FIELD: engines and pumps.
SUBSTANCE: this invention relates to bypass turbojet delivery part (1a) including multiple blower blades (20) and support disc (22) for said blades. Said disc can spin relative to blower stator part (4) relative to blower lengthwise axis (2). Blade pitch angle variation system is connected with every blower blade. These systems are developed so that every pitch angle varies in compliance with single law. This law represents a function of the blade (20) angular position relative to blower stator part with respect to said lengthwise axis (2). Said single law is a periodic law and features period P=360°n, where n is an integer larger than or equal to 1.
EFFECT: comprehensive response to irregular air feed, preventing engine surging and decrease in efficiency.
13 cl, 7 dwg
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