System and method for real-time detection of gas turbine or aircraft engine blade problems
First Claim
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1. A gas turbine or aircraft engine bucket failure mode detection system configured to identify changes between measured relative or absolute bucket temperatures and baseline temperatures.
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Abstract
A method and system are implemented to detect gas turbine blade problems in real time and provide more accurate prediction capabilities than known techniques due to inclusion of physics-based correction and temperature modeling methods for the hot gas path parts lifing. The system and method use pyrometer data and operational data to generate physics-based corrections of pyrometer data and physics-based bucket temperature estimations and failure signatures.
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Citations
21 Claims
- 1. A gas turbine or aircraft engine bucket failure mode detection system configured to identify changes between measured relative or absolute bucket temperatures and baseline temperatures.
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10. A gas turbine or aircraft engine bucket failure mode detection system comprising:
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a first pyrometer and at least one on-site monitor configured together to generate gas turbine or aircraft engine operational parameters; a first model based filter configured to reduce variations in pyrometer signals based on variations in the operational parameters and to generate a first corrected pyrometer signal therefrom; a first physics-based signal processor configured to generate a normalized gas turbine or aircraft engine bucket temperature signature in response to the corrected pyrometer signal; a bucket failure mode signature database; and a first comparator configured to compare the normalized gas turbine or aircraft engine bucket temperature signature with bucket failure mode signature data within the database to identify a failure mode associated with a failed bucket. - View Dependent Claims (11, 12, 13, 14, 15)
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16. A method for detecting gas turbine or aircraft engine bucket failure modes, the method comprising:
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monitoring gas turbine or aircraft engine bucket operational parameters in real-time via a pyrometer and at least one on-site monitor; filtering pyrometer signals based on variations in the operational parameters and generating a corrected pyrometer signal therefrom; generating a normalized gas turbine or aircraft engine bucket temperature signature in response to the corrected pyrometer signal; generating a bucket failure mode signature database offline; and comparing the normalized gas turbine or aircraft engine bucket temperature signature with bucket failure mode signature data within the database to identify a failure mode associated with a failed bucket. - View Dependent Claims (17, 18, 19, 20, 21)
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Specification