GB851379A - Aircraft - Google Patents

Abstract

851,379. Jet propelled aircraft. POWER JETS (RESEARCH & DEVELOPMENT) Ltd. Nov. 20, 1958 [Nov. 20, 1957], No. 36130/57. Addition to 829,753. Class 4. [Also in Group XXVI] An aircraft wing comprises stress-carrying structure including front and rear spars, and a plurality of straight tubular members arranged side by side along the wing span and extending chordwise from a position forward of the front spar, through the spars to which they are rigidly attached to a position rearward of the rear spar, where they are connected to rearwardly directed nozzles, and comprises at least one jet engine of the type producing two jet streams at different temperatures, the engine discharging the cooler stream through at least one of the tubular members and nozzles, and the hotter stream through a separate nozzle outside the wing structure and discharging clear of the wing. The structural members of the wing shown are spars 2 and 13, and a spanwise series of tubular ducts 4 (one shown). Where the thickness of the wing permits, each duct has fins 5, and the wing skins 6, 7, are secured to flanges on the spars and fins. A by pass or ducted fan gas turbine engine 8 is mounted in a nacelle 9, there being one engine for every two ducts 4. The hot turbine exhaust is led through a cranked duct 16 to a nozzle 17 above or below the wing and faired by a cover 18. The annular by-pass or fan air stream is divided by splitter plates 14 into two semi-annular streams, each flowing into one of two ducts 13 having semiannular intakes merging into circular outlets. The air stream then flows into the two tubular ducts 4 associated with the engine and exhausts through fish tail nozzles 19 over a trailing edge flap 21. The nozzles and flap form a jet flap arrangement. By this means, the flow of hot gases through the wing is avoided. Another form of engine which can be used is one in which a turbine is driven by rocket gases, and drives a ducted fan producing a cooler jet stream. The wing may also embody further features of the parent Specification, particularly in the formation and accommodation of fuel tanks. In another arrangement the engines may be installed above or below the wing, the hotter stream being discharged directly rearwardly, while the cooler stream is ducted downwardly or upwardly into the tubular members 4. The cooler stream may be discharged through one, or more than two, tubular members. Specifications 749,009, 787,011, 787,012, 787,013, 787,014, 787,015, 790,193, 790,194, 790,298, 823,591, 823,592 and 823,593 also are referred to.