Jet Stream Deflecting Means Patents (Class 60/230)
  • Patent number: 10378483
    Abstract: A motor assembly is provided for use with projectiles, such as munitions, having relatively low length to diameter ratios. The motor assembly has an aerospike nozzle and a casing disposed about the aerospike nozzle, where interior aerospike volume contains propellant and where walls of both the cowl of the casing and of the aerospike nozzle jointly define a combustion chamber.
    Type: Grant
    Filed: November 12, 2015
    Date of Patent: August 13, 2019
    Assignee: Raytheon Company
    Inventors: James Kendall Villarreal, Mark T. Langhenry, Jeremy C. Danforth
  • Patent number: 10082079
    Abstract: An engine cowling of an aircraft gas-turbine engine with a core engine and a bypass duct surrounding the latter, with a front cowling enclosing the bypass duct and a rear cowling movable in the axial direction, and with stator vanes arranged in the bypass duct, where recesses for removing fluid from the bypass duct are provided in the area of the stator vanes on the inside of the front cowling, where the fluid discharged through the recesses is routed by means of flow ducts through the front cowling, brought into contact with at least one heat exchanger, and subsequently discharged to the environment.
    Type: Grant
    Filed: February 18, 2016
    Date of Patent: September 25, 2018
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Predrag Todorovic, Sascha Poenick
  • Patent number: 9447749
    Abstract: A thrust reverser includes a translating sleeve and a blocking door assembly that includes two, three, or four blocker door segments. The translating sleeve is movable axially with respect to a fan case and a core cowl between a cruise position and a thrust reversal position. The blocker door segments are positioned adjacent an inner wall of the translating sleeve in the cruise position, and are pivotable to a position in which the blocker door segments substantially block the bypass duct in the thrust reversal position. Each blocker door segment is connected to the translating sleeve at transverse ends by a pair of support bearings that establish a pivot axis along an arc chord of the blocker door segment.
    Type: Grant
    Filed: April 2, 2013
    Date of Patent: September 20, 2016
    Assignee: Rohr, Inc.
    Inventor: Norman John James
  • Patent number: 9222755
    Abstract: A simpler, smaller, less costly intercepting vehicle is provided. For example, a highly scalable intercepting vehicle may include a single axial rocket motor and a body-fixed, wide field of view (FOV) sensor unit to accommodate attitude changes required to steer the intercepting vehicle. This intercepting vehicle may be much smaller and less costly than conventional intercepting vehicles.
    Type: Grant
    Filed: February 3, 2014
    Date of Patent: December 29, 2015
    Assignee: The Aerospace Corporation
    Inventor: Kevin L. Zondervan
  • Patent number: 9157460
    Abstract: A device, system and method for controlling the fluid flow of a process fluid in a tube with a magnetic field. A ferrogel can be included in the tube with the process fluid. A membrane can encapsulate the ferrogel. A mounting support can secure the membrane within the tube, and a magnetic field generator can generate the magnetic field to deform the membrane and the ferrogel from a natural position to a deformed position.
    Type: Grant
    Filed: June 5, 2012
    Date of Patent: October 13, 2015
    Assignee: Toyota Motor Engineering & Manufacturing North America, Inc.
    Inventors: Shailesh N. Joshi, Jaewook Lee
  • Patent number: 9108711
    Abstract: A method of producing a pulsatile jet flow from a substantially constant flow primary jet in a way that is mechanically efficient, easy to implement, and allows direct control over pulse duration and pulsing frequency is disclosed herein. The invention includes at least two components: (a) a constant flow fluid jet produced by any normal method (e.g., propeller) that can be directionally vectored fluidically, mechanically, or electromagnetically and (b) a nozzle with multiple outlets (orifices) through which the vectored jet may be directed. By alternately vectoring the jet through different outlets, a transient (pulsatile) flow at an outlet is obtained even with a substantially constant primary jet flow. Additionally, the nozzle outlets may be oriented in different directions to provide thrust vectoring, making the invention useful for maneuvering, directional control, etc.
    Type: Grant
    Filed: March 18, 2010
    Date of Patent: August 18, 2015
    Assignee: SOUTHERN METHODIST UNIVERSITY
    Inventor: Paul S. Krueger
  • Patent number: 8997454
    Abstract: An embodiment of the invention is a technique to suppress noise in a jet engine. A substantially annular fan nozzle of a separate-flow turbofan engine includes a flow boundary surface and an outlet to discharge fan air into atmosphere. At least one vane extends substantially radially from the flow boundary surface to vector at least a portion of the fan air toward a direction where noise suppression is desired. The-vane is situated in proximity of the outlet and has a span substantially greater than a thickness of a local boundary layer of the fan air.
    Type: Grant
    Filed: January 10, 2007
    Date of Patent: April 7, 2015
    Assignee: The Regents of the University of California
    Inventor: Dimitri Papamoschou
  • Patent number: 8959924
    Abstract: Disclosed is a turbofan engine for an aircraft. An inner fan cowl of the turbofan engine bounds an annular cold-stream duct proximate to the engine's central hot-stream generator, and an outer fan cowl bounds the annular cold-stream duct proximate to an outer nacelle cowl. An annular boss is provided along the inner fan cowl, with the annular boss having a rounded cross section that projects with respect to a smooth shape configuration of the inner fan cowl. The annular boss is configured to locally change speed of a cold stream flow in the annular cold-stream duct from a subsonic range to a supersonic range and to originate a first shockwave characteristic in a succession of shockwave characteristics, with the first shockwave characteristic being inclined from its origin toward the rear portion of the turbofan engine.
    Type: Grant
    Filed: September 25, 2008
    Date of Patent: February 24, 2015
    Assignee: Airbus Operations SAS
    Inventors: Franck Crosta, Damien Prat, David Grossein
  • Patent number: 8939401
    Abstract: A nacelle for a turbojet engine includes an air inlet forward section, a median section surrounding a fan of the turbojet engine, an aft section equipped with a thrust reverser system, a power control unit able to convert a high voltage electric supply into an electric supply towards an electromechanical actuator, and a drive unit for the power control unit which is distinct and separate from the latter and has a control input and a drive output to be connected to the power control unit. The thrust reverser system includes a mobile cowl which, under action of an electromechanical actuator, is able to move from a closed position to an open position in which the mobile cowl opens a passage in the nacelle.
    Type: Grant
    Filed: November 21, 2008
    Date of Patent: January 27, 2015
    Assignee: Aircelle
    Inventors: David Pereira, Jean Lamarre, Philippe Vancon, Manuel Sanchez
  • Patent number: 8919668
    Abstract: The present disclosure relates to a thrust reverser including at least one translatably movable cowl capable of alternately shifting between a closed position in which same ensures the aerodynamic continuity of the nacelle and which covers the deflecting means, and an open position in which same opens a passage in the nacelle and uncovers the deflecting means, said thrust reverser likewise including at least one variable nozzle section arranged in the extension of the movable thrust-reversing cowl and provided with at least one locking means capable of engaging with a complementary locking means of the movable reversing cowl so as to optionally mechanically link the movable nozzle section of the movable reversing cowl.
    Type: Grant
    Filed: January 15, 2013
    Date of Patent: December 30, 2014
    Assignee: Aircelle
    Inventors: Guy Bernard Vauchel, Jean-Philipe Joret, Loïc Le Boulicuat, Philippe Avenel
  • Patent number: 8919667
    Abstract: The invention relates to a nacelle that comprises a fixed structure (20), a nozzle with a variable section, and a cowling (30) mounted on said fixed structure (20) so as to be capable of sliding particularly along a travel so as to modify the section of said nozzle, characterized in that the nacelle further comprises an aerodynamic continuity assembly (40) provided between the fixed structure (20) and the mobile cowling (30), said assembly (40) including an elastic means that can be compressed between the fixed structure and said mobile cowling when the cowling is in the upstream portion of the travel thereof and that can expand when the cowling is in the downstream portion of the travel thereof so as to ensure the aerodynamic continuity of the lines between said fixed structure (20) and said mobile cowling (30).
    Type: Grant
    Filed: July 10, 2009
    Date of Patent: December 30, 2014
    Assignee: Aircelle
    Inventor: Guy Bernard Vauchel
  • Patent number: 8892295
    Abstract: A monitoring system and a monitoring method applied to the monitoring system, in which the monitoring system includes detectors detecting a state of a turbojet thrust reverser, a monitoring computer device controlling the reverser monitored by the computer as a function of information from the detectors provided to the computer by way of the control device, and a device regulating the turbojet monitored by the computer as a function of the information from the detectors provided to the computer by way of the control device.
    Type: Grant
    Filed: October 24, 2008
    Date of Patent: November 18, 2014
    Assignee: Airbus Operations S.A.S.
    Inventor: Patrick Zaccaria
  • Patent number: 8875486
    Abstract: A guide system for translating components of an aircraft engine nacelle includes a track assembly and a slider assembly. The track assembly includes a track guide member and a track liner engaged therewith. The track guide member includes a track channel configured to receive the track liner. The track liner defines an interior surface and includes a projection portion projecting inwardly of the track channel to define a convex surface. The slider assembly translatably engages the track assembly and includes a slider member having a head portion configured to be received within the track channel. The head portion defines a concave surface substantially corresponding to the convex surface of the track liner and is configured to mate therewith. The slider member further includes an extension portion extending from the head portion and outwardly of the track assembly.
    Type: Grant
    Filed: May 17, 2010
    Date of Patent: November 4, 2014
    Assignee: Rohr, Inc.
    Inventor: Stephen Michael Roberts
  • Patent number: 8876018
    Abstract: An arrangement is provided that includes a thrust reverser flap link rod on an internal fixed structure of a turbojet engine nacelle. The link rod is connected to the internal fixed structure by an elastic means that is a spring.
    Type: Grant
    Filed: October 22, 2012
    Date of Patent: November 4, 2014
    Assignee: Aircelle
    Inventors: Guy Bernard Vauchel, Peter Segat
  • Patent number: 8869507
    Abstract: A nacelle assembly for a high-bypass gas turbine engine includes a fan nacelle that includes a first fan nacelle section and a second fan nacelle section, the second fan nacelle section movable relative to the first fan nacelle section. A cascade array is mounted to the first fan nacelle section for movement relative thereto between a stored position and a deployed position, the stored position locates the cascade array at least partially within the first fan nacelle section.
    Type: Grant
    Filed: January 13, 2010
    Date of Patent: October 28, 2014
    Assignee: United Technologies Corporation
    Inventors: Thomas G. Cloft, Robert L. Gukeisen
  • Patent number: 8869506
    Abstract: A nacelle for a turbojet engine of an aircraft is provided that includes a fan case, an internal structure positioned upstream from the fan case, and a thrust reverser positioned downstream from the fan case. The thrust reverser includes a cowl delimiting an external line (LE) and including two removable half cowls. A device for absorbing circumferential stresses are shaped so as to lock the half cowls in the closed position when it occupies a locking configuration on the one hand and for allowing the opening of the half cowls when it occupies an unlocking configuration on the other hand. The stress absorbing device is positioned under an upstream portion of a pylon and is exclusively attached to the half cowls in order to allow the opening of the two half cowls independently of the opening/closing of an external fan cowl.
    Type: Grant
    Filed: December 3, 2012
    Date of Patent: October 28, 2014
    Assignee: Aircelle
    Inventors: Jean-Philippe Joret, Peter Segat, Guy Bernard Vauchel, Georges Alain Bouret
  • Patent number: 8869505
    Abstract: A nozzle for use in a gas turbine engine includes a nozzle door having a first end, a second end opposed from the first end, and a first pivot on the door between the first and second ends. A linkage connects to the nozzle door and to an actuator. The actuator is selectively operative to move the linkage about a second pivot to in turn move the nozzle door about the first pivot between a plurality of positions, such as stowed, intermediate, and thrust reverse positions to influence bypass airflow through a fan bypass passage. A lip extends from the nozzle door between the first pivot and one of the first end and second end.
    Type: Grant
    Filed: September 4, 2012
    Date of Patent: October 28, 2014
    Assignee: United Technologies Corporation
    Inventors: Edward B. Pero, Leonard D. Aceto
  • Patent number: 8840064
    Abstract: A stub frame for a cascade vane thrust reverser structure of an aircraft nacelle is attached to one or more cascade vanes. The stub frame includes an integral primary structure with a C-shaped longitudinal section, a secondary structure acting as a cascade edge and attached to the primary structure at one end, and transverse stiffeners connecting the two ends of the primary structure.
    Type: Grant
    Filed: November 29, 2010
    Date of Patent: September 23, 2014
    Assignee: Aircelle
    Inventors: Alexandre Bellanger, Laurent Dubois, Florent Bouillon, Stephane Bardin
  • Patent number: 8839601
    Abstract: A door for a thrust reverser of a nacelle of an aircraft being pivotally amounted on a fixed structure of the nacelle, in particular, the door being fitted with deflectors deflecting air flow is disclosed. The deflectors are arranged at an upstream end of the door and mounted such that they can move in a deflection plane perpendicular to the plane of the door. Each deflector is associated at its ends with an articulation arm capable of rotating about a pivot axis perpendicular to the deflection plane, allowing the deflectors to move in a straight line in the deflection plane. The present disclosure also relates to a thrust reverser system including the door and a fixed structure on which the door is pivotally mounted between a closing position and an open position.
    Type: Grant
    Filed: July 15, 2013
    Date of Patent: September 23, 2014
    Assignee: Aircelle
    Inventors: Loic Chapelain, Denis Guillois
  • Patent number: 8833055
    Abstract: A locking/unlocking device for a thrust reverser with sliding cover and adaptive nozzle is provided that includes a fixed pin secured to a fixed structure of the reverser, a first sleeve secured to the sliding cover and able to accommodate the pin, a second sleeve slidably mounted on the first sleeve, a third sleeve secured to the adaptive nozzle and slidably mounted on the second sleeve, first locking means able to lock the first sleeve with respect to the pin, second locking means able to lock the second sleeve with respect to the first sleeve, and third locking means able to lock the third sleeve with respect to the second sleeve.
    Type: Grant
    Filed: March 13, 2013
    Date of Patent: September 16, 2014
    Assignee: Aircelle
    Inventors: Patrick Gonidec, Philippe Avenel, Pierre Moradell-Casallas
  • Patent number: 8800262
    Abstract: The invention relates to a thrust reverser for a turbofan engine nacelle including a stationary portion (15) downstream from which is mounted at least one cowl (9) movable between a direct-jet position, in which the cowl (9) is aligned with the stationary portion (15), and a thrust-reversal position, in which the mobile cowl (9) is spaced apart from the stationary portion (15) so as to define an opening for the passage of a secondary flow (F), a means for deflecting (16) the secondary flow (F) through the passage opening, an actuator means (45) and a means (24) for guiding the mobile cowl (9) relative to the stationary portion (15), at least a first and a second adjacent cascade vane (13), positioned at an angle (B) relative to the movement axis (A) of the mobile cowl (9), arranged opposite the passage opening such that the deflected secondary flow (F) at least partially passes through the first and second vanes (13) in order to increase the deflection of said secondary flow (F) in the upstream direction, sai
    Type: Grant
    Filed: November 23, 2009
    Date of Patent: August 12, 2014
    Assignee: Aircelle
    Inventors: Guy Bernard Vauchel, Pierre Caruel
  • Patent number: 8800259
    Abstract: In one embodiment, a nozzle of a gas turbine engine may be provided having a coanda injector and a fluidic injector which operate together to provide for a change in exhaust flow direction. The fluidic injector may be coincident with or downstream of the coanda injector and both may be used in high pressure ratio operations of the nozzle. The fluidic injector may be positioned opposite the coanda injector and, when activated, may provide for a region of separated flow on the same side of the nozzle as the fluidic injector. The coanda injector may provide additional momentum to an exhaust flow flowing through the nozzle and may encourage the flow to stay attached on the coanda injector side of the nozzle.
    Type: Grant
    Filed: September 22, 2008
    Date of Patent: August 12, 2014
    Assignee: Rolls-Royce North American Technologies, Inc.
    Inventors: Crawford F. Smith, III, Steve Bergeron
  • Patent number: 8793973
    Abstract: The invention relates to a thrust reverser (1) for the nacelle of a dual-flow turbine engine, in which the bypass means (4) and the actuation jacks (22) of the sliding cowling (2) and of the reverse flaps (20) are arranged in two substantially parallel planes arranged above one another in the radial direction of the nacelle. The invention also relates to a nacelle for a dual-flow turbine engine that comprises such a thrust reverser.
    Type: Grant
    Filed: May 18, 2010
    Date of Patent: August 5, 2014
    Assignee: Aircelle
    Inventor: Guy Bernard Vauchel
  • Patent number: 8769926
    Abstract: A thrust reversal device for a turbojet engine nacelle is provided that includes a deflection means and at least one cowl moveable relative to at least one fixed structure including at least one at least partly peripheral front frame and equipped with means for connection to a corresponding upstream portion. The front frame has a deflection edge having an upstream extension forming a deformable flap intended to become an aerodynamic interface with the corresponding upstream portion to which is attached the front frame, and in that a portion of the moveable cowl is conformed so as to, in the closing position, interface with said upstream attachment portion by forcing withdrawal of the deformable flap.
    Type: Grant
    Filed: January 7, 2013
    Date of Patent: July 8, 2014
    Assignee: Aircelle
    Inventors: Guy Bernard Vauchel, Jean-Philippe Joret
  • Patent number: 8727284
    Abstract: An electromechanical actuation system (10) for a space vehicle includes a propellant source (18) and at least one turbine (14) operably connected to the propellant source (18) and rotatable by a flow of propellant (16) therefrom. At least one electrical generator (20) is operably connected to the at least one turbine (14) and is configured to convert rotation of the turbine (14) into electrical energy. At least one electromechanical actuator (12) is operably connected to the at least one electrical generator (20) such that electrical energy from the at least one electrical generator (20) drives operation of the at least one electromechanical actuator (12). A method of operating a turbine powered electromechanical actuator (12) for a space vehicle includes rotating the at least one turbine (14) via a flow of propellant (16) therethrough.
    Type: Grant
    Filed: January 22, 2010
    Date of Patent: May 20, 2014
    Assignee: Hamilton Sundstrand Corporation
    Inventor: David G. Hill
  • Patent number: 8720182
    Abstract: A variable area fan nozzle for use with a gas turbine engine system includes a nozzle having a cross-sectional area associated with a discharge air flow from a fan bypass passage. The nozzle is selectively moveable between multiple static positions for varying the cross-sectional area and multiple thrust reverse positions that are different from the static positions for reversing a direction of the discharge flow from the fan bypass passage to produce a thrust reversing force.
    Type: Grant
    Filed: October 12, 2006
    Date of Patent: May 13, 2014
    Assignee: United Technologies Corporation
    Inventor: Ashok K. Jain
  • Patent number: 8713910
    Abstract: Assembly for supporting a gas turbine engine comprises a support member including mounting sites for attachment to an associated aircraft. The support member includes integral slider tracks disposed on opposed sidewalls for selective engagement with a translatable cowl. The translatable cowl is translatable along the slider tracks to selectively cover and expose a cascade thrust-reversing structure. The cascade structure includes arcuate segments mounted in hinged relationship to the support member. Rearward translation of the translatable cowl to a service position permits the cascade structure to be opened for access to the core engine.
    Type: Grant
    Filed: July 31, 2009
    Date of Patent: May 6, 2014
    Assignee: General Electric Company
    Inventors: Alan Roy Stuart, John Robert Fehrmann
  • Patent number: 8627644
    Abstract: The invention relates to a thrust reverser (9) for an aircraft nacelle (1), including: a front frame (11), a cowl (21) which can move between an operating position and an intermediate maintenance position downstream of the front frame (11), means (26) for moving the cowl (21) between closed and open positions, and an inner structure (23) which can move between an operating position and an intermediate maintenance position downstream of the front frame (11). In addition, the cowl (21) comprises two half-cowls (21a, 21b) and the inner structure (23) comprises two structure halves (23a, 23b), whereby said half-cowls (21a, 21b) and said inner structure halves (23a, 23b) can open outward when the cowl (21) and the inner structure (23) are in the intermediate maintenance position.
    Type: Grant
    Filed: February 20, 2008
    Date of Patent: January 14, 2014
    Assignee: Aircelle
    Inventor: Guy Bernard Vauchel
  • Patent number: 8615982
    Abstract: An integrated variable area fan nozzle (VAFN) and thrust reversing actuation system (TRAS) system includes movable surfaces for adjusting an exit area for bypass flow and cowls moved for directing discharge flow in a reverser manner. The movable surfaces of the VAFN and TRAS systems are both coupled for movement by a common actuator arrangement. A power drive unit drives each of the actuators on each of the actuators through a gearbox or other linkage such that one common motor or motor combination is utilized for driving all of the actuators. A series of redundant and separately actuateable locks control deployment of the surfaces of the thrust reverse system such that thrust reversing system can move to an open or deployed position only in response to each of the locks being actuated to an unlocked condition.
    Type: Grant
    Filed: October 4, 2011
    Date of Patent: December 31, 2013
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Dale B. Sundstrom, Kevin Gibbons, Teddy L. Jones
  • Patent number: 8613185
    Abstract: Disclosed is a ventilating air intake arrangement of an aircraft. The arrangement includes at least one air duct connected to an air intake orifice. At least one confined zone connects with the air duct and the air intake orifice, and the confined zone is configured in a manner in which outside air enters through the air intake orifice. A controllable mobile element modifies the flow of air entering the confined zone by varying a cross section of the air duct. A control unit is used to control the controllable mobile element, with the control unit being arranged so as to control the controllable mobile element to vary the cross section of the at least one air duct as a function of speed and altitude of the aircraft.
    Type: Grant
    Filed: June 26, 2009
    Date of Patent: December 24, 2013
    Assignee: Airbus Operations SAS
    Inventor: Alain Dupre
  • Patent number: 8590287
    Abstract: A device for opening and closing a thrust reverser door (3) of a jet engine includes at least one actuator and at least one locking mechanism (10) including at least one first locking element (11) arranged on the thrust reverser door (3) and at least one second locking element (13) arranged on the thrust reverser structure (5). To open the locking mechanism (10) against higher internal pressures in the thrust reverser (1) without increasing a power of the actuator or requiring the operation of the latter, the device includes, in addition to the actuator, at least one unloading mechanism (20) which is coupled to the locking mechanism (10).
    Type: Grant
    Filed: September 4, 2009
    Date of Patent: November 26, 2013
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Olaf Lenk
  • Patent number: 8578699
    Abstract: The invention relates to a turbojet engine nacelle that includes a power supply source (113) for a system for actuating and controlling a thrust reverser device (121), and for a system for actuating and controlling a variable nozzle device (120), characterised in that the power supply can be switched between a first position in which it powers the system for actuating and controlling the thrust reverser device, and a second position in which it powers the system for actuating and controlling the variable nozzle device, wherein the switching is carried out under the action of a control output from a computer (103) capable of receiving a thrust reverser opening control (100).
    Type: Grant
    Filed: November 21, 2008
    Date of Patent: November 12, 2013
    Assignee: Aircelle
    Inventor: Benoit Kubiak
  • Patent number: 8561385
    Abstract: A flying object is provided with an engine comprising a combustion chamber with a combustion space and a nozzle with a nozzle space following the combustion chamber, the transition between combustion chamber and nozzle lying in a plane in which a cross-section of the combustion space converges, in which thrust control in terms of magnitude and/or thrust vector can be carried out in a simple manner, it is provided that a centre body adapted to have combustion products flowing around it is at least partially arranged in the nozzle space, outside of the combustion space, and at least three jet vanes are arranged at the centre body.
    Type: Grant
    Filed: October 13, 2010
    Date of Patent: October 22, 2013
    Assignee: Deutsches Zentrum fuer Luft- und Raumfahrt e.V.
    Inventors: Helmut Ciezki, Ralf Stark
  • Patent number: 8528312
    Abstract: The turbojet engine inlet and exhaust covers are permanently installed at the inlet and exhaust outlet or nozzle of an aircraft turbojet engine installation. The covers preclude the entrance of small animals, windblown debris, snow, and/or other contaminants into the engine inlet or exhaust while the airplane is inoperative. The covers have an iris-type shutter configuration, each cover having a plurality of leaves pivotally attached to a circumferential stationary housing that is attached to the engine or nacelle. A rotary ring is rotated through a small arc to pivot the shutter leaves inward and outward to close and open the engine opening. The rotary ring may be driven by an electric motor, or by hydraulic or pneumatic power. The system may be automated to close according to engine temperature after flight, and/or to open upon initiation of the engine start sequence for the aircraft.
    Type: Grant
    Filed: January 8, 2013
    Date of Patent: September 10, 2013
    Inventor: Ali A. A. J. Shammoh
  • Patent number: 8509968
    Abstract: Systems and methods for real-time efficiency and aircraft performance monitoring and delta efficiency calculations between various user- or system-selected phases of flight by determining an efficiency messaging index that gets translated into a messaging profile. That messaging profile is then used to obtain necessary flight and other information from multiple sources. The efficiency calculations and deltas can be used to determine real-time or post-processed benefits, which can then be used to optimize flight(s). Additionally, data is post-processed, which allows the calculation, storage and subsequent usage of efficiency coefficients to enhance the accuracy of the efficiency calculations. There are a number of ways to implement the architecture and order of processing.
    Type: Grant
    Filed: March 20, 2012
    Date of Patent: August 13, 2013
    Assignee: The Boeing Company
    Inventors: Gregory T. Saccone, Ryan D. Hale, Nicholas P. G. Impert, Louis J. Bailey
  • Patent number: 8468796
    Abstract: A by-pass turbojet including a thrust reverser is disclosed. The thrust reverse includes a deflector device which deflects all or part of the primary stream gas in such a manner that the deflected primary stream gas encounters the secondary stream, thereby reducing the injection speed of the secondary stream in an aft direction, and thus generating the thrust-reversal effect. The secondary stream escapes from the aft end of the nacelle. In the thrust-reversal position, the deflector device is inscribed radially substantially within the section of the primary nozzle cowl at the aft end of the nacelle. Such a thrust reverser is particularly simple in design, inexpensive, and makes it possible to avoid having moving parts present on the outside portion of the nacelle, thus simplifying the design of the turbojet.
    Type: Grant
    Filed: April 10, 2008
    Date of Patent: June 25, 2013
    Assignee: SNECMA
    Inventors: Yves Emprin, Jeremy Edmond Fert, Jean-Pierre Valentin Wesolowski
  • Patent number: 8453457
    Abstract: Dielectric barrier discharge plasma actuators are used to manipulate exhaust flow within and behind a jet engine nozzle. The dielectric barrier discharge plasma actuators may be used to direct cooling airflow near the surface of the nozzle to reduce heating of the nozzle, create thrust vectoring, and reduce noise associated with the exhaust flow exiting the nozzle.
    Type: Grant
    Filed: August 26, 2009
    Date of Patent: June 4, 2013
    Assignee: Lockheed Martin Corporation
    Inventors: Kerry B. Ginn, Stewart A. Jenkins, David M. Wells, Brent N. McCallum
  • Patent number: 8443585
    Abstract: A gas turbine engine system includes a first nozzle section associated with a gas turbine engine bypass passage and a second nozzle section that includes a plurality of positions relative to the first nozzle section. In at least one of the positions, there is a gap between the first nozzle section and the second nozzle section. A movable door between the first nozzle section and the second nozzle section selectively opens or closes the gap.
    Type: Grant
    Filed: August 1, 2011
    Date of Patent: May 21, 2013
    Assignee: United Technologies Corporation
    Inventor: Alfred M. Stern
  • Patent number: 8434715
    Abstract: A thrust reverser nozzle for a gas turbine engine nacelle includes opposite and asymmetrically pivoting first and second doors defining a nacelle aft section, first and second trailing edges of the first and second doors adjacent to a propulsive jet nozzle outlet of the nacelle, the doors being pivotable simultaneously between a stowed position and a deployed position such that the first trailing edge is positioned behind the second trailing edge when the doors are in the deployed position, and the first and second fairings attached to the first and second doors in relative fixed positions to the first and second doors respectively. Male contour middle portions of the first fairings may complementarily match female contour middle portions of the second fairings and are received within the female contour middle portion when the doors are in the stowed position. The fairings may be removably attached to the doors.
    Type: Grant
    Filed: July 29, 2010
    Date of Patent: May 7, 2013
    Inventors: Jean-Pierre Lair, Paul Weaver
  • Patent number: 8418436
    Abstract: A nozzle for use in a gas turbine engine includes a nozzle door having a first end, a second end opposed from the first end, and a first pivot on the door between the first and second ends. A linkage connects to the nozzle door and to an actuator. The actuator is selectively operative to move the linkage about a second pivot to in turn move the nozzle door about the first pivot between a plurality of positions, such as stowed, intermediate, and thrust reverse positions to influence bypass airflow through a fan bypass passage. The fan bypass passage has a radially outward side defined by a nacelle in at least one position. At least a portion of the nozzle door is radially outward of the nacelle and includes a lip extending from the nozzle door between the first pivot and one of the first end and second end.
    Type: Grant
    Filed: September 21, 2011
    Date of Patent: April 16, 2013
    Assignee: United Technologies Corporation
    Inventors: Edward B. Pero, Leonard D. Aceto
  • Patent number: 8408491
    Abstract: A nacelle assembly includes an inlet lip section and an airfoil adjacent to the inlet lip section. The airfoil is selectively moveable between a first position and a second position to adjust the flow of oncoming airflow and to influence an effective boundary layer thickness of the nacelle assembly.
    Type: Grant
    Filed: April 24, 2007
    Date of Patent: April 2, 2013
    Assignee: United Technologies Corporation
    Inventors: Ashok K. Jain, Michael Winter
  • Patent number: 8402743
    Abstract: A turbomachine including at least one thrust reverser and a device for actuating the thrust reverser, which includes at least one hydraulic engine supplied with pressurized fluid by a fuel circuit of the turbomachine, is disclosed.
    Type: Grant
    Filed: June 23, 2009
    Date of Patent: March 26, 2013
    Assignee: SNECMA
    Inventor: Christophe Claude Philippe Nouhaud
  • Patent number: 8353698
    Abstract: A coaxial injection device for injecting and dispersing reagents into a reactor, including an exterior duct for high-velocity gas injection; an outer-middle injector with at least one nozzle for liquid injection; an inner-middle duct for low-velocity gas injection; and an interior injector with nozzle for liquid injection; wherein, the exterior duct is formed by the internal wall of an insert and the external wall of the outer-middle injector; and is located externally to and circumferentially surrounds all other injectors and ducts; the outer-middle injector is formed by two concentric cylinders with end plate and injector nozzles; the inner-middle duct is formed by interior wall of the outer-middle injector and the exterior wall of the interior injector; the interior injector is formed by a cylinder with an endplate, the endplate having a nozzle; thereby ensuring the mixing and dispersion of the liquids and gases into the reactor to increase reaction homogeneity, reaction efficiency, reactor efficiency and
    Type: Grant
    Filed: June 13, 2003
    Date of Patent: January 15, 2013
    Assignee: Nalco Mobotec, Inc.
    Inventor: Goran Moberg
  • Patent number: 8347601
    Abstract: A device is provided for pivoting at least one pivotable element in a gas turbine engine between a first and a second position in order to influence a gas flow in an annular gas duct in at least one of the positions. The device includes a moveable annular member which is arranged externally around the gas duct and is connected to the pivotable element in order to effect the pivoting of the pivotable element. The annular member is more specifically arranged to be displaced in a substantially axial direction and arranged to pivot the pivotable element when it is displaced axially.
    Type: Grant
    Filed: May 4, 2006
    Date of Patent: January 8, 2013
    Assignee: Volvo Aero Corporation
    Inventor: Rustan Brogren
  • Patent number: 8341935
    Abstract: An integrated, single piece mixer-center body ventilation apparatus is disclosed for use with a turbofan jet engine. The apparatus may incorporate a circumferential forward body portion adapted to be coupled to an aft end of a core engine turbine case of the jet engine, and a center body tube portion integrally formed with the forward body portion and having an axially opening vent exit. The forward body portion may have a plurality of inner mixer flow paths in communication with scalloped projecting portions. The inner mixer flow paths direct a pressurized core exhaust flow through the mixer device and mix the pressurized core exhaust flow with a portion of a pressurized fan exhaust flow, to thus significantly cool the pressurized core exhaust flow.
    Type: Grant
    Filed: May 13, 2010
    Date of Patent: January 1, 2013
    Assignee: The Boeing Company
    Inventors: Edward C. Marques, Matthew D. Moore
  • Publication number: 20120285138
    Abstract: The present invention relates to an aircraft gas-turbine engine with a core engine surrounded by a bypass duct, with a radially outer engine cowling enclosing the bypass duct and being provided at its rear region with a thrust-reversing device which is moveable relative to the engine cowling, with at least one cooler element extending over at least part of the circumference being arranged in the intermediate area between the engine cowling and the thrust-reversing device.
    Type: Application
    Filed: May 10, 2012
    Publication date: November 15, 2012
    Applicant: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Predrag TODOROVIC
  • 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
  • Patent number: 8285467
    Abstract: The invention relates to a method for controlling at least one actuator for actuating the cowlings of a thrust inverter in a turbojet engine, the actuator being driven by an electric motor including a relative position sensor providing information on the evolution of the movement thereof, wherein the motor is controlled based on the instantaneous position of the cowling in at least one portion of the movement thereof between an open position and a closed position, the instantaneous position of the cowling being determined from at least one reference position absolute data and relative position data relative to said reference position provided by the relative position sensor of the motor, wherein in case the actuation is resumed after an interruption, a new determination of the reference position is initiated.
    Type: Grant
    Filed: July 16, 2008
    Date of Patent: October 9, 2012
    Assignee: Aircelle
    Inventor: Hakim Maalioune
  • Patent number: 8268438
    Abstract: The present application provides a component for use in streams of hot gas, which comprises a first region of fiber-ceramic material, a second region of fiber-ceramic material and a middle layer of fiber-ceramic material which is arranged between the first region and the second region, wherein the fiber-ceramic material of the middle layer has a lower ceramic content than the fiber-ceramic material of the first region and the second region, and wherein at least one acute-angled in-flow edge and/or away-flow edge of the component is formed on the middle layer.
    Type: Grant
    Filed: March 4, 2010
    Date of Patent: September 18, 2012
    Assignee: Deutsches Zentrum fuer Luft—und Raumfahrt e.V.
    Inventors: Martin Friess, Markus Keck
  • Patent number: 8205821
    Abstract: A method for exhausting gas from an aircraft engine assembly is provided. The method includes coupling a first exhaust duct in fluid communication only to a first engine. The first exhaust duct includes a primary outlet and a secondary outlet. The method further includes coupling a second exhaust duct in fluid communication only to a second engine. The second exhaust duct includes a primary outlet and a secondary outlet. The method also includes aligning a portion of the first engine secondary outlet concentrically within a portion of the second engine secondary outlet.
    Type: Grant
    Filed: December 13, 2006
    Date of Patent: June 26, 2012
    Assignee: General Electric Company
    Inventor: Robert Andrew Peck