General Electric Company

Robert Edward Goeller

Michael E Colman

Joseph Alfred Iannotti

Aaron Jay Knobloch

David Allen Gutz

William James Mailander

Douglas Scott Jacobs

Mudassar Ali Muhammad

Lauren Marie Kelly

A gas turbine engine and system for measuring torque for a gas turbine engine shaft is provided. The system may include a first sensor module, a second sensor module, a first coupler, a second coupler, and a static antenna. The first and second sensor modules may include strain sensors positioned on the gas turbine engine shaft. The first coupler may be positioned on the gas turbine engine shaft and electrically connected with the first sensor module. The second coupler may be positioned on the gas turbine engine shaft and electrically connected with the second sensor module. The static antenna may include a first band and a second band. The first signal band may be in operable communication with the first sensor module and positioned radially outward from the first coupler. The second signal band may be in operable communication with the second sensor module and positioned radially outward from the second coupler.

Turbine engine shaft torque sensing

A computer-implemented method for controlling a fuel flow to a gas turbine engine of an aircraft includes determining a control initiated fuel flow demand that is based, at least in part, on an operator command. In addition, the method includes determining a first rate of change of fuel flow demand based, at least in part, on a tracking error of the gas turbine engine that indicates a difference between a desired rotational speed and an actual rotational speed. The method also includes integrating the first rate of change of fuel flow demand to determine a tracking error fuel flow demand. In addition, the method includes summing the control initiated fuel flow demand and tracking error fuel flow demand to determine a composite fuel flow demand. The method also includes controlling a fuel flow to the gas turbine engine based, at least in part, on the composite fuel flow demand.

System and method for controlling a fuel flow to a gas turbine engine

A direct metering architecture is provided having a metering pump and a servo pump wherein the metering and servo pumps are driven by an engine shaft by way of a gearbox transmission. The system reduces wasted horsepower previously occurring with oversized fixed displacement pumps, reduces instances of engine flameout and reduces the amount of heat added to fuel which ultimately improves engine oil cooling.

Direct metering using a variable displacement vane pump

The invention comprises a system for cooling a component in a gas turbine engine, and, in particular, for cooling an engine electronic control thereof. The cooling system includes a housing for mounting the control having a plurality of heat transfer fins extending outwardly therefrom. The housing is mounted in the engine upstream of a compressor and to a front frame having an aperture through which the fins extend. The front frame defines a flowpath to the compressor and the fins extend into the flowpath without adversely affecting the aerodynamic airflow pattern thereof. In a preferred embodiment, the fins extend substantially only to an inner surface of the front frame, and the housing includes temperature and pressure sensors disposed below root sections of the fins.

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Beverly, MA, United States of America

Robert Edward Goeller