Gas turbine engine - has multiple compressors between pre-compressor and combustion chamber and mounted circumferentially

摘要

The gas turbine engine has individual compressors (2), located on the circumference between a precompressor (1) and the combustion chamber (3). The compressors are driven by a turbine shaft (6) via a transmission. Each compressor has several stages. A heat exchanger for intermediate cooling of the working gas is located between the outlet of the precompressor, and the intakes of the individual compressors. ADVANTAGE - Allows high pressure ratios.