Engine mounting and boundary layer control fluid supply apparatus

Abstract

A midwing aircraft employs a unique configuration for mounting three high bypass turbofan engines. All three engines are mounted so that a portion thereof projects forwardly of the leading edge of the airfoil on which they are mounted and so that the chordal plane of the airfoil longitudinally bisects the engine. The exhaust from each of the engines is directed by two nozzles. Internal bifurcators split both the turbine exhaust and the fan exhaust from each of the engines evenly between the two nozzles. A pair of channels in each of the wing mounted engines intercepts a portion of the fan effluent and directs it rearwardly into boundary layer control supply plenums in the wing structure. Valve mechanisms for opening and closing the channels are mounted in the forward portions of the channels. Check valves are also provided in each of the channels to prevent backflow of fluid from the supply plenums into the channels. The engines are mounted on the airfoils by a pair of box beams that run along the interior longitudinal sides of each of the engine nacelles. The turbine portion of the turbofan engines is mounted to the inner sides of the box beams at a location forwardly of the leading edge of the airfoils. The box beams can be shrouded to serve as the fluid inlet channels for the fluid supply plenums. The rear portion of the box beams are removably affixed to ribs or flanges extending forwardly from the front main spar of the wing.