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The fans on turbofan engines are essentially single stage axial compressors with a zero inflow swirl angle (a1 = 0). Consider a fan that has a...

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The fans on turbofan engines are essentially single stage axial compressors with a zero inflow swirlangle (a1 = 0). Consider a fan that has a pitchline radius of I'm = 1.5 m, spins at 2250 rpm, andprovides a pressure ratio at cruise of Itf = 1.6. The stage efficiency is nist = 0.96 and the pitchline ischaracteristic of the entire fan. The inflowing air has Cp = 1000 J/kgk and y = 1.4. Cruise conditionsare a flight Mach number of M = 0.85 at an altitude where Ta = 230 K. (18 pts)a) Determine the swirl velocity leaving the rotor at the pitchline in the engine fixed frame ( Cez). (7.5pts)b) Draw qualitatively correct overlapped velocity triangles before and after the rotor, labelingC1, C2, W1, W2, and U. (3 pts)The low pressure turbine drives the fan via a shaft with nm = 0.95. The specific heat in the lowpressure turbine is CpLPT = 1200 J/kgK. The bypass ratio is B = 8 and you can assume f << 1.c) What is the stagnation temperature drop over the low pressure turbine? (7.5 pts)
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