Abstract: A pulsed turbine rotary engine comprising a fixed section, an output shaft, a plurality of nozzle openings, an air supply system, a fuel supply system, and an ignition system. The fixed section defines a plurality of intake openings each defining an intake axis. The output shaft is supported by the fixed section for rotation about a shaft axis. The nozzle housings are operatively connected to the output shaft for rotation about the shaft axis. Each nozzle housing defines a nozzle chamber in fluid communication with a nozzle inlet and a nozzle outlet defining a thrust axis. The air and fuel supply systems direct air and fuel through the intake openings. The ignition system comprises spark plugs for igniting fuel within the nozzle chambers.

Abstract: A pulse detonation system for a gas turbine engine having a longitudinal centerline axis extending therethrough includes a rotatable cylindrical member having a forward surface, an aft surface, and an outer circumferential surface, where at least one stage of spaced detonation passages are disposed therethrough. The pulse detonation system further includes a shaft rotatably connected to the cylindrical member and a stator configured in spaced arrangement with the forward surface of the cylindrical member and a portion of the shaft. The stator has at least one group of ports formed therein alignable with the detonation passages as the cylindrical member rotates. In this way, detonation cycles are performed in the detonation passages so that combustion gases exit the cylindrical manner in a substantially tangential direction with respect to the outer circumferential surface to create a torque which causes the cylindrical member to rotate.

Abstract: A turbine engine has a circumferential array of combustion chamber conduits downstream of the compressor and upstream of the turbine. Means are provided for directing oxygen-containing gas from the compressor to the conduits so as to cyclically feed a gas charge into each conduit through its first port and permit discharge of combustion products of the charge and fuel through both the first and second ports.

Abstract: A pulsed combustion device includes a support structure and a combustor carousel supported by the support structure and rotating relative thereto about an axis. The carousel has a number of combustion conduits in a circumferential array. Each conduit cyclically receives a charge and discharges combustion products of the charge. A venturi effect may help control fuel/air charge leakage from a flowpath spanning the carousel and a stationary manifold.

Abstract: The invention relates to a method of a continuous determination of an instantaneous position of an impeller blade tip (5′) in a rotor turbine machine, particularly in a turbine impeller (6) in a turbojet engine during its operation in a real condition in order to obtain a current information on a technical state of the blade (5). In a selected place of an housing (7) of a rotor turbo machine, in a movement plane of impeller blade tips (5′), it is arranged in a stable manner at least one microwave antenna (3) with an aperture shape (4) which is consistent with an internal surface of an housing (7). The microwave signal (11), which is produced by a microwave homodyne system, is emitted, and then received, through a microwave antenna (3). The output signal (9) from that system, which carries out information on each instantaneous position of an impeller blade tip (5′) in relation to an antenna aperture (4), is converted by an electronic system, and then it is read.

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: 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: An apparatus for generating torque, the apparatus comprising: a rotor hub adapted for applying torque to a shaft; and a plurality of pulse detonation engines adapted for impulsively detonating a plurality of fuel/air mixtures to generate thrust forces and applying the thrust forces to the rotor hub to generate the torque.

Abstract: A steam-powered rotary engine is provided in which a rotor arm assembly and an outer ring are positioned such that steam ejected from outlets at the two ends of the rotor arm assembly will impact at a substantially right angle onto steps or depressions formed on the inner portion of the outer ring. Both the rotor arm assembly and the outer ring are mounted or supported in a freely rotatable manner on a housing or frame. The ejection of the steam from the rotor arm causes the rotor arm to rotate in a direction opposite the direction of travel of the exiting steam. The reaction of the steam impacting the steps causes the outer ring to rotate in a direction opposite the direction of rotation of the rotor arm. Power take-off devices are provided to use the rotational movement of the rotor arm and the outer ring to generate electricity.

Abstract: Process of producing power comprising:

Abstract: An apparatus (100) for generation of mechanical and electrical power. Ramjet type thrust modules (102a, 102b) operate at supersonic speeds (preferably Mach 3 to 4) at the distal or tip ends (116a, 116b) of a low aerodynamic drag rotor (106). Rotor (106) is affixed at a hub means (114) to a power output means including central rotating upper (104a) and lower (104b) shaft portions. Rotor (106) is a structural member which transmits the thrust generated by the thrust modules (102a, 102b) to the shaft portions (104a, 104b). The ramjet thrust modules (102a, 102b) capture and compress a supplied free air stream, which is mixed with and oxidizes a convenient liquid or gaseous fuel such as natural gas from fuel supply means (103). Combustion gases expand to create thrust to rotate the thrust modules (102a, 102b), which are constrained by the rotor (106), to rotates about the axis defined by the shaft (104a, 104b) at supersonic thrust module velocities, producing shaft energy.

Abstract: A ramjet engine power generator. Supersonic ramjets are provided at the distal ends of a low aerodynamic drag rotor. The rotor is affixed at a central hub to a shaft, and rotates about an axis defined by the shaft. The rotor acts as a structural member which transmits to the shaft the thrust generated by the ramjets. In the preferred embodiment, a partially shrouded ramjet inlet captures and compresses an impinging inlet air stream by utilizing inlet structures and an adjacent housing sidewall. The compressed air inlet stream provides oxygen for mixing with a fuel, such as natural gas, other suitable hydrocarbons, or hydrogen, which is supplied to the novel, preferably replaceable ramjet combustion chamber(s). Fuel is oxidized in the combustion chamber(s) to produce expanding combustion gases. Such gases escape out through a partially shrouded nozzle, acting against three outlet structures and an adjacent housing sidewall, rotating the ramjet at supersonic velocities, and producing shaft energy.

Abstract: An apparatus (100) for generation of mechanical and electrical power. Ramjet type thrust modules (102a, 102b) operate at supersonic speeds (preferably Mach 3 to 4) at the distal or tip ends (116a, 116b) of a low aerodynamic drag rotor (106). Rotor (106) is affixed at a hub means (114) to a power output means including central rotating upper (104a) and lower (104b) shaft portions. Rotor (106) is a structural member which transmits the thrust generated by the thrust modules (102a, 102b) to the shaft portions (104a, 104b). The ramjet thrust modules (102a, 102b) capture and compress a supplied free air stream, which is mixed with and oxidizes a convenient liquid or gaseous fuel such as natural gas from fuel supply means (103). Combustion gases expand to create thrust to rotate the thrust modules (102a, 102b), which are constrained by the rotor (106), to rotates about the axis defined by the shaft (104a, 104b) at supersonic thrust module velocities, producing shaft energy.

Abstract: A ramjet engine power generator. Supersonic ramjets are provided at the distal ends of a low aerodynamic drag rotor. The rotor is affixed at a central hub to a shaft, and rotates about an axis defined by the shaft. The rotor acts as a structural member which transmits to the shaft the thrust generated by the ramjets. In the preferred embodiment, a partially shrouded ramjet inlet captures and compresses an impinging inlet air stream by utilizing inlet structures and an adjacent housing sidewall. The compressed air inlet stream provides oxygen for mixing with a fuel, such as natural gas, other suitable hydrocarbons, or hydrogen, which is supplied to the novel, preferably replaceable ramjet combustion chamber(s). Fuel is oxidized in the combustion chamber(s) to produce expanding combustion gases. Such gases escape out through a partially shrouded nozzle, acting against three outlet structures and an adjacent housing sidewall, rotating the ramjet at supersonic velocities, and producing shaft energy.