FIELD: engines and pumps.
SUBSTANCE: gas turbine engine blade includes lots of sections (22), located along radial axis (Z-Z) in which projection of line (28a), connecting leading edges of sections of lower set of sections (28) in meridian plane, is inclined at the first angle of longitudinal tilt (α) to leading edge (24) which is from 10° to 25°; projection of line (30a), connecting leading edges of sections of middle set of sections (30), is inclined at the second angle of longitudinal tilt (β) to back edge (26) which is from 10° to 25°; projection of line (32a), connecting leading edges of upper set (32) of blade sections, is inclined at the third longitudinal angle of tilt (γ) to back edge (26) which is from 20° to 50°; and lower boundary (34) of middle set (30) of blade sections is located between 30% and 40% of total radial height (h) of blade sections set.
EFFECT: improving efficiency upon reduction of noise produced by gas flow.
6 cl, 3 dwg
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