Systems and methods for optimizing clearances within an engine include an adjustable coupling configured to couple a thrust link to the aircraft engine, an actuator coupled to the adjustable coupling, where motion produced by the actuator adjusts a hinge point of the adjustable coupling, sensors configured to capture real time flight data, and an electronic control unit. The electronic control unit receives flight data from the sensors, implements a machine learning model trained to predict clearance values within the engine based on the received flight data, predicts, with the machine learning model, the clearance values within the engine based on the received flight data, determines an actuator position based on the clearance values, and causes the actuator to adjust to the determined actuator position.

A system and method for determining performance of an engine is provided. The system includes two or more sensors configured in operable arrangement at two or more respective positions at a flowpath. The system includes one or more computing devices configured to perform operations, the operations include acquiring, via the two or more sensors, parameter sets each corresponding to two or more engine conditions different from one another, wherein each parameter set indicates a health condition at a respective location at the engine; comparing, via the computing device, the parameter sets to determine the respective health condition corresponding to the respective location at the engine; and generating, via the computing device, a health condition prediction based on the compared parameter sets.

A power generation system includes one or more micro-turbine electric generators (“MTEGs”). The MTEGs include a housing having an inlet for receiving pressurized gas and an outlet for releasing expanded gas. The MTEGs also include a rotor, a user-replaceable nozzle for directing pressurized gas over blades of the rotor, and a stator for generating alternating current (“AC”) responsive to rotation of the rotor. The power generation system also includes a programmable logic controller (“PLC”) coupled to the MTEGs that operates flow control valves (“FCVs”) coupled to the MTEGs to modulate the flow of gas to the MTEGs to generate output power suitable to support an electrical load. The system also includes power conversion circuitry configured to convert AC generated by the MTEGs to direct current (“DC”) and to provide the DC to an electrical load. The system also includes a skid for mounting multiple and MTEGs and FCVs.

A valving system has an actuator member connected to move with an actuator piston and change the position of a valve member. There is a smaller face fluid chamber acting on a small area piston face, and a larger face fluid chamber acting on a larger face of the actuator piston. The torque motor has an armature and a flapper caused to move by current received at the armature. The flapper moves between two fluid ports to control the pressure in the larger face chamber. The flapper further has a positioning extension engaging a first feedback spring operable between it and a forward face of the actuator piston and providing a spring force in combination with a spring force from the positioning extension. A control is operable to provide current to the armature to control the fluid received in the larger face chamber. The controller is programmed to associate the current supplied to the armature to an actual position of the valve member. A method is also disclosed.

A bleed air system for a pneumatic system of an aircraft includes a low-pressure bleed tap configured to bleed a low-pressure compressed air from a low-pressure source; a high-pressure bleed tap configured to bleed a high-pressure compressed air from a high-pressure source; an upstream duct configured to receive one or both of the low-pressure compressed air and the high-pressure compressed air; a downstream duct configured to provide a regulated compressed air to the pneumatic system; a high-pressure shutoff valve positioned between the high-pressure bleed tap and the upstream duct; a low-pressure non-return valve positioned between the low-pressure bleed tap and the upstream duct; a pressure regulating and shutoff valve positioned between the upstream duct and the downstream duct, the pressure regulating and shutoff valve configured to generate the regulated compressed air; and a pressure relief valve positioned within the upstream duct.

A power generation system includes one or more micro-turbine electric generators (“MTEGs”). The MTEGs include a housing having an inlet for receiving pressurized gas and an outlet for releasing expanded gas. The MTEGs also include a rotor, a user-replaceable nozzle for directing pressurized gas over blades of the rotor, and a stator for generating alternating current (“AC”) responsive to rotation of the rotor. The power generation system also includes a programmable logic controller (“PLC”) coupled to the MTEGs that operates flow control valves (“FCVs”) coupled to the MTEGs to modulate the flow of gas to the MTEGs to generate output power suitable to support an electrical load. The system also includes power conversion circuitry configured to convert AC generated by the MTEGs to direct current (“DC”) and to provide the DC to an electrical load. The system also includes a skid for mounting multiple and MTEGs and FCVs.

A system and method for determining performance of an engine is provided. The system includes two or more sensors configured in operable arrangement at two or more respective positions at a flowpath. The system includes one or more computing devices configured to perform operations, the operations include acquiring, via the two or more sensors, parameter sets each corresponding to two or more engine conditions different from one another, wherein each parameter set indicates a health condition at a respective location at the engine; comparing, via the computing device, the parameter sets to determine the respective health condition corresponding to the respective location at the engine; and generating, via the computing device, a health condition prediction based on the compared parameter sets.

A system and method for determining performance of a turbine engine, and operation thereof. The system and method includes a plurality of sensors and one or more computing devices executing operations including acquiring a plurality of parameter sets each corresponding to a plurality of engine conditions in which each parameter set corresponding to each engine condition indicates a health condition at a plurality of locations at the engine; comparing the plurality of parameter sets to determine a health condition corresponding to a location at the engine; and generating a health condition prediction at the engine based on the compared parameters.

A power generation system includes one or more micro-turbine electric generators (MTEGs). The MTEGs include a housing having an inlet for receiving pressurized gas and an outlet for releasing expanded gas. The MTEGs also include a rotor, a user-replaceable nozzle for directing pressurized gas over blades of the rotor, and a stator for generating alternating current (AC) responsive to rotation of the rotor. The power generation system also includes a programmable logic controller (PLC) coupled to the MTEGs that operates flow control valves (FCVs) coupled to the MTEGs to modulate the flow of gas to the MTEGs to generate output power suitable to support an electrical load. The system also includes power conversion circuitry configured to convert AC generated by the MTEGs to direct current (DC) and to provide the DC to an electrical load. The system also includes a skid for mounting multiple and MTEGs and FCVs.

A power generation system includes one or more micro-turbine electric generators (MTEGs). The MTEGs include a housing having an inlet for receiving pressurized gas and an outlet for releasing expanded gas. The MTEGs also include a rotor, a user-replaceable nozzle for directing pressurized gas over blades of the rotor, and a stator for generating alternating current (AC) responsive to rotation of the rotor. The power generation system also includes a programmable logic controller (PLC) coupled to the MTEGs that operates flow control valves (FCVs) coupled to the MTEGs to modulate the flow of gas to the MTEGs to generate output power suitable to support an electrical load. The system also includes power conversion circuitry configured to convert AC generated by the MTEGs to direct current (DC) and to provide the DC to an electrical load. The system also includes a skid for mounting multiple and MTEGs and FCVs.