| Patent application number | Description | Published |
|---|
| 20100092287 | PRESSURIZED SEALED CHAMBER BETWEEN MULTIPLE PRESSURIZED CASINGS OF MACHINE AND RELATED METHOD - A standard for supporting a bearing for a rotating shaft of a machine including a plurality of casings having different gas pressures greater than atmospheric pressure includes a sealed chamber for fluidly coupling to an end packing of a first casing and a second casing of the machine, the sealed chamber having a pressure greater than atmospheric pressure. The pressure in the sealed chamber reduces the leakage from the casing making more pressurized gas available for producing work in the machine. | 04-15-2010 |
| 20100112899 | VISUAL FEEDBACK FOR AIRFOIL POLISHING - A visual feedback system and method for airfoil polishing is disclosed. In one aspect there is a system for providing visual feedback during a polishing operation of a workpiece. In this system there is a model having a representation of a desired shape of the workpiece. A scanning system generates a representation of a current shape of the workpiece while in-process during the polishing operation. A comparator compares the current shape of the workpiece to the desired shape of the workpiece. An illumination system highlights the workpiece with visible light during the polishing operation. The highlighting of the workpiece with visible light is a function of the comparison between the current shape and the desired shape. The illumination system highlights a portion of the workpiece that needs additional polishing to conform to the desired shape. | 05-06-2010 |
| 20100158665 | SUPERSONIC COMPRESSOR - A novel supersonic compressor is provided by the present invention. In one embodiment, the novel supersonic compressor comprises a fluid inlet, a fluid outlet, and at least two counter rotary supersonic compressor rotors, said supersonic compressor rotors being configured in series such that an output from a first supersonic compressor rotor having a first direction of rotation is directed to a second supersonic compressor rotor configured to counter-rotate with respect to the first supersonic compressor rotor. | 06-24-2010 |
| 20100316488 | MIXING HOTTER STEAM WITH COOLER STEAM FOR INTRODUCTION INTO DOWNSTREAM TURBINE - Apparatus and methods are presented for mixing a high temperature steam, perhaps leaked from an upstream turbine, with the cooler steam from a lower temperature, downstream turbine and introducing the mixture into the downstream turbine. | 12-16-2010 |
| 20100329856 | SUPERSONIC COMPRESSOR COMPRISING RADIAL FLOW PATH - The present invention provides novel supersonic compressors comprising novel supersonic compressor rotors. The supersonic compressor rotors are designed to operate at very high rotational speed wherein the velocity of the gas entering the supersonic compressor rotor is greater than the local speed of sound in the gas, hence the descriptor “supersonic”. The new supersonic compressors comprise at least one supersonic compressor rotor defining an inner cylindrical cavity and an outer rotor rim and at least one radial flow channel allowing fluid communication between the inner cylindrical cavity and the outer rotor rim, said radial flow channel comprising a supersonic compression ramp. The novel supersonic compressor rotors are expected to enhance the performance of supersonic compressors comprising them, and to provide for greater design versatility in systems comprising such novel supersonic compressors. | 12-30-2010 |
| 20110126510 | PULSE DETONATION COMBUSTOR - In one embodiment, a pulse detonation combustor includes a gas discharge annulus including multiple nozzles engaged with one another via mating surfaces to support the gas discharge annulus in a circumferential direction. The pulse detonation combustor also includes multiple pulse detonation tubes extending to the nozzles. | 06-02-2011 |
| 20110126511 | THRUST MODULATION IN A MULTIPLE COMBUSTOR PULSE DETONATION ENGINE USING CROSS-COMBUSTOR DETONATION INITIATION - A method and apparatus for modulating the thrust during a flight envelope of a multiple combustor chamber detonation engine using cross-combustor chamber detonation initiation are provided. The detonation combustor chambers are filled with a combustible mixture of fuel and oxidizer. The combustible mixture in one of the detonation combustor chambers is ignited by an ignition source, and the remaining detonation combustor chambers are ignited by detonation cross-firing via connectors. A controller controls the ignition source and the supply of oxidizer and fuel to the detonation combustor chambers to modulate the thrust of the engine during the flight envelope. | 06-02-2011 |
| 20110142592 | SUPERSONIC COMPRESSOR ROTOR - The present invention provides a supersonic compressor comprising a supersonic compressor rotor comprising a clockable rotor disk allowing restriction or opening of portions of a fluid flow channel of the rotor in order to enhance performance of the rotor during different operational stages, for example rotor start-up or steady state. The supersonic compressor rotor comprises a first rotor disk, a second rotor disk and a third rotor disk which share a common axis of rotation. The first and second rotor disks are rotatably coupled, and the third rotor disk is disposed between them. The third rotor disk is independently rotatable relative to said first and second disks, and comprises a raised surface structure for restricting or opening a portion of the flow channel defined by the rotor disks and at least two vanes. The flow channel comprises a supersonic compression ramp and encompasses the raised surface structure. | 06-16-2011 |
| 20110146232 | CONTROL SYSTEM FOR A PULSE DETONATION TURBINE ENGINE - A pulse detonation turbine engine (PDTE) includes at least one controllable multi-tube pulse detonation combustor (PDC) configured to initiate firing of one or more pulse detonation tubes in response to operation of a plurality of controllable peripheral PDC components to regulate PDTE output characteristics. A control system including a programmable controller directed by algorithmic software operates to generate control inputs for the plurality of controllable peripheral PDC components in response to PDTE input conditions, such that one or more PD tube controllable inputs can be different for at least one PD tube relative to another PD tube within the multi-tube PDC, and further such that detonation timing can be different for at least one PD tube relative to another PD tube within the multi-tube PDC. | 06-23-2011 |
