Abstract: According to one embodiment of the invention, a system for altering a fluid flow includes a nozzle having a fluid flow and including a converging portion, a diverging portion downstream of the converging portion, and a throat coupling the converging portion to the diverging portion, at least one port located in a wall of the nozzle and angled with respect to the fluid flow, and at least one pulse detonation device operable to inject a plurality of detonation waves in a pulsed manner through the port and into the fluid flow. The pulsed detonation waves operate to alter the fluid flow.

Abstract: According to one embodiment of the invention, a system for altering a fluid flow includes a nozzle having a fluid flow and including a converging portion, a diverging portion downstream of the converging portion, and a throat coupling the converging portion to the diverging portion, at least one port located in a wall of the nozzle and angled with respect to the fluid flow, and at least one pulse detonation device operable to inject a plurality of detonation waves in a pulsed manner through the port and into the fluid flow. The pulsed detonation waves operate to alter the fluid flow.

Abstract: A fuel containing methylacetylene-propadiene, commonly referred to as MAPP gas, produces thrust in a flight vehicle having a pulse detonation engine. The MAPP gas fuel of this invention may be used alone or combined with other conventional fuels such as hydrogen, JP-4, JP-5, JP-10, kerosene or any other suitable hydrocarbon fuel. Such hydrocarbon containing fuel includes, but is not limited to, acetylene, methane, ethylene, propane, butane or liquified petroleum gas. MAPP gas fuel is mixed with an oxidant containing oxygen or air and ignited. The detonation wave created produces thrust for the flight vehicle. A method of powering a flight vehicle having a pulse detonation engine with MAPP gas fuel is also disclosed.

Abstract: A fuel containing methylacetylene-propadiene, commonly referred to as MAPP gas, produces thrust in a flight vehicle having a pulse detonation engine. The MAPP gas fuel of this invention may be used alone or combined with other conventional fuels such as hydrogen, JP-4, JP-5, JP-10, kerosene or any other suitable hydrocarbon fuel. Such hydrocarbon containing fuel includes, but is not limited to, acetylene, methane, ethylene, propane, butane or liquified petroleum gas. MAPP gas fuel is mixed with an oxidant containing oxygen or air and ignited. The detonation wave created produces thrust for the flight vehicle. A method of powering a flight vehicle having a pulse detonation engine with MAPP gas fuel is also disclosed.

Abstract: A combined cycle pulse combustion/gas turbine engine has a gas turbine engine used in conjunction with a plurality of pulse combustion engines. In one embodiment, the gas turbine engine includes a housing, a bypass fan, a central engine core, and a diffuser section. The diffuser section is used to route bypass air from the bypass fan around the central engine core and out of the housing. The pulse engines are mounted in the diffuser section and receive bypass air from the bypass fan. In a first alternate embodiment, bypass air is routed from the diffuser section through a duct to the pulse engine. A valve is disposed between the bypass fan and the pulse engines for selectively allowing bypass air from the bypass fan to enter the duct. In a second alternate embodiment, a fan mounts to each inlet port. The gas turbine engine has a drive shaft that drives the fan. A clutch selectively disengages the fans.

Abstract: A pulse detonation cluster includes a cluster housing and a plurality of pulse detonation engines mounted within the housing. Each pulse detonation engine has an inner tubular housing rigidly and concentrically mounted within a cylindrical bore of an outer tubular housing. The inner housing has a plurality of inner housing ports, and the outer housing has a plurality of outer housing ports. A detonation chamber is formed in the annulus between the inner housing and the outer housing. An outer valve sleeve is rotatably mounted to the outer housing for selectively allowing air to enter the detonation chamber through the outer housing ports. A fuel delivery member is aligned with each inner housing port to deliver fuel to the detonation chamber through the inner housing ports. An inner sleeve is mounted to the inner housing to protect the fuel delivery members during detonation. The air and fuel mixture is detonated by several igniters located in the detonation chamber.

Abstract: A pulse detonation engine has an inner tubular housing rigidly and concentrically mounted within a cylindrical bore of an outer tubular housing. The inner housing has a plurality of inner housing ports, and the outer housing has a plurality of outer housing ports. A detonation chamber is formed in the annulus between the inner housing and the outer housing. In one embodiment, an outer valve sleeve is rotatably mounted to the outer housing for selectively allowing air to enter the detonation chamber through the outer housing ports. A movable, inner protective sleeve is mounted to the inner housing for protecting a plurality of fuel injectors that supply liquid fuel to the detonation chamber through the inner housing ports. The air and liquid fuel mixture is detonated by several igniters located in the detonation chamber. In a second embodiment, an inner valve sleeve is rotatably mounted to the inner housing for selectively allowing air to enter the detonation chamber through the inner housing ports.

Abstract: A pulse detonation engine has a pulse ignition system, a plurality of detonation chambers (15), an oxygen source (33), and a fuel source (35). The oxygen source and the fuel source supply oxygen and fuel, respectively, to both the pulse ignition system and to the detonation chambers. The pulse ignition system creates detonation waves by igniting a first series of fuel mixtures inside a plurality of igniter tubes (39) equal to the number of detonation chambers (15). One detonation wave is delivered by each igniter tube into each detonation chamber for igniting a second series of fuel mixtures inside the detonation chambers. The detonation waves increase in magnitude as they travel through the detonation chambers before exiting the rearward ends of the detonation chambers. After detonation, the detonation engine is purged of residual gases by a ventilation system (81) and the process is repeated sequentially as described.

Abstract: A coal gasification system has a pulse detonation device. The pulse detonation device is employed to discharge hot exhaust pulses into the coal gasifier. Also, a pulse detonation device discharges reverse flow pulses into a ceramic candle filter system to dislodge particulate build up on the candles. The pulse detonation device utilizes a rotatable core feed cylinder. The core feed cylinder is carried within an inner side wall of the stationary annular detonation chamber. The core feed cylinder has ports in the side wall that will register with ports in the inner side wall of the annular detonation chamber at least once each revolution. Fuel is introduced through valves mounted to the outer side wall of the annular detonation chamber.

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 pivotal housing member has an end pivotally coupled to an end of a base housing member for movement between a retracted or folded position and an extended position. The pivotal housing member has a pulsed deflagration or detonation device located therein for producing pulsed deflagration or detonation pressure waves for cleaning purposes. When the pivotal member is in its folded position, the two housing members may be moved through the opening formed through the wall of a boiler, etc. for cleaning the interior surface of the wall with the pulsed pressure waves. In order to increase the wall area cleaned from a given wall opening, the two housing members may be rotated about an axis of the base housing member and the pivotal housing member pivoted to different extended positions from its folded position.

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.