TSCP700 provides a mechanical output of 105 kW (for TSP700-5 version used on Airbus aircraft).[2] It has a two-shaft architecture. The compressor design is quite peculiar, as the LP compressor is axial and the HP compressor is centrifugal. After the HP compressor, air is fed to a combustion chamber, and blown through two turbines. The first high-pressure turbine drives the HP compressor and provides the "useful" output (driving, e.g., a power generator), while the second, low-pressure turbine drives the LP compressor shaft.[3]
^Malohn, Donald A. (1 February 1970). "TSCP700 Auxiliary Power Unit for the DC-10 Aircraft": 700815. doi:10.4271/700815. {{cite journal}}: Cite journal requires |journal= (help)
