Abstract: A turbo engine for an aircraft includes a gas turbine engine having a fuel system to provide fuel to a combustion section. The fuel system includes a variable displacement pump driven by an accessory gearbox that is powered by a shaft of the gas turbine engine. The variable displacement pump has an inlet side and an outlet side. The variable displacement pump includes an actuator configured to adjust a discharge flow rate of the variable displacement pump. The fuel system also includes a fuel metering valve configured to receive pressurized fuel from the variable displacement pump and control a flow rate of the pressurized fuel to the combustion section. The fuel system further includes a bypass valve fluidly coupling the outlet side and the inlet side of the variable displacement pump to direct an excess portion of the pressurized fuel at the outlet side back to the inlet side.

Abstract: A pump mixer separator unit is provided in communication with a stripping gas line that provides an inlet stripping gas flow and a fuel line that provides an inlet fuel flow. The pump mixer separator unit includes a first pump in fluid communication with the stripping gas line and the fuel line to form a fuel/gas mixture flow and generate a first pressure rise from the inlet fuel flow to the fuel/gas mixture flow; and a second pump in fluid communication with the first pump, wherein the second pump receives the fuel/gas mixture flow from the first pump, wherein the second pump separates the fuel/gas mixture flow into an outlet stripping gas flow and an outlet fuel flow and generates a second pressure rise from the fuel/gas mixture flow to the outlet fuel flow, wherein the first pump includes a supplemental pump feature for drawing an inlet fuel flow through the fuel line during operation.

Abstract: A fuel oxygen reduction unit assembly for a fuel system is provided. The fuel oxygen reduction unit assembly includes: a fuel oxygen reduction unit located downstream from the fuel source and defining a stripping gas flowpath and a liquid fuel flowpath, the fuel oxygen reduction unit comprising a means for transferring an amount of oxygen from a liquid fuel flow through the liquid fuel flowpath to a gas flow through the stripping gas flowpath; and an oxygen conversion unit in flow communication with the stripping gas flowpath configured to extract a flow of oxygen from a gas flow through the stripping gas flowpath, the oxygen conversion unit defining an oxygen outlet configured to provide the extracted flow of oxygen to an external system.

Abstract: A method of delivering fuel to an engine during operation of the engine, that includes, sensing the speed of sound in the fuel, determining a density or property of the fuel, and based on that density or fuel property adjusting the flow rate of the fuel. Further, an established fuel profile or determined energy density value can also be used to adjust the flow rate of the fuel.

Abstract: A fuel oxygen reduction unit assembly for a fuel system is provided. The fuel oxygen reduction unit assembly includes: a fuel oxygen reduction unit located downstream from the fuel source and defining a stripping gas flowpath and a liquid fuel flowpath, the fuel oxygen reduction unit comprising a means for transferring an amount of oxygen from a liquid fuel flow through the liquid fuel flowpath to a gas flow through the stripping gas flowpath; and an oxygen conversion unit in flow communication with the stripping gas flowpath configured to extract a flow of oxygen from a gas flow through the stripping gas flowpath, the oxygen conversion unit defining an oxygen outlet configured to provide the extracted flow of oxygen to an external system.

Abstract: A fuel metering system for a combustion section of a turbo machine is provided. The turbo machine includes a main fuel line configured to provide a flow of fuel and a zone fuel line split from the main fuel line through which at least a portion of the flow of fuel is provided. A fuel valve is disposed at the zone fuel line and is configured to obtain and receive a present fuel valve area value and a present valve position value. A first pressure sensor is disposed upstream of the fuel valve, in which the first pressure sensor is configured to obtain a first pressure value. A second pressure sensor is disposed downstream of the fuel valve, in which the second pressure sensor is configured to obtain a second pressure value. A flow meter is disposed downstream of the fuel valve.

Abstract: A method of delivering fuel to an engine during operation of the engine, that includes, sensing the speed of sound in the fuel, determining a density or property of the fuel, and based on that density or fuel property adjusting the flow rate of the fuel. Further, an established fuel profile or determined energy density value can also be used to adjust the flow rate of the fuel.

Abstract: In accordance with one exemplary embodiment of the present disclosure, a method for providing overspeed protection for a gas turbine engine is provided. The gas turbine engine may include an engine core and an engine shaft. The method may include determining an overspeed condition of the engine. The overspeed condition may be indicative of an above normal rotational speed of the engine shaft. The method may also include reducing an airflow through the engine core of the gas turbine engine in response to the determined overspeed condition to reduce the rotational speed of the engine shaft.

Abstract: A pump mixer separator unit is provided in communication with a stripping gas line that provides an inlet stripping gas flow and a fuel line that provides an inlet fuel flow. The pump mixer separator unit includes a first pump in fluid communication with the stripping gas line and the fuel line to form a fuel/gas mixture flow and generate a first pressure rise from the inlet fuel flow to the fuel/gas mixture flow; and a second pump in fluid communication with the first pump, wherein the second pump receives the fuel/gas mixture flow from the first pump, wherein the second pump separates the fuel/gas mixture flow into an outlet stripping gas flow and an outlet fuel flow and generates a second pressure rise from the fuel/gas mixture flow to the outlet fuel flow, wherein the first pump includes a supplemental pump feature for drawing an inlet fuel flow through the fuel line during operation.

Abstract: A fuel metering system for a combustion section of a turbo machine is provided. The turbo machine includes a main fuel line configured to provide a flow of fuel and a zone fuel line split from the main fuel line through which at least a portion of the flow of fuel is provided. A fuel valve is disposed at the zone fuel line and is configured to obtain and receive a present fuel valve area value and a present valve position value. A first pressure sensor is disposed upstream of the fuel valve, in which the first pressure sensor is configured to obtain a first pressure value. A second pressure sensor is disposed downstream of the fuel valve, in which the second pressure sensor is configured to obtain a second pressure value. A flow meter is disposed downstream of the fuel valve.

Abstract: A rotary actuator for control of variable geometry vanes is provided. The actuator is rotary so that operating components are internalized to protect fuel from contamination. The rotary actuator is a self-contained unit so that the device may be removed from the gas turbine engine without requiring removal of additional fuel system components. Finally, some embodiments of the rotary actuator may comprise multiple actuator loops to provide adjustment for two or more rows of vanes, independently.

Abstract: Methods and apparatus for measuring liquid fuel flows within a conduit are disclosed. An example flow sensor may include a conduit arranged to flow fuel therethrough along a flow axis, the conduit defining a flow area orthogonal to the flow axis. The flow sensor may further include a first transducer arranged to direct a first signal through the conduit proximate the flow area to a second transducer, the second transducer being arranged to direct a second signal through the conduit proximate the flow area to the first transducer, the first transducer being spaced apart from the second transducer by a signal path length, and in a direction parallel to the flow axis by an axial distance. The fuel flow measuring system may further include a processor arranged to calculate a fuel mass flow rate based on first and second signal transit times, known fuel properties and a fuel temperature.

Abstract: In accordance with one exemplary embodiment of the present disclosure, a method for providing overspeed protection for a gas turbine engine is provided. The gas turbine engine may include an engine core and an engine shaft. The method may include determining an overspeed condition of the engine. The overspeed condition may be indicative of an above normal rotational speed of the engine shaft. The method may also include reducing an airflow through the engine core of the gas turbine engine in response to the determined overspeed condition to reduce the rotational speed of the engine shaft.

Abstract: 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.

Abstract: Methods and apparatus for measuring liquid fuel flows within a conduit are disclosed. An example flow sensor may include a conduit arranged to flow fuel therethrough along a flow axis, the conduit defining a flow area orthogonal to the flow axis. The flow sensor may further include a first transducer arranged to direct a first signal through the conduit proximate the flow area to a second transducer, the second transducer being arranged to direct a second signal through the conduit proximate the flow area to the first transducer, the first transducer being spaced apart from the second transducer by a signal path length, and in a direction parallel to the flow axis by an axial distance. The fuel flow measuring system may further include a processor arranged to calculate a fuel mass flow rate based on first and second signal transit times, known fuel properties and a fuel temperature.

Abstract: 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.

Abstract: A rotary actuator for control of variable geometry vanes is provided. The actuator is rotary so that operating components are internalized to protect fuel from contamination. The rotary actuator is a self-contained unit so that the device may be removed from the gas turbine engine without requiring removal of additional fuel system components. Finally, some embodiments of the rotary actuator may comprise multiple actuator loops to provide adjustment for two or more rows of vanes, independently.

Abstract: Rotary vane actuator operated air valves associated with gas turbine engines are disclosed. An example gas turbine engine may include a fan, a compressor, a combustor, and a turbine in a serial flow relationship; a supply pipe arranged to convey compressed air from one or more of the fan and the compressor; a valve operatively disposed in the supply pipe, the valve including a rotatable valve member arranged to modulate flow of the compressed air through the supply pipe based upon an angular position of the valve member, the valve member being rotatable between an open position and a shut position; and/or a hydraulically operated rotary vane actuator operatively coupled to rotate the valve member.

Abstract: A gas turbine engine control component includes at least one electronic device, electronics such as an integrated circuit associated with the device, and a thermoelectric cooler for cooling the electronics mounted in a compartment. The thermoelectric cooler may be disposed in or on a wall of the compartment with a heat sink connected to a hot side of the thermoelectric cooler and a cold side of the thermoelectric cooler exposed to an interior of the compartment. Data about and/or operating instructions for the device may be stored in memory on the integrated circuit. The data may be calibration information for the device. A bus connector is connected to the integrated circuit for transferring operating instructions and/or data from the integrated circuit out and/or out of the component. A controller or control system incorporating these devices and components have the devices electronically connected to the integrated circuit.

Abstract: A gas turbine engine control component includes at least one electronic device, electronics such as an integrated circuit associated with the device, and a thermoelectric cooler for cooling the electronics mounted in a compartment. The thermoelectric cooler may be disposed in or on a wall of the compartment with a heat sink connected to a hot side of the thermoelectric cooler and a cold side of the thermoelectric cooler exposed to an interior of the compartment. Data about and/or operating instructions for the device may be stored in memory on the integrated circuit. The data may be calibration information for the device. A bus connector is connected to the integrated circuit for transferring operating instructions and/or data from the integrated circuit out and/or out of the component. A controller or control system incorporating these devices and components have the devices electronically connected to the integrated circuit.