Abstract: 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.

Abstract: A fluid pumping system for an engine includes a pump; a summing differential connected to the pump; a gearbox connected to the summing differential, wherein the gearbox causes the pump to rotate to provide a fluid flow in the engine via the summing differential; and a motor connected to the summing differential, wherein the motor adjusts a rotational speed of the pump via the summing differential

Abstract: A distributed electronic control system for an aircraft includes an engine data controller arranged on an airframe of the aircraft and a plurality of engine data concentrators arranged proximate an engine of the aircraft in signal communication with the engine data controller. The engine data controller is configured to process information related to the engine of the aircraft, the plurality of engine data concentrators are configured to receive engine sensor information from a plurality of engine sensors, and the plurality of engine data concentrators are further configured to transmit the engine sensor information to the engine data controller.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: A full authority digital engine controller (FADEC) controls an engine attached to an airframe. The FADEC includes an electronic engine controller (EEC) attached to the engine, an airframe data concentrator (ADC) attached to the airframe, and a digital data bus electrically connecting the ADC to the EEC. The ADC is electrically connected to a plurality of airframe sensors to convert the airframe sensor signals to airframe sensor digital data. The digital bus conducts the airframe sensor digital data to the EEC.

Abstract: A fuel metering unit (FMU) for an aircraft engine includes an effector and an electronic engine controller (EEC). The effector is electrically connected to the EEC to adjust a rate of fuel flowing into the engine. The adjustment is in response to a control signal sent from the EEC. The control signal sent from the EEC is responsive to an engine sensor signal and to airframe sensor information.

Abstract: A system for configuring a full authority digital engine controller (FADEC) for use with an engine and an airframe combination. The system includes the FADEC and a data entry plug. The FADEC includes an electronic engine controller (EEC) attached to the engine, an airframe data concentrator (ADC) attached to the airframe, and a digital bus electrically connecting the ADC to the EEC. The ADC includes a data storage device and a data entry plug socket. The data entry plug includes electrical components configured for the engine and the airframe combination. The data entry plug is inserted into the data entry plug socket to direct the ADC to recall configuration data from the data storage device for the engine and the airframe combination and send the configuration data over the digital bus to the EEC.

Abstract: 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.