The application provides a
turbine guide vane and a
throat area design and adjustment method thereof, and the method comprises the following steps:
turbine guide vane aerodynamic and cooling structure design is performed; a three-dimensional geometric model of at least one
cascade passage is established, the pressure and temperature of inlet gas and inlet cold gas are given, gas flow calculation is performed, the gas flow and a Mach surface in a hot
cascade are obtained; the theoretical hot state
throat area of the
turbine guide vane is calculated; the heat insulation
coating design of the turbine guide vane blade body and the rim plate flow channel surface is performed; the
coating process test of the turbine guide vane is performed, the actual
coating thickness of each characteristic position point is measured, the actual coating thickness is used to calculate the
throat area of the turbine guide vane after the heat insulation coating is sprayed; the turbine guide vane is rotated at different angles around the blade radial direction, and the gas flow of the
cascade passage under different angles is obtained; when the flow and the throat area meet the requirements, the throat area of the turbine guide vane with the coating under the rotation angle meets the gas flow requirement.