GB568366A - Improvements in and relating to air intake systems for the engines of aircraft - Google Patents

Abstract

568,366. Aircraft engine air intakes. BLACKBURN AIRCRAFT, Ltd., TOPLIS, J. G., and TRUYENS, C. P. J. July 16,1943, No. 11586. [Class 4] An air intake system for an aero-engine comprises a forward main intake and a rearwardly situated sheltered intake, a semicylindrical element provided with at least one curved deflector being mounted for partial rotation concentrically within a duct leading to the engine so that in one position of the element air entering the main intake is deflected into the duct and in its other position air entering the sheltered intake is so deflected. As shown, a main intake 1 is situated just below the leading edge of a wing and a sheltered intake 3 is arranged in the lower surface of the wing, and both give access to a chamber in the wing, from one wall of which extends a duct leading to the engine. Extending across the chamber opposite to the duct is an element comprising a disc 7 and a ring 6 connected by a cylindrical plate 8, a curved deflector 9 being arranged within it as shown. A second plate 10 connects the end disc 7 to the plate 8 to round off the corner. With the element in the ,position shown in Fig. 1, air entering the intake 3 passes over two filters 4 arranged as described in Specification 566,819, and is deflected into the duct by the plates 8, 9, 10. When the element is turned through 180 degrees, air entering the forward intake 1 is deflected into the duct, but sufficient air escapes past the edges of the plate 8 to clear the filters 4 before passing out through the opening 3 or other. orifice provided. A butterfly valve 11 is geared to the element 6, 7, as shown, so that the forward intake 1 is completely closed when the sheltered intake is in use.