= 1.333, R = (30 points) Combustion gases (y repeating stages at T01 = 1200K and...

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= 1.333, R = (30 points) Combustion gases (y repeating stages at T01 = 1200K and P01 = 287 J/kgK)) axially enter a turbine with 1500 kPa. The flow coefficient for the stage is 0.8 and the reaction is R = 0.4. If the inlet absolute Mach number to the stage is M a. the rotor velocity at midspan = = 0.4, find: b. the absolute Mach number leaving the stator and the relative Mach number leaving the rotor C. the ratio of rotor blade spacing to axial chord, using the Zweifel criterion. Use the incompressible relation which for a stator is given as: opt = 0.4 [cos2 (tan 1 + tan 2)] d. the total-to-total efficiency of the stage, using the Soderberg correlation. Use the nominal (uncorrected) Soderberg correlation for both rotor and stator: 2 3=0.04+0.06 (100) and the simplified efficiency expression derived in class: 1 ntt =1+ 2014 (34/cos2a2 + R/ cos3)] = 1.333, R = (30 points) Combustion gases (y repeating stages at T01 = 1200K and P01 = 287 J/kgK)) axially enter a turbine with 1500 kPa. The flow coefficient for the stage is 0.8 and the reaction is R = 0.4. If the inlet absolute Mach number to the stage is M a. the rotor velocity at midspan = = 0.4, find: b. the absolute Mach number leaving the stator and the relative Mach number leaving the rotor C. the ratio of rotor blade spacing to axial chord, using the Zweifel criterion. Use the incompressible relation which for a stator is given as: opt = 0.4 [cos2 (tan 1 + tan 2)] d. the total-to-total efficiency of the stage, using the Soderberg correlation. Use the nominal (uncorrected) Soderberg correlation for both rotor and stator: 2 3=0.04+0.06 (100) and the simplified efficiency expression derived in class: 1 ntt =1+ 2014 (34/cos2a2 + R/ cos3)]