Abstract: A thrust reversing arrangement for an aircraft turbofan propulsive power unit includes a flow redirecting structure which has reverse flow enhancing sub-structures comprising: (i) a cavity which is so dimensioned as to generate a back pressure which supports redirection of flow; (ii) a cascade assembly which provides a flow control slot so dimensioned as to optimize reverse thrust for predetermined fan duct flow conditions; (iii) an obstructing duct wall portion having a leading edge so positioned as to form a leakage slot providing controlled leakage of forward flow; (iv) a box structure, the dimensions of which are such as to optimize back pressure in the cavity; and (v) provision for gaseous fluid under static pressure from the fan duct to load the redirecting structure to the inoperative position.

Abstract: A thrust reversing arrangement for an aircraft turbofan propulsive power unit includes a flow redirecting structure which has reverse flow enhancing sub-structures comprising: (i) a cavity which is so dimensioned as to generate a back pressure which supports redirection of flow; (ii) a cascade assembly which provides a flow control slot so dimensioned as to optimize reverse thrust for predetermined fan duct flow conditions; (iii) an obstructing duct wall portion having a leading edge so positioned as to form a leakage slot providing controlled leakage of forward flow; (iv) a box structure, the dimensions of which are such as to optimize back pressure in the cavity; and (v) provision for gaseous fluid under static pressure from the fan duct to load the redirecting structure to the inoperative position.