Abstract: An example apparatus includes a parameter calculator to determine a baseline value of a set of health parameters for a turbine engine of a vehicle based on a first set of sensor measurements to estimate an initial health of turbine engine components, and determine an operational value of the set of health parameters based on a second set of sensor measurements to estimate an operational health of the turbine engine components. The apparatus further includes a difference calculator to calculate a difference between the baseline value and the operational value to assess a health of the turbine engine, a database to store the first set of sensor measurements or the initial health of the turbine engine components, and an alert generator to generate an alert when the difference satisfies a threshold, the alert including a notification to perform maintenance on the component based on the difference and the threshold.

Abstract: 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.

Abstract: Systems and methods for estimating engine and electrical machine health are provided. The systems and methods therefore include features that provide for improved health estimates of one or more engines and/or electrical machines of one or more engines having an electrical machine embedded therein or coupled thereto. In particular, the systems and methods therefore include features for utilizing sensed or measured operating parameters of the electrical machines and/or operating parameters of the prime mover to estimate the health of the prime mover and/or the electrical machines embedded therein or coupled thereto.

Abstract: Systems and methods for adjusting an operating parameter of a machine based on an operating state of a component of the machine are provided. A method may be implemented by an electronic control unit (ECU) of the machine and includes determining that a performance of the machine has degraded. The method further includes selecting a predetermined adjustment to the operating parameter, wherein the selected predetermined adjustment reduces an effect of the operating state of the component on the performance of the machine, and operating the machine using the selected predetermined adjustment to the operating parameter.

Abstract: A combustion engine includes a combustion section; a fuel delivery system for providing a fuel flow to the combustion section, the fuel delivery system including an oxygen reduction unit for reducing an oxygen content of the fuel flow; a thermal management system including a heat sink heat exchanger, the heat sink heat exchanger in thermal communication with the fuel delivery system at a location downstream of the oxygen reduction unit; and a control system including a sensor operable with the fuel delivery system for sensing data indicative of an operability of the oxygen reduction unit and a controller operable with the sensor, the controller configured to initiate a corrective action based on the data sensed by the sensor indicative of the operability of the oxygen reduction unit.

Abstract: A pipe fault detection system is provided for a gas turbine engine having a compressor and a turbine. The pipe fault detection system includes a cooling manifold configured to direct cooling air from the compressor to the turbine. The cooling manifold includes at least two cooling pipes, a sensor configured to detect an operating condition indicative of a pipe break, and a controller configured to control the amount of cooling air through the cooling manifold in response to the operating condition detected by the sensor.

Abstract: A method of operating a hybrid-electric propulsion system for an aircraft includes determining a flight phase parameter for the aircraft is equal to a first value, and operating the hybrid-electric propulsion system in an electric charge mode in response to determining the flight phase parameter for the aircraft is equal to the first value. The method also includes determining the flight phase parameter for the aircraft is equal to a second value different from the first value, and operating the hybrid-electric propulsion system in an electric discharge mode in response to determining the flight phase parameter for the aircraft is equal to the second value.

Abstract: Systems and methods for estimating engine and electrical machine health are provided. The systems and methods therefore include features that provide for improved health estimates of one or more engines and/or electrical machines of one or more engines having an electrical machine embedded therein or coupled thereto. In particular, the systems and methods therefore include features for utilizing sensed or measured operating parameters of the electrical machines and/or operating parameters of the prime mover to estimate the health of the prime mover and/or the electrical machines embedded therein or coupled thereto.

Abstract: A computer-implemented method of assessing a health of a gas turbine engine of a hybrid-electric propulsion system for an aircraft includes receiving, by one or more computing devices, data indicative of an amount of electrical power provided to, or extracted from, an electric machine. The method also includes receiving, by the one or more computing devices, data indicative of an operating parameter of the hybrid-electric propulsion system. The method also includes assessing, by the one or more computing devices, a health of the gas turbine engine based at least in part on the received data indicative of the amount of electrical power provided to, or extracted from, the electric machine and the received data indicative of the operating parameter of the hybrid electric propulsion system. The method also includes providing, by the one or more computing devices, information to a user indicative of the health of the gas turbine engine.

Abstract: A hybrid-electric propulsion system for an aircraft includes a turbomachine, the turbomachine including a first spool and a second spool. A method for operating the hybrid electric propulsion system includes operating, by one or more computing devices, the turbomachine such that the first spool mechanically drives a prime propulsor of the hybrid-electric propulsion system; and modifying, by the one or more computing devices, a speed relationship parameter defined between the first spool and second spool by providing electrical power to, or drawing electrical power from, an electric machine mechanically coupled to the first spool, the second spool, or both.

Abstract: Generation of models in real time embedded systems that approximate non-embedded models while reducing a complexity associated with the non-embedded models is provided herein. A system can comprise a memory coupled to a processor. The memory stores executable components executed by the processor. The executable components can comprise an evaluation manager component that identifies an input parameter of a first model based on a defined output parameter of the first model and a relation manager component that determines one or more relations in the first model. Relations of the one or more relations can comprise an intermediary parameter determined based on the input parameter and the defined output parameter of the first model. Further, the system can comprise a model generator manager component that generates a second model that approximates the first model and includes a replication of the one or more relations of the first model.

Abstract: The present disclosure is directed to a method of control of a gas turbine engine comprising a fan section coupled to a low turbine together defining a low spool, an intermediate compressor coupled to an intermediate turbine together defining an intermediate spool, and a high compressor coupled to a high turbine together defining a high spool. The method includes providing an intermediate spool speed to low spool speed characteristic curve to a controller; providing a commanded power output to the controller; providing one or more of an environmental condition to the controller; determining, via the controller, a commanded fuel flow rate; determining, via the controller, a commanded intermediate compressor loading; and generating an actual power output of the engine, wherein the actual power output is one or more of an actual low spool speed, an actual intermediate spool speed, an actual high spool speed, and an actual engine pressure ratio.

Abstract: A system and method for determining leakage in a fluid supply line assembly are provided. The system includes a source of pressurized fluid, a pressurized fluid load, and a fluid supply line coupled to the source and the load. The leak detection system also includes a source isolation valve configured to control a flow of fluid into the fluid supply line from the source, a load isolation valve configured to control a flow of fluid from the fluid supply line to the pressurized fluid load, and a processor communicatively coupled to a memory device. The memory device includes instructions that when executed by the processor, cause the processor to close the load isolation valve and open the source isolation valve to supply pressurized fluid to the fluid supply line, and after a predetermined interval, determine a leakage of pressurized fluid from the fluid supply line.

Abstract: A compressor water-wash advisory system generates compressor water-wash notifications or initiates on-line water-wash cycles for a gas turbine or turbofan jet engine based on monitored health parameters of the engine. A high-fidelity model of engine compressor performance defines nominal expected values of engine performance parameters, such as compressor efficiency and air flow, as a function of current operating conditions. A tracking filter component compares the modeled performance parameters with actual calculated performance parameters obtained from sensor data, and maintains a separate actual model of engine performance that modifies the nominal performance parameter values to match the calculated parameter values using parameter modifiers. A health index is derived as a function of the parameter modifiers, and a water-wash notification is generated when the health index is indicative of a significant loss of fuel efficiency due to dirt accumulation in the engine's compressor.

Abstract: Systems and methods for enhancing engine performance based on atmospheric ice particles are provided. For example, a method can include selecting one or more points along a flight path of an aircraft and receiving a reflectivity measurement for each of the one or more points obtained using a device located on the aircraft. The method can further include determining an estimate of ice water content for each of the one or more points based at least in part on the reflectivity measurements; and controlling at least one component of the aircraft engine (e.g., a variable bleed valve) based at least in part on the estimate of ice water content for at least one of the plurality of points.

Abstract: Methods, apparatus, and articles of manufacture to monitor health information of a turbine engine are disclosed. An example apparatus includes a parameter calculator to determine a baseline value of a set of health parameters for a turbine engine of a vehicle based on a first set of sensor measurements to estimate an initial health of turbine engine components, and determine an operational value of the set of health parameters based on a second set of sensor measurements to estimate an operational health of the turbine engine components.

Abstract: Systems and methods for adjusting an operating parameter of a machine based on an operating state of a component of the machine are provided. A method may be implemented by an electronic control unit (ECU) of the machine and includes determining that a performance of the machine has degraded. The method further includes selecting a predetermined adjustment to the operating parameter, wherein the selected predetermined adjustment reduces an effect of the operating state of the component on the performance of the machine, and operating the machine using the selected predetermined adjustment to the operating parameter.

Abstract: Systems and methods for stabilizing an aircraft in response to a yaw movement are provided. In one embodiment, a method includes detecting a yaw movement of the aircraft. The yaw movement can cause a front portion of the aircraft to move towards a first side of the aircraft. The method can further include, in response to the yaw movement, initiating a trim process resulting in a thrust differential. The trim process can include increasing thrust in one or more engines on the first side of the aircraft and decreasing thrust in one or more engines on a second side of the aircraft. The method can include controlling the trim process based at least in part on a detected yaw movement of the aircraft.

Abstract: Systems and methods for enhancing engine performance based on atmospheric rain conditions are provided. For example, a method can include selecting one or more points along a flight path of an aircraft and receiving a radar reflectivity measurement for each of the one or more points obtained using a radar device located on the aircraft. The method can further include determining an estimate of liquid water content for each of the one or more points based at least in part on the radar reflectivity measurements; and controlling at least one component of the aircraft engine (e.g., a variable stator vane) based at least in part on the estimate of liquid water content for at least one of the plurality of points.

Abstract: Systems and methods for enhancing aircraft performance are provided. In one example, a method can include accessing an initial model that defines operating cost of an aircraft at a series of model operating states. The method also can include identifying one or more sample operating states for analyzing aircraft cost during flight. The method also can include receiving one or more real-time flight performance parameters indicative of aircraft operating cost while the aircraft is operating at the identified sample operating states. The method also can include generating an updated model that defines operating cost of the aircraft using the initial model as well as data defined by the real-time flight performance parameters. The method also can include determining an enhanced operating state based at least in part on the updated model and outputting the enhanced operating state for control of the aircraft.