A film-cooled radial-inflow turbine is to be used in a high-performance open Brayton cycle gas turbine. The rotor is made of a material able to withstand a temperature of 1145 K at a tip speed of 600 m/s for short periods of operation. Cooling air is supplied by the compressor that operates at a stagnation pressure ratio of 4- 1, with an isentropic efficiency of 80%, when air is admitted to the compressor at a stagnation temperature of 288 K. Assuming that the effectiveness of the film cooling is 0.30 and the cooling air temperature at turbine entry is the same as that at compressor exit, determine the maximum permissible gas temperature at entry to the turbine. Take γ = 1.4 for the air. Take γ = 1.333 for the gas entering the turbine. Assume R = 287 J/(kg K) in both cases