FIELD: engines and pumps.
SUBSTANCE: cascade thrust reverser of a turbojet engine comprises a fairing, a sliding bonnet, at least one fold and arresting devices. The inner surface of the sliding bonnet comprises a circular part protruding radially inside and made as capable of adjacency in the mode of thrust reverse to the circular part of the inner surface of the fan channel. Each fold is installed on the circular part of the inner surface of the sliding bonnet as capable of rotation around the middle hinged axis from the folded position into the unfolded position. In the folded position each fold is arranged as aflush with the inner surface of the sliding bonnet, and in the unfolded position the front part of the fold, in front of its middle hinged axis, protrudes into the fan channel. Arresting devices are made as capable to impact the rear part of the fold, behind its middle hinged axis, in the mode of thrust reverse, to rotate the fold into the unfolded position to close the fan channel. Another invention of the group relates to a turbojet engine body comprising the above cascade thrust reverser.
EFFECT: inventions make it possible to provide for efficient reversing of thrust without increase in body diameter.
12 cl, 13 dwg
