Abstract: A combustion system for a vehicle having an engine includes a hydrogen fuel system having a fuel source providing a hydrogen fuel, a combustor operable to combust the hydrogen fuel to generate combustion gases, and a fuel delivery assembly operable to deliver the hydrogen fuel from the fuel source to the combustor. A first control system has a first update rate and is operable to control one or more operational aspects of the turbine engine. A second control system is in communication with the first control system and the hydrogen fuel system and has a second update rate faster than the first update rate. The second control system is operable to monitor at least one parameter associated with the hydrogen fuel system and output at least one control signal to the hydrogen fuel system to control the delivery or the combustion of the hydrogen fuel.

Abstract: Provided is a tangible computer-readable, non-transitory storage medium storing instructions that, when executed by a hardware processor of an aircraft, causes the hardware processor to execute a method. The method includes receiving, from an engine particulate sensor of the aircraft, a measure of particulate matter in a gas path of the engine during flight of the aircraft. The method also includes presenting to a pilot of the aircraft, a visualization of the particulate matter measure, wherein the visualization supports a navigation of the aircraft responsive to the presence of the particulate matter.

Abstract: A combustion system for a vehicle having an engine includes a hydrogen fuel system having a fuel source providing a hydrogen fuel, a combustor operable to combust the hydrogen fuel to generate combustion gases, and a fuel delivery assembly operable to deliver the hydrogen fuel from the fuel source to the combustor. A first control system has a first update rate and is operable to control one or more operational aspects of the turbine engine. A second control system is in communication with the first control system and the hydrogen fuel system and has a second update rate faster than the first update rate. The second control system is operable to monitor at least one parameter associated with the hydrogen fuel system and output at least one control signal to the hydrogen fuel system to control the delivery or the combustion of the hydrogen fuel.

Abstract: A system includes one or more debris sensors or particulate sensors are used to sense engine inlet debris or particulate matter which are drawn into the engine during flight, in real-time. The system employs that information, in conjunction with other engine health and module health techniques, to identify which gas-path modules of the aircraft engine may require maintenance or repair. In one embodiment, existing engine health technique may be based on various engine operational parameters for a new engine or an average engine.

Abstract: A system includes one or more debris sensors or particulate sensors are used to sense engine inlet debris or particulate matter which are drawn into the engine during flight, in real-time. The system employs that information, in conjunction with other engine health and module health techniques, to identify which gas-path modules of the aircraft engine may require maintenance or repair. In one embodiment, existing engine health technique may be based on various engine operational parameters for a new engine or an average engine.

Abstract: Provided is a tangible computer-readable, non-transitory storage medium storing instructions that, when executed by a hardware processor of an aircraft, causes the hardware processor to execute a method. The method includes receiving, from an engine particulate sensor of the aircraft, a measure of particulate matter in a gas path of the engine during flight of the aircraft. The method also includes presenting to a pilot of the aircraft, a visualization of the particulate matter measure, wherein the visualization supports a navigation of the aircraft responsive to the presence of the particulate matter.

Abstract: Systems and methods for controlling powerplants that include and/or leverage one or more health models to proactively optimize component life or minimize damage of one or more components of the powerplant are provided. In one exemplary aspect, a control system for a powerplant feeds engine data into one or more health models. The health models output health data indicative of a condition of one or more components of the powerplant. The control system utilizes the health data outputs to proactively control the components of the powerplant in such a way so as to optimize component life/damage.

Abstract: Systems and methods are provided that include features for determining a hover time remaining for an aircraft performing a hover maneuver. In some exemplary embodiments, the hover time remaining can be communicated to a pilot or aircrew member.

Abstract: A method for determining an engine heath of an aircraft engine includes determining, by one or more control devices, the aircraft engine is operating in a bleed off condition; determining, by the one or more control devices, a first engine health modifier value while the aircraft engine is operating in the bleed off condition, the first of engine health modifier value including a compressor leakage flow value; determining, by the one or more control devices, a second plurality of engine health modifier values while the aircraft engine is operating in a bleed on condition; and determining, by the one or more control devices, an engine health parameter using at least one of the second plurality of engine health modifier values determined while the aircraft engine is operating in the bleed on condition and the compressor leakage flow value determined while the aircraft engine was operating in the bleed off condition.

Abstract: A method for determining an engine heath of an aircraft engine includes determining, by one or more control devices, the aircraft engine is operating in a bleed off condition; determining, by the one or more control devices, a first engine health modifier value while the aircraft engine is operating in the bleed off condition, the first of engine health modifier value including a compressor leakage flow value; determining, by the one or more control devices, a second plurality of engine health modifier values while the aircraft engine is operating in a bleed on condition; and determining, by the one or more control devices, an engine health parameter using at least one of the second plurality of engine health modifier values determined while the aircraft engine is operating in the bleed on condition and the compressor leakage flow value determined while the aircraft engine was operating in the bleed off condition.

Abstract: Systems and methods for controlling powerplants that include and/or leverage one or more health models to proactively optimize component life or minimize damage of one or more components of the powerplant are provided. In one exemplary aspect, a control system for a powerplant feeds engine data into one or more health models. The health models output health data indicative of a condition of one or more components of the powerplant. The control system utilizes the health data outputs to proactively control the components of the powerplant in such a way so as to optimize component life/damage.

Abstract: Systems and methods are provided that include features for determining a hover time remaining for an aircraft performing a hover maneuver. In some exemplary embodiments, the hover time remaining can be communicated to a pilot or aircrew member.

Abstract: Systems and methods for modelling an engine in a vehicle are provided. A method can include determining a first solver for modelling the engine. The first solver can include a first routine configured for determining one or more parameters of the engine. The method can further include obtaining a first set of inputs associated with the first solver. The first set of inputs can include one or more inputs obtained from the first solver and one or more previous engine states. The method can further include modelling the engine based at least in part on the first set of inputs to generate a first set of outputs. The first set of outputs can include one or more parameters of the engine and one or more engine states. The method can further include providing the one or more parameters to the solver.

Abstract: Systems and methods for modelling an engine in a vehicle are provided. A method can include determining a first solver for modelling the engine. The first solver can include a first routine configured for determining one or more parameters of the engine. The method can further include obtaining a first set of inputs associated with the first solver. The first set of inputs can include one or more inputs obtained from the first solver and one or more previous engine states. The method can further include modelling the engine based at least in part on the first set of inputs to generate a first set of outputs. The first set of outputs can include one or more parameters of the engine and one or more engine states. The method can further include providing the one or more parameters to the solver.

Abstract: Systems and methods for determining torque split among engines in a multi-engine system using adaptive engine models are provided. In one embodiment, a method of determining a torque split can include generating a first model specifying torque versus fuel flow for a first engine based at least in part on measured operating points for the first engine; and generating a second model specifying torque versus fuel flow for a second engine based at least in part on measured operating points for the second engine. The method can further include determining a torque split for the first engine and the second engine that reduces total fuel flow for the first engine and the second engine based at least in part on the first model and the second model; and controlling the torque output of the first engine and the second engine based at least in part on the torque split.