FIELD: engines and pumps.
SUBSTANCE: proposed bypass turbojet comprises nacelle, cold airflow annular channel, fan outer cowling and multiple bulges nearby cold airflow channel outlet. Nacelle is provided with external cowl and comprises fan and central generator. Fax external cowling confines said annular channel on the side of nacelle outer cowl. Cold flow outlet hole edge makes rear edge of said nacelle and is defined by nacelle outer cowl and fan outer cowling arranged opposite each other. Every said bulge enters said annular channel and has bulged surface and two flat lateral surfaces extending in lengthwise direction relative to turbojet. Bulged surface and two side surfaces impart approximately rectangular section to said bulge extending in direction parallel with lengthwise axis.
EFFECT: efficient noise killing.
4 cl, 6 dwg
