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| Number | Title | Issue Date |
| 7328114 | Methods and systems for measuring a rate of change of frequency A method for measuring a rate of change of frequency includes estimating at least one phasor value, estimating a frequency based on the estimated at least one phasor value, compensating the estimated at least one phasor value based on the estimated frequency, calcul... | 02/05/2008 |
| 7255318 | Stud mounting system A housing for a motor is described. The housing extends between a pair of endshields and includes an inner surface, an outer surface, and at least one raised projection extending outwardly from at least one of the housing inner and outer surfaces. The projection inc... | 08/14/2007 |
| 7253634 | Generator protection methods and systems self-tuning to a plurality of characteristics of a machine A method for detecting stator ground faults in a generator is described. The method includes receiving a neutral voltage signal from a neutral point of a stator, receiving a plurality of terminal voltage and current signals from the stator, deriving a magnitude of a... | 08/07/2007 |
| 7252543 | Methods and systems for measuring system loads and sub-metering electric power distribution Methods and systems for electrical distribution submetering are provided. The electrical distribution submetering system includes a modular load sensing assembly including a plurality of load sensors. The load sensing assembly further includes a first cable having a... | 08/07/2007 |
| 6592330 | Method and apparatus for non-parallel turbine dovetail-faces A dovetail assembly including non-parallel relief faces that facilitates reduced pressure face brinelling in turbine engines. The assembly includes a plurality of rotor blades, each including a dovetail. Each dovetail includes at least a pair of blade tan... | 07/15/2003 |
| 6584778 | Methods and apparatus for supplying cooling air to turbine engines A cooling air cooling system is selectively operable to reduce fuel gum deposits within the cooling system during gas turbine engine operations. The cooling system includes a recirculating loop that includes at least three heat exchangers in fluid communi... | 07/01/2003 |
| 6584766 | Methods and apparatus for minimizing thermal stresses in a centerbody A centerbody for a gas turbine engine includes a thermal control system which minimizes the thermal stresses between the centerbody and at least one stiffener. The centerbody stiffener extends radially inward from a centerbody shell. A cavity is defined w... | 07/01/2003 |
| 6582187 | Methods and apparatus for isolating gas turbine engine bearings A gas turbine engine including a rotor shaft includes a bearing isolation system including an isolation shaft and a pair of pilots. The pilots are disposed between the isolation and rotor shafts and connect the isolation shaft to the rotor shaft to form a... | 06/24/2003 |
| 6578362 | Methods and apparatus for supplying cooling air to turbine engines A cooling air cooling system operable to reduce fuel gum deposits within the cooling system when a gas turbine engine operates above a predefined percentage of rated engine power. The cooling system includes a recirculating loop including a plurality of h... | 06/17/2003 |
| 6561758 | Methods and systems for cooling gas turbine engine airfoils A gas turbine engine includes rotor blades including airfoils that facilitates reducing manufacturing losses due to airfoil trailing edge scarfing. Each airfoil includes a first and second sidewall connected at a leading edge and a trailing edge. The side... | 05/13/2003 |
| 6557349 | Method and apparatus for increasing heat transfer from combustors A combustor for a gas turbine engine includes a deflector assembly that enhances heat transfer from the combustor and minimizes low cycle fatigue stresses induced within the combustor. The deflector assembly includes a plurality of deflectors secured to a... | 05/06/2003 |
| 6558121 | Method and apparatus for turbine blade contoured platform A turbine blade assembly for a gas turbine engine that includes a turbine platform including contoured edges. The turbine blade assembly includes a platform, a turbine airfoil extending radially outward from the platform, a shank that extends radially inw... | 05/06/2003 |
| 6551062 | Turbine airfoil for gas turbine engine A hollow cooled turbine airfoil is provided having pressure and suction side walls and a plurality of trailing edge cooling passages that feed cooling air bleed slots at the trailing edge. The suction side wall has a selectively reduced thickness, which a... | 04/22/2003 |
| 6546732 | Methods and apparatus for cooling gas turbine engine combustors A one-piece deflector-flare cone assembly for a gas turbine engine combustor that facilitates extending a useful life of the combustor in a cost-effective and reliable manner is described. The one-piece assembly includes a deflector portion and a flare co... | 04/15/2003 |
| 6546733 | Methods and systems for cooling gas turbine engine combustors A combustor for a gas turbine includes a dome assembly that facilitates extending a useful life of the combustor in a cost-effective and reliable manner. The dome assembly includes a dome plate and a heat shield coupled to the dome plate. The dome plate i... | 04/15/2003 |
| 6530744 | Integral nozzle and shroud A gas turbine engine component including a nozzle outer band, a plurality of nozzle vanes extending inward from the outer band, and an inner band extending circumferentially around inner ends of the vanes. Further, the component has a shroud integral with... | 03/11/2003 |
| 6522990 | Methods and apparatus for reducing temperature overshoot Methods and apparatus for reducing temperature overshoot in an engine, such as in a gas turbine aircraft engine, are described. In an exemplary embodiment, an unmeasured temperature to be regulated in an engine is determined by measuring a temperature in ... | 02/18/2003 |
| 6516605 | Pulse detonation aerospike engine An aerospike engine has at least one nozzle surface and a plurality of pulse detonation devices mounted to the nozzle surface in place of the more common deflagration-based combustors. Each pulse detonation device is oriented such that its combustion prod... | 02/11/2003 |
| 6514037 | Method for reducing cooled turbine element stress and element made thereby A cooled turbine element including an airfoil and a flowpath boundary member extending laterally from either an inboard end or an outboard end of the airfoil. The member has a flowpath face and an outside face which is cooler than said flowpath face creat... | 02/04/2003 |
| 6511294 | Reduced-stress compressor blisk flowpath A gas turbine engine rotor assembly including a rotor having a radially outer rim with an outer surface shaped to reduce circumferential rim stress concentration between each blade and the rim. Additionally, the shape of the outer surface directs air flow... | 01/28/2003 |
| 6508613 | Drill guide and method for drilling holes A drill guide that is capable of guiding the drilling holes, in particular lockwire holes, transversely through one corner of a nut at an oblique angle to a face thereof and a method for using same. The drill guide comprises at least one guide component h... | 01/21/2003 |
| 6502400 | Combustor dome assembly and method of assembling the same A combustor dome assembly includes a spectacle plate having an opening formed therein that defines an inner circumferential edge, at least one swirler assembly defining an inner cylindrical surface, and at least one deflector having an outer cylindrical s... | 01/07/2003 |
| 6497103 | Methods for decreasing combustor emissions A combustor for a gas turbine engine operates with high combustion efficiency, and low carbon monoxide and nitrous oxide emissions during low, intermediate, and high engine power operations. The combustor includes a fuel delivery system that includes at l... | 12/24/2002 |
| 6487861 | Combustor for gas turbine engines with low air flow swirlers A combustor for a gas turbine engine includes outer and inner liners defining a combustion chamber and an igniter mounted to the outer liner. A dome plate is disposed between the outer and inner liners and has a plurality of circumferentially spaced openi... | 12/03/2002 |
| 6484492 | Magnetohydrodynamic flow control for pulse detonation engines Flow control in pulse detonation engines is accomplished using magnetohydrodynamic principles. The pulse detonation engine includes a tube having an open forward end and an open aft end and a fuel-air inlet formed in the tube at the forward end. An ignite... | 11/26/2002 |
| 6484489 | Method and apparatus for mixing fuel to decrease combustor emissions A combustor for a gas turbine engine operates with high combustion efficiency and low carbon monoxide, nitrous oxide, and smoke emissions during low, intermediate, and high engine power operations is described. The combustor includes a mixer assembly incl... | 11/26/2002 |
| 6471484 | Methods and apparatus for damping rotor assembly vibrations A multi-stage rotor assembly for a gas turbine engine includes a damper system that facilitates damping vibrations induced to the rotor assembly. The rotor assembly includes a blisk rotor including a plurality of rotor blades and a radially outer rim. The... | 10/29/2002 |
| 6471474 | Method and apparatus for reducing rotor assembly circumferential rim stress A rotor assembly for a gas turbine engine operates with reduced circumferential rim stress. The rotor assembly includes a rotor including a plurality of rotor blades extending radially outward from an annular rim. A root fillet extends circumferentially a... | 10/29/2002 |
| 6471469 | Methods and apparatus for sealing gas turbine engine variable nozzles A gas turbine engine variable geometry exhaust nozzle including a seal system that facilitates extending a useful life of the engine variable geometry system is described. The seal system includes a backbone and an attachment assembly. The attachment asse... | 10/29/2002 |
| 6463739 | Afterburner heat shield A heat shield and support strut for a turbine engine afterburner. The heat shield can be replaced without moving or disconnecting the fuel tube. The heat shield includes a housing that may be telescoped over the fuel injection tube and is attachable to th... | 10/15/2002 |
| 6442940 | Gas-turbine air-swirler attached to dome and combustor in single brazing operation A one-piece deflector-flare cone assembly for a gas turbine engine combustor that facilitates extending a useful life of the combustor in a cost-effective and reliable manner is described. The combustor includes an air swirler, and the one-piece assembly ... | 09/03/2002 |
| 6438940 | Methods and apparatus for providing uniform ignition in an augmenter An augmenter includes at least one igniter which provides a uniform ignition within the augmenter. The igniter is secured to an igniter housing with a self-locking nut and each igniter includes a biasing mechanism which biases the igniter against the augm... | 08/27/2002 |
| 6438958 | Apparatus for reducing heat load in combustor panels A combustor liner has a stepped combustor liner surface defining a combustion zone and an overhang portion forming an air cooling slot. A layer of thermal barrier material is applied to the combustor liner such that at least one portion of the combustor l... | 08/27/2002 |
| 6431820 | Methods and apparatus for cooling gas turbine engine blade tips A turbine for a gas turbine engine including a turbine nozzle assembly that facilitates reducing an operating temperature of rotor blades in a cost-effective and reliable manner is described. Each rotor blade includes a tip that rotates in close proximity... | 08/13/2002 |
| 6418726 | Method and apparatus for controlling combustor emissions A combustor for a gas turbine engine operates with high combustion efficiency and low carbon monoxide, nitrous oxide, and smoke emissions during low, intermediate, and high engine power operations is described. The combustor includes a mixer assembly incl... | 07/16/2002 |
| 6412161 | Shim removing method A tool for removing a shim from a dovetail of a fan blade for a turbine engine rotor includes a clip and a handle. The clip includes a release edge configured to engage a flared lip of a dovetail shim. The handle extends from the clip and contacts the ext... | 07/02/2002 |
| 6412284 | Methods and apparatus for supplying air to gas turbine engines A gas turbine engine assembly including a gas turbine engine mounted within a module and including an inlet in flow communication with a module inlet area and a module exhaust area is described. The turbine engine also includes an exhaust, and is mounted ... | 07/02/2002 |
| 6409464 | Methods and apparatus for supplying oil to bearing assemblies A gas turbine engine includes a lubrication system that supplies oil through a plurality of circumferential grooves and radial grooves to a bearing assembly. The grooves extend within an inner surface of a first rotor shaft sized to fit in an interference... | 06/25/2002 |
| 6398487 | Methods and apparatus for supplying cooling airflow in turbine engines A gas turbine engine rotor assembly includes a plurality of aerodynamic devices to direct airflow radially inward. The gas turbine engine rotor assembly includes a rotor shaft that includes a plurality of openings. The aerodynamic devices include a pair o... | 06/04/2002 |
| 6241466 | Turbine airfoil breakout cooling A turbine airfoil includes pressure and suction sides extending between leading and trailing edges and defining an internal cooling air passage. A row of trailing edge holes is disposed in flow communication with the air passage behind the trailing edge. ... | 06/05/2001 |
