| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 060390760 | Intermittent combustion type | 20 |
| 20090000266 | Pneumatic Operating Driving Device - A pneumatic operating driving device, comprising at least one rotor ( | 01-01-2009 |
| 20090007540 | PINTLE-CONTROLLED PROPULSION SYSTEM WITH EXTERNAL DYNAMIC SEAL - A propulsion system with a pintle for variable thrust is constructed such that the pintle contains a shaft at its fore end which passes through an opening in the thrust chamber wall and extends into a boss on the outside surface of the thrust chamber. A dynamic seal that maintains the pressurization of the thrust chamber while allowing movement of the pintle is positioned inside the boss, between the pintle shaft and the boss, and actuation of the pintle is achieved by a rack affixed to the fore end of the pintle and a gear that engages the rack. The dynamic seal, rack and gear are thus external to the thrust chamber, providing the thrust chamber with a compact external envelope, a greater thermal standoff, or both. | 01-08-2009 |
| 20090133377 | MULTI-TUBE PULSE DETONATION COMBUSTOR BASED ENGINE - An engine contains a compressor stage, a pulse detonation combustion stage and a turbine stage. The pulse detonation combustion stage contains at least one pulse detonation combustor which has an inlet portion. The pulse detonation combustor is positioned such that the inlet portion of the pulse detonation combustor is located forward of an outlet of the compressor stage with respect to the engine. The pulse detonation combustor is angled with respect to a centerline of the engine. | 05-28-2009 |
| 20090241507 | GROUND BASED PULSE DETONATION COMBUSTOR FOR POWER GENERATION - A ground based power generation system contains at least two compressor stages, a combustion stage and a turbine stage. An intercooler is positioned between the two compressor stages and a regenerator is positioned between the compressor stages and the combustion stage. The combustion stage contains at least one of a pulse detonation combustor and constant volume combustor. Downstream of the combustion stage is the turbine stage. Heat for the regenerator is supplied from the turbine stage. Further, a bypass flow device is included which re-directs flow upstream of the combustion stage to downstream of the combustion stage and upstream of the turbine stage. | 10-01-2009 |
| 20090266047 | MULTI-TUBE, CAN-ANNULAR PULSE DETONATION COMBUSTOR BASED ENGINE WITH TANGENTIALLY AND LONGITUDINALLY ANGLED PULSE DETONATION COMBUSTORS - An engine contains a compressor stage, a pulse detonation combustion stage and a turbine stage. The pulse detonation combustion stage contains at least one pulse detonation combustor which has an inlet portion. The pulse detonation combustor is oriented longitudinally and/or tangentially with respect to a centerline of the engine. | 10-29-2009 |
| 20110056182 | VALVELESS PULSE COMBUSTOR - A valveless pulse combustor having a combustion chamber with a closed first end and an open second end, the combustor also having a tailpipe in fluid communication with the open second end of the combustion chamber, the combustor further having an inlet pipe in fluid communication with the open second end of the combustion chamber, the inlet pipe and the tailpipe being arranged such that one is located within the other. | 03-10-2011 |
| 20120017563 | JET ENGINE, IN PARTICULAR A JET ENGINE FOR AN AIRCRAFT - The invention relates to a jet engine ( | 01-26-2012 |
| 20120131899 | INTEGRATED DEFLAGRATION-TO-DETONATION OBSTACLES AND COOLING FLUID FLOW - A detonation chamber and a pulse detonation combustor including a detonation chamber, wherein the detonation chamber includes a plurality of initiation obstacles and at least one injector in fluid flow communication with each of the plurality of initiation obstacles. The plurality of initiation obstacles are disposed on at least a portion of an inner surface of the detonation chamber with each of the plurality of initiation obstacles defining a low pressure region at a trailing edge. The plurality of initiation obstacles are configured to enhance a turbulence of a fluid flow and flame acceleration through the detonation chamber. The at least one injector in provides a cooling fluid flow to each of the plurality of initiation obstacles, wherein the cooling fluid flow is one of a fuel, a combination of fuels, air, or a fuel/air mixture. | 05-31-2012 |
| 20120151895 | HOT GAS PATH COMPONENT COOLING FOR HYBRID PULSE DETONATION COMBUSTION SYSTEMS - The flow through the core of a hybrid pulse detonation combustion system is passed through a compressor and then separated into a primary flow, that passes directly to the combustor, and a bypass flow, which is routed to a portion of the system to be used to cool components of the system. The bypass includes a pump that raises the pressure of the bypass flow sufficient to deliver it to downstream stations of the engine that contain combustion products that are at a higher pressure than the compressor exit. | 06-21-2012 |
| 20120151896 | HOT GAS PATH COMPONENT COOLING FOR HYBRID PULSE DETONATION COMBUSTION SYSTEMS - The flow through the core of a hybrid pulse detonation combustion system is passed through a compressor and then separated into a primary flow, that passes directly to the combustor, and a bypass flow, which is routed to a portion of the system to be used to cool components of the system. The bypass flow is routed to a nozzle of the pulse detonation combustor. The flow is then passed back into the primary flow through the core downstream of where it was extracted. | 06-21-2012 |
| 20120216504 | ENGINE AND COMBUSTION SYSTEM - One embodiment of the present invention is an engine. Another embodiment is a unique combustion system. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for engines and combustion systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith. | 08-30-2012 |
| 20120324860 | GAS TURBINE ENGINE AND PULSE DETONATION COMBUSTION SYSTEM - One embodiment of the present invention is a unique pulse detonation combustion system. Another embodiment is a unique gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for pulse detonation combustion systems, gas turbine engines, and other machines and engines. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith. | 12-27-2012 |
| 20130139486 | VARIABLE INITIATION LOCATION SYSTEM FOR PULSE DETONATION COMBUSTOR - A pulse detonation combustor (PDC) includes a combustion tube, an inlet located on an upstream end of the combustion tube which receives a flow of a fuel/air mixture, an enhanced DDT region located within the tube downstream of the inlet, a nozzle disposed on a downstream end of the tube and a fortified region disposed downstream of the enhanced DDT region and upstream of the nozzle. A combustion initiation system that provides multiple initiation locations at different axial stations along the length of the tube are positioned downstream of the inlet and upstream of the fortified region. The initiator system is operable to initiate combustion of a fuel-air mixture within the tube at a selected one of the initiation locations. | 06-06-2013 |
| 20130139487 | VARIABLE INITIATION LOCATION SYSTEM FOR PULSE DETONATION COMBUSTOR - A pulse detonation combustor (PDC) includes a combustion tube, an inlet located on an upstream end of the combustion tube which receives a flow of a fuel/air mixture, an enhanced DDT region located within the tube downstream of the inlet, a nozzle disposed on a downstream end of the tube and a fortified region disposed downstream of the enhanced DDT region and upstream of the nozzle. A combustion initiation system that provides multiple initiation locations at different axial stations along the length of the tube are positioned downstream of the inlet and upstream of the fortified region. The initiator system is operable to initiate combustion of a fuel-air mixture within the tube at a selected one of the initiation locations. | 06-06-2013 |
| 20130263569 | HELICAL CROSS FLOW (HCF) PULSE DETONATION ENGINE - A helical cross flow pulse detonation engine. | 10-10-2013 |
| 20140083077 | ENVIRONMENTALLY SEALED COMBUSTION POWERED LINEAR ACTUATOR - A combustion powered linear actuator features an actuator body having a first chamber therein and a power piston mounted in the first chamber movable between retracted and extended positions. The power piston has a combustion chamber therein. A first seal about the piston seals the piston with respect to the actuator body. A vent region in the body of increased diameter allows exhaust gases to bypass the first seal and flow into a space between the piston and the actuator body and to then vent out of the actuator body. A second seal proximate the distal end of the actuator body cooperates with another piston seal to seal the annular region when the piston is retracted. The vent region may include a vent gland in the first chamber about the piston defining a vent chamber between the actuator body and the vent gland. | 03-27-2014 |
| 20140216000 | Indexed Positive Displacement Rotary Motion Device - Disclosed herein is an indexing system for a rotor assembly where in one example the indexing system regulates the rotational location of drive rotors. In one example the rotors are configured to rotate about a shaft. | 08-07-2014 |
| 20160102609 | PULSE DETONATION COMBUSTOR - A pulse detonation combustor may include a valve and a tubular combustor wall, which forms an airflow inlet and a combustion chamber. The valve may be configured to selectively fluidly couple the airflow inlet with the combustion chamber. The valve may include a center body and an annular projection. The center body and the projection may be configured to sealingly engage with one another. | 04-14-2016 |
| 060390780 | Rotating, oscillating, or reciprocating | 2 |
| 20090193786 | 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 that the circumferential wall of the rotatable member is spaced radially inwardly from the outer circumferential wall; at least one helical channel formed by a plurality of helical sidewalls extending between the circumferential wall of the rotatable member and the outer circumferential wall, each helical channel being open at the forward end and the aft end of the rotatable member so as to provide flow communication therethrough; an air supply for providing air to each helical channel; and, a fuel supply for providing fuel to each helical channel. In this way, a mixture of the fuel and air is continuously detonated within each helical channel in a manner such that combustion gases exit therefrom with an increased pressure and temperature. | 08-06-2009 |
| 20110214407 | PULSE DETONATION SYSTEM - In one embodiment, a pulse detonation system includes a pulse detonation tube including a base tube and a thermally protective layer disposed adjacent to an inner surface of the base tube. The thermally protective layer is configured to limit temperature fluctuations at the inner surface of the base tube to less than approximately 20 degrees Celsius during operation of the pulse detonation system, and the thermally protective layer does not comprise a ceramic coating. | 09-08-2011 |
