Abstract: A method of controlling the oil flow in an engine is provided. In preferred embodiments, the method comprises: flowing oil to a first oil pump upstream or downstream of a fuel oil heat exchanger and flowing oil to a second oil pump upstream or downstream of an air oil heat exchanger. One of two control functions to control the oil mass flow rate through the first oil pump is selected wherein the first control function minimizes specific fuel consumption (“SFC”) by the engine and the second control function minimizes average oil temperature. Preferably, the oil pumps are electric and the total combined oil mass flow rate of the first and second oil pumps is maintained constant.

Abstract: A cooling system for an engine of an aircraft of a having hybrid-electric propulsion system including a nacelle body including a bottom cooling air intake disposed below a propeller hub for supplying air to an oil-air cooler, wherein the bottom cooling air intake includes a splitter dividing the bottom cooling air intake into a first channel and a second channel.

Abstract: A combustion device burns fuel ammonia in a combustion chamber using compressed combustion air, and includes a combustion air cooling unit which is configured to cool the combustion air by heat exchange with the fuel ammonia during or before a compression process.

Abstract: A turbo machine including a heat exchanger flowpath is generally provided. The turbo machine includes an outer casing extended along an axial direction, a prediffuser defining an inlet passage into a combustion section of the turbo machine, an inner casing extended from the prediffuser, in which a diffuser cavity is defined between the outer casing and the inner casing, a first plenum wall extended outward along a radial direction from the prediffuser, and a second plenum wall extended outward along a radial direction from the prediffuser. The second plenum wall is separated along the axial direction from the first plenum wall. A plenum is defined between the first plenum wall and the second plenum wall. The turbo machine includes a heat exchanger including a first conduit in fluid communication with the diffuser cavity. The first conduit is in fluid communication with a passage, and a second conduit in fluid communication with the passage and the plenum.

Abstract: The invention relates to a waste heat recovery system (3) for an internal combustion engine (1), having a working fluid circuit (19) with a condenser (31) that is also connected to a working fluid cooling circuit (34), and wherein the working fluid cooling circuit (34) has a cooler (35). The invention provides a waste heat recovery system (3) having a working fluid cooling circuit (34) which is improved in comparison to one design of a working fluid cooling circuit (34). This is achieved by the working fluid cooling circuit (34) having a cooler bypass (46). This configuration makes it generally possible for part of the coolant volume flow to be routed past the cooler (35). This is advantageous in particular at low temperatures since otherwise very low pressures arise in the working fluid cooling circuit (34).

Abstract: A method of cooling a gas turbine engine case assembly includes moving a fan air valve that is operatively connected to a precooler having a bypass inlet that is configured to receive bypass air that bypasses a gas turbine engine core to facilitate a provision of bypass air through a fan air valve inlet to the bypass inlet to a first open position, in response to a core compartment temperature being greater than a target core compartment temperature. The method further includes bleeding the bypass air through a bypass outlet of the precooler into a core compartment.

Abstract: Methods, systems, and device for cycle enhancement are provided in accordance with various embodiments. Various embodiments generally pertain to refrigeration and heat pumping. Different embodiments may be applied to a variety of heat pump architectures. Some embodiments may integrate with vapor compression heat pumps in industrial, commercial, and/or residential applications. Some embodiments include a method that may include at least: removing a first heat from a vapor compression cycle; utilizing the first removed heat from the vapor compression cycle to drive a thermally driven heat pump; or removing a second heat from the vapor compression cycle utilizing the thermally driven heat pump to reduce a temperature of a refrigerant of the vapor compression cycle below an ambient temperature.

Abstract: A turbine inlet cooling method and system is disclosed that takes advantage of chilled fuel gas from one or more turbo-expanders, while taking advantage of the power generated from this process for refrigerant compression. In particular, mechanical work from the pressure drop of fuel gas through the turbo expanders will allow power generators to provide electricity to turn a refrigeration compressor's electric motor. In addition, the temperature drop of the fuel gas can operate as a first stage of cooling for a refrigeration medium returning from a turbine inlet cooler housing, among other advantages.

Abstract: According to some embodiments, a flexible regasification system comprises a floating liquefied natural gas (LNG) storage vessel; a LNG vaporizer disposed on a jetty proximate the LNG storage vessel to vaporize the LNG into natural gas; and a thermal fluid source. The LNG storage vessel is coupled to the LNG vaporizer and supplies LNG to the LNG vaporizer. The thermal fluid source is coupled to the LNG vaporizer and sends heated thermal fluid to the LNG vaporizer for converting the LNG to natural gas, which converts the heated thermal fluid to a cooled thermal fluid. The cooled thermal fluid is discharged back to the thermal fluid source, comprising a closed loop. In particular embodiments, the thermal fluid storage comprises a floating vessel disposed near the jetty. In some embodiments, the cooled thermal fluid from the LNG vaporizer is first sent to a power plant or refrigeration plant.

Abstract: A hybrid cooling system is disclosed including but not limited to an array of solar cells electrically connected to inverters for producing electricity from the sun; a chiller controller processor in data communication with the inverters and a non-transitory computer readable medium; a chiller in data communication with the chiller controller processor and in thermal communication with inverters in a sealed enclosure, wherein the inverters are cooled by an inverter coolant fluid; an array of solar cells attached to the inverters for producing power from the sun; a free cooler in data communication with the chiller controller processor and in thermal communication with the inverter cooling fluid; a Freon loop positioned a water pipe carrying the inverter cooling fluid from the invert to the chiller; and a temperature sensor apparatus in thermal communication with the inverter cooling fluid; a switch for controlling an on off state for the chiller and the cooler, where in the processor for turns the chiller on

Abstract: A system includes a turbine with an expansion section configured to expand an exhaust flow in a downstream direction, such that the expansion section includes a plurality of stages and a diffuser section coupled downstream of the expansion section. The diffuser section receives the exhaust flow along an exhaust path and an energizing flow along a wall, and the diffuser section includes the wall comprising an inner surface, so the wall is disposed about the exhaust path, and an energizing port disposed in the wall at or downstream of a last stage of the plurality of stages of the expansion section. The energizing port is configured to direct the energizing flow along the inner surface of the wall to energize a boundary layer along the wall, and a first pressure of the energizing flow is greater than a second pressure of the exhaust flow at the energizing port.

Abstract: An inner diffuser case for a turbine engine includes a fore gas path edge and an aft gas path edge defining a strut, wherein each of the fore gas path edge and the aft gas path edge include a gas path opening, a support cone structure extending radially outward from the strut, wherein the support cone structure is operable to structurally connect the strut to a turbine engine case, a diffuser case skirt structure extending radially inward from the strut, wherein the diffuser case skirt structure is operable to structurally connect the diffuser case strut to an inner support structure of the turbine engine, and at least one direct feed air passage passing radially through the strut including a radially outward upper mixing chamber opening and a radially inward direct air feed opening, the direct air feed opening is connected to a direct air feed.

Abstract: An apparatus and a process for converting a twin spool aero gas turbine engine to an industrial gas turbine engine, where the fan of the aero engine is removed and replaced with an electric generator, a power turbine is added that drives a low pressure compressor that is removed from the aero engine, variable guide vanes are positioned between the high pressure turbine and the power turbine, and a low pressure compressed air line is connected between the outlet of the low pressure compressor and an inlet to the high pressure compressor, where a hot gas flow produced in the combustor first flows through the high pressure turbine, then through the low pressure turbine, and then through the power turbine.

Abstract: A gas turbine engine including core engine is provided. Air may enter the core engine through an inlet and travel through and engine air flowpath extending through the core engine, e.g., generally along an axial direction of the gas turbine engine. The gas turbine engine additionally includes a cooling air flowpath extending outwardly generally along the radial direction of the gas turbine engine. The cooling air flowpath extends between an inlet in flow communication with engine air flowpath and an outlet defined by an opening in an outer casing of the core engine. Moreover, the gas turbine engine includes a heat exchanger positioned at least partially within the outer casing the core engine with the cooling air flowpath extending over or through the heat exchanger.

Abstract: A controller, for use in a power plant having a liquid cooling system and an air cooling system, comprising one or more inputs, configured to receive a signal from at least one deposit sensor, wherein the signal from the deposit sensor is indicative of deposits in the liquid cooling system; and one or more processors, configured to process the signal received from the deposit sensor to control the air cooling system.

Abstract: An inlet air conditioning system for a gas turbine includes an inlet duct for the with an air flow path to provide inlet air to the gas turbine; evaporative cooling media disposed in the air flow path; a water chiller; and a circulation pump that circulates water through the water chiller and the evaporative media in series. The chiller is configured to chill the water to below ambient wet-bulb temperature before the water is circulated to the evaporative cooling media. A power plant includes a gas turbine including a compressor, a combustion system, and a turbine section; a load; and the inlet air conditioning system.

Abstract: A combined cycle power plant with a gas and steam turbine system arranged on a single shaft and integrated with a cogeneration plant having a heat consumer such as a district heating system or industrial plant, including one or more steam extractions at an intermediate-pressure steam turbine that are arranged at the upper casing half-shell of the turbine and extraction steam lines that lead the extracted steam to heat exchangers of the cogeneration plant. The steam extraction outlets are arranged either singly at or near the uppermost point of the casing or in pairs to either side of the uppermost point of the casing. The specific arrangement of the extractions allows a floor-mounting of the single-shaft combined cycle power plant and as such a cost and space efficient realization of the power plant.

Abstract: A turbine housing of the exhaust turbocharger, having an inlet, which is adjoined by a spiral; having an outlet; and having a coolant arrangement; wherein the coolant arrangement has a plurality of coolant ducts, which branch off from an inlet duct section and open into an outlet duct section.

Abstract: A fluid cooling device for the propulsion unit of a propfan type aircraft including a compressed air intake at the air compressor of the turbomachine, an air vein capable of conveying the collected compressed air to a cooler, and a system for conveying the heat of the lubricant to the cooler is provided. The cooler includes a matrix body provided with a plurality of ducts for a cooling agent, the ducts extending along a first inner surface up to a second outer surface of the matrix body such that the collected pressurized air serving as a cooling agent can pass through the matrix body, the matrix body of the cooler forming a portion of the outer skin of the propulsion unit; and a set of fins extending from the outer surface towards the outside of the propulsion unit, and oriented mainly parallel to the air flow direction when the aircraft is in flight.

Abstract: A system and method for regasifying LNG using ambient air vaporizers without ambient air fog formation. The warm moist ambient air is cooled and dried using cold recovery from the cryogenic LNG stream by means of an intermediate heat transfer fluid circulated in a closed loop followed by the addition of a warm diluent air stream such that the final temperature of the exit stream of mixed air is at or above the ambient air dew point. Adjustable diluent air dampers permit an induced draft ambient vaporizer assembly.

Abstract: An inlet air conditioning system for a gas turbine includes an inlet duct for the with an air flow path to provide inlet air to the gas turbine; evaporative cooling media disposed in the air flow path; a water chiller; and a circulation pump that circulates water through the water chiller and the evaporative media in series. The chiller is configured to chill the water to below ambient wet-bulb temperature before the water is circulated to the evaporative cooling media. A power plant includes a gas turbine including a compressor, a combustion system, and a turbine section; a load; and the inlet air conditioning system.

Abstract: An air intake system for a gas turbine includes one or more coils in airflow communication with an inlet arrangement. Each coil is constructed and arranged to have a respective upstream face velocity that is intended to be within 20% of the other coils. Each coil utilizes a working fluid of a predetermined temperature range conveyed there through and a plurality of spaced fins. The fins are spaced apart to permit air to flow between adjacent fins as air flows through the coil. At least one of the coils has a number of fins per inch that is different from the number of fins per inch of the other coils. Alternatively, each individual coil has at least one section with fewer or greater numbers of fins per inch that the other sections of that coil.

Abstract: A heat exchanger which may be used in an engine, such as a vehicle engine for an aircraft or orbital launch vehicle. is provided. The heat exchanger may be configured as generally drum-shaped with a multitude of spiral sections, each containing numerous small diameter tubes. The spiral sections may spiral inside one another. The heat exchanger may include a support structure with a plurality of mutually axially spaced hoop supports, and may incorporate an intermediate header. The heat exchanger may incorporate recycling of methanol or other antifreeze used to prevent blocking of the heat exchanger due to frost or ice formation.

Abstract: A combustor of a gas turbine engine is fed with liquid ammonia and that liquid ammonia is burned to drive a turbine. Inside the exhaust passage of the gas turbine engine, an NOX selective reduction catalyst is arranged. Inside the intake air which flows into the compressor, liquid ammonia is fed. This liquid ammonia is used to cool the intake air. The NOX which is contained in the exhaust gas is reduced by the unburned ammonia which is exhausted into the exhaust passage by the NOX selective reduction catalyst.

Abstract: 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.

Abstract: The invention relates to a combined cycle power plant including a gas turbine the exhaust gas outlet of which is connected to a heat recovery steam generator, which is part of a water/steam cycle, whereby, for having a large power reserve and at the same time a higher design performance when operated at base load, the gas turbine is designed with a steam injection capability for power augmentation. For having a large power reserve at improved and optimized design performance when the plant is being operated at base load, the gas turbine includes at least one combustor, and a compressor for providing cooling air for that gas turbine, which is extracted from the compressor and cooled down in at least one cooling air cooler. The steam for steam injection is generated in said cooling air cooler, whereby said steam is injected into an air side inlet or outlet of said cooling air cooler and/or directly into said at least one combustor.

Abstract: A power plant including a thermal machine, an inlet duct for delivering a combustive first fluid in said thermal machine, a ventilation circuit for delivering a cooling second fluid to said thermal machine, the first and/or the second fluid including water therein, and a water recovery device connected with the inlet duct and/or the ventilation circuit for condensing and collecting said water from the first and/or the second fluid, the water recovery device being associated with at least one heat exchanger thermally connected with the inlet duct and/or the ventilation circuit for cooling said first and/or said second fluid beyond the dew point thereof, the water recovery device further including connecting means for delivering the water condensed from the first and/or the second fluid to a water using device.

Abstract: In an aircraft including a gas turbine engine having a compressor including a compressor booster, a turbine, and a nacelle, a system for cooling compressor discharge air provided to the turbine to cool the turbine includes a heat exchanger provided in a nacelle compartment of the gas turbine engine configured to cool the compressor discharge air by exchanging heat from the compressor discharge air to a cooling fluid; and a cooling fluid circuit configured to circulate cooling fluid through the heat exchanger and a heat sink, wherein the heat sink is at least one of an inlet of the nacelle compartment, an inlet of the compressor booster, or outlet guide vanes of the gas turbine engine.

Abstract: The present invention discloses a novel apparatus and methods for augmenting the power of a gas turbine engine, improving gas turbine engine operation, and reducing the response time necessary to meet changing demands of a power plant. Improvements in power augmentation and engine operation include additional heated compressed air injection, steam injection, water recovery, exhaust tempering, fuel heating, and stored heated air injection.

Abstract: A heat exchanger has a first passage to be connected to a source of fuel. The heat exchanger has an outlet to communicate the fuel downstream. A second passage connects to a source of air. The air passes adjacent to the first passage to heat fuel in the first passage. A jet pump is positioned downstream of the second passage to receive air from the second passage. The jet pump includes a tap connected to a housing compartment to drain fluid from the compartment. A method is also disclosed.

Abstract: A system for the generation of energy includes a further chain of units coupled with a gas turbine plant and at least one compressor consuming mechanical energy and/or at least one generator generating electrical energy. The further chain of units comprises a closed circuit having a work fluid and at least one heat exchanger, at least one expander for expanding the work fluid and for subsequently obtaining mechanical energy for the compressor and/or generator, at least one condenser for condensing the expanded work medium, and at least one pump for conveying the work fluid. The coupling of the gas turbine plant to the further chain of units is carried out by means of the heat exchanger which is fed with heat by means of the compressor air of the compressor and starts the closed circuit through the work fluid.

Abstract: An intake air cooling system 100 for a gas turbine 18 is provided with: an intake duct 12 for leading intake air from an intake-air inlet 22 to a compressor 14 of the gas turbine, the intake duct having a vertical duct 12c and a manifold part 12d disposed on a downstream side of the vertical duct; a cooling part 26 provided in the intake duct to cool the intake air by heat exchange with a cooling medium which is introduced from an outside; a filter part 42 provided on an inlet side of the manifold part to remove impurities contained in the intake air introduced through the vertical duct; and a drain catcher 110 constituted by a gutter member provided immediately above the filter part along inner wall surfaces 12c1, 12c2 of the vertical duct, the drain catcher being configured to collect drain water flowing along the inner wall surfaces of the vertical duct.

Abstract: An apparatus for increasing the efficiency of a fuel driven turbine generator, including a system comprising a turbo compressor and turbo expander that produces super chilled air mixed with ambient air to produce relatively cool dry inlet air that can be introduced under pressure into the generator. A separation compartment with a passageway extending normal to the travel direction of the chilled air is used to remove ice particles and particulates from the cool inlet air to avoid damage to the turbine blades. Additional apparatuses such as heat exchangers and steam driven turbine generators and chillers, as well as thermal energy storage systems, are contemplated.

Abstract: Methods and systems for controlling a gas turbine system are provided herein. In one embodiment, a method includes the steps of receiving at least one parameter of turbine inlet air and determining, based on the at least one parameter, an expected condensation level at an intercooler disposed downstream of an inlet air chilling system and in-line between a low pressure compressor and a high pressure compressor. The method further includes determining a desired temperature of the turbine inlet air corresponding to substantially no expected condensation at the intercooler and controlling the inlet air chilling system to chill the turbine inlet air to the desired temperature.

Abstract: A solid oxide fuel cell system (10) comprises a solid oxide fuel cell stack (12) and a gas turbine engine (14). The solid oxide fuel cell stack (12) comprises a plurality of solid oxide fuel cells (16). The gas turbine engine (14) comprises a compressor (24) and a turbine (26). The compressor (24) supplies oxidant to the cathodes (22) of the fuel cells (16) via an oxidant ejector (60) and the oxidant ejector (60) supplies a portion of the unused oxidant from the cathodes (22) of the fuel cells (16) back to the cathodes (22) of the fuel cells (16) with the oxidant from the compressor (24). The fuel cell system (10) further comprises an additional compressor (64), an electric motor (66) arranged to drive the additional compressor (64), a cooler (70) and a recuperator (72). The compressor (24) supplies oxidant via the cooler (70) to the additional compressor (64) and the additional compressor (64) supplies oxidant to the oxidant ejector (60) via the recuperator (72).

Abstract: A method and installation are disclosed which can, for example, provide for reliable, low-Nox-emission operation of a gas turbine installation with hydrogen-rich fuel gas. An exemplary gas turbine installation includes an arrangement for flue gas recirculation into a compressor inlet and for fuel gas dilution. Oxygen content in combustion air can be reduced by recirculation of recooled flue gas, and the fuel gas can be diluted with compressed flue gas. The oxygen reduction in the combustion air can lead to minimum residual oxygen in the flue gas which can be used for fuel gas dilution. As a result of the flue gas recirculation, water content in the combustion air can be increased by feedback of the water which results as a combustion product. The oxygen reduction, increased water content, and fuel dilution can reduce the flame velocity of hydrogen-rich fuel gases and enable a robust, reliable and low-emission combustion.

Abstract: A cooling system for a gas turbine engine (10) having a compressor (14), a combustor (16) and a turbine section arranged to receive combustion products from the combustor. The cooling system includes ducting (32,44) defining a flow path from the compressor to a component, such as a turbine blade (26) to be cooled within the turbine section. The ducting (32) bypasses the combustor (16). A heat exchanger (34) may be arranged in the flow path to extract heat from the flow between the compressor and the component. One or more valves (36;64;66) in the flow path are actuated under the control of a controller (48;60) at a predetermined frequency of actuation so as to pulse the flow between the heat exchanger and the component, typically to improve the aerodynamic efficiency of turbine blades in use.

Abstract: An integrated inducer heat exchanger is provided. The integrated inducer heat exchanger includes multiple airfoil devices disposed in an annular array within an inner circular casing and an outer circular casing forming multiple passages for allowing a flow of fluid from a forward side to an aft side of the integrated inducer heat exchanger. The integrated inducer heat exchanger also includes multiple annular manifolds arranged about the outer circular casing configured for supplying a flow of coolant at low temperature from one or more coolant sources and returning the flow of coolant at high temperature to the one or more coolant sources via an external heat exchanger for dissipating heat and multiple transfer tubes connecting the multiple annular manifolds with the multiple airfoil devices for transferring the flow of coolant within the airfoil devices for exchanging heat between the coolant and the fluid passing through the multiple passages.

Abstract: A gas turbine engine with a closed loop liquid metal cooling fluid system for cooling stator vanes within the turbine, in which the stator vanes include a liquid metal cooling passage lined with Tantalum or Molybdenum and a liquid metal cooling fluid of Bismuth or Lead or Zinc or Tin or alloy mixtures of these metals.

Abstract: An air-to-air cooler has a heat exchanger integrated to a housing. A first passage extends through the housing for directing a flow of cooling air through the heat exchanger. A second passage extends through the housing for directing a flow of hot air to be cooled through the heat exchanger. The first passage has a cooling air outlet tube disposed downstream of the heat exchanger. The cooling air outlet tube extends across the second passage between the heat exchanger and a hot air inlet of the second passage. The hot air inlet is disposed to cause incoming hot air to flow over the cooling air outlet tube upstream of the heat exchanger. An ejector drives the flow of cooling air through the first passage of the air-to-air cooler. A portion of the hot air flow may be used to drive the ejector.

Abstract: A turbine engine includes an air inlet fluidly coupleable with an air compressor subassembly. The air compressor subassembly is fluidly coupleable with a combustion subassembly. The combustion subassembly generates and combusts ionic hydrogen, and is fluidly coupleable with a mid-turbine subassembly. The mid-turbine subassembly is fluidly coupleable with a rear turbine subassembly. The rear turbine subassembly is fluidly coupleable with an exhaust outlet for exhausting combustion products from said mid-turbine subassembly. The combustion subassembly includes an electrostatic subassembly fluidly coupleable with a combustion chamber subassembly. The combustion chamber subassembly is fluidly coupleable with the mid-turbine subassembly. The air compressor subassembly can compress and humidify air.

Abstract: Embodiments of methods and apparatus for providing compressor extraction cooling are provided. According to one example embodiment, a method is disclosed for controlling compressor extraction cooling. The method can include providing a cooling medium. The method can include extracting air from a compressor associated with a gas turbine. The method can also include introducing the cooling medium to the compressor extraction air, wherein the compressor extraction air is cooled by the cooling medium prior to or during introduction to the turbine section. Furthermore, method can include selectively controlling at least one of the compressor extraction air or the cooling medium based at least in part on a characteristic associated with the gas turbine.

Abstract: A cooling arrangement for a gas turbine engine. The cooling arrangement comprises a discharge channel for air flow from a compressor, a first cooling channel and at least one aperture providing communication between the flow of air through the discharge channel and the first cooling channel. A restrictor device in the aperture regulates the flow of air between the discharge channel and the first cooling channel. The restrictor device deforms to vary air flowing through the aperture in response to a physical condition of the engine. This physical condition of the engine may be that of the temperature of air flowing through the discharge channel, the restrictor device responding to regulate the flow of air based on that temperature. The restrictor device may be a two-way shape memory alloy.

Abstract: In a jet engine with compressor air circulation provided for stabilizing the flow conditions, the compressed hot compressor air tapped from the flow path of the compressor (1) is first cooled in the bypass duct (3) and then resupplied to the upstream compressor via line (12). This reduces the thermal load of the blades and improves efficiency.

Abstract: A method of heating liquid fuel upstream of a combustor in a system where compressor discharge air is cooled before being supplied to fuel nozzles in the combustor includes the steps of passing the compressor discharge air through a heat exchanger in heat exchange relationship with the liquid fuel to heat the liquid fuel and cool the compressor discharge air; supplying the heated liquid fuel and the cooled compressor discharge air to the combustor.

Abstract: A gas turbine system includes a compressor; a combustion chamber; a gas turbine; and an evaporative cooler. The evaporative cooler includes a plurality of cooling elements, a flow channel, and a feed device. The plurality of cooling elements are arranged in the flow channel. The feed device supplies a liquid to the plurality of cooling elements. The liquid is evaporated or vaporized. Each of the plurality of cooling elements is a flat cooling sheet, a surface of the cooling sheet having hydrophilic properties at least in a subregion which is specified for forming a liquid film. The evaporative cooler is connected ahead of the compressor on an intake side.

Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform that axially extends between a leading edge and a trailing edge and circumferentially extends between a first mate face and a second mate face and a trench disposed on at least one of the first mate face and the second mate face. A plurality of cooling holes are axially disposed within the trench.

Abstract: An object of the present invention is to provide a solar thermal gas turbine system enhanced in resistance to effects of disturbances including weather conditions in a gas turbine which sprays water into intake air of a compressor.

Abstract: Systems, methods, and apparatus are provided for controlling the oxidant feed in low emission turbine systems to maintain stoichiometric or substantially stoichiometric combustion conditions. In one or more embodiments, such control is achieved by diverting a portion of the recirculating exhaust gas and combining it with the oxidant feed to maintain a constant oxygen level in the combined oxidant-exhaust stream fed to the combustion chamber.

Abstract: A method for cooling inlet air to a gas turbine is provided. For example, a method is described including passing inlet air through a cooling coil that includes an opening for receiving the inlet air and that is operably connected to a gas turbine power plant. The gas turbine power plant may include at least one gas turbine, and at least one gas turbine inlet which receives the inlet air. The method may further include passing circulating water through a water chiller at a first flow rate to reduce the temperature of the circulating water, the water chiller including a conduit through which the circulating water is capable of passing and passing the circulating water having the first flow rate through the cooling coil in an amount sufficient to lower the temperature of the inlet air.