Natural gas, with the
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- Q1/1In a single-stage axial flow gas turbine of A319 Airbus Airplane has an axial velocity is equal to 250 m/s, and assume equal inlet and outlet velocities. Stage exit swirl angle is 9° , mass flow rate of gas is 15 kg/s, and nozzle efflux angle is 63°. Assume that blade speed is 350 m/s, gas enters at stagnation pressure of 5 bar, and stagnation temperature of 1980 °R. Also, assume y = 1.33, and C,,=1.147 kJ/kg. K. Determine the rotor blade gas angles, output power, blade-loading coefficient, and degree of reaction.arrow_forwardQ 2. Air at 400°C and 1.7 bar flows through a horizontal 8.2-cm ID pipe at a velocity of 50.0 m/s. I. Calculate Ék (W)? Assuming ideal gas behavior and Mol.Wt (Air)=29 g/mol. I. If the air is cooled to 250°C at constant pressure, what is AER? III. Why would it be incorrect to say that the rate of transfer of heat to the gas must equal the rate of change of kinetic energy?arrow_forward3. Assume the turbine as an incompressible flow machine. The average meridional speed is given as 150m/s. The flow coefficient is 0.5. Determine the blade speed that satisfies the above conditions.4. In a two-dimensional compressor cascade, inlet stagnation air pressure is 1.5 bar and inlet stagnation temperature is 330K. For an inlet Mach number of 0.75 and an inlet flow angle of 500, the exit flow angle is measured as 15.80. Determine the mass flow rate per unit frontal area, the exit Mach number and the static pressure ratio across the cascade. Assume the flow is isentropic.arrow_forward
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