Hamilton Sundstrand Corporation

Thaddeus J Zebrowski

Richard E Versailles

Kevin P Roy

A gas turbine engine includes a plurality of fuel injectors grouped operatively by stages in a multistage combustor. A fuel system for the gas turbine engine includes at least one fuel metering module per stage of the multistage combustor. Each fuel metering module includes a pump, a flow meter, a pressure sensor, a controller, and a motor, which work together to control fuel output.

Distributed aircraft engine fuel system

A flow balancing valve for a multistage combustor includes a first pressure feedback line, a first burn line, and a first metering port fluidly connected to the first fuel injector. The flow balancing valve further includes a second pressure feedback line, a second burn line, and a second metering port fluidly connected to the second fuel injector. A metering land is located between and defines sizes of the first metering port and the second metering port. An increase in pressure differential between the first pressure feedback line and the second pressure feedback line causes a compensatory movement in the metering land to balance fuel flow for the first fuel injector and the second fuel injector.

Flow balancing valve

An assembly for sensing temperature in a gas turbine engine includes a first array of RTDs connected in parallel, a second array of RTDs connected in parallel, and a circuit electrically connected to the first and second arrays. The circuit determines an approximate temperature of a medium as a function of resistance of the first and second arrays.

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Windsor, CT, United States of America

Thaddeus J Zebrowski