Abstract: A device for compressing and feeding to a microturbine power generator a high humidity fuel gas such as biogas, which cools the high humidity fuel gas condensed by the compressor using an air-cooling type fin-tube radiator, condenses and liquefies the moisture, then removes it by a moisture-removing means such as a gas/liquid separator or adsorption type moisture-removing tank, which requires only enough power to drive a cooling fan, which heats the fuel gas from which the majority of the moisture has been removed in a heat exchanger utilizing the heat of compression generated in the compressor, then feeds it to piping leading to the microturbine power generator, and which is free from the residual moisture liquefying and freezing even if the fuel gas is cooled in the piping.

Abstract: A gas turbine plant comprises an air compressor, gas turbine including at least one high temperature section, a driven equipment, which are operatively connected in series, a gas turbine combustor arranged between the air compressor and the gas turbine, a fuel system disposed for supplying a fuel to the gas turbine combustor, and a heat exchange section for heating the fuel from the fuel by means of a high pressure air as a heating medium fed from the air compressor.

Abstract: In a reheat gas turbine engine for power generation, fuel is burnt with compressed air from a compressor in a first or primary combustor, the combustion products are passed through a high pressure turbine, the exhaust of the high pressure turbine is then burnt together with further fuel in a reheat combustor to consume the excess air, and the exhaust of the second combustor is passed through a lower pressure turbine. Excess air is supplied to the first combustor, thereby enabling so-called “lean burn” combustion for production of low levels of pollutants in the exhaust of the engine. Some turbine components of the turbines, e.g., blades or vanes, are cooled by cooling air supplies tapped off from the compressor.

Abstract: A gas turbine combustor transition piece outlet structure enabling a reduction in the temperature difference of a flange formed at the transition piece outlet. A flange is formed with a cooling medium channel along the inner circumference, cooling medium channels along the left and right side surfaces, and heating medium channels along the top and bottom surfaces. By cooling the inner circumference or the side surfaces of the flange by a cooling medium or heating the top and bottom surfaces of the flange by a heating medium, the temperature difference of the flange is reduced. Note that as the cooling medium, it is possible to use compressed air, low temperature steam, or fuel, while as the heating medium, it is possible to use high temperature steam or combustion gas.

Abstract: A gas turbine plant comprises an air compressor, gas turbine including at least one high temperature section, a driven equipment, which are operatively connected in series, a gas turbine combustor arranged between the air compressor and the gas turbine, a fuel system disposed for supplying a fuel to the gas turbine combustor, and a heat exchange section for heating the fuel from the fuel by means of a high pressure air as a heating medium fed from the air compressor.

Abstract: The invention relates to a device for preheating combustibles in combined gas and steam turbine installations. Said device comprises at least one steam generator (5, 6, 7) for heating, evaporating and superheating feed water, which has a feed water preheater (15, 16, 43, 51), an evaporator (8, 9, 10) and a superheater (11, 12, 13), at least part of the heated feed water being used for preheating combustibles in a combustible preheater, which can be supplied with feed water of a predetermined temperature by a feed water supply line (35, 36, 37, 56, 58, 60, 73) Once the combustible has been heated, the cooled feed water can be drained using a feed water drain line (57, 59, 61, 74). The aim of the invention is to configure a device of this type so that it can be used in different gas turbine installations and its heating capacity can be rapidly and cost-effectively adapted to predetermined combustible preheating requirements.

Abstract: A gas turbine plant comprises an air compressor, gas turbine turbine including at least one high temperature section, a driven equipment, which are operatively connected in series, a gas turbine combustor arranged between the air compressor and the gas turbine, a fuel system disposed for supplying a fuel to the gas turbine combustor, and a heat exchange section for heating the fuel from the fuel by means of a high pressure air as a heating medium fed from the air compressor.

Abstract: A turbine power generation system is provided for use with an off-gas fuel source. The system comprises first compression means for compressing air; second compression means for compressing off-gas; combustion means for combusting a mixture of said compressed air and a fuel comprising said off-gas; turbine means for converting energy released from combustion into mechanical energy; transduction means for converting the mechanical energy into electrical energy; a shaft linking the first compression means, turbine means, and transduction means, to allow mechanical energy produced by the turbine means to be used by the transduction means and first compression means; and an off-gas heating means for heating the compressed off-gas to a temperature greater than the gas dew point of the off-gas to ensure that no liquids are formed in the fuel gas supply to the combustor.

Abstract: Syngas for use, as fuel in the combustion turbine of an IGCC process is heated to a maximum temperature of about 350° F. (177° C.) prior to entering the combustor. Non-combustible diluent gas and additional fuel with a high heating value is also added to the syngas to increase the total heating value of the feed to the combustor of the gas turbine. The cooler temperature allows for more mass flow to the combustion turbine, allowing for greater sensible heat in the syngas to offset the latent heat loss due to the cooler temperature. Because the syngas/diluent feed steam is not heated to the high temperatures disclosed in the prior art, the steam that would otherwise heat the feed stream is available for power generation in the steam turbine, increasing its individual power output and the overall power output of the IGCC process.

Abstract: A fuel system (10) comprises a tank (12), a pump (14), heat exchangers (16 & 18) and a filter (20) in series fluid flow relationship. A fuel metering unit (24) returns a proportion of the filtered fuel to the tank (12) and is controlled by the engine electronic control (30). The system (10) operates so that fluid is not returned to the tank (12) when a pressure differential of the order of 5 psi is detected across the fluid filter (20) and the temperature of the fluid is below 0° C. The fluid is not returned to the tank (12) for a period of time to reduce the flow of fluid passing through the heat exchangers (16 & 18). The reduced flow of fluid passing through the heat exchangers (16 & 18) is heated to a temperature sufficient to melt any solidified impurities blocking the fluid filter (20).

Abstract: A cooling air cooling system is selectively operable to reduce fuel gum deposits within the cooling system during gas turbine engine operations. The cooling system includes a recirculating loop that includes at least three heat exchangers in fluid communication with the recirculating loop. A first heat exchanger cools cooling air supplied to the gas turbine engine. A second heat exchanger cools fluid exiting the first of the heat exchangers with fan discharge air prior to the fluid entering the third heat exchanger. A third heat exchanger uses combustor main fuel flow to cool the fluid circulating in the recirculating loop.

Abstract: A cooling air cooling system operable to reduce fuel gum deposits within the cooling system when a gas turbine engine operates above a predefined percentage of rated engine power. The cooling system includes a recirculating loop including a plurality of heat exchanges in fluid communication with the recirculating loop. A first head exchange uses heat transfer fluid to cool cooling air used by the gas turbine engine. A second head exchange is a fluid-fuel head exchanger that uses combustor main fuel flow to cool the head transfer fluid circulating in the recirculating loop.

Abstract: In a method for operating a gas turbo group, partial streams of compressed air are cooled in cooling air coolers and are used as cooling air for thermally highly stressed components of the gas turbo group. The cooling air coolers are constructed as steam generators. Steam generated in the cooling air coolers is fed in part to the gas turbo group and is expanded there while providing usable power, while another part of the steam is fed into the cooling system, where the steam displaces air, which air then becomes available again to the gas turbine process. In this way, the steam generated with the help of heat removed from the cooling air is re-used.

Abstract: A gas turbine plant comprises an air compressor, gas turbine turbine including at least one high temperature section, a driven equipment, which are operatively connected in series, a gas turbine combustor arranged between the air compressor and the gas turbine, a fuel system disposed for supplying a fuel to the gas turbine combustor, and a heat exchange section for heating the fuel from the fuel by means of a high pressure air as a heating medium fed from the air compressor.

Abstract: A combined cycle power plant system, comprising a compressor; a combustor receiving air provided by the compressor; a gas turbine for expanding gas provided by the compressor; a heat recovery steam generator (HRSG) for receiving exhaust gases from the gas turbine. The heat recovery steam generator (HRSG) receives exhaust gases from the gas turbine. The HRSG includes a low pressure (LP) section; a high pressure (HP) section for receiving exhaust gases from the gas turbine and located upstream of the LP section, each of the LP and HP sections include an evaporator section. An intermediate pressure (IP) section is located between the HP and the LP sections, the IP section includes an economizer, first and second evaporators, and a water heater (34) disposed between the first and second evaporators. A fuel gas heater is provided for receiving heated water from the water heater.

Abstract: A cast heat exchanger, having an inlet and an outlet and defining an internal passage therebetween, includes a wall structure disposed within the internal passage that defines a series of interconnected chambers through which a cooling medium flows in a serpentine path. The outer surface of the heat exchanger is covered with pin fins that transfer heat away from the hot working medium flowing over the pin fins and into the cooling medium within the chambers of the heat exchanger.

Abstract: A gas turbine plant comprises an air compressor, gas turbine turbine including at least one high temperature section, a driven equipment, which are operatively connected in series, a gas turbine combustor arranged between the air compressor and the gas turbine, a fuel system disposed for supplying a fuel to the gas turbine combustor, and a heat exchange section for heating the fuel from the fuel by means of a high pressure air as a heating medium fed from the air compressor.

Abstract: A thermal management system avoids problems associated with the recirculation of fuel through a fuel tank on an aircraft in a system that includes a fuel reservoir (70), a pump (72) for pumping fuel from the reservoir (70) to a first heat load (74) and then to a check valve (76) to a junction (78). At least one second heat load (80), (82), (84) is connected to the junction (78) and a fuel/fan air heat exchanger (104) having a fan air flow path in heat exchange relation with a fuel flow path having a fuel discharge end (106) connected to the junction (78). The fan air flow path is adapted to be connected to receive compressed air from the fan (30) of an engine (10). A bleed air/fuel heat exchanger (92) receives fuel from the second heat load and bleed air from the engine (10) and is connected to deliver fuel to the engine (10).

Abstract: In a liquid fuel turbine engine, the liquid fuel is vaporized prior to being mixed with air and injected into the combustion chamber to be combusted therein. The heat for vaporizing the fuel may be provided by the turbine engine and may be drawn from the turbine exhaust or may be electrically generated, where electrical power may be supplied by a generator coupled to the turbine.

Abstract: A method and system for monitoring the dew point of a fuel gas for a combustion turbine. A flow of fuel gas is filtered of particulate matter and liquid droplets in an aerosol interception and removal system. The pressure of the filtered fuel gas may be reduced at a pressure reduction station. The flow of fuel gas is analyzed by a dew point monitoring device that sends a signal to the heating system. The heating system may then adjust the temperature of the fuel gas flow within the permissible range necessary for operation of the combustion turbine. The filtered flow of fuel gas is then directed to a heating system where the temperature of the fuel gas is regulated. The flow of the heated flow of fuel gas may then be regulated at a flow metering station. The heated flow of fuel gas is then sent to a combustion turbine's combustion chamber.

Abstract: Fuel gas is saturated with water heated with a heat recovery steam generator heat source. The heat source is preferably a water heating section downstream of the lower pressure evaporator to provide better temperature matching between the hot and cold heat exchange streams in that portion of the heat recovery steam generator. The increased gas mass flow due to the addition of moisture results in increased power output from the gas and steam turbines. Fuel gas saturation is followed by superheating the fuel, preferably with bottom cycle heat sources, resulting in a larger thermal efficiency gain compared to current fuel heating methods. There is a gain in power output compared to no fuel heating, even when heating the fuel to above the LP steam temperature.

Abstract: Gas turbine combined cycle system is improved to enhance gas turbine efficiency and combined efficiency by effecting steam-cooling of combustor tail tube and turbine blades. In the combined cycle system comprising; gas turbine (8) having generator (1), compressor (2), combustor (3), blade cooling air cooler (4), fan (5) and turbine (6); steam turbine (29) having high pressure turbine (21), intermediate pressure turbine (22) and low pressure turbine (23); and waste heat recovery boiler (9), saturated water of intermediate pressure economizer (12) is partially led into fuel heater (30) for heating fuel and the water cooled thereby is supplied to feed water heater (10). Steam of intermediate pressure superheater (16) is led into the combustor tail tube for cooling thereof and the steam is then supplied to inlet of the intermediate pressure turbine (22).

Abstract: A gas turbine and a method for operating a gas turbine includes a combustion chamber, a turbine having rows of blades, an air compressor, a combustion-air line for feeding compressed air into the combustion chamber, a fuel supply unit, at least one fuel line, at least one cooling-air line. Some of the blades have an interior defining cavities whereby first cavities direct at least a portion of fuel to the combustion chamber through the first cavities at least in a section of the blades, thereby preheating the fuel before being introduced into the combustion chamber. The system defined by the first cavities and the section of the blades is closed relative to an interior of the gas turbine. Second cavities fluidically connect to the air compressor and receive at least a portion of the cooling air for cooling the blades.

Abstract: A gas turbine system for utilizing waste fuel gas is described that includes a combustor that provides combusted fuel to the expansion stage of the turbine. The fuel gas entering the combustor by an inlet pipeline is a compressed admixture with air of a concentration below the lower explosive limit. The fuel gas/air admixture passes within a tube to pass to the combustion zone where combustion occurs only by reaction/self-combustion. The combusted gas passes by a tortuous path provided by an arrangement of baffles to the outlet duct. The exhausting combusted gas passes over the outer surface of the tube and gives up preheating heat to the inlet gas therein.

Abstract: A method and apparatus for increasing power output and efficiency of gas turbines. Power output is enhanced and NOx emissions are lowered while heat rate penalties are minimized by adding nitrogen or a mixture of nitrogen and water vapor to the gas turbine in conjunction with the use of low pressure steam.

Abstract: A gas turbine plant comprises an air compressor, gas turbine turbine including at least one high temperature section, a driven equipment, which are operatively connected in series, a gas turbine combustor arranged between the air compressor and the gas turbine, a fuel system disposed for supplying a fuel to the gas turbine combustor, and a heat exchange section for heating the fuel from the fuel by means of a high pressure air as a heating medium fed from the air compressor.

Abstract: A combined cycle cogeneration power plant includes a combustion turbine formed by an inlet for receiving fuel, an inlet for receiving air, a combustor for burning the combustion fuel and the air, and an outlet through which hot gaseous combustion product is released; a regenerative fuel heating system formed by a plurality of heat exchangers for transferring heat to combustion fuel for heating the combustion fuel, and modulating control valves for controlling temperature of the combustion fuel; a heat recovery steam generator (HRSG) connected to the outlet of the combustion turbine for receiving the gaseous combustion product. The HRSG is formed by a plurality of heat exchangers including steam/water drums, each having a surface blowdown connection, and evaporators connected to the steam/water drums, a water inlet connected with the heat exchangers of the HRSG, a steam outlet, and a stack for releasing the exhausted gaseous combustion product.

Abstract: A gas turbine plant comprises an air compressor, gas turbine including at least one high temperature section, and driven equipment, which are operatively connected in series, a gas turbine combustor arranged between the air compressor and the gas turbine, a fuel system disposed for supplying a fuel to the gas turbine combustor, and a heat exchange section for heating the fuel from the fuel by means of a high pressure air as a heating medium fed from the air compressor.

Abstract: A description is given of a method for feeding liquid and/or gaseous fuels to gas turbines, by means of which method the same feed path to the burner of the gas turbine can be used for both fuels, the liquid fuel being processed before being fed to the burner. This processing takes place in a fuel pre-evaporator which, for the purpose of processing the liquid fuel, has an evaporator tube 2, which is made of a material with good thermal conductivity, interacts with a heating device (3) and, at its one end, is connected to a feed device (4) for a flushing gas, and, at its other end, is connected to a fuel feed and discharge appliance (5).

Abstract: A combustion plant for a combustion process is disclosed. The plant has a pressurized combustion chamber (1), which encloses a fluidized bed and in which combustion of a fuel is to take place while producing combination gases, a gasifying device (40), which is arranged to produce a combustible gas and a degassed combustible product, and a transportation device (6, 44) for discharging the product from the gasifying device (40) and supplying it to the combustion chamber (1) for combustion of the product in the combustion chamber. The transportation device has a discharge conduit (44) connected to the gasifying device (40) and is arranged to discharge the product from the gasifying device (40). The discharge conduit (44) has a cooling member (45), which is arranged to cool the product discharged from the gasifying device (40), and a pneumatic supply conduit device.

Abstract: A combined cycle power plant includes a combination of a gas turbine plant and steam turbine plant. The gas turbine cooling steam temperature is adjusted appropriately so that the gas turbine can be made of easily obtainable material. Steam supplied from the intermediate pressure evaporator is mixed into the cooling steam supply passage for supplying therethrough exhaust steam from the high pressure steam turbine into the gas turbine high temperature portion as cooling steam. Thus, cooling steam temperature is lowered without lowering of the entire efficiency, and material of less heat resistant ability becomes usable as material forming the gas turbine high temperature portion to be cooled. Thus, design and manufacture of the gas turbine may be satisfied by less expensive and easily obtainable material.

Abstract: An aircraft engine assembly includes an engine, an engine control actuator responsive to flow of high pressure fuel therethrough for actuating engine controls, a fuel heat exchanger for heating fuel, a fuel controller for controlling flow of fuel in the aircraft engine assembly, a fuel pump having a low pressure section for pressurizing the fuel to a low pressure, and a high pressure section for pressurizing the fuel to a high pressure, an engine gearbox, a seal plate, and a manifold mounted on the engine gearbox and having the fuel pump and the fuel controller mounted thereon, with the seal plate between the fuel pump and fuel controller and the manifold. The manifold provides fuel flow paths between the fuel pump and fuel controller and the several other components of the aircraft engine assembly, replacing the several pipe connections of the prior art.

Abstract: The liquid fuel injector includes continuous air assist with both the liquid fuel injector tube and the surrounding air assist tube constrained or reduced in diameter at the discharge ends thereof. The associated gas turbine engine compressor provides combustion air to the combustor and also air for continuous air assist with a separate air pump. The air assist air may be cooled in a heat exchanger either before or after the separate air pump. The liquid fuel injector may be mounted within an annular air blast tube and directed tangentially at the inner wall of the combustor. A solenoid valve controlled purge line, together with solenoid valves in the liquid fuel and air assist lines can be utilized to purge any liquid fuel in the liquid fuel injector and manifold upon shutdown of the combustor. The liquid fuel injector can also be insulated and liquid fuel can be used to cool the fuel injector.

Abstract: Method and apparatus to prevaporize and premix liquid and/or gaseous fuels with air in two stages at two different temperatures prior to combustion. The invention is directed to the entry of a finely atomized liquid fuel, such as No. 2 diesel, into an inlet end of an annular chamber. Air is mixed with finely atomized liquid fuel, preferably generated by a small flow number liquid fuel nozzle, in a first chamber of the annular chamber at a first (relatively high) temperature for a relatively long residence time. The air and liquid fuel is moved into a second chamber of the annular chamber where a secondary hotter air is injected into the annular chamber by a plurality of staggered high velocity jets to prevaporize and premix the combined fuel and air mixture at a second higher temperature, but for a shorter time. The intense prevaporization and premixing make the mixture suitable for entry into a combustor, but without the need to add water or steam to keep pollutant emissions low.

Abstract: In a power generating plant which utilizes fuel gas for combustion at a predetermined pressure to drive a primary load, and where the fuel gas is supplied at a pressure higher than the predetermined pressure, an improvement is provided wherein a fuel gas expander is located downstream of a source of the fuel gas and upstream of a combustor for decreasing the pressure of the fuel gas, and wherein excess energy from the expander is used to drive a secondary load.

Abstract: This invention relates to an apparatus and method for increasing the reactivity of a fuel/air mixture prior to homogenous combustion of the mixture. More specifically, this invention is a pilot for a gas turbine combustor which utilizes the heat of combustion within the pilot to increase the reactivity of a portion of the fuel/air mixture utilized by the pilot.

Abstract: A method and apparatus are provided for rejecting waste heat (12) from a system (10) including a combustion engine (14), an oxidizer supply (16), and a fuel supply (18). The method includes the steps of providing a fuel flow (32) from the fuel supply (18), providing an oxidizer flow (30) from the oxidizer supply (16), splitting one of the fuel flow and the oxidizer flow into cooling flow (34) and a combustion flow (36), rejecting system waste heat (12) to the cooling flow (34), combusting the combustion flow (36) with the other of the fuel flow (32) and the oxidizer flow (30) to supply combustion gas for the combustion engine (14), and directing the cooling flow (34) into the combustion gas to reduce the temperature of the combustion gas.

Abstract: A steam cooled gas turbine system in a combined power plant, constituted such that gas turbine blade cooling steam and combustor tail pipe cooling steam are bled from an outlet of a high pressure turbine, passed through a fuel heater for heat exchange with fuel, sprayed with water to be cooled to predetermined temperatures, and then supplied to cooling areas, whereby the cooling steam supply temperatures can be maintained at predetermined values during partial load operation as well as rated operating to achieve effective cooling.

Abstract: An actual Wobbe Index is calculated for a turbine and compared to a reference Wobbe Index. By comparing the actual and reference Wobbe Indices and recognizing that the reference Wobbe Index has acceptable combustion dynamics, a measure of the combustion dynamics of the operating turbine can be obtained. To lower the possibility of combustion dynamics, causing combustor distress, a feedback signal is provided to change the temperature of the fuel gas provided the combustor. Since the Wobbe Index is a function of temperature and fuel composition, the variation in temperature can be effected to change the Wobbe Index to a reference Wobbe Index having known low combustion dynamics.

Abstract: The object of the invention is to produce a method, for operating a gas turbine installation combustion chamber with liquid fuel, by means of which the NO.sub.X figures obtained when liquid fuel is employed are similar to those for gaseous fuels. The size of the burner is then also reduced. It is also an object of the invention to provide a corresponding appliance for carrying out the method.This is achieved in accordance with the invention in that the liquid fuel (38) is evaporated in at least two steps in a separate evaporative reactor (12). In this arrangement, the liquid fuel (38) is first atomized to a fuel vapor/liquid fuel mixture (61) by direct heat exchange with a first heat exchange medium (21) and is instantaneously evaporated in this process. The evaporation of the remaining residue of the liquid fuel (38) then takes place by indirect heat exchange with a second heat exchange medium (51).

Abstract: A combined cycle power generating system includes high, intermediate and low pressure vapor turbines for driving a generator or other load by expanding a multi-component fluid mixture through the turbines. A gas turbine is drivingly connected to the generator or other load. The expanded multi-component mixture exhausted from the intermediate pressure turbine flows in heat exchange relation with the fuel inlet to the combustor for the gas turbine whereby the gas turbine fuel is preheated to reduce fuel consumption of the gas turbine and increase combined cycle efficiency.

Abstract: A waste-heat steam generator of a gas-turbine and steam-turbine system. The steam-generating heat content in the expanded working medium from the gas turbine is used for the steam turbine connected into a water/steam loop. Condensed steam from the steam turbine is supplied as condensate to the water/steam loop. A partial flow is diverted from the water-steam loop for selectively preheating the condensate or the fuel with the partial flow. To achieve high efficiency, irrespective of the fuel used for the gas turbine, when oil is used as the fuel for the gas turbine, the partial flow from the water/steam loop is used for condensate preheating. When gas is used as the fuel for the gas turbine, the partial flow is used for fuel preheating. A heat exchanger for the selective preheating either of the gas-turbine fuel or of the condensate with the partial flow is provided.

Abstract: A fuel supply apparatus for a gas turbine comprises a fuel supply system for sending fuel in a fuel reservoir to a plurality of gas turbine combustors, a heater provided for the fuel supply system for heating the fuel, a pressure reducing valve for reducing a pressure of the fuel, which has been heated, according to a required fuel pressure of a gas turbine, and a surge tank absorbing a change of the fuel pressure after the pressure reduction.

Abstract: A gas turbine combustor 1 prevents an inequality of distribution of temperatures at the outlet of the combustor which might otherwise be caused by cooling air introduced into the combustor. A liner 2 having an outer liner 2' and an inner liner 2", is disposed within a casing 3 of the gas turbine combustor 1. The liner 2 is composed of a liner inner cylinder 15, having liner cooling paths 16, and a liner outer cylinder 14. Fuel supplied via upstream side manifolds 9 and 10 flows through the liner cooling paths 16 and is discharged from a downstream side manifold 11 after cooling the liner 2. The fuel is boosted by a pump and is supplied to a fuel-air pre-mixer 13 from a fuel supply port 12 so as to be burned in the combustion chamber.

Abstract: The combustion turbine system comprises a fuel line connected to the combustor with a portion of the fuel line being disposed in heat transfer relationship with the exhaust gas from the combustion turbine so that the fuel may be heated by the exhaust gas prior to being introduced into the combustor. The system may also comprise a fuel by-pass control system for mixing unheated fuel with the heated fuel to control the temperature of the fuel being introduced into the combustor.

Abstract: A combustion chamber for a gas turbine using hydrogen as fuel, is equipped with an evaporator for liquid hydrogen which converts the hydrogen into its gaseous form that is fed directly or for instance via an external control valve into the combustor. The evaporator covers and protects at least a portion of the inner and/or outer wall that encloses the combustion chamber, whereby the evaporator also cools the combustion chamber while converting the liquid hydrogen to gaseous hydrogen.

Abstract: A system is disclosed that provides for a more efficient combined cycle turbine system by using heated coolant returning from the gas turbine engine to pre-heat fuel before that fuel is injected into the combustor. Coolant, such as steam, that is used to cool gas turbine combustors and/or transitions carries high grade heat energy that was removed from the top cycle. By returning the heat energy to the incoming fuel, energy is recovered at a more efficient rate than would result from recovering that heat energy in the bottom cycle.

Abstract: A fuel heating apparatus for a gas turbineis provided in which contact of high temperature air and fuel at the time of fuel leakage is prevented so that safety is ensured. The apparatus includes a turbine cooling air cooler of the air cooling type for cooling turbine cooling air and a fuel heater connected to the exhaust side of the turbine cooling air cooler for heating the fuel by the refrigerant air. The turbine cooling air cooler and the fuel heater 4, respectively, form a separate unit so that contact of high temperature air and fuel at the time of fuel leakage is prevented.

Abstract: Convective cooling of turbine hot parts using a closed loop system is disclosed. Preferably, the present invention is applied to cooling the hot parts of combustion turbine power plants, and the cooling provided permits an increase in the inlet temperature and the concomitant benefits of increased efficiency and output. In preferred embodiments, methods and apparatus are disclosed wherein air is removed from the combustion turbine compressor and delivered to passages internal to one or more of a combustor and turbine hot parts. The air cools the combustor and turbine hot parts via convection and heat is transferred through the surfaces of the combustor and turbine hot parts.

Abstract: A coal burner combined power plant includes a gas turbine for burning coal in a furnace under the pressure and uses produced gas. A steam turbine is combined with an exhaust gas boiler using exhaust gas from the gas turbine. Another fuel is burned at an inlet of the gas turbine for allowing the temperature at the inlet of the gas turbine to rise. A fuel reformer reforms the other fuel and is located within the furnace.