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. Q1/ In a single-stage axial flow gas turbine of A319 Airbus Airplane has an axialvelocity is equal to 250 m/s, and assume equal inlet and outlet velocities. Stage exitswirl 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, andstagnation temperature of 1980 °R. Also, assume y = 1.33, and Cpg =1.147kJ/kg.K. Determine the rotor blade gas angles, output power, blade-loadingcoefficient, and degree of reaction.

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Answered: Q1/1In a single-stage axial flow gas…

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

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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.

Q1/ In 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 Cpg =1.147
kJ/kg.K. Determine the rotor blade gas angles, output power, blade-loading
coefficient, and degree of reaction.

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