Method and apparatus for determining engine part life usage
First Claim
1. A method for determining an engine part life usage of a gas turbine engine life limited part used on an aircraft, said method comprising:
- operating a gas turbine engine that includes a plurality of rotating components and a plurality of sensors configured to monitor a plurality of gas turbine engine operating parameters;
continuously sampling the plurality of sensors during each flight using an engine control system coupled to the gas turbine engine;
obtaining outputs from the plurality of sensors;
sorting the sensor outputs based on predefined events using the engine control system;
transmitting at least some of the sorted sensor outputs to a remote server for viewing by at least one customer; and
utilizing the at least some of the sorted outputs to calculate the life usage of at least one life limited part to facilitate tracking the life-usage of an individual life limited part on the gas turbine engine that is consumed on a flight by flight basis.
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Abstract
A method for determining an engine part life usage of a gas turbine engine life limited part used on an aircraft. The method includes operating a gas turbine engine that includes a plurality of rotating components and a plurality of sensors configured to monitor a plurality of gas turbine engine operating parameters, obtaining outputs from the plurality of sensors, and utilizing at least some of the outputs to calculate the life usage of at least one life limited part to facilitate tracking the life-usage of an individual life limited part on the gas turbine engine that is consumed on a flight by flight basis.
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Citations
20 Claims
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1. A method for determining an engine part life usage of a gas turbine engine life limited part used on an aircraft, said method comprising:
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operating a gas turbine engine that includes a plurality of rotating components and a plurality of sensors configured to monitor a plurality of gas turbine engine operating parameters; continuously sampling the plurality of sensors during each flight using an engine control system coupled to the gas turbine engine; obtaining outputs from the plurality of sensors; sorting the sensor outputs based on predefined events using the engine control system; transmitting at least some of the sorted sensor outputs to a remote server for viewing by at least one customer; and utilizing the at least some of the sorted outputs to calculate the life usage of at least one life limited part to facilitate tracking the life-usage of an individual life limited part on the gas turbine engine that is consumed on a flight by flight basis. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10)
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11. A control system coupled to a gas turbine engine, wherein the gas turbine engine includes a plurality of life limited parts, and a plurality of sensors configured to monitor a plurality of gas turbine engine operating parameters, said control system is configured to:
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operate the gas turbine engine; continuously sample the plurality of sensors during each flight using said control system coupled to the gas turbine engine; obtain outputs from the plurality of sensors; sort the sensors outputs based on predefined events using said control system; transmit at least some of the sorted sensor outputs to a remote server for viewing by at least one customer; and utilize the at least some of the sorted outputs to calculate the life usage of at least one of said life limited parts to facilitate tracking the life-usage of an individual life limited part on the gas turbine engine that is consumed on a flight by flight basis. - View Dependent Claims (12, 13, 14, 15, 16, 17, 18, 19, 20)
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Specification