Combined propulsion unit for sub-to hypersonic flight speeds

摘要

Combined propulsion unit for hypersonic flight, comprising a rocket engine independent of the ambient air, a turbojet engine whose compressor is driven by a turbine independent of the ambient air, and if required a ram-jet engine which is identical to the turbojet engine with respect to the flow channel. Arranged on the rocket engine is a gas generator (4) having two sealing devices which optionally produce a connection to the rocket combustion chamber or to the turbine group of the turbojet engine. The turbine group and the compressor group consist of a plurality of counter-rotating rotors (11, 12, 13) without interposed stators, each turbine rotor forming a free-wheeling rotor with one compressor rotor in each case, the turbine blades being arranged radially inside or outside the compressor blades. …??The outlet channel of the turbine group is constructed towards the combustion chamber as a device for mixing the turbine working gases with the ambient air. …IMAGE…