Two-stage compressor for turbines in super ultrasonic jet aircraft engines

摘要

The high pressure compressor (6) runs on the main shaft (1) and the low pressure compressor runs in front of the high pressure compressor on a coaxial shaft positioned around the main shaft. The low pressure compressor can be connected and disconnected via lamella couplings. Air conducted through channels can be directly fed into the low pressure compressor on starting and landing or changed over by flaps directly into the high pressure compressor. The high pressure compressor comprises several stages of an axial compressor, at the end of which is a radial compressor. Around the blade ring of the radial compressor is a ring of guide blades, which guides the air flying away at sound speed in a rotary movement into the combustion chamber.