Detection of gas turbine airfoil failure
AssigneeSiemens Power Generation, Inc.
InventorHans-Gerd Johann Brummel
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AssigneeSiemens Power Generation, Inc.
InventorHans-Gerd Johann Brummel
Estimating the term…
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.
A method of detecting a failure of an airfoil of a gas turbine engine, the airfoil comprising an outer skin having an outer surface defining an airfoil shape and an inner surface, an impingement structure spaced from the inner surface to define an outer cooling chamber between the inner surface and the impingement structure and an inner cooling chamber, and impingement holes in the impingement structure for directing a cooling fluid from the inner cooling chamber into the outer cooling chamber and against the outer skin inner surface, the method comprising:
An apparatus for detecting a failure of an airfoil of a gas turbine engine, the airfoil comprising an outer skin having an outer surface defining an airfoil shape and an inner surface, an impingement structure spaced from the inner surface to define an outer cooling chamber between the inner surface and the impingement structure and an inner cooling chamber, and impingement holes in the impingement structure for directing a cooling fluid front the inner cooling chamber into the outer cooling chamber and against the outer skin inner surface, the apparatus comprising:
A vane monitoring system for a gas turbine engine comprising:
Dependencies are inferred from the claim text.