A gas turbine engine is operating under the following conditions:

Stagnation temperature at turbine inlet Stagnation pressure at the turbine inlet Static temperature at turbine exit Velocity at turbine exit Total-to-total efficiency of turbine $\mathrm{J} / \mathrm{k} \mathrm{K}$ $\gamma$ (ratio of specific heats) $\mathrm{C}_{\mathrm{P}}($ specific heat at constant pressure $)$ $1.147 \mathrm{~kJ} / \mathrm{kgK}$

The stagnation pressure (in bar) in the nozzle (considering isentropic nozzle) is equal to__________

A gas turbine engine is operating under the following conditions:

Stagnation temperature at turbine inlet Stagnation pressure at the turbine inlet Static temperature at turbine exit Velocity at turbine exit Total-to-total efficiency of turbine $\mathrm{J} / \mathrm{k} \mathrm{K}$ $\gamma$ (ratio of specific heats) $\mathrm{C}_{\mathrm{P}}($ specific heat at constant pressure $)$ $1.147 \mathrm{~kJ} / \mathrm{kgK}$

The stagnation pressure (in bar) in the nozzle (considering isentropic nozzle) is equal to__________

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