| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 060224000 |
Interrelated reaction motors
| 363 |
| 060204000 |
Method of operation
| 223 |
| 060770000 |
Particular exhaust nozzle feature
| 96 |
| 060202000 |
Ion motor
| 65 |
| 060253000 |
Solid propellant
| 38 |
| 060247000 |
Intermittent combustion
| 37 |
| 060266000 |
Including heat exchange means
| 36 |
| 060228000 |
With thrust direction modifying means
| 34 |
| 060257000 |
Liquid oxidizer
| 33 |
| 060767000 |
Air supplied by ram effect (e.g., ramjet, etc.)
| 22 |
| 060761000 |
Having afterburner
| 20 |
| 060203100 |
Electric, nuclear, or radiated energy fluid heating means
| 20 |
| 060262000 |
Air passage bypasses combustion chamber
| 17 |
| 060251000 |
Solid and fluid propellant
| 11 |
| 060233000 |
Condition responsive thrust varying means
| 11 |
| 060268000 |
Including counter rotating rotors
| 10 |
| 060264000 |
Including motive fluid treating means
| 10 |
| 060221000 |
Motive fluid principally liquid
| 9 |
| 060269000 |
Including mechanical air compressor or air flow inducing means
| 8 |
| 060246000 |
Turborocket
| 7 |
| 060263000 |
Plural motive fluid generating means or plural outlets
| 6 |
| 060250000 |
Plural propellants to burn sequentially | 4 |
| 20080236140 | Noncircular transient fluid fuel injector control channels in propellant injector combustion systems - A fuel injector system for combustion engines and motors, such as pulsed bipropellant thrusters, includes noncircular fuel and oxidizer injectors at the ends of respective dribble channels for controlling the mixture ratio of the propellants passing into a combustion chambers for maintaining a desire or ideal mixture ratio as determined by the cross-sectional area of the injectors well suited for pulse combustion fuel injector systems. | 10-02-2008 |
| 20120036831 | Pellet-Loaded Multiple Impulse Rocket Motor - There is disclosed an apparatus which may include a common nozzle and a plurality of combustion chambers coupled to the nozzle. Each of the plurality of combustion chambers may include a case, a solid fuel propellant charge in the form of a plurality of fuel pellets, and an igniter disposed to ignite the propellant charge. Each of the plurality of combustion chambers may also include a pellet retainer disposed to retain unignited fuel pellets within the case and a burst disk disposed between the propellant charge and the nozzle. Each burst disk may adapted to rupture when the associated propellant charge is ignited and to not rupture when a propellant charge of any of the other combustion chambers is ignited | 02-16-2012 |
| 20130014491 | COMBUSTION GAS SUPPLY CONTROL DEVICEAANM SUZUKI; TasukuAACI TokyoAACO JPAAGP SUZUKI; Tasuku Tokyo JPAANM MIHARA; ChiyakoAACI TokyoAACO JPAAGP MIHARA; Chiyako Tokyo JPAANM IEKI; KatsunoriAACI TokyoAACO JPAAGP IEKI; Katsunori Tokyo JP - A combustion gas generator has: a motor case; a first propellant loaded within the motor case to burn at a first pulse; a second propellant loaded within the motor case to burn at a second pulse subsequent to the first pulse a front motor head fixed to a front portion of the motor case and having a combustion gas exhaust hole; and a rear motor head fixed to a rear portion of the motor case and having a combustion gas exhaust hole. A combustion gas supply control device prevents combustion gas of the first propellant at the first pulse from flowing into the combustion gas exhaust hole of the front motor head and supplies combustion gas of the second propellant at the second pulse to the combustion gas exhaust hole of the front motor head. | 01-17-2013 |
| 20130327016 | IGNITION DEVICE FOR TWO-PULSE ROCKET MOTOR WITH THERMAL BARRIER MEMBRANE - In a two-pulse rocket motor provided with a pressure vessel, a first propellant placed within the pressure vessel that burns during a first pulse stage, a second propellant placed within the pressure vessel that burns during a second pulse stage following the first pulse stage, and a barrier membrane placed so as to cover the entire initial burning surface of the second propellant, wherein the barrier membrane is provided with an inner barrier membrane that covers the inner peripheral surface of the second propellant and an aft barrier membrane that covers the rear surface of the second propellant, and an end portion where the aft barrier membrane and the inner barrier membrane meet is joined over the entire circumference thereof. The ignition device includes an energy supply unit, an energy transfer unit connected at one end to the energy supply unit, and an ignition unit. | 12-12-2013 |
| 060201000 |
Rotating or cyclic movement during axial thrust | 3 |
| 20080236136 | LINKAGE SYSTEM WITH WEAR REDUCTION - A linkage system includes a pivot bias assembly at each pivot which removes internal clearances and resultant vibratory wear. The pivot bias assembly includes a cavity which defines an axis transverse to the pivot axis. A spring biased piston is located therein to provide a radial load toward the rotation pivot to close radial clearances. The spring loaded piston reduces all the radial internal clearances to zero to reduce vibratory wear created by engine vibratory inputs. An assembly flat is positioned such that the component is assembled in a non-operating angular position such that the spring biased piston is under minimal or no load then the component is rotated into operating position so as to preload the spring biased piston. | 10-02-2008 |
| 20100071344 | Closed-circuit hydraulic thruster - The present invention provides closed-circuit hydraulic thruster used for the generation of thrust, or lift, force from the torque provided by a prime mover, or a motor. In a preferred embodiment the closed-circuit hydraulic thruster comprises an outer casing; at least two inner-members; at least one intermediate body; a drive shaft; at least one rotor assembly including a central disk and a plurality of circumferentially arranged, low angle of attack, hydrofoil-like blades; and an incompressible fluid completely filling the space enclosed within the casing. In operation, the incompressible fluid will circulate within the passages confined between the opposing surfaces of the casing, inner-members, and intermediate body due to its acceleration by the rotor blades, with the blades' generated thrust force being transmitted to the thruster's casing through thrust bearing arrangement(s) Means for cooling the incompressible viscous fluid are also provided. | 03-25-2010 |
| 20120117937 | USES OF HYDROCARBON NANORINGS - Hydro-carbon nanorings may be used, e.g., in power storage power transmission and transportation. Sufficiently cooled, an externally hydrogen doped carbon nanoring may be used to create a radial dipole containment field for electrons rotating in the nanoring. Such nanorings may transmit DC current with little or no loss. Similarly, an internally hydrogen doped carbon nanoring may be used to create a radial dipole containment field for positrons rotating in the nanoring. Virtually lossless transmission of AC current may be achieved by pairing such streams of electrons and positrons in their respective containment fields. Closed rotation of such streams may also be used to efficiently store large amounts of electrical energy. Finally, by selectively accelerating and decelerating pairs of such paired electron and positron streams, which are moving at relativistic speeds, differential momentum may be created to cause physical movement. | 05-17-2012 |
| 060244000 |
Motive fluid from diverse generators alternatively ejected through outlet | 3 |
| 20080256924 | Ultra-compact, high performance aerovortical rocket thruster - An ultra-compact aerovortical swirl-enhanced combustion (ASC) system features an aerovortical swirl generator for use in rocket thrusters utilizing hypergolic or non-hypergolic propellants. The ACS thruster can be sized for diameters ranging from about 0.5 to about 2.0 inches, and producing thrust levels of approximately 5 lb | 10-23-2008 |
| 20120144797 | ROCKET ENGINE WITH CRYOGENIC PROPELLANTS - A cyrogenic-propellant rocket engine includes: at least a first tank for a first liquid propellant; a second tank for a second liquid propellant; a third tank for an inert fluid; an axisymmetrical nozzle including a combustion chamber, a device for injecting first and second liquid propellants into the combustion chamber, a nozzle throat, and a divergent section; and a heater device including at least one duct for conveying the inert fluid and arranged outside the nozzle in immediate proximity thereof, but without making contact therewith, to recover energy of thermal radiation emitted when the rocket engine is in operation and to heat the inert fluid. | 06-14-2012 |
| 20130327015 | DUAL USE HYDRAZINE PROPULSION THRUSTER SYSTEM - Some embodiments provide a dual use hydrazine propulsion thruster system. The dual use hydrazine propulsion thruster system may include a storage vessel configured to store hydrazine and a chemical thruster configured to provide thrust using the hydrazine. The dual use hydrazine propulsion thruster system may also include a convertor configured to catalytically convert hydrazine to a product comprising ammonia, and an electric thruster configured to provide thrust by ionizing ammonia and accelerating the ionized ammonia out of the electric thruster. | 12-12-2013 |
| 060227000 |
Motive fluid principally steam | 3 |
| 20080236139 | Power generation system - To provide a power generation system that prevents a reduction in the efficiency of a steam turbine due to an aperture adjustment of a turbine governing valve. There is provided a power generation system comprising: a furnace in which a solid fuel or a liquid fuel is combusted; a steam turbine that generates electric power by rotating a turbine rotor using steam generated by the furnace; a superheater that is provided between the furnace and the steam turbine and that superheats the steam; a first steam piping that connects the furnace to the superheater; a second steam piping that connects the superheater to the steam turbine; a first valve provided in the first steam piping; a turbine governing valve provided in the second steam piping; and a control section that adjusts an aperture of the first valve according to a load of the steam turbine. | 10-02-2008 |
| 20090056308 | Jet-type steam engine - A simply constituted steam engine efficiently obtains mechanical energy not only from a heat source of a high temperature but also from the exhaust heat of an internal combustion engine and various kinds of heat sources of a low-temperature state such as the solar heat. In the engine, a rotor ( | 03-05-2009 |
| 20090211223 | HIGH EFFICIENT HEAT ENGINE PROCESS USING EITHER WATER OR LIQUEFIED GASES FOR ITS WORKING FLUID AT LOWER TEMPERATURES - The high efficient heat engine process can use either water or liquefied gases for its working fluid to extract thermal energy from the ambient or non-ambient heat sources to increase its heat transfer rate and its power generation efficiency. The slower-speed two-phase turbine has a high ratio gear reducer to increase a generator's speed and produce power at about 50% efficiency. A high ratio gear reducer is used to increase its generator's speed and meet its power generation requirements (3,600 RPM). The two-phase separator and compressor/pump substitute the cooling condenser's position and compress the waste streams directly back to the boiler and allow the process to run at temperatures lower than room temperature, with no need for a conventional cooling condenser. Owing to these two-phase separator/compressor/pump processes, this new heat engine process will not discharge thermal pollution and/or radioactive/hazardous wastes into the heat sink and global environment. | 08-27-2009 |
| 060223000 |
With destruction sensing and preventing means | 3 |
| 20090007542 | TITANIUM TREATMENT TO MINIMIZE FRETTING - A method for surface treating a titanium gas turbine engine component. The method includes providing a gas turbine engine component having a titanium-containing surface. The component is heated to a temperature sufficient to diffuse carbon into the titanium and below 1000° F. The surface is contacted with a carbon-containing gas to diffuse carbon into the surface to form carbides. Thereafter, the carbide-containing surface is coated with a lubricant comprising a binder and a friction modifier. The binder preferably including titanium oxide and the friction modifier preferably including tungsten disulfide. The coefficient of friction between the surface and another titanium-containing surface is less than about 0.6 in high altitude atmospheres. | 01-08-2009 |
| 20090139201 | DECOUPLER SYSTEM FOR ROTOR ASSEMBLIES - A rotor decoupler system for a gas turbine engine is disclosed, comprising a load reduction system disposed between a bearing system and the bearing support. The load reduction system comprises a fuse and a damper such that the damper transfers at least a part of the radial load from the rotor to the bearing support when a fuse fails. In one exemplary embodiment the damper comprises a wire mesh, disposed around the outer race of the bearing. In another exemplary embodiment the damper comprises a rope damper assembly. In yet another exemplary embodiment, a load reduction system is disposed between a support structure and a frame, comprising an extensional fuse and a damper disposed between the support structure and the frame such that the damper transfers at least a part of the unbalance load to the frame when an extensional fuse fails. | 06-04-2009 |
| 20110041474 | METHOD AND SYSTEM FOR DETECTING THE INGESTION OF AN OBJECT BY AN AIRCRAFT TURBINE ENGINE DURING A MISSION - The invention relates to a method and a system for detecting the ingestion of an object by an aircraft turbine engine during a mission. The method includes the steps of acquiring during the mission digital images of the operating fan of the turbine engine, these images being acquired at an acquisition frequency proportional to the speed of rotation of the fan and to the number of blades of the fan (E | 02-24-2011 |
| Entries |
| Document | Title | Date |
|---|
| 20090107106 | Gas Turbine Engine Systems Involving Hydrostatic Face Seals - Gas turbine engine systems involving hydrostatic face seals are provided. In this regard, representative compressor assembly for a gas turbine engine includes a compressor having a hydrostatic seal formed by a seal face and a seal runner. | 04-30-2009 |
| 20090107107 | Multi-function rural fuel platform - A multi function rural fuel platform has a biofuel production unit and a diesel engine incorporated onto a transportable platform, wherein said biofuel production unit produces fuel for said diesel engine. | 04-30-2009 |
| 20090235636 | Reinforced, regeneratively cooled uni-body rocket engine - A rocket engine having a combustion chamber, a throat, and an exhaust bell is made with spaced apart inner and outer skins each unitarily formed in one piece of carbon fiber fabric. Longitudinal ribs in the space between the skins reinforce the engine and divide the space into a plurality of flow channels. An oxidizer ring at the bottom of the exhaust bell is in fluid flow communication with the flow channels, and one or more oxidizer tubes are connected tangentially at one end to the ring to supply oxidizer to the ring and thence to the flow channels. The oxidizer tubes are connected at their other end to the engine above the throat, further reinforcing the engine. An igniter is in the combustion chamber, and ignition fuel ports are directed toward the igniter to provide a soft start ignition. | 09-24-2009 |
| 20100031626 | Carbon-Kevlar uni-body rocket engine and method of making same - A rocket engine has spaced apart inner and outer skins each unitarily formed in one piece from carbon fiber fabric. The inner skin is formed on a two-part mold that is separated and removed from the inner skin after it is cured. An oxidizer ring encircles the bottom of the engine and is in flow communication with flow channels between the skins. Oxidizer tubes are connected at one end to the ring and at their other end to support brackets on the engine. The oxidizer ring is formed as an integral part of the engine by extending the outer skin over an inflatable mold, which is deflated and removed from the ring after the ring is cured. The oxidizer tube is formed on a mold with a rigid spine that holds the shape of the mold until the oxidizer tube is cured. The spine and the mold are then removed. | 02-11-2010 |
| 20100205929 | BASALT FIBER AND NANOCLAY COMPOSITIONS, ARTICLES INCORPORATING THE SAME, AND METHODS OF INSULATING A ROCKET MOTOR WITH THE SAME - An insulation composition that comprises at least one nitrile butadiene rubber, basalt fibers, and nanoclay is disclosed. Further disclosed is an insulation composition that comprises polybenzimidazole fibers, basalt fibers, and nanoclay. The basalt fibers may be present in the insulation compositions in a range of from approximately 1% by weight to approximately 6% by weight of the total weight of the insulation composition. The nanoclay may be present in the insulation compositions in a range of from approximately 5% by weight to approximately 10% by weight of the total weight of the insulation composition. Rocket motors including the insulation compositions and methods of insulating a rocket motor are also disclosed. | 08-19-2010 |
| 20100212283 | COATING FOR COMPONENTS REQUIRING HYDROGEN PEROXIDE COMPATIBILITY - The present invention provides a heretofore-unknown use for zirconium nitride as a hydrogen peroxide compatible protective coating that was discovered to be useful to protect components that catalyze the decomposition of hydrogen peroxide or corrode when exposed to hydrogen peroxide. A zirconium nitride coating of the invention may be applied to a variety of substrates (e.g., metals) using art-recognized techniques, such as plasma vapor deposition. The present invention further provides components and articles of manufacture having hydrogen peroxide compatibility, particularly components for use in aerospace and industrial manufacturing applications. The zirconium nitride barrier coating of the invention provides protection from corrosion by reaction with hydrogen peroxide, as well as prevention of hydrogen peroxide decomposition. | 08-26-2010 |
| 20110113749 | APPARATUS, PROPULSIVE ELEMENT AND METHOD FOR PROCESSING NON-CONSOLIDATED MATERIALS - A propulsive element usable for producing a jet of fluid using a pressurized fluid. An inlet receives the pressurized fluid; a propulsive element passageway extends from the inlet; two main outlets are in fluid communication with the propulsive element passageway and located substantially opposed to the inlet relative to the propulsive element passageway. The two main outlets are configured and sized for releasing each a respective main jet portion when the pressurized fluid is injected in the inlet, the two main jet portions being each substantially divergent, the two main jet portions creating a low pressure zone therebetween. An auxiliary outlet is located between the two main outlets, the auxiliary outlet being in fluid communication with the propulsive element passageway and located substantially opposed to the inlet relative to the propulsive element passageway. The auxiliary outlet is configured and sized for releasing an auxiliary jet portion when the pressurized fluid is injected in the inlet, the auxiliary jet portion being released in the low pressure zone. The auxiliary jet portion has a flow rate, a velocity, a configuration and dimensions such that forces exerted on the two main jet portions by the low pressure zone are reduced by the release of the auxiliary jet portion in the low pressure zone so as to reduce turbulence in the two main jet portions substantially adjacent to the two main outlets. Also, a method and an apparatus respectively using and including | 05-19-2011 |
| 20110214408 | LIQUID PROPELLANT TANK AND VAPOR JET EMITTING DEVICE INCLUDING SAME - A liquid propellant tank for storing a liquid propellant A and supplying vapor produced by evaporation of part of the liquid propellant A to an external location comprises a tank body for storing the liquid propellant A, and a plurality of holder plates arranged inside the tank body, around an axis L of the tank body. The holder plates cause the liquid propellant A to adhere to them by surface tension, thereby establishing, inside the tank body, a liquid propellant holding area LA in which the liquid propellant A is held and a gas accumulation area GA in which vapor produced by evaporation of part of the liquid propellant A accumulates. The tank body has a propellant inlet open into the liquid propellant holding area LA and a gas outlet open into the gas accumulation area GA. | 09-08-2011 |
| 20120110976 | Universal aero space , naval eternal technology systems - The invention is a universal aero, naval and space, one class integrated technology, originated from a common, fundamental unique basic absolute maximum efficiency technology, total endothermic, hyperbaric, adiabatic and stoichiometric maximum power capacity, with unlimited pressure ratio, which is the unification of the way to produce a top absolute efficiency by cryogenic electrification of all the transportation systems from ground to the entire universe. | 05-10-2012 |
| 20120210695 | BELTED TOROID PRESSURE VESSEL AND METHOD FOR MAKING THE SAME - A toroid pressure vessel includes a toroid body having an inner shell and an outer shell. The toroid body includes a toroid outer perimeter. The outer shell extends along the toroid outer perimeter. A planar exterior face extends along at least a portion of the outer shell and the toroid outer perimeter. A support belt circumscribes the toroid outer perimeter and is coupled along the planar exterior face. The support belt braces and supports the pressure vessel along the toroid outer perimeter against bulging force (and hoop stress) generated by pressurized fluids within the vessel. The support belt facilitates the use of thinner pressure vessel shells and thereby decreases the weight of the pressure vessel while providing a support to the outer shell that substantially prevents deformation of the planar exterior face. | 08-23-2012 |
| 20120247082 | Clean up - rocket - The purpose is to develop, design a very inexpensive rocket to “clean up” the expendable debris orbiting the earth. This liter is a serious pollution of space and a threat to working satellites and the space station. Develop an inexpensive rocket engine with optimum efficiency conversion: propellants-chemicals to acquire the maximum thrust generation offering an inexpensive means to acquire low orbit to space. Parameters selected to minimize fuel consumption: by trying different hydrogen-oxygen mixture ratios. | 10-04-2012 |
| 20130014485 | Apparatus for propulsionAANM Nguyen; Peter HoangAACI SacramentoAAST CAAACO USAAGP Nguyen; Peter Hoang Sacramento CA US - An apparatus for propulsion includes a main body, a fluid flow channel for fluid mass to circulate within a self-sealed apparatus, an air flow channel for air to circulate within a self-sealed apparatus and/or to the open environment, a fluid mass, a rotator having compartments to move the fluid mass centrifugally, a cover providing sealed containment for the apparatus and providing the means to remove the rotator from the main body, and a rotator shaft providing rotation to the rotator by motor. A preferred embodiment includes an apparatus with two or more fluid flow channels for fluid mass to circulate within a self-sealed apparatus. Another preferred embodiment includes an apparatus with two or more air flow channels for air to circulate within a self-sealed apparatus and/or to the open environment. And another preferred embodiment includes the main body that can be manufactured in one or more parts. | 01-17-2013 |
| 20130086884 | Unknown - Whereby the spiral channels of the bladeless rotor and stator of the Bezentropic Bladeless Turbine are attached to the Laval nozzle, as well as to any preferred modification of the same nozzle, act as an extension of nozzle's divergent end, transforming it into a Bezentropic Bladeless Turbine, all the while retaining the nozzle's efficiency and efficacy, achieved as a result of the maintenance and sustenance of the mono-directional rectified molecular flow of gas, steam or its combination thereof, emitted by the nozzles into the Bezentropic Bladeless Turbines spiral channels to produce mechanical work or thrust. | 04-11-2013 |
| 20130192194 | SYSTEM FOR THE RECOVERY, STORAGE AND UTILISATION OF ATMOSPHERIC GAS FOR USE AS A VEHICLE PROPELLANT - A system for the recovery and management of atmospheric gas is disclosed, such as for use as a vehicle propellant in a vehicle propulsion system. The system can include a compressor configured to compress atmospheric gas and first and second storage tanks configured to store liquefied atmospheric gas from the compressor. The second storage tank can have a heater operable to heat liquefied atmospheric gas therein to convert it to a high pressure gas. The second storage tank includes an outlet duct fluidly coupled to the first storage tank for supplying high pressure gas to the first storage tank. | 08-01-2013 |
| 20130219853 | MID-SECTION OF A CAN-ANNULAR GAS TURBINE ENGINE WITH AN IMPROVED ROTATION OF AIR FLOW FROM THE COMPRESSOR TO THE TURBINE - A midframe portion ( | 08-29-2013 |
| 20130263573 | Rocket Stage Having Engine Thrust Frame Integrated With Tank - A rocket stage for a spacecraft includes an engine, a tank for storing a fuel and an oxidizer for combustion in the engine, a rocket stage primary structure, and an engine thrust frame that connects and transmits forces between the engine and the primary structure. The engine thrust frame includes at least an internal part thereof arranged internally within the tank. This internal part of the engine thrust frame forms an imperforate partition that divides an interior space of the tank into at least two chambers for storing the fuel and the oxidizer separately from one another. Propellant management devices including liquid guide vanes and refillable liquid reservoirs may be provided in connection with the partition in the tank interior space. | 10-10-2013 |
| 20130298523 | CONSTANT PRESSURE AEROSPIKE THRUSTER - A constant pressure aerospike thruster has been developed. The aerospike thruster includes a hollow combustion chamber with a circular shaped throat area, a spring loaded pintle located inside the combustion chamber and a spike extended out from the pintle through the throat area. | 11-14-2013 |
| 20130318943 | ROCKET MOTOR COMBUSTION CHAMBER INJECTION HEAD - An injection head including an annular distribution cavity for distributing a propellant upstream from an injection plate supporting injectors. The cavity includes a multiply-perforated distribution grid distributing the propellant, which grid is coaxial with the distribution cavity and of a concave shape that projects into the distribution cavity, the grid being fastened to a dome of the cavity. | 12-05-2013 |
| 20140196435 | Space Impulse Drive - Invention discloses an Impulse Drive useful to propel all types of flying, water or land vehicles or devices, without need of the lift the fluid air or water could provide. | 07-17-2014 |
| 20160032734 | FAN FOR A MULTI-FLOW TURBOSHAFT ENGINE, AND TURBOSHAFT ENGINE EQUIPPED WITH SUCH A FAN - The fan comprises a fan disk able to be rotationally driven about a longitudinal axis and provided at the periphery with radial blades each comprising a root slideably engaged in a groove of the disk and, on the outside thereof, a vane, platforms surrounding the disk being interposed between the radial blades. Advantageously, the fan additionally comprises shock-absorbing wedges which are arranged tangentially at the exterior periphery of said disk underneath the platforms and between two roots of adjacent radial blades, each wedge being in tangential contact with the two adjacent blades. | 02-04-2016 |
