Bizarre Patents
A method to tenderize meat with an explosive shockwave.
PatentStorm News
Make the Most of Our Site
See this month's Top Inventors and Most Cited Patents.
Stay on top of the latest innovations by subscribing to an RSS feed.
Registered users: Manage your profile.
| Number | Title | Issue Date |
| 8166748 | Gas turbine engine booster having rotatable radially inwardly extending blades and non-rotatable vanes A gas turbine engine booster includes one or more rotatable booster stages having booster blades extending radially inwardly from a rotatable drum and one or more non-rotatable vane stages having booster vanes extending radially outwardly from a non-rotatable shell.... | 05/01/2012 |
| 8156745 | Exhaust nozzle seal with segmented basesheet An aircraft gas turbine engine exhaust nozzle basesheet includes longitudinally extending plurality of basesheet segments. Each of the basesheet segments includes a panel body between segment leading and trailing edges and slidable sealing joints with slidingly un-r... | 04/17/2012 |
| 8147178 | Centrifugal compressor forward thrust and turbine cooling apparatus A gas turbine engine centrifugal compressor axial forward thrust apparatus bleeds impeller tip aft bleed flow from between an annular centrifugal compressor impeller of a high pressure rotor and a diffuser directly downstream of the impeller. The apparatus then uses... | 04/03/2012 |
| 8126628 | Aircraft gas turbine engine blade tip clearance control A method and system adjusts blade tip clearance between rotating aircraft gas turbine engine blade tips and a surrounding shroud in anticipation of and before an engine command that changes an engine rotational speed. The method may include determining when to begin... | 02/28/2012 |
| 8123471 | Variable stator vane contoured button A variable stator vane airfoil is mounted on a button centered about a rotational axis and includes circular leading and trailing edges circumscribed about the rotational axis at a button radius. Contoured pressure and suction sides extend from the circular leading ... | 02/28/2012 |
| 8122722 | Exhaust nozzle seal with segmented basesheet disposed between side rails An aircraft engine exhaust nozzle basesheet includes longitudinally extending plurality of basesheet segments having panel bodies between segment leading and trailing edges and slidable sealing joints with slidingly un-restrained center surfaces between adjacent seg... | 02/28/2012 |
| 8087880 | Active clearance control for a centrifugal compressor Apparatus and method of operating a centrifugal compressor and active control system includes a centrifugal compressor with compressor blades mounted on an impeller, an annular cavity bounded in part by a shroud adjacent to the blades, and an active control system f... | 01/03/2012 |
| 8087249 | Turbine cooling air from a centrifugal compressor A gas turbine engine turbine cooling system includes an impeller and a diffuser directly downstream of the impeller, a bleed for bleeding clean cooling air from downstream of the diffuser, and one or more channels in fluid communication with the bleed. Each of the c... | 01/03/2012 |
| 8063528 | Counter-rotatable generator A counter-rotatable generator includes a generator stator concentric with concentric counter-rotatable radially inner pole and outer magnet rotors. The magnet rotor encircles the pole rotor and the pole rotor encircles the generator stator. A rotor air gap is dispos... | 11/22/2011 |
| 8051709 | Method and apparatus for pre-spinning rotor forgings A method and system for relieving forging induced residual stresses in a rotor forging balances a pre-spin machine with the forging mounted thereon at a first rotational speed and then pre-spins the forging with it mounted on the machine at a substantially greater s... | 11/08/2011 |
| 8020367 | Nozzle with yaw vectoring vane An exhaust vane disposed in a divergent section of an aircraft gas turbine engine exhaust nozzle is sideways pivotable about a vane pivot axis. The nozzle vane pivot axis may be centrally located at an unvectored nozzle throat. Transversely spaced apart upper and lo... | 09/20/2011 |
| 8011877 | Fiber composite reinforced aircraft gas turbine engine drums with radially inwardly extending blades A gas turbine engine assembly having one or more blade rows with blades extending radially inwardly from a rotatable drum, one or more composite fiber material rings disposed circumferentially around the rotatable drum, and the composite fiber material rings includi... | 09/06/2011 |
| 8011188 | Augmentor with trapped vortex cavity pilot A gas turbine engine augmentor includes an annular trapped vortex cavity pilot having a cavity forward wall, a cavity radially outer wall, and a cavity aft wall, an annular cavity therebetween, and cavity fuel injector tubes operably disposed through the outer wall ... | 09/06/2011 |
| 7942641 | Varying fluence as a function of thickness during laser shock peening A method for simultaneously laser shock peening opposite laser shock peening surfaces on opposite sides of an article, such as a gas turbine engine airfoil, with varying thickness using oppositely aimed laser beams and varying surface fluence of the laser beams over... | 05/17/2011 |
| 7891938 | Multi sensor clearance probe A multi sensor clearance probe with at least longitudinally and transversely spaced apart first and second sensors operable to measure first and second distances respectively between the sensors and a longitudinally spaced apart rotating rotor. The sensors being ope... | 02/22/2011 |
| 7870719 | Plasma enhanced rapidly expanded gas turbine engine transition duct A plasma enhanced rapidly expanded duct system includes a gas turbine engine inter-turbine transition duct having radially spaced apart conical inner and outer duct walls extending axially between a duct inlet and a duct outlet. A conical plasma generator produces a... | 01/18/2011 |
| 7854111 | Axial flow positive displacement turbine An axial flow positive displacement turbine includes inner and outer bodies having offset inner and outer axes respectively extending between a relatively high pressure inlet and a relatively low pressure outlet. At least one of the bodies is rotatable about its axi... | 12/21/2010 |
| 7819626 | Plasma blade tip clearance control A gas turbine engine plasma blade tip clearance control system includes an annular shroud surrounding rotatable blade tips and an annular plasma generator spaced radially outwardly and apart from the blade tips. An exemplary embodiment of the annular plasma generato... | 10/26/2010 |
| 7779866 | Segmented trapped vortex cavity An annular trapped vortex cavity assembly segment comprising includes a cavity forward wall, a cavity aft wall, and a cavity radially outer wall therebetween defining a cavity segment therein. A cavity opening extends between the forward and aft walls at a radially ... | 08/24/2010 |
| 7779811 | Thermoelectrically cooled components for distributed electronics control system for gas turbine engines A gas turbine engine control component includes at least one electronic device, electronics such as an integrated circuit associated with the device, and a thermoelectric cooler for cooling the electronics mounted in a compartment. The thermoelectric cooler may be d... | 08/24/2010 |
| 7775048 | Seal assembly A sprung seal assembly includes a flexible sprung seal having a center section disposed between opposing curved and cantilevered first and second end sections. First and second free edges of the first and second end sections respectively are trapped within a retaine... | 08/17/2010 |
| 7766599 | Plasma lifted boundary layer gas turbine engine vane A plasma boundary layer lifting system includes at least one gas turbine engine vane having a spanwise extending airfoil with an outer surface extending in a chordwise direction between opposite leading and trailing edges and chordwise spaced apart plasma generators... | 08/03/2010 |
| 7758303 | FLADE fan with different inner and outer airfoil stagger angles at a shroud therebetween A FLADE fan assembly includes radially inner and outer airfoils extending radially inwardly and outwardly respectively from an annular shroud circumferentially disposed about a centerline. Inner and outer chords extend between inner and outer leading and trailing ed... | 07/20/2010 |
| 7753230 | Nut feeder A nut feeder having a piston with a rod attached thereto disposed within a chamber of a cylinder. A rod air passage extending through the rod between a rear port at a groove circumscribed around a back end of the rod and a front end of the rod. A ring disposed withi... | 07/13/2010 |
| 7739873 | Gas turbine engine combustor hot streak control A gas turbine engine combustion system includes a plurality of fuel injectors circumferentially disposed around a combustor in a one to one fuel supply relationship with a plurality of fuel nozzle valves, and an electronic controller for controlling the fuel nozzle ... | 06/22/2010 |
| 7736450 | Varying fluence as a function of thickness during laser shock peening A method for laser shock peening an article, such as a gas turbine engine airfoil, with varying thickness by varying a surface fluence of a laser beam over a laser shock peening surface as a function of the thickness beneath a laser shock peened spot formed by the b... | 06/15/2010 |
| 7736123 | Plasma induced virtual turbine airfoil trailing edge extension A trailing edge vortex reducing system includes a gas turbine engine airfoil extending in a spanwise direction, one or more spanwise extending plasma generators in a trailing edge region around a trailing edge of the airfoil. The plasma generators may be mounted on ... | 06/15/2010 |
| 7735350 | Measuring intensity of shot peening in areas with difficult accessibility Determining shot peening intensity by affixing a Almen test strip to a shot peening surface, removing the peened strip from the shot peening surface, measuring an arc height of the shot peened strip, and determining peening intensity on the surface from the measured... | 06/15/2010 |
| 7730714 | Turbofan gas turbine engine with variable fan outlet guide vanes A turbofan gas turbine engine includes a forward fan section with a row of fan rotor blades, a core engine, and a fan bypass duct downstream of the forward fan section and radially outwardly of the core engine. The forward fan section has only a single stage of vari... | 06/08/2010 |
| 7726115 | Axial flow positive displacement worm compressor An axial flow positive displacement compressor has an inlet axially spaced apart and upstream from an outlet. Inner and outer bodies have offset inner and outer axes extend from the inlet to the outlet through first and second sections of a compressor assembly in se... | 06/01/2010 |
| 7707815 | Axial flow positive displacement worm gas generator An axial flow positive displacement engine has an inlet axially spaced apart and upstream from an outlet. Inner and outer bodies have offset inner and outer axes extend from the inlet to the outlet through first, second, and third sections of a core assembly in seri... | 05/04/2010 |
| 7695241 | Downstream plasma shielded film cooling An downstream plasma boundary layer shielding system includes film cooling apertures disposed through a wall having cold and hot surfaces and angled in a downstream direction from a cold surface of the wall to an outer hot surface of the wall. A plasma generator loc... | 04/13/2010 |
| 7628585 | Airfoil leading edge end wall vortex reducing plasma A leading edge vortex reducing system includes a gas turbine engine airfoil extending in a spanwise direction away from an end wall, one or more plasma generators extending in the spanwise direction through a fillet between the airfoil and the end wall in a leading ... | 12/08/2009 |
| 7624565 | Hybrid worm gas turbine engine A gas turbine engine has components including a compressor, a combustor, and a turbine. At least one component is radially bladed having at least one row of radially extending rotatable blades and at least another is a worm component having an inner body disposed wi... | 12/01/2009 |
| 7597537 | Thermal control of gas turbine engine rings for active clearance control A gas turbine engine thermal control apparatus includes at least one annular spray tube having spray holes oriented to impinge thermal control air onto a fillet between an outer casing and a forward thermal control ring and, in a more particular embodiment, into a c... | 10/06/2009 |
| 7596950 | Augmentor radial fuel spray bar with counterswirling heat shield A gas turbine engine augmentor radial fuel spray bar has a counterswirling spray bar heat shield. Two embodiments of the heat shield include one with a cambered airfoil cross-section and another with a twisted airfoil cross-section and may have varying or constant d... | 10/06/2009 |
| 7588413 | Upstream plasma shielded film cooling An upstream plasma boundary layer shielding system includes film cooling apertures disposed through a wall having cold and hot surfaces and angled in a downstream direction from a cold surface of the wall to an outer hot surface of the wall. A plasma generator locat... | 09/15/2009 |
| 7000581 | Mono-shaft four-stroke engine A 4-stroke engine incorporating a mono-shaft multi-valve operating system, the multi-valve operating system incorporating a first cam follower assembly that is associated with an intake valve, a second cam follower assembly that is associated with an exhaust valve, ... | 02/21/2006 |
| 6901892 | Two stroke engine with rotatably modulated gas passage A two stroke internal combustion engine includes at least one gaseous communication passage between a crankcase chamber and a combustion chamber of the engine. A first rotary shut-off valve on a periphery of a rotatable circular disk is operatively disposed between ... | 06/07/2005 |
| 7530965 | Protective device for a needle Protective device for a needle, more particularly for a catheter introducing needle or so-called cannula needle, whereby this protective device comprises protective means which slidably cooperate with the needle, characterized in that said protective means comprise ... | 05/12/2009 |
