Reduction of equally spaced turbine nozzle vane excitation

Method for reducing excitation amplitudes affecting turbine blade durability in a turbine nozzle assembly having a plurality of vanes and turbine blades, comprising the steps of:

• identifying a turbine blade design of said turbine nozzle assembly;
• performing a modal model analysis of at least one of said turbine blades in said turbine blade design using a computer;
• reducing aerodynamic impact by ensuring that each of said turbine blades is free of aero-excitation from an upstream flow at said vanes in an operating speed range;
• identifying blade natural frequencies with respect to said nozzle vanes using said computer;
• and
• determining at least one modification to a trailing edge of at least one of said vanes to reduce said excitation amplitudes.