Outlet Area Control Patents (Class 60/242)
  • Patent number: 10995879
    Abstract: A microfabricated valve with no moving parts. In one embodiment, the valve includes a reservoir of a liquid that is in fluid communication with an outlet channel having a throat that is less than 100 microns wide. Preferably, the channel is an elongated slit. The configuration of channel is adapted and configured such that surface tension of the liquid prevents flow out of the channel. A heater increases the temperature of the meniscus of the fluid, until a portion of the fluid is ejected from the channel. The ejection of the fluid creates both a thrusting effect and a cooling effect.
    Type: Grant
    Filed: December 6, 2016
    Date of Patent: May 4, 2021
    Assignee: Purdue Research Foundation
    Inventors: Alina Alexeenko, Anthony George Cofer, Stephen Douglas Heister
  • Patent number: 10807703
    Abstract: A combustion system includes at least one plasma actuator disposed along a substrate at a plasma location, and at least one fuel injector disposed along the substrate at an injection location. The fuel injector disperses fuel toward the plasma location. The plasma from plasma actuator ignites fuel from the fuel injector proximate the plasma location.
    Type: Grant
    Filed: July 19, 2018
    Date of Patent: October 20, 2020
    Assignee: General Electric Company
    Inventors: Nicholas William Rathay, Narendra Digamber Joshi
  • Patent number: 10054045
    Abstract: A power plant (10) having a first and second turboshaft engines (11, 16) and an emergency system (20) for injecting fluid into said engines (11, 16). First and second pressurization pipes (26, 28) connect a tank (21) to each gas generator of the engines. In addition, the system (20) includes an injector device (35, 40) for each engine, which device comprises an injector pipe (36, 41) connecting said tank (21) to at least one injector nozzle (31). A distributor (51, 52) is arranged on each injector pipe (36, 41), each valve (51) feeding one of the engines while being connected to the gas generator of the other engine.
    Type: Grant
    Filed: June 9, 2014
    Date of Patent: August 21, 2018
    Assignee: Airbus Helicopters
    Inventors: Frederic Dyrla, Romain Stephant
  • Patent number: 10036321
    Abstract: Systems and methods for utilizing gas turbine compartment ventilation discharge air. In one embodiment, a system may include a gas turbine engine having a compressor. The system also may include a gas turbine compartment disposed about the gas turbine engine. Moreover, the system may include an inlet bleed heat (IBH) manifold in fluid communication with the compressor. The gas turbine compartment may be in fluid communication with the IBH manifold for providing the IBH manifold with ventilation discharge air from the gas turbine compartment.
    Type: Grant
    Filed: May 29, 2014
    Date of Patent: July 31, 2018
    Assignee: General Electric Company
    Inventors: Sanji Ekanayake, Alston Ilford Scipio, Joseph Klosinski, Pierre Antoine Semel
  • Patent number: 9752453
    Abstract: The present invention relates to a mechanical system that modulates airflow in an aircraft inlet diffuser that is used in conjunction with an aircraft engine that integrates both a center turbine engine and a high Mach engine such as a constant volume combustor (CVC) arrangement or ramjet arrangement with intakes formed co-centrically about the turbine. The modulation system uses an articulating cone. When in a retracted position the articulating cone allows the aircraft to operate in low speed mode as only the turbo jet receives airflow. At its widest expanse, the articulating cone completely covers the turbo jet circular intake face, precluding operation of the turbine engine.
    Type: Grant
    Filed: July 7, 2015
    Date of Patent: September 5, 2017
    Assignee: NORTHROP GRUMMAN SYSTEMS CORPORATION
    Inventors: George D. Rupp, Trajaen J. Troia
  • Patent number: 9725185
    Abstract: A power generation system includes a ram air turbine that is connected to a generator. The power generation system may be located in a pod, for example a pod for mounting on an aircraft. The ram air turbine receives air that passes through an air path through the pod, going in through an air inlet, through the turbine to turn the turbine, and out through an air outlet. The system includes a deployable flow obstruction, such as one or more airbags, that are deployable to suddenly obstruct the flow through the air path. The obstruction may be used to cut off flow (or greatly reduce flow), when overspeed of the ram air turbine is detected. The obstruction deploys (for example, airbags deploy in an air inlet of the system) to prevent continuation of the overspeed operation of the turbine, which may damage parts of the system.
    Type: Grant
    Filed: July 26, 2013
    Date of Patent: August 8, 2017
    Assignee: Raytheon Company
    Inventors: Richard M. Weber, Scott E. Johnson
  • Patent number: 8769959
    Abstract: One embodiment of the present invention includes a nozzle defining a passage to receive and discharge working fluid to produce thrust. The nozzle includes the first wall structure opposite a second wall structure. The first wall structure includes a first convergent flap pivotally connected to a first divergent flap. The second wall structure includes a second convergent flap pivotally connected to a second divergent flap. The first wall structure and the second wall structure define the throat along the passage and are reconfigurable to adjust dimensional area of the throat. One or more control valves modulate flow of the pressurized fluid into the passage through a first opening in the first wall structure and a second opening in the second wall structure approximate to the throat to change effective area of the throat by fluidic control.
    Type: Grant
    Filed: September 13, 2010
    Date of Patent: July 8, 2014
    Assignee: Rolls-Royce Corporation
    Inventors: Von David Baker, Baily Ramachandra Vittal
  • Patent number: 8707675
    Abstract: A hot-gas thruster is actuated using a relatively small electric motor. The hot-gas thruster includes a pressure assisted pilot shaft to keep electric power demand to only a few hundred watts peak and only tens of watts on average, while exhibiting relatively fast response times.
    Type: Grant
    Filed: January 20, 2011
    Date of Patent: April 29, 2014
    Assignee: Honeywell International Inc.
    Inventors: Steve Abel, Raymond R. Tseng
  • Patent number: 8646251
    Abstract: An exemplary gas turbine engine assembly includes a fan casing within a nacelle, a variable area fan nozzle. A controller is operable to move the variable area fan nozzle to influence a discharge airflow area associated with the variable area fan nozzle in response to an airfoil flutter condition. A gear train reduces a rotational speed of a fan in the gas turbine engine relative to another portion of the gas turbine engine.
    Type: Grant
    Filed: January 9, 2012
    Date of Patent: February 11, 2014
    Assignee: United Technologies Corporation
    Inventors: William E. Rosenkrans, Robert J. Morris
  • Patent number: 8601786
    Abstract: A turbofan engine control system is provided for managing a low pressure compressor operating line. The engine includes a low spool having a low pressure compressor housed in a core nacelle. A turbofan is coupled to the low spool. A fan nacelle surrounds the turbofan and core nacelle and provides a bypass flow path having a nozzle exit area. A controller is programmed to effectively change the nozzle exit area in response to an undesired low pressure compressor stability margin which can result in a stall or surge condition. In one example, the physical nozzle exit area is decreased at the undesired stability condition occurring during engine deceleration. A low pressure compressor pressure ratio, low spool speed and throttle position are monitored to determine the undesired stability margin.
    Type: Grant
    Filed: October 12, 2006
    Date of Patent: December 10, 2013
    Assignee: United Technologies Corporation
    Inventors: Wayne Hurwitz, William J. McVey
  • Patent number: 8365513
    Abstract: (A1) A turbofan engine (10) is provided that includes a spool (14). The spool (14) supports a turbine (18) and is housed within a core nacelle (12). A fan (20) is coupled to the spool (14) and includes a target operability line. The target operability line provides desired fuel consumption, engine performance, and/or fan operability margin. A fan nacelle (34) surrounds the fan (20) and core nacelle (12) to provide a bypass flow path (39) having a nozzle exit area (40). A controller (50) is programmed to command a flow control device (41) for changing the nozzle exit area (40). The change in nozzle exit area (40) achieves the target operability line in response to an engine operating condition that is a function of airspeed and throttle position. A change in the nozzle exit area (40) is used to move the operating line toward a fan stall or flutter boundary by manipulating the fan pressure ratio.
    Type: Grant
    Filed: October 12, 2006
    Date of Patent: February 5, 2013
    Assignee: United Technologies Corporation
    Inventor: William J. McVey
  • Patent number: 8235325
    Abstract: A positional measurement system for a fan variable area nozzle (FVAN) remotely determines the position of each flap or set of flaps relative a core nacelle. The positional measurement system includes a sensor system with a multiple of transceivers located within the core nacelle to remotely measure the position of each flap or set of flaps without the heretofore necessity of moving measurement components.
    Type: Grant
    Filed: October 12, 2006
    Date of Patent: August 7, 2012
    Assignee: United Technologies Corporation
    Inventor: Bradley C. Schafer
  • Publication number: 20120186224
    Abstract: The invention relates to an aircraft jet engine comprising a nozzle (2) intended to eject a gas stream, and a system for reducing the noise (3) generated by the ejection of the gas stream. This system comprises several ducts (11a) which each, on the one hand, are connected upstream to a recess divided into several chambers and, on the other hand, open, downstream, at the outlet of nozzle (2). In this way, each duct ejects a fluid jet deriving from the recess and which interacts with the gas stream of the engine. The system also comprises a pulsation means (12) for the fluid jet which brings about its ejection at the nozzle outlet and/or modulates its speed by varying the volume contained in the recess. The system is configured in particular for balancing static pressures between the chambers.
    Type: Application
    Filed: January 24, 2012
    Publication date: July 26, 2012
    Applicants: Airbus Operations (S.A.S.), UNIVERSITE DE POITIERS, CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE
    Inventors: Jerome Huber, Jean Paul Bonnet, Luis Gomes, Remy Maury
  • Patent number: 8215097
    Abstract: A rocket thruster of this invention includes a nozzle and a valve assembly. The valve subassembly includes a pintle with a head portion, which has a truncated substantially conical surface region facing and concentric with converging and throat regions of the nozzle to provide a variable effective throat area therebetween. The truncated portion of the head portion has an outer edge defining a bleed passageway opening communicating with a primary bleed passage leading through the head portion to a bleed cavity located on an opposite side of the head portion. During activation of a rocket motor to which the rocket thruster is coupled, gases imparting a load on the head portion pass through the primary bleed passage to the opposite side of the head portion for counterbalancing loads acting on the head portion. A thrust control subassembly moves the pintle axially for changing the effective throat area.
    Type: Grant
    Filed: December 13, 2010
    Date of Patent: July 10, 2012
    Assignee: Alliant Techsystems Inc.
    Inventors: Cary L. Cover, Albert S. Drendel
  • Patent number: 8209950
    Abstract: A turbofan engine deicing system includes a core nacelle (12) housing a turbine. A turbofan (20) is arranged upstream from the core nacelle. A controller (50) manipulates the turbofan in response to detecting an icing condition for avoiding undesired ice buildup on the turbofan engine (10) and nacelle parts. In one example, a variable area nozzle (40) is actuated to generate pressure pulses or a surge condition to break up any ice buildup. The icing condition can be determined by at least one sensor (52) and/or predicted based upon icing conditions schedules.
    Type: Grant
    Filed: October 12, 2006
    Date of Patent: July 3, 2012
    Assignee: United Technologies Corporation
    Inventors: Ashok K. Jain, Michael Winter
  • Patent number: 8122723
    Abstract: A fluid flow control device (26, 28) comprising a guide member (30) to guide a fluid passing through a duct (22, 24, 76), the guide member (30) being movable between first and second positions; and an urging arrangement (32) capable of providing an urging force (F1) to urge the guide member (30) towards the first position, characterised in that the urging arrangement (32) is a resilient torsion bar that is formed so as to allow the guide member (30) to be moved towards the second position by a pressure force (F2) exceeding and opposite to the urging force (F1), the pressure force (F2) being provided by a pressure difference across the guide member (30).
    Type: Grant
    Filed: March 8, 2007
    Date of Patent: February 28, 2012
    Assignee: Rolls-Royce PLC
    Inventor: Barry N Hocking
  • Patent number: 8001763
    Abstract: A turbine engine provides a spool supporting a turbine. The spool is arranged in a core nacelle and includes a thrust bearing. A fan is arranged upstream from the core nacelle and is coupled to the spool. A fan nacelle surrounds the fan and core nacelle and provides a bypass flow path that includes a fan nozzle exit area. A flow control device is adapted to effectively change the fan nozzle exit area. A controller is programmed to monitor the thrust bearing and command the flow control device in response to an undesired load on the thrust bearing. Effectively changing the fan nozzle exit area with the flow control device actively manages the bearing thrust load to desired levels.
    Type: Grant
    Filed: September 16, 2010
    Date of Patent: August 23, 2011
    Assignee: United Technologies Corporation
    Inventors: Zbigniew M. Grabowski, Michael Winter
  • Patent number: 7950237
    Abstract: A turbine engine provides a spool supporting a turbine. The spool is arranged in a core nacelle and includes a thrust bearing. A fan is arranged upstream from the core nacelle and is coupled to the spool. A fan nacelle surrounds the fan and core nacelle and provides a bypass flow path that includes a fan nozzle exit area. A flow control device is adapted to effectively change the fan nozzle exit area. A controller is programmed to monitor the thrust bearing and command the flow control device in response to an undesired load on the thrust bearing. Effectively changing the fan nozzle exit area with the flow control device actively manages the bearing thrust load to desired levels.
    Type: Grant
    Filed: June 25, 2007
    Date of Patent: May 31, 2011
    Assignee: United Technologies Corporation
    Inventors: Zbigniew M. Grabowski, Michael Winter
  • Patent number: 7854124
    Abstract: A balance pressure control is provided for flaps which pivot in a rear of a gas turbine engine nozzle to change the cross-sectional area of the nozzle. An actuator drives a sync ring to move the flaps through a linkage. A supply of pressurized air is also provided to the sync ring to assist the actuator in resisting forces from high pressure gases within the nozzle. When those forces are lower than normal the flow of air to the rear of the sync ring is reduced or blocked. A ring rotates with another ring to control both this air flow, and a supply of cooling air to an interior of the nozzle.
    Type: Grant
    Filed: October 27, 2006
    Date of Patent: December 21, 2010
    Assignee: United Technologies Corporation
    Inventors: Andreas Sadil, Timothy A. Swandon, Roger O. Coffey, Debora F. Kehret
  • Patent number: 7849695
    Abstract: A rocket thruster of this invention includes a nozzle and a valve assembly. The valve subassembly includes a pintle with a head portion, which has a truncated substantially conical surface region facing and concentric with converging and throat regions of the nozzle to provide a variable effective throat area therebetween. The truncated portion of the head portion has an outer edge defining a bleed passageway opening communicating with a primary bleed passage leading through the head portion to a bleed cavity located on an opposite side of the head portion. During activation of a rocket motor to which the rocket thruster is coupled, gases imparting a load on the head portion pass through the primary bleed passage to the opposite side of the head portion for counterbalancing loads acting on the head portion. A thrust control subassembly moves the pintle axially for changing the effective throat area.
    Type: Grant
    Filed: September 17, 2001
    Date of Patent: December 14, 2010
    Assignee: Alliant Techsystems Inc.
    Inventors: Cary L. Cover, Albert S. Drendel
  • Patent number: 7815146
    Abstract: A fixed sized bell rocket nozzle is lined with a layer of combustible material that is ignited during launch ignition and burns to outgas into the rocket exhaust for spatially variably confining the exhaust and perfecting an effective variably sized altitude compensating exhaust nozzle that maximizes lift during the launch of a spacecraft into orbit.
    Type: Grant
    Filed: August 29, 2001
    Date of Patent: October 19, 2010
    Assignee: The Aerospace Corporation
    Inventors: Gary F. Hawkins, John W. Murdock
  • Publication number: 20090211225
    Abstract: The thrust of a rocket motor can be varied to optimize Nozzle Pressure Ratio (NPR) using a design that allows for adjusting the relative position of a plug and a combustion chamber exit. The plug or the exit may be attached to an adaptive control system for position modification. The relative position of the plug and exit may be adjusted to optimize NPR to account for changing propellant flow and/or changing ambient pressure.
    Type: Application
    Filed: January 29, 2007
    Publication date: August 27, 2009
    Applicant: GHKN Engineering, LLC
    Inventors: Donald Gerrit Nyberg, Thomas Adrian Groudle, Richard Doyle Smith, John A. Shuba, Richard T. Smith
  • Patent number: 7565797
    Abstract: The thrust of a rocket motor can be varied while maintaining efficiency over a range of pressure ratios using a design that allows for changing the relative position of a plug and a combustion chamber exit. The plug or the chamber exit may be attached to an adaptive control system for position modification. The plug may be positioned in a plug nozzle configuration or in an expansion-deflection (ED) configuration. In either configuration, the elongated downstream portion of the plug allows for efficiency over a wide range of pressure ratios, while ability to change plug position with respect to the chamber exit allows adjustment of rocket thrust.
    Type: Grant
    Filed: February 25, 2005
    Date of Patent: July 28, 2009
    Assignee: GHKN Engineering LLC
    Inventors: Donald Gerrit Nyberg, Thomas Adrian Groudle, Richard Doyle Smith
  • Publication number: 20090100823
    Abstract: A gas turbine propulsion engine reheat system having a variable area exhaust nozzle comprising a nozzle area control system including means for accelerating increases of nozzle area
    Type: Application
    Filed: October 15, 2008
    Publication date: April 23, 2009
    Applicant: ROLLS-ROYCE PLC
    Inventor: David I. Jones
  • Publication number: 20090064659
    Abstract: A turbofan engine includes a fan variable area nozzle having a multiple of vents through a fan nacelle and rotatable elements rotatable within the vents by an actuator system. Rotation of the rotatable element within each vent changes the effective area of the fan nozzle exit area to permit efficient operation at a multiple of flight conditions.
    Type: Application
    Filed: May 31, 2007
    Publication date: March 12, 2009
    Inventor: Eric W. Alletzhauser
  • Patent number: 7127880
    Abstract: A turbofan nacelle includes forward and aft cowls adjoining at a joint, and including an exhaust duct having a main outlet for discharging exhaust. A variable nozzle surrounds the exhaust duct and includes a secondary outlet around the main outlet. A thrust reverser bridges the forward and aft cowls upstream from the variable nozzle. The variable nozzle is inductively powered and controlled across the closed joint, and is uncoupled inductively from the forward cowl when the joint is open.
    Type: Grant
    Filed: August 16, 2004
    Date of Patent: October 31, 2006
    Assignee: The Nordam Group, Inc.
    Inventors: Jean-Pierre Lair, Gregory Thomas Wolters
  • Patent number: 7093793
    Abstract: An exhaust nozzle includes an exhaust duct with an outlet and a row of radial apertures upstream therefrom. A radial frame surrounds the duct upstream from the apertures. A row of flaps are hinged to the frame to selectively cover and uncover the apertures for controlling exhaust flow discharged therethrough. An arcuate unison bar surrounds the duct adjacent to the frame and includes circumferentially spaced apart cam followers engaging corresponding cams affixed to the flaps. An actuator is joined to the bar for selective rotation thereof between opposite first and second directions to pivot open and closed the flaps atop the apertures.
    Type: Grant
    Filed: July 26, 2004
    Date of Patent: August 22, 2006
    Assignee: The NORDAM Group, Inc.
    Inventor: Jean-Pierre Lair
  • Patent number: 6986246
    Abstract: A side thruster valve of an aerospace craft is improved to reduce torque of a servo-motor, etc. needed for nozzle opening and closing to thereby realize a compact and light weight device. The side thruster valve comprises a valve plug having its back directed to an axis of the aerospace craft and independently movable between a fully opened position and a fully closed position of the valve plug in a plane orthogonal to the axis of the aerospace craft, an actuating means for moving the valve plug in an axial direction of the valve plug and an elastic member for activating the valve plug in the axial direction of the valve plug. In a side thruster device comprising a plurality of the side thruster valves, the side thruster valves are arranged independently of each other to thereby broaden freedom of combustion control and improve fuel consumption.
    Type: Grant
    Filed: May 20, 2003
    Date of Patent: January 17, 2006
    Assignee: Mitsubishi Heavy Industries, Ltd.
    Inventor: Toshiharu Fujita
  • Patent number: 6892127
    Abstract: A method and apparatus for assessing damage to machine components is provided. The method includes calculating an expected parameter value based on a first parameter value indicator, calculating an estimate of an actual parameter value based on a second parameter value indicator, the second parameter value indicator being different than the first parameter value indicator, determining if the calculated expected parameter value is different than the calculated estimate of the actual parameter value by a predefined limit, and generating a damage flag based on a result of the comparison. The apparatus includes a computing device including a processor and a memory communicatively coupled to the processor, the processor programmed to execute a software product code segment that includes a detection boundary module, an estimator, and a comparator wherein the computing device is programmed to assess damage within an engine.
    Type: Grant
    Filed: February 28, 2003
    Date of Patent: May 10, 2005
    Assignee: General Electric Company
    Inventor: Matthew William Wiseman
  • Patent number: 6758032
    Abstract: According to one embodiment of the invention, a system for altering a fluid flow includes a nozzle having a fluid flow and including a converging portion, a diverging portion downstream of the converging portion, and a throat coupling the converging portion to the diverging portion, at least one port located in a wall of the nozzle and angled with respect to the fluid flow, and at least one pulse detonation device operable to inject a plurality of detonation waves in a pulsed manner through the port and into the fluid flow. The pulsed detonation waves operate to alter the fluid flow.
    Type: Grant
    Filed: February 7, 2002
    Date of Patent: July 6, 2004
    Assignee: Lockheed Martin Corporation
    Inventors: Louis G. Hunter, Daniel N. Miller, Paul E. Hagseth
  • Patent number: 6574952
    Abstract: The invention refers to an apparatus for controlling the flow separation line of rocket nozzles for reducing side loads. For obtaining this control it is suggested according to the invention that the inside of the nozzle (1) has circumferentially regular spaced areas (2) with increased surface roughness compared with the rest of the inside of the nozzle.
    Type: Grant
    Filed: November 15, 2001
    Date of Patent: June 10, 2003
    Assignee: Volvo Aero Corporation
    Inventor: Arne Boman
  • Patent number: 6543717
    Abstract: The thrust device comprises a valve body (20) having a chamber (24) surrounding part of the needle, at least one gas admission opening (27) opening out into the chamber, and a gas outlet opening (25) opening out into the chamber and defined by a wall portion which co-operates with a nose portion (14) of a moving needle (10) to define an outlet section for gas leaving the chamber. Actuator means (40, 41, 43) control the position of the needle in the valve body by acting on a rear end portion of the needle. The nose (14) of the moving needle (10) has an aerodynamic concave profile (15) and the wall portion (29) which defines the outlet (25) from the chamber is shaped in such a manner as to be capable of directing the exiting gases essentially against the concave side of the nose of the needle, which needle acts as the main member for taking up thrust.
    Type: Grant
    Filed: December 22, 2000
    Date of Patent: April 8, 2003
    Assignee: Societe Nationale d'Etude et de Construction de Moteurs d'Aviation S.N.E.C.M.A.
    Inventors: Thierry Le Fur, Bernard Debons, André LaFond, André Dumortier
  • Patent number: 6233919
    Abstract: A thruster valve has a continuously positionable piston between a closed position and a maximum open position. The piston moves in response to the difference in pressure between the pressure of the valve's inlet and thruster nozzle and the pressure behind the piston. A pivotable flapper valve regulates this pressure difference. When a change in thrust is required a force is applied to the flapper causing a change in this pressure difference which causes the piston to move until the desired thrust level is obtained.
    Type: Grant
    Filed: August 16, 2000
    Date of Patent: May 22, 2001
    Assignee: Honeywell International, Inc.
    Inventors: Stephen G. Abel, William F. Ryan, Michael A. Pepe, Joseph P. Silk, Douglas T. Hopper
  • Patent number: 6220852
    Abstract: A method and apparatus for adjusting the flame exit velocity of a high velocity burner. The burner includes burner combustor chamber having a fluid accelerating nozzle and a burner combustor exhaust port. Fuel is delivered to the burner combustor through a fuel inlet. An ignitor is provided to initiate combustion of the fuel which is mixed with air from an air inlet. An adjusting device is provided to vary the flame exit area of the burner. The adjusting device includes an adjusting rod connected to an extension rod which preferably extends through the burner ignition chamber to the burner combustion exit port. For example, a tapered plug is attached to the end of the extension rod. The tapered plug is tapered in a direction decreasing toward the burner combustion exit port and can include fins attached around a periphery of the plug.
    Type: Grant
    Filed: June 1, 2000
    Date of Patent: April 24, 2001
    Assignee: Hauck Manufacturing Company
    Inventor: Edward E. Moore
  • Patent number: 6170257
    Abstract: A variable thrust nozzle system comprises a housing, a pair of nozzle skirts. attached to the outer surface of the housing so as to open in opposite directions, respectively, a pair of nozzle plugs disposed in the pair of nozzle skirts so as to define a nozzle throat between the outer surface of each nozzle plug and the inner surface of the corresponding nozzle skirt, a shaft supported for sliding in the housing and having opposite ends connected to the nozzle plugs, respectively, and an actuator linked to the shaft to drive the shaft for sliding motions to vary the sectional areas of the nozzle throats.
    Type: Grant
    Filed: August 26, 1998
    Date of Patent: January 9, 2001
    Assignee: Kawasaki Jukogyo Kabushiki Kaisha
    Inventors: Ken Harada, Yoshihiko Nishida, Kiyoyuki Watanabe
  • Patent number: 5833140
    Abstract: A variable exhaust nozzle (26) for a turbine engine nacelle (16) includes a pair of semi-cowls (58, 60) disposed about a longitudinally extending central axis (14) and a pair of corresponding shells (36, 38) each of which is spaced radially inwardly from the corresponding semi-cowl and is pivotable about a pivot axis (42, 44) between an extended position and a retracted position. The semi-cowls and shells have curved, geometrically similar inner and outer surfaces (86, 100) respectively so that gap (108) between the shells and the cowl is uniform irrespective of the angular orientation of the shells. A seal (128) which includes longitudinally extending legs (128a, 128b) and an optional circumferential leg (128c) prevents detrimental air leakage. Pivotal movement of the shells effects large changes in the discharge area A.sub.D of the nozzle without compromising the external aerodynamic characteristics of the nacelle.
    Type: Grant
    Filed: December 12, 1996
    Date of Patent: November 10, 1998
    Assignee: United Technologies Corporation
    Inventors: Constantino V. Loffredo, Charles J. Szyszko
  • Patent number: 5826794
    Abstract: An engine exhaust nozzle (36) is provided for reducing exhaust noise in an intermediate bypass ratio turbofan engine. The nozzle (36) includes a plurality of scoop ejectors (38) placed equal distances about the circumference of a nozzle outer structure (46). A translatable centerbody (52) is located within the outer structure (46). The annular space between the outer structure (46) and the centerbody (52) define a convergent-divergent exhaust duct (56). Each scoop ejector (38) has a forward inlet (71) and an aft outlet (72). The scoop ejectors are rotatably connected to the outer structure (46) at a pivot point located approximately midway along the ejectors. The axes of rotation (82) of the scoop ejectors lie transverse to the nozzle longitudinal centerline. In an open position, the scoop ejectors are rotated so that the inlets (71) extend into the ambient airstream and the outlets (72) extend into the exhaust duct (56). Aft nozzle flaps (114) are used to form the rearmost portions of the nozzle (36).
    Type: Grant
    Filed: February 28, 1997
    Date of Patent: October 27, 1998
    Assignee: The Boeing Company
    Inventor: Peter K. C. Rudolph
  • Patent number: 5687564
    Abstract: Corrected fan speed (N1C2) and engine pressure ratio (EPR) are controlled, by controlling exhaust nozzle area (EA) according to a schedule or map so that as altitude increases (P2 decreases) the axial forces on the low rotor are sufficient to minimize low rotor vibrations. The altitude band (critical load region) is determined that produces loading levels in which vibrations appear. As this band is approached, conventional control of N1C2 and EPR is automatically over-ridden. N1C2 is decreased with altitude and exhaust area is reduced, thereby increasing the axial force (load) on the low rotor. When the upper limit of the band is reached, conventional control of N1C2 and EPR is automatically resumed, resulting in crossing the critical load region rapidly over a narrow altitude band.
    Type: Grant
    Filed: December 4, 1995
    Date of Patent: November 18, 1997
    Assignee: United Technologies Corporation
    Inventors: James B. Kelly, Kenneth D. Olson, Johnny B. Davis, Gerald Bracci
  • Patent number: 5664415
    Abstract: An after-burning turbo-fan engine system (10) includes turbo-fan engine (14) for producing exhaust gas (20), and jet thrust therefrom. After-burning chamber (16) receives turbo-fan exhaust and injects a controllable amount of fuel into turbo-fan exhaust to cause after burning of the turbo-fan exhaust to produce after-burned exhaust (20). Nozzle (18) associates with after-burning chamber (16) for receiving after-burned exhaust (20). Nozzle (18) has a fixed geometry. Nozzle (18) flow coefficient control mechanism (22 and 24) controls the approach of after-burned exhaust (20) through nozzle (18) to change the nozzle (18) flow coefficient. This controls the volumetric flow rate of after-burned exhaust (20) through the nozzle (18).
    Type: Grant
    Filed: June 1, 1994
    Date of Patent: September 9, 1997
    Assignee: Lockheed Fort Worth Company
    Inventor: Douglas A. Terrier
  • Patent number: 5579635
    Abstract: A rocket motor nozzle has a nozzle core that defines a nozzle passage through which combustion products travel during flight. The erosive forces created by the combustion products are longitudinally distributed over the nozzle core so that the nozzle's smallest area remains substantially constant in spite of the erosion. An inner surface of the nozzle core defines the nozzle passage. The inner surface includes an entry region which defines a nozzle entry, an exit region which defines an exit, and an elongate erosion region which defines an erosion passage between the entry and exit. The erosion region length is greater than the average smallest passage diameter, thereby allowing the location of the erosion focus along the erosion region to vary over time as a result of erosion of the erosion region. The nozzle core is formed of a fibrous composite material which is selected according to the type of propellant used and which includes fibers oriented transverse to the erosion passage to resist erosion.
    Type: Grant
    Filed: November 18, 1994
    Date of Patent: December 3, 1996
    Assignee: Thiokol Corporation
    Inventors: Hermann L. Miskelly, Jr., Mark C. Horton, Sheryl H. Hepler
  • Patent number: 5571262
    Abstract: Disclosed is a variable supersonic nozzle for a turbojet engine having an improved control system for varying the convergent and divergent nozzle flaps. All of the flaps are supported on several beams about the circumference of a gas passage. A control linkage interconnects hydraulic control cylinders, which are also mounted on the beams, with the convergent and divergent flaps such that, as the piston rod of the hydraulic control system extends and retracts, the angles of the flaps are varied accordingly. Additionally, cold flaps may be attached to the beams and interconnected with the linkage system such that their positions may also be varied by the control cylinder.
    Type: Grant
    Filed: January 12, 1984
    Date of Patent: November 5, 1996
    Assignee: Societe Natinonale d'Etude ed de Construction de Moteurs d'Aviation S.N.E.C.M.A.
    Inventor: Andre A. M. L. Camboulives
  • Patent number: 5491973
    Abstract: A rocket motor is provided with a self-actuated nozzle throat control mechanism. The motor includes a casing that forms a combustion chamber and houses propellant. An exhaust nozzle extends from the motor casing and is fluidly coupled to the combustion chamber. A pintle assembly is provided to vary the throat area of the nozzle. The pintle assembly includes a pintle and a support member. The pintle is coupled to the support member for movement from a first position to a second position where the pintle extends farther into the throat than when in the first position. A locking member secures the pintle to the support member in the first position when the pressure in the combustion chamber is in a first range and releases the pintle from the support member when the pressure in the combustion chamber changes to a value in another range. With this construction, a multistep pintle, which moves in response to change in combustion chamber pressure, can be constructed without complex control instrumentation.
    Type: Grant
    Filed: October 17, 1994
    Date of Patent: February 20, 1996
    Assignee: Aerojet General Corporation
    Inventors: Raymond Knapp, Robert Woodruff
  • Patent number: 5463866
    Abstract: A supersonic jet engine having a nozzle section into which ambient air can be selectively introduced for a noise suppressing mode of operation, with this ambient air being intermixed with engine exhaust flow, through passageway segments. Flow modulating plugs or vanes are positioned at the exhaust end of engine exhaust outlet segments in a mixing section, and these are operated during noise suppression mode to match engine requirements. There is a final nozzle section which during the noise suppressing mode is opened to present a relatively large cross sectional flow area to accommodate the mixed flow.During the non-noise suppressing mode, the final nozzle has a convergent/divergent configuration to control flow, and the plug or vane flow modulating means are positioned to permit unrestricted flow from the engine exhaust outlet segments.
    Type: Grant
    Filed: December 30, 1993
    Date of Patent: November 7, 1995
    Assignee: The Boeing Company
    Inventor: Garry W. Klees
  • Patent number: 5448881
    Abstract: Circumferential and radial inlet pressure distortion on an aircraft gas turbine engine are detected by a plurality of static pressure sensors and a signal processor, which computes the total pressure for each sensor to determine a pressure distortion pattern which the processor correlates with stored data for the engine and inlet to determine if the airflow geometry should be altered during flight. Time varying changes in the pressure from one or more of the pressure sensors is used to determine a stall condition, causing a change in engine airflow geometry to increase stall margin.
    Type: Grant
    Filed: June 9, 1993
    Date of Patent: September 12, 1995
    Assignee: United Technologies Corporation
    Inventors: Gregory S. Patterson, George W. Gallops, Jr.
  • Patent number: 5435128
    Abstract: A pyrotechnically driven device for restricting the area of the nozzle throat in a solid propellant rocket motor is disclosed. In one embodiment, the device includes a piston support mounted to the rocket motor in the exit cone. A restrictor is attached to a piston which is supported by the piston support. The restrictor is movable from a retracted position outside the nozzle throat to a restricting position within the throat upon actuation of the device. The piston and attached restrictor are driven by a pyrotechnic driving means that is actuatable separately from the solid propellant of the rocket motor. A locking means locks the restrictor in its restricting position.
    Type: Grant
    Filed: November 15, 1993
    Date of Patent: July 25, 1995
    Assignee: Thiokol Corporation
    Inventors: Hermann L. Miskelly, Jr., R. Lance Alldredge, Thomas F. Owens
  • Patent number: 5402963
    Abstract: A flade exhaust nozzle for a high thrust jet engine is configured to form an acoustic shield around the core engine exhaust flowstream while supplementing engine thrust during all flight conditions, particularly during takeoff. The flade airflow is converted from an annular 360.degree. flowstream to an arcuate flowstream extending around the lower half of the core engine exhaust flowstream so as to suppress exhaust noise directed at the surrounding community.
    Type: Grant
    Filed: October 18, 1993
    Date of Patent: April 4, 1995
    Assignee: General Electric Company
    Inventors: John P. Carey, Robert Lee, Rudramuni K. Majjigi
  • Patent number: 5394690
    Abstract: A pressure controlled pintle is employed in combination with a throttling quid, gel, or hybrid engine to provide a constant pressure and variable thrust from a single operating engine. As the propellants are throttled back and the chamber pressure drops, the pintle moves and closes the gap between the pintle and nozzle throat, thereby lowering the throat area and re-establishing the design chamber pressure related to pintle spring tension. By retaining the design pressure over a wide thrust range, the engine efficiency remains at the design value. This eliminates the drop of Isp due to pressure and keeps the cost of the system reasonable because only one engine is required. When a higher thrust is desired, a throttling valve in an injector increases the propellant flow rate, which causes a higher pressure in the combustion chamber. The constant pressure actuator moves the pintle to open the nozzle throat, which reduces the pressure to the design value. The design value may not be optimum.
    Type: Grant
    Filed: September 20, 1993
    Date of Patent: March 7, 1995
    Assignee: The United States of America as represented by the Secretary of the Army
    Inventors: Jerrold H. Arszman, William M. Chew, Barry D. Allan
  • Patent number: 5379585
    Abstract: A method of controlling a system is adapted to control flow to throat nozzle and vectoring nozzle actuators. The method comprises the steps of summing a plurality of signals representative of flow to the vectoring nozzle actuators with a signal representative of flow to the throat nozzle actuators to generate a total hydraulic flow signal. The total flow signal is then compared to a signal representative of total pump output to generate a reserve signal. Finally, a scaled rate limit signal is generated from the reserve signal and multiplied by predetermined ratio signals such that the ratio signals are limited by the difference between pump output and pump demand.
    Type: Grant
    Filed: July 6, 1993
    Date of Patent: January 10, 1995
    Assignee: General Electric Company
    Inventors: Barton H. Snow, David M. Leighton, Michael J. Steckler
  • Patent number: 5305599
    Abstract: Control of a gas turbine engine, suitable for powering an aircraft, is accomplished by varying outlet nozzle cross section and/or a mixing of bypass air with exhaust gas at an inlet to the nozzle. The engine includes a core engine having a combustion chamber and high and low pressure turbines followed by an exhaust plenum. High and low pressure compressors driven by the turbine assembly direct air into the combustion chamber and into a bypass duct. The bypass duct extends from an outlet of the low pressure compressor. Pressure of fluid (air or exhaust) is measured at an inlet to the high pressure compressor, in the bypass duct, and in the exhaust plenum. Ratios of the pressure of the duct pressure or of the pressure at the inlet of the high-pressure compressor, to the plenum pressure are employed in a feedback loop for control of nozzle size, and also of mixing valve position in an alternate embodiment of the invention.
    Type: Grant
    Filed: April 10, 1991
    Date of Patent: April 26, 1994
    Assignee: General Electric Company
    Inventor: Ira E. Marvin
  • Patent number: 5267435
    Abstract: A control system and method provide thrust droop compensation in a gas turbine engine. A droop compensation signal is generated for increasing turbine exit temperature T.sub.5 based on a predetermined model, and is selectively reduced for limiting the increase in temperature T.sub.5 when the temperature T.sub.5 is above a predetermined threshold temperature for a predetermined time. The reduced droop signal is added as a bias signal into an error signal which effects thrust droop concentration in a variable area exhaust nozzle of the engine.
    Type: Grant
    Filed: August 18, 1992
    Date of Patent: December 7, 1993
    Assignee: General Electric Company
    Inventors: Richard G. Frenkel, James A. Huffman, Jonathan A. Rennert, Dominic Stasio