| 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 |
| 20120023892 | SYSTEMS AND METHODS FOR CO2 CAPTURE - The present disclosure relates to the separation of CO | 02-02-2012 |
| 20120023947 | SYSTEMS AND METHODS FOR CO2 CAPTURE - The present disclosure relates to the separation of CO | 02-02-2012 |
| 20120087779 | SUPERSONIC COMPRESSOR STARTUP SUPPORT SYSTEM - A supersonic compressor includes a fluid inlet, a fluid outlet, a fluid conduit extending therebetween, and at least one supersonic compressor rotor disposed within the fluid conduit and including a fluid flow channel that includes a throat portion. The supersonic compressor also includes a fluid control device coupled in fluid communication with at least one fluid source and an inlet of the fluid flow channel. The fluid control device channels a first fluid to the fluid flow channel inlet. The first fluid has a first plurality of fluid properties that facilitate attainment of supersonic flow of the first fluid in the throat portion during a first operational mode. The fluid control device further channels a second fluid to the fluid flow channel inlet. The second fluid has a second plurality of fluid properties that permit maintenance of supersonic flow of the second fluid in the throat portion. | 04-12-2012 |
| 20120107106 | SYSTEM AND METHOD OF ASSEMBLING A SUPERSONIC COMPRESSOR SYSTEM INCLUDING A SUPERSONIC COMPRESSOR ROTOR AND A COMPRESSOR ASSEMBLY - A supersonic compressor system. The supersonic compressor system includes a casing that defines a cavity that extends between a fluid inlet and a fluid outlet, and a first drive shaft that is positioned within the cavity. A centerline axis extends along a centerline of the first drive shaft. A supersonic compressor rotor is coupled to the first drive shaft and is positioned in flow communication between the fluid inlet and the fluid outlet. The supersonic compressor rotor includes at least one supersonic compression ramp that is configured to form at least one compression wave for compressing a fluid. A centrifugal compressor assembly is positioned in flow communication between the supersonic compressor rotor and the fluid outlet. The centrifugal compressor assembly is configured to compress fluid received from the supersonic compressor rotor. | 05-03-2012 |
| 20120151895 | HOT GAS PATH COMPONENT COOLING FOR HYBRID PULSE DETONATION COMBUSTION SYSTEMS - The flow through the core of a hybrid pulse detonation combustion system is passed through a compressor and then separated into a primary flow, that passes directly to the combustor, and a bypass flow, which is routed to a portion of the system to be used to cool components of the system. The bypass includes a pump that raises the pressure of the bypass flow sufficient to deliver it to downstream stations of the engine that contain combustion products that are at a higher pressure than the compressor exit. | 06-21-2012 |
| 20120151896 | HOT GAS PATH COMPONENT COOLING FOR HYBRID PULSE DETONATION COMBUSTION SYSTEMS - The flow through the core of a hybrid pulse detonation combustion system is passed through a compressor and then separated into a primary flow, that passes directly to the combustor, and a bypass flow, which is routed to a portion of the system to be used to cool components of the system. The bypass flow is routed to a nozzle of the pulse detonation combustor. The flow is then passed back into the primary flow through the core downstream of where it was extracted. | 06-21-2012 |
| 20120156015 | SUPERSONIC COMPRESSOR AND METHOD OF ASSEMBLING SAME - A supersonic compressor includes a fluid inlet and a fluid outlet, a fluid conduit extending therebetween, and a supersonic compressor rotor disposed within the fluid conduit. The rotor includes at least one rotor disk that includes a substantially cylindrical body extending between a radially inner and outer surface and a plurality of vanes coupled to the body that extend radially outward from the rotor disk and adjacent vanes form a pair of vanes. The rotor disk further includes a shroud extending about at least a portion of the rotor disk. The shroud is coupled to at least a portion of each of the plurality of vanes. The radially outer surface, the pair of adjacent vanes, and the shroud are oriented such that a fluid flow channel is defined therebetween. The rotor disk also includes a plurality of adjacent supersonic compression ramps positioned within the fluid flow channel. | 06-21-2012 |
| 20120156016 | SUPERSONIC COMPRESSOR ROTOR AND METHODS FOR ASSEMBLING SAME - A supersonic compressor rotor that includes a rotor disk that includes a body that extends between a radially inner surface and a radially outer surface. A plurality of vanes are coupled to the body. The vanes extend outwardly from the rotor disk. Adjacent vanes form a pair and are oriented such that a flow channel is defined between each pair of adjacent vanes. The flow channel extends between an inlet opening and an outlet opening. At least one supersonic compression ramp is positioned within the flow channel. The supersonic compression ramp is configured to condition a fluid being channeled through the flow channel such that the fluid includes a first velocity at the inlet opening and a second velocity at the outlet opening. Each of the first velocity and the second velocity being supersonic with respect to said rotor disk surfaces. | 06-21-2012 |
| 20120224952 | SYSTEM AND METHODS OF ASSEMBLING A SUPERSONIC COMPRESSOR ROTOR INCLUDING A RADIAL FLOW CHANNEL - A supersonic compressor rotor that includes a rotor disk that includes a substantially cylindrical endwall, a radially inner surface, and a radially outer surface. The endwall extends between the radially inner surface and the radially outer surface. A plurality of vanes are coupled to the endwall. The vanes extend outwardly from the endwall. Adjacent vanes form a pair and are spaced a circumferential distance apart such that a flow channel is defined between each pair of circumferentially-adjacent vanes. The flow channel extends generally radially between an inlet opening and an outlet opening. A first supersonic compression ramp is coupled to the endwall. The first supersonic compression ramp is positioned within the flow channel to facilitate forming at least one compression wave within the flow channel. | 09-06-2012 |
| 20120301270 | SUPERSONIC COMPRESSOR STARTUP SUPPORT SYSTEM - A supersonic compressor includes a fluid inlet, fluid outlet, and a fluid conduit extending therebetween with a supersonic compressor rotor disposed therein. The supersonic compressor rotor includes a first endwall and a plurality of vanes coupled thereto. Each pair of the vanes defines a fluid flow channel. The fluid flow channel defines a flow channel inlet opening and a flow channel outlet opening and includes a throat portion. The supersonic compressor rotor also includes a second endwall and at least one axially translatable fluid control device positioned adjacent to the rotor. The axially translatable fluid control device is configured to obstruct the throat portion and includes at least one axially translatable protrusion insertable into at least a portion of the throat portion. | 11-29-2012 |
| 20120301271 | SUPERSONIC COMPRESSOR ROTOR AND METHOD OF COMPRESSING A FLUID - A supersonic compressor rotor. The supersonic compressor rotor includes a substantially cylindrical disk body that includes an upstream surface, a downstream surface, and a radially outer surface that extends generally axially between the upstream surface and the downstream surface. The disk body defines a centerline axis. A plurality of vanes are coupled to the radially outer surface. Adjacent vanes form a pair and are oriented such that a flow channel is defined between each pair of adjacent vanes. The flow channel extends generally axially between an inlet opening and an outlet opening. At least one supersonic compression ramp is positioned within the flow channel. The supersonic compression ramp is selectively positionable at a first position, at a second position, and at any position therebetween. | 11-29-2012 |
| 20130104595 | SYSTEMS AND METHODS FOR TREATING CARBON DIOXIDE | 05-02-2013 |
| 20130125580 | EXPANDER AND METHOD FOR CO2 SEPARATION - In one aspect an expander for separating carbon dioxide (CO | 05-23-2013 |
| 20130216393 | RADIAL IMPELLER WITH A RADIALLY FREE BASIC RIM - The invention provides an impeller designed to be mounted on a rotary shaft. The impeller comprises a basic rim provided with blades protruding on one surface of the basic rim, and a hub capable of being coupled to the basic rim and to the rotary shaft. In certain embodiments, the impeller comprises an annular plate and the hub, the plate and the basic rim are configured to interact together so as to hold the basic rim axially and to maintain a freedom of radial deformation of the basic rim relative to the hub and to the plate. | 08-22-2013 |
| 20140119881 | APPARATUS FOR RECIRCULATING A FLUID WITHIN A TURBOMACHINE AND METHOD FOR OPERATING THE SAME - A turbomachine for use with a high-temperature and high-pressure working fluid is provided. The turbomachine includes a rotatable shaft and a casing enclosing the rotatable shaft, which defines at least a first and second compartment fluidly coupled together. The first compartment at least partially encloses one of a compressor and an expander. The second compartment at least partially encloses a generator. Attached to opposite ends of the rotatable shaft is a compressor for compressing the working fluid and an expansion turbine for expanding the working fluid. A motor-generator is attached to the rotatable shaft between the compressor and expansion turbine. The turbomachine includes at least one sealing system positioned between the first and second compartments that includes a number of seals for regulating the flow rate of the working fluid between the first and second compartments and for suppressing the heat and pressure transfer between the first and second compartments. | 05-01-2014 |
| 20150033792 | SYSTEM AND INTEGRATED PROCESS FOR LIQUID NATURAL GAS PRODUCTION - A system and method for producing liquid natural gas (LNG) from a natural gas stream is presented. The system includes a moisture removal device and compressor for removing moisture from and compressing the natural gas stream. The low moisture compressed natural gas stream is cooled in a heat exchanger to discharge a cooled compressed discharge stream. A multi-phase turbo expander provides for further cooling and expansion of the cooled compressed discharge stream, generating an expanded exhaust stream comprising a mixture of a vapor comprised substantially of CH | 02-05-2015 |
