Class / Patent application number | Description | Number of patent applications / Date published |
060767000 | Air supplied by ram effect (e.g., ramjet, etc.) | 22 |
20090094987 | APPARATUS AND METHOD FOR PROCESSING AIRFLOW WITH FLOWFIELD MOLDED HYPERSONIC INLET - A diverterless hypersonic inlet (DHI) for a high speed, air-breathing propulsion system reduces the ingested boundary layer flow, drag, and weight, and maintains a high capture area for hypersonic applications. The design enables high vehicle fineness ratios, low-observable features, and enhances ramjet operability limits. The DHI is optimized for a particular design flight Mach number. A forebody segment generates and focuses a system of multiple upstream shock waves at desired strengths and angles to facilitate required inlet and engine airflow conditions. The forebody contour diverts boundary layer flow to the inlet sides, effectively reducing the thickness of the boundary layer that is ingested by the inlet, while maintaining the capture area required by the hypersonic propulsion system. The cowl assembly is shaped to integrate with the forebody shock system and the thinned boundary layer region. | 04-16-2009 |
20090158744 | Statically-Operating Ejector Ramjet - The present invention provides a statically starting and operating ramjet engine system. The system includes a pumping ejector coupled to a ramjet engine upstream of the ramjet inlet. A subsonic converging nozzle is placed in fluid communication between the pumping ejector and ramjet inlet. The pumping ejector ejects a primary fluid into the ramjet inlet to entrain a secondary fluid and create a mixed flow with sufficient momentum and internal energy to achieve characteristic speed. The converging nozzle provides a characteristic cross section necessary for the mixed flow to achieve characteristic speed as it moves through the nozzle, thereby producing a standing shock wave at the point of maximum convergence of the nozzle and creating sonic conditions at the inlet of the ramjet engine. | 06-25-2009 |
20090158745 | Ramjet Superheater - The present invention provides a regenerative superheater system for an ejector ramjet engine. The invention includes a superheater in thermal communication with the combustion chamber of the ramjet engine. The superheater transfers thermal energy from combustion chamber to an ejectant which is then redirected upstream to the ramjet ejector. In one embodiment of the invention the temperature of the ejectant is modulated by a variable geometry cooler that controls the amount of thermal energy removed from the superheater system by ambient air. In an alternate embodiment of the invention, the temperature of the ejectant is modulated by a variable geometry superheater that controls the amount of thermal energy added to the superheater system through combustion gas. | 06-25-2009 |
20090241549 | SUBSONIC AND STATIONARY RAMJET ENGINES - A ramjet engine ( | 10-01-2009 |
20100126178 | Hybrid propulsive engine including at least one independently rotatable turbine stator - One aspect relates to a hybrid propulsive technique, comprising providing a flow of a working fluid through at least a portion of an at least one jet engine. The at least one jet engine includes an at least one turbine section, wherein the at least one turbine section includes at least one turbine stage. The at least one turbine stage includes an at least one turbine rotor and an at least one independently rotatable turbine stator. The hybrid propulsive technique further involves extracting energy at least partially in the form of electrical power from the working fluid, and converting at least a portion of the electrical power to torque. The hybrid propulsive technique further comprises rotating an at least one at least one independently rotatable turbine stator at least partially responsive to the converting the at least a portion of the electrical power to torque. | 05-27-2010 |
20110100014 | Hybrid propulsive engine including at least one independently rotatable propeller/fan - One aspect relates to a hybrid propulsive technique comprising providing at least some first thrust associated with a flow of a working fluid through at least a portion of an at least one axial flow jet engine. The hybrid propulsive technique comprises extracting energy from the working fluid that is at least partially converted into electrical power, and converting at least a portion of the electrical power to torque. The hybrid propulsive technique further comprises rotating an at least one independently rotatable propeller/fan of at least one rotatable propeller/fan assembly at least partially responsive to the converting the at least a portion of the electrical power to torque, wherein the rotating of the at least one independently rotatable propeller/fan of the at least one rotatable propeller/fan assembly is arranged to produce at least some second thrust. | 05-05-2011 |
20110146286 | SELF-STARTING TURBINELESS JET ENGINE - The self-starting turbineless jet engine has fuel delivery, fuel combustion and airflow components, but it does not contain and therefore avoids the limitations associated with turbines or other moving parts other than those associated with the fuel delivery. The jet engine provides inlet louvers or vanes which direct air through an internal restriction to before mixing it with a fuel for combustion in a combustion chamber. While most of the combustion gases are exhausted through an outlet portion of the turbineless jet engine, a portion of the combustion gases are mixed with air received from an aft inlet duct in sixteen thermodynamic air compressors and back through a centrally located hot gas and fire pressure conduit where the gases are further redirected by a high temperature insulated nose cone back into the air flow received by the inlet louvers, thereby providing heat and air compression, even at zero airspeed. | 06-23-2011 |
20120144836 | INTEGRATED AERO-ENGINE FLOWPATH STRUCTURE - One embodiment of the present invention is an integrated aero-engine flowpath structure. Another embodiment is a method of manufacturing integrated aero-engine flowpath structure. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for aero-engine flowpath structures. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith. | 06-14-2012 |
20120159956 | TOP CYCLE POWER GENERATION WITH HIGH RADIANT AND EMISSIVITY EXHAUST - The present invention generally relates to power generation methods and secondary processes requiring high radiant and emissivity homogeneous combustion to maximize production output. In one embodiment, the present invention relates to a top cycle power generator with combustion exhaust modified to have radiant flux in excess of 500 kW per square meter and emissivity greater than 0.90, and supercritical CO2 power generating cycle to maximize exergy efficiency. | 06-28-2012 |
20130014511 | HIGHLY INTEGRATED INSIDE-OUT RAMJET - The present invention generally relates to power generation and compression methods requiring high efficiency and low capital cost. In one embodiment, the present invention relates to an inside-out ramjet having both circumferential components and radial components on a single shaft to maximize exergy efficiency and minimize system size. | 01-17-2013 |
20130098045 | RAM AIR FAN OUTER HOUSING - A ram air fan outer housing for directing air from a ram air fan rotor and air from a ram air bypass into a ram air fan outlet. The outer housing includes an outer cylinder and a plenum connected at a joint region. The outer cylinder and the plenum are made of a laminate stacking sequence of at least four adjacent layers of plain-weave carbon-fiber fabric. Each layer of the stacking sequence has a weave orientation such that a first layer and a fourth layer are oriented forty-five degrees from each of a second layer and a third layer. The joint region is made of at least eight adjacent layers of plain-weave carbon-fiber fabric. The joint region laminate stacking sequence is formed by interleaving the four adjacent outer cylinder layers in the joint region with the four adjacent plenum layers in the joint region. | 04-25-2013 |
20140196460 | RAMJET INCLUDING A DETONATION CHAMBER AND AIRCRAFT COMPRISING SUCH A RAMJET - The invention relates to a ramjet including a detonation chamber and an aircraft comprising such a ramjet. According to the invention, the ramjet (S | 07-17-2014 |
20140230443 | ROTOR ASSEMBLY HAVING A CONCENTRIC ARRANGEMENT OF A TURBINE PORTION, A COOLING CHANNEL AND A REINFORCEMENT WALL - The present disclosure introduces a rotor assembly having a concentric arrangement comprising a rotating turbine portion, a cooling channel and an annular reinforcement wall. The concentric arrangement is configured to rotate around a common axis. Also introduced is a rotary engine comprising the rotor assembly, in which the cooling channel further functions as a rotating compressor portion. The rotary engine also comprises a stator assembly that itself comprises a static turbine portion positioned upstream of the rotating turbine portion, a static compressor portion positioned downstream of the rotating compressor portion, and a combustion chamber positioned downstream of the static compressor portion and upstream of the static turbine portion | 08-21-2014 |
20140283521 | INNER HOUSING ASSEMBLY INCLUDING RETENTION SLOTS - A ram air fan assembly includes a motor/bearing housing that extends along a horizontal length of the ram air fan assembly. An inner housing assembly is in fluid communication with the motor/bearing housing to define a joint. The inner housing assembly includes first and second ellipse-shaped slots. The first slot is positioned at a first angle with respect to a radial axis of the inner housing assembly that is perpendicular to the horizontal length, and the second slot is positioned at a second angle with respect to the radial axis, the second angle being different from the first angle, and each slot extending along a first direction parallel to the horizontal length to define an axial width and extending along a radial axis to define a radial width being greater than the axial width. | 09-25-2014 |
20140290259 | COMBUSTION SYSTEMS AND COMBUSTION SYSTEM COMPONENTS FOR ROTARY RAMJET ENGINES - A combustion systems and components for rotary ramjet engines. An injection system, optionally stratified for ease of engine startup, provides an air and fuel mixture to a combustion chamber. An ignition system ignites the mixture. A flameholding system may be positioned for communication with the combustion chamber to force an ignited flow of the air and fuel mixture toward a center of rotation within the ramjet engine. The ramjet engine may have a diverging stator for improved exhaust efficiency. The ignition may take place in the engine air intake. Alternatively, the ignition may take place within the combustion chamber using a dual-hub electrically charged system. An impulse turbine may use recirculation of injected fuel to cool a rim-rotor and/or to reduce windage on the rim-rotor. A sealing system may reduce gas leaks from a fuel conduit into the engine air intake. | 10-02-2014 |
20150354592 | RAM AIR FAN OUTER HOUSING - A ram air fan outer housing for directing air from a ram air fan rotor and air from a ram air bypass into a ram air fan outlet. The outer housing includes an outer cylinder with a ram air fan rotor end and a ram air fan outlet end. The ram air fan rotor end and the ram air fan outlet end are at opposite ends of an axis of the outer cylinder. A plenum is joined at a joint region for directing air from the ram air bypass into the outer cylinder. The plenum includes two plenum ridges with one at each of two walls of the plenum. The two walls of the plenum are parallel to the axis of the outer cylinder. Each of the two plenum ridges includes a protruding section of the corresponding plenum wall. | 12-10-2015 |
060768000 | Supersonic speed therethrough (e.g., scramjet, etc.) | 6 |
20080223045 | Combustor Configurations - The present specification generally relates to improvements to combustors such as burners and engines. In one aspect, the specification presents an acoustically enhanced ejector system which can be used as part of an intake system for a combustor. In another aspect, the specification teaches the use of a combustor combustion chamber as an oscillator to magnify a harmonic frequency of a pulsating frequency of the combustor. In still other aspects, the specification presents a combustion chamber having an inlet with a plurality of tangentially spaced apertures, and an in-line intake system connected to the apertures. | 09-18-2008 |
20100242486 | FUEL-COOLED HEAT EXCHANGER WITH THERMOELECTRIC DEVICE COMPRESSION - An apparatus includes an inlet conduit assembly surrounding a gas flow path and a combustor arranged downstream of the inlet conduit assembly. The inlet conduit assembly includes a thermoelectric (TE) device configured to convert heat into electrical energy, a gas flow conduit arranged between the gas flow path and the TE device, and a resilient member configured to bias the TE device into contact with the gas flow conduit. | 09-30-2010 |
20100281873 | Variable Supersonic Mach Number Air Heater Utilizing Supersonic Combustion - A supersonic combustion apparatus including a fixed geometric nozzle having a converging area, throat, and a diverging area, at least one movable combination of a fuel injector and an oxygen injector where the combined fuel injector and the oxygen injector is located within the divergent area of the fixed geometric nozzle, and an exit plane adjacent and downstream to the diverging area. The exit plane Mach speed is varied by heat addition in the diverging area by introduction of a combustible fuel through the fuel injector and oxygen through the oxygen injector and then axially aligning and positioning the combination of the fuel injector and the oxygen injector along the length of the diverging area to obtain a stabilized flame at the exit plane. | 11-11-2010 |
20110030379 | ENERGY- DEPOSITION SYTEMS,EGUIPMENT AND METHOD FOR MODIFYING AND CONTROLING SHOCK WAVES AND SUPERSONIC FLOW - Systems, equipment, and methods to deposit energy to modify and control shock waves and hypersonic or supersonic fluid flow, including systems for controlling, mitigating, and/or effecting air flow in relation to air vehicles, wind tunnels, or other assets, or the like, as well as systems, equipment, and methods for disrupting the shock structure at the inlet for the engine of an air vehicle traveling at supersonic or hypersonic speed; mitigating blast effects on vehicles; mitigating heating of throats in supersonic and hypersonic wind tunnels, as well as control the flow parameters and Mach number in their test sections. | 02-10-2011 |
20110173985 | THRUSTER COMPRISING A PLURALITY OF ROCKET MOTORS | 07-21-2011 |
20140331682 | HIGH-SPEED-LAUNCH RAMJET BOOSTER - A high-speed-launch ramjet boost (HSLRB) engine includes a combustion system for igniting fuel pumped by a fuel pump from a fuel tank, where the combustion system includes an igniter, fuel injectors and frame holders. An inlet provides a pathway for air to flow toward the fuel injectors. A variable geometry (VG) nozzle having a nozzle actuator is included for exhausting exhaust gas from combustion of the fuel by the combustion system. A processor is coupled to receive sensing signals from at least one of a pressure sensor and a temperature sensor during flight, wherein the processor provides control signals to the nozzle actuator for dynamically controlling an aperture size of the VG nozzle. | 11-13-2014 |