General Electric Company

General Electric Company Polska Sp. Z O.o.

Ge Avio S.r.l.

Generale Electric Company Polska Sp. Z O.o

Inenhe Mohammed Khalid

Stefan Joseph Cafaro

Daniel Edward Mollmann

James Ryan Reepmeyer

Arjan Johannes Hegeman

Amit Zutshi

Rafal Sarba

Jason Scott Dangel

Brandon Wayne Miller

Arthur William Sibbach

Andrea Piazza

Hejie Li

Andrew Hudecki

Kevin Richard Graziano

Michael Joseph Murray

Daniel Roy Kiracofe

David Allen Bradford

Daryl S Schneider

An open rotor aeronautical engine may include a core engine, a plurality of unducted airfoils, and a pitch change assembly. The pitch change assembly may include an ensemble actuator assembly and a unitary actuator assembly. The ensemble actuator assembly may have one or more ensemble actuators and a unison ring that is movable by actuation of the one or more ensemble actuators to collectively change a pitch angle of the plurality of unducted airfoils. The unitary actuator assembly comprising a plurality of unitary actuators respectively coupled to a corresponding one of the plurality of unducted airfoils, the plurality of unitary actuators respectively movable to change the pitch angle of the corresponding one of the plurality of unducted airfoils.

Controlling excitation loads associated with open rotor aeronautical engines

A gas turbine engine includes a fan section having a fan rotatable with a fan shaft, a turbomachinery section having a turbine and a turbomachine shaft rotatable with the turbine, a power gearbox mechanically coupled to the fan shaft and the turbomachine shaft such that the fan shaft is rotatable by the turbomachine shaft across the power gearbox, a grounded structure coupled to and supporting the power gearbox, and a torque monitoring system. The torque monitoring system includes a gearbox sensor. The gearbox sensor is coupled to the grounded structure and the torque monitoring system configured to determine a torque across the power gearbox using the gearbox sensor.

System and method for detecting and reducing torque in a turbine engine

An open rotor engine includes a core engine, a plurality of guide vanes positioned within or extending from the core engine; and a pitch change assembly operably coupled to the plurality of guide vanes. The pitch change assembly includes one or more actuators configured to change a pitch angle of respective ones of the plurality of guide vanes, and a plurality of linkage arms that are respectively movable by actuation of at least one of the one or more actuators. The plurality of linkage arms are directly or indirectly coupled to a corresponding one of the plurality of guide vanes. The plurality of linkage arms may have a length that differs from one another, and such length may orient a displacement or a range of motion of the respective linkage arm to an envelope of rotation about a guide vane axis that differs as between the plurality of guide vanes.

A method of controlling an aeronautical gas turbine engine may be performed with an electronic controller. The method may include determining an airfoil pitch control command for at least one of a plurality of airfoils of the aeronautical gas turbine engine based at least in part on an excitation load acting upon the aeronautical gas turbine engine, and outputting the airfoil pitch control command to one or more actuators actuatable to change a pitch angle of the at least one of the plurality of airfoils. The airfoil pitch control command may be configured to augment and/or compensate for the excitation load acting upon the aeronautical gas turbine engine. The method may be embodied by a non-transitory computer-readable medium that includes computer-executable instructions, which when executed by a processor associated with the electronic controller, cause the electronic controller to perform the method.

Pursuant to various embodiments, systems, apparatuses and methods are provided herein useful to monitoring one or more components coupled to shaft-driven gearbox of an engine or motor. In some approaches, the systems include a sensor, such as a vibration sensor, mechanically linked or mounted to the shaft-driven gearbox. The vibration sensor may be used to monitor a vibration response of one or more components coupled to the shaft-driven gearbox. It is contemplated, by monitoring a component coupled to the shaft-driven gearbox using the systems and methods described herein, is possible to proactively detect one or more faults in the component and/or to identify one or more maintenance actions.

Systems and methods for monitoring component failure in a gear train based system

Systems and methods for indirect monitoring of combustor dynamics in a gas turbine engine include collecting vibration data acquired by a vibration sensor, which is mounted proximate to an operational component positioned relative to a combustor of a gas turbine engine. The vibration data can be transformed into a frequency domain representation at periodic intervals. The relative signal strength of the vibration data can be determined over the one or more identified frequency bands. The relative signal strength can be adjusted with hysteresis at each of the one or more identified frequency bands. Occurrence of a combustor dynamics event at one or more specific resonant frequencies can be determined based at least in part on evaluation of the adjusted relative signal strength relative to one or more event detection threshold levels.

Indirect monitoring of aircraft combustor dynamics

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Hamilton, OH, United States of America

Inenhe Mohammed Khalid