Abstract: A power event manager controller for a gas turbine engine power system, the gas turbine engine power system comprising at least one gas turbine engine, a thermal management system and at least one of a generator, an energy storage system, the power event manager controller receiving an input power demand, and receiving input relating to the mission plan, and inputs from each of the systems within the gas turbine engine power system, based upon the inputs from the from the power demand and the mission plan the power event controller defines a series of constraints, and wherein the power event manager controller utilises an optimiser function to obtain control reference trajectories which minimise an objective cost function of modelled states, whilst being subject to the series of constraints.

Abstract: The present disclosure relates to an apparatus (e.g., a data processing apparatus) for planning a route of a vehicle. The apparatus is configured to: determine a trajectory solution TS1, TS2 for the vehicle based on: one or more objective parameters; at least one scenario SN, S1, S2 defined by one or more constraint parameters relating to the vehicle and/or to a journey the vehicle is to make; and at least one situation N, ET, ER which the vehicle could experience while making the journey. The present disclosure also relates to a computer-implemented method for planning a route of a vehicle.

Abstract: A method of controlling a vapour-compression system for circulating a working fluid. The vapour-compression system comprises a compressor, an expansion device and an evaporator configured to facilitate heat transfer from a thermal source into the working fluid. The method comprises: determining or receiving a cooling demand, the cooling demand being associated with a demand to cool the thermal source; determining a preliminary thermofluidic property objective value based on the cooling demand; determining a final thermofluidic property objective value based on the preliminary thermofluidic property objective value and one or more thermofluidic property objective value thresholds, wherein the final thermofluidic property objective value relates to a target thermofluidic property of the working fluid at a control location within the vapour-compression system; and controlling at least one of the compressor and the expansion device based on the final thermofluidic property objective value.

Abstract: Disclosed is a computer-implemented method for controlling an engine system of a vehicle comprising: determining an operating condition of the vehicle; determining one or more contextual conditions relevant to the vehicle; selecting, based upon both the determined operating condition and the determined one or more contextual conditions, a control profile for the engine system from a directory comprising a plurality of control profiles having different control characteristics; applying the selected control profile to a controller of the engine system; and controlling the engine system with the controller in accordance with the selected control profile. Also disclosed are an engine control system, a gas turbine engine, and an aircraft.

Abstract: There is disclosed a gas turbine engine comprising: an electrically-powered motor configured to rotate a driven spool of the gas turbine engine; a primary controller configured to conduct a primary function using the motor; and a bow controller configured to selectively control the motor to perform a rotor bow mitigation operation in which the motor drives the driven spool to rotate to mitigate a non-uniform thermal distribution in a rotor of a spool of the gas turbine engine.

Abstract: There is provided a method of starting a gas turbine engine, comprising: selecting a baseline starting procedure of the gas turbine engine based on environmental data; receiving condition information for the gas turbine engine and/or for a starting system of the gas turbine engine, the condition information comprising at least one of: health information for the gas turbine engine and/or the starting system; maintenance information for the gas turbine engine and/or the starting system; and operation information relating to an expected future usage of the gas turbine engine. The method further comprises determining a predicted degradation profile for the gas turbine engine and/or the starting system based on the condition information; determining a starting procedure of the gas turbine engine by adapting the baseline starting procedure based on the predicted degradation profile; and controlling the gas turbine engine and/or the starting system according to the determined starting procedure.

Abstract: There is provided a method of starting a gas turbine engine, comprising: selecting a baseline starting procedure of the gas turbine engine based on environmental data; receiving condition information for the gas turbine engine and/or for a starting system of the gas turbine engine, the condition information comprising at least one of: health information for the gas turbine engine and/or the starting system; maintenance information for the gas turbine engine and/or the starting system; and operation information relating to an expected future usage of the gas turbine engine. The method further comprises determining a predicted degradation profile for the gas turbine engine and/or the starting system based on the condition information; determining a starting procedure of the gas turbine engine by adapting the baseline starting procedure based on the predicted degradation profile; and controlling the gas turbine engine and/or the starting system according to the determined starting procedure.

Abstract: A method of operating a gas turbine engine having a spool includes executing, by a controller, a shutdown procedure. The shutdown procedure includes: performing an idle rotation operation; determining a parameter associated with a thermal condition of the gas turbine engine while the idle rotation operation is performed; determining, based on the determined parameter, whether the gas turbine engine has met a pre-determined criterion corresponding to a thermally stabilised condition; and terminating the idle rotation operation in response to a determination that the gas turbine engine has met the pre-determined criterion.

Abstract: A method of operating a gas turbine engine having a spool includes executing, by a controller, a pre-shutdown procedure. The pre-shutdown procedure includes: determining a parameter associated with a thermal condition of the gas turbine engine; and calculating an idle period for an idle rotation operation to be performed in a shutdown procedure. Calculation of the idle period is based on the determined parameter.

Abstract: There is provided a method of starting a gas turbine engine, comprising: selecting a baseline starting procedure of the gas turbine engine based on environmental data; receiving condition information for the gas turbine engine and/or for a starting system of the gas turbine engine, the condition information comprising at least one of: health information for the gas turbine engine and/or the starting system; maintenance information for the gas turbine engine and/or the starting system; and operation information relating to an expected future usage of the gas turbine engine. The method further comprises determining a predicted degradation profile for the gas turbine engine and/or the starting system based on the condition information; determining a starting procedure of the gas turbine engine by adapting the baseline starting procedure based on the predicted degradation profile; and controlling the gas turbine engine and/or the starting system according to the determined starting procedure.

Abstract: There is disclosed a gas turbine engine comprising: an electrically-powered motor configured to rotate a driven spool of the gas turbine engine; a primary controller configured to conduct a primary function using the motor; and a bow controller configured to selectively control the motor to perform a rotor bow mitigation operation in which the motor drives the driven spool to rotate to mitigate a non-uniform thermal distribution in a rotor of a spool of the gas turbine engine.

Abstract: Described herein is a method of monitoring a condition of a component of a gas turbine engine, comprising: obtaining, with a non-contact monitoring sensor, monitoring data, wherein a portion of the monitoring data relates to the condition of the component of the gas turbine engine; obtaining, using a position sensor, positional data relating to the component's position; communicating the monitoring data and the positional data to a processing module, and analysing, using the processing module, the monitoring data and positional data to determine the portion of the monitoring data which relates to the component and determine a condition of the component. Also described herein is a system for monitoring and a gas turbine engine comprising the system.

Abstract: Disclosed is a computer-implemented method for controlling an engine system of a vehicle comprising: determining an operating condition of the vehicle; determining one or more contextual conditions relevant to the vehicle; selecting, based upon both the determined operating condition and the determined one or more contextual conditions, a control profile for the engine system from a directory comprising a plurality of control profiles having different control characteristics; applying the selected control profile to a controller of the engine system; and controlling the engine system with the controller in accordance with the selected control profile. Also disclosed are an engine control system, a gas turbine engine, and an aircraft.

Abstract: A computer-implemented method of enabling optimisation of trajectory for a vehicle, the method comprising: determining a trajectory for the vehicle using: an algorithm; a vehicle model defining path constraints for the vehicle through space; a propulsion system model defining parameters of a propulsion system of the vehicle; an objective function defining one or more objectives; and controlling output of the determined trajectory.

Abstract: A computer-implemented method of enabling optimisation of derate for a propulsion system of a vehicle, the method comprising: determining a derate for the propulsion system of the vehicle using: an algorithm; a vehicle model defining path constraints for the vehicle through space; a propulsion system model defining parameters of the propulsion system; an objective function defining one or more objectives; and controlling output of the determined derate.

Abstract: A control system of a gas turbine engine is provided. The engine has a fuel flow metering valve which regulates a fuel flow to the engine, and one or more variable geometry components which are movable between different set points to vary an operating configuration of the engine. The control system has an engine fuel control sub-system which provides a fuel flow demand signal for controlling the fuel flow metering valve. The control system further has a variable geometry control sub-system which determines current set points to be adopted by the variable geometry components given the current engine operating condition in order to comply with one or more engine constraints. The control system further has an optimiser that receives the current set points and determines adjusted values of the set points which optimise, while complying with the engine constraints, an objective function modelling a performance characteristic of the engine, the objective function adapting to change in engine performance with time.

Abstract: A computer-implemented method of optimizing the performance of a reconfigurable power system is provided. The method comprises the steps of: receiving an operating profile for the power system; partitioning the operating profile into a plurality of sub-phases; performing a coarse optimisation routine of the power system over each sub-phase of the operating profile to derive a respective coarsely optimised configuration of the power system; performing a fine optimisation routine of each coarsely optimised configuration over its respective sub-phase of the operating profile to derive a respective finely optimised configuration for that sub-phase; and defining settings of the power system to implement the finely optimised configurations thereon.

Abstract: A method of optimizing the operation of a gas turbine engine is provided. The method comprises the steps of: (a) measuring respective values for plural control actuator settings within the gas turbine engine; (b) deriving, based on data external to the operation of the gas turbine engine, a desired performance modification of the gas turbine engine; (c) determining, based on the measured control actuator settings, one or more respective trim signals for varying selected of the control actuator settings to achieve the desired performance modification; and (d) transmitting the trim signals to an electronic controller of the engine to vary the selected control actuator settings accordingly.

Abstract: A method of optimising the performance of a machine that comprises an element, comprises the steps of: (a) receiving operational data, the operational data being representative of an operational state of the machine; (b) transmitting an adjustment signal to the element to change the operational state of the element from a first state to a second state, the predetermined second state being dependent on the operational state of the machine; (c) generating an optimising action by processing the operational data, a history of previous operational states of the machine, a history of previous adjustment signals, and a sequence of previously applied optimising actions; and (d) applying the optimising action to the machine to optimise the performance of the machine.

Abstract: A payload deployment system includes a mount for receiving one or more payload modules that each include one or more payloads to be deployed. The payload modules also each include a sleeve, with the one or more payloads are in one or more openings in the sleeve. The payloads may be contained in respective containers, such as hermetically-sealed containers, that are in the openings. The electrical coupling may be wireless coupling, for transferring electrical power to the payload module(s), and for communication, such as networked communication, between the mount and the one or more payload modules. The wireless coupling may be inductive coupling that involves overlap of inductive elements such as wire coils. The payload deployment system may also include one or more translators for translating commands and/or other communications between the one or more payload modules and a platform to which the payload deployment system is coupled.