Air Intakes Patents (Class 244/53B)
  • Patent number: 6142417
    Abstract: A self-deploying inlet for an air breathing missile including an inlet body having a natural shape which defines a deployed condition for the air inlet, wherein an air deflecting surface is provided thereby. The inlet body is made from a material having a flexibility which enables the inlet body to flex from the deployed condition to a stowed condition, and a resiliency which biases the inlet body toward the deployed condition when in the stowed condition. The air inlet further includes a sealing connector system for connecting the inlet body to the vehicle in a manner which enables the inlet body to move between the stowed condition and the deployed condition. The natural spring force provided by the resiliency of the inlet body, along with the aerodynamic forces to which the inlet is subjected during missile flight, are sufficient to cause the inlet to self-deploy to the deployed condition from the stowed condition without the need for a deployment actuator.
    Type: Grant
    Filed: October 26, 1998
    Date of Patent: November 7, 2000
    Assignee: Atlantic Research Corporation
    Inventor: Irving E. Figge, Sr.
  • Patent number: 6138950
    Abstract: In accordance with the present invention, there is provided an aircraft engine air intake cover for use with an air intake which is characterized by an air velocity profile therewithin. The air intake cover is provided with an air induction plate which disposed across at least a portion of the air intake. The air intake cover is further provided with a multitude of air induction ducts. The induction ducts are disposed about and extend through the air induction plate. Each induction duct has a duct inlet, a duct outlet and a duct body interposed between the duct inlet and the duct outlet. The duct inlets each respectively define an effective inlet diameter. The duct bodies each respectively define a duct body length which is greater than the associated effective duct inlet diameter. The duct outlets each respectively define an effective outlet diameter greater than the effective inlet diameter for increasing the cohesiveness of the air velocity profile within the air intake.
    Type: Grant
    Filed: October 6, 1998
    Date of Patent: October 31, 2000
    Assignee: Northrop Grumman Corporation
    Inventors: Barnaby Sam Wainfan, Yu Ping Liu, Daniel R. Rihn, Douglas William Leggett, Martin James Georges, Jeffry Scott Philhower, Douglas Ellwood Shultz, Charles Boccados
  • Patent number: 6138946
    Abstract: The device for lift and to reduce forward resistance of aircraft consists of a converging input duct of truncated-cone-shaped or truncated-pyramid-shaped, arranged lengthwise inside the fuselage and inclined to the longitudinal axis, with the larger opening coinciding with the front fuselage contour or periphery of maximum cross-section, and reducing in bore backwards so that its generatrix or lower side coincides with the lower surface of the fuselage parallel to the aircraft's longitudinal axis and the generatrix or upper edge forms an acute angle with the aircraft's longitudinal axis. The narrowest end of the duct discharges into the input of the turbofan, UHD, etc. type drive engines which discharge through a rear outlet duct facing backwards with the rear end curved slightly downward.
    Type: Grant
    Filed: August 7, 1998
    Date of Patent: October 31, 2000
    Inventor: Manuel Munuoz Saiz
  • Patent number: 6131855
    Abstract: The present invention relates to an air inlet cowl (9) for a jet engine. According to the invention, provided in the partition (20) delimiting the de-icing chamber (21) in the hollow leading edge (16) of the cowl is a trough-shaped duct (22) for ejecting to the outside pressurized hot air which has flowed through the chamber (21). The duct (22) is reduced in cross section by a single oblong orifice (18) made, parallel to the leading edge (16), in a part (23) that forms part of the external surface (9E) of the cowl (9).
    Type: Grant
    Filed: December 2, 1998
    Date of Patent: October 17, 2000
    Assignee: Societe Nationale Industrielle et Aerospatiale
    Inventor: Alain Porte
  • Patent number: 6129509
    Abstract: The particle trap (15) that extends behind an elbow in the air flow stream (6) in a turbo-prop engine is delimited at the back by an end plate (12) to which intake housing suspension rods (10) supporting the front of the rotating shaft (2), are fastened. It is divided by suspension arms (11) which may be drilled (21) to restore the continuity of the annular chamber forming the trap. Therefore the intake housing suspension device extends through the trap. This type of trap makes use of the inertia of solid bodies carried by the air drawn in, and which could damage the engine blades, and to collect them.
    Type: Grant
    Filed: June 29, 1999
    Date of Patent: October 10, 2000
    Assignee: Societe Nationale d'Etude et de Construction de Moteurs d'Aviation "Snecma"
    Inventors: Antoine Emmanuel Cousin, Georges Mazeaud
  • Patent number: 6129309
    Abstract: An aircraft engine apparatus with a reduced inlet vortex is provided which utilizes a vortex disruption system that periodically discharges pulses of engine bleed fluid through at least one outlet port opening through the inlet of the engine nacelle to disrupt the engine inlet vortex. The vortex disruption system thereby prevents ingestion of foreign matter into the engine inlet without sacrificing engine power, efficiency, or aircraft cruise performance.
    Type: Grant
    Filed: July 24, 1998
    Date of Patent: October 10, 2000
    Assignee: McDonnell Douglas Corporation
    Inventors: David M. Smith, John Dorris, III
  • Patent number: 6119985
    Abstract: A reusable rocket airplane which may be utilized to launch satellites and other payloads into space. The airplane may also be used for rapid surface to surface flight. The reusable rocket airplane may be safely supplied with oxidizer in mid-air, achieve an altitude outside the Earth's atmosphere, and return safely to be used again. The rocket airplane utilizes unique concepts to secure its gas turbine engines for high speed flight, minimize fluid spillage during mid-air oxidizer transfer, as well as employs design features advantageous to the economical building and reuse of the rocket airplane.
    Type: Grant
    Filed: March 7, 1997
    Date of Patent: September 19, 2000
    Assignee: Pioneer Rocketplane Corporation
    Inventors: Mitchell B. Clapp, Robert M. Zubrin
  • Patent number: 6089505
    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: July 22, 1997
    Date of Patent: July 18, 2000
    Assignee: McDonnell Douglas Corporation
    Inventors: Cynthia Ann Gruensfelder, Robert Henry Wille
  • Patent number: 6089504
    Abstract: A jet aircraft has a generally cylindrical fuselage section defining a passenger compartment and a generally conical aft fuselage section having a maximum lateral dimension substantially smaller than the lateral dimension of the fuselage section. A propulsion engine is mounted on the vertical stabilizer of the fuselage and has an air inlet disposed entirely within a rearward projection of the fuselage passenger compartment to preclude the ingestion of foreign objects into the engine.
    Type: Grant
    Filed: July 22, 1997
    Date of Patent: July 18, 2000
    Assignee: Williams Internaitonal Co., L.L.C.
    Inventors: Samuel B. Williams, Elbert L. Rutan
  • Patent number: 6082669
    Abstract: The system (13) for admitting external air (12) into a working section (11) of a gas turbine engine through a jacket (10) of the working section is characterised by the combination of doors (15) sliding towards the front (ramps) and rotating doors (14). The ramps (15) are fitted with grooved lateral arms (30) in which run wheels mounted on the doors (14). When they reach an ascending part (33) of the grooves (31) after sufficient movement of the ramps (15) towards the front, they are caused to rise, which opens the doors (14). This system can be used on double flow gas turbine engines for supersonic aircraft.
    Type: Grant
    Filed: May 4, 1998
    Date of Patent: July 4, 2000
    Assignee: Societe Nationale d'Etude et de Construction de Moteurs d'Aviation "Snecma"
    Inventors: Thierry Pascal Bardagi, Gerard Ernest Andre Jourdain
  • Patent number: 6079667
    Abstract: An auxiliary inlet (60) for a jet engine has a first rod block (62) attached to a first side (64) of a hole (66) in a skin (68) of an inlet of the jet engine. A second rod block (80) is attached to an opposing side (82) of the hole (66) in the skin (68) of the inlet of the jet engine. A first reinforced elastomer section (70) is attached to the first rod block (62). A center beam (74) has a first side attached to the first reinforced elastomer section (70). A second reinforced elastomer section (78) is attached to the second rod block (80) and attached to the center beam (74). An actuation system (88, 90) is connected to an intake end of the center beam (74). The actuation system (88, 90) moves the center beam (74) from a first in-moldline position to a second out-of-moldline position.
    Type: Grant
    Filed: June 9, 1998
    Date of Patent: June 27, 2000
    Assignee: McDonnell Douglas Corporation
    Inventor: Cynthia Ann Gruensfelder
  • Patent number: 6079670
    Abstract: The present invention relates to an air inlet cowl (9) for a jet engine, especially for an aircraft. According to the invention, the diffuser (12) of hot air for de-icing, arranged in the hollow leading edge (16) of the cowl (9) is in the form of a polygonal ring and is fixed by elastic support tabs (24) each equipped with a ball joint (25) holding a straight portion (22) of the polygonal ring.
    Type: Grant
    Filed: December 2, 1998
    Date of Patent: June 27, 2000
    Assignee: Aerospatiale Societe Nationale Industrielle
    Inventor: Alain Porte
  • Patent number: 6068213
    Abstract: A ducted fan aircraft turbojet engine having an inner engine core cowling, an outer fan shroud, an outer fan outlet cowling including a thrust reverser, a fan exhaust duct between the inner engine core cowling and the outer fan outlet cowling, at least one fan shroud brace connecting the engine and the outer fan shroud, and at least one fairing element extending into and along the fan exhaust duct and located directly adjacent and rearwardly of the at least one fan shroud brace. The at least one fairing may be connected directly to the at least one fan shroud brace, the inner engine core cowling or the outer fan outlet cowling. The invention has utility where the fan outlet cowling and thrust reverser are mounted independently of the inner engine core cowling over their respective inner areas.
    Type: Grant
    Filed: June 12, 1998
    Date of Patent: May 30, 2000
    Assignee: Societe Hispano Suiza Aerostructures
    Inventors: Patrick Gonidec, Pascal Gerard Rouyer, Guy Bernard Vauchel
  • Patent number: 6050527
    Abstract: A flow control device and method for eliminating flow-induced cavity resonance within a closed or nearly closed end flow passage (20) having an inlet opening (30) defined between an upstream inlet edge (32) and a downstream inlet edge (34). The passage accepts exterior fluid flow (38) therein via the opening (30). The flow control device includes a stationary inlet guide vane (44) having a leading edge (46), a trailing edge (48), and a number of support members (50) to connect the vane to the inlet. The vane (44) is positioned such that the vane leading edge intercepts the exterior fluid flow shear layer, and the vane trailing edge extends into the passage at the inlet. In a preferred embodiment, the inlet guide vane is located approximately midway between the upstream and downstream inlet edges. The inlet guide vane is cross-sectionally shaped as a cambered airfoil.
    Type: Grant
    Filed: December 19, 1997
    Date of Patent: April 18, 2000
    Assignee: The Boeing Company
    Inventors: Leonard J. Hebert, Wendell R. Miller, Eric H. Nesbitt, Jerry Piro, Michael L. Sangwin
  • Patent number: 6027078
    Abstract: A method and apparatus using localized heating to encourage laminar flow along an airfoil exterior surface. The airfoil includes a leading edge (24), a controlled surface (18), and an uncontrolled surface (20). The present invention localized heating system (38) includes a heat source (40) located within the airfoil and connected to the leading edge (24), and a heat sink (42) positioned aft of the heat source (40) and arranged to transfer heat from the airfoil controlled surface (18) to the uncontrolled surface (20). The heat sink (42) preferably expels heat along uncontrolled surface adjacent to turbulent air flow. In one preferred embodiment as applied to a generally circular aircraft engine nacelle (12), the heat source (40) is an electro-thermal heat source (44) having a high resistance wire embedded in a composite material leading edge structure (50), and the heat sink (42) is a heat pipe (52) having a wicking material (58) and a vaporizing agent (60).
    Type: Grant
    Filed: February 27, 1998
    Date of Patent: February 22, 2000
    Assignee: The Boeing Company
    Inventors: Jeffrey D. Crouch, Lian L. Ng
  • Patent number: 6003302
    Abstract: A ramjet having an annular working duct (10) which is formed by outer (15) and inner (20) tubular casings. The duct (10) is adjustable by the longitudinal displacement of inner casing (20) along outer casing (15).
    Type: Grant
    Filed: May 10, 1996
    Date of Patent: December 21, 1999
    Inventor: Peter Feldman
  • Patent number: 5961067
    Abstract: An apparatus and method for reducing noise within the fuselage of a propeller driven aircraft. In one embodiment the propeller blades are spaced apart and in front of an offset inlet. The inlet provides air to a gas turbine engine powering the propeller, and also to a scavenge duct. The propeller blades and inlet are spaced apart such that during cruise conditions for the aircraft, the trailing edge of the propeller blades are spaced apart from the inlet by more than one-fourth of the chord length of the propeller blades, and less than about the chord length of the propeller blades. This spacing reduces the aerodynamic interaction between the propeller blades and a bubble of partially stagnated air in front of the inlet. In another embodiment, the scavenge duct is constructed such that it flows an increased amount of air, thus allowing the inlet duct to flow an increased amount of air.
    Type: Grant
    Filed: August 27, 1997
    Date of Patent: October 5, 1999
    Assignee: Allison Engine Company
    Inventors: Edward J. Hall, Joseph P. Meade
  • Patent number: 5957405
    Abstract: A jet aircraft has a generally conical front fuselage section, a cylindrical intermediate fuselage section defining a passenger compartment and a generally conical aft fuselage section having a maximum lateral dimension substantially smaller than the maximum lateral dimension of the intermediate fuselage section. The aircraft's propulsion engines are mounted on combination vertical and horizontal stabilizers in spaced relation to the conical aft fuselage section with the air inlets and exhaust nozzles thereof disposed entirely within a rearward projection of the lateral cross section of the intermediate fuselage section to preclude the ingestion of foreign objects thereinto and maximize efficiency of boundary layer air flow.
    Type: Grant
    Filed: July 21, 1997
    Date of Patent: September 28, 1999
    Assignee: Williams International Co., L.L.C.
    Inventor: Samuel B. Williams
  • Patent number: 5934611
    Abstract: An air intake system disposable in an air vehicle turbo engine housing disposed in an exterior airflow for selectively reducing external engine boundary layer separation drag and external engine friction drag on the engine housing comprising an air inlet member for receiving engine intake air disposable within the engine housing. The air intake system further comprising a first air exit port disposed in fluid communication with the air inlet member, adapted to direct intake air from the air inlet member and to direct intake air substantially in the direction of exterior airflow, to reduce external engine boundary layer separation drag. The air intake system further comprising a second air exit port disposed in fluid communication with the air inlet member, adapted to direct intake air from the air inlet member and to direct intake air substantially in a direction perpendicular to the exterior airflow, to reduce external engine friction drag.
    Type: Grant
    Filed: October 20, 1997
    Date of Patent: August 10, 1999
    Assignee: Northrop Grumman Corporation
    Inventors: Runyon H. Tindell, Charles A. Parente
  • Patent number: 5906334
    Abstract: An aircraft turboshaft engine intake includes an axial diffuser and a colinear plenum disposed in flow communication therewith for collecting diffuser air therefrom. A scroll is disposed radially below the plenum in flow communication therewith for accelerating the plenum air for discharge to the aircraft engine. In this arrangement, propeller air is diffused in the diffuser and collected in the plenum wherein it is turned radially inwardly and accelerated through the scroll into the, engine. Diffusion is uncoupled from air turning for improving the efficiency thereof.
    Type: Grant
    Filed: January 29, 1998
    Date of Patent: May 25, 1999
    Assignee: General Electric Company
    Inventors: Anthony J. Chamay, Isaac Zelazny
  • Patent number: 5881758
    Abstract: An internal compression engine inlet (39) including a flexible external cowl with leading edge cowl lips (72); a duct comprising a supersonic diffuser (44) defined by upper and lower forward ramps (50), (52), a subsonic diffuser (46) defined by upper and lower aft ramps (54), (56), and a throat region (48); a first slot (58) formed between adjacent ends of the upper forward and upper aft ramps; and a second slot (60) formed between adjacent ends of the lower forward and lower aft ramps, is provided. Each slot (58), (60) opens to a plenum (120), (122) having a vent door (126) covering a vent (124) that opens to a low pressure volume.
    Type: Grant
    Filed: March 28, 1996
    Date of Patent: March 16, 1999
    Assignee: The Boeing Company
    Inventors: Joseph L. Koncsek, Kenneth J. Marrs
  • Patent number: 5865398
    Abstract: A multi-function air inlet control apparatus for an aircraft engine includes an air inlet frame housing a plurality of adjacent, spaced apart louvers attached by hinges at opposing ends to the air inlet frame. The hinges allow the louvers to pivot through a substantially 180 degree angle defined by a vertical plane of the air inlet frame. A linking device interconnects with each of louvers, whereby the louvers are moved in unison through the substantially 180 degree angle. An actuator communicates with the linking device for controlling the movement of the louvers in response to operating parameters of the aircraft engine. The multi-function air inlet control is a single device that fulfills the need for additional air during takeoff and other critical modes, and that will dump air overboard when the engine is throttling or is shut down.
    Type: Grant
    Filed: January 14, 1997
    Date of Patent: February 2, 1999
    Assignee: McDonnell Douglas Corporation
    Inventors: Terry F. Pashea, Donald L. Williams
  • Patent number: 5779189
    Abstract: A diverterless engine inlet system that integrates a "bump" surface with a forward swept, aft-closing cowl to divert substantially all of the boundary layer air from the inlet. The bump includes an isentropic compression surface raised outwardly from the body of the aircraft to form a portion of the inner surface of the inlet. The cowl couples to the body of the aircraft to form the remaining surfaces of the inlet and closes against the body of the aircraft at the aft-most points of the inlet opening. The bump and the cowl work together to divert low energy boundary layer air from the inlet during aircraft operation, thus eliminating the requirement for a boundary layer diverter. The diverterless inlet provides a lower cost, reduced complexity air induction system that can be used on a supersonic aircraft engine.
    Type: Grant
    Filed: March 19, 1996
    Date of Patent: July 14, 1998
    Assignee: Lockheed Martin Corporation
    Inventors: Jeffrey William Hamstra, Thomas Gerard Sylvester
  • Patent number: 5779169
    Abstract: An aircraft for vertical or short take off and landing operations having two main lift nozzles, both positioned at or near the aircraft center of gravity utilizes one or more jet screen nozzles, arranged in a variety of shapes and combinations, discharging bypass air from a position forward of the center of gravity, and a variable pitch nozzle discharging engine exhaust gas mixed with bypass air from a position aft of the center of gravity, to achieve pitch control while airborne in vertical take off or landing mode. The jet screen nozzle also prevents or reduces ingestion of mixed hot exhaust gas and bypass air discharged through the main lift nozzles. The jet screen nozzle further prevents or reduces ingestion of foreign object debris disturbed by the vertical lift discharge flowing from the main lift nozzles.
    Type: Grant
    Filed: December 15, 1995
    Date of Patent: July 14, 1998
    Assignee: The Boeing Company
    Inventor: Mark L. Sloan
  • Patent number: 5749542
    Abstract: A diverterless engine inlet system that integrates a transition shoulder into a system for diverting air from the inlet of an aircraft engine. ????? The bump includes an isentropic compression surface raised outwardly from the body of the aircraft to form a portion of the inner surface of the inlet. The transition surface works with the compression surface to divert low energy boundary layer air from the inlet during aircraft operation.
    Type: Grant
    Filed: May 28, 1996
    Date of Patent: May 12, 1998
    Assignee: Lockheed Martin Corporation
    Inventors: Jeffrey William Hamstra, Brent Neal McCallum, Thomas Gerard Sylvester, Brett Willian Denner, Jeffrey Allen Moorehouse
  • Patent number: 5743488
    Abstract: Boundary layer separation at the boundary surface of an intake duct (18) of a turbofan aeroengine nacelle (12) at conditions of high incidence and high engine mass flow arises from shockwave induced pressure gradients in the boundary layer. To control separation, gaseous fluid is withdrawn from a high pressure region of the boundary layer at a downstream region of the boundary surface, conveyed within the intake duct structure (19) and discharged at an upstream region of the boundary surface into a low pressure region of the boundary layer.
    Type: Grant
    Filed: December 5, 1995
    Date of Patent: April 28, 1998
    Assignee: Short Brothers PLC
    Inventors: Stephen C. Rolston, Edward M. Ashford
  • Patent number: 5737914
    Abstract: Device for fixing an air intake to a jet engine and jet engine incorporating such a device.This device for fixing an air intake (24) to a jet engine (10) installed on a support strut (12) and having a fan (18) and a fan frame or case (20) is characterized in that the device has a hinge (32) fitted between the air intake (24) and the support strut (12) of the jet engine (10), in order to support and pivot the air intake (24) between a closed position, where the intake (24) and the fan frame (20) are arranged substantially coaxially, and an open position, where the intake is angularly spaced from said frame (20).
    Type: Grant
    Filed: February 28, 1996
    Date of Patent: April 14, 1998
    Assignee: Aerospatiale Societe Nationale Industrielle
    Inventors: Alain Porte, Jean-Louis Lasserre
  • Patent number: 5725180
    Abstract: An aircraft turboshaft engine intake includes an axial diffuser and a colinear plenum disposed in flow communication therewith for collecting diffuser air therefrom. A scroll is disposed radially below the plenum in flow communication therewith for accelerating the plenum air for discharge to the aircraft engine. In this arrangement, propeller air is diffused in the diffuser and collected in the plenum wherein it is turned radially inwardly and accelerated through the scroll into the engine. Diffusion is uncoupled from air turning for improving the efficiency thereof.
    Type: Grant
    Filed: December 29, 1995
    Date of Patent: March 10, 1998
    Assignee: General Electric Company
    Inventors: Anthony J. Chamay, Isaac Zelazny
  • Patent number: 5697394
    Abstract: A turbine engine inlet system includes a duct 14 to deliver air to the engine, inlet lips 16 and 52 to smooth the entry of air flowing into the duct, a screen 50 between the lips 52 and 16 for passage of inlet air, a forward inlet section 18 submerged within the aircraft skin contour to provide a degree of ram recovery to the duct, and a movable air deflector 20 which is positionable in a retracted position during normal flight, is extendable outward to a second position substantially flush with the screen 50 for maximum protection against foreign object damage (FOD), and is further extendable outward to a third position beyond the screen to provide an air bypass path when the screen is iced-over.
    Type: Grant
    Filed: March 2, 1993
    Date of Patent: December 16, 1997
    Assignee: United Technologies Corporation
    Inventors: David R. Smith, Armand F. Amelio
  • Patent number: 5662292
    Abstract: A specially contoured barrier type filter disposed in front of a helicopter turbine inlet provides for maximized airflow during forward, as well as sideways flight. The contouring additionally reduces the tendency of the filter to clog. A bypass mechanism is provided should the pressure differential across the filter exceed a predetermined value. The bypass configuration achieves a limited particle separation function in order to provide residual protection. An air box attached to the inlet is formed to provide low distortion levels in the airflow entering the engine inlet.
    Type: Grant
    Filed: May 3, 1995
    Date of Patent: September 2, 1997
    Inventors: Andrew T. Greene, Andrew D. B. Rowen
  • Patent number: 5660357
    Abstract: A missile engine inlet cover has an elongate air scoop having a rigid forward shell and a rearward attached flexible molded end piece. The missile engine inlet cover is held in place by the launch rail with the flexible molded end piece releasably inserted into or over the missile engine inlet. During missile launch, flow of air into the open end of the air scoop forces the air scoop to rotate rearward and dislodges the flexible molded end piece from the missile engine inlet to allow operation of the missile engine.
    Type: Grant
    Filed: July 24, 1995
    Date of Patent: August 26, 1997
    Assignee: Northrop Grumman Corporation
    Inventors: Stephen P. Grossman, Stephen K. Laird
  • Patent number: 5657946
    Abstract: This invention provides a static vent unit e.g. for use on the side of an aircraft and which in operation is subjected to airflow from any direction within a wide airflow incidence range comprises a generally flat plate having an outer surface for fitment generally to flush to an outer surface of the aircraft, a vent port through the plate for connection during operation to a static vent line in the aircraft, and a bulge on the plate outer surface surrounding at least part of a circumference of the vent port and having in cross section a convex curved upper surface extending radially inwardly from an outer edge on the plate to an inner edger on the plate adjacent the circumference of the vent port and adapted during operation to promote attachment of an airflow from within at least part of the airflow incidence range to its surface and direct the airflow into the vicinity of the vent port to provide a compensating increase in ambient pressure at the vent port.
    Type: Grant
    Filed: September 13, 1995
    Date of Patent: August 19, 1997
    Assignee: Westland Helicopters Limited
    Inventor: Terrence Leydon Perkins
  • Patent number: 5636813
    Abstract: A fighter aircraft achieves low aerodynamic drag and radar signature without sacrificing flight performance through a unique arrangement of the air inlets, the weapons bays, and the main landing gear. Separate main and auxiliary weapons bays permit a narrower fuselage than could be obtained with a single common bay. Also, the auxiliary weapons bays and the landing gear can be aligned outboard of the main weapons bay without needing to increase the length or width of the aircraft. The air intake ducts extend aft from each intake and curve upwardly and inwardly over the main weapons bay. The result of the design configuration is an aircraft of minimum fuselage width for optimal performance and which has a forward aspect reduced to the minimum necessary to accommodate the components that need forward visibilities, which translates to minimum aerodynamic drag and radar signature.
    Type: Grant
    Filed: June 5, 1995
    Date of Patent: June 10, 1997
    Assignee: The Boeing Company
    Inventors: Richard Hardy, Frank D. Neumann, Dennis E. Ruzicka
  • Patent number: 5588620
    Abstract: Arcs of segmented spoilers generate a ring on intake airfoil surface of cantilever-suspended jet engines. Strain and temperature sensors on sides of a cantilever connecting structure feed data to a stress-limiting computer whose output communicates with actuator motors of spoiler segments. This stress-feedback network selects and actuates segmented spoiler surfaces to release radial forces that normally are balanced within the engine intake zone. The stress-limiting computer also takes autopilot data of anticipated attitude change patterns and forecasts anticipated strain patterns of an aircraft. An output communication is integrated with an electric power conditioning that actuates motors to position the segmented spoiler barriers.
    Type: Grant
    Filed: December 1, 1994
    Date of Patent: December 31, 1996
    Inventor: Raymond D. Gilbert
  • Patent number: 5586735
    Abstract: The air intake includes two main flaps (1, 2) facing each other and each pivoting about a pin (4, 5) adjacent to a wall (6, 7) extending the flap in question (1, 2) rearwards, and in which a first boundary layer bleed (8a, 8b) is arranged, the pins (4, 5) being substantially parallel to the plane of the wings or of the fuselage so that the flaps (1, 2) move perpendicularly to this plane, and a ramp (11) pivoting about a pin (12) adjacent to its leading edge (11a) by which it is adjacent to the wings and to the fuselage and substantially parallel to the pins (4, 5) is upstream of the flap (1) which is closest to the wings and with which it delimits another boundary layer bleed (13) of variable cross section.
    Type: Grant
    Filed: September 30, 1994
    Date of Patent: December 24, 1996
    Assignee: Office National d'Etudies et de Recherches Aerospatiales
    Inventors: Francois Falempin, Olivier Fourt, Jean-Louis Pastre
  • Patent number: 5579999
    Abstract: A method of forming a shock-free supersonic elliptic nozzle, in which the nozzle to be designed is divided into three sections, a circular-to-elliptic section which begins at a circular nozzle inlet, an elliptic subsonic section downstream from the circular-to-elliptic section and a supersonic section downstream from the elliptic subsonic section. The maximum and minimum radii for each axial point in the circular-to-elliptic section and the elliptic subsonic section are then separately determined, the maximum and minimum radii being the radii for the widest part of an elliptic cross-section and the narrowest part of the elliptic cross-section, respectively. The maximum and minimum radii for each axial point in the supersonic section are determined based on the Method of Characteristics, Then, each of the three sections are based on the maximum and minimum radii for each axial point in the section. The resulting nozzle is acoustically superior.
    Type: Grant
    Filed: March 22, 1995
    Date of Patent: December 3, 1996
    Assignee: The United States of America as represented by the United States National Aeronautics and Space Administration
    Inventors: John M. Seiner, Roy S. Baty
  • Patent number: 5522566
    Abstract: A fighter aircraft achieves low aerodynamic drag and radar signature without sacrificing flight performance through a unique arrangement of the main weapons bay, the auxiliary weapons bays, and the main landing gear. Separate main and auxiliary weapons bays permit a narrower fuselage than could be obtained with a single common bay. Also, the auxiliary weapons bays and the landing gear can be aligned outboard of the main weapons bay without needing to increase the length or width of the aircraft. The air intake ducts extend aft from the intake and curve upwardly and inwardly over the main weapons bay. The result of the design configuration is an aircraft which has a forward aspect reduced to the minimum necessary to accommodate the components that need forward visibilities, which translates to minimum aerodynamic drag and radar signature.
    Type: Grant
    Filed: August 10, 1994
    Date of Patent: June 4, 1996
    Assignee: The Boeing Company
    Inventors: Richard Hardy, Frank D. Neumann, Dennis E. Ruzicka
  • Patent number: 5511044
    Abstract: A device for producing thrust has a variety of uses, such as pumping liquid, compressing or blowing air, or powering an aircraft. The device has a chamber with a sound driver located therein. The sound driver creates a compression standing wave in the chamber which will have at least one low pressure node and at least two high pressure peaks. An intake port extends through the chamber and is located adjacent the low pressure node for drawing in a fluid into the chamber. A discharge port extends through the chamber and is located adjacent the high pressure peak for discharging fluid from the chamber.
    Type: Grant
    Filed: October 19, 1991
    Date of Patent: April 23, 1996
    Assignee: Lockheed Corporation
    Inventor: Boyd B. Bushman
  • Patent number: 5490644
    Abstract: Boundary layer control apparatus is provided (22). The boundary layer control apparatus (22) is for use with an aircraft propulsion nacelle (12) positioned such that the air inlet (14) of the propulsion nacelle is located proximate an aircraft surface (10), wherein a boundary layer is established on the surface when the aircraft is propelled through an atmosphere, causing air to flow over the surface. The boundary layer control apparatus (22) includes a duct having an entrance (24) positioned between the aircraft surface (10) and the inlet (14) of the propulsion nacelle (12) for capturing the boundary layer air passing over the aircraft surface and diverting the boundary layer air away from the inlet.
    Type: Grant
    Filed: December 20, 1993
    Date of Patent: February 13, 1996
    Assignee: The Boeing Company
    Inventors: Joseph L. Koncsek, Steven L. McMahon
  • Patent number: 5485975
    Abstract: The lower lip of an aircraft inlet cowl has a first transverse slot formed through an upper surface of the lower lip while a second transverse slot is formed through a lower surface of the lip. A rotating vane is transversely located in the interior of the lip, between the upper and lower slots. A duct located within the interior of the lower lip delivers pressurized engine bleed air to the rotating vane. Selectively driven gears position the vane so as to block either one or the other of the slots, depending upon aircraft speed, so that normal cowl inlet air is energized in the vicinity of the slot outlet. This prevents separation of the normal inlet airflow from the cowl surface - and reduces drag that would otherwise develop.
    Type: Grant
    Filed: July 19, 1994
    Date of Patent: January 23, 1996
    Assignee: Northrop Grumman Corporation
    Inventor: Runyon H. Tindell
  • Patent number: 5483791
    Abstract: A turboprop engine has in flow series arrangement a crescent shaped inlet, an annular plenum, a compressor, a combustor, and a turbine. The plenum is defined by inner and outer annular walls. A support member referred to as a "boat tail" extends between the walls and is circumferentially positioned 180 degrees from the inlet. A strake extends downstream from the support member and is angled in a direction opposite the rotational direction of the compressor. Thus air entering the engine with either positive or negative swirl is forced to enter the impeller with negative swirl.
    Type: Grant
    Filed: June 14, 1994
    Date of Patent: January 16, 1996
    Assignee: AlliedSignal Inc.
    Inventors: Rangnath A. Kotwal, Jacob S. Obayomi, Henry J. Ruzicka, William F. Waterman
  • Patent number: 5480110
    Abstract: A transport plane with stub tail, which is preferably propelled by two jet engines. The intake air is fed to the engines directly integrated in the fuselage tail via a diffusor, the diffusor is a short diffusor. The air obtained by boundary layer suction via a suction slot with a combination of ejectors and diffusors is fed into the rest of the intake air.
    Type: Grant
    Filed: March 25, 1994
    Date of Patent: January 2, 1996
    Assignee: Daimler-Benz Aerospace AG
    Inventor: Gerhard Lobert
  • Patent number: 5447282
    Abstract: For bringing about the attachment of a turbojet engine (10) to an aircraft tructure such as a wing (12), use is made of a non-rotary, front, central body of the engine, which is connected by a ball joint (16) to a thrust transmission member such as an air intake (14), which is itself connected to the wing (12) by a thrust transmitting system (18). In this way, the thrust (X) of the turbojet engine is transmitted to the air intake (14) along the engine longitudinal axis before being transmitted to the aircraft structure by the system (18). Therefore the casings and lines of shafts of the turbojet engine are not exposed to any bending moment, which makes it possible to optimize the performance characteristics of said engine. Moreover, it is still possible to deform the wing (12) without any risk of surging or hunting of the turbojet engine.
    Type: Grant
    Filed: August 5, 1993
    Date of Patent: September 5, 1995
    Assignee: Societe Nationale Industrielle et Aerospatiale des Poudres et Explosifs
    Inventor: Yves Durand
  • Patent number: 5447283
    Abstract: A blown boundary layer control system for an aircraft having a jet engine with an engine compressor, an inlet including a compression surface with an external part and internal part, a cowl lip including an internal lip surface and an external lip surface and an external afterbody. The system includes several ducts from the engine compressor. A series of nozzles and valves control and direct air flow to various surfaces. A computer is electrically connected to the valves to control the operation of the valves thereby controlling the blowing of air from a commanded number of nozzles. The computer controls the valves in position as functions of RPM of the engine, free stream flight conditions and aircraft attitude.
    Type: Grant
    Filed: February 2, 1994
    Date of Patent: September 5, 1995
    Assignee: Grumman Aerospace Corporation
    Inventor: Runyon H. Tindell
  • Patent number: 5433070
    Abstract: A flexible engine inlet duct mounting system for integrating an engine inlet duct in combination with an engine system to minimize or eliminate turbulence-inducing structural discontinuities therebetween wherein non-turbulent intake airflow is provided to the engine system. The mounting system includes a mechanical support assembly that constrains the relative motion between the aft ends of the inlet duct and the engine system, and a dual seal assembly that accommodates such relative motion while concomitantly maintaining seals between the inlet duct and the engine system. The duct support assembly includes an annular duct support member and an annular spherical adaptor member having interacting ends that have complementary arcuate configurations which constrain the relative motion of the aft ends of the inlet duct to in-plane displacements about a duct pivot point coincident with the engine system centerline.
    Type: Grant
    Filed: September 8, 1993
    Date of Patent: July 18, 1995
    Assignee: United Technologies Corporation
    Inventor: Armand F. Amelio
  • Patent number: 5410870
    Abstract: Aircraft engine, whose ancillary equipment forms a unitary assembly wherein the equipment is located to the rear of the air intake duct in a substantially closed central compartment just upstream of the gas generator. The equipment positioned along the engine axis, which, inter alia, leads to low engine drag in operation.
    Type: Grant
    Filed: November 29, 1993
    Date of Patent: May 2, 1995
    Assignee: Societe Nationale d'Etude et de Construction de Moteurs d'Aviation "SNECMA"
    Inventors: Michel G. R. Brault, Georges Mazeaud, Jean-Marie N. Pincemin, Pascal C. Wurniesky
  • Patent number: 5411224
    Abstract: A guard apparatus for the intake of a jet engine includes a generally conically shaped structure that has a plurality of concentric rings of gradually decreasing diameter beginning at a largest ring that affixes to the cowl of the jet engine and progressively smaller diameter concentric rings spaced toward the front end portion of the guard apparatus. The guard apparatus also includes a plurality of longitudinally extended rods each of which forms a structural connection with one or more of the plurality of concentric rings, the rods defining an acute angle with the central longitudinal axis of the guard. Overall, the front end portion of the guard is generally hemispherically shaped defining a generally convex front end portion of the guard apparatus. Each of the longitudinally extending rods is acircular in shape, providing a transverse section that includes a semicircular shaped rear portion and a pointed front portion.
    Type: Grant
    Filed: March 21, 1994
    Date of Patent: May 2, 1995
    Inventors: Raymond M. Dearman, John J. Bethea
  • Patent number: 5397077
    Abstract: An inlet bleed system for a supersonic aircraft engine having a longitudinally downstream extending inlet bounded by a boundary wall that in part defines a supersonic flowpath through the inlet, a transversely extending boundary layer scoop extends into a boundary layer region of the flowpath and has an upstream facing bleed aperture, and a shock generating means for generating a shockwave in a supersonic flow in the flowpath such that the shockwave passes through the bleed aperture. One embodiment provides a scoop which extends a height above the wall such that it is operable to scoop off no more than a sufficient amount of a boundary layer flow that would exist in the boundary region and be momentum deficient relative to predetermined conditions that would exist downstream of the scoop under supersonic operating conditions. Another embodiment provides for the scoop to be disposed a throat section of the inlet wherein the aperture located is just upstream of the normal shock location.
    Type: Grant
    Filed: March 3, 1994
    Date of Patent: March 14, 1995
    Assignee: General Electric Company
    Inventor: Paul H. Kutschenreuter, Jr.
  • Patent number: 5357742
    Abstract: The hot core engine compartment of a turbojet engine is cooled by the metered flow of cooling air exhausted through a laminar flow nacelle system. This arrangement reduces the need for extracting bypass ram air from the engine performance cycle for cooling purposes and thereby improves specific fuel consumption and engine efficiency. A turbocompressor pump driven by bleed air from the core engine compressor draws cooling air through the laminar flow nacelle system and pumps the air into a manifold surrounding the core engine.
    Type: Grant
    Filed: January 12, 1994
    Date of Patent: October 25, 1994
    Assignee: General Electric Company
    Inventor: Franklin E. Miller
  • Patent number: RE35387
    Abstract: A superagile tactical fighter aircraft and a method of flying it are disclosed. The superagile aircraft is characterized by articulatable air inlets, articulatable exhaust nozzles, highly deflectable canard surfaces, and control thruster jets located around the nose of the fuselage, on the top and bottom surfaces of the propulsion system near the exhaust nozzles, and on both sides of at least one vertical tail. The method of operating the superagile aircraft comprises the step of articulating the air inlets and exhaust nozzles, deflecting the canard surfaces, and vectoring the thruster jets so that supernormal flight is attained. Supernormal flight may be defined as flight at which the superagile aircraft operates at an angle of attack much greater than the angle of attack which produces maximum lift. In supernormal flight, the superagile aircraft is capable of almost vertical ascents, sharp turns, and very steep descents without losing control.
    Type: Grant
    Filed: January 30, 1992
    Date of Patent: December 3, 1996
    Assignee: Dynamic Engineering, Inc.
    Inventor: Thomas H. Strom