Detection of gas turbine airfoil failure

Data processing: vehicles – navigation – and relative location – Vehicle control – guidance – operation – or indication – With indicator or control of power plant

Reexamination Certificate

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C701S031000, C415S115000

Reexamination Certificate

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07412320

ABSTRACT:
A system and method for early detection of a failure of a gas turbine engine airfoil (10), such as but not restricted to a burn through of the airfoil outer skin (12). A sensor (52) provides a signal (54) responsive to a condition of fluid flowing through an outer cooling chamber (24) of the airfoil. A detected change in the condition of the fluid is correlated to a failure of the airfoil, which for example can be detected by measuring the static fluid pressure. An increase in the static pressure of fluid in the outer cooling chamber may indicate a breach in the region of the leading edge of the airfoil. A decrease in the static pressure of fluid in the outer cooling chamber may indicate a breach along other portions of the profile of the airfoil outer skin. Both pressure and temperature parameters of the fluid may be measured and coincident changes thereof correlated to a condition of failure of the airfoil.

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