$9\mathrm{.}3$ When running at a low$-$power condition a gas turbine with a free power thibine operates at a compressor pressure ratio of $2\mathrm{.}60.$ The combustion chamber pressure loss is $4$ per cent of the compressor delivery pressure and the exhaust pressure loss can be ignored.

The turbine characteristics are given below:

The 'non$-$dimensional' flows are based on $\backslash ($ m $\backslash )$ in $\backslash (\backslash$mathrm$\{$kg$\}/\backslash$mathrm$\{$s$\},$ p $\backslash )$ in bar and $\backslash ($ T $\backslash )$ in K $,$ all pressures and temperatures being stagnation values.

Calculate the gas$-$generator turbine pressure ratio at this condition. Assuming the compressor characteristic to be known, indicate briefly how you would calculate the turbine inlet temperature.