| Patent application number | Description | Published |
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| 20090089417 | DIALOGUE ANALYZER CONFIGURED TO IDENTIFY PREDATORY BEHAVIOR - A dialogue analyzer configured to identify online communications relating to lewd, predatory, hostile, and/or otherwise inappropriate subject matter is disclosed. Identified communications include those occurring via social networks, instant messaging, online chat rooms, computer in-game chat, email and the like. The communications of a monitored computer user are scanned to identify those communications that match predetermined lexical rules. The rules comprise sets of word-concepts that may be associated based on spelling, sound, meaning, appearance or probability of appearance in a text string, etc. Various numbers and configurations of word concepts may be implemented in a rule in order to more accurately scan the online communication data for a potential match. When a match is found, a copy of the communication, along with contextual information, is presented to a parent or guardian user. This information is presented at a central website and via an email notification to the parent or guardian. Various embodiments are described. | 04-02-2009 |
| 20110178793 | DIALOGUE ANALYZER CONFIGURED TO IDENTIFY PREDATORY BEHAVIOR - A dialogue analyzer configured to identify online communications relating to lewd, predatory, hostile, and/or otherwise inappropriate subject matter is disclosed. Identified communications include those occurring via social networks, instant messaging, online chat rooms, computer in-game chat, email and the like. The communications of a monitored computer user are scanned to identify those communications that match predetermined lexical rules. The rules comprise sets of word-concepts that may be associated based on spelling, sound, meaning, appearance or probability of appearance in a text string, etc. Various numbers and configurations of word concepts may be implemented in a rule in order to more accurately scan the online communication data for a potential match. When a match is found, a copy of the communication, along with contextual information, is presented to a parent or guardian user. This information is presented at a central website and via an email notification to the parent or guardian. Various embodiments are described. | 07-21-2011 |
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| 20080273969 | 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 within an outer body. The inner and outer bodies have offset inner and outer axes, intermeshed inner and outer helical blades wound about the inner and outer axes respectively, and at least one of the inner and outer bodies being rotatable about a corresponding one of the inner and outer axes. An aircraft gas turbine engine has components in serial downstream flow relationship including a fan, a low pressure compressor, a high pressure compressor, a combustor, a high pressure turbine, and a low pressure turbine. At least one of the components is radially bladed and at least one of the components is a worm component. | 11-06-2008 |
| 20100166591 | POSITIVE DISPLACEMENT ROTARY COMPONENTS HAVING MAIN AND GATE ROTORS WITH AXIAL FLOW INLETS AND OUTLETS - An axial flow positive displacement gas turbine engine component such as a compressor or a turbine or an expander includes a rotor assembly extending from a fully axial flow inlet to a downstream axially spaced apart axial flow outlet. The rotor assembly includes a main rotor and one or more gate rotors rotatable about parallel main and gate axes of the main and gate rotors respectively. The main and gate rotors having intermeshed main and gate helical blades extending radially outwardly from annular main and gate hubs, circumscribed about, and wound about the main and gate axes respectively. Intersecting main and gate annular openings in the axial flow inlet extend radially between a casing surrounding the rotor assembly and the main and gate hubs. The main helical blades transition from 0 to a full radial height in a downstream direction in an inlet transition section. | 07-01-2010 |
| 20110076158 | METHOD OF OPERATING ADAPTIVE CORE ENGINES - A method of operating a compressor in an adaptive core engine is disclosed. The method comprises the steps of operating a front block compressor to increase pressure of a fluid to a first pressure ratio in a high-power mode operation; operating a rear block compressor coupled to the front block compressor such that the front block compressor and the rear block compressor operate at the same physical speed; closing a rear block stator vane located axially forward from the rear block compressor such that the flow of the fluid into the rear block compressor is substantially cut off; and keeping a blocker door opened such that substantially all of the fluid pressurized by the front block compressor flows through a bypass passage during the high-power mode operation. The operation may be transitioned from the high-power mode to a low-power mode by opening a rear block stator such that the rear block compressor receives at least a portion of the fluid flowing from the front block compressor and maintains an overall engine pressure ratio. | 03-31-2011 |
| 20110120082 | MULTISTAGE TIP FAN - A fan assembly having an outer fan system is disclosed, the fan assembly comprising an outer fan first stage and an outer fan second stage both extending radially outward from an arcuate platform. | 05-26-2011 |
| 20110120083 | GAS TURBINE ENGINE WITH OUTER FANS - A gas turbine engine comprising an outer fan system is disclosed, having an outer fan first stage having a circumferential row of outer fan first blades, an outer fan second stage having a circumferential row of outer fan second blades located axially aft from the outer fan first stage wherein the outer fan first stage and the outer fan second stage are adapted to rotate with the fan rotor. | 05-26-2011 |
