With Plural Selectively Usable Motive Fluid Ejecting Means Patents (Class 60/229)
  • Patent number: 11047336
    Abstract: A gas turbine engine that includes a nozzle assembly that has features that facilitate airflow into and through a bypass passage of the gas turbine engine during a reverse thrust operation is provided. The nozzle assembly of the gas turbine engine also includes features that increase the effectiveness of the thrust reverse system of the gas turbine engine. Methods for reversing the thrust of a gas turbine engine are also provided.
    Type: Grant
    Filed: February 20, 2019
    Date of Patent: June 29, 2021
    Assignee: GENERAL ELECTRIC COMPANY
    Inventor: Tomasz Iglewski
  • Patent number: 10865737
    Abstract: A system and method for an improved thrust reverser is provided. The provided thrust reverser employs hidden linkage assemblies to decrease drag in the engine exhaust flow and increase turbine engine performance. The hidden linkage assemblies are placed in a space between the blocker door and the transcowl, thereby not affecting the engine exhaust flow.
    Type: Grant
    Filed: August 29, 2017
    Date of Patent: December 15, 2020
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Danis Burton Smith, Alexandre Guerinot, Remo Neri, James Thomas Ayers, III
  • Patent number: 10837404
    Abstract: An assembly is provided for an aircraft propulsion system. This assembly includes a fixed structure, a translating structure, a blocker door and a rigid linkage. The translating structure is configured to translate relative to the fixed structure. The blocker door extends between a blocker door first end and a blocker door second end. The translating structure is pivotally attached to the blocker door at the blocker door first end. The rigid linkage includes a first pivot attachment, a second pivot attachment and a third pivot attachment. The first pivot attachment is coupled to the fixed structure. The second pivot attachment is coupled to the translating structure. The third pivot attachment is coupled to the blocker door at the blocker door second end.
    Type: Grant
    Filed: July 10, 2018
    Date of Patent: November 17, 2020
    Assignee: Rohr, Inc.
    Inventors: Peter W. Aziz, Pablo T. Sanz Martinez
  • Patent number: 10794328
    Abstract: An assembly is provided for an aircraft propulsion system. This assembly includes a fixed structure, a translating structure, a blocker door and a folding linkage. The translating structure is configured to move between a stowed position and a deployed position. The blocker door is pivotally attached to the translating structure at a first pivot joint. The folding linkage links the blocker door to the fixed structure. The folding linkage includes a member pivotally attached to the blocker door at a second pivot joint that is radially outboard of a skin of the blocker door when the translating structure is in the stowed position. The second pivot joint is radially outboard of the first pivot joint when the translating structure is in the stowed position.
    Type: Grant
    Filed: July 6, 2018
    Date of Patent: October 6, 2020
    Assignee: Rohr, Inc.
    Inventor: Timothy Gormley
  • Patent number: 10731603
    Abstract: A nacelle for a turbofan including a mobile cowl mobile in translation between a closing position and an opening position, a window on the upstream side by a fixed cowl and on the downstream side by the mobile cowl, and a reverser flap in rotation between a closed position and an open position. The nacelle includes a locking system with a groove fixed to the mobile cowl and extending between a first end and a second end, and a guided element mounted guided in the slide and fixed to the reverser flap, the guided element moving from the second end towards the first end with cowl movement and leaving the groove when the reverser flap begins rotation, and the guided element moving outside the groove while the reverser flap pivots from the positions and entering the groove at the end of rotation of the reverser flap.
    Type: Grant
    Filed: March 21, 2018
    Date of Patent: August 4, 2020
    Assignee: Airbus Operations (S.A.S.)
    Inventor: Nicolas Jolivet
  • Patent number: 10641206
    Abstract: The present disclosure provides a nacelle rear assembly for turbojet engine including at least one thrust reverser device to redirect air flow circulating from upstream to downstream in a flow path of the turbojet engine and a mast to link the nacelle to a structure of the aircraft. In one form, the nacelle extends longitudinally from forth to back along an axis and includes a cradle fastened on the mast. In one form, the cradle includes a first longeron and a second longeron extending longitudinally on either side of the mast. The first and second longeron each include a sliding guide device for sliding of a movable cowl and of a cascade of the thrust reverser device.
    Type: Grant
    Filed: July 19, 2017
    Date of Patent: May 5, 2020
    Assignee: SAFRAN NACELLES
    Inventors: Patrick Boileau, Olivier Kerbler, Julien Lezerac, Armel Gautier, Loïc Grall, Ludovic Toupet
  • Patent number: 10590886
    Abstract: The present disclosure relates to an aircraft turbojet engine nacelle, the nacelle including a rear section without a lower bifurcation, the rear section including a thrust reversal system, the thrust reversal system including a mobile cowl. The nacelle includes a guide system that translates as one with the mobile cowl, the guide system collaborating with at least one slide that is fixed in relation to the nacelle, the guide system and the slide being arranged near the position referred to as the 6 o'clock position.
    Type: Grant
    Filed: July 20, 2017
    Date of Patent: March 17, 2020
    Assignee: SAFRAN NACELLES
    Inventors: Olivier Kerbler, Fabrice Henri Emile Metezeau, Patrick Gonidec, Loïc Grall
  • Patent number: 10563617
    Abstract: Electrically operated propellant is used to supplement the thrust provided by solid rocket motor (SRM) propellant to manage thrust produced by a SRM. The gas produced by burning the electrically operated propellant may be injected upstream of the nozzle to add mass and increase chamber pressure Pc, injected at the throat of the nozzle to reduce the effect throat area At to increase chamber pressure Pc or injected downstream of the throat to provide thrust vector control or a combination thereof. Certain types of electrically operated propellants can be turned on and off provided the chamber pressure Pc does not exceed a self-sustaining threshold pressure eliminating the requirement for physical control valves.
    Type: Grant
    Filed: September 23, 2016
    Date of Patent: February 18, 2020
    Assignee: Raytheon Company
    Inventors: James K. Villarreal, Mark T. Langhenry, Matt H. Summers
  • Patent number: 9217390
    Abstract: A thrust reverser system for a gas turbine engine includes a duct including a cowling movable between an open position and a closed position in a direction transverse to a centerline of the gas turbine engine. The thrust reverser is supported within the cowling and movable between an axial closed position, an axial intermediate position and an axial open position. A controller is actuateable to command movement of the thrust reverser from the axial closed position to the axial intermediate position such that the cowling is free to move to the open position.
    Type: Grant
    Filed: June 28, 2012
    Date of Patent: December 22, 2015
    Assignee: United Technologies Corporation
    Inventors: James L. Lucas, Michael Charron
  • Patent number: 9188026
    Abstract: A nacelle for housing an engine includes a fan cowl sized to cover at least a first axial portion of the engine. The engine includes an inlet end, an exhaust end, and an axis extending through the engine from the inlet end through the exhaust end. The fan cowl is coupled to an engine mounting pylon via a slider-type mounting system that includes at least one slider track assembly defining at least one slot therein. The at least one slot is configured to receive at least one fan cowl slider fitting.
    Type: Grant
    Filed: June 15, 2012
    Date of Patent: November 17, 2015
    Assignee: MRA Systems, Inc.
    Inventors: David P. Calder, Graham F. Howarth
  • Patent number: 9115668
    Abstract: The present invention relates to a thrust reversal device (1) for a turbojet engine nacelle, characterized in that: (i) the movable cowl (3) is provided with at least one driving lead screw (30) having at least one peripheral groove over at least part of the length thereof, whereby said groove can engage with a stationary guide means (31) of the nacelle so as to rotate the lead screw during the translational movement of the movable cowl; and (ii) the lead screw is associated with at least one means for transmitting (32, 35, 36) the rotational movement thereof towards at least one drive system (33, 34, 25) of the flap.
    Type: Grant
    Filed: July 15, 2010
    Date of Patent: August 25, 2015
    Assignee: AIRCELLE
    Inventor: Guy Bernard Vauchel
  • Patent number: 9115602
    Abstract: A turbine exhaust diffuser for a gas turbine engine. The diffuser includes a flow ramp positioned on an ID flowpath boundary within a flowpath of the diffuser. The flow ramp extends circumferentially about the hub and includes a downstream, radially outward point that extends radially outward further from the ID flowpath boundary than an upstream, radially outward point that is positioned upstream from the downstream, radially outward point. A wavy portion is located at the downstream, radially outward point of the flow ramp. The wavy portion includes a circumferentially extending, undulating surface defined by alternating axially extending crests and troughs.
    Type: Grant
    Filed: October 15, 2013
    Date of Patent: August 25, 2015
    Assignee: Siemens Aktiengesellschaft
    Inventors: Anthony J. Malandra, John A. Orosa
  • Publication number: 20140360157
    Abstract: A rocket vehicle includes a controller that integrates operation of a variable-vector main thruster and attitude control thrusters. When the main thruster is firing and roll is commanded, the controller can provide roll moment by firing only a single attitude control thruster, while changing the thrust vector of the main thruster to offset any pitch/yaw moments induced by the firing of the single attitude control thruster. The single attitude control thruster may be a thruster on the leeward side of the rocket vehicle. Since there is a lower wall pressure on the leeward side of the rocket vehicle, the thruster efficiency is improved by accomplishing roll by use of a single thruster (which may be one of a pair of thrusters used to achieve roll in one direction). A significant reduction in fuel use may be accomplished.
    Type: Application
    Filed: June 7, 2013
    Publication date: December 11, 2014
    Inventors: Michael A. Barker, Dean W. Smith, Edward J. Marquart, Joseph R. Corrado
  • Patent number: 8746613
    Abstract: A first trailing edge portion of a scarfed jet engine exhaust nozzle aft of a second trailing edge portion relative to a central axis of an associated exhaust duct causes an automatic nozzle-pressure-ratio responsive transverse deflection of the associated exhaust flow away from the first trailing edge portion. When offset from both the center of gravity (CG) and the central longitudinal axis of an aircraft, at a relatively low nozzle pressure ratio, e.g. during takeoff, the thrust vector from the exhaust flow acts relatively close to the CG, whereas at a relatively high nozzle pressure ratio, e.g. during relatively high-speed cruise, the scarfed exhaust nozzle deflects the exhaust flow so that the resulting thrust vector is relatively parallel to the path of the aircraft. With the final portion of the exhaust duct skewed, the primary axis of the jet engine can be relatively parallel to the path of the aircraft.
    Type: Grant
    Filed: August 20, 2009
    Date of Patent: June 10, 2014
    Assignee: Williams International Co., L.L.C.
    Inventors: Mark E. Suchezky, Lisa M. Simpkins
  • Publication number: 20130219858
    Abstract: A turbine engine exhaust nozzle includes a core gas duct, a nozzle duct, and a thrust vectoring duct system having a duct valve, a first vectoring duct and a second vectoring duct. The nozzle duct directs a first portion of core gas from the core gas duct through a nozzle duct outlet along a centerline. The duct valve connects the core gas duct to the first vectoring duct during a first mode of operation, and connects the core gas duct to the second vectoring duct during a second mode of operation. The first vectoring duct directs a second portion of core gas from the core gas duct through a first vectoring duct outlet along a first trajectory. The second vectoring duct directs a third portion of core gas from the core gas duct through a second vectoring duct outlet along a second trajectory that is angularly offset to the first trajectory.
    Type: Application
    Filed: February 23, 2012
    Publication date: August 29, 2013
    Applicant: United Technologies Corporation
    Inventor: Wendell V. Twelves, JR.
  • Patent number: 8387360
    Abstract: An apparatus for vectoring the thrust of a motor that produces thrust along a longitudinal axis by expelling combustion gases through a nozzle may include a plurality of linearly-positionable non-rotatable thrust deflectors. The thrust deflectors may be disposed at around a perimeter of the nozzle. Each thrust deflector may be independently extended to simultaneously generate both a force transverse to the longitudinal axis and a torque about the longitudinal axis.
    Type: Grant
    Filed: May 19, 2009
    Date of Patent: March 5, 2013
    Assignee: Raytheon Company
    Inventors: Lloyd E. Kinsey, Robert J. Cavalleri
  • Patent number: 8312705
    Abstract: A gas control valve is configured to controllably supply propellant gas to a thruster so that the thruster may produce thrust over a relatively wide range, and so that the thruster exhibits relatively fine minimum impulse bit (MIB) performance. The gas control valve includes a pilot stage having a pilot valve, and a main stage having a main valve. The gas control valve responds to control signals supplied to the pilot stage and is configured such that for commands of relatively short duration, only the pilot valve responds. Conversely, for commands of relatively longer duration, the pilot valve and main valve both respond.
    Type: Grant
    Filed: August 12, 2008
    Date of Patent: November 20, 2012
    Assignee: Honeywell International Inc.
    Inventors: Don Christensen, Steve Abel, Raymond R. Tseng
  • Patent number: 8291691
    Abstract: A multi-pulse rocket is equipped with a thermally insulating barrier that serves as a rupture disk or a movable plug or plate separating staged propellant grains. When a rupture disk it used, the disk can be equipped with a pyrotechnic actuator to weaken the disk upon command, enabling the propellant grain on the fore side of the disk to burst the disk at a relatively low pressure when ignition of the propellant grain is needed for additional thrust. Rupturing of the disk can also be controlled by attitude maneuvering ports on the fore side of the barrier whose open or closed conditions are controlled by independently operable closures. When a movable plug is used, the plug is movable between a closed position separating rocket chamber into subchambers isolating the propellant grains from each other and an open position allowing the flow of combustion gas between the two subchambers to achieve additional axial thrust.
    Type: Grant
    Filed: March 4, 2008
    Date of Patent: October 23, 2012
    Assignee: Aerojet-General Corporation
    Inventors: Guy B. Spear, Katherine L. Clopeck, Richard T. Brown, Michael Digiacomo, William M. Wallace
  • Publication number: 20120256044
    Abstract: One embodiment of the present invention is a unique flight vehicle. Another embodiment is a unique propulsion system. Another embodiment is a unique thrust vectoring system. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for flight vehicles, propulsion systems and thrust vectoring systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.
    Type: Application
    Filed: December 23, 2011
    Publication date: October 11, 2012
    Inventor: Bryan Henry Lerg
  • Publication number: 20120233983
    Abstract: Improved rocket nozzle designs for vehicles with nozzles embedded in or protruding from surfaces remote from the desired thrust axis. The nozzle configurations are for rocket vehicles where the nozzles are not located at the optimal thrust axis of the vehicle. Two examples include nozzles located on the forward end of the vehicle (also called tractor nozzles) and attitude control nozzles located on the periphery of the vehicle. More particularly, the disclosed nozzle shapes enhance the axial thrusts and/or maneuver torques on the vehicle. These unconventional nozzle shapes improve vehicle performance.
    Type: Application
    Filed: May 3, 2012
    Publication date: September 20, 2012
    Applicant: AEROJET-GENERAL CORPORATION
    Inventor: Melvin J. Bulman
  • Patent number: 8245496
    Abstract: Control and/or drive device for a flying body for ejecting hot gas streams of a combusted fuel combination of at least a first and second component. Device includes a first hollow chamber body structured and arranged to contain first component, a second hollow chamber body structured and arranged to contain second component, a controllable fuel valve arranged between first hollow chamber body and second hollow chamber body to control feed of first component to second hollow chamber body, and a plurality of outlets structured and arranged to eject respective hot gas streams for influencing a flight path of flying body. Second hollow chamber body is formed as a combustion chamber for combusting the at least first and second components within second hollow chamber body to generate respective hot gas streams, and plurality of outlets are connected to the second hollow chamber body.
    Type: Grant
    Filed: March 19, 2010
    Date of Patent: August 21, 2012
    Assignee: Astrium GmbH
    Inventor: Thomas Maier
  • Patent number: 8215096
    Abstract: An outlet device for a jet engine comprises a number of fixed ducts, each with a gas intake and a gas outlet for conducting a gas from the jet engine, at least two of the outlets of said gas ducts open in different directions, and a gas distribution arrangement is arranged at the gas intakes for selective distribution of the gas to the ducts.
    Type: Grant
    Filed: October 20, 2005
    Date of Patent: July 10, 2012
    Assignee: Volvo Aero Corporation
    Inventors: Anders Lundbladh, Melker Härefors, Richard Avellán
  • Publication number: 20120137653
    Abstract: A deployable raceway harness assembly for use with a multi-stage rocket includes a first cable bundle configured to extend across a second stage of a multi-stage rocket from a guidance unit to a first stage of the rocket. The deployable raceway harness assembly includes a deployable raceway cover configured for detachable coupling with the multi-stage rocket. The deployable raceway cover extends over at least the first cable bundle and a second cable bundle. The first cable bundle is fastened to the deployable raceway cover. The second cable bundle is configured to extend from the guidance unit to the second stage and is shorter than the first cable bundle. An in-flight deployment mechanism is configured to detach the deployable raceway cover and the first cable bundle extending across the second stage from the multi-stage rocket in-flight leaving the second cable bundle extending to the second stage in place.
    Type: Application
    Filed: December 2, 2010
    Publication date: June 7, 2012
    Applicant: Raytheon Company
    Inventors: Andrew B. Facciano, Sandie Y. Worley, Robert D. Travis, Dale O. Widmer
  • Patent number: 8186145
    Abstract: Improved rocket nozzle designs for vehicles with nozzles embedded in or protruding from surfaces remote from the desired thrust axis. The nozzle configurations are for rocket vehicles where the nozzles are not located at the optimal thrust axis of the vehicle. Two examples include nozzles located on the forward end of the vehicle (also called tractor nozzles) and attitude control nozzles located on the periphery of the vehicle. More particularly, the disclosed nozzle shapes enhance the axial thrusts and/or maneuver torques on the vehicle. These unconventional nozzle shapes improve vehicle performance.
    Type: Grant
    Filed: February 26, 2008
    Date of Patent: May 29, 2012
    Assignee: Aerojet-General Corporation
    Inventor: Melvin J. Bulman
  • Patent number: 8128352
    Abstract: The invention relates to a turbomachine thermomechanical part forming a body of revolution about a longitudinal axis, and including at least one abradable ring for a labyrinth seal. In characteristic manner, the abradable ring is made up of angular sectors that present different stiffnesses between adjacent pairs of sectors. The invention is applicable to a compressor, a turbine, or to a rotor and stator assembly.
    Type: Grant
    Filed: April 23, 2009
    Date of Patent: March 6, 2012
    Assignee: SNECMA
    Inventors: Mathieu Caucheteux, Francois Maurice Garcin, Jean-Pierre Francois Lombard, Nicolas Christian Triconnet
  • Publication number: 20120011828
    Abstract: A propulsion system may include a cylindrical support member and a tubular rotatable member rotatably mounted within the support member that may be adapted to permit fluid flow therethrough. The tubular rotatable member may extend past a down stream end of the support member. An exemplary embodiment of a propulsion system may also disclose a vane attached on an interior surface of the tubular member and may include a blade which extends in a direction toward a rotational axis of the rotatable member such that rotation of the tubular member and the vane attached thereon draws fluid into the tubular member to accelerate the fluid flow through the tubular member. Additionally, a nozzle may be attached to the down stream end of the support member and include a primary nozzle and a secondary nozzle within the primary nozzle. The secondary nozzle may be engaged with the primary nozzle by a stator.
    Type: Application
    Filed: September 23, 2011
    Publication date: January 19, 2012
    Inventor: Hugh B. NICHOLSON
  • Patent number: 8020365
    Abstract: A gas turbine engine comprising a compressor, a combustion chamber, and at least two turbines mounted oppositely to the combustion chamber, such that the gas turbine engine is capable of generating multidirectional thrust.
    Type: Grant
    Filed: June 13, 2008
    Date of Patent: September 20, 2011
    Inventor: Kamyar Brothers
  • Patent number: 7980058
    Abstract: The present invention relates to an air compression type engine for aviation. The conventional aircraft engine is complicated in structure, consumes expensive aero fuel, and produces extremely loud noise during operation. Therefore, the present invention employs a turbo-charged air compressor to generate high temperature and high pressure gas in the pressure chamber, and uses the reaction thrust force generated by ejecting the compressed air through the nozzle to make the aircraft vertically take off/land, suspend in the air and fly forwardly. Benefited from the simple structure, the manufacture cost of the aircraft engine can be dramatically decreased. Vertically raising and landing the aircraft can be achieved by changing the ejection directed of the compressed air in the pressure chamber. The commonly used gasoline or diesel, which is cost saving and capable of combusting with a high combustion value, can be used instead of the expensive aviation kerosene. Further, the generated noise is quite small.
    Type: Grant
    Filed: April 19, 2006
    Date of Patent: July 19, 2011
    Inventor: Stanley Chang
  • Publication number: 20110168833
    Abstract: The present invention describes an aircraft having a rotating engine. The aircraft comprises a means for rotating the engine 360° to allow directional control of the aircraft via rotation of the engine's thrust output. The aircraft can further comprise a plurality of flap members located on the wings of the aircraft and in communication with the rotating gas turbine engine to further control and stabilize flight of the aircraft. The gas turbine engine of the aircraft can comprise a compressor, a combustion chamber, and at least two turbines mounted oppositely to the combustion chamber, such that the gas turbine engine is capable of generating more thrust from a single engine.
    Type: Application
    Filed: April 6, 2010
    Publication date: July 14, 2011
    Inventor: Kamyar Brothers
  • Patent number: 7958718
    Abstract: A multiple-stage solid rocket motor is operated in a manner designed to control its mass discharge profile. This is accomplished by providing means for igniting one stage and then igniting a subsequent stage while the first continues to burn.
    Type: Grant
    Filed: July 7, 1989
    Date of Patent: June 14, 2011
    Assignee: Alliant Techsystems Inc.
    Inventors: L. Don Berchtold, Ralph S. Tappan
  • Patent number: 7856806
    Abstract: A propulsion system includes a canted multinozzle plate, which has a multitude of small nozzles angled (not perpendicular) to major surfaces of the multinozzle grid plate. The multinozzle plate may be a cylindrical section or plate, and the multitude of nozzles may be substantially axisymmetric about the cylindrical plate. The propulsion system includes a pressurized gas source which may be placed either forward or aft of the multinozzle grid plate. The propulsion system may have a conical insert, an internal flow separator cone, to aid in changing directions of flow from the pressurized gas source, to divert the flow through the multiple nozzles.
    Type: Grant
    Filed: November 6, 2006
    Date of Patent: December 28, 2010
    Assignee: Raytheon Company
    Inventors: Daniel Chasman, Stephen D. Haight
  • Patent number: 7784284
    Abstract: A propulsion gas exhaust assembly in an aircraft propelled by hot gases produced along the axis of the latter by a gas generator is disclosed. The exhaust assembly includes a duct which forms a vertical elbow and a nozzle.
    Type: Grant
    Filed: April 27, 2007
    Date of Patent: August 31, 2010
    Assignee: SNECMA
    Inventors: Edgar Brunet, Thomas Daris, Alain Pierre Page, Jackie Raymond Julien Prouteau
  • Patent number: 7735778
    Abstract: The thrust reverser is used with a gas turbine engine and includes first and second doors pivotable between a stowed position and a deployed position. When deployed, pivoting fairings on the first door are moved so as to give room to the second door as its trailing edge moves within the first door. When stowed, the second door preferably provides the locking mechanism to the pivoting fairings of the first door.
    Type: Grant
    Filed: November 16, 2007
    Date of Patent: June 15, 2010
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Jean-Pierre Lair, Paul Weaver
  • Publication number: 20100140388
    Abstract: An aircraft air cushion landing system (2) includes a skirt (6) defining a plenum (22) on an underside of the aircraft, a plenum fan (26) arranged to induce an airflow into the plenum (22) and controller configured to control operation of the plenum fan (26). The controller includes a sensor (30) adapted to sense an imminent landing event and a fan control system (28) configured to automatically operate the plenum fan (26) to provide a first flow in a first direction out of the plenum (22) so that as the skirt (6) engages a landing surface air is being evacuated from the plenum (22). A method also operates such a system (2).
    Type: Application
    Filed: September 22, 2009
    Publication date: June 10, 2010
    Applicant: Air Cushion Landing Systems Limited
    Inventors: Russell John London, Malcolm John COX
  • Patent number: 7716912
    Abstract: A propulsion thrust control system and method for controlling thrust in a rocket motor includes configuring valves of an energized rocket motor to an initial total valve area according to a total thrust command. The total thrust command is converted into a commanded propellant mass flow discharge rate. A varying total valve area is computed from an error between the commanded propellant mass flow discharge rate and a calculated propellant mass flow discharge rate. The valves are reconfigured according to a distribution of the varying total valve area. The propulsion system includes a pressure vessel with valves and a controller for regulating the valve area according to a propellant mass flow discharge rate from the pressure vessel.
    Type: Grant
    Filed: March 2, 2006
    Date of Patent: May 18, 2010
    Assignee: Alliant Techsystems Inc.
    Inventors: Cary Lee Cover, Sean Scott Stroud, Michael Joseph Piovoso, Timothy James Kelly
  • Patent number: 7707820
    Abstract: Control and/or drive device for a flying body for ejecting hot gas streams of a combusted fuel combination of at least a first and second component. Device includes a first hollow chamber body structured and arranged to contain first component, a second hollow chamber body structured and arranged to contain second component, a controllable fuel valve arranged between first hollow chamber body and second hollow chamber body to control feed of first component to second hollow chamber body, and a plurality of outlets structured and arranged to eject respective hot gas streams for influencing a flight path of flying body. Second hollow chamber body is formed as a combustion chamber for combusting the at least first and second components within second hollow chamber body to generate respective hot gas streams, and plurality of outlets are connected to the second hollow chamber body.
    Type: Grant
    Filed: September 19, 2005
    Date of Patent: May 4, 2010
    Assignee: Astrium GmbH
    Inventor: Thomas Maier
  • Patent number: 7665294
    Abstract: Apparatus including an exhaust nozzle assembly having a translatable structure operable to open and close a flow diverting port in an exhaust duct. The translatable structure includes a forward region partly defining a converging nozzle region. The translatable structure includes a rearward region partly defining a diverging nozzle region. The forward region and the rearward region join at an inner edge that partly defines a throat constriction. The translatable structure is translatable between a plurality of operational positions each associated with a longitudinal position of the throat constriction. In a first operational position, the flow diverting port is fully closed. In a second operational position, the flow diverting port is fully opened. In a first intermediate operational position, the flow diverting port is fully closed. In a second intermediate operational position, the flow diverting port is at least partly opened.
    Type: Grant
    Filed: December 27, 2006
    Date of Patent: February 23, 2010
    Assignee: General Electric Company
    Inventors: Thomas Anthony Hauer, Cy W. Overbeck
  • Patent number: 7631486
    Abstract: The present invention relates to a thrust orienting nozzle, shaped in such a way as to divide a principal propulsion gas flow coming from at least one gas generator into a first flow and a second flow for an ejection in a first half-nozzle and in a second half-nozzle and comprising at least one of following two piloting means: a means of dividing the principal flow into each of the two half-nozzles, and a means of orienting the thrust vector produced by each of the two half-nozzles. The invention applies in particular to the yaw control of an aircraft without a vertical tail unit.
    Type: Grant
    Filed: June 29, 2006
    Date of Patent: December 15, 2009
    Assignee: SNECMA
    Inventors: Alain Page, Jackie Prouteau, Thomas Daris, Marc Doussinault, Frederic Schenher
  • Patent number: 7628006
    Abstract: Disclosed is an abrupt opening apparatus of a pressurized chamber in an intended procedure to accomplish thrust termination for a stage separation of the solid rocket motor. It can open trust termination ports with simple mechanical structure to thereby terminate the normal thrust of a nozzle reliably, if it is intended to terminate the normal thrust produced from the nozzle of the rocket motor to thereby impede the forward movement of the rocket motor by producing the reverse thrust. The thrust termination device for the rocket motor comprises a closure 210 for closing the thrust termination ports in an air-tight structure; a snap ring 220 for supporting the closure 210; a wedge 230 arranged between both free ends of the snap ring; a wedge fixing plate 240 for fixing the wedge; and, a pulling wire 250 linked to the wedge at one end thereof for extracting the wedge by being drawn when the thrust termination is performed.
    Type: Grant
    Filed: November 1, 2006
    Date of Patent: December 8, 2009
    Assignee: Agency For Defense Development
    Inventors: Hwan-Gyu Lee, Shin-Hoe Kim, Hong-Been Chang, Moon-Joong Kang
  • Publication number: 20090288389
    Abstract: An apparatus for vectoring the thrust of a motor that produces thrust along a longitudinal axis by expelling combustion gases through a nozzle may include a plurality of linearly-positionable non-rotatable thrust deflectors. The thrust deflectors may be disposed at around a perimeter of the nozzle. Each thrust deflector may be independently extended to simultaneously generate both a force transverse to the longitudinal axis and a torque about the longitudinal axis.
    Type: Application
    Filed: May 19, 2009
    Publication date: November 26, 2009
    Inventors: Lloyd E. Kinsey, Robert J. Cavalleri
  • Patent number: 7610747
    Abstract: A side thruster module, comprises: a cavity-type body skin extending in a longitudinal direction; a first thruster arranged in the body skin and extending in a longitudinal direction; and a conversion nozzle arranged in the body skin and extending in a radial direction perpendicular to the longitudinal direction, for converting a direction of a thrust generated from the first thruster in the longitudinal direction into the radial direction. A large number of thrusters can be mounted at the side thruster module thus to generate a high thrust, and the side thruster module can be slim in the radial direction perpendicular to the longitudinal direction.
    Type: Grant
    Filed: August 14, 2006
    Date of Patent: November 3, 2009
    Assignee: Agency for Defense Development
    Inventors: Won-Hoon Kim, Won-Man Cho, Bang-Eop Lee, Soon-Il Moon, Young-Il Son
  • Patent number: 7581381
    Abstract: A ducted air power plant, comprising a motor driven fan (7) situated in a duct (4), the fan (7) having an air intake side and in operation providing a high pressure air stream in the duct, and the fan being located adjacent air splitter mechanism (18), the air splitter mechanism (18) being arranged to divert the air stream into two or more subsidiary streams for delivery to respective jet nozzles (9) of the plant. The plant may be used in a vehicle such as an aircraft in order to provide a vertical take-off and hover capability as well a level flight power source.
    Type: Grant
    Filed: June 27, 2003
    Date of Patent: September 1, 2009
    Assignee: Vtol Technologies Limited
    Inventor: Ashley Christopher Bryant
  • Publication number: 20090211224
    Abstract: An outlet device for a jet engine comprises a number of fixed ducts, each with a gas intake and a gas outlet for conducting a gas from the jet engine, at least two of the outlets of said gas ducts open in different directions, and a gas distribution arrangement is arranged at the gas intakes for selective distribution of the gas to the ducts.
    Type: Application
    Filed: October 20, 2005
    Publication date: August 27, 2009
    Applicant: VOLVO AERO CORPORATION
    Inventors: Anders Lundladh, Melker Harefors, Richard Avellan
  • Patent number: 7578121
    Abstract: Disclosed is a thrust termination device for a solid rocket motor, which terminates the net thrust by the reverse thrust of the rocket motor produced from the emission of the combustion gas in the reverse direction, when the stage separation signal is transferred at the normal thrust state of the rocket motor. An object of the present invention is to provide a thrust termination device for a rocket motor, which can contrive to accomplish the structural safety and mechanical sealing performance at the combustion chamber condition of the high temperature and high pressure, and easily remove the thrust termination device even at the low pressure state and open the trust termination ports successively with very small impacts when the thrust termination is commanded.
    Type: Grant
    Filed: November 1, 2006
    Date of Patent: August 25, 2009
    Assignee: Agency For Defense Development
    Inventors: Hong-Been Chang, Moon-Joong Kang
  • Publication number: 20090145107
    Abstract: A propulsion system may include a cylindrical support member and a tubular rotatable member rotatably mounted within the support member that may be adapted to permit fluid flow therethrough. The tubular rotatable member may extend past a down stream end of the support member. An exemplary embodiment of a propulsion system may also disclose a vane attached on an interior surface of the tubular member and may include a blade which extends in a direction toward a rotational axis of the rotatable member such that rotation of the tubular member and the vane attached thereon draws fluid into the tubular member to accelerate the fluid flow through the tubular member. Additionally, a nozzle may be attached to the down stream end of the support member and include a primary nozzle and a secondary nozzle within the primary nozzle. The secondary nozzle may be engaged with the primary nozzle by a stator.
    Type: Application
    Filed: February 21, 2008
    Publication date: June 11, 2009
    Inventor: Hugh B. Nicholson
  • Patent number: 7051512
    Abstract: A fluidic diverter valve includes valve element freely disposed within a valve bore. The valve bore has a cross sectional area that varies. As a result, the clearance between the valve element and an inner surface of the valve bore also varies. This variation in cross sectional area, and thus clearance, is such that a force of sufficient magnitude to move the valve element from a seated position is initially applied to the valve element, but the force on the valve element is reduced once it is moved from the seated position. Thus, the impact force upon attaining another seated position is reduced.
    Type: Grant
    Filed: December 10, 2003
    Date of Patent: May 30, 2006
    Assignee: Honeywell International, Inc.
    Inventors: Donald J. Christensen, Stephen G. Abel
  • Patent number: 6973773
    Abstract: A propellant supply device (10) is provided for a vehicle (11) having a main propulsion motor (12) and having an attitude control system (11) including a plurality of thrusters (14A, 14B, 14C, . . . , 14F). The improved device comprises: a pressure vessel (15); first and second movable walls (20, 21) operatively arranged within the pressure vessel and dividing the interior space therewithin into three separate sealed chambers (22, 23, 24) from each of which fluid may be supplied; a first fluid (e.g., a first bipropellant) in one of the chambers; a second fluid (e.g., a second bipropellant) in a second of the chambers; and a third fluid (e.g., ammonia) in a third of the chambers, the third fluid being a volatile liquid having a liquid phase and a gaseous phase, and wherein all three chambers are pressurized to the vapor pressure of the third fluid.
    Type: Grant
    Filed: March 19, 2002
    Date of Patent: December 13, 2005
    Assignee: Moog Inc.
    Inventor: Robert H. Reinicke
  • Patent number: 6918244
    Abstract: This patent concerns VTOL propulsion systems that develop a forward flow of air through the air intake duct(s), by the methods of a internal duct system, reversing the rotation of the fan, or a variable pitch (thrust reversing) fan.
    Type: Grant
    Filed: August 12, 2002
    Date of Patent: July 19, 2005
    Inventor: John Eugene Dickau
  • Patent number: 6837038
    Abstract: The present invention relates to a variable cycle boost propulsor system for use on an aircraft. The variable cycle boost propulsor system includes an engine, a turbine, a fan connected to the turbine, and a valve system for delivering the fluid output from the engine to the turbine for driving the turbine and the fan and thereby generating additional thrust for the aircraft. The engine is also used to provide power to one or more systems onboard the aircraft.
    Type: Grant
    Filed: October 15, 2002
    Date of Patent: January 4, 2005
    Assignee: United Technologies Corporation
    Inventors: Donald C. Eiler, Michael J. Larkin
  • Patent number: 6820411
    Abstract: An apparatus for providing propulsive power that utilizes a novel swirl generator for rapidly and efficiently atomizing, vaporizing, as necessary, and mixing a fuel into an oxidant. The swirl generator converts an oxidant flow into a turbulent, three-dimensional flowfield into which the fuel is introduced. The swirl generator effects a toroidal outer recirculation zone and a central recirculation zone, which is positioned within the outer recirculation zone. These recirculation zones are configured in a backward-flowing manner that carries heat and combustion byproducts upstream where they are employed to continuously ignite a combustible fuel/oxidizer mixture in adjacent shear layers. The swirl generator is compatible with the throttle range of conventional gas turbine engines, provides smooth combustion with no instabilities and minimum total pressure losses, enables significant reductions the in L/D ratio of the combustor and is readily packaged into various applications.
    Type: Grant
    Filed: September 13, 2002
    Date of Patent: November 23, 2004
    Assignee: The Boeing Company
    Inventors: Robert J. Pederson, Stephen N. Schmotolocha, Donald H. Morris, Calvin Q. Morrison, Jr., Raymond B. Edelman