Method of monitoring gas turbine engine operation
First Claim
Patent Images
1. A method of monitoring the performance of an aircraft-mounted gas turbine engine, the method comprising the steps of:
- selecting at least one engine parameter to monitor, wherein the engine parameter is indicative of a deterioration condition of the engine as the engine is operated;
selecting an engine at-limit point corresponding to the parameter;
selecting an engine warn point corresponding to the at-limit point, where the warn point is different than the at-limit point and provides an operating margin for the parameter between the warn point and the at-limit point;
monitoring the engine parameter;
determining a difference in the engine parameter between an actual value and an expected value;
adjusting a counter value based on the engine parameter actual-expected difference;
comparing the counter value to the warn point;
setting a warning flag indicative of an impending maintenance condition when the counter value meets at least a first criterion based on said comparison; and
indicating to an operator of the aircraft that the warning flag has been set.
1 Assignment
0 Petitions
Accused Products
Abstract
A system, method and apparatus for monitoring the performance of a gas turbine engine. A counter value Indicative of the comparison between the engine condition and the threshold condition is adjusted. The aircraft operator is warned of an impending maintenance condition based on the counter value and determines an appropriate course of action.
-
Citations
47 Claims
-
1. A method of monitoring the performance of an aircraft-mounted gas turbine engine, the method comprising the steps of:
-
selecting at least one engine parameter to monitor, wherein the engine parameter is indicative of a deterioration condition of the engine as the engine is operated; selecting an engine at-limit point corresponding to the parameter; selecting an engine warn point corresponding to the at-limit point, where the warn point is different than the at-limit point and provides an operating margin for the parameter between the warn point and the at-limit point; monitoring the engine parameter; determining a difference in the engine parameter between an actual value and an expected value; adjusting a counter value based on the engine parameter actual-expected difference; comparing the counter value to the warn point; setting a warning flag indicative of an impending maintenance condition when the counter value meets at least a first criterion based on said comparison; and indicating to an operator of the aircraft that the warning flag has been set. - View Dependent Claims (2, 3, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14, 15, 16, 17, 18, 19, 20)
-
-
4. The method of claim further wherein the steps of sensing and adjusting are iterated until the step of setting a warning flag is achieved.
-
21. A method of tracking the cumulative effect of ambient operating temperature on an aircraft-mounted gas turbine engine, the method comprising the steps of:
-
selecting at least one parameter to be trended, said parameter having a relationship to said effect of ambient operating temperature on a gas turbine engine; selectively comparing a measured value of the parameter with an expected value of the parameter to determine a difference therebetween and adjusting a counter based on the difference determined; and warning an operator when the counter reaches a margin limit, the margin limit selected to provide a remaining operating margin for the counter between the margin limit and a final limit the final limit associated with a maximum amount of engine deterioration permissible before a maintenance operation is required. - View Dependent Claims (22, 23, 24, 25, 26, 27, 28, 29, 30, 31, 32, 33, 34, 35, 36, 37, 38, 39, 40, 41, 42, 43, 44, 45, 46, 47)
-
Specification