Disc shaped vertical lifting turbocompressor for turbojet engine of aircraft, has combustion chamber which is arranged on the tangent line of rotary compressor for adjusting the time required for flow of gas through combustion chamber

摘要

The turbocompressor has two-stage rotary compressor (1), tangential combustion chamber (2) and two-stage centripetal turbine (3). The compressor stage (5) and turbine stage (6) are arranged coaxially and concentrically with compressor stage (4) and turbine stage (7). The high pressure armature (9) is provided with impellers of compressor stages (5) and turbine stage (6) respectively. The tangential combustion chamber is arranged on the tangent line of rotary compressor for allowing the adjustment of time required for flow of gas through the combustion chamber.