Air Supplied By Ram Effect (e.g., Ramjet, Etc.) Patents (Class 60/767)
-
Patent number: 11359877Abstract: An apparatus includes an energy source and an expansion structure. The energy source is configured to convey an amount of energy operable to increase a pressure of a compressible gas disposed in a chamber. The expansion structure is configured to be placed in fluid communication with the chamber and to receive a flow of the compressible gas in response to the increase in pressure. The expansion structure includes an inlet having a first diameter and an outlet having a second diameter greater than the first diameter and is configured to allow the compressible gas to expand as the compressible gas flows from the inlet to the outlet such that a supersonic free jet of the compressible gas exits the outlet. In some instances, the supersonic free jet of the compressible gas can accelerate, relative to the expansion structure, a projectile disposed outside of the expansion structure.Type: GrantFiled: January 6, 2021Date of Patent: June 14, 2022Assignee: Wave Motion Launch CorporationInventor: Finn Van Donkelaar
-
Patent number: 11255266Abstract: A gas turbine engine includes a rotatable first shaft, a first disk connected to the first shaft, a second disk connected to the first shaft, a combustor radially outward from the first disk and the second disk, and a heat exchanger connected to the combustor aft of the second disk. The first disk includes a row of low pressure compressor blades and a row of high pressure turbine blades connected to a radially outer end of the row of low pressure compressor blades. The second disk includes a row of high pressure compressor blades and a row of low pressure turbine blades connected to a radially outer end of the row of high pressure compressor blades.Type: GrantFiled: March 23, 2020Date of Patent: February 22, 2022Assignee: Raytheon Technologies CorporationInventor: Victor Pascu
-
Patent number: 10837643Abstract: A mixer assembly for a turbine engine is generally provided. The mixer assembly includes a vane assembly including a plurality of vanes configured to direct a flow of oxidizer to mix with a flow of fuel. The vane assembly includes a fluid diode disposed within a vane flow path between each pair of vanes of the vane assembly.Type: GrantFiled: August 6, 2018Date of Patent: November 17, 2020Assignee: General Electric CompanyInventors: Sibtosh Pal, Clayton Stuart Cooper, Arthur Wesley Johnson, Steven Clayton Vise, Michael Anthony Benjamin, Allen Michael Danis
-
Patent number: 10788213Abstract: Embodiments of the invention provide a system or a method for combusting reactants including a fuel and an oxidizer into combustion products in a combustor. A combustor can be configured to contain a flow of the reactants and the combustion products that extends in a first direction. The flow can be subject to acceleration in a second direction at least partly transverse to the first direction. One or more micro-flameholders can be disposed within the combustor at or upstream of a location at which the flow is subject to the acceleration in the second direction. The one or more micro-flameholders can be configured to facilitate or promote Rayleigh-Taylor instability to cause interpenetration of the reactants and the combustion products within the combustor.Type: GrantFiled: August 4, 2016Date of Patent: September 29, 2020Assignee: Arizona Board of Regents on behalf of Arizona State UniversityInventor: Werner Dahm
-
Patent number: 9009966Abstract: The construction of an internal/external single expansion ramp nozzle (nxSERN), and method of designing the same, is provided. Initial design parameters for primary stream construction are selected and additional parameters are determined by isentropic relations using the selected design parameters and Prandtl-Meyer function. The nozzle throat input and output angles are determined and used to define an initial portion of the nozzle primary stream lower expansion surface. The nozzle primary stream upper expansion surface and an aft portion of the primary stream lower expansion surface are defined using a method of characteristics. Initial and aft portions of the primary stream lower expansion surface are then connected by a straight line to define the primary stream nozzle.Type: GrantFiled: March 15, 2013Date of Patent: April 21, 2015Assignee: Northrop Gurmman Systems CorporationInventors: Shane Bunnag, Gordon Hall, Kelly Strominger, John Tapee, Trajaen J. Troia
-
Patent number: 8973370Abstract: A supersonic nacelle design employing a bypass flow path internal to the nacelle and around the engine is disclosed herein. A set of aerodynamic vanes may be used to shape a supersonic airflow within a bypass around an engine. The vanes may be capable of compressing the supersonic airflow into a subsonic airflow, direct the subsonic airflow around the engine, and then expand the subsonic airflow into a supersonic exhaust. The vanes may shape the airflow by reducing sonic boom strength, cowl drag, and airframe interference drag.Type: GrantFiled: June 13, 2014Date of Patent: March 10, 2015Assignee: Gulfstream Aerospace CorporationInventor: Timothy R. Conners
-
Patent number: 8950172Abstract: The jet (40) has an air-fuel combustion chamber (42) and a plurality of rocket engines (11) arranged upstream from the combustion chamber (42), each rocket engine having its own combustion chamber with the wall thereof being cooled by lateral injection of fuel through said wall.Type: GrantFiled: July 10, 2009Date of Patent: February 10, 2015Assignee: SnecmaInventors: Daniel Peyrisse, Jean-Marie Conrardy
-
Publication number: 20140290259Abstract: 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.Type: ApplicationFiled: May 25, 2012Publication date: October 2, 2014Applicant: SOCPRA SCIENCES ET GENIE, S.E.C.Inventors: Jean-Sébastien Plante, Mathieu Picard, David Rarncourt
-
Publication number: 20140283521Abstract: 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.Type: ApplicationFiled: March 19, 2013Publication date: September 25, 2014Applicant: Hamilton Sundstrand CorporationInventors: Eric Chrabascz, William R. Fiske, David A. Dorman
-
Publication number: 20140230443Abstract: 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.Type: ApplicationFiled: September 11, 2012Publication date: August 21, 2014Inventors: Jean-Sebastien Plante, David Rancourt, Mathieu Picard
-
Patent number: 8783039Abstract: A supersonic nacelle design employing a bypass flow path internal to the nacelle and around the engine is disclosed herein. A set of aerodynamic vanes may be used to shape a supersonic airflow within a bypass around an engine. The vanes may be capable of directing the subsonic airflow around the engine, and then expanding the subsonic airflow into a supersonic exhaust. The vanes may shape the airflow by reducing sonic boom strength, cowl drag, and airframe interference drag.Type: GrantFiled: October 23, 2009Date of Patent: July 22, 2014Assignee: Gulfstream Aerospace CorporationInventor: Timothy R. Conners
-
Publication number: 20140196460Abstract: The invention relates to a ramjet including a detonation chamber and an aircraft comprising such a ramjet. According to the invention, the ramjet (S1) comprises an annular detonation chamber (2) having a continuous detonation wave and fuel injection means (6) for continuously injecting fuel (F2) directly into the chamber (2) just downstream of an air injection base (3). The fuel (F2) and the air (F1) are injected separately into the detonation chamber (2) in a permanent manner throughout the operation of the ramjet (S1).Type: ApplicationFiled: May 9, 2012Publication date: July 17, 2014Applicant: MBDA FRANCEInventors: François Falempin, Bruno Le Naour
-
Patent number: 8776526Abstract: The present invention provides a motor including a combustion chamber, an oxidizer injector, a vortex generators and a nozzle. The combustion chamber can be used to dispose a solid fuel, and the oxidizer injector is used to control the flow rate of an oxidizer and to inject the oxidizer into the combustion chamber. The vortex generators is disposed on the inner wall of the combustion chamber for generating eddies to enhance the mixing of the fuel and the oxidizer. Additionally, the nozzle is connected with the combustion chamber for exhausting the gas generated by the combustion of the propellants.Type: GrantFiled: February 1, 2011Date of Patent: July 15, 2014Assignee: National Applied Research LaboratoriesInventors: Yen-Sen Chen, Jong-Shinn Wu, Tzu-Hao Chou
-
Patent number: 8720205Abstract: With turbine segments controlled electrically in a shaftless design, the turbine of the present invention creates high propulsion efficiencies over a broader range of operating conditions through the integration of gas turbine, electric and magnetic power systems, advanced materials and alternative petroleum-based combustion cycles.Type: GrantFiled: September 11, 2006Date of Patent: May 13, 2014Inventor: Richard H. Lugg
-
Patent number: 8528341Abstract: 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.Type: GrantFiled: January 24, 2013Date of Patent: September 10, 2013Assignee: Grossi Aerospace, Inc.Inventor: Fabio G. Grossi
-
Patent number: 8484980Abstract: A new dual-mode ramjet combustor used for operation over a wide flight Mach number range is described. Subsonic combustion mode is usable to lower flight Mach numbers than current dual-mode scramjets. High speed mode is characterized by supersonic combustion in a free-jet that traverses the subsonic combustion chamber to a variable nozzle throat. Although a variable combustor exit aperture is required, the need for fuel staging to accommodate the combustion process is eliminated. Local heating from shock-boundary-layer interactions on combustor walls is also eliminated.Type: GrantFiled: September 30, 2010Date of Patent: July 16, 2013Assignee: The United States of America as Represented by the Administrator of National Aeronautics and Space AdministrationInventors: Charles J Trefny, Vance F Dippold
-
Publication number: 20130098045Abstract: 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.Type: ApplicationFiled: October 24, 2011Publication date: April 25, 2013Applicant: HAMILTON SUNDSTRAND CORPORATIONInventors: Lawrence Binek, Brent J. Merritt
-
Patent number: 8393158Abstract: A supersonic inlet with a cowl lip may be configured to capture the conic shock and exhibit a zero or substantially zero cowl angle. The inlet may be configured to employ a relaxed isentropic compression surface and an internal bypass. The nacelle bypass may prevent flow distortions, introduced by the capture of the conic shock, from reaching the turbomachinery, thereby allowing the cowl angle to be reduced to zero or substantially zero. Such a cowl angle may reduce the inlet's contribution to the overall sonic boom signature for a supersonic aircraft while allowing for an increase in engine pressure recovery and a subsequent improvement in generated thrust by the engine.Type: GrantFiled: December 7, 2007Date of Patent: March 12, 2013Assignee: Gulfstream Aerospace CorporationInventor: Timothy R. Conners
-
Patent number: 8381528Abstract: 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.Type: GrantFiled: February 1, 2008Date of Patent: February 26, 2013Assignee: Grossi Aerospace, Inc.Inventor: Fabio G. Grossi
-
Patent number: 8360097Abstract: Embodiments of a valve actuator are provided for adjusting the position of a main valve element in relation to the pressure of a fluid supplied by a supply duct. The valve actuator includes a housing, a control pressure valve disposed in the housing, and a piston slidably disposed in the housing and mechanically coupled to the main valve element. The housing has a control pressure chamber therein, which is configured to be fluidly coupled to the supply duct. The control pressure valve is configured to substantially impede fluid flow into the control pressure chamber until the fluid pressure within the supply duct surpasses a minimum actuation pressure. The piston normally resides in a first position and is configured to move toward a second position as the pressure within the control pressure chamber increases.Type: GrantFiled: April 22, 2008Date of Patent: January 29, 2013Assignee: Honeywell International Inc.Inventors: Justin A. Tanner, Larry Blessing, Doug Kortum, Benjamin Tang
-
Publication number: 20130014511Abstract: 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.Type: ApplicationFiled: January 4, 2012Publication date: January 17, 2013Inventor: Michael Gurin
-
Patent number: 8341963Abstract: In a valve control unit for a ram jet propulsion system having a power unit space a valve for controlling a fuel quantity required to the propulsion system, and a valve adjusting unit which is constructed to be operable by means of an electronic control unit, the valve is combined with its valve adjusting unit and its electronic control unit to form a thermally insulated valve assembly. The valve assembly is configured for the arrangement in the power unit space.Type: GrantFiled: March 3, 2008Date of Patent: January 1, 2013Assignee: LFK-Lenkflugkoerpersysteme GmbHInventors: Walter Hetzer, Ernst Lenz, Fridbert Kilger
-
Patent number: 8333076Abstract: A supersonic inlet employs relaxed isentropic compression to improve net propulsive force by shaping the compression surface of the inlet. Relaxed isentropic compression shaping of the inlet compression surface functions to reduce cowl lip surface angles, thereby improving inlet drag characteristics and interference drag characteristics. Supersonic inlets in accordance with the invention also demonstrate reductions in peak sonic boom overpressure while maintaining performance.Type: GrantFiled: December 15, 2006Date of Patent: December 18, 2012Assignee: Gulfstream Aerospace CorporationInventors: Timothy R. Conners, Donald C. Howe, Preston A. Henne
-
Patent number: 8327645Abstract: A supersonic inlet employs relaxed isentropic compression to improve net propulsive force by shaping the compression surface of the inlet. Relaxed isentropic compression shaping of the inlet compression surface functions to reduce cowl lip surface angles, thereby improving inlet drag characteristics and interference drag characteristics. Supersonic inlets in accordance with the invention also demonstrate reductions in peak sonic boom overpressure while maintaining performance.Type: GrantFiled: December 27, 2011Date of Patent: December 11, 2012Assignee: Gulfstream Aerospace CorporationInventors: Preston A. Henne, Timothy R. Conners, Donald C. Howe
-
Patent number: 8286434Abstract: A supersonic inlet employs relaxed isentropic compression to improve net propulsive force by shaping the compression surface of the inlet. Relaxed isentropic compression shaping of the inlet compression surface functions to reduce cowl lip surface angles, thereby improving inlet drag characteristics and interference drag characteristics. Supersonic inlets in accordance with the invention also demonstrate reductions in peak sonic boom overpressure while maintaining performance.Type: GrantFiled: December 27, 2011Date of Patent: October 16, 2012Assignee: Gulfstream Aerospace CorporationInventors: Preston A. Henne, Timothy R. Conners, Donald C. Howe
-
Publication number: 20120240550Abstract: A vehicle propulsion system having a manifold in fluid communication with a cross flow fan which adjusts to control an amount lift generated by a plurality of airfoils providing lift from air from the cross flow fan.Type: ApplicationFiled: April 4, 2012Publication date: September 27, 2012Inventors: Gordon S. Kolacny, Bruce A. Kolacny
-
Patent number: 8256203Abstract: The present disclosure generally pertains to rocket based combined cycle (RBCC) propulsion units. In one exemplary embodiment, at least one rocket thruster is integrated with a jet engine but is external to the flow path of the jet engine, forming an altitude compensating plug nozzle. Since the rocket thruster is external to such flow path, the rocket flow from the rocket thruster interacts with the jet flow from the jet engine aft of the nozzle of the jet engine. Such interaction occurs without a significant performance penalty in the operation of the jet engine. In fact, it is possible that the interaction of the rocket flow with the jet flow may actually improve the efficiency of the jet engine under some conditions. Moreover, having the rocket thrusters positioned external to the flow path of the jet engine helps to avoid many of the problems plaguing conventional RBCC propulsion units.Type: GrantFiled: January 28, 2008Date of Patent: September 4, 2012Assignee: The University of Alabama in HuntsvilleInventors: James B. Blackmon, David B. Landrum, Sean Entrekin
-
Publication number: 20120159956Abstract: 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.Type: ApplicationFiled: December 23, 2011Publication date: June 28, 2012Inventor: Michael Gurin
-
Publication number: 20120144836Abstract: 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.Type: ApplicationFiled: December 27, 2010Publication date: June 14, 2012Inventors: Robert A. Ress, JR., Randall E. Yount, Thomas D. Destefano, Jitendra R. Patel
-
Patent number: 8117847Abstract: A propulsion system, such as for use in a missile, includes a multinozzle grid having a pair of plates that are separably mechanically coupled together. When coupled together in a first configuration, the plates provide multiple nozzles in a first nozzle configuration (geometry). Separation of the plates, such as by separating an aft plate from a forward plate that remains with the missile, reconfigures the multinozzle grid to a second configuration that has nozzles in a second nozzle configuration (geometry). The nozzle configurations may be suitable for different types of propulsion mechanisms. The hybrid propulsion system utilizing the multinozzle grid may include a pair of pressurized gas sources, for example a solid rocket fuel and a combustion chamber for a ramjet.Type: GrantFiled: March 7, 2008Date of Patent: February 21, 2012Assignee: Raytheon CompanyInventors: Stephen D. Haight, Daniel Chasman, Juan A. Perez
-
Publication number: 20110146286Abstract: 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.Type: ApplicationFiled: February 28, 2011Publication date: June 23, 2011Inventor: THOMAS H. SHARPE
-
Patent number: 7954329Abstract: 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.Type: GrantFiled: February 1, 2008Date of Patent: June 7, 2011Assignee: Grossi Aerospace, Inc.Inventor: Fabio G. Grossi
-
Patent number: 7950235Abstract: A jet engine is constructed of a fanjet; a plurality of ramjets provided around said fanjet; a plurality of air flow spaces between said fanjet and said plurality of ramjets; and a cooling jacket provided around said plurality of ramjets.Type: GrantFiled: October 26, 2007Date of Patent: May 31, 2011Inventor: Donald Giddings
-
Patent number: 7937945Abstract: Units of engines are described herein. The units contain a unique combined-cycle (deflagration-detonation) “contra-rotation, anti-gyration, gyroscopic,” turbine fan-jet/free-piston engine configuration for induced air supercharging that boosts the performance of novel Ramjet engines or Ramjet engine configurations by improving internal air-stream dynamics. These dynamics are the result of co-operative air stream intermixing through convergent, supercharge-attenuated, inducted, compressed, tuned, pre-heated ambient air. Results are achieved through the varying of the geometric structural form and the utilization of unique engines and air induction and propulsion conformations, aided with supplemental air, fuel, oxygen and optional water and electrolyte charging.Type: GrantFiled: February 5, 2007Date of Patent: May 10, 2011Inventor: Ronald August Kinde, Sr.
-
Publication number: 20110100014Abstract: 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.Type: ApplicationFiled: October 30, 2009Publication date: May 5, 2011Inventors: Roderick A. Hyde, Muriel Y. Ishikawa, Edward K.Y. Jung, Jordin T. Kare, Nathan P. Myhrvold, Clarence T. Tegreene, Thomas A. Weaver, Lowell L. Wood, JR., Victoria Y.H. Wood
-
Patent number: 7849670Abstract: The present invention relates to a propulsion system for a vehicle. The propulsion system has an airframe integrated hydrocarbon fueled airbreathing engine, such as a ramjet or a scramjet. The propulsion system further has at least one rocket positioned so as to use the aft body contour of the vehicle directly for flow expansion. In a preferred embodiment, a plurality of rockets are arrayed across the width of the engine nozzle.Type: GrantFiled: April 15, 2003Date of Patent: December 14, 2010Assignee: United Technologies CorporationInventors: Stephen A. Beckel, James D. Blevins, Thomas Verdi
-
Publication number: 20100251692Abstract: The present invention generally relates to units of engines and more particularly to units containing a unique combined-cycle (combustion-detonation) “counter-rotation, anti-gyration, gyroscopic,” turbine fan-jet/free-piston engine configuration for induced air supercharging and boosting the performance of novel Ramjet engines or Ramjet engine configurations by improving internal air-stream dynamics. These dynamics are the result of co-operative air stream intermixing through convergent, supercharge-attenuated, inducted, compressed, tuned, pre-heated ambient air. Achieved through the varying of the geometric structural form and the utilization of unique engines and air induction and propulsion conformations, aided with supplemental air, fuel, oxygen and optiomal water and electrolyte charging.Type: ApplicationFiled: February 5, 2007Publication date: October 7, 2010Inventor: Ronald August Kinde, SR.
-
Patent number: 7797943Abstract: A pilot for a scramjet provides a flame front whose arrival at the wall of the scramjet combustor is delayed thereby reducing combustor heat load. By combining in-stream injection of fuel with an interior pilot and a lean (fuel-poor) outer annulus, the bulk of combustion is confined to the scramjet combustor center. This concept, referred to as “core-burning,” further reduces combustor heat load. One such pilot is for a two dimensional scramjet effective to propel a vehicle. This pilot includes a plurality of spaced apart struts separated by ducts and a strut pilot contained within each strut. A second such pilot is for an axisymmetric scramjet engine has, in sequence and in fluid communication, an air intake, an open bore scramjet isolator and a scramjet combustor. This centerbody pilot pod includes a pilot isolator disposed between the air intake and a pilot diffuser, the pilot diffuser disposed between the pilot isolator and a pilot with the pilot disposed between the pilot diffuser and a pilot combustor.Type: GrantFiled: October 18, 2006Date of Patent: September 21, 2010Assignee: Aerojet-General CorporationInventor: Melvin J. Bulman
-
Patent number: 7765790Abstract: A ramjet engine (3, 4, 5), flying at Mach 3 has 64% efficiency, and at Mach 4 has 76% efficiency. Ramjet engines are currently only used for supersonic flight and have not been used as stationary engines with mechanical output. The present invention, in addition to subsonic flight, can be operated as a stationary engine, and can expand the use of the ramjet engine for mechanical output in vehicles, power plants, and in generator sets for large buildings, homes, and industry. The present invention provides the means to use ramjet engines as stationary engines by building nearly adiabatic compressors (1, 2, 12, 13, 14, 15) and expanders (6, 7, 8, 9, 10, 11) capable of (de-)compression ratios up to about 92:1 to supply the high energy gas/air required by ramjet engines, and shows how to replace de Laval nozzles with sonic converters (49, 50, 51) that convert supersonic to subsonic flow and sonic converters (45, 46, 47) that convert subsonic to supersonic flow without having choke areas.Type: GrantFiled: March 25, 2009Date of Patent: August 3, 2010Assignee: Amicable Inventions LLCInventors: Rufus G. Clay, Robert G. Hockaday
-
Patent number: 7762077Abstract: A single-stage hypersonic vehicle is comprised of a low-speed and a high-speed propulsion system. The low-speed propulsion system propels the single-stage vehicle to a threshold velocity, after which the high-speed propulsion system then takes over. The low-speed propulsion system includes a combined-cycle engine featuring a swirl generator that is integrated into a turbojet engine to provide a compact turbojet and swirl afterburner-ramjet propulsion system. The high-speed propulsion system includes a hypersonic engine that is operable at the threshold takeover velocity and beyond. In various embodiments, the high-speed propulsion system comprises a scramjet, rocket, or scramjet/rocket engine depending requirements.Type: GrantFiled: December 5, 2006Date of Patent: July 27, 2010Assignee: Pratt & Whitney Rocketdyne, Inc.Inventors: Robert J. Pederson, Stephen N. Schmotolocha, William W. Follett
-
Publication number: 20100126178Abstract: 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.Type: ApplicationFiled: October 30, 2009Publication date: May 27, 2010Inventors: Roderick A. Hyde, Muriel Y. Ishikawa, Edward K.Y. Jung, Jordin T. Kare, Nathan P. Myhrvold, Clarence T. Tegreene, Thomas A. Weaver, Lowell L. Wood, JR., Victoria Y.H. Wood
-
Publication number: 20100083668Abstract: 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 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 a torque. The hybrid propulsive technique also comprises rotating an at least one independently rotatable compressor stator at least partially responsive to the converting the at least a portion of the electrical power to the torque.Type: ApplicationFiled: October 8, 2008Publication date: April 8, 2010Inventors: Glenn B. Foster, Roderick A. Hyde, Muriel Y. Ishikawa, Edward K.Y. Jung, Jordin T. Kare, Nathan P. Myhrvold, Clarence T. Tegreene, Thomas Allan Weaver, Lowell L. Wood, JR., Victoria Y.H. Wood
-
Patent number: 7685824Abstract: A Brayton-cycle rotary ramjet engine (10) operated within the confines of a helically elongated pass-through duct formed between a preferably stationary radially outward surface (14) and an outer rotating flow channel (36). The flow channel (36) is contoured between its inlet (34) and outlet (38) to include a supersonic diffuser (40), a combustor (42) and an expansion nozzle (44). Gaseous fuel, or liquid fuel atomized by a fuel slinger (58) within a housing (46), or solid fuel in the form of fine particulates, is inter-mixed with an oxidizer prior to being directed to the flow channel inlets (34). The air and fuel are combusted in the flow channels (36) and exhausted through the rear of the housing (46). A generator (22) can be coupled to a power shaft (18) to convert net shaft power into electricity. Preferably, the rotor (24) and stator (12) are fabricated from a ceramic or other high-temperature material so that combustor exit temperatures (T3) can be operated at highly efficient levels.Type: GrantFiled: January 5, 2006Date of Patent: March 30, 2010Assignee: The Regents of the University of MichiganInventor: Werner J. A. Dahm
-
Publication number: 20090241549Abstract: A ramjet engine (3, 4, 5), flying at Mach 3 has 64% efficiency, and at Mach 4 has 76% efficiency. Ramjet engines are currently only used for supersonic flight and have not been used as stationary engines with mechanical output. The present invention, in addition to subsonic flight, can be operated as a stationary engine, and can expand the use of the ramjet engine for mechanical output in vehicles, power plants, and in generator sets for large buildings, homes, and industry. The present invention provides the means to use ramjet engines as stationary engines by building nearly adiabatic compressors (1, 2, 12, 13, 14, 15) and expanders (6, 7, 8, 9, 10, 11) capable of (de-)compression ratios up to about 92:1 to supply the high energy gas/air required by ramjet engines, and shows how to replace de Laval nozzles with sonic converters (49, 50, 51) that convert supersonic to subsonic flow and sonic converters (45, 46, 47) that convert subsonic to supersonic flow without having choke areas.Type: ApplicationFiled: March 25, 2009Publication date: October 1, 2009Inventors: Rufus G. Clay, Robert G. Hockaday
-
Publication number: 20090162213Abstract: The present invention provides a fluid pumping ejector. The ejector includes a reservoir containing a primary fluid and a mixing duct. An ejector nozzle ejects the primary fluid from said reservoir into the mixing duct to entrain a secondary fluid and create a mixed flow with sufficient momentum and internal energy to achieve characteristic speed. A subsonic converging nozzle is coupled to the mixing duct downstream of the ejector nozzle and provides a characteristic cross section necessary for the mixed flow to achieve characteristic speed as it moves through said converging nozzle, thereby producing a standing shock wave at the point of maximum convergence of the nozzle. The ejector nozzle is fully-expanded, wherein exit speed of the primary fluid is supersonic and exit static pressure of the primary fluid is equal to secondary fluid pressure.Type: ApplicationFiled: February 1, 2008Publication date: June 25, 2009Inventor: Fabio G Grossi
-
Publication number: 20090158744Abstract: 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.Type: ApplicationFiled: February 1, 2008Publication date: June 25, 2009Inventor: Fabio G. Grossi
-
Publication number: 20090158745Abstract: 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.Type: ApplicationFiled: February 1, 2008Publication date: June 25, 2009Inventor: Fabio G. Grossi
-
Publication number: 20090094987Abstract: 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.Type: ApplicationFiled: December 16, 2008Publication date: April 16, 2009Applicant: LOCKHEED MARTIN CORPORATIONInventors: Bradley C. Leland, John D. Klinge, Brian F. Lundy
-
Publication number: 20090071120Abstract: An engine that operates and produces the entire required vehicle thrust below Mach 4 is useful for a Hypersonic combined cycle vehicle by saving vehicle and engine development costs. One such engine is a combined cycle engine having both a booster and a dual mode ramjet (DMRJ). The booster and the DMRJ are integrated to provide effective thrust from Mach 0 to in excess of Mach 4. As the booster accelerates the vehicle from Mach 0 to in excess of Mach 4, from Mach 0 to about Mach 2 incoming air delivered to the DMRJ is accelerated by primary ejector thrusters that may receive oxidizer from either on-board oxidizer tanks or from turbine compressor discharge air. As the TBCC further accelerates the vehicle from about Mach 0 to in excess of Mach 4 exhaust from the turbine and exhaust from the DMRJ are combined in a common nozzle disposed downstream of a combustor portion of said DMRJ functioning as an aerodynamic choke.Type: ApplicationFiled: December 18, 2006Publication date: March 19, 2009Inventor: Melvin J. Bulman
-
Publication number: 20080264385Abstract: In a valve control unit for a ram jet propulsion system having a power unit space a valve for controlling a fuel quantity required to the propulsion system, and a valve adjusting unit which is constructed to be operable by means of an electronic control unit, the valve is combined with its valve adjusting unit and its electronic control unit to form a thermally insulated valve assembly. The valve assembly is configured for the arrangement in the power unit space.Type: ApplicationFiled: March 3, 2008Publication date: October 30, 2008Applicant: LFK-Lenkflugkoerpersysteme GmbHInventors: Walter Hetzer, Ernst Lenz, Fridbert Kilger