE - A two-shaft gas turbine control system and method are provided that can enhance the efficiency and reliability thereof by controlling the amount of intake air spray and the rotational speed of a high-pressure turbine in accordance with the aperture of an inlet guide vane in a state where a two-shaft gas turbine is being operated with the efficiency of its compressor reduced. | 05-21-2015 |
| 20150292402 | GAS TURBINE ENGINE - A gas turbine engine. The engine includes a first compressor coupled to a first turbine by a first shaft, the first turbine having first and second turbine stages. A first combustor is provided downstream of the first compressor and upstream of the first stage of the first turbine. A second combustor is provided downstream of the first stage of the first turbine, and upstream of the second stage of the first turbine. A further turbine is provided downstream of the first turbine, and is coupled to a further compressor by a further shaft. | 10-15-2015 |
| 20150322822 | SIMPLIFIED WATER INJECTION SYSTEM FOR COMBINED CYCLE POWER PLANT - In one or more of the inventive aspects, a boiler feedwater pump may provide feedwater to a heat recovery steam generator, and the heated feedwater may be used for liquid fuel heating in a liquid fuel heater. The feedwater from the boiler feedwater pump may also be used for water injection in a combustor. | 11-12-2015 |
| 20150345387 | PLANT CONTROL APPARATUS AND PLANT STARTING-UP METHOD - In one embodiment, a plant control apparatus controls a combined cycle power generation plant. The plant includes a gas turbine, an exhaust heat recovery boiler including an evaporator to recover heat from an exhaust gas discharged from the gas turbine to generate steam and including a heat exchanger to exchange heat between the steam and an exhaust gas from the gas turbine and generate main steam, and a steam turbine driven by the main steam. The apparatus includes a control unit to increase output of the gas turbine to a target output after the gas turbine is paralleled with a generator. The target output is set so that an exhaust gas temperature of the gas turbine exceeds a maximum operating temperature of the exchanger and that a temperature of the exchanger becomes the maximum operating temperature or less by using a cooling effect given by the main steam. | 12-03-2015 |
| 20150354450 | GAS TURBINE ENGINE DRIVEN BY SUPERCRITICAL POWER GENERATION SYSTEM - A gas turbine engine includes a shaft having a first air compressor coupled thereto, a combustor positioned to receive compressed air from the first compressor, and a power source coupled to the shaft, the power source powered by a working fluid other than the compressed air. | 12-10-2015 |
| 20150361878 | GEARED TURBOFAN ARCHITECTURE - A gas turbine engine includes a fan bypass ratio greater than 12. A speed reduction device includes a gear ratio of at least 2.6. A turbine section includes a transition duct that is located between a high pressure turbine and a low pressure turbine and includes fewer support struts than vanes in a first vane row of the low pressure turbine. | 12-17-2015 |
| 20150361880 | GAS TURBINE ENGINE WITH DISTRIBUTED FANS WITH DRIVE CONTROL - A gas turbine engine comprises a plurality of fan rotors. A gas generator comprises at least one compressor rotor, at least one gas generator turbine rotor, a combustion section, and a fan drive turbine downstream of at least one gas generator turbine rotor. A shaft is configured to be driven by the fan drive turbine. The shaft engages gears to drive the plurality of fan rotors. A system controls the amount of power supplied to the plurality of fan rotors. A method of operating a gas turbine engine is also disclosed. | 12-17-2015 |
| 20150377125 | REVERSE-FLOW CORE GAS TURBINE ENGINE WITH A PULSE DETONATION SYSTEM - The engine ( | 12-31-2015 |
| 20160003044 | Internal Detonation Engine, Hybrid Engines Including the Same, and Methods of Making and Using the Same - Hybrid internal detonation-gas turbine engines incorporating detonation or pulse engine technology (such as an internal detonation engine), and methods of manufacturing and using the same are disclosed. The internal detonation engine includes a detonation chamber having a fuel igniter therein, a stator at one end of the detonation chamber having at least a first opening to receive fuel, a rotor adjacent to the stator, and an energy transfer mechanism configured to convert energy from igniting or detonating the fuel to mechanical energy. The detonation chamber and fuel igniter are configured to ignite or detonate a fuel in the detonation chamber. Either the stator or the detonation chamber has a second opening to exhaust detonation gas(es). The rotor has one or more third openings therein configured to overlap with at least the first opening as the rotor rotates. | 01-07-2016 |
| 20160003155 | TWO-SHAFT GAS TURBINE - A two-shaft gas turbine is provided which includes: a compressor; a combustor having multiple fuel systems and generating combustion gas by combusting fuels from the fuel systems and air compressed by the compressor; a high-pressure turbine coupled coaxially with the compressor and rotated by the combustion gas; a low-pressure turbine having a shaft structure independent of the high-pressure turbine and rotated by exhaust gas from the high-pressure turbine; an air extraction channel for extracting the air compressed by the compressor; an injection flow channel for feeding the air extracted through the air extraction channel back to the combustor; and a controller for controlling the flow rate of the fuel supplied to each of the fuel systems based on the air flow rate of the compressor, on the flow rate of the fuel supplied to the combustor, and on the temperature of the air in the injection flow channel. | 01-07-2016 |
| 20160010485 | COMBINED CYCLE PROPULSION SYSTEM | 01-14-2016 |
| 20160010510 | POWER PLANT AIR COOLED HEAT EXCHANGER OR CONDENSER WITH PRESSURIZED GAS ENTRAINED COOLING LIQUID MISTER | 01-14-2016 |
| 20160032787 | SOLID OXIDE CELL SYSTEM AND METHOD FOR MANUFACTURING THE SAME - Provided are a solid oxide cell (SOC) system producing a synthetic gas by using a waste gas discharged from a power plant, or the like, and a method for controlling the same. The SOC system includes i) a first power plant configured to provide a waste gas and first electrical energy, ii) a second power plant configured to provide second electrical energy using an energy source different from that of the first power plant, and iii) a solid oxide cell (SOC) connected to the first power plant and the second power plant, configured to receive the waste gas and the second electrical energy to manufacture carbon monoxide and hydrogen, and providing the carbon monoxide and the hydrogen to the first power plant. | 02-04-2016 |
| 20160115869 | METHOD FOR OPERATING A COMBINED CYCLE POWER PLANT - A method for operating a combined cycle power plant includes additional burners being arranged in the waste heat boiler, the burners being supplied with secondary air from the gas turbine, the gas turbine is operated without a supply of fuel, and driving is effected by means of a start-up inverter. A plant includes a waste heat boiler, additional burners for generating thermal energy being arranged within the waste heat boiler, a gas turbine designed such that the necessary air mass flow for the additional burners can be supplied by the gas turbine, wherein the gas turbine is operated without a supply of fuel, the plant further including a start-up inverter, wherein driving is effected by means of the start-up inverter. | 04-28-2016 |
| 20160123192 | PROCESS AND PLANT FOR POWER GENERATION - Power generation plant and process comprising: providing a steam generator; first, second and third steam turbines; a reheater; a gas turbine; and at least one heat exchanger; supplying feedwater bypassing the steam generator to the heat exchanger and heating the feedwater stream therein by supplying the at least one hot exhaust gas stream from the gas turbine to the heat exchanger; and recovering heated steam from the heat exchanger and supplying at least part of the recovered heated steam stream to the second steam turbine to generate power in the second steam turbine. | 05-05-2016 |
| 20160123226 | GAS TURBINE USING A CRYOGENIC FUEL AND EXTRACTING WORK THEREFROM - There is disclosed a method of operating a gas turbine engine of a type having a compressor section, a combustor section, and a turbine section arranged in flow series. The method involves the steps of: providing a supply of cryogenic liquid fuel; vaporising the cryogenic liquid fuel to produce a gaseous fuel; expanding said gaseous fuel in at least one fuel turbine external to the engine's turbine section; and thereafter directing said expanded gaseous fuel into the engine's combustion section for combustion therein. A related gas turbine arrangement configured for implementation of the method is also disclosed. | 05-05-2016 |
| 20160146060 | METHOD FOR OPERATING A COMBINED CYCLE POWER PLANT - A method for operating a combined cycle power plant, according to which shortly before the planned start-up of a parked load, the steam turbine is lowered to a very low output, the gas turbine is then operated in parked load, and next the steam turbine is powered up to a parked output. The GT operating power can be the rated power of the gas turbine. The ST operating power can be the rated power of the steam turbine. | 05-26-2016 |
| 20160177839 | METHOD FOR MONITORING A COLD START OF A BRAYTON CYCLE POWER GENERATION SYSTEM | 06-23-2016 |
| 20160195014 | Membrane Technology for Use in a Power Generation Process | 07-07-2016 |
| 20160201518 | SYSTEMS AND METHODS FOR ADJUSTING FLOOR PRESSURE LEVELS TO IMPROVE COMBINED CYCLE PLANT STARTUP | 07-14-2016 |
