TURBOMACHINE BLADE SYSTEM Russian patent published in 2017 - IPC F01D5/14 

FIELD: machine engineering.

SUBSTANCE: turbomachine blade system comprises blades arranged between the end surfaces, wherein a finning is made on the inner side of at least one of the end surfaces in the interblade channels. The fining is made in the form of a main fin and an additional fin of curvilinear shape of triangular cross-section. The longitudinal axis of the main fin is located on a line connecting the centres of circles inscribed between adjacent blades. The input edge of the main fin is located at the inlet section of the interblade channel, and the output edge of the main fin is located at the outlet section of the interblade channel. The height of the main fin is linearly increasing from the zero value in the area of its input edge to a value equal to 0. 08 of the profile chord size in the blade system in the output edge area. The longitudinal axis of the additional fin is located on the line connecting the centres of circles inscribed between the main fins and the backs of the blades. The input edge of the additional fin is located in the throat section, and the output edge of the additional fin is located in the direction of its longitudinal axis beyond the outlet section of the interblade channel at a distance from 0. 08 to 0. 1 of the profile chord size in the blade system. The height of the additional fin is equal to 0. 08 of the profile chord length in the blade system, and the width of the main and additional fins at the base does not exceed 1 mm.

EFFECT: increased aerodynamic efficiency of the turbomachine blade system.

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