Did You Know...
...that power steering was invented by independent inventor Francis W. Davis? As chief engineer in the 1920s of the truck division of the Pierce Arrow Motor Car Company, he saw how hard it was to steer heavy vehicles. So that he would be able to keep the profits from his future invention, Davis left his job, rented a small engineering shop in Waltham, Mass., and developed a hydraulic power steering system that led to power steering.
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| Number | Title | Issue Date |
| 8172175 | Pivoting door thrust reverser for a turbofan gas turbine engine A pivot arrangement for a thrust reverser door of a gas turbine engine, the pivot fitting having a base and a shaft projecting from a main side of the base. The shaft receives a preferably curved pivot arm of the door to provide a low profile arrangement which impro... | 05/08/2012 |
| 8162542 | Environment controlled cargo container A cargo container includes a cargo box affixed atop a hollow base, with the base including forklift tunnels extending therethrough with elongate bays disposed parallel thereto. Each bay includes a removable tray for receiving electrical batteries. And, a temperature... | 04/24/2012 |
| 8127530 | Thrust reverser for a turbofan gas turbine engine The thrust reverser comprises sections, such as arms and skins, which may be connected along joints to provide a thrust reverser body. A plurality of fittings may be integrally formed on a surface of each arm. ... | 03/06/2012 |
| 8091827 | Thrust reverser door A thrust reverser door provides in one aspect a separation of structural and aerodynamic functions through the provision of individual structures. In some embodiments, an aerodynamic element is adjustable in position, while in other embodiments, the relative positio... | 01/10/2012 |
| 8057624 | Dual panel fabrication A pair of laminated panels are simultaneously manufactured in a single panel press. A thermal band is stacked between two panel sets and then the two panel sets are simultaneously heated and compressed together in a common stack with the band, with the band being se... | 11/15/2011 |
| 8052086 | Thrust reverser door A thrust reverser door is provided, in one configuration, with a plurality of peripherally-disposed frames circumferentially spaced apart from one another and projecting radially inwardly on an interior side of the door to thereby provide a channel for redirecting t... | 11/08/2011 |
| 8052085 | Thrust reverser for a turbofan gas turbine engine The thrust reverser includes, in one aspect, an interior flow deflector which defines a portion of a substantially continuous and uninterrupted nozzle interior surface with the interior of a jet pipe when the door is in a stowed position, thereby reducing aerodynami... | 11/08/2011 |
| 8051639 | Thrust reverser The thrust reverser is used with an aircraft gas turbine engine and includes upper and lower doors pivotable between a stowed position and a deployed position. When deployed, the doors redirect a portion of the efflux to generate a nose-down pitching moment on an ai... | 11/08/2011 |
| 8015797 | Thrust reverser nozzle for a turbofan gas turbine engine The thrust reverser comprises a first reverser door and a second reverser door asymmetrically pivotable between a stowed position and a deployed position, one having a pivot axis closer to the central axis than the other. ... | 09/13/2011 |
| 7988094 | Aircraft window erosion shield An erosion shield for an aircraft window includes an annular band having a radially outer brim and a radially inner clip. The shield is sized to cover a composite window frame having an outer rim and an inner sash around a central aperture in which is mounted a wind... | 08/02/2011 |
| 7963099 | Fluted chevron exhaust nozzle A gas turbine engine exhaust nozzle includes a fluted shell terminating in a row of chevrons. The nozzle is radially serpentine circumferentially around the shell and has a circumferentially serpentine trailing edge. ... | 06/21/2011 |
| 7926289 | Dual interstage cooled engine A gas turbine engine includes a compressor, combustor, and high pressure turbine operatively joined together. A first interstage bleed circuit is joined in flow communication between a first preultimate stage of the compressor and hollow blades in the turbine to pro... | 04/19/2011 |
| 7926285 | Modular chevron exhaust nozzle An exhaust nozzle for a gas turbine engine includes a modular chevron. The chevron includes dual skins fixedly joined together at a base flange, and at a rim extending along the trailing edge of the chevron between the base and apex thereof. ... | 04/19/2011 |
| 7870743 | Compound nozzle cooled engine A gas turbine engine includes a compressor, combustor, and high pressure turbine operatively joined together. The turbine includes a nozzle followed by a row of rotor blades. A first bleed circuit is joined in flow communication between the last stage of the compres... | 01/18/2011 |
| 7870742 | Interstage cooled turbine engine A gas turbine engine includes a compressor, combustor, and high pressure (HP) turbine operatively joined together. An interstage cooling circuit is joined in flow communication from an intermediate stage of the compressor to a forward face of an HP disk supporting a... | 01/18/2011 |
| 7836703 | Reciprocal cooled turbine nozzle A turbine nozzle includes first and second vanes joined to outer and inner bands. The vanes include outboard sides defining outboard flow passages containing axial splitlines, and opposite inboard sides defining an inboard flow passage without axial splitline. The t... | 11/23/2010 |
| 7824158 | Bimaterial turbine blade damper A turbine blade damper includes an outer part for damping vibration of the blade airfoil and a supporting inner part. The two parts are formed of different materials for the different performance required thereof in the blade. ... | 11/02/2010 |
| 7823389 | Compound clearance control engine A gas turbine engine includes a compressor, combustor, and turbine having a row of blades mounted inside a surrounding turbine shroud. A heat exchanger is used for cooling pressurized air bled from the compressor. A distribution network joins the heat exchanger to t... | 11/02/2010 |
| 7743613 | Compound turbine cooled engine A gas turbine engine includes a compressor, combustor, and high pressure turbine operatively joined together. The turbine includes a row of nozzle vanes followed by a row of rotor blades. The vanes and blades have corresponding forward and aft internal cooling chann... | 06/29/2010 |
| 7740443 | Transpiration clearance control turbine A row of turbine blades is surrounded by a turbine shroud. The shroud is supported by a turbine case having a pair of radially outwardly extending rails. The rails are perforate for channeling therethrough control air to control thermal radial movement of the case, ... | 06/22/2010 |
| 7736124 | Damper configured turbine blade A turbine rotor blade includes a hollow airfoil joined to a platform and dovetail. A main flow channel extends longitudinally in span through the blade and is bound chordally by opposite partitions transversely bridging opposite sidewalls of the airfoil. A damper ri... | 06/15/2010 |
| 7695243 | Dust hole dome blade A hollow turbine airfoil includes a tip cap bounding an internal cooling circuit between opposite pressure and suction sidewalls. The tip cap includes an internal dome surrounding a dust hole, and the dome is inclined inwardly toward the airfoil root both transverse... | 04/13/2010 |
| 7686578 | Conformal tip baffle airfoil A turbine blade includes an airfoil tip with first and second tip ribs extending from a tip floor. The ribs extend along the opposite pressure and suction sides of the blade and are joined together at opposite leading and trailing edges. A tip baffle is nested trans... | 03/30/2010 |
| 7674093 | Cluster bridged casting core A casting core for a turbine blade includes a plurality of rods extending above a shank. The rods define internal cooling channels in the airfoil of the blade, and the shank defines an inlet channel in the dovetail of the blade. A plurality of stubs are clustered to... | 03/09/2010 |
| 7624581 | Compact booster bleed turbofan A Turbofan engine includes a fan mounted to a fan frame inside a fan nacelle. A booster compressor is joined to the fan inboard a flow splitter. A booster bleed system is disposed inside the splitter, and includes an inlet at the compressor outlet, and an outlet joi... | 12/01/2009 |
| 7614210 | Double bypass turbofan A variable cycle turbofan engine includes first and second fans independently joined to respective turbines. A first bypass duct surrounds a core engine disposed in flow communication with the second fan. A second bypass duct surrounds the first bypass duct in flow ... | 11/10/2009 |
| 7607893 | Counter tip baffle airfoil A turbine blade includes an airfoil having first and second tip ribs extending along the opposite pressure and suction sides thereof. The tip ribs are spaced apart between the leading and trailing edges of the airfoil to include a tip baffle. The baffle extends chor... | 10/27/2009 |
| 7607308 | Shrouded turbofan bleed duct A bleed duct is configured for bleeding fan air from the fan bypass duct in a turbofan aircraft engine. The bleed duct includes a tubular conduit having an inlet and outlet at opposite ends. The conduit is configured in flow area for recovering pressure from speedin... | 10/27/2009 |
| 7594388 | Counterrotating turbofan engine A turbofan engine includes a fan, compressor, combustor, high pressure turbine, and low pressure turbine joined in serial flow communication. The high pressure turbine includes two stages of rotor blades to effect corresponding exit swirl in the combustion gases dis... | 09/29/2009 |
| 7588811 | Columnar adhesive label roll A label roll includes a web having front and back surfaces wound in a roll. The back surface includes adhesive patches aligned in a column along the running axis of the web. The front surface includes a release strip behind the column of patches and laminated theret... | 09/15/2009 |
| 7581398 | Purged flameholder fuel shield A fuel shield is configured for use in the afterburner of a turbofan aircraft engine. The shield includes wings obliquely joined together at a nose to conform with the leading edge region of a flameholder vane. A hood is joined to the wings and extends obliquely the... | 09/01/2009 |
| 7578653 | Ovate band turbine stage A turbine stage includes a stator nozzle having a row of vanes mounted between inner and outer bands. The inner band terminates in an ovate ledge converging aft from the vanes with radially outer and inner convex surfaces joined at a convex apex. The ovate ledge red... | 08/25/2009 |
| 7565804 | Flameholder fuel shield A fuel shield is configured for use in the afterburner of a turbofan aircraft engine. The shield includes wings obliquely joined together at a nose, with each of the wings including an offset mounting tab at a proximal end thereof. The wings and tabs are configured ... | 07/28/2009 |
| 7519544 | Material browser The material browser utilizes software interacting with the user using customer application criteria to determine the most appropriate raw material required for an application. The customer application criteria used to determine the best raw material type includes: ... | 04/14/2009 |
| 7513102 | Integrated counterrotating turbofan A turbofan engine includes a fan, compressor, combustor, single-stage high pressure turbine, and low pressure turbine joined in serial flow communication. First stage rotor blades in the low pressure turbine are oriented oppositely to the rotor blades in the high pr... | 04/07/2009 |
| 7510376 | Skewed tip hole turbine blade A turbine blade includes a hollow airfoil having a plurality of bowed tip holes extending through a tip floor thereof and skewed toward a squealer rib extending outwardly from the floor. ... | 03/31/2009 |
| 7510371 | Forward tilted turbine nozzle A turbine nozzle includes a row of vanes joined to radially outwardly inclined outer and inner bands. Each vane has camber and an acute twist angle for importing swirl in combustion gases discharged at trailing edges thereof. The trailing edges are tilted forwardly ... | 03/31/2009 |
| 7509797 | Thrust vectoring missile turbojet A turbojet engine includes a core engine, an afterburner, and a converging-diverging exhaust nozzle in serial flow communication. A thrust vectoring system is joined between a compressor and the nozzle. A controller is operatively joined to the thrust vectoring syst... | 03/31/2009 |
| 7475545 | Fladed supersonic missile turbojet A turbojet engine includes a core engine, afterburner, and converging-diverging exhaust nozzle disposed in serial flow communication. A bypass duct surrounds the core engine and afterburner and terminates in flow communication with the exhaust nozzle. The compressor... | 01/13/2009 |
| 7448199 | Self powdered missile turbojet A turbojet engine includes a core engine, an afterburner, and a converging-diverging exhaust nozzle in serial flow communication. An integral starter-generator is disposed inside the core engine and is joined to the rotor for equal speed rotation therewith. An elect... | 11/11/2008 |
