Operating aircraft propulsion system during engine-inoperative event
AssigneePratt & Whitney Canada Corp.
InventorsPatrick Gates, Melanie Papillon
Life of this patent
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Abstract
A method is provided for operating an aircraft having a first propulsion unit and a second propulsion unit. During this method a propulsion unit-inoperative event is identified where the first propulsion unit is inoperative and the second propulsion unit is operative. A trimmed parameter for the second propulsion unit is converted to an actual parameter for the second propulsion unit. The actual parameter is monitored over a period of time the second propulsion unit operates during the propulsion unit-inoperative event. An action is performed in response to determining that the second propulsion unit has operated for at least a time threshold with the actual parameter being equal to or greater than a parameter threshold.
Claims18
A method of operating an aircraft having a first propulsion unit and a second propulsion unit, comprising:
- at one or more processing systems of the aircraft, identifying a propulsion unit-inoperative event where the first propulsion unit is inoperative and the second propulsion unit is operative, the first propulsion unit uniquely associated with a first dataset, the second propulsion unit uniquely associated with a second dataset that is different than the first dataset;
- at one or more of the one or more processing systems of the aircraft, converting a trimmed parameter for the second propulsion unit to an actual parameter for the second propulsion unit, the converting of the trimmed parameter to the actual parameter comprising processing the trimmed parameter using the second dataset;
- at one or more of the one or more processing systems of the aircraft, monitoring the actual parameter over a period of time the second propulsion unit operates during the propulsion unit-inoperative event;
- and
- at one or more of the one or more processing systems of the aircraft, in response to determining that the second propulsion unit has operated for at least a time threshold with the actual parameter being equal to or greater than a parameter threshold, performing an action;
- wherein the trimmed parameter for the second propulsion unit comprises a measured temperature of the second propulsion unit which is adjusted to performance match the first propulsion unit;
- and
- wherein the actual parameter is indicative of a temperature of gas flowing through the second propulsion unit and providing motive power of the second propulsion unit.
An operating method, comprising:
- identifying an event where a first propulsion unit is inoperative and a second propulsion unit is operative;
- processing a trimmed parameter to provide an actual parameter;
- monitoring the actual parameter for the second propulsion unit during the event;
- determining a period of time the actual parameter is at or above a threshold during the event;
- and
- performing an action in response to the identifying of the event based on the period of time;
- wherein the trimmed parameter comprises a measured temperature which is corrected to match performance between the first propulsion unit and the second propulsion unit;
- and
- wherein the actual parameter is indicative of a temperature of gas flowing through the second propulsion unit and providing motive power of the second propulsion unit.
An aircraft system, comprising:
- a first propulsion unit;
- a second propulsion unit;
- and
- a monitoring system configured to
- identify a propulsion unit-inoperative event where the first propulsion unit is inoperative and the second propulsion unit is operative;
- convert a trimmed parameter for the second propulsion unit to an actual parameter for the second propulsion unit;
- determine an operational characteristic of the second propulsion unit during the propulsion unit-inoperative event, the operational characteristic indicative of a period of time the second propulsion unit operates with the actual parameter equal to or greater than a threshold during the propulsion unit-inoperative event, and the operational characteristic indicative of a period of time the second propulsion unit operates with a second parameter equal to or greater than a second threshold during the propulsion unit-inoperative event;
- and
- initiate an action in response to the identifying of the propulsion unit-inoperative event based on the operational characteristic;
- wherein the trimmed parameter comprises a measured temperature which is adjusted to match performance between the first propulsion unit and the second propulsion unit;
- and
- wherein the actual parameter comprises a temperature within the second propulsion unit.
Dependencies are inferred from the claim text.