FIELD: engines and pumps.
SUBSTANCE: turbojet engine rotary blade incorporates set of sections arranged along centers of gravity of blade sections between root and outer edge. Blade is limited in lengthwise direction by front and rear edges and comprises along the engine radial axis lower, medium and upper parts. Blade lower part is arranged radially between blade root and medium part lower edge. Blade upper part is arranged radially between medium part upper edge and blade outer edge. Front edge lower part is inclined in the lengthwise direction. Front edge outline in medium part is inclined backward in the lengthwise direction. Front edge outline upper part backward inclination is different in the lengthwise direction. Line of blade sections centers of gravity is inclined tangentially opposite the blade sense of rotation.
EFFECT: optimum aerodynamic characteristics in all operating conditions and lower noise.
11 cl, 4 dwg
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