expansion and booster for cooling gases or gas mixtures and to provide mechanical power for traction purposes

摘要

A multistage compressor assembly 4 is driven by a multistage turbine assembly 2 and a cooler 3, is arranged therebetween, in which respect a flowpath diversion 7 of approximately 180 DEG is arranged in the area of the cooler so that the turbine assembly and the compressor assembly have opposing flow directions. The upstream end of the turbine assembly 2 consists of an output-shaft driving turbine 23, and all adjacent stages of the turbine compressor assembly 2/4 stages of the compressor assembly 4 are designed for rotation alternately in opposing directions without stator-blade cascades inbetween. With the exception of the output-shaft turbine 23 every turbine stage and its corresponding compressor stage are coupled to a respective free-running rotor 10 to 16 in which respect the turbine blades may be arranged either radially outwardly or inwardly of the compressor blades. An after cooler 8 may be provided. The device may be used on hypersonic missiles and driven by pilot air (ram air). IMAGE