With Condition Responsive Control Means Patents (Class 137/15.2)
  • Patent number: 9752589
    Abstract: A suction surface of a blade forming a blade row of an axial compressor includes a concave region having a negative curvature at a leading edge part, and a flat region having substantially zero curvature continued rearwardly of the concave region, so that multiple compression waves are generated, enabling moderation of magnitude of a 1st passage shock to reduce pressure loss and suppress boundary layer separation on the suction surface. Providing a concave region having a negative curvature in a frontal part on a pressure surface of the blade suppresses an increase in the airflow velocity in the frontal part, thus weakening a 2nd passage shock generated on the pressure surface to enable reduction of pressure loss. The concave region of the pressure surface may be extended from a position having a chord length of no greater than 10% to a position having at least 20%.
    Type: Grant
    Filed: May 15, 2014
    Date of Patent: September 5, 2017
    Assignee: HONDA MOTOR CO., LTD.
    Inventors: Toyotaka Sonoda, Toshiyuki Arima, Giles Endicott, Markus Olhofer
  • Patent number: 9493244
    Abstract: An air vehicle powered by a gas turbine engine, particularly, but not exclusively, an air vehicle having a blended wing body includes a gas turbine engine disposed in the body of the vehicle including an inlet face. An inlet channel having a convoluted geometry is configured such that air flow incident on the inlet face during operation is disordered. A structural element associated with the inlet channel and locate upstream of the inlet face is provided. The element is configured to modulate air flow, at least partially, to improve flow ordering in the incident air.
    Type: Grant
    Filed: May 23, 2012
    Date of Patent: November 15, 2016
    Assignee: BAE SYSTEMS PLC
    Inventor: Ian Whitmore
  • Patent number: 9447731
    Abstract: A supersonic inlet includes a supersonic section including a cowl which is at least partially elliptical, a ramp disposed within the cowl, and a flow inlet disposed between the cowl and the ramp. The ramp may also be at least partially elliptical.
    Type: Grant
    Filed: August 15, 2012
    Date of Patent: September 20, 2016
    Assignee: THE BOEING COMPANY
    Inventors: Eric E. Adamson, Lawrence E. Fink, Spencer R. Fugal
  • Patent number: 9429071
    Abstract: A flow control device generates counter-rotating vortices in the boundary layer of the flow in a supersonic inlet diffuser for an aircraft turbine engine. The flow control device comprises a flap attached to the duct wall for selective deployment, wherein it extends into the boundary layer, and retraction, wherein it lies substantially flush with the duct wall. In one embodiment an actuating mechanism comprising one or more shape-memory alloy wires moves the flap between two stable positions. In another embodiment the deployment height of the flap can be controlled as desired, preferably using a shape-memory alloy actuating mechanism. Typically, an array of plural flow control devices is disposed in the inlet duct for selective actuation according to a predetermined schedule.
    Type: Grant
    Filed: April 24, 2012
    Date of Patent: August 30, 2016
    Assignee: CONTINUUM DYNAMICS, INC.
    Inventors: Todd R. Quackenbush, Robert M. McKillip, Jr., Pavel V. Danilov
  • Patent number: 9422062
    Abstract: Disclosed is an air intake arrangement for an aircraft. The arrangement includes an air intake orifice, which is configured to bleed off a flow of external air, pass the external air through at least one air passage channel and ventilate a confined zone of the aircraft. An aerodynamically controlled shut-off means, comprised of a controllable mobile element and control means, is configured to regulate flow of the external air through the air passage channel to vary a cross section of the air passage channel relative to aircraft speed. The control means are arranged in the air passage channel and include an aerodynamic surface configured to apply a lift force to the control means to vary the cross section of the air passage channel as the flow of external air passes through the channel and toward the confined zone.
    Type: Grant
    Filed: April 14, 2008
    Date of Patent: August 23, 2016
    Assignee: AIRBUS OPERATIONS SAS
    Inventors: Franck Alvarez, Emeric Chancerelle, Alain Porte, Damien Prat
  • Patent number: 9032706
    Abstract: A turbofan engine which has a composite fan case surrounding a fan with a plurality of fan blades is disclosed. The composite fan case includes a containment zone having an inner fabric layer composed of resin-impregnated fibers substantially uni-axially oriented in a common angular direction corresponding to a blade release angle of the fan blades. The fan case also includes a composite outer shell and an energy absorbing core disposed radially between the inner fabric layer and the composite outer shell. The energy absorbing core includes non resin impregnated multidirectional fibers.
    Type: Grant
    Filed: September 26, 2008
    Date of Patent: May 19, 2015
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Andrew R. Marshall
  • Patent number: 8997494
    Abstract: A fan blade for a gas turbine engine includes an airfoil that includes leading and trailing edges joined by pressure and suction sides to provide an exterior airfoil surface that extends in a radial direction to a tip. The external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil described by a set of Cartesian coordinates set forth in Table 1. The Cartesian coordinates are provided by an axial coordinate scaled by a local axial chord. A circumferential coordinate is scaled by the local axial chord, and a span location. The local axial chord corresponds to a width of the airfoil between the leading and trailing edges at the span location.
    Type: Grant
    Filed: October 31, 2012
    Date of Patent: April 7, 2015
    Assignee: United Technologies Corporation
    Inventors: Sue-Li Chuang, Yuan Dong, Sanjay S. Hingorani, Dilip Prasad
  • Patent number: 8984855
    Abstract: A rotating inlet cowl for a turbine engine, having a rotation axis and for which the forward end is arranged to be eccentric relative to this rotation axis. Furthermore, a forward cone of the cowl is truncated by a truncation surface defining the forward end of the inlet cowl.
    Type: Grant
    Filed: March 31, 2010
    Date of Patent: March 24, 2015
    Assignee: SNECMA
    Inventors: Mickael Delapierre, Herve Gignoux, Gael Loro, Sylvie Wintenberger
  • Patent number: 8950191
    Abstract: Variable speed drive controlled discharge pumps are used for pumping chilled water from a chilled water storage tank to coils operatively associated with the air inlet of a gas turbine, wherein the gas turbine is used to generate electricity. Use of the variable speed drive controlled discharge pumps aids is protecting the temperature distribution in the chilled water storage tank so that a thermocline rises with the addition of chilled water during charging of the tank with chilled water, and lowers during discharge of the tank when using the chilled water to cool inlet air at one or more gas turbines operated at a facility.
    Type: Grant
    Filed: June 23, 2010
    Date of Patent: February 10, 2015
    Assignee: Bicent Power LLC
    Inventors: Frank Landis, James Nolan
  • Patent number: 8931252
    Abstract: A gas turbine engine having a rotational axis, an intake and a compressed gas source; the intake includes a lining having a facing which defines an inlet surface and an array of holes; the array of holes includes at least a first set of holes and a second set of holes, the holes of the first set of holes are angled a relative to a radial line and the holes of the second set of holes are angled ? relative to the radial line; the angles ? and ? are different. An active flow control arrangement including a compressed gas supply pipe, a valve arrangement, a controller, a compressed gas distribution pipe may be provided. Compressed gas may be provided to prevent the formation of separation of a main gas flow through the intake and prevent or remove ice accretion.
    Type: Grant
    Filed: December 13, 2012
    Date of Patent: January 13, 2015
    Assignee: Rolls-Royce PLC
    Inventors: Giles Anthony Richardson, David MacManus, Christopher Thomas John Sheaf
  • Publication number: 20140311580
    Abstract: An air intake guide for a jet propulsion power plant for a supersonic aircraft comprises an intake aperture, an intake centre body and an intake adjustment device. The intake aperture has an intake lip, an intake centre body is positioned within the aperture, and an intake adjustment device is positioned on a radially inwardly facing surface of the air intake guide downstream of the intake lip. The intake adjustment device comprises a flexible panel and an actuator with the actuator being adapted to deflect the flexible panel in a radially inwardly direction so as to reduce a cross-sectional area of the intake aperture and thereby to position a shock wave at the intake lip.
    Type: Application
    Filed: March 21, 2014
    Publication date: October 23, 2014
    Applicant: ROLLS-ROYCE PLC
    Inventor: Nicholas HOWARTH
  • Patent number: 8831783
    Abstract: A biochemical processing apparatus is provided having a stage receiving a biochemical reaction cartridge which includes chambers and flow paths communicating therebetween, a moving system for moving liquid via the flow paths, and a detector for detecting the presence of the liquid in a chamber and/or the amount of the liquid. In addition, a determining device determines a result of the movement of the liquid from the information of the liquid in the chamber detected by the detector.
    Type: Grant
    Filed: August 24, 2011
    Date of Patent: September 9, 2014
    Assignee: Canon Kabushiki Kaisha
    Inventor: Yasuyuki Numajiri
  • Patent number: 8820344
    Abstract: The invention relates to a turbojet engine nacelle (1) comprising: an outer structure including an annular lip defining an air inlet and a cowl (9) extending as a continuation of the annular lip, and an inner fixed structure (19) extending as a continuation of the air inlet and including a region equipped with at least one piece of equipment requiring maintenance or monitoring. The aforementioned outer structure can move in relation to the inner structure between an operating position in which the cowl (9) covers the region equipped with the equipment and a maintenance position in which the cowl (9) reveals said region so as to allow access to the equipment from outside.
    Type: Grant
    Filed: February 1, 2010
    Date of Patent: September 2, 2014
    Assignee: Aircelle
    Inventors: Guy Bernard Vauchel, Stephane Beilliard
  • Patent number: 8661832
    Abstract: The present invention relates to control of engine variable of a gas turbine engine to regulate the surge margins of at least two compressors. A controller (20) receives data measured from engine sensors (22, 23) and uses said data to determine an indication of surge margin for each of at least two compressors (6, 7) of the gas turbine engine. The controller (20) uses the indications of surge margin for each of the compressors to determine a control strategy that balances the requirements of each compressor. In one embodiment a surge margin operating map divided into different control domains (40, 43, 43) is used. The indication of surge margin determined for each compressor is plotted to determine which control domains the current operating point on the surge margin operating map falls within.
    Type: Grant
    Filed: July 27, 2010
    Date of Patent: March 4, 2014
    Assignee: Rolls-Royce PLC
    Inventors: Ian A. Griffin, Arthur L. Rowe
  • Patent number: 8528318
    Abstract: A propulsion system includes an engine with a fan and a nacelle that circumscribes the engine. The engine defines an axis. A distance between a forwardmost point at the top of the nacelle and at the front of the nacelle to a forwardmost point of the fan is greater than a distance between a forwardmost point at the bottom of the nacelle and at the front of the nacelle.
    Type: Grant
    Filed: August 13, 2012
    Date of Patent: September 10, 2013
    Assignee: United Technologies Corporation
    Inventor: Gavin Hendricks
  • Patent number: 8516785
    Abstract: A jet engine air intake guard system wherein direct axial air flow into an engine during takeoff and landing may be temporarily closed off while air intake is provided laterally through screened air intake ports located on a cylindrical housing that extends forward of the conventional air intake cowling openings.
    Type: Grant
    Filed: December 9, 2010
    Date of Patent: August 27, 2013
    Assignee: Tojali Corporation, Inc.
    Inventor: Myron L. Brown
  • Patent number: 8439297
    Abstract: The present invention relates to an air inlet (10) for a turbine engine (2) of an aircraft (1), the air inlet comprising an air delivery duct (20) defined by a side wall (21) and extended by a dynamic inlet duct (30), said dynamic inlet duct (30) extending along a dynamic axis (AX1) towards a front flow section (31), said dynamic inlet duct (30) being provided with a grid (40) for protection against ingesting foreign bodies. The grid (40) is suitable for moving in translation along said dynamic axis (AX1) relative to said front flow section (31), and said air inlet (10) includes at least one lateral inlet (50) arranged in said side wall (21) and cover means (41) for covering said lateral inlet (50) that are movable relative to said lateral inlet (50), said air inlet (10) including movement means (60) controlled by said movement in translation of the grid (40) to request movement of said cover means (41) relative to said lateral inlet (50).
    Type: Grant
    Filed: November 8, 2010
    Date of Patent: May 14, 2013
    Assignee: Eurocopter
    Inventors: Marc Colaprisco, Victor Gerin-Roze
  • Patent number: 8439061
    Abstract: The present invention relates to an emergency ram air inlet valve, also designated as an ERAI valve, of an aircraft. The valve includes an actuating element for opening and/or closing the valve and a controller operatively coupled to the valve, by which the valve can be set at different open angles. The open angle is set as a function of a temperature prevailing or preset in the aircraft cabin.
    Type: Grant
    Filed: October 25, 2006
    Date of Patent: May 14, 2013
    Assignee: Airbus Deutschland GmbH
    Inventor: Joerg Baumann
  • Patent number: 8429890
    Abstract: A retractable deflector to deflect birds and debris from an air intake duct of an aircraft jet engine. The duct has a central longitudinal axis and a forward opening for air receipt. The deflector includes a plurality of elongate first support members disposed on the duct having leading ends which extend from a perimeter of the opening, mounted for movement to extend and retract the leading ends. A second support member is coupled to these leading ends to retain them in spaced relation. The second support member is extendible in length and configured to hold the leading ends of the first support members sufficiently close together to cause the first support members to deflect at least one of a bird and debris when deployed, and to allow the leading ends to maintain a spaced-apart relation along a line which approximately corresponds to the perimeter of the duct when retracted.
    Type: Grant
    Filed: January 19, 2010
    Date of Patent: April 30, 2013
    Inventor: Jeffrey A. Matos
  • Patent number: 8403264
    Abstract: The present invention provides an air intake valve for an aircraft and a method for the production of an air intake valve. The air intake valve has an opening region for letting ambient air through into a fuselage inner region of the aircraft and a flap for opening and closing the opening region, the opening region and the flap each having a shape which is capable of forming air vortices on edges of the opening region when ambient air flows through the air intake valve.
    Type: Grant
    Filed: November 18, 2010
    Date of Patent: March 26, 2013
    Assignee: Airbus Operations GmbH
    Inventors: Thorsten Schiek, Markus Petrac, Thomas Scherer
  • Patent number: 8402739
    Abstract: A nacelle assembly includes an inlet section having a plurality of discrete sections. Each of the plurality of discrete sections includes an adaptive structure. A thickness of each of the plurality of discrete sections is selectively adjustable between a first position and a second position to influence the adaptive structure of each of the plurality of discrete sections.
    Type: Grant
    Filed: June 28, 2007
    Date of Patent: March 26, 2013
    Assignee: United Technologies Corporation
    Inventors: Ashok K. Jain, Zaffir A. Chaudhry
  • Patent number: 8371324
    Abstract: A collapsible flow control structure for an axisymmetric inlet employs trapezoidal alternating actuated and non-actuated strips having leading edges hinged to a missile forebody and free trailing edges extending into an inlet aperture, the strips positionable to form a variable angle frustum of a cone. An interengagement mechanism secures adjacent strips and actuators are attached to an inner surface of the actuated strips for urging the strips between a collapsed, retracted position for a first angle frustrum to an extended position for a second angle frustrum for aerodynamic flow control.
    Type: Grant
    Filed: June 19, 2009
    Date of Patent: February 12, 2013
    Assignee: The Boeing Company
    Inventor: Lawrence E. Fink
  • Patent number: 8359825
    Abstract: A method of using one or more microjets to create and/or control oblique shock waves. The introduction of microjet flow into a supersonic stream creates an oblique shock wave. This wave can be strengthened—by increasing microjet flow rate or the use of many microjets in an array—in order to form an oblique shock. Such an oblique shock can be used to decelerate flow in a jet aircraft engine inlet in a controlled fashion, thus increasing pressure recovery and engine efficiency while reducing flow instability. Adjusting the pressure ratio across the microjet actually alters the angle of the oblique shock. Thus, the use of microjets allows decelerating shock waves in an inlet engine to be properly positioned and controlled. Microjet arrays can also be used to ameliorate shock waves created by external aircraft surfaces, such as sensor pods and weapons.
    Type: Grant
    Filed: May 20, 2009
    Date of Patent: January 29, 2013
    Assignee: Florida State University Research Foundation
    Inventor: Farrukh S. Alvi
  • Patent number: 8262018
    Abstract: A ram-air duct includes a ram-air inlet duct and a ram-air outlet duct arranged downstream of the ram-air inlet duct and in fluid communication with the ram-air inlet duct. At an inlet of the ram-air inlet duct, a first movable element is arranged and adapted to set an inlet parameter of the inlet. At an outlet of the ram-air outlet duct, a second movable element is arranged and adapted to set an outlet parameter of the outlet. The outlet parameter and the inlet parameter are linked together by a function, so that an outlet parameter corresponding to a value of the function is assigned to each inlet parameter. A controller implements the control function by actuating movements of the first and second movable elements.
    Type: Grant
    Filed: April 2, 2010
    Date of Patent: September 11, 2012
    Assignee: Airbus Operations GmbH
    Inventors: Thomas Scherer, Alexander Solntsev, Ruediger Schmidt
  • Publication number: 20110259435
    Abstract: The present invention relates to a jet engine nacelle comprising a forward air inlet section, a mid-section intended to surround a jet engine fan, and an aft section equipped with at least one thrust reversal system comprising, on the one hand, means for deflecting at least part of an air flow of the jet engine and, on the other hand, at least one cowl (12) mounted translatably along at least one guide rail (15) in a direction substantially parallel to a longitudinal axis of the nacelle, said movable cowl being able to switch alternately from a closed position, in which it provides the nacelle with aerodynamic continuity and covers the deflection means, to an open position in which it opens a passage in the nacelle and uncovers said deflection means, the nacelle being characterized in that the aft section is equipped with at least one stud (18) mounted such that it can move over a fixed structure of the aft section in the region of the guide rail between a retracted position, in which said stud is withdrawn f
    Type: Application
    Filed: June 16, 2008
    Publication date: October 27, 2011
    Applicant: AIRCELLE
    Inventors: Pascal Gerard Rouyer, Emmanuel Lesteven
  • Publication number: 20110240137
    Abstract: The invention relates to an overpressure hatch (21) intended to be mounted on a wall (23) of a nacelle (1) for a turbojet engine (5), the overpressure hatch (21) comprising a support (22) intended to be fixed to the wall (23), and at least one discharge element (25) able to move with respect to said support (22), said hatch (21) comprising at least one part (27) of lower mechanical strength than the remainder of the overpressure hatch (21) so that air at an overpressure inside the nacelle (1) can be discharged when the internal pressure applied to said hatch (21) more or less reaches a threshold pressure level lower than the maximum pressure that the nacelle structure can withstand. The invention also relates to a turbojet engine nacelle comprising at least one hatch (21) according to the invention.
    Type: Application
    Filed: November 18, 2009
    Publication date: October 6, 2011
    Applicant: AIRCELLE
    Inventor: Guy Bernard Vauchel
  • Publication number: 20110173947
    Abstract: A gas turbine power augmentation system and method are provided. The system includes a chiller, a controller, a heat exchanger, and a gas turbine inlet air flow. The chiller may be operable to chill a coolant flow using energy from a heat source. The controller may be operably connected to the chiller and configured to regulate operation of the chiller in relation to at least one environmental condition. The heat exchanger may be in fluid communication with the chiller and configured to allow the coolant flow to pass through the heat exchanger. The gas turbine inlet air flow may be directed through the heat exchanger before entering a gas turbine inlet, allowing the air flow to interact with the coolant flow, thereby cooling the air flow.
    Type: Application
    Filed: January 19, 2010
    Publication date: July 21, 2011
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: JIANMIN ZHANG, LISA KAMDAR AMMANN, BRADLY AARON KIPPEL, HUA ZHANG, JAMES PATRICK TOMEY
  • Patent number: 7832684
    Abstract: A ram air channel (10) for the supply of ambient air in an aircraft includes a first air inlet (12) and a main flow channel (16) which extends downstream of the first air inlet (12). In order to guarantee that the systems on board the aircraft are supplied, in a simple and reliable way, with the required ambient air in any operational state of the aircraft, i.e. both during the flight and on the ground, the ram air channel (10) has a second air inlet (24) which is independent from the first air inlet (12).
    Type: Grant
    Filed: December 30, 2004
    Date of Patent: November 16, 2010
    Assignee: Airbus Deutschland GmbH
    Inventors: Thomas Scherer, Alexander Solntsev, Michael Heesch
  • Publication number: 20100237200
    Abstract: A propulsion unit comprises a turbojet engine and a thermal exchanger, situated above the turbojet engine.
    Type: Application
    Filed: July 20, 2006
    Publication date: September 23, 2010
    Inventor: Herve Marche
  • Patent number: 7784732
    Abstract: A system for reducing distortion at the aerodynamic interface plane of a boundary-layer-ingesting inlet using a combination of active and passive flow control devices is disclosed. Active flow control jets and vortex generating vanes are used in combination to reduce distortion across a range of inlet operating conditions. Together, the vortex generating vanes can reduce most of the inlet distortion and the active flow control jets can be used at a significantly reduced control jet mass flow rate to make sure the inlet distortion stays low as the inlet mass flow rate varies. Overall inlet distortion, measured and described as average SAE circumferential distortion descriptor, was maintained at a value of 0.02 or less. Advantageous arrangements and orientations of the active flow control jets and the vortex generating vanes were developed using computational fluid dynamics simulations and wind tunnel experimentations.
    Type: Grant
    Filed: December 18, 2007
    Date of Patent: August 31, 2010
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventors: Lewis R. Owens, Brian G. Allan
  • Publication number: 20090288711
    Abstract: A method of using one or more microjets to create and/or control oblique shock waves. The introduction of microjet flow into a supersonic stream creates an oblique shock wave. This wave can be strengthened—by increasing microjet flow rate or the use of many microjets in an array—in order to form an oblique shock. Such an oblique shock can be used to decelerate flow in a jet aircraft engine inlet in a controlled fashion, thus increasing pressure recovery and engine efficiency while reducing flow instability. Adjusting the pressure ratio across the microjet actually alters the angle of the oblique shock. Thus, the use of microjets allows decelerating shock waves in an inlet engine to be properly positioned and controlled. Microjet arrays can also be used to ameliorate shock waves created by external aircraft surfaces, such as sensor pods and weapons.
    Type: Application
    Filed: May 20, 2009
    Publication date: November 26, 2009
    Inventor: Farrukh S. Alvi
  • Patent number: 7617670
    Abstract: A method operable to improve pressure recovery and/or distortion within engine inlet is disclosed. A first fluid flow is provided to primary jet vortex generator(s) operable to inject fluid at a first injection rate into a boundary layer of a primary fluid flow within the inlet. A secondary fluid flow is injected by secondary jet vortex generator(s) at a second injection rate into the boundary layer of the primary fluid flow, The fluid injected at the first injection rate and second injection rate is operable to induce secondary flow structures within the boundary layer. These secondary close structures are then operable to improve or manipulate the pressure recovery of the inlet. At specific engine conditions, this method may redistribute the ratio of the first injection rate and second injection rate in order to improve pressure recovery and/or distortion of the inlet when the particular engine conditions.
    Type: Grant
    Filed: May 4, 2006
    Date of Patent: November 17, 2009
    Assignee: Lockheed Martin Corporation
    Inventors: Philip P. Truax, Daniel N. Miller, Edward C. Ma
  • Patent number: 7540142
    Abstract: An auxiliary power unit (APU) compartment air inlet system seals, via one or more inlet doors driven by a single actuator, an APU compartment, and isolates the APU inlet and cooling system inlets from each other. The system includes either one or two inlet doors, depending on the number of ram air inlets formed in the APU compartment. In either instance, however, a single actuator is used to move the inlet door(s) between open and closed positions.
    Type: Grant
    Filed: June 23, 2006
    Date of Patent: June 2, 2009
    Assignee: Honeywell International Inc.
    Inventors: Yogendra Y. Sheoran, John G. Zimmerer, Kyle D. Asplund
  • Publication number: 20090008508
    Abstract: A gas turbine engine includes a compressor section, a combustor section, a turbine section and a nacelle assembly which at least partially surrounds the compressor section, the combustor section and the turbine section. At least a portion of the nacelle assembly includes an adjustable contour. The portion of the nacelle assembly including the adjustable contour is selectively moveable between a first portion and a second position to influence the adjustable contour of the nacelle assembly. A controller identifies an abnormal aircraft operating condition and selectively moves the portion of the nacelle assembly including the adjustable contour between the first position and the second position in response to detecting the abnormal aircraft operating condition.
    Type: Application
    Filed: July 2, 2007
    Publication date: January 8, 2009
    Inventors: Ashok K. Jain, Michael Winter
  • Patent number: 7322179
    Abstract: An air intake includes a spike and a cylindrical cowl. The spike is composed of a plurality of plates which are arranged axial symmetrically around a central axis thereof, and the cowl includes an inner wall parallel to the central axis and is formed so as to enclose a rear portion of the spike via a given space. The adjacent ones of the plates form respective aerodynamic compressive surfaces in spaces formed by the adjacent ones. The distances between the adjacent ones of the plates are variable, and the distance between the forefront of the spike along the central axis and the cowl is variable.
    Type: Grant
    Filed: January 20, 2004
    Date of Patent: January 29, 2008
    Assignee: Japan Aerospace Exploration Agency
    Inventors: Hiroaki Kobayashi, Nobuhiro Tanatsugu, Tetsuya Sato, Takayuki Kojima, Yusuke Maru
  • Patent number: 7207520
    Abstract: An advanced aperture inlet (AAI) uses a three-dimensional, mixed compression inlet design derived from computational fluid dynamics (CFD) by streamline tracing a supersonic section from an axisymmetric mixed compression inlet solution. The axisymmetric design is used to obtain a CFD solution with slip wall boundaries at the inlet design point and serves as a flow field generator for the AAI. The AAI geometry is obtained by projecting a desired aperture shape onto a surface model of the external oblique shock. Streamline seeds are located on the projected aperture segments and transferred into the CFD solution space. The streamlines generated by these seeds inside the CFD solution space are then used as a wireframe to define the supersonic diffuser back to the throat location. Traditional design techniques are then used to define the subsonic diffuser from the inlet throat to the engine face.
    Type: Grant
    Filed: May 31, 2005
    Date of Patent: April 24, 2007
    Assignee: Lockheed Martin Corporation
    Inventors: Brian F. Lundy, John D. Klinge, Bradley C. Leland
  • Patent number: 6920890
    Abstract: The invention provides an airflow controller for a propulsion inlet system including a bleed section having two or more bleed plenum chambers, each of the chambers having a porous inlet surface and an exit surface and two or more plates slidably mounted to the bleed section and in fluid communication with the exit surface of the bleed section; and two or more plates being adjustable in multiple positions with respect to the exit surface of the bleed plenum chambers.
    Type: Grant
    Filed: July 30, 2002
    Date of Patent: July 26, 2005
    Assignee: Techland Research, Inc.
    Inventors: Bobby W. Sanders, Charlotte A. Sanders, Lois J. Weir
  • Patent number: 6880342
    Abstract: System and method for controlling inlet shock position and airflow Mach number of a hypersonic vehicle is described wherein thermally controlled fuel is controllably injected into the airflow at the inlet of the propulsion system of the vehicle.
    Type: Grant
    Filed: September 22, 2003
    Date of Patent: April 19, 2005
    Assignee: The United States of America as represented by the Secretary of the Air Force
    Inventor: David J. Moorhouse
  • Patent number: 6270309
    Abstract: A low drag ducted ram air turbine generator and cooling system is provided. The ducted ram air turbine generator and cooling system has reduced drag while extracting dynamic energy from the air stream during the complete range of intended flight operating regimes. A centerbody/valve tube having an aerodynamically shaped nose is slidably received in a fairing and primary structure to provide a variable inlet area. An internal nozzle control mechanism attached to the valve tube positions nozzle control doors to provide variable area nozzles directing air flow to the turbine stator and rotor blades to maintain optimum generator efficiency. An alternate embodiment includes an annular internal nozzle having interleaved panels to modulate the air flow to the turbine.
    Type: Grant
    Filed: December 14, 1999
    Date of Patent: August 7, 2001
    Assignee: Ghetzler Aero-Power Corporation
    Inventors: Richard Ghetzler, Jerome F. Wojtalik, Jr., Neils Kruse, Kendal R. Stephens, Harold Schmulenson
  • Patent number: 6260567
    Abstract: A mission adaptive inlet (42) for an aircraft (40) has a rigid lip panel (56) pivotally attached to an inlet (42) of the aircraft (40). An actuation mechanism is coupled to the rigid lip panel (56) and causes the rigid lip panel (56) to pivot from a first position to a second position. A reinforced elastomer system (48) is connected the rigid lip panel and the inlet (42).
    Type: Grant
    Filed: March 28, 2000
    Date of Patent: July 17, 2001
    Assignee: The Boeing Company
    Inventors: Cynthia Ann Gruensfelder, Robert Henry Wille
  • Patent number: 6209821
    Abstract: The apparatus and method employ remote sensing to measure the air temperature a sufficient distance ahead of the aircraft to allow time for a variable inlet/engine assembly to be reconfigured in response to the measured temperature, to avoid inlet unstart and/or engine compressor stall. In one embodiment, the apparatus of the invention has a remote sensor for measuring at least one air temperature ahead of the vehicle and an inlet control system for varying the inlet. The remote sensor determines a change in temperature value using the at least one temperature measurement and prior temperature measurements corresponding to the location of the aircraft. The control system uses the change in air temperature value to vary the inlet configuration to maintain the position of the shock wave during the arrival of the measured air in the inlet.
    Type: Grant
    Filed: September 14, 1999
    Date of Patent: April 3, 2001
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventor: Bruce L. Gary