Reduction of equally spaced turbine nozzle vane excitation
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United States of America Patent
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May 8, 2018
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N/A
app pub date -
Oct 23, 2012
filing date -
Oct 23, 2012
priority date (Note) -
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Abstract
A reduction in excitation amplitudes affecting turbine blade durability in a turbine nozzle assembly having a plurality of vanes and turbine blades, includes: identifying a turbine blade design of the turbine nozzle assembly; performing a modal model analysis of at least one of the turbine blades in the turbine blade design; reducing aerodynamic impact by ensuring that each of the turbine blades is free of aero-excitation from an upstream flow at the vanes in an operating speed range; identifying blade natural frequencies with respect to the nozzle vanes; and modifying a trailing edge of at least one of the vanes to reduce the excitation amplitudes.
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