A slip factor calculation in centrifugal impellers based on linear ...

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Compressor Stages used to test the model 1. Stage of turbojet Olympus 2. Stage tested by Stechk<strong>in</strong> 3. Stage designed by Beker Eng<strong>in</strong>eer<strong>in</strong>g and tested at Concept. 4. Stage designed by Beker Eng<strong>in</strong>eer<strong>in</strong>g , not tested 5. Stage C1 (tandem blades) (data from USSR) 6. Monig et al. Trans ASME. Journal of turbomach<strong>in</strong>ery 1993,v115, p.565-571. 7. Stage C9 (data from USSR) 8. Musgrave D., Plehn N.J. Mixed flow stage design and test results with a pressure ratio of 3:1. ASME Gas turb<strong>in</strong>e conference presentation 87-GT-20. 16
Results 510.6 165 60.05 0.612 1.0 1.78 19.9 2.89 6.36 12/24 8 520 161 46.25 0.175 0.56 2.18 6.25 2.75 6.79 18/36 7 425 160 50.47 0.316 0.74 2.0 8.48 2.0 3.86 15/30 6 455 185.3 46.65 0.346 0.25 2.12 9.0 2.7 4.54 27/27 5 550 182.9 56.33 0.641 1.50 2.1 48.28 1.0 3.87 7/14 4 500 189.3 57.48 0.397 1.27 1.89 12.0 0.48 5.23 11/22 3 483 170 32.7 - 0.50 2.30 33.58 3.0 3.95 12 2 472.3 180 57.8 0.695 1.0 1.83 16.99 0.41 4.35 6/12 1 u 2 m/s (tip velocity) c a2 m/s β 1 (<strong>in</strong>let flow angle ) t 2,mean (outlet relative pitch) t 1,mean (<strong>in</strong>let relative pitch) β 2k (outlet blade angle) G Kg/s Rotor pressure ratio Z number of blades Rotor No. Table 1. Rotor parameters. 1 2 r r 17
Page 1 and 2: A slip fac
Page 3 and 4: Rotors with splitters or with high
Page 5 and 6: Slip flow in Centr
Page 7 and 8: ∆P ρ w 1 General Inviscid ∆P
Page 9 and 10: ( ) w / w ( w / w ) 2 2 ( ) = K cos
Page 11 and 12: W 1 K Calculation of the coefficien
Page 13 and 14: Impellers with high blade load<stro
Page 15: Maximal pressure gradient Analysis
Page 19 and 20: Measured and calculated sli
Page 21: Conclusions • Suggested method al

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