Patent application number | Description | Published |
20120027164 | APPARATUS AND METHOD FOR MAGNETIC CONTROL OF AN ELECTRON BEAM - An apparatus and method for an electron beam manipulation coil for an x-ray generation system includes the use of a control circuit. The control circuit includes a first low voltage source, a second low voltage source, and a first switching device coupled in series with the first low voltage source and configured to create a first current path with the first low voltage source when in a closed position. The control circuit also includes a second switching device coupled in series with the second low voltage source and configured to create a second current path with the second low voltage source when in a closed position and a capacitor coupled in parallel with an electron beam manipulation coil and positioned along the first and second current paths. | 02-02-2012 |
20120027165 | APPARATUS AND METHOD FOR MAGNETIC CONTROL OF AN ELECTRON BEAM - An apparatus and method for magnetic control of an electron beam includes a control circuit having a first low voltage source and a second low voltage source. The control circuit also includes a first switching device coupled in series with the first low voltage source and configured to create a first current path with the first low voltage source when in a closed position and a second switching device coupled in series with the second low voltage source and configured to create a second current path with the second low voltage source when in a closed position. The control circuit further includes a capacitor coupled in parallel with an electron beam manipulation coil and positioned along the first and second current paths and a current source circuit electrically coupled to the electron beam manipulation coil and constructed to generate an offset current in the first and second current paths. | 02-02-2012 |
20120274139 | SWITCHING COORDINATION OF DISTRIBUTED DC-DC CONVERTERS FOR HIGHLY EFFICIENT PHOTOVOLTAIC POWER PLANTS - A distributed photovoltaic (PV) power plant includes a plurality of distributed dc-dc converters. The dc-dc converters are configured to switch in coordination with one another such that at least one dc-dc converter transfers power to a common dc-bus based upon the total system power available from one or more corresponding strings of PV modules. Due to the coordinated switching of the dc-dc converters, each dc-dc converter transferring power to the common dc-bus continues to operate within its optimal efficiency range as well as to optimize the maximum power point tracking in order to increase the energy yield of the PV power plant. | 11-01-2012 |
20130076144 | SYSTEM AND METHOD FOR LIMITING PHOTOVOLTAIC STRING VOLTAGE - A system and method are provided for enabling a PV inverter to be connected to a string of series connected PV modules without exposing the inverter to elevated voltage stresses. The input voltage to the inverter is gradually built up by sequentially switching in more series PV modules. This system and method are simple to implement in both centralized and distributed PV power plants and in either case, it significantly increases the utilization of the PV inverter. The input switching elements can be implemented using a wide variety of parts including electro-mechanical switches, semiconductor switches (IGBTs, MOSFETs . . . , etc.) as well as MEMS devices depending on the current level and target cost. A mix of switches can also be used to assist in minimizing impedance of the final switching stage that remains connected during normal operation. | 03-28-2013 |
20140001856 | MULTILEVEL POWER CONVERTER | 01-02-2014 |
20140146585 | SYSTEM AND METHOD FOR POWER CONVERSION - A power converter is provided. The power converter includes a converter leg including switches for converting power. The power converter also includes a controller for switching the switches using a pulse width modulation technique. The power converter further includes an interface inductor coupled to the converter leg for avoiding a reverse recovery of current in the switches during operation. | 05-29-2014 |
20140176151 | METHODS FOR LOCATING GROUND FAULTS AND INSULATION DEGRADATION CONDITION IN ENERGY CONVERSION SYSTEMS - Methods for determining a ground fault or insulation degradation condition within energy conversion systems are described. A method for determining a ground fault within an energy conversion system may include, in part, a comparison of baseline waveform of differential current to a waveform of differential current during operation for a plurality of DC current carrying conductors in an energy conversion system. A method for determining insulation degradation within an energy conversion system may include, in part, a comparison of baseline frequency spectra of differential current to a frequency spectra of differential current transient at start-up for a plurality of DC current carrying conductors in an energy conversion system. In one embodiment, the energy conversion system may be a photovoltaic system. | 06-26-2014 |
20150015066 | METHOD AND SYSTEM FOR CONTROL AND PROTECTION OF DIRECT CURRENT SUBSEA POWER SYSTEMS - A method and a high-voltage DC (HVDC) power system are provided. The system includes a plurality of sending-end (SE) modules coupled in electrical series and divided into at least two groups that each operate independently with respect to an electrical ground and a plurality of receiving-end (RE) power converter modules electrically coupled to the plurality of SE modules, the plurality of RE power converter modules including a fast ground-fault detection and control device, the plurality of RE power converter modules including a receiving-end front-end DC-DC converter controller, and an output current damping control. | 01-15-2015 |
Patent application number | Description | Published |
20090103975 | Attaching element - An attaching element for the connection of two components | 04-23-2009 |
20100223905 | SCOOP OF A RUNNING-GAP CONTROL SYSTEM OF AN AIRCRAFT GAS TURBINE - A scoop for a fairing | 09-09-2010 |
20100224348 | METHOD FOR THE MANUFACTURE OF AN EJECTOR NOZZLE TUBE - A method for manufacturing an ejector nozzle tube, includes forming an essentially rectangular plate-type blank | 09-09-2010 |
20110005858 | NOISE-REDUCED AIRCRAFT ENGINE AND METHOD FOR REDUCING NOISE EMISSIONS OF AN AIRCRAFT ENGINE - A method for reducing noise emissions of an aircraft engine ( | 01-13-2011 |
20110121136 | AIRCRAFT DE-ICING DEVICE AND ENGINE NACELLE OF AN AIRCRAFT GAS TURBINE WITH DE-ICING DEVICE - An aircraft de-icing device and an engine nacelle of an aircraft gas turbine is provided with a de-icing device, with the engine nacelle | 05-26-2011 |
20110139925 | ARRANGEMENT FOR THE SUSPENSION OF A JET ENGINE TO A SUPPORTING STRUCTURE - An arrangement ( | 06-16-2011 |
20110215172 | Aircraft engine with optimized oil heat exchanger - This invention relates town ejector nozzle tube | 09-08-2011 |
20120006614 | GAS-TURBINE EXHAUST CONE - A gas-turbine exhaust cone includes a cone shaped outside cone | 01-12-2012 |
20120285138 | AIRCRAFT GAS-TURBINE ENGINE WITH OIL COOLER IN THE ENGINE COWLING - The present invention relates to an aircraft gas-turbine engine with a core engine surrounded by a bypass duct, with a radially outer engine cowling enclosing the bypass duct and being provided at its rear region with a thrust-reversing device which is moveable relative to the engine cowling, with at least one cooler element extending over at least part of the circumference being arranged in the intermediate area between the engine cowling and the thrust-reversing device. | 11-15-2012 |
20120298802 | De-icing device of an aircraft gas-turbine engine - The present invention relates to a de-icing device of an aircraft gas-turbine engine with an engine cowling enclosing at least one inflow region, with the engine cowling having a double-walled design and including at least one annular tube element extending in the circumferential direction and being provided with outlet openings for passing hot air to an inflow region, in order to de-ice it, with the tube element in the circumferential direction including multiple individual tube segments which can be attached relative to one another. | 11-29-2012 |
20130008147 | Aircraft gas turbine with variable bypass nozzle - The present invention relates to an aircraft gas turbine with a core engine | 01-10-2013 |
20130011246 | Gas-Turbine Aircraft Engine With Structural Surface Cooler - The present invention relates to a gas-turbine aircraft engine with a core engine surrounded by a bypass duct, with a substantially annular cooling element being provided in the area of a radially inner wall of the bypass duct downstream of stator vanes of the bypass duct. | 01-10-2013 |
20130025962 | Gas-turbine exhaust cone with three-dimensionally profiled partition wall and plate-type wall element - A gas-turbine exhaust cone has an outer wall with a plurality of recesses, a honeycomb-structured layer arranged at the inside of the outer wall and extending along said inside of the outer wall, an inner wall connected to the honeycomb structure and extending essentially parallel to the outer wall, and at least one annular chamber centered on a central axis and adjoining the inner wall. The inner wall has passage recesses connecting the area of the honeycomb structure to the annular chamber, with the annular chamber being subdivided in the circumferential direction by at least one partition wall into several chambers. The partition wall is made from a sheetmetal-like material and has a plurality of raised and/or recessed areas in a uniform arrangement formed by shaping of the sheetmetal-like material. | 01-31-2013 |
20130180227 | Fastening element and de-icing device of an aircraft gas-turbine engine - The present invention relates to a fastening element, in particular to its use in a de-icing device of an aircraft gas-turbine engine, for connecting two components, with the fastening element ensuring a connection of the components with a predetermined relative movability to each other, with the fastening element including two struts arranged at an angle to each other, where two first end areas, spacedly arranged to each other, can be fastened to one of the components, and the two other second end areas can be connected to each other and fastened to the other component. | 07-18-2013 |
20130205753 | Aircraft gas turbine thrust-reversing device - An aircraft gas turbine thrust-reversing device has an engine cowling, the rear area of which is displaceable in the axial direction of the engine from a closed forward thrust position into a rearwardly displaced thrust reversal position, resulting in an essentially annular space to a front and stationary area of the engine cowling. The rear area of the engine cowling is coupled to deflecting elements and blocker doors, which in the forward thrust position are arranged completely inside the front area of the engine cowling. A drive element is provided between the front area and the rear area, which effects the axial displacement of the rear area. The drive element is a two-stage drive element, effecting in a first stage an axial displacement by an axial partial displacement path, and in a second stage an axial displacement by the full axial displacement path. | 08-15-2013 |
20130230383 | Aircraft gas turbine with adjustable fan - The present invention relates to an aircraft gas turbine having a fan rotatable about an engine axis in the inflow region of the aircraft gas turbine, with the fan having several fan blades, with each fan blade being moveably mounted on a hub rotatable about the engine axis by means of its blade root on an area which is at the front in the flow direction, and with each fan blade being moveably mounted on an area at the rear in the flow direction, on an adjusting disk axially displaceable relative to the engine axis and non-rotatable with the hub, with the pitch angle of the fan blades being variable by the axial movement of the adjusting disk. | 09-05-2013 |
20130306401 | SOUND ABSORBER FOR A GAS TURBINE EXHAUST CONE, AND METHOD FOR THE PRODUCTION THEREOF - A method for manufacturing a sound absorber, the outer wall of which is provided with a plurality of recesses, with funnel-like cone elements each being assigned to the recesses inside the sound absorber, said cone elements having a larger opening facing radially outwards and a smaller opening facing radially inwards, with adjacent cone elements each being provided on a strip-shaped first carrier band, with cup elements being provided radially on the inside relative to the cone elements, and each cup element receiving one cone element, with adjacent cup elements each being provided on a strip-shaped first carrier band, with the first carrier bands being arranged adjacently in a first direction, and the second carrier bands being arranged adjacently in a second direction, with the directions crossing each other and the carrier bands being joined to one another and to the outer wall to form a rigid body. | 11-21-2013 |
20130306402 | METHOD FOR THE PRODUCTION OF A SOUND ABSORBER, ESPECIALLY FOR A GAS TURBINE EXHAUST CONE - The present invention relates to a method for manufacturing a body provided with a honeycomb structure, which body is designed preferably axis-symmetrical, with sheet-metal parts being provided with a wave-like structuring by means of a forming process and formed to ring elements, with the sheet-metal parts being shaped and designed in a substantially identical way as regards their structuring, with adjacent sheet-metal parts being arranged offset to one another and then joined together to form the honeycomb structure. | 11-21-2013 |
20130306403 | METHOD FOR THE PRODUCTION OF A SOUND ABSORBER, ESPECIALLY FOR A GAS TURBINE EXHAUST CONE - The present invention relates to a gas-turbine exhaust cone having an outer wall, which is provided with a plurality of recesses, a honeycomb-structured layer, which is arranged on the inside of the outer wall and extends along the inside of the outer wall, an inner wall, which extends substantially parallel to the outer wall and is connected to the honeycomb structure, and at least one annular chamber, which adjoins the inner wall and is centered relative to a central axis, with the inner wall being provided with passage recesses 33-connecting the area of the honeycomb structure to the annular chamber. | 11-21-2013 |
20130318945 | AVIATION GAS TURBINE THRUST REVERSING DEVICE - The present invention relates to an aircraft gas turbine thrust-reversing device with an engine having an engine cowling, the rear area of which can be displaced in the axial direction of the engine from a closed forward thrust position into a rearwardly displaced thrust reversal position, resulting in an essentially annular free space towards a forward stationary area of the engine cowling, with the rear area of the engine cowling being functionally coupled to deflecting elements arranged in the forward thrust position within the front area of the engine cowling, with the deflecting elements during displacement of the rear area of the engine cowling being moveable on a partial-circular path facing the central axis of the engine and contactable by their rear end areas with a cowling of the core engine. | 12-05-2013 |
20140064928 | Engine casing of an aircraft gas turbine having sound-absorbing elements in the fan inflow region - The present invention relates to an engine casing of an aircraft gas turbine having a radially inner honeycomb-structured layer arranged on the engine casing in the flow direction upstream of a fan in the area of an inflow-side air inlet, characterized in that sound-absorbing elements are arranged radially outside at least one axial section of the honeycomb-structured layer, said elements extending in the axial direction and being arranged annularly next to one another in the circumferential direction. | 03-06-2014 |
20140116025 | AEROENGINE THRUST REVERSER ARRANGEMENT - A blocker door for a gas turbine engine thrust reverser having a tray with a base and sidewalk extending about the base to define a volume, the volume being dosed by a cover that extends beyond the periphery of the tray. The extension of the cover beyond the periphery provides a sealing feature. | 05-01-2014 |
20140116026 | AEROENGINE THRUST REVERSER ARRANGEMENT - A gas turbine engine has a core engine and a nacelle having a cowl translatable along the axis of the engine from a stowed position to a deployed position, A thrust reverser cascade extends circumferentially about the engine axis. To obviate the need for additional blanking cascades the cowl has a forwardly extending tongue that in the deployed position of the cowl is at the same axial position as the thrust reverser cascade. | 05-01-2014 |
20140127001 | GAS-TURBINE ENGINE WITH A TELESCOPIC AIR INLET IN THE ENGINE LINING - An aircraft gas-turbine engine has an engine cowling-nacelle which surrounds a core engine in a tubular way, characterized in that at least one inflow-side part of the engine cowling-nacelle is telescopically movable against the flow direction. | 05-08-2014 |
20140140820 | AEROENGINE SEALING ARRANGEMENT - A bifurcation aerofoil having a leading edge portion and flanks where the leading edge portion is mounted to an inner wall of the bypass duct using a floating seal which permits circumferential movement of the leading edge. A cowl has a wall that provides the flanks of the aerofoil. On closing of the cowl into its flight position any contact between the flanks and the leading edge portion enables realignment of the leading edge portion to the inner wall of the bypass duct. | 05-22-2014 |
20150052908 | BLEED DUCT ASSEMBLY FOR A GAS TURBINE ENGINE - A bypass duct has a support unit comprising a pair of aerofoils arranged as an “A” frame. A bleed duct assembly is provided on the radially inner wall of the bypass duct annulus and the aerofoils project from the surface and extend across the annulus between the inner wall and an outer wall of the annulus. The aerofoils lean at an acute angle to the surface with the first flank facing toward the inner wall and adjoining a bleed duct opening. The bleed duct having a bleed duct passage and a submerged scoop. | 02-26-2015 |