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.
23 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