Performance Analysis on Fuel Turbo-pump and Motor System of Scramjet Engine

摘要

A fuel supply and generating system on actively cooled scramjet engine were developed. A turbo-pump driven by fuel vapor is connected to a motor which turns a generator when the turbo power is rich. The specific power of cracked Norpar 12 through an isentropic expansion was calculated. Then the performances of the system at flight conditions were studied, and the results showed that the turbo began to generate power at Ma6 and about 40kJ/kg power generation could be made at the expansion ratio of 1.6. To improve the performances of the system at low Ma numbers, a flowing bypass was developed and the optimization was carried out. It was proved that this design could expand the working range of the turbo to lower Ma numbers.