Process and methodology for root cause identification in gas turbine engine performance tracking
First Claim
Patent Images
1. A performance tracking method for narrowing an assessment of root cause RC to a single turbine or compressor stage, or a combination of stages within at least one gas turbine engine module comprising:
- inputting engine gas path measurement data from a gas turbine engine module;
performing a gas path analysis on the gas path measurement data to derive % Δ
performance vectors;
calculating estimated module efficiency {circumflex over (η
)} and flow parameter F{circumflex over (P)} deltas (Δ
'"'"'s) for each % Δ
performance vector;
calculating a coupling ratio Δ
C{circumflex over (R)} for each % Δ
performance vector;
calculating a variability for each coupling ratio Δ
C{circumflex over (R)};
calculating a level-of-belief lob(x,RCi) for each coupling ratio Δ
C{circumflex over (R)} and each root cause RCi;
calculating a confidence level for each module RCk;
selecting a module root cause RC having a maximum confidence level; and
determining from said selected module root cause having said maximum confidence level a single turbine or compressor rotor or a combination of turbine or compressor stages in said at least one gas turbine engine module having deterioration issues.
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Abstract
A system and method for narrowing an assessment of root cause to a single stage within a gas turbine engine module using coupling factors and known instrumentation non-repeatability. Embodiments examine certain root cause (RC) effects that manifest themselves as coupling levels, or ratios (CR), between an engine module'"'"'s efficiency change Δη and its flow parameter change ΔFP.
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Citations
7 Claims
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1. A performance tracking method for narrowing an assessment of root cause RC to a single turbine or compressor stage, or a combination of stages within at least one gas turbine engine module comprising:
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inputting engine gas path measurement data from a gas turbine engine module; performing a gas path analysis on the gas path measurement data to derive % Δ
performance vectors;calculating estimated module efficiency {circumflex over (η
)} and flow parameter F{circumflex over (P)} deltas (Δ
'"'"'s) for each % Δ
performance vector;calculating a coupling ratio Δ
C{circumflex over (R)} for each % Δ
performance vector;calculating a variability for each coupling ratio Δ
C{circumflex over (R)};calculating a level-of-belief lob(x,RCi) for each coupling ratio Δ
C{circumflex over (R)} and each root cause RCi;calculating a confidence level for each module RCk; selecting a module root cause RC having a maximum confidence level; and determining from said selected module root cause having said maximum confidence level a single turbine or compressor rotor or a combination of turbine or compressor stages in said at least one gas turbine engine module having deterioration issues. - View Dependent Claims (2, 3, 4, 5, 6, 7)
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Specification