Turbomachine airfoil erosion determination
a technology of airfoils and turbines, which is applied in the direction of instruments, marine propulsion, vessel construction, etc., can solve the problems of unreliable prediction, insufficient accuracy, and eroded airfoils of turbines
Inactive Publication Date: 2015-05-14
GENERAL ELECTRIC CO
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Benefits of technology
The patent aims to address certain problems that are currently being faced. The technical effects of the patent text provide solutions for these problems.
Problems solved by technology
Turbomachine airfoils erode over time in all settings in which they are used.
This approach has proven to be unreliable for prediction of overall chord loss or erosion, in part, because it is not easily repeatable, which results in inadequate accuracy.
This approach is oftentimes unworkable because manufacturing variation in certain turbomachine airfoils is too large to allow determination of erosion by measuring leading edge width.
Method used
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[0016]As indicated above, the disclosure provides for erosion determination of a turbomachine airfoil. The teachings of the invention may be applied to any variety of turbomachine airfoil including but not limited to blades or nozzles of: a compressor, gas turbine, steam turbine, jet engine, etc. In general terms, a system, method or program product according to embodiments of the invention attains a two-dimensional used profile of a leading edge at a specified radial position on a turbomachine airfoil after use, e.g., using a laser profiler. Opposing substantially straight alignment portions of the two-dimensional used profile are aligned with opposing substantially straight alignment portions of a previously attained, two-dimensional, baseline profile of the turbomachine airfoil. The alignment portions of each profile are in substantially identical radial locations of the turbomachine airfoil. A comparison of the used profile to the baseline profile then determines whether the lea...
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A system may include at least one computer device configured to attain a two-dimensional used profile of a leading edge at a specified radial position on a turbomachine airfoil after use. The system aligns opposing substantially straight alignment portions of the two-dimensional used profile with opposing substantially straight alignment portions of a previously attained, two-dimensional, baseline profile of the turbomachine airfoil. The alignment portions of each profile are in substantially identical radial locations of the turbomachine airfoil. Comparing the used profile to the baseline profile determines whether the leading edge at the specified radial position of the used turbomachine airfoil has erosion. The system may also include a laser profiler for measuring the turbomachine airfoil.
Description
BACKGROUND OF THE INVENTION[0001]The disclosure relates generally to turbomachine airfoils and, more particularly, to a method and system for turbomachine airfoil erosion determination.[0002]Turbomachine airfoils erode over time in all settings in which they are used. For example, compressor blade erosion is of concern with gas turbines operating with evaporative coolers, inlet foggers, and water wash operations.[0003]Several inspection methods for erosion on turbomachine airfoils have been attempted. In one approach, a three-dimensional scanner or optical system is used. These inspection systems require line of sight to the blade being measured, preventing an in-situ measurement. In another approach, a caliper device is used to measure the chord length of the compressor blade. Chord length is a length between a leading edge and a trailing edge of a turbomachine airfoil. A change in chord length is an indicator of erosion. In this setting, the caliper device must be positioned paral...
Claims
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IPC IPC(8): F01D21/00
CPCF01D21/003G01M5/0016G01M5/0033G01M5/0075G01B11/24
Inventor SALM, JACOB ANDREWBEACH, KELSEY ELIZABETHPISTNER, ALEXANDER JAMESTURAN, BIROL
Owner GENERAL ELECTRIC CO