Question

Problem 10.4 aircraft propulsion farokhi

A turbine stage is designed with a constant axial velocity of 250 m/s and zero exit swirl. For a rotor rotational speed Um at the pitchline of 600 m/s. Calculate and comment on your results

a) the nozzle exit flow angle, ?2 in degrees for ◦Rm = 0.50

b) the nozzle exit flow angle, ?2 in degrees for ◦Rm = 0.0

c) the rotor specific work at the pitchline radius, for ◦Rm = 0.50 and ◦Rm = 0.0

10.4 A turbine stage is designed with a constant axial velocity of 250 m/s and zero exit swirl. For a rotor rotational speed Um at the pitchline of 600 m/s. Calculate (a) the nozzle exit flow angle, az in degrees for 0.50 (b) the nozzle exit flow angle, a, in degrees for 0.0 (c) the rotor specific work at the pitchline radius, for 0.50 and °Rm = 0.0 Rim = ºRm = °R. = =

Answer 1

Given Data Axial velocity Ca = 250 m/s zero exit swirl Coro Rotor speed um 2 Goo m/s a) Rm 20.5 tor 501 reaction turbine Cus = C Ca tan d2 -u) -250 tan da 고 6oo) da 67.38 R=0 from exit velocity triangle Un = Ca C tan 8.3 tana) boo 250 C (tan (23) ß 3 = 67.38 Degree of Reaction ca Rz ( tan 123- dan 32) 24 ca zu 02 (ten pz-tan 32) 82 283 = 67.38 uz Ca (tan 2 -tan 122) boo 2 250 C tanda tan 67.38°) x2 2 78.23°

c) Rotor specific work Specific work w z u C Couto - ches) u x ca tan 22 Rzo.5 tan (6738) 6000 250x w 360 k kJ/kg. R20 x tan ( 98.23) Wz 600 x 250 720 kuling w z
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