Abstract: A machine for generating energy by exploiting the flow of a fluid. The machine includes a first fixed or static component part or stator which defines a first cylindrical inner surface and a second outer surface. The machine further includes a second component part or rotor configured to be rotated and accommodated in the inner space confined by the first cylindrical inner surface. The first fixed or static component part or stator is configured to introduce a fluid into the inner space confined by the first inner surface through the second outer surface and first inner surface of the stator, such that the interaction between the flow of fluid introduced into the inner space and the second component part or rotor results in the second component part or rotor being rotated.

Abstract: A combustion engine (10) comprises a radial compressor (16) in flow communication via a flow passage (22) with a compressor-combustor array (20) radially outward of the radial compressor (16), both rotatable around a central axis (12). The compressor-combustor (20) comprises an array of rotor blades (26). The walls of the blades (26) define a plurality of chambers (28, 30). Each chamber (28, 30) has a flow inlet (32) to receive fluid from the radial compressor (16), and a flow outlet to exhaust fluid radially outwards from the compressor-combustor (20). The plurality of chambers (28, 30) comprises a first pilot combustion chamber (28a) and a second pilot combustion chamber (28b). The first pilot combustion chamber (28a) is provided with a first fuel injector (40a), and the second pilot combustion chamber (28b) is provided with a second fuel injector (40a).

Abstract: Electromagnetic gyroscopic stabilizing propulsion system method and apparatus is an electric gyroscope that creates magnetic fields used to rotate its flywheel. The rotation of its flywheel creates both a gyroscopic effect and thrust with airfoil shaped spokes. The invention attaches to an airframe through an articulating joint that causes the axle of the gyroscope to precess in a vertical orientation regardless of the movements/angle of the airframe. The gyroscope's thrust aligns itself with the axle of the gyroscope. The net effect is that the invention has tremendous efficiency, no external drive because it is also a motor, tremendous power from magnetic leverage of the flywheel, and stability because of the gyroscopic effect.

Abstract: A dynamic pressure exchanger configured for a combustion process includes a seal plate and a rotor assembly. The rotor assembly is mounted for rotation relative to the seal plate about a central axis of the dynamic pressure exchanger.

Abstract: A wave rotor combustor includes an inlet plate, an outlet plate, and a rotor drum assembly positioned therebetween. The inlet plate is formed to include an inlet port arranged to receive a mixture of fuel and air. The outlet plate is formed to include an outlet port arranged to receive combusted gasses flowing out of the wave rotor combustor. The rotor drum assembly is arranged to rotate relative to the inlet and outlet plates and to combust the fuel and air mixture as part of a combustion process. Conditioned air is passed through the wave rotor combustor to regulate a temperature distribution of the wave rotor combustor.

Abstract: A combustion engine comprising a radial compressor in flow communication via a flow passage with an annular compressor-combustor array radially outward of the radial compressor. Both the radial compressor and compressor-combustor are co-axial with, and rotatable around, a central axis.

Abstract: A vented combustion chamber for an insect attractant engine is provided for a flying insect trapping device of the type that relies upon combustion of a fuel to generate a flow of carbon dioxide to attract flying insects. The combustion chamber, which is generally tubular and horizontally oriented in operation, is vented through a hole formed in one side of the chamber wall that extends from the outer surface of the chamber into the interior thereof. During operation of the device, this through-hole allows gas inside the chamber to be vented to the outside, changing the effective length of the combustion chamber for the purposes of wave generation is changed so that creation of a resonance cycle or standing wave, and the resulting acoustic phenomenon of howling, is prevented.

Abstract: The present disclosure introduces a rotor assembly having a concentric arrangement comprising a rotating turbine portion, a cooling channel and an annular reinforcement wall. The concentric arrangement is configured to rotate around a common axis. Also introduced is a rotary engine comprising the rotor assembly, in which the cooling channel further functions as a rotating compressor portion. The rotary engine also comprises a stator assembly that itself comprises a static turbine portion positioned upstream of the rotating turbine portion, a static compressor portion positioned downstream of the rotating compressor portion, and a combustion chamber positioned downstream of the static compressor portion and upstream of the static turbine portion.

Abstract: A device for pivoting a rotor of a turbomachine from a first—preferably horizontal—position into a second—preferably vertical—position is provided. The rotor includes a plurality of rotor discs held together by at least one tension rod, the device includes two sidewall elements arranged parallel to one another, a bridge element connecting the sidewall elements to one another, and a divisible turning ring for form-fittingly holding an axial section of the rotor to be positioned perpendicularly. The rotor further includes two pins rotatably seated in the sidewall elements and arranged flush to the turning ring in order to pivot the turning ring about a pivot axis parallel to the horizontal plane. The bridge element includes a disk, wherein the disk is movable perpendicularly to the horizontal plane in order to be bolted in a flange-like manner onto a rotor retained by the device.

Abstract: A fully enclosed fan motor assembly includes a motor housing. A stator is located radially inward from the motor housing. A rotor is located radially inward from the stator, and the gap in between the rotor and stator defines a rotor stator gap. A shaft is located radially inward from the rotor. A fin portion extending radially outward from the shaft is used to dissipate heat from the rotor to air drawn through the rotor stator gap and over the fin portion.

Abstract: An air compressor includes a compression mechanism for compressing intake air and discharging the compressed air, and an intake chamber portion through which intake air is introduced into the compression mechanism. The intake chamber portion has an inlet of intake air and an outlet connected to the compression mechanism. The intake chamber portion is integrated with the compression mechanism. The intake chamber portion has therein a partition wall extending in the direction from the inlet toward the outlet to form plural flow passages in the intake chamber portion. The plural flow passages have different flow path lengths and connect between the inlet and the outlet.

Abstract: A device comprising a combustion toroid for receiving combustion-induced centrifugal forces therein to continuously combust fluids located therein and an outlet for exhaust from said combustion toroid.

Abstract: A flywheel engine which contains the shell, ignition system, cranking system and fuel system. Install flywheel shaft on shell while at least install a flywheel on the flywheel shaft. Set up gas mixture room on flywheel and open air inlet louver at the central part of the room. Install air cylinder at the peripheral region of flywheel and open jet exhaust at the peripheral region of gas mixture room. Set up admittance port at the bottom of the air cylinder; connect the admittance port and the jet exhaust. Install flame lighter in the air cylinder. The angle of the jet direction of chambers and the radius of flywheel is ?1.

Abstract: A combustion systems and components for rotary ramjet engines. An injection system, optionally stratified for ease of engine startup, provides an air and fuel mixture to a combustion chamber. An ignition system ignites the mixture. A flameholding system may be positioned for communication with the combustion chamber to force an ignited flow of the air and fuel mixture toward a center of rotation within the ramjet engine. The ramjet engine may have a diverging stator for improved exhaust efficiency. The ignition may take place in the engine air intake. Alternatively, the ignition may take place within the combustion chamber using a dual-hub electrically charged system. An impulse turbine may use recirculation of injected fuel to cool a rim-rotor and/or to reduce windage on the rim-rotor. A sealing system may reduce gas leaks from a fuel conduit into the engine air intake.

Abstract: An axially aligned combustion engine with a rotationally fixed housing and rotationally disposed rotor is presented. Particularly, the rotor includes an engine assembly and one or more air compressor assemblies axially aligned about an axis within the housing. The engine assembly includes a plurality of radially disposed combustion chambers extending from a closed interior edge outward toward an at least partially open access port disposed at an outer peripheral edge of the engine assembly. As the engine assembly rotates within the housing, the radially disposed combustion chambers are successively aligned with or communicatively disposed with an air manifold to receive compressed air, actuator(s) to receive fuel and ignite the fuel, and an exhaust manifold to expel the combusted gases.

Abstract: A prime mover uses detonation chambers to provide rotary power through a center hub. The center hub has a center shaft able to rotate and mounted to the center hub, and rotating arms are mounted to the center shaft. A detonation chamber is mounted to each rotating arm at a distance from the center hub which establishes a force moment about the center hub. Fuel passages connect an external fuel source, such as hydrogen and oxygen, with the detonation chambers to deliver fuel to the detonation chambers. Fuel delivered to the detonation chambers is ignited to establish a reaction force which is transferred through the rotating arms and the center hub. The rotating force is used to drive a generator.

Abstract: The engine includes a stator including an inlet to admit a compressed gaseous oxidant flow, and an exhaust to discharge burnt gases; and a rotor mounted in the stator in a fluid-tight manner and rotatable with respect to the stator around a rotation axis. The rotor has an inlet orifice oriented in the axial direction and faces the inlet opening in a manner to receive the compressed air flow, a combustion chamber communicating with the inlet orifice, and an exhaust duct which leads in a transverse direction from the combustion chamber to the periphery of the rotor for discharging burnt gases through the exhaust. The inlet, the combustion chamber and the exhaust duct are arranged in fluid communication with each other during the rotor rotation, without the interposition of valve members. Seal members seal the inlet orifice and the exhaust duct when they face the internal surface of the stator.

Abstract: Certain embodiments of the invention may include systems and methods for providing unchoked control of gas turbine fuel control valves. According to an exemplary embodiment of the invention, a method is provided for active control of a gas flow control valve. The method may include receiving a desired fuel command and an inlet pressure parameter, and determining a gas flow gain based at least in part on the inlet pressure parameter. The method may also include determining a valve flow coefficient based at least in part on the desired fuel command and the gas flow gain, and controlling the gas flow control valve based at least in part on the valve flow coefficient.

Abstract: A rotating device for producing pressure by expansion of a-pressurized process substance is provided. The rotating device includes a U-channel structure arranged to be rotatable around an axis of a shaft. The U-channel structure includes an expansion point arranged at a periphery of the rotating device, a sinking channel for delivery of the pressurized process substance to the expansion point, a rising channel for delivery of the expanded process substance from the expansion point to a regulating valve for a delivery of the expanded process substance under a higher pressure than that of the pressurized process substance through an outlet channel to an energy recovery device. The rotating device is connected to driving devices in order to rotate the U-channel structure around the axis of the shaft.

Abstract: The turbojet engine inlet and exhaust covers are permanently installed at the inlet and exhaust outlet or nozzle of an aircraft turbojet engine installation. The covers preclude the entrance of small animals, windblown debris, snow, and/or other contaminants into the engine inlet or exhaust while the airplane is inoperative. The covers have an iris-type shutter configuration, each cover having a plurality of leaves pivotally attached to a circumferential stationary housing that is attached to the engine or nacelle. A rotary ring is rotated through a small arc to pivot the shutter leaves inward and outward to close and open the engine opening. The rotary ring may be driven by an electric motor, or by hydraulic or pneumatic power. The system may be automated to close according to engine temperature after flight, and/or to open upon initiation of the engine start sequence for the aircraft.

Abstract: A stationary crankshaft, cylindrical rotor, low friction, adjustable timing, pistonless, rotary internal combustion engine. A cylindrical rotor rotates freely about a stator, also cylindrical in shape. A plurality of cavities are circumferentially disposed along the external circumference of the stator and the internal circumference of the rotor that, when rotationally aligned, form combustion chambers. Rotation of the rotor is induced by electrical-spark induced combustion of a fuel/air mixture in the combustion chambers. The combustive exhaust is vented into an exhaust manifold for transport to an exhaust disposal system, such as a catalytic converter. Cooling, fuel pressurization, and electrical generation can be internal to the engine or supplied externally. Engine speed, torque, and other operational requirements can be accommodated by coupling multiple rotational units together and engine vibration can be virtually eliminated by offsetting the combustion chambers on coupled units.

Abstract: A pollution-free propulsion engine includes a rotating arm, a hollow axle defining a fuel delivery chamber, and hydrogen and oxygen sources. The rotating arm is formed with a detonation chamber, an opening and two tubular ducts therebetween. The axle is inserted into the opening. A pair of holes is formed in the axle to establish paths of fluid communication from the fuel delivery chamber through the ducts and into the detonation chamber as the rotating arm turns. The hydrogen source comprises a thin palladium binding layer deposited onto an aluminum sheet. Hydrogen molecules that are trapped in the binding layer are released, and the hydrogen is fed into the delivery chamber, through one duct and into the detonation chamber. At the same time, oxygen is delivered into the detonation chamber through the other duct, and the oxygen-hydrogen combination is detonated to release energy, which is converted into mechanical energy.

Abstract: A rotary engine includes a rotor having one or more combustion chambers connected to an exhaust passageway extending radially outward from the combustion chamber to an exhaust port adjacent a peripheral edge of the rotor. The exhaust gas is expelled at an angle to thereby generate cause the rotor to rotate. The housing may include reflective surfaces that reflect shockwaves from the exhaust gas back towards vanes on the rotor to thereby capture additional energy from the exhaust gas. The housing may also include stators that capture additional energy from the exhaust gas and rotate the rotor. An intake port fluidly connected to the combustion chamber is aligned with an opening in the housing as the rotor rotates to thereby allow comprised air to flow into the combustion chamber. As the combustion chamber rotates, it is closed off by a closed portion of the housing, fuel is injected, and ignited, to thereby generate exhaust gases and generate power.

Abstract: A pollution-free propulsion engine includes a rotating arm, a hollow axle defining a fuel delivery chamber, and hydrogen and oxygen sources. The rotating arm is formed with a detonation chamber, an opening and two tubular ducts therebetween. The axle is inserted into the opening. A pair of holes is formed in the axle to establish paths of fluid communication from the fuel delivery chamber through the ducts and into the detonation chamber as the rotating arm turns. The hydrogen source comprises a thin palladium binding layer deposited onto an aluminum sheet. Hydrogen molecules that are trapped in the binding layer are released, and the hydrogen is fed into the delivery chamber, through one duct and into the detonation chamber. At the same time, oxygen is delivered into the detonation chamber through the other duct, and the oxygen-hydrogen combination is detonated to release energy, which is converted into mechanical energy.

Abstract: A rotary engine includes a rotor having one or more combustion chambers connected to an exhaust passageway extending radially outward from the combustion chamber to an exhaust port adjacent a peripheral edge of the rotor. The exhaust gas is expelled at an angle to thereby generate cause the rotor to rotate. The housing may include reflective surfaces that reflect shockwaves from the exhaust gas back towards vanes on the rotor to thereby capture additional energy from the exhaust gas. The housing may also include stators that capture additional energy from the exhaust gas and rotate the rotor. An intake port fluidly connected to the combustion chamber is aligned with an opening in the housing as the rotor rotates to thereby allow comprised air to flow into the combustion chamber. As the combustion chamber rotates, it is closed off by a closed portion of the housing, fuel is injected, and ignited, to thereby generate exhaust gases and generate power.

Abstract: The present invention provides an ultra micro gas turbine engine which includes a wave rotor. In various embodiments, the ultra micro gas turbine engine of the present invention includes a rotating disk which has a compressor, a wave rotor and a turbine, a first stationary member which includes an inlet and a first wave rotor port end plate, a second stationary member which includes an outlet and a second wave rotor port end plate and a combustion chamber which includes a fuel inlet and an igniter.

Abstract: The present invention publishes a flywheel engine which contains the shell, ignition system, cranking system and fuel system. Install flywheel shaft on shell while at least install a flywheel on the flywheel shaft. Set up gas mixture room on flywheel and open air inlet louver at the middle part of the room. Install air cylinder at the peripheral region of flywheel and open jet exhaust at the peripheral region of gas mixture room. Set up admittance port at the bottom of the air cylinder; connect the admittance port and the jet exhaust. Install flame lighter in the air cylinder. The angle of the jet direction of chambers and the radius of flywheel is ?1. The advantages of the present invention includes: Consumes less energy during the intermediate links, improve the energy usage ratio, burns the fuel more fully. It could discharge less harmful gases and could be more environmentally friendly. It improves the engine's power output incalculably and simplifies the structure of the engine greatly.

Abstract: A sump housing for scavenging lubricant is disclosed herein. The sump housing includes an outer wall defining a chamber. A lubricated structure operable to rotate can be disposed within the sump housing. The sump housing also includes an out-take for lubricant scavenging. The out-take extends across a chordal arc of the chamber. The out-take includes an upstream first portion of the outer wall diverging away from the chordal arc at a first rate. The out-take also includes a downstream second portion of the outer wall opposite the first portion. The second portion diverges away from the chordal arc toward the first portion at a second rate greater than said first rate to define a blunt wall facing the first portion for reducing the likelihood that windage will limit lubricant scavenging.

Abstract: A rotor of a supersonic rotary heat engine comprises a rotor axis about which the rotor is adapted and configured to rotate, a plurality of thrust matter passageways, and a plurality of cooling passageways. Each of the thrust matter passageways is at least partially bound by a gas permeable wall. The outlet port of each thrust matter passageway is adapted and configured to discharge gaseous fluid into an exhaust environment external to the rotor in a manner creating a torque on the rotor about the rotor axis. Each of the cooling passageways is in fluid communication with a respective one of the thrust matter passageways via the gas permeable wall that at least partially bounds the respective thrust matter passageway.

Abstract: This invention presents a compact, light, efficient and high power output rotary internal combustion engine utilizing the waste heat. The engine has a rotor rotatable within a housing, but has no piston. The rotor has a plurality of combustion chambers, with inlets for introduction of fuel and outlets for exhaust of combustion products. The exhaust imparts rotation to the rotor within the housing. Fixed end caps are provided at each end of the housing. The engine is cooled with steam, air and water. The engine is suitable for applications that require efficient, high power to weight ratio, such as aircrafts, ships, and heavy duty transportation. The engine may use low grade fuel with a low cetane number, by using specially treated pulverized coal.

Abstract: A tangential combustion turbine is disclosed which is based on a casing, a rotor, and moving levers. A radial compressor is attached to the rotor and creates air pressure which pushes air into the combustion chamber based on the position and design of the combustion lever. The combustion chamber is defined by spaces between rotor lobes, and by combustion levers and exhaust levers which follow the rotor surface. A premix fuel system or direct fuel injection is used to create combustion. The exhaust gases then pass through the exhaust lever into the exhaust piping as the rotor rotates.

Abstract: A rotary piston engine having a housing defining an un-obstructed circular toroidal chamber, a toroidal segment piston in said chamber, a detonation chamber having an outlet substantially tangential to the outer diameter of said toroidal chamber wherein said piston is driven in a continuous circular orbit by energy derived from pulse-detonation generated shock wave and pulse-jet gas flow.

Abstract: A gas generator for providing continuous pressure rise combustion, including: a rotatable member including a forward end, an aft end, a circumferential wall and a longitudinal centerline axis extending therethrough; an outer circumferential wall, wherein the rotatable member is positioned therein so that the circumferential wall of the rotatable member is spaced radially inwardly from the outer circumferential wall; at least one helical channel formed by a plurality of helical sidewalls extending between the circumferential wall of the rotatable member and the outer circumferential wall, each helical channel being open at the forward end and the aft end of the rotatable member so as to provide flow communication therethrough; an air supply for providing air to each helical channel; and, a fuel supply for providing fuel to each helical channel.

Abstract: A small scale apparatus for generating heat and power is presented which comprises a small rotary turbomachine, in such a manner that compression, heating and expansion of the working medium take place in a connected rotating component, with a diameter of less than 200 mm and which then has a rotational speed of higher than 50 000 revolutions per minute, the rotor completely or partially rotating in an atmosphere which is formed by the expanded gas or vapor. Additional characteristic features mentioned include a multistage compressor, intercooling of the working medium, recovery of residual heat (regeneration) from the expanded gases, external heating of the working medium and a procedure based on a two-phase substance as working medium.

Abstract: An orbiting combustor nozzle (OCN) engine, having a rotating assembly comprising a co-rotating compressor and nozzle wheel enclosed within a non-rotating outer casing, defining a rotating combustion chamber, is disclosed. Combustion occurs in the combustion chamber in a vortex of gas that rotates at the same angular velocity as the rotating assembly. Also disclosed, is a method of cooling a blade of a rotating wheel, such as a turbine wheel or nozzle wheel, by projecting cool air at the base of the vane form a nozzle corotating with the blade. Such cooling is easily implemented in an OCN engine with use of an innovative annular combustor. Also disclosed is a method of countering axial backflow by use of a combustion chamber compressor.

Abstract: An engine for providing rotary power about an output shaft with a high power-to-weight ratio includes a plurality of flow guiding blades mounted on the inner surface of an annular thruster base. The flow guiding blades cooperate with the peripheral surface of a rotor for forming a plurality of ramjet-like thrusters. The configuration of the flow guiding blades allows for optimization of the number of thrusters. The centrifugal forces generated by the rotating components is compensated by an annular reinforcement wall made with high strength materials allowing for downsizing of the rotor and associated components.

Abstract: An apparatus for generating electricity that uses at least one jet-type engine fueled with fissile material. The nuclear fueled jet engine is affixed to a connecting member that projects from a central, rotatable shaft, which is in engageable communication with an apparatus for converting the rotation of the central shaft to electricity, such as a stator and rotor combination. The engine is positioned so that the thrust produced by the jet engine causes the engine and connecting member to travel in a radial direction around the longitudinal axis of the central shaft, rotating the central shaft. As the central shaft rotates, the rotational motion of the central shaft is transmitted to conversion apparatus. An operating gas is used to cool the nuclear fueled jet engines and as the propellant for the jet engines.

Abstract: A single wheel radial flow gas turbine having a single rotating wheel and a stationary shroud. The wheel has a radial flow compressor section at its inner portion and a turbine section at its outer portion. The compressor and turbine sections are located on the same side of the wheel, which is directly or indirectly coupled to a generator for absorbing the excess rotational energy. A radial flow combustor section and a nozzle section are mounted on the stationary shroud. Air flows radially through the compressor, combustor, nozzle, and turbine sections; there is essentially no axial flow component. Optionally, water may be injected radially downstream from the fuel injectors for power augmentation, NOx reduction, and metal temperature moderation.

Abstract: A jet-propelled rotary engine comprises a stator and a rotor operatively coupled to the stator for rotation of the rotor relative to the stator about a rotor axis. The rotor comprises at least first and second jet assemblies wherein the first jet assembly defines a first converging flow region, a first diverging flow region downstream of the first converging flow region, and a first discharge port and wherein the second jet assembly defines a second converging flow region, a second diverging flow region downstream of the second converging flow region, and a second discharge port. The rotary engine further comprises a combustion region having an upstream portion and is adapted to cause a combustion reaction of an oxygen-fuel mixture in the combustion region in a manner to form combustion reaction products which comprise at least a part of thrust matter to be discharged through the discharge ports of the first and second jet assemblies.

Abstract: A thermodynamic pressure generator having an oscillating valve that allows premixed fuel to enter a combustion chamber in turbulence, until it comes into contact with an annular spoiler, which converts a portion of the fuel into a Karmon vortex ring for delayed ignition. A continuous spark then ignites the remaining fuel with rapid pressure rise that kills the vortex. The fuel in the vortex goes from laminar to turbulence, adding fuel to the already burning charge, super charging it and permitting total ignition. Thus, present invention exhaust contains no polluting by-products and only sensible heat is released into the environment. Exhaust gases are released radially through turbine vanes having a shape that permits a relatively low rotational speed, with sufficient peripheral speed to create torque of considerable degree. Applications include, but are not limited to, land transportation vehicles, propeller-driven airplanes, and marine vessels.

Abstract: The cryogenic rotary coupling comprises segments of a cryogenic line that are capable of turning relative to each other about a pivot axis of the rotary coupling. Radial retaining elements and axial retaining elements define the pivot axis of the rotary coupling. One of the segments comprises a vacuum-insulated double-walled female portion and the other segment comprises a vacuum-insulated double-walled male portion engaged at least in part in the female portion. A first sealing gasket is interposed between a free end of the male portion engaged in the female portion and one of the retaining means. A second sealing gasket is interposed between a free end of the female portion surrounding the male portion and the other one of the retaining elements. A heater device is disposed in the vicinity of the second gasket.

Abstract: A fuel cell system and method of operation in which the fuel cell system has a fuel cell unit with anode and cathode, a media flow path for supplying substantially pure hydrogen to the anode, a media flow path for the cathode, an anode exhaust-gas flow path and a cathode exhaust-gas flow path. A fan for supplying air to the cathode is provided in the flow path of the cathode, and a catalytic burner is arranged in the cathode exhaust-gas flow path. The anode exhaust-gas flow path opens into the catalytic burner and/or into the cathode exhaust-gas flow path upstream of the catalytic burner. The combined, catalytically converted fuel cell exhaust-gas flow is passed into an expansion machine.

Abstract: An apparatus for generating electricity that uses at least one jet-type engine fueled with fissile material. The nuclear fueled jet engine is affixed to a connecting member that projects from a central, rotatable shaft, which is in engageable communication with an apparatus for converting the rotation of the central shaft to electricity, such as a stator and rotor combination. The engine is positioned so that the thrust produced by the jet engine causes the engine and connecting member to travel in a radial direction around the longitudinal axis of the central shaft, rotating the central shaft. As the central shaft rotates, the rotational motion of the central shaft is transmitted to conversion apparatus. An operating gas is used to cool the nuclear fueled jet engines and as the propellant for the jet engines.

Abstract: A main engine mounted auxiliary power unit comprises an auxiliary power unit integrated with a primary gas turbine engine into a single power plant suited for aircraft applications. The auxiliary power unit can be mounted within an engine core compartment of the main engine or at the main engine aft center body. The integration of the auxiliary power unit provides for installation and certification cost savings to the airframer by eliminating the need for mounting an auxiliary power unit to the tail section of the aircraft.

Abstract: Embodiments of the invention provide an IGCC which achieves improved plant thermal efficiency by using a cooling steam supply system that cools the high-temperature sections of the gas turbine 34. Embodiments of the invention further provide and IGCC in which the cooling steam recovery system recovers steam after cooling the gas-turbine high-temperature section and makes practical re-use of the energy and substances within the system. Therefore, embodiments of the invention can reduce or eliminate the degradation of certain equipment by cooling the high-temperature sections. Methods are provided for increasing the thermal efficiency o an IGCC.

Abstract: The new concept design proposed by Feodor Koudinov of the configuration of heat engines combustion chamber in the earth atmosphere and airless conditions with intended use in:

Abstract: A turbine suitable for use for low-power cogeneration or as a power generator of electric automobiles, the turbine being characterized in that a vane (1) curved in section and having a nozzle (2) somewhere in the inner side is constructed to extend along the axis of a hollow vane shaft (3), wherein the fluid fed from the vane shaft end into the vane shaft is spouted through the nozzle (2) against the inner side of the vane and is rotated.

Abstract: A rotary ramjet engine. A rotary ramjet engine is provided operating with a very low axial flow component. The engine has a closely housed rotor and shaft mounted for rotary motion with respect to an engine case. A plurality of ramjet combustors are provided at the periphery of the rotor, and a set of spaced apart helical strakes are provided extending outward from the surface portion of the rotor toward the interior wall of the engine case, less a running clearance therefrom. A centerbody is provided for each ramjet inlet. The centerbody is disposed along a helical axis parallel to the strakes, and includes a leading edge structure, opposing sidewalls, and a shaped cavity, and a rear end wall. Each set of strakes cooperate to define, rearward of the rear end wall of each inlet centerbody, a combustion chamber for mixing therewithin and inlet fluid and burning fuel therein to form hot combustion gases therefrom.

Abstract: A rotary ramjet engine generator set. An exemplary embodiment of a rotary ramjet engine is provided operating with a very low axial flow component. The engine has a closely housed rotor and shaft mounted for rotary motion with respect to an engine case. A plurality of ramjet combustors are provided at the periphery of the rotor, and a pair of spaced apart helical strakes are provided extending outward from the surface portion of the rotor toward the interior wall of the engine case, less a running clearance therefrom. An inlet centerbody is provided for each ramjet. The centerbody is disposed along a helical axis parallel to the strakes, and includes a leading edge structure, a pair of sidewalls defining therebetween a shaped cavity, and a rear end wall. Each pair of strakes cooperate to define, rearward of the rear end wall of each inlet centerbody, a combustion chamber for mixing therewithin and inlet fluid and burning fuel therein to form hot combustion gases therefrom.

Abstract: An engine for providing rotary power about an output shaft with a high power-to-weight ratio includes a plurality of flow guiding blades mounted on the inner surface of an annular thruster base. The flow guiding blades cooperate with the peripheral surface of a rotor for forming a plurality of ramjet-like thrusters. The configuration of the flow guiding blades allows for optimization of the number of thrusters. The centrifugal forces generated by the rotating components is compensated by an annular reinforcement wall made with high strength materials allowing for downsizing of the rotor and associated components.