This project investigates the design and optimization of a high efficiency turbo-compressor for use in jet-powered aircraft. The purpose of the turbo-compressor it to take warm bleed air from the main jet engine and condition it to an acceptable temperature and pressure such that it can be used for cabin and electronics cooling aboard the aircraft. The turbo-compressor consists of a single-stage centrifugal compressor paired with a single-stage radial turbine on a common shaft, as well as an inter-stage heat exchanger. The turbo-compressor must be able to operate at a range of inlet temperatures and pressures, and must output useable cool air at ambient pressure during all phases of flight (from ground level to 35,000 feet). The scope of this project includes the thermodynamic cycle analysis, 1-D meanline analysis of both compressor and turbine, as well as CFD and FEA of both turbine and compressor blade geometry.