Detecting gas or fuel leaks in a gas turbine engine
AssigneePratt & Whitney Canada Corp.
InventorsSafi Nizami, Andrew Roach
Life of this patent
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Abstract
An aircraft engine diagnostic system includes at least one sensor and a diagnostic controller. The at least one sensor measures a parameter of a gas turbine engine. The diagnostic controller is in signal communication with the at least one sensor. The diagnostic controller determines an actual thrust output of the gas turbine engine and an execution of at least one control system limiter configured to limit control of the gas turbine engine based on the measured parameter. The diagnostic controller further determines an existence of an engine fault based on the actual thrust output of the gas turbine engine and an execution of the at least one control system limiter.
Claims18
An aircraft engine diagnostic system comprising:
- at least one sensor configured to measure a parameter of a gas turbine engine;
- and
- a diagnostic controller in signal communication with the at least one sensor, the diagnostic controller configured to determine an actual thrust output of the gas turbine engine and an execution of at least one control system limiter configured to control the fuel flow to the engine so to limit control of the gas turbine engine based on the measured parameter,
- wherein the diagnostic controller is a closed loop controller configured to determine a persistent operation of the at least one control system limiter in response to the execution time exceeding the time period threshold, and
- wherein the diagnostic controller determines an existence of an engine fault based on the actual thrust output of the gas turbine engine and an execution of the at least one control system limiter, in response to detecting the persistent operation of the at least one control system limiter and the actual thrust output failing to meet a target thrust parameter.
A method of determining an engine fault, the method comprising:
- measuring a parameter of a gas turbine engine using at least one sensor;
- and
- determining, by a diagnostic controller, an actual thrust output of the gas turbine engine;
- controlling a fuel flow to the gas turbine engine based on an execution of at least one system limiter;
- determining, by the diagnostic controller, the execution of the at least one control system limiter configured to limit control of the gas turbine engine based on the measured parameter,
- determining, by the diagnostic controller, an existence of an engine fault based on the actual thrust output of the gas turbine engine and an execution of the at least one control system limiter, following a persistent operation of the at least one control system limiter that is detected in response to the execution time of the at least one control system limiter exceeding the time period threshold and the actual thrust output failing to meet a target thrust parameter.
Dependencies are inferred from the claim text.