| Patent application number | Description | Published |
|---|
| 20100127496 | GAS TURBINE ENGINE WITH INTEGRATED ELECTRIC STARTER/GENERATOR - An electrical machine is embedded into the compressor assembly of a gas turbine engine. An electrical system interface module distributes electrical current to and from the embedded electrical machine for starting the gas turbine engine and for operating accessory components. Accordingly, the gas turbine engine and accessory components can be started and operated without a power-takeoff shaftline and without an external accessory gearbox. | 05-27-2010 |
| 20110018273 | STARTER/GENERATOR INTEGRATED INTO COMPRESSOR OF TURBINE ENGINE - A turbine engine compressor has a rotor including rotating compressor discs. Magnets are positioned on the rotating compressor discs. Electrical coils are positioned in a stationary guide vane internal ring so as to create an electric machine providing starting torque to a rotor, and/or generating electrical energy once the rotor is rotating. | 01-27-2011 |
| 20110024567 | ELECTRICAL POWER GENERATION APPARATUS FOR CONTRA-ROTATING OPEN-ROTOR AIRCRAFT PROPULSION SYSTEM - An electrical power generation apparatus is embedded in a contra-rotating propulsion system that includes overlapping first and second shafts operatively connected for counter-rotation about a common axis. The electrical power generation apparatus includes a winding mounted to one of the shafts and a field array mounted to the other of the shafts adjacent to the winding. Relative rotation of the winding and the field array induces electrical current in the winding. | 02-03-2011 |
| 20110025157 | SYSTEM OF ELECTRICAL GENERATION FOR COUNTER-ROTATING OPEN-ROTOR BLADE DEVICE - A counter-rotating open-rotor blade aircraft propulsion system includes a structure supporting a plurality of blades. A rotor is drivingly coupled to the structure supporting the plurality of blades. The rotor includes a rotating coil disposed in the structure supporting the plurality of blades. A rotating magnetic field source includes two Halbach permanent magnet arrays. | 02-03-2011 |
| 20110283708 | LANDFILL GAS UTILIZATION - A method for utilizing landfill gas is disclosed herein. The method includes the step of collecting landfill gas. The method also includes the step of fueling a turbine engine that is at least part of a power generation system with the landfill gas to generate power. The method also includes the step of cooling one or more components of the power generation system with the landfill gas prior to the fueling step. A power generation system capable of practicing the method is also disclosed. A landfill gas utilization system capable of practicing the method is also disclosed. | 11-24-2011 |
| 20120247117 | VEHICLE SYSTEM - A system is disclosed one form of which is an aircraft that includes a pod capable of housing a work providing device. The pod can also include a thermal conditioning system and a power generation device that can be powered from the work providing device. The pod can provide thermal conditioning services and power services to a payload aboard the aircraft. In one non-limiting form the payload is a directed energy member that can be cooled using the thermal conditioning system and powered using the power generation device. | 10-04-2012 |
| 20120248242 | AIRCRAFT AND AIRBORNE ELECTRICAL POWER AND THERMAL MANAGEMENT SYSTEM - One embodiment of the present invention is a unique airborne electrical power and thermal management system. Another embodiment is a unique aircraft. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for aircraft and electrical power and thermal management systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith. | 10-04-2012 |
| 20120256045 | AIRBORNE COOLING SYSTEM - An aircraft having a cooling system is disclosed. The cooling system can be used to cool a heat emitting component. In one form the cooling system is a refrigerant system and includes a relatively high temperature device such as, but not limited to, a condenser. The relatively high temperature component is placed in thermal communication with a passing air flow. In one embodiment the aircraft includes a pod in which at least a portion of the cooling system is disposed. For example, a condenser of a vapor cycle refrigerant system can be located in the pod and in thermal communication with the air flow. The cooling system can also include a device capable of delivering a cooling fluid into the air flow and/or to the relatively high temperature component. The cooling fluid can be evaporated to provided additional cooling. | 10-11-2012 |
