METHOD FOR PROCESSING BLADE BLANK NOZZLE APPARATUS OF GAS TURBINE ENGINE Russian patent published in 2018 - IPC F01D9/04 

FIELD: engine building.

SUBSTANCE: invention relates to the field of engine building and can be used in the manufacture of high-pressure turbine blades for a gas turbine engine nozzle apparatus. When processing blanks of blades of a nozzle apparatus, these blanks are digitized by an optical system, collect the digitized models of blades blanks into the wheel of the nozzle apparatus, set the axis of rotation of each model of the blade blank, set the nominal area of the passage section of the interblade channel and calculate the nominal total area of the interlamer channels of the nozzle apparatus. Specify the range of rotation angles of blade blades models for optimization of the flow section, set the initial rotation angle of the blade blades models and rotate them to the specified initial rotation angle. Next, the current total area of the cross-section of the interlamer channel of the nozzle apparatus is calculated, and, if the total area of the cross-sectional area of the interlamer channels of the nozzle apparatus does not turn out to be within the nominal value, the correction of the rotation angle of the blade models is calculated to obtain the nominal total cross-sectional area. To do this, calculate the average rotation angle, which is the same for all models of blade blanks, so that the current total cross-sectional area of the interlamer channels is within the tolerance limits. Correction values are formed and used to process blade blanks.

EFFECT: invention makes it possible to provide the blanks of blades of the nozzle apparatus with the area of the cross-sectional area of the interblade channels within the tolerance limits.

1 cl, 3 dwg