Abstract: Propeller blade assemblies and a propeller blade retention assembly including a sleeve for operably coupling a propeller blade to a hub wherein the sleeve retains the propeller blade within the hub and allows the propeller blade to rotate about its pitch axis and where the sleeve includes a self-aligning mechanism.
Type:
Grant
Filed:
June 16, 2015
Date of Patent:
May 1, 2018
Assignee:
GE Aviation Systems, LLC
Inventors:
Rajendra Vishwanath Pawar, Ravindra Shankar Ganiger, Murugesan Periasamy, David Raju Yamarthi, Sandeep Kumar, Amit Arvind Kurvinkop, Bajarang Agrawal, Nagashiresha G
Abstract: A method and system are provided for coordinating a propeller with a controller module including a machine having a controller module and a propeller mounted to a propeller shaft at a hub. The shaft is arranged to be received in the machine, and a sensor is mounted to the machine, connected to the electronic controller module, and configured to sense the propeller when the propeller shaft is received in the machine.
Abstract: A current-sensing assembly that includes a power module, for providing switchable power, having a current output extending through and directly away from the top exterior surface of the power module, a Hall sensor, capable of measuring current traversing through a conductor, having an opening, and the current output extending through the opening.
Type:
Grant
Filed:
February 14, 2014
Date of Patent:
April 3, 2018
Assignee:
GE Aviation Systems, LLC
Inventors:
Ryan Lee Buffenbarger, Hao Huang, Chad Joseph Brown
Abstract: Systems and methods for predicting aircraft navigation performance are provided. In one embodiment, a method can include determining that one or more navigational aid measurements are not available to the aircraft. The method can include estimating a future actual navigation performance of the aircraft for a future point in the flight plan. The method can include determining a future required navigation performance associated with the future point in the flight plan. The method can include comparing the future actual navigation performance to the future required navigation performance to determine if the future actual navigation performance satisfies the future required navigation performance. The method can include providing, to an onboard system of the aircraft, information indicative of whether the future actual navigation performance satisfies the future required navigation performance.
Abstract: A method and power converter unit for operating a generator includes a rotatable shaft operably coupled with a source of rotational force, a rotor mounted to the rotatable shaft and having at least one rotor pole defining a rotatable direct axis, a stator encircling the rotor and having a set of stator windings, and a power output electrically coupled with the set of stator windings and operable in a power generating mode and a power absorption mode
Type:
Grant
Filed:
February 13, 2016
Date of Patent:
March 13, 2018
Assignee:
GE Aviation Systems, LLC
Inventors:
Ryan Lee Buffenbarger, Xiaochuan Jia, Slobodan Gataric
Abstract: An aircraft power distribution system (22) includes at least one DC power source, a first DC power distribution bus and a second DC power distribution bus (36), a tie bus (33) coupling the at least one DC power source, first DC power distribution bus, and second DC distribution bus, wherein the first or second DC power distribution buses are selectively coupled and decoupled to the tie bus by means of a solid-state poer controller (SSPC) (46, 48, 62, 64, 66).
Type:
Application
Filed:
October 4, 2013
Publication date:
September 29, 2016
Applicant:
GE Aviation Systems LLC
Inventors:
Arthur Vorwerk RADUN, Steven Allan TOOTHMAN
Abstract: A three phase inverter consisting of three single phase legs using either switch mode or linear control is fed by a DC-DC converter to provide input output isolation. This requires that the DC-DC converter delivers equal positive and negative voltages to the single phase legs to allow each output to generate a high fidelity sine wave outputs to the load. By measuring the error voltages on the positive output, the negative output and the total output of the DC-DC converter it is possible to control a single duty cycle while maintaining all three output voltages within the limits required by the DC-AC phase legs. This significantly reduces the cost and complexity of the DC-DC converter and eliminates the need to use a fourth phase leg to generate the neutral connection for a three phase output.
Type:
Grant
Filed:
June 26, 2014
Date of Patent:
August 23, 2016
Assignee:
GE Aviation Systems, LLC
Inventors:
Philip Henry Richard Epps, Andrew Benjamin Cole
Abstract: A turbofan engine having a turbine engine, a nacelle surrounding a portion of the turbine engine, and a thrust reverser. The thrust reverser comprises a movable control surface movable to and from a reversing position and a thrust reverser actuation system having at least one actuator operably coupled to the movable control surface to move the movable control surface into and out of the reversing position. A guide comprising a rail and a bogie having at least one rotatable bearing surface coupled to the rail for relative translational movement between the rail and bogie connects the turbine engine to the movable control surface such that operation of the at least one actuator moves the movable control surface by translation movement between the rail and the bogie.
Type:
Application
Filed:
June 2, 2014
Publication date:
June 30, 2016
Applicant:
GE Aviation Systems LLC
Inventors:
John S. Mears, George Stephen Billisits, Chad Russell Wentling
Abstract: A jet engine assembly includes a jet engine having at least one spool and a generator. The generator comprising a rotor and a stator, with the rotor being operably coupled to the at least one spool, and an electronic commutator controlling the rotation of a magnetic field of the rotor such that the electric motor generates electricity. Also, a method of generating electricity from a generator having a stator and a rotor, the method comprising controlling a rotation of a magnetic field to generate electricity.
Type:
Application
Filed:
June 6, 2013
Publication date:
May 12, 2016
Applicant:
GE Aviation Systems LLC
Inventors:
Rock O'Brien BLAZER, Joshua Martin RHYNARD
Abstract: A turbofan engine having a thrust reverser having at least one movable control surface, movable to and from a reversing position where at least a portion of the bypass air flow is at least partially reversed, a thrust reverser actuation system having multiple actuators and a lockout mechanism movable between an inhibit condition, wherein movement of the multiple actuators is prevented, and a permit condition, wherein movement of the multiple actuators is permitted.
Type:
Application
Filed:
June 7, 2013
Publication date:
March 17, 2016
Applicant:
GE Aviation Systems LLC
Inventors:
Kenneth R. WILLETT, Brent Michael Ozanich, George Arnold Conway, Jonathan L. Spiry, Daniel Peter Beck, Jeffrey Michael Larkin
Abstract: A method of projecting into space, from a first object, a plurality of modulated lines to form a grid defining a first relative reference frame, the method includes projecting polarized light having a first orientation to form a horizontal grid line projecting from the first object and projecting polarized light having a second orientation different than the first orientation to from a vertical grid line projecting from the first object and modulating the horizontal grid line and the vertical grid line to carry first and second grid words, respectively.
Abstract: A method of providing synchronization and integrity checking in a high integrity processing system having at least two redundant processing lanes, with each lane having an application processor, with the application processors running the same application software in a non-lockstep configuration, and outputting transactions requiring access to an addressable space.
Abstract: An electric machine having a rectifier assembly placed within a rotating shaft of the electric machine to convert the AC output of the electric machine to the DC input prior to transmission of the electricity from the electric machine.
Abstract: An electric machine, such as a generator, providing for the generation of electricity and includes a rotor generating a magnetic field and a stator having stator windings. The interaction of the magnetic field with the stator windings generates current in the windings. The generator may provide the generated current to a power output of the generator, where it may be further transmitted to an electrical load to power the load.
Type:
Application
Filed:
February 28, 2014
Publication date:
September 3, 2015
Applicant:
GE Aviation Systems LLC
Inventors:
Paul James Wirsch, JR., Winfred Dwight Koontz, James Patrick Mahle
Abstract: A rotor assembly for an electric machine includes a core having at least one post and a cap wherein electrical windings are wound about the rotor assembly to define a pole. The rotation of the rotor and rotor pole relative to a stator generates a current supplied from the electric machine to a power consuming device.
Type:
Application
Filed:
February 28, 2014
Publication date:
September 3, 2015
Applicant:
GE Aviation Systems LLC
Inventors:
Paul James Wirsch, JR., Hao Huang, Xiaochuan Jia, Jan Zywot
Abstract: The invention relates a method of identifying a tracked object that has a known database of hyperspectral and spatial information. The method associates an identifier with the tracked object; selects a parameter associated with the hyperspectral or spatial information of the tracked object; detects a deviation in the selected parameter; compares the deviation with the database; and if the deviation exceeds a predetermined threshold, assigns a new identifier to the tracked object, and if the deviation does not exceed the predetermined threshold, continues tracking the tracked object.
Type:
Grant
Filed:
August 17, 2012
Date of Patent:
September 1, 2015
Assignee:
GE Aviation Systems, LLC
Inventors:
Eric Daniel Buehler, Benjamin Thomas Occhipinti, Konrad Robert Kuczynski
Abstract: A method of projecting into space, from a first object, a plurality of modulated lines to form a grid defining a first relative reference frame, the method includes simultaneously projecting into space from the first object a horizontal grid line and a vertical grid line to form a set of grid lines, modulating the horizontal grid line and the vertical grid line to carry first and second grid words, respectively.
Abstract: A method and system for thermal management includes an engine heat exchanger configured to transfer waste heat from an engine to a heat transfer fluid and an engine exhaust heat exchanger coupled in flow communication with the engine heat exchanger wherein the engine exhaust heat exchanger is configured to transfer heat from an exhaust of the propulsive engine to the pumped heat transfer fluid. A bypass valve is coupled in parallel with the engine exhaust heat exchanger wherein the bypass valve is selectable to modulate a flow of the heat transfer fluid through the engine exhaust heat exchanger and a plurality of accessory heat exchangers that are coupled in flow communication with at least one of the engine heat exchanger and the engine exhaust heat exchanger and each of the plurality of accessory heat exchangers flow is controllable using a modulating valve.
Type:
Grant
Filed:
August 30, 2010
Date of Patent:
August 25, 2015
Assignee:
GE Aviation Systems, LLC
Inventors:
Kent I. Weber, Athanasios Kyriazopoulos, Peter C. Hightower, Lance F. Miller, Ronald J. Soave
Abstract: A power controller system configured to electrically supply a load via a circuit is provided. The system comprises, a switching device provided in an electrical pathway for supplying current to the load, a controller configured to open the switching device when a current through or voltage across the switching device exceeds a predetermined level; and an electrical pathway provided parallel to the load to enable load current to continue to flow through the parallel electrical pathway and the load when the switching device is open to dissipate inductive energy stored in the circuit connecting the parallel electrical pathway to the load.
Abstract: A current-sensing assembly for aircraft includes a power module for providing switchable power and a Hall sensor capable of measuring current traversing through a conductor.
Type:
Application
Filed:
February 14, 2014
Publication date:
August 20, 2015
Applicant:
GE Aviation Systems LLC
Inventors:
Ryan Lee Buffenbarger, Hao Huang, Chad Joseph Brown