GB1278069A - Thrust deflectors for aircraft jet propulsion engines - Google Patents

Abstract

1278069 Thrust deflectors for gas turbine engine ROLLS-ROYCE Ltd 20 Jan 1970 [22 Jan 1969 8 March 1969 20 March 1969] 3600/69 12337/69 and 14611/69 Heading B7G A gas turbine engine 2, for example one mounted beneath an aircraft wing 3, is provided with a scoop 12 for spoiling and/or reversing thrust. The scoop 12 is pivoted at 13, is controlled by jacks 15 and is provided with sidewalls 14 for minimizing spillage of gas. When the thrust deflector is not being employed (chain dotted lines, Fig. 2) the lower surface of the scoop 12 forms part of the continuous lower surface of the wing; when the scoop 12 is lowered (full lines, Fig. 2) gases emerging from nozzle 7 are deflected through a passage 10 in the wing, at the outlet of which there may be vanes 19 to impart a forward component of velocity to the gases. The outlet may be provided with doors (not shown), moved in conjunction with the scoop 12, which may be pivotable in such a manner as to impart forward motion to the gases. In a related embodiment, Figs. 6 and 7 (not shown), the scoop may be provided with a cascade of vanes (62) which may be either closed so that gases are deflected through the passage in the wing, or may be opened to deflect the gases downwardly to afford lift. In the variant of Fig. 5 a similar scoop (shown for simplicity as a flat plate 41 is mounted at pivots 13 which may be moved in tracks 45 by jacks 46, and is also connected by links 50 pivoted at 51 on the engine and 52 on the scoop. When the deflector is not being applied it is in position A; when it is moved to position B the gases are deflected downwardly to afford lift, while in the position C the gases are deflected upwardly through the passage 53 to afford thrust reversal.