Abstract: A nozzle for a detonative combustion engine, the engine having multiple combustor tubes, comprises a common plenum communicating with the combustor tubes. The common plenum combines separate exhaust streams from the combustor tubes into a compound subsonic exhaust stream. A compound flow throat communicates with the common plenum. The compound flow throat converts the compound subsonic exhaust stream into a compound sonic exhaust stream. The common plenum and compound flow throat cooperate to maintain a predetermined upstream combustor pressure regardless of down stream pressure exiting the expansion section. Optionally, an interface section is inserted between the plenum and the engine such that it communicates with the common plenum section and with outlets of the combustor tubes. The interface section is compartmentalized into flow passages with each flow passage having a cross-sectional area that increases from that of a particular nozzle intake port connected to a conductor tube exit.

Abstract: A liquid propellant rocket engine comprising a chamber body connected to a converging/diverging thrust nozzle and to at least one lightly pressurized propellant feed duct, said body including a body bore in which an injector-forming piston can move longitudinally between a rest first position and an operating second position, the piston comprising a piston head and a piston rod, and subdividing the chamber body bore into a combustion chamber in front of the piston, and at least one injection chamber surrounding the piston rod, the chamber body further including a flow section that is closed in said rest position to prevent any propellant being fed from the injection chamber(s) and that is opened when the piston moves from said rest position to said operating position in order to allow the injection chamber(s) to be filled via said flow section directly from the feed duct(s), the propellant(s) being injected into the combustion chamber via injection channels formed between the combustion chamber and the inject

Abstract: A pulse detonation rocket engine, having at least two detonation chambers. The rocket propelled vehicle includes at least one fuel delivery system in fluid communication with each of the at least two detonation chambers, and at least one oxidant delivery system in fluid communication with the detonation chambers, along with fast-acting valves to inject fuel and oxidant controlledly into the chambers. An ignitor in each of the detonation chambers intermittently initiates detonation of a fuel and oxidant mixture in the chamber, in a controlled cycle, to provide motive force. Also provided is a combined cycle engine, able to operate in air breathing mode, oxidant augmented mode, and as a rocket engine. The combined cycle engine includes at least one detonation chamber, and may include a plurality of such chambers. The invention further provides methods of intermittently detonating sequentially created fuel and oxygen mixtures in these engines, and methods of using these engines.

Abstract: A liquid propellant rocket engine comprising a chamber body connected to a converging/diverging thrust nozzle and to at least one lightly pressurized propellant feed duct, said body including a body bore in which an injector-forming piston can move longitudinally between a rest first position and an operating second position, the piston comprising a piston head and a piston rod, and subdividing the chamber body bore into a combustion chamber in front of the piston, and at least one injection chamber surrounding the piston rod, the chamber body further including a flow section that is closed in said rest position to prevent any propellant being fed from the injection chamber(s) and that is opened when the piston moves from said rest position to said operating position in order to allow the injection chamber(s) to be filled via said flow section directly from the feed duct(s), the propellant(s) being injected into the combustion chamber via injection channels formed between the combustion chamber and the inject

Abstract: A rotary engine is disclosed having a rotor and rotor housing for mounting therewithin said rotor for its rotation within the inner wall of the rotor housing, the gap between the rotor and the inner wall of the rotor housing defining the engine room. A plurality of telescopic sealing blades which can elongate and shorten with respect to the rotor are attached, respectively at positions substantially equally spaced on the circumference of said rotor so that the sealing blades elastically contact to the inner wall of the rotor housing, the sealing blades sliding along the inner wall of the rotor housing during the rotation of the rotor and separating the engine room in an airtight manner so that the suction of fuel gas, its succeeding compression and the exhaust of burnt gas are carried out.

Abstract: A pulse detonator particularly for an aircraft power supply has a tubular housing. A valve sleeve rotates within the bore of the housing. The valve sleeve and housing have ports which align with each other at least once per revolution. A manifold is mounted to the exterior of the housing. The manifold has outer valves which open to admit fuel and oxygen simultaneously with the alignment of the valve sleeve ports with the housing ports. The fuel and oxygen flow into a detonation chamber where they mix. Igniters ignite the mixture to create a detonation wave which passes out the downstream end.

Abstract: A pulse detonation apparatus utilizes a rotatable core feed cylinder. The core feed cylinder is carried within a inner sidewall of a stationary annular detonation chamber. The core feed cylinder has ports in the sidewall that will register with ports in the inner sidewall of the annular detonation chamber at least once each revolution. A fuel valve means mounted to the outer sidewall of the annular detonation chamber supplies pulses of gaseous fuel. The oxygen content at the forward end of the detonation chamber is richer than toward the rearward end. The fuel is ignited to create a detonation wave. A purge gas flowing through the core feed cylinder enters the detonation cavity after the detonation wave has discharge for purging.

Abstract: A pulse detonation device is used to create high temperature high pressure pulses, such as for generating thrust for an aircraft or rocket. The device has a rotating cylinder located within a sleeve. A jacket is spaced outward from the sleeve. The seal and the sleeve are rotatable relative to each other. Each has ports which align with each other to communicate the annular passage with the annulus between the jacket and the sleeve. The jacket has at least one outer port. An outer valve in the exterior of the jacket opens and closes the outer port. A first portion of a fuel mixture, such as oxygen, is supplied to the inner passage within the cylinder, to flow into the annulus through the inner ports. The second ingredient of the fuel mixture, such as fuel, is supplied through the outer valves and outer ports to the annulus. An igniter in the annulus creates a detonation wave.

Abstract: A pulse detonation apparatus utilizes an inner housing which rotates relative to an outer housing. The inner housing has spherical inner seal surfaces that rotate with it. The outer housing has mating spherical seal surfaces that rotationally receive the inner seal surfaces. Ports extend through the inner seal surface and the outer seal surface. These ports register at least once per revolution. An inlet supplies a fuel mixture to the interior of the inner housing and each time the inner and outer housing ports align, the fuel mixture is transmitted into an annular detonation chamber where an igniter ignites the mixture to create a detonation wave. Circular seals surround the outer housing port to provide sealing against the high pressure, high temperature detonations. Purge air is admitted into the detonation chamber, a new fuel mixture is delivered to the detonation chamber, and the cycle is repeated.

Abstract: A pulse detonation engine has a detonation chamber with a sidewall. At least two fuel ports are located in the sidewall, spaced longitudinally apart from each other. An oxygen fuel mixture is introduced into the forward port and detonated. This creates a detonation wave which propagates with an air fuel mixture introduced into the rearward fuel port. After the detonation, purge air passes through the chamber before the next detonation. A rotating sleeve valve mounted around the detonation opens and closes the fuel ports as well the purge ports.

Abstract: An air-breathing pulsed jet engine for aircraft propulsion which employs a piston compressor rather than much more expensive axial or centrifugal compressors and turbines employed by conventional turbojet engines. The engine is similar to the common two-cycle gasoline engine, except its cylinder head comprises a jet nozzle with an internal pressure-activated nozzle-blocking valve. A spring keeps this valve closed during the engine's compression stroke when the piston, connected to a crankshaft and flywheels by a connecting rod, is forced by the moment-of-inertia of the flywheels toward the cylinder head. When ignition and combustion of the compressed air and fuel occurs slightly before the piston reaches the top of its stroke, the much greater pressures within the engine's combustion chamber force the valve to pivot open. This allows a jet of combustion gases to be released through the jet nozzle into the atmosphere.

Abstract: A pulse detonation engine is provided with several detonation combustors selectively coupled to an air inlet and fuel source by a rotary valve. The rotary valve isolates the steady operation of the air inlet and fuel system from the unsteady nature of the detonation process, and allows the fueling of some of the detonation chambers while detonation occurs in other detonation chambers. The fuel system may use a solid fueled gas generator.

Abstract: To promote fuel and air mixing combustor of a scramjet engine, fuel is injected as a succession of pulses into the airstream flowing through the combustor. By controlling the duty cycle and flow rate of the fuel pulses, increased fuel penetration and mixing efficiency are obtained with an overall fuel flow schedule comparable to steady state fuel injection. With sequential pulsed operation of plural, variously located fuel injectors in phased relation, the combustor remains in a transient state to enhance mixing and to spread out the combustor heat load.

Abstract: A pulse thruster delivering electrically charged fuel attracted to a plate having an opposite charge where such fuel is ignited, causing an impulse force which process is repeated.

Abstract: In a method and apparatus for controlling total ignition delay time in a pulse combustor, and thus controlling the mixing characteristics of the combustion reactants and the combustion products in the combustor, the total ignition delay time is controlled by adjusting the inlet geometry of the inlet to the combustion chamber. The inlet geometry may be fixed or variable for controlling the mixing characteristics. A feedback loop may be employed to sense actual combustion characteristics, and, in response to the sensed combustion characteristics, the inlet geometry may be varied to obtain the total ignition delay time necessary to achieve the desired combustion characteristics. Various embodiments relate to the varying of the mass flow rate of reactants while holding the radius/velocity ratio constant.

Abstract: A turbocharged, compounded cycle ducted fan engine system includes a conventional internal combustion engine drivingly connected to a fan enclosed in a duct. The fan provides propulsive thrust by accelerating air through the duct and out an exhaust nozzle. A turbocharger is disposed in the duct and receives a portion of the air compressed by the fan. The turbocharger compressor further pressurizes the air and directs it to the internal combustion engine where it is burned and exits as exhaust gas to drive the turbine. A power turbine also driven by exhaust gas is also drivingly connected through the engine to the fan to provide additional power. The size and weight of the turbocharger are reduced since the compressor's work is partially achieved by the compression effect of the fan. The total propulsive thrust includes the fan generated thrust which bypasses the turbocharger and the thrust of exhaust gases exiting the turbine.

Abstract: Combustion supporting air in the resonator tube of a pulse jet engine is cyclically compressed by combustion and discharged through a decelerating passage of a diffuser in a tail section of the engine to internally pressurize an afterbody preceding atmospheric dishcarge of the combustion products through nozzle passages, followed by primary refill with air from the pressurized afterbody and secondary refill by reentry of external air. The nozzle passages are formed in angularly spaced, rearwardly diverging vane formations of the tail section projecting from a protective casing directing ram air intake into orifice openings formed in a rear end portion of the diffuser to regulate afterbody pressurization under control of ram pressure created by forward propulsion of the engine.

Abstract: A thermally driven gas resonance device includes a resonance tube (3) which expands in cross-section along its length from one end to the other, a heat source (2) located at the one end of the resonance tube, and an igniter (14) to trigger oscillations in a gas in the tube. The heat source (2) is preferably a pulsed heat source having a repetition frequency corresponding to a resonant frequency of the gas tube (3). The mechanical energy produced in the oscillating gas may be used to operate a pressure swing gas separator by including a bed (16) of molecular sieve material in the other end of the tube (3). Alternatively, the mechanical energy may be used to drive a heat pump (19). In this case a heat sink (21) is located at the other end of the tube (3), a regenerator (20) is also located adjacent the other end, and ports (8) on the side of the regenerator (20) towards the heat source (2) effect heat exchange between the gas in the resonance tube (3) and a source of low grade heat.

Abstract: A pulse combustor having a combined mixing and ignition chamber in communication with a fuel inlet tube and an air inlet tube. The fuel inlet tube and air inlet tube inject fuel and air, respectively, forming a fuel/air mixture in the mixing and ignition chamber. An ignition source for igniting the fuel/air mixture is located within the mixing and ignition chamber. A main combusiton chamber is sealably secured to the main combustion chamber wall and in comunication with the mixing and ignition chamber. The main combustion chamber first splits into a plurality of downstream combustion chamber branches, each of which further split into a plurality of exhaust tubes. The combustion chamber branches of the main combustion chamber have a slot between the combustion chamber branches. At least one reinforcing strut is secured between the combustion chamber branches within the slot between the combustion chamber branches of the main combustion chamber.

Abstract: A pulse combustion burner is disclosed having a combustion chamber and a passageway for delivering a combustible gaseous mixture of air and fuel gas to the chamber. A self-feeding flapper valve and air and fuel gas flow restrictor members are positioned in close proximity along the passageway for metering the air and fuel gas flows through the passageway and combining the flows and enhancing quality and rate of mixing of the air and fuel gas.

Abstract: The invention consists of an engine that converts hydrothermomechanical energy into thrust. There is but a single internal moving part . . . the piston. When in operation, the piston preforms two distinct functions: (1) as a valve allowing intermittent injection of a fuel/air mixture for combustion and (2) as a hydraulic fluid pump. Resultant chemical reactions in the combustion chamber produces intermittent high velocity gases at the exit nozzle of the said engine, which provides sufficient thrust for subsonic and sonic aircraft operations. The intermittent thermal activity and specific manner of braking action of the hydraulic fluid, causes the said piston to function as a hydraulic fluid pump. Thereby providing mechanical energy to power cranes, pumps, compressors, generators, etc., etc., and, or provide impetus for aquatic craft and ground vehicles.

Abstract: A turbocharged, compounded cycle ducted fan engine system includes a conventional internal combustion engine drivingly connected to a fan enclosed in a duct. The fan provides propulsive thrust by accelerating air through the duct and out an exhaust nozzle. A turbocharger is disposed in the duct and out an exhaust nozzle. A turbocharger is disposed in the duct and receives a portion of the air compressed by the fan. The turbocharger compressor further pressurizes the air and directs it to the internal combustion engine where it is burned and exits as exhaust gas to drive the turbine. A power turbine also driven by exhaust gas is also drivingly connected through the engine to the fan to provide additional power. The size and weight of the turbocharger are reduced since the compressor's work is partially achieved by the compression effect of the fan. The total propulsive thrust includes the fan generated thrust which bypasses the turbocharger and the thrust of exhaust gases exiting the turbine.

Abstract: An improved arrangement for a pulse jet engine assembly wherein pulsations of the engine are utilized to operate a motive source for a fuel pump which pumps fuel from a fuel supply source to the engine, the entire pulse jet engine assembly being internally self-sufficient after initial starting operation.

Abstract: A compact, valve assembly (10) is provided having multiple chambers. A forward chamber (14) retains dual T-shaped blades (36) having shaped orifices (38) for controllably metering at least two fluids passing through the valve assembly. The valve assembly is also provided with a servo-valve assembly (70) and a piston indicator (62) assembly in cooperative association with the valve assembly.

Abstract: A compact pulse-rocket engine assembly comprising an elongated substantially cylindrical housing containing an axially extending substantially cylindrical combustion chamber which terminates at one end in a nozzle means. Within the housing at the opposite end of the combustion chamber are a pair of charging chambers. Intermediate the charging chambers and the combustion chambers are a pair of valve means which are parallel and linked together for ensuring that the valves operate in unison.

Abstract: A compact pulse-rocket engine assembly comprising an elongated housing containing an axially extending substantially cylindrical combustion chamber terminating in a nozzle means at one end. An opposite end of the housing contains a pair of angularly disposed charging chambers. Intermediate the charging chambers and the combustion chamber are a pair of angularly disposed piston valve means. The arrangement of the valve means provides for the injection of propellants into the combustion chamber for impingement at the same point throughout the operation of the piston valve means.

Abstract: An improved valveless pulse jet combustor having an air inlet pipe connected to a combustion chamber having ignition means and fuel supply means is disclosed. The combustion chamber is further connected to an exhaust pipe. The combustion chamber is connected to the air inlet pipe via tapered fitting means adapted to receive relief port means, fuel injection means and compressed air inlet means directed towards the center of the chamber. Adjustable orifice flanges are positioned between the combustion chamber and an extension of the exhaust pipe. The inlet pipe and the tapered means have diverging interior diameters, the combustion chamber a converging interior diameter and the extension and exhaust pipe have diverging interior diameters such that in operation, backward thrust is directed through the release port means thereby reducing back flow through the inlet pipe.

Abstract: The combination of a pulsed rocket engine 12 and a sleeve valve 10 coupled to the engine output and receiving in its internal chamber 16 the gas generated by the engine 12. The sleeve valve 10 has a movable sleeve 24 with ports 26, 28 therethrough surrounding the wall 18 of the chamber 16, the wall 18 having ports 38, 40 which axially align with the sleeve ports 26, 28 in the valve's open position to allow rapid discharge of the contents of the chamber 16. The sleeve is ordinarily biased to a closed, or non-aligned, position for the ports by a spring 32. When the gas pressure in the chamber 16 reaches a predetermined amount, a pressure sensor 54 commands a gas source to send pressurized gas into the valve 10 to force the sleeve 24 into its open position against the bias of the spring 32, thereby aligning the ports 26, 28 and 38, 40 and allowing rapid discharge of the gas from the sleeve-valve chamber 16.

Abstract: A propellant injector for a liquid rocket engine has an injection cylinder and moving piston in the cylinder. The cylinder on one side of the piston opens into the combustion chamber of the engine. The other side of the piston has a coaxial tubular portion projecting therefrom. A pair of valve members have concentric sleeves slidably mounted respectively on the inside and outside surfaces of the tubular portion of the piston. The outer ends of the concentric sleeves and tubular portion extend through an end wall of the injection cylinder. The valves open and close passages extending through the piston by relative axial movement of the sleeves and the piston. Pneumatic actuator means, connected to the outer ends of the sleeves and tubular portion, moves the sleeves axially relative to the piston to open the valves and move the piston toward the end wall of the injection cylinder to force propellant through the passages into the combustion chamber.

Abstract: A resonant or pulsating combustion heating apparatus of the present invention provides a high thermal efficiency heater with low concentrations of carbon monoxide and nitrogen oxides in the exhaust gas. The pulsation heater is constructed to provide an afterburner or late-combustion reactor in the pulsation tube. Combustion in the combustion chamber is of a relatively rich fuel/air mixture in which no nitrogen oxides are produced. The afterburning in the pulsation tube is carried out in the presence of excess air providing late combustion to remove carbon monoxide (CO).

Abstract: The gas turbine engine includes a centrifugal fan having radial blades for receiving inlet air through inner entrance openings to spaces between adjacent blades. The air passes through outer exit openings from the spaces between the blades. Stationary inner and outer circumferential segments define closure members which successively eclipse the inner entrance and outer exit openings of the centrifugal fan blades when the fan rotates to position adjacent blades between the closure members. The closure members and space between the blades thus define closed combustion chambers. Fuel is injected and ignited so that continuous combustion takes place at constant volume, the exhaust gases escaping through the outer exit openings when rotation of the fan positions these openings beyond the outer closure members. This continuous combustion at constant volume provides for increased efficiency in the gas turbine engine over the Brayton cycle constant pressure type turbine engine.

Abstract: At least two gas combustion tubes disposed in an end-to-end relationship provide an elongate combustion chamber closed at both ends. A fuel mixture admitted alternatively into each closed end is ignited for generating positive pressure pulses traveling from one end of the chamber to the other. The combustion energy at one end compressed the fuel mixture from the other to permit ignition. A standing wave thus is formed having a pressure anti-node at each of the closed ends. The combustion chamber length is fixed relative to the frequency of the alternating ignitions to produce in the chamber a standing wave having an even number of quarter wave lengths with pressure anti-nodes and velocity nodes at its ends. The wave form thus has a pressure node and velocity anti-node at its mid-point. Combustion gases are discharged at this mid-point to a storage reservoir and, from the reservoir, to the propulsion turbine.

Abstract: An intermittent burning ramjet engine having a rough wall combustor with fuel supplied to a fuel injector upstream of the combustor. The fuel is cyclically ignited at a predetermined frequency. A resonator tuned to a frequency less than one-tenth of the combustor frequency is positioned between the combustor and the ramjet inlet.

Abstract: An air-breathing pulsed jet engine for aircraft propulsion which employs a piston compressor rather than much more expensive axial or centrifugal compressors and turbines employed by conventional turbojet engines. The engine is similar to the common two-cycle gasoline engine, except its cylinder head comprises a jet nozzle with an internal pressure-activated nozzle-blocking valve. A spring keeps this valve closed during the engine's compression stroke when the piston, connected to a crankshaft and flywheels by a connecting rod, is forced by the moment-of-inertia of the flywheels toward the cylinder head. When ignition and combustion of the compressed air and fuel occurs slightly before the piston reaches the top of its stroke, the much greater pressures within the engine's combustion chamber force the valve to pivot open. This allows a jet of combustion gases to be released through the jet nozzle into the atmosphere.