Class 60/207 - Utilizing plural reaction zones within a system

Subclass of Class 60 - Power plants
Definition: Process directed to utilizing a plurality of chemical reaction
No. of patents: 37
Last issue date: 12/26/2006

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Number	Title	Issue Date
7152408	Vehicle with a combustion engine and a fuel cell device A vehicle having a combustion engine, a fuel cell device having a fuel cell unit, a compressed air storage for supply of a compressed air, a supply conduit provided between the fuel cell unit of the fuel cell device and the compressed air storage, for supplying the ...	12/26/2006
7093442	Augmentor A turbine engine augmentor has a centerbody within a gas flowpath. A flameholder is positioned in the flowpath outboard of the centerbody. A burner within the centerbody has an outlet for expelling combustion products of a first pilot fuel. A pilot fuel conduit has ...	08/22/2006
7062901	Variable geometry nozzle with flexible side wall The disclosed device is directed toward a periodic combustion propulsion system. The periodic combustion propulsion system comprises at least one periodic combustion chamber configured to contain periodic combustion and at least one supersonic exhaust nozzle coupled...	06/20/2006
6973774	Hybrid propulsion system While commercial jet aircraft are capable of transporting large pay load economically, the same is not true for rockets. To solve this problem, a hybrid propulsion system is proposed for use in Horizontal Take-Off and Land (HOTOL) craft. The purpose is to maximized ...	12/13/2005
6968673	Cool gas generator and ultra-safe rocket engine A gas generator or rocket engine includes: a first storage tank configured to contain a high-pressure liquid propellant; a nozzle connected to the first storage tank; a heat source connected between the first storage tank and the nozzle and configured to add heat to...	11/29/2005
6964154	Axisymmetric, throttleable non-gimballed rocket engine A rocket engine assembly is provided for a vertically launched rocket vehicle. A rocket engine housing of the assembly includes two or more combustion chambers each including an outlet end defining a sonic throat area. A propellant supply for the combustion chambers...	11/15/2005
6948306	Apparatus and method of using supersonic combustion heater for hypersonic materials and propulsion testing A supersonic combustion apparatus and method of using the same including a side wall cavity having an enhanced mixing system with ground-based oxygen injection for hypersonic material and engine testing. ...	09/27/2005
6935109	Monoprolellant/hypergolic powered proportional actuator Systems and methods involving monopropellant and hypergolic powered proportional actuators that may be used in applications such as robotics. A blowdown tank delivers fuel to a reaction site, produce gaseous products. Those gaseous products are transported to a pres...	08/30/2005
6931832	Monopropellant combustion system An apparatus and method are provided for decomposition of a propellant. The propellant includes an ionic salt and an additional fuel. Means are provided for decomposing a major portion of the ionic salt. Means are provided for combusting the additional fuel and deco...	08/23/2005
6931833	Pulse combustion device 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 no...	08/23/2005
6918243	Bi-propellant injector with flame-holding zone igniter A bi-propellant injector (66) includes a first injector element (68) and a second injector element (70) injecting a first propellant (69) and a second propellant (71), respectively, into a combustion chamber (53). A flame-ho...	07/19/2005
6832471	Expander cycle rocket engine with staged combustion and heat exchange In a supersonic nozzle incorporating injectors and a combustion chamber as part of an expander cycle rocket engine, the oxidizer is injected in two streams. One of the streams, preferably a small fraction of the total, is injected into an upstream or preburner secti...	12/21/2004
6807804	Hybrid rocket motor having a precombustion chamber A hybrid rocket motor is provided with a precombustion chamber supplied with propellant from separate fuel and oxidizer sources. The propellant can be in the form of gas or liquid and injected substantially tangentially into the head end of the hybrid motor adjacent...	10/26/2004
6679049	Hybrid rocket motor having a precombustion chamber A hybrid rocket motor is provided with a precombustion chamber supplied with propellant from separate fuel and oxidizer sources. The propellant can be in the form of gas or liquid and injected substantially tangentially into the head end of the hybrid mot...	01/20/2004
6668541	Method and apparatus for spraying fuel within a gas turbine engine A fuel spraybar assembly for spraying fuel within a gas turbine engine. The spraybar assembly includes radial and lateral members that distribute fuel within the flowpath. In one embodiment two lateral members are located at the radially inward end of a r...	12/30/2003
6250072	Multi-ignition controllable solid-propellant gas generator Batch-mode and continuous-mode decomposition of nitrous oxide is used to provide multiple ignitions of a solid-propellant gas generator and subsequently control its output gas temperature and flow rate, respectively. To reignite the solid-propellant gas g...	06/26/2001
5925322	Fuel cell or a partial oxidation reactor or a heat engine and an oxygen-enriching device and method therefor The present invention relates to a combined cycle system of enhanced efficiency. The system comprises a top stage, such as a fuel cell, a partial oxidation reactor or a heat engine, and an oxygen-enriching device, such as a temperature swing adsorption de...	07/20/1999
5873240	Pulsed detonation rocket engine 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 ...	02/23/1999
5727368	Hybrid motor system with a consumable catalytic bed a composition of the catalytic bed and a method of using A method, device and composition for achieving ignition and sustained combustion using a solid consumable catalytic bed (CCB) is described. The CCB accomplishes this by decomposition of an injected fluid. Initially this reaction is catalytic or hypergolic...	03/17/1998
5582001	Hybrid rocket combustion enhancement The combustion of a hybrid engine is improved by continuously injecting into a precombustion chamber a hypergolic fluid such as triethyl aluminum which exothermically reacts with and vaporizes the oxidizer such as liquid oxygen. The prevaporized oxidizer ...	12/10/1996
5487267	Suppression of infrared radiation emissions from jet engines A reduction in the emission of infrared radiation by the engine of a jet aircraft can be achieved by employing a low molecular weight monohydric alcohol, having a luminometer number of at least about 200 as at least a portion of the fuel. Additional reduc...	01/30/1996
5339624	Ramjet propellants The present invention relates to a general method for increasing the energy conversion from metal-containing rocket and ramjet propellants. According to the invention, this is achieved by means of combining the combustion of the fuel with exothermic inter...	08/23/1994
5320692	Solid fuel ramjet composition A ramjet solid fuel composed of Hydroxyl terminated polybutadiene aluminum, agnesium, and boron carbide is described. The high volumetric heating value fuel of the present invention significantly increases the distance range of missiles....	06/14/1994
5143566	Composite solid propellant with a metal/inorganic fluoride admixture or a stable burning rate A composite solid propellant with a stable burning rate comprising an oxidizer, a binder system of telomeric polybutadiene or copolymers of butadiene and acrylonitrile with terminal functional groups or functional groups distributed statistically along th...	09/01/1992
5139587	Composite solid propellant with a pulverulent metal/oxidizer agglomerate base A composite solid propellant with a stable burning rate comprising ammonium perchlorate, a binder system of telomeric polybutadiene or copolymers of butadiene and acrylonitrile with terminal functional groups or functional groups distributed statistically...	08/18/1992
5099644	Lean staged combustion assembly A combustion assembly includes a combustor having inner and outer liners, and pilot stage and main stage combustion means disposed between the liners. A turbine nozzle is joined to downstream ends of the combustor inner and outer liners and the main stage...	03/31/1992
5085717	Autopyrolyzable composition for aerobic propulsion, the oxidizing agent of which is an explosive An autopyrolyzable solid composition for aerobic propulsion consists essentially of an oxidizing agent, a binder and a crosslinking agent. The oxidizing agent is a nitrated explosive material wherein the amount, by weight, of oxygen atoms fixed to the nit...	02/04/1992
5012719	Method of and apparatus for generating hydrogen and projectile accelerating apparatus and method incorporating same A projectile is accelerated through a barrel by a high pressure hydrogen gas jet that is derived by exothermically reacting water or a water-hydrogen peroxide liquid mixture with metal or a metal hydride. The temperature of the reaction is controlled by c...	05/07/1991
4925909	Gas-generating agent for use in ducted rocket engine A gas-generating agent for use in a ducted rocket engine essentially consists of an aliphatic polyester represented by the formula: ##STR1## or the formula: ##STR2## and a curing agent and optionally incorporating therein additives such as ...	05/15/1990
4787579	Gas thruster A thruster system has a main bipropellant propulsion unit including a propulsion engine (50) and bipropellant supply having a tank (3) for an oxidizing agent and a tank (4) for a fuel. An auxiliary cold propellant thruster (21) uses propellant supplied by...	11/29/1988
4527389	Highly soluble, non-hazardous hydroxylammonium salt solutions for use in hybrid rocket motors Non-hazardous, highly soluble hydroxylammonium salt solutions are disclosed. These solutions have utility as liquid oxidizers in solid/liquid hybrid rocket motors....	07/09/1985
4452039	Expendable infrared source and method therefor An IR source and method for generating IR radiation whereby a propellant is urned in a first chamber to produce a product gas which is exited through a critical exit, is accelerated to a supersonic velocity by expanding into a second chamber, is passed thr...	06/05/1984
4392895	Ramjet fuel A solid ramjet fuel composition comprising a hydroxyl-terminated or carbo-terminated fluorocarbon binder, a polybutadiene prepolymer, a curative cross-linking compound, and a metal selected from the group consisting of aluminum, zirconium, amorphous boro...	07/12/1983
4332631	Castable silicone based magnesium fueled propellant A castable solid propellant composition suitable for use as a fuel generator for a ducted rocket motor is provided. The binder for the composition is a crosslinked polysiloxane. The polysiloxane polymer which is crosslinked to form the binder has a viscos...	06/01/1982
4133173	Ducted rockets The overall efficiency of a reaction engine having primary and secondary combustion chambers is greatly improved by reducing the primary exhaust velocity to subsonic speed. This is accomplished in a preferred embodiment by using an exhaust tube downstream...	01/09/1979
4007597	Power plant and system for accelerating a cross compound turbine in such plant, especially one having an HTGR steam supply An electric power plant having a cross compound steam turbine and a steam source that includes a high temperature gas-cooled nuclear reactor. The steam turbine includes high and intermediate-pressure portions which drive a first generating means, and a lo...	02/15/1977
3946555	Process for simulating turbojet engine plumes A process for simulating the infrared radiation in wave length and intensity and the spatially extended characteristics of the plumes of turbojet engines comprising burning fuel-rich solid gas generator compositions, comprising an organic binder, an oxidi...	03/30/1976

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Class 60/207 - Utilizing plural reaction zones within a system