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 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: A pulsejet system and method requires no pulsejet internal moving parts. Each pulsejet includes a combustion chamber having an upstream inlet port joined to an inlet diffuser, boundary layer air ports enveloping the combustion chamber, and a downstream exit port joined to a discharge nozzle. Each pulsejet discharges into an ejector to increase net thrust. Each ejector includes an augmentor cell having side walls and perforated end plates. The perforated end plate between each pair of pulsejets is shared to permit the discharge thrust to equalize across the pulsejet group. Air and fuel mix in the combustion chamber and are detonated by a reflected back-pressure wave. Detonation/deflagration reverse pressure waves compressing boundary layer air flow act as a pneumatic throat to temporarily choke off inlet fresh air at the upstream inlet port. The pneumatic throat replaces the conventional mechanical valve used for this purpose.

Abstract: A shock wave reflector includes a number of reflective units positioned along a longitudinal direction and separated by a gap G. Each reflective unit has a length L. The length L and the gap G are governed by a relationship L+G??. The variable ? characterizes a cell size for a detonation mixture. A detonation chamber includes a receiving end, a discharge end, and a wall extending along a longitudinal direction between the receiving and discharge ends. The detonation chamber further includes a number of reflective units formed in the wall and positioned along the longitudinal direction. The reflective units are separated by a gap G, and each reflective unit has a length L.

Abstract: An engine includes at least one pulse detonation chamber configured to receive and detonate a fuel and an oxidizer. The pulse detonation chamber has an outlet end and includes a porous liner adapted to fit within an inner surface of the pulse detonation chamber within a vicinity of the outlet end. The engine also includes a casing housing the pulse detonation chamber.

Abstract: A method for operating a pulse detonation system. The method includes providing a pulse detonation chamber including a plurality of detonation tubes extending therein, and detonating a mixture of fuel and air within each detonation tube such that at least a first tube is detonated at a different time than at least a second detonation tube.

Abstract: A pulse combustion device has a number of combustors with upstream bodies and downstream nozzles. Coupling conduits provide communication between the combustors. For each given combustor this includes a first communication between a first location upstream of the nozzle thereof and a first location along the nozzle of another. There is second communication between a second location upstream of the nozzle and a second communication between a second location upstream of the nozzle of a second other combustor and a second nozzle location along the nozzle of the given combustor.

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 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 circumferentially spaced detonation chambers is disposed therein. The pulse detonation system further includes a shaft rotatably connected to the cylindrical member and a stator configured in spaced arrangement around the forward surface, the aft surface, and the outer circumferential surface of the cylindrical member and a portion of the shaft. The stator has at least one group of ports formed therein which sequentially align with the detonation chambers as the cylindrical member rotates. In this way, detonation cycles are performed in the detonation chambers of each detonation stage so that reaction forces induced by the detonation cycles create a torque which causes the cylindrical member to rotate.

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.

Abstract: A shaped charge engine includes multiple blast forming chambers, each chamber having a primary convergence zone that is variably shape to alter the shape of the exhaust gas emanating from each chamber. Thereafter, each chamber's variably shaped exhaust is merged at a secondary convergence zone into a shape further modified to alter the thrust characteristics of the exiting exhaust gases from the shaped charged engine.

Abstract: A method for operating a pulse detonation system. The method includes providing a pulse detonation chamber including a plurality of detonation tubes extending therein, and detonating a mixture of fuel and air within each detonation tube such that at least a first tube is detonated at a different time than at least a second detonation tube.

Abstract: This invention is a fuel injection control system for a turbine engine. The invention uses at least one fuel injector, having means for injecting fuel in pulses to the combustion chamber of a turbine engine, and an electronic control unit to receive and interpret input sensor signals from selected operating functions of the engine and to generate and direct fuel injection signals to modify the pulse duration and/or frequency of fuel injection in response to a deviation from a selected operating function, such as the desired operating speed, caused by variable operating loads encountered by the turbine engine. This configuration provides significantly greater fuel efficiency, better operational control and response time, and a lighter weight than is currently available in turbine engines. The invention may be used in many applications such as commercial, private, experimental and military aviation, power plant turbines, and other industrial, military and mining applications.

Abstract: A shaped charge engine includes an annular blast-forming chamber formed by joining inner and outer housings. A central through hole in the inner housing allows exhaust gases to exit. The outer housing comprises a generally round disk with an inner conical concave depression and through holes for the insertion of fuel and ignition. The blast chamber is preferably taper-conical in shape, wider at the base, and gradually decreasing in cross-sectional area as it rises to the apex. This construction forms a circular pinch point or throat toward the apex that produces a primary or first stage compression area. A secondary compression zone is created at the apex of the outer housing, just beyond the throat, producing hypersonic gases as generally opposing exhaust streams collide and are forced to exit the through hole in the inner housing. The collided streams propel a turbine rotor to turn a shaft.

Abstract: A shock wave reflector includes a number of reflective units positioned along a longitudinal direction and separated by a gap G. Each reflective unit has a length L. The length L and the gap G are governed by a relationship L+G≧&lgr;. The variable &lgr; characterizes a cell size for a detonation mixture. A detonation chamber includes a receiving end, a discharge end, and a wall extending along a longitudinal direction between the receiving and discharge ends. The detonation chamber further includes a number of reflective units formed in the wall and positioned along the longitudinal direction. The reflective units are separated by a gap G, and each reflective unit has a length L.

Abstract: This invention relates to air breathing engines, such as ramjets, scramjets and internal combustion, and more particularly to an active combustion control device for a combustor. In more particularity, the present invention relates to a method and apparatus that applies active combustion control technology to advanced propulsion devices and closed-loop fuel injection at sub-harmonic frequencies of the instability frequency of the combustor. The problem of limited actuator frequency response is addressed by injecting fuel pulses at sub-harmonic frequencies of the instability. The fuel may be liquid, solid or gas. To achieve this desired result, a closed loop controller is designed to determine sub-harmonic frequencies using a divider to divide the instability frequency of a combustor, yielding a fraction of the harmonic frequency.

Abstract: A high frequency pulsed fuel injector is disclosed. The fuel injector incorporates a resonance tube in outlet fluid communication with a fuel nozzle. During operation the resonance tube provides a pulsating output which is directed into the fuel nozzle. The pulsating output of the resonance tube perturbs the flow of fuel in the fuel nozzle, effectively breaking it up into discrete slugs or chunks for subsequent combustion in a combustion chamber. The combustion process is greatly enhanced by this breakup of the fuel jet, improving combustion efficiency as well as reducing undesirable emissions.

Abstract: The cryogenic propulsion module comprises a main cryogenic thruster (10), two attitude-controlling secondary thrusters (21, 22), tanks (31, 32, 33, 34) for feeding cryogenic propellants, a device for intermittently pressurizing the tanks (31, 32, 33, 34), and a device for initiating firing of the main cryogenic thruster (10) in intermittent manner while the tanks (31, 32, 33, 34) are intermittently pressurized. The device for intermittently pressurizing a tank (31, 32, 33, 34) comprises a heat exchange circuit associated with a heat accumulator (61, 62) and a device (71, 72) for putting a predetermined quantity of a propellant into circulation in the heat exchanger circuit. The module also comprises a device for heating the heat accumulator (61, 62) in the periods between two consecutive firings.

Abstract: The present disclosure relates to a flow control system, comprising a controller, an ignition device whose activation is controlled by the controller, a combustion-driven jet actuator, and a fuel source in fluid communication with the jet actuator that supplies fuel to the jet actuator. Typically, the jet actuator comprises a combustion chamber, an orifice that serves as an outlet for combustion products emitted from the combustion chamber, and at least one inlet through which fuel is supplied to the chamber for combustion. In use, the combustion-based jet actuator can emit jets of fluid at predetermined frequencies.

Abstract: Flow control in pulse detonation engines is accomplished using magnetohydrodynamic principles. The pulse detonation engine includes a tube having an open forward end and an open aft end and a fuel-air inlet formed in the tube at the forward end. An igniter is disposed in the tube at a location intermediate the forward end and the aft end. A magnetohydrodynamic flow control system is located between the igniter and the fuel-air inlet for controlling detonation in the tube forward of the igniter. The magnetohydrodynamic flow control system utilizes magnetic and electric fields forward of the igniter to dissipate or at least reduce the ignition potential of the forward traveling detonation flame front.

Abstract: A pulsating combustor has a plurality of annular plate elements (12), which are stacked in spaced vertical alignment so as to define a central space (14). There is a plurality of slot-like passages (18), one such passage between each adjacent pair of elements. There is at least one combustion chamber (21) in communication with at least one slot-like passage. Fuel and combustion air are fed into the combustion chambers. There is a spark plug for igniting a fuel-air mixture in the combustion chamber. Preferably there is a first housing (24) defining the combustion chamber and another housing defining a collection chamber for combustion gases emerging from the passages.

Abstract: A rotary valve for pulse detonation engines includes a rotor rotatively mounted in the forward end of the pulse detonation tube and a plurality of transfer plenums for receiving fuel and air arranged around the rotor and partially disposed over the forward end of the tube. The rotor has a plurality of internal flow passages formed therein which periodically align with a plurality of inlet ports formed near the forward end of the tube as the rotor rotates. Each one of the transfer plenums is aligned with a corresponding one of the inlet ports so that the flow passages will establish fluid communication between the tube and the transfer plenums when aligned with the inlet ports. Additional features include axial injection of the fuel-air mixture into the pulse detonation tube, pre-compression of the inlet flow and a drive system located outside of the primary gas path.

Abstract: A shaped charge engine includes an annular blast-forming chamber formed by joining inner and outer housings. A central through hole in the inner housing allows exhaust gases to exit. The outer housing comprises a generally round disk with an inner conical concave depression and through holes for the insertion of fuel and ignition. The blast chamber is preferably taper-conical in shape, wider at the base, and gradually decreasing in cross-sectional area as it rises to the apex. This construction forms a circular pinch point or throat toward the apex that produces a primary or first stage compression area. A secondary compression zone is created at the apex of the outer housing, just beyond the throat, producing hypersonic gases as generally opposing exhaust streams collide and are forced to exit the through hole in the inner housing. The shaped charge engine may be used in a variety of applications, including as a pulsed direct propulsion device, as a turbine driver, or in a wide array of tools and appliances.

Abstract: Provided is a combustion chamber for producing a pressurized gas containing:

Abstract: A pulsating combustion unit includes an elongate combustion chamber having an interior cross-section, an intake end and an exhaust end and sides which are parallel from the intake end to the exhaust end. There is an intake portion adjacent to the intake end and an exhaust portion adjacent to the exhaust end. Preferably the combustion chamber has a generally equal cross-section between the intake end and the exhaust end. The combustion chamber may have an intake bulkhead adjacent to the intake end. The intake portion includes a slot in the bulkhead. The intake portion may also include a pair of spaced-apart plates extending outwardly from the slots in the bulkhead. Preferably these plates are spaced-apart closer together than the combustion chamber. The exhaust portion may include an exhaust bulkhead having an opening therein.

Abstract: An air compressor device and method for producing compressed air. The device comprises a rotatable cylinder assembly having a drive shaft extending along a central axis and three equally sized combustion chambers extending parallel to the center axis. The drive shaft is connected to a turbine or other drive means which provides rotational movement to the drive shaft and cylinder assembly. Two circular end plates are concentrically positioned with the central axis on each end of the cylinder assembly. The end plates are stationary with respect to the rotatable cylinder assembly and comprise an intake plate and an outlet plate. Openings are provided on the end plates to allow for communication of a gas into and out of the combustion chambers at designated times during operation of the compressor. A fuel injector is positioned upon the intake plate along with an ignition means. The device operates on a modified Schmidt-type pulsejet cycle. Fresh air is received in each of the chambers and compressed.