I need to perform a cycle balance on a gas generator using two independent turbines (one for each compressor). The rocket has a thrust of 5.83 MN, Isp=287 s, chamber stagnation pressure of 12.1 MPa and r=2.8 (oxidizer/fuel mass ratio). The max inlet temperature for the turbine is 3,170 K, the turbine efficiency is 0.73, the pump efficiency is 0.67 and the mechanical efficiency is 0.78. Use gamma=1.32 and the mixture MW=22.6. The oxidizer density is 1,140 kg/m^3 and for the fuel is 750 kg/m^3. The pressure in the propellant tanks is 0.335 MPa. The injector velocity is 58 m/s and 2.5% of the mass goes to the gas generator. I need the pressure ratio across both turbines.