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| Number | Title | Issue Date |
| 8127533 | System and method for power production using a hybrid helical detonation device The system and method described herein uses a hybrid pulsed detonation engine (PDE) system to drive a turbine that powers an electric generator. The combustion chamber of the PDE is shaped in a helical form, so that the external length of the section is reduced, whi... | 03/06/2012 |
| 8117828 | Constant volume combustor having a rotating wave rotor A pressure wave apparatus utilizing the principles of pulsed detonation and wave rotor technologies. The apparatus includes inlet and outlet ports that interface with a plurality of fluid flow passageways on a rotor. A buffer gas is routed through some of the inlet ... | 02/21/2012 |
| 8091336 | Method to initiate multiple chamber detonation wave combustors A pulse detonation wave engine (PDWE) detonation system provides for optical ignition. The detonation system has a plurality of detonation banks, where each detonation bank has a plurality of detonation chambers for receiving a fuel/oxidizer mixture from a propellan... | 01/10/2012 |
| 8082728 | System and method of continuous detonation in a gas turbine engine A continuous detonation system, including: a rotatable member including a forward end, an aft end, a circumferential wall and a longitudinal centerline axis extending therethrough; an outer circumferential wall, wherein the rotatable member is positioned therein so ... | 12/27/2011 |
| 7950219 | Dual mode combustion operation of a pulse detonation combustor in a hybrid engine A dual mode combustor of a gas turbine engine contains at least one dual mode combustor device having a combustion chamber, a fuel air mixing element, a high frequency solenoid valve and a fuel injector. During a first mode of operation the dual mode combustor devic... | 05/31/2011 |
| 7905084 | Rotary pressure rise combustor for a gas turbine engine A gas generator for providing continuous pressure rise combustion, including: a rotatable member including a forward end, an aft end, a circumferential wall and a longitudinal centerline axis extending therethrough; an outer circumferential wall, wherein the rotatab... | 03/15/2011 |
| 7752835 | Pulsed combustion engine A turbine engine has a case with an axis. A fan is mounted for rotation about the axis. A turbine is mechanically coupled to the fan to drive rotation of the fan about the axis. A number of compressor/turbine units are downstream of the fan and upstream of the turbi... | 07/13/2010 |
| 7748211 | Vapor cooling of detonation engines An engine cooling system includes a combustion chamber assembly configured to generate detonation waves and a first vapor cooling assembly. The combustion chamber assembly defines a flowpath between an inner liner and an outer liner. The first vapor cooling assembly... | 07/06/2010 |
| 7739867 | Compact, low pressure-drop shock-driven combustor A system for efficiently creating cyclic detonations is provided. The system includes at least a first initiator chamber configured to generate an initial wave, at least one main chamber coupled to the first initiator chamber. The main chamber is configured to gener... | 06/22/2010 |
| 7735311 | Pulsed detonation engines manufactured from materials having low thermal stability Pulsed detonation engines (PDEs), or various components thereof, such as the detonation chamber and/or nozzle, can be economically constructed from materials having low thermal stability, such as plastics, composites, and light metals. During operation, the intermit... | 06/15/2010 |
| 7690191 | Fuel preconditioning for detonation combustion A fuel preconditioning system for use with a pulse detonation combustor (PDC) makes use of a heat source to pyrolyze fuel prior to injecting it into the PDC for detonation. The fuel is decomposed into a more detonable form by pyrolysis in a conditioner that applies ... | 04/06/2010 |
| 7685806 | Method and apparatus for supersonic and shock noise reduction in aircraft engines using pneumatic corrugations An aircraft engine is provided with at least one pulse detonation device connected to an engine exhaust nozzle portion with a plurality of supersonic injectors. The flow from the pulse detonation device is passed through the supersonic injectors into the primary eng... | 03/30/2010 |
| 7669405 | Shaped walls for enhancement of deflagration-to-detonation transition A detonation chamber for a pulse detonation combustor including: a plurality of dimples disposed on at least a portion of an inner surface of the detonation chamber wherein the plurality of dimples enhance a turbulence of a fluid flow through the detonation chamber.... | 03/02/2010 |
| 7669406 | Compact, low pressure-drop shock-driven combustor and rocket booster, pulse detonation based supersonic propulsion system employing the same A supersonic propulsion system is provided. The supersonic propulsion system includes a plurality of systems for efficiently creating cyclic detonations and at least one rocket booster device. Each of the systems include at least a first initiator chamber configured... | 03/02/2010 |
| 7637096 | Pulse jet engine having pressure sensor means for controlling fuel delivery into a combustion chamber A pressure rise combustor is provided with fuel provided at intermittent periods. The fuel is pulsed at timings such that the phase lag between the addition of the fuel and a resultant pressure rise is minimized. The fuel is pulsed such that the unsteady addition of... | 12/29/2009 |
| 7634904 | Methods and apparatus to facilitate generating power from a turbine engine A turbine disk assembly including a rotatable cylindrical member rotatably coupled to a shaft and a plurality of turbine blades extend circumferentially outward from said cylindrical member. The turbine blades include at least two different geometrical shapes, a fir... | 12/22/2009 |
| 7631487 | Constant volume rocket motor The present invention is a constant volume rocket motor that uses a non-detonating constant-volume, bipropellant combustion process in pulse-mode operation. Opening and closing of the combustion chamber exhaust outlet is controlled by an actuated reciprocating thrus... | 12/15/2009 |
| 7621118 | Constant volume combustor having a rotating wave rotor A constant volume combustor device includes, in one form, a detonative combustion. In one form the wave rotor of the constant volume combustor is supported by magnetic bearings. The constant volume combustor device includes a rotor having a number of fluid passagewa... | 11/24/2009 |
| 7614211 | Swirling flows and swirler to enhance pulse detonation engine operation A swirler having cross-sectional area comparable to the area of a detonation chamber is placed upstream of the detonation chamber to enhance the fuel-air mixing. The swirler has a first region and a second region, each of which induces swirl in the flow through the ... | 11/10/2009 |
| 7581383 | Acoustic pulsejet helmet A pulsejet is provided that includes an inlet, an exhaust nozzle, and a combustion chamber between the inlet and the exhaust nozzle. The pulsejet additionally includes a flow-turning device positioned over an end of the inlet. The flow turning device forms an air fl... | 09/01/2009 |
| 7526912 | Pulse detonation engines and components thereof A pulse detonation engine comprises a primary air inlet; a primary air plenum located in fluid communication with the primary air inlet; a secondary air inlet; a secondary air plenum located in fluid communication with the secondary air inlet, wherein the secondary ... | 05/05/2009 |
| 7520123 | Mixing-enhancement inserts for pulse detonation chambers The present invention provides a pulse detonation insert that induces flow obstructions within the pulse detonation chambers, wherein the flow obstructions are operable to induce turbulence within a primary fluid flow passing over the obstructions. This turbulence m... | 04/21/2009 |
| 7448200 | 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... | 11/11/2008 |
| 7427048 | Linear acoustic pulsejet A linear acoustic pulsejet (LAP) including a body having a first side panel and an opposing substantially parallel second side panel. A plurality of substantially parallel intercostals are orthogonally connected to each of the first and second side panels to create ... | 09/23/2008 |
| 7410131 | Pulsed detonation engines for reaction control systems Pulsed detonation engines (PDEs) are adapted for use in reaction control systems (RCS), such as thrusters for orbital correction and control (e.g., for earth-orbiting satellites), divert thrust generation and control for space-based interceptor devices, and for miss... | 08/12/2008 |
| 7367194 | Pulse detonation engine system for driving turbine A pulse detonation engine system (1) for driving a turbine is comprises a detonation generator section (5) including a detonation tube (7) having a tubular hollow section for permitting detonation to be generated therein during combustion stage ... | 05/06/2008 |
| 7353647 | Methods and apparatus for assembling gas turbine engines A method facilitates assembling a gas turbine engine including a compressor and a rotor assembly coupled in axial flow communication downstream from the compressor. The method comprises coupling a bypass system in flow communication with the compressor to channel a ... | 04/08/2008 |
| 7328570 | Pulse detonation system for a gas turbine engine having multiple spools A gas turbine engine having a longitudinal centerline axis therethrough, including: a fan section at a forward end of the gas turbine engine including at least a first fan blade row connected to a first drive shaft; a booster compressor positioned downstream of the ... | 02/12/2008 |
| 7310951 | Steady-state detonation combustor and steady-state detonation wave generating method A steady-state detonation combustor and a steady-state detonation wave generating method, in which a stabilized detonation wave can be generated by generating a hypersonic and unburned premixed gas. An rich premixed gas whose gas fuel is rich is combusted in a rich ... | 12/25/2007 |
| 7311175 | Acoustic liner with bypass cooling An acoustic liner 20 includes a remote panel 26, a proximate panel 28 transversely spaced from the remote panel and a resonator chamber 34b residing between the panels. Perforations 38 penetrate the proximate panel in regist... | 12/25/2007 |
| 7278611 | Pulsed detonation engines for reaction control systems Pulsed detonation engines (PDEs) are adapted for use in reaction control systems (RCS), such as thrusters for orbital correction and control (e.g., for earth-orbiting satellites), divert thrust generation and control for space-based interceptor devices, and for miss... | 10/09/2007 |
| 7269951 | Throat retention apparatus for hot gas applications A nozzle for use in a hot gas valve is provided that includes a housing, an insert, and a throat retainer. The housing is constructed of an insulating material and has a flow path formed therein. The flow path has a throat section. The insert is made of material cap... | 09/18/2007 |
| 7251928 | Pulse detonation engine and valve Pressure and density of a gaseous mixture are increased in the process of introducing the gaseous mixture into the combustor of an air-breathing pulse detonation engine employing atmospheric oxygen as an oxidizer. The exit valve 20 able to be opened and close... | 08/07/2007 |
| 7246483 | Energetic detonation propulsion A propulsion system for creating a propulsive force has a combustion chamber, a pair of electrodes within the combustion chamber and a power supply attached to the electrodes to create a high voltage field within an initiation zone of the combustion chamber, and an ... | 07/24/2007 |
| 7228683 | Methods and apparatus for generating gas turbine engine thrust using a pulse detonator Methods and apparatus for generating thrust from a gas turbine engine using a pulse detonation system is provided. The gas turbine engine includes a fan assembly, and a bypass duct channeling air to a core engine and the pulse detonation system. The method includes ... | 06/12/2007 |
| 7200987 | Off-axis pulse detonation configuration for gas turbine engine The present invention is a gas turbine engine system containing a compressor stage, a pulse detonation stage, and a turbine stage. During operation of the engine system, compressed flow from the compressor stage is directed to at least one off-axis pulse detonation ... | 04/10/2007 |
| 7188467 | Methods and apparatus for assembling a gas turbine engine A method for assembling a gas turbine engine includes providing a core engine, and providing a flade system including a flade stream augmentor positioned within a flade duct. The method also includes channeling airflow through the core engine to produce engine thrus... | 03/13/2007 |
| 7178338 | Variable area nozzle An exhaust nozzle assembly for a gas turbine engine, the assembly comprises a main axis, an inner nozzle, an outer nozzle, a translatable centre-body and an actuator for translating the centre-body between a forward position and a rearward position. The centre-body ... | 02/20/2007 |
| 7140174 | Methods and apparatus for assembling a gas turbine engine A method for assembling a gas turbine engine includes providing a core engine, an inner fan assembly, and a fladed fan assembly, coupling a plurality of airflow ducts to the engine including an inner fan duct for channeling airflow through the inner fan assembly, a ... | 11/28/2006 |
| 7137243 | Constant volume combustor A pressure wave apparatus utilizing the principles of pulsed detonation and wave rotor technologies. The apparatus includes inlet and outlet ports that interface with a plurality of fluid flow passageways on a rotor. A buffer gas is routed through some of the inlet ... | 11/21/2006 |
