| WILLIAMS INTERNATIONAL CO., L.L.C. Patent applications |
| Patent application number | Title | Published |
|---|
| 20120011845 | Internal Combustion Engine Cylinder Head With Integral Exhaust Runners And Turbocharger Housing - An internal combustion engine cylinder head is based upon a one-piece structure including a number of exhaust runners, an exhaust collector, and a turbocharger exhaust turbine housing, all formed as one-piece. | 01-19-2012 |
| 20110208400 | SYSTEM AND METHOD FOR CONTOLLING A SINGLE-SPOOL TURBOSHAFT ENGINE - A controller receives a power-level command representative of a level of power to be transmitted by a single-spool turboshaft engine to a controllable load. A torque command determined responsive to a measure of inlet pressure, from a control schedule responsive to the power-level command, is representative of a level of torque to be transmitted by an element to drive the controllable load. Under some operating conditions, a rotational speed command provides for at least nearly minimizing a measure of associated fuel consumption when the transmitted torque is regulated to the level corresponding to the torque command by controlling one of the controllable load and a fuel flow to the engine, and the other of the controllable load and the fuel flow to the engine is controlled so as to regulate an associated rotational speed to a level corresponding to the rotational speed command. | 08-25-2011 |
| 20110007991 | SYSTEM AND METHOD FOR ISOLATING A ROLLING-ELEMENT BEARING - Lubrication fluid is discharged through an axial gap between a outer bearing race and a bearing housing from an enclosed volume bounded in part by a forward surface of the outer bearing race that is axially slideable within the bearing housing so as to provide for changing the axial gap. The pressure in the enclosed volume is automatically controlled responsive to an axial force on outer bearing race by an axial position of the outer bearing race that determines a size of the axial gap, so as to provide for increasing the pressure responsive to increasing axial force over at least a portion of an operating range. The lubrication fluid in the axial gap provides for isolating axial vibrations of the outer bearing race relative to the bearing housing. | 01-13-2011 |
| 20100212325 | COMBUSTION SYSTEM - Fuel and air are injected in a first poloidal flow in a first poloidal direction within a first annular zone of an annular combustor. A first combustion gas from the at least partial combustion of the fuel and air is discharged into an annular transition zone of the annular combustor and transformed to a second combustion gas therein within an at least partial second poloidal flow followed by an at least partial third poloidal flow in the annular transition zone, wherein the direction of the second poloidal flow is opposite to that of the first and third poloidal flows. The second combustion gas is discharged into a second annular zone of the annular combustor, and then transformed to a third combustion gas therein before being discharged therefrom, responsive to which a back pressure is generated in the annular combustor. | 08-26-2010 |
| 20100212288 | Jet Engine Exhaust Nozzle and Associated System and Method of Use - A first trailing edge portion of a scarfed jet engine exhaust nozzle aft of a second trailing edge portion relative to a central axis of an associated exhaust duct causes an automatic nozzle-pressure-ratio responsive transverse deflection of the associated exhaust flow away from the first trailing edge portion. When offset from both the center of gravity (CG) and the central longitudinal axis of an aircraft, at a relatively low nozzle pressure ratio, e.g. during takeoff, the thrust vector from the exhaust flow acts relatively close to the CG, whereas at a relatively high nozzle pressure ratio, e.g. during relatively high-speed cruise, the scarfed exhaust nozzle deflects the exhaust flow so that the resulting thrust vector is relatively parallel to the path of the aircraft. With the final portion of the exhaust duct skewed, the primary axis of the jet engine can be relatively parallel to the path of the aircraft. | 08-26-2010 |
| 20100180592 | Turbocharger - A bearing housing of a rotor shaft support assembly of a turbocharger core mounts to and closes a forward end of a cavity that both receives and discharges exhaust gases of an internal combustion engine. A turbine rotor operatively coupled to a rotor shaft and a compressor rotor of an associated turbocharger rotor assembly rotates within a turbine rotor shroud portion of an associated turbine nozzle cartridge assembly, wherein the rotor shaft is rotationally supported by at least one bearing within the bearing housing. The turbine nozzle cartridge assembly provides for directing exhaust gases from the cavity through a peripheral inlet leading to a plurality of vanes between forward and aft walls, through the turbine rotor shroud portion, and then through a nozzle exhaust portion incorporating an external sealing surface on an aft portion thereof that cooperates with a sealing element where the exhaust gases are discharged from the cavity. | 07-22-2010 |
| 20080199303 | Gas Turbine Engine Cooling System and Method | 08-21-2008 |
