Hypersonic aircraft reaction drive - has flow tube with frontal air entry slot and trough at trailing end

摘要

The drive comprises a gas producer, axial compressor, combustor and turbine with the output turbine and coupled blower and air inlet and outlet on a flow tube enclosing the drive and gas producer with clearance. This basic drive is fitted with an open-ended thrust channel with upstream second air entry and the producer has an upstream air entry ring fixed to a casing tube. The flow tube (40) has a frontal frist air entry slot (16) and has a ring trough (46) at the trailing end plus coaxial to the tube dia. and adjuster (18) which revolves round the drive axis and has second air entry slots (17). Rim toothing in the adjuster is engaged by an adjuster motor pinion and an entry curve part (19) is joined to an adjuster and can move axially. The thrust channel (2) is ringed by equi-spaced gas producers and output turbines (5) are coupled downstream via drive shafts (6) and front and rear plates to the blower (7) rollers (48,49). A gas collector space (8) downstream of the turbines (5) has equi-spaced centripetal gas offtake channels (33) with premounted flow ribs (21) plus second afterburners (54) to issue into a two nozzle (10,11) pulse chamber. USE/ADVANTAGE - Hypersonic aircraft. Booster air throughput and thrust combine with temp. control at high Mach speeds.