Prognostic health management approaches for propulsion control system
AssigneeRolls-Royce North American Technologies Inc.
InventorsRichard J. Skertic, Joseph D. Myer
Life of this patent
Estimating the term…
Abstract
A real-time gas turbine management system includes a controller system coupled to a gas turbine engine. The controller system is configured to control demand on a first and second component of a gas turbine engine. The controller system is configured to identify a set point reference of the first component, identify a set point reference of the second component, and identify a data set indicative of a level of deterioration of the gas turbine engine. The controller system is also configured to change the set point reference of the first component to extend a lifespan of the gas turbine engine and/or change the set point reference of the second component to extend the lifespan of the gas turbine engine.
Claims15
A real-time system, comprising:
- a controller system having a system controller with a processor, the controller system being coupled to an engine and configured to control demand on a first and second component of the engine, the controller system is configured to:
- operate the engine in a control mode associated with one of the first component and the second component;
- identify, by way of the system controller, a set point reference of the first component;
- identify, by way of the system controller, a set point reference of the second component;
- identify, by way of the system controller, a data set indicative of a level of deterioration of the engine by at least referencing at least one reference schedule that associates a state of at least one of the first component and the second component with a given thrust;
- based on the level of deterioration determine and implement a trim scheme, which includes increasing the set point reference of the first component if the control mode is a rotor speed control mode, and decreasing the set point reference of the second component if the control mode is one of an engine pressure ratio control mode and a turbine fan power ratio control mode;
- wherein the set point reference of the first component is a fan speed set point reference and the set point reference of the second component is one of an engine pressure ratio set point reference and a turbo fan power ratio set point reference.
An aircraft, comprising:
- an engine;
- and a controller system having a system controller with a processor, the controller system being coupled to an engine and configured to control demand on a first and second component of the engine, the controller system is configured to:
- operate the engine in a control mode associated with one of the first component and the second component;
- identify, by way of the system controller, a set point reference of the first component;
- identify, by way of the system controller, a set point reference of the second component;
- identify, by way of the system controller, a data set indicative of a level of deterioration of the engine by at least referencing at least one reference schedule that associates a state of at least one of the first component and the second component with a given thrust;
- and based on the level of deterioration, determine and implement a trim scheme, which includes increasing the set point reference of the first component if the control mode is a rotor speed control mode, and decreasing the set point reference of the control mode is one of an engine pressure ratio control mode and a turbine fan power ratio control mode;
- and notify a user to change the set point reference of the second component wherein the set point reference of the first component is a fan speed set point reference and the set point reference of the second component is one of an engine pressure ratio set point reference and a turbo fan power ratio set point reference.
Dependencies are inferred from the claim text.