| 摘要 |
FIELD: engines and pumps. ^ SUBSTANCE: mixer of variable cross-section flows for double-flow jet turbine engine of supersonic aircraft includes nozzle with centre on longitudinal axis of jet turbine engine, which is concentrically installed around gas generator. Nozzle includes multiple ambient air inlet holes made in its circumferential direction and opening to convergent zone of cold flow supplied from cold flow channel enveloping gas generator, with hot flow leaving the gas generator. Movable trays installed in holes are moving between two positions: between the first position in which they cover the nozzle holes and the second position in which they open the holes and are radially located in that position in the nozzle, thus providing ambient air inlet to convergent zone. Trays have azimuth constituent part of similar direction in order to put ambient air into rotary motion in convergent zone when the trays are in the second position. ^ EFFECT: inventions allow reducing noise of jet flow of jet turbine engine without increasing its overall dimensions. ^ 5 cl, 7 dwg |
