Abstract: A method of controlling a rotary engine is disclosed. The rotary engine includes a shroud surrounding a rotor. The rotor carries a combustion chamber spaced from an axis of rotation of the rotor. A pressure activated valve is located between the combustion chamber and obliquely arranged exhaust nozzles. An ECU controls the combustion cycle of the engine based on a signal from a pressure sensor in the combustion chamber. The electronic control responds to the pressure signal from the pressure sensor to open a fuel control valve, to fire a spark plug and cause combustion of the fuel within the combustion chamber, and to thereafter open an air control valve to purge the combustion chamber of exhaust gasses.

Abstract: An engine is disclosed. The engine includes a rotary hub enclosing a manifold, blades radially distributed around the rotary hub, a combustion chamber at a distal end of each blade, an axle or shaft joined or fixed to the hub, and a generator operably connected to the axle or shaft. Each blade has a passage for air to flow to the combustion chamber and a fuel distribution conduit therein/thereon. The manifold connects a fuel supply conduit to the fuel distribution conduits. Each combustion chamber is configured to receive fuel and air from the corresponding fuel distribution conduit and passage, burn or detonate the fuel, and direct heated or expanded air and combustion gases in a direction that rotates the blades and the hub. The axle or shaft is configured to rotate with the hub. The generator is configured to convert a torque from the axle or shaft to electricity.

Abstract: A rotary engine includes a shroud surrounding a rotor. The rotor carries a combustion chamber spaced from an axis of rotation of the rotor. A pressure activated valve is located between the combustion chamber and obliquely arranged exhaust nozzles. An ECU controls the combustion cycle of the engine based on a signal from a pressure sensor in the combustion chamber. The electronic control responds to the pressure signal from the pressure sensor to open a fuel control valve, to fire a spark plug and cause combustion of the fuel within the combustion chamber, and to thereafter open an air control valve to purge the combustion chamber of exhaust gasses.

Abstract: An engine, a biomass powder energy conversion and/or generation system, hybrid turbine engines, and methods of manufacturing and using the same are disclosed. The engine includes a housing having an inner wall and an outer wall, a central rotary shaft extending from the housing, at least one fuel and air supply channel having a first portion extending radially from the rotary shaft and a second portion in fluidic communication with first portion of the fuel and air supply channel, at least two propulsion vessels, each propulsion vessel connected to the at least one of the fuel and air supply channel and configured to burn or detonate the fuel and rotate around the central rotary shaft; and at least one exhaust duct extending from the housing.

Abstract: Methods and systems for optimizing operation of a wind farm are disclosed. The method includes providing a farm-level wake model for the wind farm based on historical wake parameters corresponding to reference sets of interacting wind turbines in the wind farm. Another step includes monitoring one or more real-time wake parameters for wind turbines in the wind farm. A further step includes identifying at least two interacting wind turbines from the reference sets based on the wake parameters. Another step includes determining a wake offset angle between the interacting wind turbines as a function of at least one of a wind direction, a geometry between the interacting wind turbines, or a wake meandering component. The method also includes continuously updating the wake model online based at least partially on the wake parameters and the wake offset angle and controlling the interacting wind turbines based on the updated wake model.

Abstract: A method for optimizing the flexible constraints of an electric power system includes a step S1 of expressing the total power generation cost of the electric power system by using the sum of quadratic functions of active power outputs of all generator sets in the system and constructing an objective function, a step S2 of selecting a multi-dimensional flexible optimization model or a flexible power generation cost optimization model according to the practical situation of the electric power system and the practical purpose of optimization, a step S3 of determining the operating conditions of the electric power system, and a step S4 of carrying out load flow calculation.

Abstract: A rotary engine includes: a frame; a flywheel rotor having an axle rotatably mounted on the frame; a plurality of erectable pistons respectively mounted in an annular trough concentrically recessed in a rim of the flywheel rotor; and a cylinder block fastened on a housing secured to the frame and cooperatively forming an engine cylinder with the annular trough of the flywheel rotor, whereby each erectable piston is operatively erected beyond a cylinder head of the engine cylinder to dynamically define an instant combustion chamber among the cylinder head, the cylinder block, the piston and the annular trough of the rotor; and whereby upon combustion and explosion in the combustion chamber, the explosion gases will force and drive the erectable piston to rotate the flywheel rotor for outputting mechanical energy.

Abstract: A rotary engine includes a casing having a first circular boring and a second circular boring smaller than the first circular boring. The first circular boring interconnects with the second circular boring. A piston rotor can move in a rotating manner within the first circular boring in the casing. A power head, ported to pass exhaust gases through a hollow center shaft, can move in a rotating manner within the second circular boring in the casing. The piston rotor and the power head can be coupled via a gear system to properly rotate during operation, with the piston rotor rotating counterclockwise and the power head rotating clockwise, or vice versa.

Abstract: A rotor system is disclosed for a reactive drive rotary wing aircraft. Apparatus and methods are disclosed for mounting to the rotor hub certain controls, both electrical and mechanical, as well as fuel delivery for tipjets mounted to rotor blades. Air passively or actively drawn through rotor may feed the tipjets directly through the blades, while fuel and control is delivered along the blade to the tip thereof.

Abstract: A fuel distribution manifold comprises an outer shell having an inner surface. The outer shell defines an inlet for receiving fuel from a parent supply line, a base opposite the inlet, a central manifold axis that intersects the inlet, and a plurality of outlets for delivering fuel to offspring fuel lines, each outlet defining a respective outlet axis. In one exemplary embodiment, a fuel distribution manifold also comprises a center-body having an outer surface and being positioned within the outer shell wherein the outer surface of the center-body and the inner surface of the outer shell define a flow-path through which fluid flows from the inlet to the plurality of outlets. In another exemplary embodiment, at least one of the outlets is positioned adjacent to the base and oriented so that its respective outlet axis is rotated relatively to a radial direction that intersects the central manifold axis.

Abstract: A rotary pulse detonation engine produces mechanical output by detonating a fuel/air mixture in detonation chambers between adjacent impeller blades. The impeller is housed within an outer casing and rotated around an inner sleeve. Air is passed through a velocity stack and through intake ports on the inner sleeve into the detonation chambers. Fuel is injected into the detonation chamber through fuel line(s). Igniters on the interior of the outer casing ignite the fuel and produce the detonations. Spent gas is released through exhaust ports situated on the outer casing, front plate or rear plate. The impeller may be supported by front and rear bearings in low speed applications, or by a pressurized cushion of air provided by exhaust gases directed to the front and rear ends of the impeller by a perforated tube sheet positioned between the impeller and the inner sleeve in high speed applications.

Abstract: Apparatus and methods for combustion of fuel includes, in some embodiments, a fuel nozzle which injects fuel into a combustion channel of a wave rotor combustor or a pulse detonation combustor. In some embodiments the combustion process includes a backward-propagating detonation wave within a substantially closed channel which compresses discrete quantities of combustible and noncombustible mixture. Yet other embodiments include a precombustion chamber integrated into the wave rotor, the outlet stator or both.

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: 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 method is provided for the measurement of parameters of a gas present in a gas turbine combustion chamber. The method includes tuning a laser to a range containing the absorption lines of species to be analyzed in the gas, and directing the laser light through the combustion chamber and detecting laser light reflected off boundary walls of the combustion chamber. In order to analyze the absorption spectrum measured at high temperatures and pressures, a signature recognition algorithm is applied to the spectrum. The measured absorption spectrum is cross-correlated with a calibration absorption model spectrum for the absorption lines at several temperatures, pressures, and concentrations generated prior to the measurement. Values for pressure, temperature, and concentrations of selected species in the gas are determined simultaneously allowing direct control of the combustion chamber process. An apparatus for carrying out the method is also provided.

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: An example method of controlling performance of gearbox of a gas turbine engine includes establishing a gear characteristic of a plurality of double helical gears each disposed about a respective axis in a gearbox. Performance of the plurality of double helical gears is controlled by selecting a circumferential offset distance between a first plurality of gear teeth spaced apart from a second plurality of gear teeth on each of the plurality of double helical gears in response to the established gear characteristic.

Abstract: An aircraft propulsion system is disclosed herein. The aircraft propulsion system includes a core engine having an intake, a compressor section, a combustor section, and a turbine section arranged along a centerline axis. The aircraft propulsion system also includes a nacelle surrounding the core engine. The aircraft propulsion system also includes at least one free power turbine driven to rotate by exhaust gases exiting the turbine section. The aircraft propulsion system also includes at least one rotor module driven to rotate by at least one free power turbine. The aircraft propulsion system also includes first and second pylons extending away from the nacelle and operable to mount the core engine to an aircraft. The first and second pylons are spaced from one another on opposite sides of at least one plane containing the centerline axis and mirror one another across the at least one plane.

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: 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: Apparatus and methods for combustion of fuel. Some embodiments of the inventions include a fuel nozzle which injects fuel into a combustion channel of a wave rotor combustor or a pulse detonation combustor In some embodiments the combustion process includes a backward-propagating detonation wave within a substantially closed channel which compresses discrete quantities of combustible and noncombustible mixture. Yet other embodiments include a precombustion chamber integrated into the wave rotor, the outlet stator or both.

Abstract: When the compressor is a multistage compressor, each compression space includes an inlet arranged in the vicinity of the center axis and an outlet arranged in the vicinity of the outer circumference of the turbine wheel, and there is a connecting conduit between the outlet of a first compressor stage and the inlet of a second compressor stage. The connecting conduit is delimited by a first wall of the space of the first compressor stage and a second wall of the space of the second compressor stage. Each wall can be a friction disk.

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 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: An engine having at least one stage of propeller rotor blades, and a load, the at least one stage being associated with electrical generation means to generate electricity for the load. The load is switchable into a high load state in the event of an overspeed signal from the rotor blades. Also a method of controlling rotor overspeed of an engine, characterized by the steps of: i. detecting an overspeed signal from the at least one stage, and ii. switching the load into a high load state to apply torque to the at least one stage to counteract the overspeed.

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 method for determining wind turbine location within a wind power plant based on at least one design criteria. A wind turbine layout including at least one wind turbine location is prepared and site conditions at each wind turbine location are determined. One or more plant design metrics are evaluated in response to the site conditions. The plant design metrics are analyzed in response to the site conditions. The method further includes applying constraints to the wind turbine layout and comparing the plant design metrics to the design criteria and constraints. Thereafter, the wind turbine locations are selectively adjusted within the layout in response to the comparing step until a stop criteria is reached.

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: A gas turbine engine and method of fabrication includes a gas turbine engine with a structure having movable portions and static portions. At least a portion of the structure includes a composite material having an electrically conductive path formed from carbon nanotubes configured for conducting electrical signals therealong.

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 rotary bearing system that supports a shaft for rotating machinery in a housing comprises: at least one stationary rotary bearing mounted in the housing for supporting a respective journal of the shaft in a desired axial and radial alignment; at least one slidable rotary bearing, with an outer surface mounted within a respective inner support surface of the housing to form a respective linear bearing such that each slidable bearing may slide axially along the inner support surface of the housing, for supporting another respective journal of the shaft with the desired radial alignment; and at least one layer of a crystalline material that exhibits a high degree of basal cleavage bonded to at least one of the linear bearing surfaces; wherein each layer of crystalline material allows each slidable rotary bearing to slide axially along each respective linear bearing to compensate for differences in the coefficient of expansion of the housing and the shaft so as to prevent the bearing system from binding due to

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 rotary bearing system that supports a shaft for rotating machinery in a housing comprises: at least one stationary rotary bearing mounted in the housing for supporting a respective journal of the shaft in a desired axial and radial alignment; at least one slidable rotary bearing, with an outer surface mounted within a respective inner support surface of the housing to form a respective linear bearing such that each slidable bearing may slide axially along the inner support surface of the housing, for supporting another respective journal of the shaft with the desired radial alignment; and at least one layer of a crystalline material that exhibits a high degree of basal cleavage bonded to at least one of the linear bearing surfaces; wherein each layer of crystalline material allows each slidable rotary bearing to slide axially along each respective linear bearing to compensate for differences in the coefficient of expansion of the housing and the shaft so as to prevent the bearing system from binding due to

Abstract: A method and a pre-shaped workpiece for making at least a portion of a gas turbine fuel nozzle are disclosed having opposed gripping tabs which can be secured to machine tool holders during manufacturing by a machine tool.

Abstract: An airfoil is disclosed having a concave pressure side and a convex suction side defining a chord length, and a leading edge and a trailing edge. A leading edge protective strip is adhered by a bond layer to and protectively covers the leading edge and respective predetermined portions of the pressure side and suction side of the airfoil body from the leading edge downstream towards the trailing edge. The predetermined portion of the suction side covered by the leading edge protective strip is less than the predetermined portion of the pressure side covered by the leading edge protective strip.

Abstract: The present invention relates to an annular combustion chamber for a gas turbine engine comprising an external wall, an internal wall, a wall connecting these two walls and constituting a chamber end wall, the chamber end wall being provided with openings for the fuel injection systems, heat shielding deflectors being fixed to the wall, the deflectors comprising a flat wall portion with an opening centered on said openings for the fuel injection systems, two longitudinal edges and two transverse edges, wherein, at least along one of the longitudinal edges, a deflector comprises a tongue forming a joint cover, creating a housing along said edge for the edge of the adjacent deflector so as to seal the join between the two adjacent edges of the two deflectors, said tongue being spaced away from the chamber end wall so as to create a space supplied with cooling air via orifices in the chamber end wall.

Abstract: A first-stage turbine that is adapted for receiving high energy air directly from a combustion chamber in a gas turbine engine auxiliary power unit includes a disk formed from a first alloy and having an outer surface, and a unitary blade wheel formed from a second alloy that is different than the first alloy. The unitary blade wheel includes an annular member having an inner surface that is joined to the disk, and blades that are integrally formed with the annular member.

Abstract: A fuel nozzle includes a swirler assembly including a radially inner surface and a radially outer surface, a plurality of vanes coupled to the swirler assembly radially outer surface. Each vane includes a first sidewall and a second sidewall, the first and second sidewalls are joined at a leading edge and at an axially-spaced trailing edge, and a plurality of openings are formed through each respective vane. Each opening extends from the leading edge to the passage to define a flow passage that extends from the passage to the leading edge. A method for fabricating a fuel nozzle assembly is also described.

Abstract: Systems and method for generating electricity using heat from a SCWO reaction. The system may comprise a pump that pumps the mixture undergoing the SCWO reaction to a pressure above the critical pressure point for the mixture. The pressurized mixture is heated, by a heating system, above the critical temperature point for the mixture. The SCWO reaction occurs in a reaction chamber. The reaction chamber is in thermal communication with a vessel that holds water such that the heat from the mixture heats the water into steam. The steam powers a steam turbine, which is connected to an electrical generator to thereby generate electricity.

Abstract: A method of assembling a stator assembly includes coupling at least one stator ring segment to a portion of a casing using at least one circumferential stator ring groove defined in the casing. The method also includes coupling at least one stator blade assembly to a portion of the stator ring segment such that at least one radial passage is at least partially defined by at least one of the stator blade assembly and the stator ring segment. The stator assembly includes at least one first radial passage defined within a portion of the stator ring segment. The assembly also includes at least one second radial passage coupled in flow communication with the first radial passage. The second radial passage is at least partially adjacent to at least one of a portion of the stator blade assembly and a portion of the stator ring segment.

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: A turbine engine includes an engine housing enclosing: a centrifugal compressor having a rotor; at least one centrifugal compressor bore mounted to the rotor; at least one blade mounted to each of the at least one centrifugal bore and disposed proximate to at least one static wall; a turbine disposed in connection with the centrifugal compressor; a thrust bearing disposed in connection with the rotor; and means for moving said rotor with reference to the at least one static wall attached to the thrust bearing.

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: A pulsed combustion apparatus includes a conduit having an outer wall and an inner wall. The inner wall has a number of apertures. An interior space is separated from the outer wall by the inner wall. An induction system is positioned to cyclicly admit charges to the interior space. An ignition system is positioned to ignite the charges. Flow directing surfaces are positioned to at least cyclicly direct cooling air through the apertures.

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: A pulse detonation system for a gas turbine engine having a longitudinal centerline axis extending therethrough, the pulse detonation system includes an air inlet duct in flow communication with a source of compressed air, the air inlet duct including at least one port formed therein for permitting compressed air to flow therethrough, a fuel injector mounted to the air inlet duct in circumferentially spaced relation to each port, and a device mounted to the air inlet duct in circumferentially spaced relation to each fuel injector for initiating a detonation wave. A rotatable ring member is also positioned in coaxial relation around a portion of the air inlet duct, with the ring member including at least one stage of detonation disposed therein. Accordingly, a detonation wave is produced in each detonation stage and combustion gases following each detonation wave create a torque which causes the ring member to rotate.