Abstract: A thermal management system for a gas turbine engine includes a first heat exchanger and a second heat exchanger in communication with a bypass flow through an inlet. A valve is operable to selectively communicate the bypass flow to either the first heat exchanger or the second heat exchanger through the inlet.

Abstract: A system is disclosed one form of which is an aircraft that includes a pod capable of housing a work providing device. The pod can also include a thermal conditioning system and a power generation device that can be powered from the work providing device. The pod can provide thermal conditioning services and power services to a payload aboard the aircraft. In one non-limiting form the payload is a directed energy member that can be cooled using the thermal conditioning system and powered using the power generation device.

Abstract: A method of assembling an evaporative cooler for use with a gas turbine engine system. The method includes coupling a drain pan to a support frame, wherein the drain pan includes a front wall and a back wall. A media support assembly is coupled to the drain pan to form the evaporative cooler. The media support assembly includes a media support wall and a rear flange. The media support wall extends substantially perpendicularly from the drain pan front wall and defines a continuous drainage chamber between the drain pan front wall and the back wall.

Abstract: One embodiment of the present invention is a unique vehicle. Another embodiment is a unique propulsion system. Yet another embodiment is a unique system. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for vehicle propulsions systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

Abstract: A gas turbine generator set includes a compressor unit including at least one compressor, at least one generator and at least one combustion chamber. Exhaust gases from at least one turbine are recirculated for a further thermal utilization. At least one cooling fluid compressor is configured to compress a cooling fluid including at least one of fresh air and a portion of the recirculated exhaust gases for a cooling of thermally loaded parts.

Abstract: A gearbox support assembly for a turbine engine includes an epicyclic gear arrangement and a first tapered bearing and a second tapered bearing spaced apart from the first tapered bearing. The first tapered bearing and the second tapered bearing support the epicyclic gear arrangement.

Abstract: A gas turbine engine is provided, including an air inlet in fluid communication with a compressor, a combustor, a compressor turbine, and a power turbine. The compressor and compressor turbine may be mounted on a first drive shaft, and the power turbine may be mounted on a second shaft. The engine further includes an engagement mechanism adapted to selectively engage the first drive shaft to the second drive shaft, wherein the first drive shaft and second drive shaft rotate at substantially the same speed when the engagement mechanism is engaged. The disclosed multi-spool gas turbine engine provides improved part power fuel consumption at reduced output shaft speeds. The proposed invention can relate to turbines with two or more gas generator spools.

Abstract: A modular gasification reactor for a plasma assisted gasification reaction system is disclosed for converting fuel, such as, but not limited to, biomass, to syngas to replace petroleum based fuels used in power generation. The system may be a modular system housed within a frame facilitating relatively easy transportation. The system may include a reactor vessel with distinct reaction zones that facilitate greater control and a more efficient system. The system may include a syngas heater channeling syngas collected downstream of the carbon layer support and to the pyrolysis reaction zone. The system may also include a syngas separation chamber configured to produce clean syngas, thereby requiring less filtering. The system may further include an agitator drive assembly that prevents formation of burn channels within the fuel.

Abstract: A new gas turbine-fuel cell Hybrid Cycle is proposed. The fuel cell advantageously operates close or under atmospheric pressure and is fully integrated with the gas turbine that is based on an Inverted Brayton-Joule Cycle. The idea of the invention is to capitalize on the intrinsic oxygen-nitrogen separation characteristic of the fuel cell electrolyte by sending to the Inverted Brayton-Joule Cycle only the anodic flow, which is the one free of nitrogen. In this way the flow that expands in the turbine consists only in steam and carbon dioxide. After the expansion the steam can be easily condensed, separated and pumped up. Therefore the compressor has mainly only to compress the separated carbon dioxide. This effect generates a substantial advantage in term of efficiency and enables separating the carbon dioxide.

Abstract: A steam generator coupled in flow communication downstream from a combustion device that produces a flow of exhaust gases includes a heating device configured to heat the exhaust gases that include oxides of nitrogen (NOx), and an oxidation catalyst coupled downstream from the heating device. The oxidation catalyst facilitates reducing an amount of NOx in the exhaust gases channeled into the oxidation catalyst at a first temperature that is less than a thermal regeneration temperature for a catalytic material and at a second temperature that is approximately equal to at least the thermal regeneration temperature such that the catalytic material is simultaneously regenerated.

Abstract: A combined cycle power plant includes a compressor section including a compressor inlet and a compressor outlet, and a turbine section operatively connected to the compressor section. The turbine section includes a turbine inlet and a turbine outlet. A heat recovery steam generator (HRSG) is fluidly connected to the turbine outlet. A combustor includes a head end and a combustor discharge. The head end is fluidly connected to the compressor outlet and the combustor discharge is fluidly connected to the turbine inlet. A carbon dioxide collection system is fluidly connected to one of the compressor outlet and the head end of the combustor. The carbon dioxide collection system is configured and disposed to extract a first fluid comprising carbon dioxide and a second fluid from a substantially oxygen free fluid flow passed from the one of the compressor outlet and the head end of the combustor.

Abstract: A combustor/coil assembly for direct electromagnetic induction from a detonation wave comprises an annular combustor, a magnetic field source and a port. The annular combustor comprises an inner liner and a coaxial outer liner. The outer liner is electrically insulated from the inner liner. The magnetic field source generates a substantially axial magnetic field inside the annular combustor. The port introduces reactants into the annular combustor to form the detonation wave. The detonation wave induces a voltage between the inner liner and the outer liner by forming a current loop between the inner liner and the outer liner.

Abstract: A rotor assembly for use with a turbine engine. The rotor assembly includes at least one rotor disk that includes an inner surface that defines a dovetail groove. At least one turbine bucket is coupled to the rotor disk. The turbine bucket includes an airfoil that extends outwardly from a dovetail. The dovetail is inserted at least partially within the dovetail groove. A tang assembly extends from one of the inner surface of the rotor disk and the dovetail. the tang assembly minimizes a rotation of the turbine bucket with respect to the rotor disk.

Abstract: A system and method are disclosed for supplying fuel to an auxiliary power unit of an aircraft. The system includes a primary fuel source, a secondary fuel source, and a secondary valve. The primary fuel source is in fluid communication with the auxiliary power unit to provide a primary fuel thereto. Similarly, the secondary fuel source is in fluid communication with the auxiliary power unit to provide a secondary fuel thereto. The secondary valve regulates flow of the secondary fuel from the secondary fuel source to the auxiliary power unit. The method provides a secondary fuel from a secondary fuel source to the auxiliary power unit if an emergency operating condition experienced by the aircraft results from either exhaustion or contamination of a primary fuel.

Abstract: A fire enclosure for an auxiliary power unit having a hot zone formed by a gas turbine comprises an annular fire enclosure body, an axial expansion joint and a radial expansion joint. The annular fire enclosure body is configured to encapsulate the hot zone. The fire enclosure includes a first end and a second end. The axial expansion joint is connected to the first end. The radial expansion joint is connected to the second end.

Abstract: Hydrocarbon fuel is sent to a reformer, which produces carbon and hydrogen. The hydrogen is sent to a fuel cell which uses it to generate electricity, and the electricity is used to actuate an electric motor that is coupled to an output shaft of a turbine to impart torque to the shaft. Additionally, hydrocarbon fuel can be provided to the turbine intake directly and/or carbon from the reformer can be mixed with steam from the fuel cell and sent to the turbine intake, in either case to impinge on the turbine blades and impart further torque to the output shaft.

Abstract: A method and apparatus are disclosed for a multi-spool gas turbine power plant which utilizes motor/generator devices on two or more spools for starting the gas turbine and for power extraction after starting. Methods are disclosed for controlling engine responsiveness under changing load and/or ambient air conditions; providing a momentary power boost when required; providing some engine braking when needed; providing over-speed protection for the free power turbine when load is rapidly lowered or disconnected; charging an energy storage system; and restoring the compressors and/or turbines toward their operating lines when surge or choking limits are approached.

Abstract: A thermal power plant, in particular a solar thermal power plant, includes a gas turbine device, in which a medium circulating in a circuit and heated by thermal energy is conducted through a turbine in order to produce electric energy. The medium is subsequently circulated into a condenser cooled by a cooling device in order to liquefy the medium. The cooling device is designed as a solar-operated cooling device having a closed coolant circuit.

Abstract: A device for producing electrical power in a gas turbine or the like of an aircraft, the device including a plurality of thermoelectric cells having a face surrounding a hot source. A cold source is constituted by a cold fluid flowing over the other face of the thermoelectric cells.

Abstract: This ventilation system (1), notably for a gas turbine, comprises at least one fan (2) opening into an air extraction duct (5). It comprises at least one device (6) for varying the pressure drop in the air extraction duct (5), comprising a means (8) of regulating the air flow rate in the air extraction duct (5).

Abstract: Hydrocarbon fuel is sent to a reformer, which produces carbon and hydrogen. The hydrogen is sent to a fuel cell which uses it to generate electricity, and the electricity is used to actuate an electric motor that is coupled to an output shaft of a turbine to impart torque to the shaft. Additionally, hydrocarbon fuel can be provided to the turbine intake directly and/or carbon from the reformer can be mixed with steam from the fuel cell and sent to the turbine intake, in either case to impinge on the turbine blades and impart further torque to the output shaft.

Abstract: A rotor blade assembly is disclosed herein. The rotor blade assembly includes a composite blade portion extending a length from a root to a tip. A leading edge of the composite blade portion extends from the tip to an end point along the length between the tip and the root. The rotor blade assembly also includes a base portion fixed to the composite blade portion proximate to the root. The rotor blade assembly also includes a sheath extending around the composite blade portion. The sheath is positioned along the length adjacent to the base portion and between the root and the end point of the leading edge.

Abstract: The invention relates to a gas turbine (10) for transforming thermal energy, for example from coal, biomass or the like, to mechanical work, comprising a compressor unit (11), a turbine unit (13, a combustion chamber (15) and a heat exchanger (14) with associated pipe system. The gas turbine (10) id configured in such way that the heat is supplied to the air flow between the compressor unit (11) and the turbine unit (13) by means of hot flue gas from the combustion chamber (15) and is brought into a compression chamber (12) arranged between the compressor unit (11) and the turbine unit (13).

Abstract: A gasifying furnace gasifies solid fuel or liquid fuel. A gas turbine drives a turbine to generate power by using combustion gas generated by burning mixed gas of compressed air compressed in a compressor and gas generated in the gasifying furnace in a combustor. A booster boosts compressed air bled from the compressor, and feed the compressed air to the gasifying furnace. A bleed source valve is provided in a bleed line between the compressor and the booster. An abnormality stop controller stops the booster and the gas turbine, based on an opening angle of the bleed source valve or a bleed pressure on an upstream side of the bleed source valve.

Abstract: A multiple-fluid, multiple-substance, multiple-phase, multiple-pressure, multiple-temperature, multiple-stage turbine engine. In preferred embodiments, one or more fluids are supplied by passageways in the turbine shaft or supplied by non-shaft passageways, or both, through rotor passageways to multiple-phase, multiple-fluid, multiple-substance nozzles affixed to one or more perimeters, radial surfaces, axial surfaces, and/or curved or slanted surfaces of the turbine rotor assemblies. The multiple perimeters, radial surfaces, axial surfaces, and/or curved or slanted surfaces of the turbine rotor assemblies are preferably configured and located for multiple inlet and exit velocities of the nozzles, multiple inlet and exit pressures of the nozzles, or combinations thereof. The one or more fluids entering the turbine may each be a substance of single phase, or a substance of multiple phases, or a mix of the single-phase and/or multiple-phase conditions for two or more entrance fluids.

Abstract: It is desired to obtain a technique which enables turning of a compressor driven by a multi-shaft gas turbine. The multi-shaft gas turbine has a high-pressure side shaft and a low-pressure side shaft. A compressor drive device applies a drive force to a compressor connected to the low-pressure side shaft of the multi-shaft gas turbine. The compressor drive device includes: a motor which generates a drive force; and a control unit which controls the motor so as to generate an rpm when turning the compressor. If the torque generated by the gas turbine is insufficient, the control unit controls the motor so as to carry out a helper motor operation for increasing the torque.

Abstract: The present invention relates to a system for producing power, notably electrical power, comprising a gas turbine (10) with at least one compressor (12; 12a, 12b) having at least one compression stage, at least one expansion turbine (16), a heat exchanger (14) between said compressor and said expansion turbine, and a hot gas source (48, 72). According to the invention, the exchanger is a rotary regenerative exchanger (14) through which the hot gases and compressed gases from said compressor pass.

Abstract: A system for cooling cooling-air in a gas turbine engine, the system having an electricity generating fuel-cell, and an arrangement for receiving water produced by the fuel cell, delivering the water to the engine, and cooling cooling-air inside the engine using the water.

Abstract: A gas turbine includes a gas turbine body in which a rotor is rotated with the energy of combustion gas produced by combustion of fuel to take out rotational energy from the rotor, an inlet casing that is attached to the gas turbine body and that guides the air to a compressor section compressing the air, an air intake chamber that is connected to the inlet casing and that guides the air taken in from the atmosphere to the gas turbine body, and a notch so formed in the air intake chamber as to cover the entire range where the rotor passes or exists when the rotor is moved.

Abstract: A centrifugal de-oiler of variable flow section, the de-oiler including a hollow shaft that is movable in rotation. The shaft includes at least one air-passing orifice and a piston housed in the shaft so as to subdivide the inside of the shaft into two compartments that are sealed relative to each other. One compartment includes the air-passing orifice(s) being subjected to ambient pressure, and the other compartment is subjected to varying pressure in the air/oil enclosure. The piston is configured to move in translation inside the shaft between two extreme positions under effect of the pressure difference between the two compartments, the extreme position including a first position in which the air-passing orifice(s) is/are disengaged, and a second position in which the air-passing orifice(s) is/are partially obstructed by the piston.

Abstract: Several improvements to an aircraft turbine engine and Auxiliary Power Unit (APU) are disclosed, as well as methods of using these improvements in routine and emergency aircraft operations. The improvements comprise the addition of cockpit-controllable clutches that can be used to independently disconnect the engine's integrated drive generator (IDG), engine driven pump (EDP), fuel pump, and oil pump from the engine gearbox. These engine components may then be connected to air turbines by the use of additional clutches and then powered by the turbines. Similar arrangements are provided for the APU components. Cranking pads, attached to various engine and APU components, are disclosed to provide a means for externally powering the components for testing purposes and to assist with engine and APU start.

Abstract: A gas turbine engine comprising a nacelle and a breather duct. The breather duct provides communication between a component of the engine within the nacelle and the exterior of the nacelle and opens at an exhaust port on the external surface of the nacelle. There is a clean air outlet slot located downstream of the exhaust port and arranged to expel, in use, a sheet flow of clean air to form an aerodynamic barrier between the external surface of the nacelle and a flow of breather air expelled from the exhaust port.

Abstract: Breather air, containing oil mist, is discharged from a nacelle 4 of a gas turbine engine through an exhaust port 26 at a surface 22 of the nacelle 4. Energised air, at relatively high velocity is discharged from a clean air outlet 28, and forms a barrier between the breather air and the external surface 22, so preventing contamination of the surface 22 by oil deposited from the breather air.

Abstract: Hydrocarbon fuel is sent to a reformer, which produces carbon and hydrogen. The hydrogen is sent to a fuel cell which uses it to generate electricity, and the electricity is used to actuate an electric motor that is coupled to an output shaft of a turbine to impart torque to the shaft. Additionally, hydrocarbon fuel can be provided to the turbine intake directly and/or carbon from the reformer can be mixed with steam from the fuel cell and sent to the turbine intake, in either case to impinge on the turbine blades and impart further torque to the output shaft.

Abstract: A method of operating a drive system for a load is disclosed. The drive system may have an electric motor/generator and a gas turbine engine. The engine may have a combustor, and main and pilot flow paths via which fuel is supplied to the combustor. The engine may be operable in low and standard emissions modes. A proportion of the fuel that is supplied to the combustor via the pilot flow path may be greater in the standard emissions mode than in the low emissions mode. The method may include determining an engine power requirement of the load, and whether the engine power requirement of the load is sufficiently large to operate the engine in the low emissions mode. Additionally, the method may include operating the electric motor/generator if the engine power requirement of the load is not sufficiently large to operate the engine in the low emissions mode.

Abstract: An assembly for a gas turbine engine includes a combustor and a vane assembly disposed downstream thereof. A portion of an outer platform of the vane assembly defines an axial sliding joint connection with the combustor, and includes a plurality of depressions located in an outer circumferential surface thereof opposite the combustor. The depressions are disposed in regions of expected higher thermal growth about the circumference of the outer platform such that thermal growth of the entire outer platform is substantially uniform circumferentially therearound.

Abstract: One aspect relates to a hybrid propulsive technique, comprising providing a flow of a working fluid through at least a portion of an at least one jet engine. The hybrid propulsive technique comprises extracting energy from the working fluid that is at least partially converted into electrical power, and converting at least a portion of the electrical power to a torque. The hybrid propulsive technique also comprises rotating an at least one independently rotatable compressor stator at least partially responsive to the converting the at least a portion of the electrical power to the torque.

Abstract: A turbomachine comprising at least one Stirling cycle thermal engine which is mounted at the end of a radial arm of the exhaust casing and comprises a working chamber located outside the primary and secondary flows, a displacing piston associated with a moving element of an energy generation system, and two exchangers, heating and cooling, formed in parts of the radial arm respectively intercepting the primary flow and the secondary flow, these two exchangers communicating with each other and with the working chamber for the circulation of a working fluid.

Abstract: The present invention relates to the processing of biomass, particularly but not exclusively poultry litter, to generate energy. A method is presented for generating power from biomass comprising a gasification process (44) involving the gasification of biomass to produce a combustible fuel gas and a power generation process (49) involving combustion of the combustible fuel gas to produce a combustion exhaust gas which is fed to a power generator (49) to generate power and a generator exhaust gas. The method further comprises placing compressed air (1) in thermal contact with the generator exhaust gas (47) to facilitate heat transfer between the compressed air and the generator exhaust gas, and feeding a first portion of compressed air that has thermally contacted the generator exhaust gas to the gasification process to assist in gasification of further biomass.

Abstract: A system involving a two-step gasification of a carbonaceous source to produce bulk hydrogen that avoids the early formation of CO2 and obviates the traditional water gas shift (WGSR) step, carbochlorination of a metallic ore the production of metals found in the ore that utilizes carbon monoxide as an oxygen sink, rather than the traditional coke, and carbon oxides management that eliminates major impediments to emission-neutral power generation and the reduction of major metals. The gasification uses a rotary kiln reactor and gas-gas cyclonic separation process to separate synthesis gas into purified hydrogen and purified carbon monoxide. Purified bulk carbon monoxide issued in metallurgical reduction, and purified bulk hydrogen as fuel for an emission-neutral hydrogen combined cycle (HCC) turbine power generation station.

Abstract: In some circumstances such as with regard to contra-rotating turbo prop arrangements in aircraft it is desirable to vary the pitch of the blades and/or provide de-icing facilities. Advantageously, these blade pitch and de-icing facilities could be provided through electrical actuators. Unfortunately, provision of electrical power to such rotating components traditionally requires utilisation of slip rings which are subject to wear. By providing a self-contained electrical generator comprising a first hub and second hub with respective generator parts it is possible to utilise the contra-rotating nature in order to create relative motion and therefore electrical power generation in coils opposed by permanent magnets. Slide contacts for electrical connection are avoided whilst electrical power can be generated within the rotating reference frame defined by the hubs.

Abstract: A power plant with a CHP system having a distillation apparatus to yield a high thermally efficient electrical power plant for reduced fuel usage and subsequent lower CO2 emission specie. The incorporation of a Combined Heat and Power (CHP) system with a microturbine, makes use of the low emissions gas turbine exhaust gas waste heat of this electrical power generation plant for distillation processes, replacing the current use of electrical heating elements of the distiller unit. The inventive device includes a distiller apparatus and a microturbine gas turbine electrical power plant, a heat exchanger device where the exhaust gas waste heat energy of a gas turbine power plant passes thru one side of a series of plates/sheets of material and or tubes and heats the process fluids on the opposite side and also a surface area condenser is incorporated to reduce the product vapor state to a liquid.

Abstract: According to the inventive method, incoming air enters (via 16) the separation unit (14); at least one fraction of said incoming air is supplied from the gas turbine (2), and at least one gas flow (via 20,24), which is enriched with nitrogen, is extracted from the separation unit (16); heat exchange occurs in a first exchanger (56) between the fraction of incoming air from the gas turbine (2) and a liquid fraction (58) to be heated in order to obtain a first heated liquid fraction (58); said heated liquid fraction (58) is added to a liquid mixture fraction (48) in order to obtain a liquid fraction to be cooled (60); heat exchange occurs between said liquid fraction which is to be cooled and the nitrogen-enriched gas flow in a second exchanger (50).

Abstract: A method of producing substitute natural gas (SNG) includes providing a syngas stream that includes at least some carbon dioxide (CO2) and hydrogen sulfide (H2S). The method also includes separating at least a portion of the CO2 and at least a portion of the H2S from at least a portion of the syngas stream provided. The method further includes channeling at least a portion of the CO2 and at least a portion of the H2S separated from at least a portion of the syngas stream to at least one of a sequestration system and a gasification reactor.

Abstract: A combustor/coil assembly for direct electromagnetic induction from a detonation wave comprises an annular combustor, a magnetic field source and a port. The annular combustor comprises an inner liner and a coaxial outer liner. The outer liner is electrically insulated from the inner liner. The magnetic field source generates a substantially axial magnetic field inside the annular combustor. The port introduces reactants into the annular combustor to form the detonation wave. The detonation wave induces a voltage between the inner liner and the outer liner by forming a current loop between the inner liner and the outer liner.

Abstract: A combined gearbox breather and drain mast is mounted to a nacelle. The combined gearbox breather and drain mast is made of a composite material and includes a body portion made of a single component with a first passage in fluid communication with a gearbox and a second passage in fluid communication with an engine component. The first passage is separate from the second passage.

Abstract: An auxiliary power unit (APU) with integral firebox provides an integral unit for aircraft to utilize an APU without the use of a separate firebox. The present invention comprises a turbomachine intake air duct secured to an enclosure, the enclosure having a bleed air port extending from the combustor to outside of the enclosure, with an APU secured therein. The APU can be retrofitted to existing aircraft, or installed in newly-built aircraft.

Abstract: Disclosed is an enclosure for a gas turbine, the enclosure including an enclosure section configured to partially enclose the gas turbine, and at least one other enclosure section, the at least one other enclosure section being configured to assemble with the enclosure section in a manner that associates the at least one other enclosure section with the enclosure section, wherein said at least one other enclosure section and said enclosure section are configured to substantially enclose the gas turbine when the at least one other enclosure section is associated with the enclosure section.

Abstract: A thrust generator is provided. The thrust generator includes an air inlet configured to introduce air within the thrust generator and a plenum configured to receive exhaust gas from a gas generator and to provide the exhaust gas over a Coanda profile, wherein the Coanda profile is configured to facilitate attachment of the exhaust gas to the profile to form a boundary layer and to entrain incoming air from the air inlet to generate thrust.

Abstract: A system for removing carbon dioxide from an atmosphere to reduce global warming including an air extraction system that collects carbon dioxide from the atmosphere through a medium and removes carbon dioxide from the medium; a sequestration system that isolates the removed carbon dioxide to a location for at least one of storage and generation of a renewable carbon fuel; and one or more power supplying units that supply heat to the air extraction system to remove the carbon dioxide from the medium, at least one of the one or more power supplying units being a fossil fuel plant.