Optical measurement system for detecting turbine blade lockup
AssigneeSiemens Energy, Inc.
InventorsForrest R. Ruhge, Clifford Hatcher, Jr.
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AssigneeSiemens Energy, Inc.
InventorsForrest R. Ruhge, Clifford Hatcher, Jr.
Estimating the term…
An optical measurement system for detecting at least one locked blade assembly in a gas turbine. The system includes at least one light source for emitting light that impinges on a blade surface of each blade in a row of blade assemblies. The system also includes a video device for imaging the blades as the blades rotate about the center axis. Further, the system includes a controller for controlling operation of the light source and video device. The controller detects a pixel intensity associated with each blade and a spacing between each pixel intensity wherein a change in spacing between consecutive pixel intensities indicates that a distance between consecutive blades has changed relative to the first distance thereby indicating at least one locked blade assembly.
An optical measurement system for detecting at least one locked blade assembly that becomes locked during a turning gear operation for a gas turbine wherein the gas turbine includes a plurality of blade assemblies arranged in rows about a center axis wherein each blade assembly includes a blade and wherein adjacent blades in a row are separated by a first distance forming a space between adjacent blades to orient each blade in a first position, comprising:
A method for detecting at least one locked blade assembly that becomes locked during a turning gear operation for a gas turbine wherein the gas turbine includes a plurality of blade assemblies arranged in rows about a center axis wherein each blade assembly includes a blade and wherein adjacent blades in a row are separated by a first distance forming a space between adjacent blades to orient each blade in a first position, comprising:
A method for detecting at least one locked blade assembly that becomes locked during a turning gear operation for a gas turbine wherein the gas turbine includes a plurality of blade assemblies arranged in rows about a center axis wherein each blade assembly includes a blade and wherein adjacent blades in a row are separated by a first distance forming a space between adjacent blades to orient each blade in a first position, comprising:
Dependencies are inferred from the claim text.