Patent application number | Description | Published |
20080227648 | Winding for Use in High Temperature Superconducting Generator - A winding for use in a superconducting electric generator having a rotating rotor assembly surrounded by a non-rotating stator assembly is provided. The winding comprises at least one conductor structure associated with a component in the superconducting electric generator. The conductor structure comprises a plurality of conductive elements formed from a high temperature superconductive material. At least a portion of the conductive elements is arranged in a transposed relationship. A protective shell is positioned about the conductive elements and formed from a high strength alloy suitable for cryogenic temperatures. | 09-18-2008 |
20090315425 | SUPERCONDUCTING COIL SUPPORT STRUCTURES - Support structures ( | 12-24-2009 |
20100201220 | ROTOR WINDING SHIELD FOR A SUPERCONDUCTING ELECTRIC GENERATOR - A generator rotor core ( | 08-12-2010 |
20100299913 | ROTOR POLE CROSSOVER CONNECTION - A rotor pole crossover connection joint for use in a rotating electrical machine is disclosed. The connection joint integrally couples a bottom rotor coil strap to a rotor pole crossover connector with a single piece connector that reduces, distributes or otherwise tolerates stress concentrations in the connector. A corresponding method of forming a rotor pole crossover connection and a rotor assembly including a rotor pole crossover connection joint are also disclosed | 12-02-2010 |
20120204574 | GAS TURBINE ENGINE - A power turbine receiving cooling fluid from compressor apparatus is provided. The turbine comprises: fixed housing structure; a support shaft rotatably supported in the housing structure; at least one disk overhung on the support shaft and coupled to the support shaft so as to rotate with the support shaft; and cooling fluid structure. The at least one disk is formed from a low-alloy-content steel. The cooling fluid supply structure extends through the support shaft and the at least one disk so as to supply cooling fluid to the at least one disk. | 08-16-2012 |
20140056686 | COOLING AIR CONFIGURATION IN A GAS TURBINE ENGINE - Cooling air is provided from a source of cooling air through a cooling air circuit in a turbine section of a gas turbine engine. A first portion of cooling air is provided from the source along a first path of the circuit to a plurality of blades associated with a stage of the turbine section. A second portion of cooling air is provided from the source along a second path of the circuit. The second path includes a turbine disc bore where the cooling air provides cooling to a radially innermost portion of at least one turbine disc that forms a part of a rotor of the engine. The second path is independent from the first path such that the second portion of cooling air bypasses the stage and is not mixed with the first portion of cooling air in the circuit after leaving the source. | 02-27-2014 |
20140060068 | METHOD FOR OPERATING A GAS TURBINE ENGINE INCLUDING A COMBUSTOR SHELL AIR RECIRCULATION SYSTEM - During full load operation of gas turbine engine operation, a valve system is maintained in a closed position to substantially prevent air from passing through a piping system of a shell air recirculation system. Upon initiation of a turn down operation, which is implemented to transition the engine to a turning gear state or a shut down state, the valve system is opened to allow air to pass through the piping system. A blower is operated to extract air through at least one outlet port of the shell air recirculation system from an interior volume of an engine casing portion associated with the combustion section, to convey the extracted air through the piping system, and to inject the air into the interior volume of the engine casing portion through at least one inlet port of the shell air recirculation system to circulate air within the engine casing portion. | 03-06-2014 |
20140060082 | COMBUSTOR SHELL AIR RECIRCULATION SYSTEM IN A GAS TURBINE ENGINE - A shell air recirculation system for use in a gas turbine engine includes one or more outlet ports located at a bottom wall section of an engine casing wall and one or more inlet ports located at a top wall section of the engine casing wall. The system further includes a piping system that provides fluid communication between the outlet port(s) and the inlet port(s), a blower for extracting air from a combustor shell through the outlet port(s) and for conveying the extracted air to the inlet port(s), and a valve system for selectively allowing and preventing air from passing through the piping system. The system operates during less than full load operation of the engine to circulate air within the combustor shell but is not operational during full load operation of the engine. | 03-06-2014 |
20140119880 | TEMPERATURE CONTROL WITHIN A CAVITY OF A TURBINE ENGINE - A turbine engine including an intermediate space defined between outer and inner portions of the turbine engine. A flow energizer is provided including a flow body located within the intermediate space and including an inlet port, an outlet port and a flow passage extending within the flow body between the inlet and outlet ports. The inlet port receives a flow of a first medium located within the intermediate space and the flow body injects an energizing flow of a second medium to a portion of the first medium within the flow body to create an energized flow of a mixed medium from the outlet portion, the energized flow of mixed medium creates a flow of the first medium adjacent to the flow body within the intermediate space. | 05-01-2014 |
20140301820 | TURBINE ENGINE SHUTDOWN TEMPERATURE CONTROL SYSTEM WITH NOZZLE INJECTION FOR A GAS TURBINE ENGINE - A turbine engine shutdown temperature control system configured to limit thermal gradients from being created within an outer casing surrounding a turbine blade assembly during shutdown of a gas turbine engine is disclosed. By reducing thermal gradients caused by hot air buoyancy within the mid-region cavities in the outer casing, arched and sway-back bending of the outer casing is prevented, thereby reducing the likelihood of blade tip rub, and potential blade damage, during a warm restart of the gas turbine engine. The turbine engine shutdown temperature control system may operate during the shutdown process where the rotor is still powered by combustion gases or during turning gear system operation after shutdown of the gas turbine engine, or both, to allow the outer casing to uniformly, from top to bottom, cool down. | 10-09-2014 |
20140301834 | TURBINE CYLINDER CAVITY HEATED RECIRCULATION SYSTEM - A turbine engine heating system configured to heat compressor and turbine blade assemblies to eliminate turbine and compressor blade tip rub during warm restarts of gas turbine engines is disclosed. The turbine engine heating system may include a heating air extraction system configured to withdraw air from the turbine engine and to pass that air thru a heating element configured to increase a temperature of the air supplied by the heating air extraction system. The air may then be passed to a heating air supply system via an air movement device. The heating air supply system may be in communication with a turbine cylinder cavity of the turbine engine positioned radially outward from at least one turbine assembly. The heated air may be passed into the turbine cylinder cavity to reduce the cooling rate of the turbine vane carriers after shutdown and before a warm restart to limit tip rubbing. | 10-09-2014 |
20140321981 | TURBINE ENGINE SHUTDOWN TEMPERATURE CONTROL SYSTEM - A turbine engine shutdown temperature control system configured to foster consistent air temperature within cavities surrounding compressor and turbine blade assemblies to eliminate turbine and compressor blade tip rub during warm restarts of gas turbine engines is disclosed. The turbine engine shutdown temperature control system may include one or more air amplifiers positioned in a turbine case. An exhaust outlet of the air amplifier may extend into a cavity created by a turbine case and may be configured to exhaust air in a generally circumferential direction to entrain air within the cavity to flow circumferentially to establish a consistent air temperature within the cavity thereby preventing uneven cooling of turbine engine components after shutdown and prevent damage to turbine components during a warm restart. | 10-30-2014 |