Highspeed Fluid Intake Means (e.g., Jet Engine Intake) Patents (Class 137/15.1)
  • Patent number: 9758253
    Abstract: A swept gradient air boundary layer diverter for an aircraft. The aircraft includes a fuselage and an air inlet for an engine of the aircraft, where the air inlet includes a cowl at a leading edge of the inlet. The diverter includes a V-shaped ramp portion formed in the fuselage in an area proximate to and in front of the cowl where the ramp portion extends downward away from an outer surface of the fuselage towards an inside of the aircraft. The diverter also includes a V-shaped trough portion formed into the fuselage and being positioned adjacent to and integral with the ramp portion between the ramp portion and the air inlet. Air flowing over the fuselage towards the cowl is expanded and compressed by the ramp portion and the trough portion so as to create pressure gradients that generate vortices to redirect boundary layer airflow around the air inlet.
    Type: Grant
    Filed: June 25, 2015
    Date of Patent: September 12, 2017
    Assignee: Northrop Grumman Systems Corporation
    Inventors: Trajaen J. Troia, John F. Mangus
  • Patent number: 9719421
    Abstract: An aircraft gas-turbine engine has an engine cowling-nacelle which surrounds a core engine in a tubular way, characterized in that at least one inflow-side part of the engine cowling-nacelle is telescopically movable against the flow direction.
    Type: Grant
    Filed: May 31, 2012
    Date of Patent: August 1, 2017
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Predrag Todorovic
  • Patent number: 9705123
    Abstract: A battery enclosure is provided that externally shorts the enclosed battery, or batteries, immediately prior to the battery being punctured. As a result, the battery's state-of-charge is decreased, leading to a less severe reaction when the battery case is punctured.
    Type: Grant
    Filed: October 30, 2015
    Date of Patent: July 11, 2017
    Assignee: ATIEVA, INC.
    Inventors: Albert Liu, Guangyuan Zheng, Wilson Chou
  • Patent number: 9650147
    Abstract: Device for exhaust air cooling of aircraft air-conditioning systems comprising a bypass channel that bypasses an aircraft air-conditioning system arranged downstream of a ram air channel with a ram air inlet channel portion, and merges into an outlet channel, arranged downstream of the aircraft air-conditioning system, before a discharge opening for exhaust air, a common inlet being provided for the ram air channel and the bypass channel.
    Type: Grant
    Filed: November 23, 2010
    Date of Patent: May 16, 2017
    Assignee: Airbus Operations GmbH
    Inventors: Thomas Selchert, Alexander Solntsev
  • Patent number: 9644535
    Abstract: A nacelle for a gas turbine engine system includes a housing that has a pressure side and a suction side. A passage extends between the pressure side and the suction side for permitting airflow from the pressure side to the suction side. The passage includes a first curved section that has an inlet at the pressure side. A linear section is connected with the first curved section. A second curved section is connected with the linear section and has an outlet at the suction side. The outlet has a cross sectional area smaller than a cross sectional area of the linear section.
    Type: Grant
    Filed: July 8, 2014
    Date of Patent: May 9, 2017
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Steven H. Zysman, Wesley K. Lord, Robert M. Miller, Oliver V. Atassi
  • Patent number: 9623979
    Abstract: An aircraft nacelle comprising an air intake configured to channel an air flow in the direction of an engine assembly which comprises a fan with an axis of rotation, said air intake comprising, according to a flow direction of the air flow, a lip with a leading edge and an internal conduit which extends said lip towards the fan, wherein the air intake comprises a plurality of protrusions distributed over the circumference of the air intake and following each protrusion, a concave form configured in order to achieve compression of the air flow.
    Type: Grant
    Filed: June 2, 2015
    Date of Patent: April 18, 2017
    Assignee: Airbus Operations SAS
    Inventor: Francois Rouyre
  • Patent number: 9586692
    Abstract: An engine inlet assembly includes an inlet duct having a first inlet duct leg and a second inlet duct leg, the first inlet duct leg and the second inlet duct leg extending toward a common inlet duct outlet located at an engine inlet. The first inlet duct leg and the second inlet duct leg are fixedly secured to an airframe of an aircraft at an air inlet. The duct outlet has a floating interface with the engine inlet.
    Type: Grant
    Filed: April 14, 2014
    Date of Patent: March 7, 2017
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventors: Steven Bofill, Scott A. Chasen, Joseph Lawrence Simonetti, Donald William Lamb, Jr.
  • Patent number: 9517843
    Abstract: A flight vehicle includes a fuselage and a gas turbine engine. The gas turbine engine is coupled to the fuselage to provide thrust when air surrounding the flight vehicle is admitted to the gas turbine engine and combusted with fuel. The flight vehicle further includes a generator coupled to the gas turbine engine to provide power to equipment included in the vehicle.
    Type: Grant
    Filed: December 3, 2013
    Date of Patent: December 13, 2016
    Assignee: Rolls-Royce North American Technologies, Inc.
    Inventors: Kenneth M. Pesyna, Robert A. Ress, Jr.
  • Patent number: 9488139
    Abstract: An engine system including an air intake duct positioned upstream of an engine cylinder may include an ice ingestion feature for retaining condensation. An ice ingestion feature may include indents formed in the bottom of an air intake duct wall. As such, the ice ingestion feature may include compartments and/or grooves of varying depths, widths, and/or angles such that the ice retention rate may be based on the surface area of the compartment or grooves.
    Type: Grant
    Filed: March 11, 2016
    Date of Patent: November 8, 2016
    Assignee: Ford Global Technologies, LLC
    Inventors: Scott M. Rollins, Christopher B. Bishop
  • Patent number: 9482155
    Abstract: A supersonic inlet includes a relaxed isentropic compression surface to improve net propulsive force by shaping the compression surface of the inlet to defocus the resulting shocklets away from the cowl lip. Relaxed isentropic compression shaping of the inlet compression surface functions to reduce the cowl lip surface angle, thereby improving inlet drag characteristics and interference drag characteristics. Supersonic inlets in accordance with the invention also demonstrate reductions in peak sonic boom overpressure while maintaining overall engine performance.
    Type: Grant
    Filed: September 27, 2012
    Date of Patent: November 1, 2016
    Assignee: Gulfstream Aerospace Corporation
    Inventors: Timothy R. Conners, Preston A. Henne, Donald C. Howe
  • Patent number: 9422889
    Abstract: A combined engine includes a turbopump including a pump injecting hydrogen into a heater arranged in an outer casing downstream from a central body, and a subsonic turbine driving the pump, which turbine receives partially-expanded hydrogen collected at an outlet from the heater to apply the hydrogen to a supersonic turbine to operate the engine as a turbojet. The hydrogen from the supersonic turbine is collected in tubes inside the central body to be sent to a combustion chamber defined downstream from the central body, while the hydrogen that is partially expanded in the subsonic turbine is sent directly to the combustion chamber via injectors to operate the engine as a ramjet.
    Type: Grant
    Filed: November 14, 2011
    Date of Patent: August 23, 2016
    Assignee: SNECMA
    Inventors: Jean-Marie Conrardy, Nicolas Soulier
  • Patent number: 9403600
    Abstract: An air intake system suitable for a supersonic vehicle is disclosed. The system includes a channel comprising an inlet and a side wall and a plenum coupled to the side wall. The plenum is configured to accept a flow of coolant. In certain embodiments, the coolant is the waste coolant from an on-board electronics cooling system. The system also includes a porous region in the side wall configured to allow a flow of bleed air from the channel through the porous region of the side wall into the plenum so as to aid the transition to supersonic flow. In certain embodiments, the flow of the bleed air is reduced at supersonic speeds by pressurization of the plenum with the coolant.
    Type: Grant
    Filed: May 1, 2012
    Date of Patent: August 2, 2016
    Assignee: Lockheed Martin Corporation
    Inventors: Brad C. Leland, Andrew J. Tworek, Chan Cho
  • Patent number: 9394827
    Abstract: An inlet particle separator system for a vehicle engine includes a hub section, a shroud section, a splitter, and a hub suction flow passage. The shroud section surrounds at least a portion of the hub section and is spaced apart therefrom to define a main flow passageway that has an air inlet. The splitter is disposed downstream of the air inlet and extends into the passageway to divide the main flow passageway into a scavenge flow path and an engine flow path. The hub suction flow passage has a hub suction inlet port and a hub suction outlet port. The hub suction inlet port extends through the hub section and is in fluid communication with the air inlet. The hub suction outlet port extends through the splitter and is in fluid communication with the scavenge flow path.
    Type: Grant
    Filed: August 7, 2013
    Date of Patent: July 19, 2016
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Zedic Daniel Judd, Yogendra Yogi Sheoran, Devinder N. Katariya, Eduardo Guerra
  • Patent number: 9340295
    Abstract: An example inlet duct screen assembly includes a grid portion including a plurality of apertures and a frame portion circumscribing the grid portion. The grid portion and the frame portion are formed from a single sheet of material.
    Type: Grant
    Filed: July 30, 2014
    Date of Patent: May 17, 2016
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Brian C. DeDe, Jack V. Vitale, Jeffrey V. Stenberg
  • Patent number: 9334801
    Abstract: A supersonic inlet includes a relaxed isentropic compression surface to improve net propulsive force by shaping the compression surface of the inlet to defocus the resulting shocklets away from the cowl lip. Relaxed isentropic compression shaping of the inlet compression surface functions to reduce the cowl lip surface angle, thereby improving inlet drag characteristics and interference drag characteristics. Supersonic inlets in accordance with the invention also demonstrate reductions in peak sonic boom overpressure while maintaining overall engine performance.
    Type: Grant
    Filed: August 2, 2012
    Date of Patent: May 10, 2016
    Assignee: Gulfstream Aerospace Corporation
    Inventors: Preston A. Henne, Timothy R. Conners, Donald C. Howe
  • Patent number: 9254921
    Abstract: An air inlet (10) for an engine (20) of an aircraft (50), the air inlet (10) having a duct (2) feeding outside air to said engine (20) together with a filter system combining at least one filter (3) and at least one bypass device (4). Said filter (3) and said bypass device (4) are fastened on a common support (1) situated at one end of said duct (2) and on a flank of a fuselage (51) of said aircraft (50). Said bypass device (4) comprises a cover (5) and an actuator (6) controlling opening of said cover (5). Thus, when said filter (3) no longer allows outside air to pass therethrough, said cover (5) is opened, and outside air passes via the bypass device (4) in order to feed said engine (20) with outside air.
    Type: Grant
    Filed: December 10, 2013
    Date of Patent: February 9, 2016
    Assignee: Airbus Helicopters Deutschland GmbH
    Inventor: Ralf Braeutigam
  • Patent number: 9243562
    Abstract: A rotating inlet cowl for a turbine engine includes a rotation axis. The rotating inlet cowl includes a forward cone defining a forward end of the inlet cowl. The forward end is configured to be eccentric relative to the rotation axis of the inlet cowl. Furthermore, the forward cone is truncated by a truncation surface defining the forward end of the inlet cowl.
    Type: Grant
    Filed: February 12, 2015
    Date of Patent: January 26, 2016
    Assignee: SNECMA
    Inventors: Mickael Delapierre, Herve Gignoux, Gael Loro, Sylvie Wintenberger
  • Patent number: 9212663
    Abstract: A supersonic fan has at least two fan blades extending radially from a rim surface of a hub and is circumscribed by a duct. An inboard leading edge having an inboard sweep angle rotates at approximately Mach 1 or greater. A low-pressure zone generates propulsion. An inboard flow regime may migrate outboard from the rim surface and contaminate the low-pressure zone, reducing propulsion. An outboard leading edge having an outboard sweep angle extends radially from the inboard leading edge to form an apex. The inboard and outboard sweep angles are each at least approximately 30 degrees and in the opposite direction. An inboard vortex forming near to and as a result of the apex trails circumferentially across the fan blades and is positioned to substantially confine the inboard flow regime to be inboard of the apex, thereby preserving the low-pressure zone and increasing propulsion for the supersonic fan.
    Type: Grant
    Filed: January 27, 2014
    Date of Patent: December 15, 2015
    Inventor: Terrence O'Neill
  • Patent number: 9139306
    Abstract: An aircraft nacelle with a connecting device between a first conduit of an air intake and a second conduit of a motor, both conduits being arranged end-to-end, the connecting device including an annular flange connected to the air intake, an annular flange connected to the motor pressed against annular flange of the air intake, the flanges extending in a plane perpendicular to the longitudinal axis of the nacelle; bolt holes formed in annular flanges and disposed plumb to one another; and connecting elements located in bolt holes, for connecting the annular flanges, wherein at least one flange includes at least one opening interposed between a bolt hole and junction zone of the flange and/or between a bolt hole and outer edge of the flange.
    Type: Grant
    Filed: August 3, 2012
    Date of Patent: September 22, 2015
    Assignee: Airbus Operations (S.A.S.)
    Inventors: Alain Porte, Stéphane Dida, Matthieu Fargues, Martial Marro, Emeric Chancerelle
  • Publication number: 20150144201
    Abstract: A method of securing two components to each other includes locating a mounting strip at a first mounting flange of a first component. The mounting strip is slidably affixed to the first component and includes a plurality of strip openings and a tightening ramp located at each strip opening of the plurality of strip openings. A second component is located such that a second mounting flange of the second component abuts the first mounting flange. A plurality of fasteners are located at the second mounting flange. A fastener of the plurality of fasteners extends through each strip opening of the plurality of strip openings. The mounting strip is slid in a direction to increase tension on the plurality of fasteners via an increasing height of the tightening ramp under a fastener head of the fastener, thereby securing the first mounting flange to the second mounting flange.
    Type: Application
    Filed: November 25, 2013
    Publication date: May 28, 2015
    Applicant: Sikorsky Aircraft Corporation
    Inventor: Scott A. Chasen
  • 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
  • Publication number: 20150129045
    Abstract: A nacelle inlet is provided for a turbo-fan engine for an aircraft. The nacelle inlet includes a lip skin having first and second pad-ups, an inner barrel including a forward flange and a bulkhead. The bulkhead, the lip skin and the inner barrel are attached together at mating surfaces. The bulkhead and the lip skin are attached together at mating surfaces. Each mating surface defines a surface geometry which approximates a developable surface having parallel ruling lines. The developable surfaces are formed by machining.
    Type: Application
    Filed: November 11, 2013
    Publication date: May 14, 2015
    Applicant: The Boeing Company
    Inventors: Daniel J. Kane, Stuart W. Vogel, Hoa V. Truong, Michael W. Kass, Andrew T. Gilmore, Paul D. Whitmore, Jack W. Mauldin, Alejandro Silva, John Ybarra
  • Patent number: 9027583
    Abstract: A supersonic inlet having a cowl lip configured to capture the conic shock and exhibit a zero or substantially zero cowl angle is disclosed herein. The inlet may be configured to employ a relaxed isentropic compression surface and an internal bypass. The nacelle bypass may prevent flow distortions, introduced by the capture of the conic shock, from reaching the turbomachinery, thereby allowing the cowl angle to be reduced to zero or substantially zero. Such a cowl angle may reduce the inlet's contribution to the overall sonic boom signature for a supersonic aircraft while allowing for an increase in engine pressure recovery and a subsequent improvement in generated thrust by the engine.
    Type: Grant
    Filed: December 5, 2012
    Date of Patent: May 12, 2015
    Assignee: Gulfstream Aerospace Corporation
    Inventor: Timothy R. Conners
  • Publication number: 20150122952
    Abstract: A gas turbine engine has an inlet duct formed to have a shape with a first ellipse in one half and a second ellipse in a second half. The second half has an upstream most end which is smaller than the first ellipse. The inlet duct has a surface defining the second ellipse which curves away from the first ellipse, such that the second ellipse is larger at an intermediate location. The second ellipse is even larger at a downstream end of the inlet duct leading into a fan.
    Type: Application
    Filed: February 20, 2014
    Publication date: May 7, 2015
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: Razvan Virgil Florea, Claude G. Matalanis, Mark B. Stucky
  • Publication number: 20150122954
    Abstract: A variable area engine inlet of a helicopter is provided and includes first inlet portions disposed to face one another in opposite directions and at a distance from one another and second inlet portions extending between the first inlet portions and being disposed to face one another in opposite directions and at a distance from one another. The first and second inlet portions define a capture area and at least one or both of the first and second inlet portions include a movable portion disposed to occupy and move between first and second positions. The first position is associated with a non-constricted condition of the capture area and the second position is associated with a constricted condition of the capture area.
    Type: Application
    Filed: November 7, 2013
    Publication date: May 7, 2015
    Applicant: Sikorsky Aircraft Corporation
    Inventor: Donald William Lamb, JR.
  • Publication number: 20150113999
    Abstract: An apparatus comprises a leading edge of an inlet. The leading edge of the inlet is positioned relative to a direction of air flow such that a total pressure of air along the leading edge of the inlet is equalized within selected tolerances.
    Type: Application
    Filed: October 31, 2013
    Publication date: April 30, 2015
    Applicant: THE BOEING COMPANY
    Inventors: Paul R. Tretow, Robert Henry Willie, Donald Edwin Robinson
  • Publication number: 20150115099
    Abstract: An inlet door system includes a duct, an inlet door, and a plurality of openings. The duct is configured to extend from the auxiliary power unit (APU) to an intake opening formed in an outer surface of an aircraft. The duct includes an inlet port, an outlet port, and a duct sidewall extending between the inlet port and the outlet port. The inlet door includes an inner surface, an outer surface, and an outer peripheral edge between the inner and outer surfaces. The door is rotationally coupled to the duct, and is configured to selectively rotate between a closed position and a plurality of open positions. The openings extend through the inlet door between the inner surface and outer surface, and each opening is disposed adjacent to the outer peripheral edge.
    Type: Application
    Filed: October 25, 2013
    Publication date: April 30, 2015
    Inventors: Murali Krishnan Payangapadan, Vunnam Kiran, Lavan Kumar Gundeti, Yogendra Yogi Sheoran, Bruce Dan Bouldin
  • Publication number: 20150114481
    Abstract: A method and apparatus for supplying air to a precooler. Air flow is created through a fan duct in an engine system. A first portion of the air flow is directed into a first inlet of an inlet system to feed a first half of the precooler. A second portion of the air flow is directed through the fan duct into a second inlet of the inlet system to feed a second half of the precooler.
    Type: Application
    Filed: October 31, 2013
    Publication date: April 30, 2015
    Applicant: THE BOEING COMPANY
    Inventors: Robert Henry Willie, Paul R. Tretow
  • Patent number: 9016042
    Abstract: An inner fixed structure of a thrust reverser includes an inner skin, an outer skin, a cellular core disposed between the inner skin and the outer skin, and at least one crack and delamination stopper extending radially between the inner skin and the outer skin.
    Type: Grant
    Filed: May 11, 2012
    Date of Patent: April 28, 2015
    Assignee: Rohr, Inc.
    Inventors: Song Chiou, Jia Yu, Claude Hubert, Michael Layland
  • Patent number: 9010084
    Abstract: An aircraft nacelle including a pipe (32), a peripheral wall (34), a lip (36), and a front frame (38) connecting the peripheral wall (34) and the pipe (32) and forming with the lip (36) a space (50) in which the hot air that is provided for frost treatment can circulate, with the pipe (32) including a coating (44) for the composite material acoustic treatment, is characterized in that the nacelle includes at least one element (52) made of a heat-conducting material inserted between the lip (36) and the pipe (32) ensuring the continuity of the aerodynamic surfaces of the lip (36) and the pipe (32) and the propagation of heat from the space (50) toward the rear of the nacelle, whereby the at least one element (52) includes a coating (54) for acoustic treatment that is made of a heat-resistant material.
    Type: Grant
    Filed: January 28, 2010
    Date of Patent: April 21, 2015
    Assignee: Airbus Operations SAS
    Inventors: Frédéric Chelin, Alain Porte, Fabrice Gantie, Jacques Lalane
  • Patent number: 9003760
    Abstract: An acoustic treatment panel that is connected to an air intake of an aircraft nacelle, includes at least one acoustically resistive structure (30) and a reflective layer (32), between which are located—in a direction that is essentially perpendicular to the longitudinal direction of the nacelle—bands (34) of alveolar cells spaced in such a way as to allow the passage of hot air provided for a frost treatment, characterized in that it includes pipes (36) for hot air that are each delimited by at least one partition that extends from the acoustically resistive layer (30) up to the reflective layer (32) in such a way as to insulate the bands (34) of cells in the longitudinal direction.
    Type: Grant
    Filed: January 29, 2010
    Date of Patent: April 14, 2015
    Assignee: Airbus Operations SAS
    Inventors: Frédéric Chelin, Thierry Surply, Dominique Haro, Fabrice Gantie, David Lambert
  • Publication number: 20150096627
    Abstract: One example of an engine mounted inlet plenum for a rotorcraft includes an inlet flange, an outlet flange and a plenum duct that connects the inlet flange and the outlet flange. The inlet flange, which defines an inlet to flow air into a barrier filtration system, is configured to be substantially aligned with a closed cowl door assembly of the rotorcraft. In some implementations, the plenum duct is configured to extend to an outer mold line (OML) of the rotorcraft such that the inlet flange is aligned with the OML. The outlet flange defines an outlet to flow air filtered by the barrier filtration system into an engine of the rotorcraft. The plenum duct allows air to flow from the inlet to the outlet.
    Type: Application
    Filed: October 8, 2013
    Publication date: April 9, 2015
    Inventors: Zachary Dailey, Thomas Mast
  • 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: 8973370
    Abstract: A supersonic nacelle design employing a bypass flow path internal to the nacelle and around the engine is disclosed herein. A set of aerodynamic vanes may be used to shape a supersonic airflow within a bypass around an engine. The vanes may be capable of compressing the supersonic airflow into a subsonic airflow, direct the subsonic airflow around the engine, and then expand the subsonic airflow into a supersonic exhaust. The vanes may shape the airflow by reducing sonic boom strength, cowl drag, and airframe interference drag.
    Type: Grant
    Filed: June 13, 2014
    Date of Patent: March 10, 2015
    Assignee: Gulfstream Aerospace Corporation
    Inventor: Timothy R. Conners
  • Patent number: 8960596
    Abstract: Systems, equipment, and methods to deposit energy to modify and control shock waves and hypersonic or supersonic fluid flow, including systems for controlling, mitigating, and/or effecting air flow in relation to air vehicles, wind tunnels, or other assets, or the like, as well as systems, equipment, and methods for disrupting the shock structure at the inlet for the engine of an air vehicle traveling at supersonic or hypersonic speed; mitigating blast effects on vehicles; mitigating heating of throats in supersonic and hypersonic wind tunnels, as well as control the flow parameters and Mach number in their test sections.
    Type: Grant
    Filed: August 20, 2008
    Date of Patent: February 24, 2015
    Inventor: Kevin Kremeyer
  • 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
  • Publication number: 20150030445
    Abstract: A nacelle for a turbojet engine has a longitudinal axis and a rear section including an annular vein formed by a wall of a fixed internal structure and a wall of an external structure. The nacelle includes a device for modulating the cross-section of a space formed by the annular vein. The device includes an injector to inject an auxiliary flow of a gas so as to vary the orientation or speed of the auxiliary flow, a suction orifice for drawing in part of the injected auxiliary flow, and an internal auxiliary flow return area in one or more walls.
    Type: Application
    Filed: July 18, 2013
    Publication date: January 29, 2015
    Applicant: AIRCELLE
    Inventors: Patrick GONIDEC, Laurent Albert Blin
  • Publication number: 20150027545
    Abstract: An apparatus for suppressing shock-induced separation of high speed airflow from a relatively low-energy boundary layer. The apparatus may include an actuator or array of actuators configured to alternately inhale and exhale fluid and positioned to alternately inhale fluid from and exhale fluid into a boundary layer of a fluid mass flowing along the wall. The actuator may be positioned to inhale fluid from a boundary layer separation bubble induced by a supersonic shock wave propagated in the fluid mass.
    Type: Application
    Filed: July 26, 2013
    Publication date: January 29, 2015
    Applicant: Lockheed Martin Corporation
    Inventors: Dan J. Baruzzini, Daniel N. Miller, Neal D. Domel, Jeff G. Hakes
  • Publication number: 20150030446
    Abstract: The disclosure relates to a nacelle for a turbojet engine, including an upstream section forming an air intake lip and defining a space for the circulation of a main air flow. The nacelle includes a device for modulating the cross-section of the space and has means for injecting an auxiliary flow of a gas by means of an induced ejector effect; suction means for drawing in the injected auxiliary flow; and an internal auxiliary flow return area in one or more walls, the area being configured to allow the circulation of the injected auxiliary flow and the drawn-in auxiliary flow and to bring part of the injected auxiliary flow into contact with the main air flow. The internal return area includes an outer front part forming an area in which the thickness of the internal return area is reduced.
    Type: Application
    Filed: July 19, 2013
    Publication date: January 29, 2015
    Applicant: Aircelle
    Inventors: Patrick Gonidec, Laurent Albert Blin
  • Publication number: 20150007895
    Abstract: The present application relates to a splitter nose of an axial turbomachine configured to separate an annular flow into the turbomachine into a primary flow and a secondary flow, and including: a generally circular leading edge, an annular wall extending from the leading edge and bounding the secondary flow, and at least one duct for a de-icing fluid for the splitter nose extending substantially axially along the wall and opening out into the primary flow. The external surface of the wall is formed by a sheet bounding the de-icing duct.
    Type: Application
    Filed: July 3, 2014
    Publication date: January 8, 2015
    Inventors: Ghislain Herbaut, Benoit Baldewijns
  • Publication number: 20150007896
    Abstract: An air intake structure for a turbojet engine nacelle includes an inner panel to be attached to a fan casing, and an external panel capable of a translational movement in a longitudinal direction of the nacelle. The external panel incorporates a portion of an air inlet lip able to provide a junction between the inner panel and the external panel, and each of the air inlet lip portion and the inner panel is equipped, at least in the region of a joining end, with an acoustic attenuation structure. In particular, at least one of the joining ends is equipped with a radial buffer able to come into contact with a corresponding joining flange exhibited by the other joining end when the external panel is in a closed position.
    Type: Application
    Filed: September 25, 2014
    Publication date: January 8, 2015
    Inventors: Jean-Philippe JORET, André BAILLARD
  • Publication number: 20150000252
    Abstract: A propulsion system and methods are presented. A substantially tubular structure comprises a central axis through a longitudinal geometric center, and a first fan rotates around the central axis, and comprises a first fan hub and first fan blades. The fan hub is rotationally coupled to the substantially tubular structure, and the first fan blades are coupled to the first fan hub and increase in chord length with increasing distance from the first fan hub. A second fan is rotationally coupled to the substantially tubular structure and rotates around the central axis and contra-rotates relative to the first fan. Second fan blades are coupled to the second fan hub, and a nacelle circumscribing the first fan and the second fan is coupled to and rotates with the first fan.
    Type: Application
    Filed: November 12, 2012
    Publication date: January 1, 2015
    Inventors: Matthew D. Moore, Kelly L. Boren
  • Publication number: 20140373927
    Abstract: A supersonic nacelle design employing a bypass flow path internal to the nacelle and around the engine is disclosed herein. A set of aerodynamic vanes may be used to shape a supersonic airflow within a bypass around an engine. The vanes may be capable of compressing the supersonic airflow into a subsonic airflow, direct the subsonic airflow around the engine, and then expand the subsonic airflow into a supersonic exhaust. The vanes may shape the airflow by reducing sonic boom strength, cowl drag, and airframe interference drag.
    Type: Application
    Filed: June 13, 2014
    Publication date: December 25, 2014
    Inventor: Timothy R. Conners
  • Patent number: 8915061
    Abstract: A propulsion system and an aircraft that includes the propulsion system are provided. The propulsion system includes an engine and a cowling that surrounds at least a portion of the engine. The propulsion system also includes an inlet. The inlet includes a compression surface that is upstream and external to the cowling. The compression surface can slow air flow from a supersonic speed to a subsonic speed before the air flow enters the cowling.
    Type: Grant
    Filed: May 24, 2010
    Date of Patent: December 23, 2014
    Assignee: Lockheed Martin Corporation
    Inventors: Jon Thomas Anderson, John D. Klinge, Kenneth J. Hajic, Zachary S. Davis
  • Publication number: 20140352797
    Abstract: In various embodiments, a jet engine, as described herein, may include a fan case, a fan cowl, and an air inlet. Further, in various embodiments, at least one of the fan case and the fan cowl may be directly coupled to the air inlet. In addition, in various embodiments, the fan case, the fan cowl, and the air inlet may be manufactured as a single, unitary, engine part.
    Type: Application
    Filed: June 4, 2013
    Publication date: December 4, 2014
    Inventors: Michael Aten, Aleksandar Ratajac
  • Publication number: 20140352795
    Abstract: An air inlet deflector for a structure having an air inlet. The deflector may be retractable within the structure, may be integrally formed with the structure, and may prevent the structure from ingesting foreign matter, such as birds. The deflector may include a series of ribs, spokes, or vanes that may vary in width and/or thickness from fore to aft, and/or may be curvilinear in one or more planes of view, and/or may serve double duty as inlet vanes for redirecting inlet air.
    Type: Application
    Filed: May 7, 2013
    Publication date: December 4, 2014
    Inventor: Michael J. Kline
  • Patent number: 8899255
    Abstract: A turbojet engine nacelle, including an air intake structure for directing an airflow towards a fan of the turbojet engine, a middle structure attached to the air intake structure for surrounding the fan of the turbojet engine, the air intake structure including an inner panel attached to the middle structure and defining a fixed structure with the middle structure, and an outer panel including an air intake lip at the end thereof opposite the middle structure, the outer panel being longitudinally translatably movable relative to the inner panel. The nacelle further includes at least one rod having one end attached onto a flange of the air intake lip and a mechanism rigidly connected to the middle structure for securing and locking the other end of each rod by applying a traction force thereon.
    Type: Grant
    Filed: February 4, 2010
    Date of Patent: December 2, 2014
    Assignee: SNECMA
    Inventors: Herve Jean Albert Mouton, Thomas Alain Christian Vincent
  • Patent number: 8887486
    Abstract: A ram air fan inlet housing for containing a ram air fan rotor. The inlet housing includes a flanged surface and an interior surface. The flanged surface is perpendicular to an axis of the inlet housing and defines a flange plane at an axial end of the inlet housing. The interior surface is symmetric about the axis of the inlet housing and includes a flange section, a transition section, an outlet section, a rotor section, and an inlet section.
    Type: Grant
    Filed: October 24, 2011
    Date of Patent: November 18, 2014
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Seth E. Rosen, Eric Chrabascz, Victoria S. Richardson
  • 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