Correlation of part-span damper losses through transonic rotors operating near design point

The design-point losses caused by part-span dampers (PSD) were correlated for 21 transonic axial flow fan rotors that had tip speeds varying from 350 to 488 meters per second and design pressure ratios of 1.5 to 2.0. For these rotors a correlation using mean inlet Mach number at the damper location, along with relevant geometric and aerodynamic loading parameters, predicts the variation of total pressure loss coefficient in the region of the damper to a good approximation.

[1]  D. C. Urasek,et al.  Performance of inlet stage of transonic compressor , 1976 .

[2]  E. R. Tysl,et al.  Performance of a transonic compressor rotor with an aspect ratio of 6.5 , 1974 .

[3]  T. C. Ware,et al.  High-tip-speed, low-loading transonic fan stage. Part 3: Final report , 1974 .

[4]  W. M. Osborn,et al.  Performance of a single-stage transonic compressor with a blade-tip solidity of 1.5 and comparison with 1.3 and 1.7 solidity stages , 1973 .

[5]  D. C. Urasek,et al.  Performance of transonic fan stage with weight flow per unit annulus area of 198 kilograms per second per square meter (40.6(lb/sec)/sq ft) , 1973 .

[6]  G. Kovich,et al.  Overall and blade-element performance of a multiple-circular-arc bladed transonic compressor rotor with tip speed of 1375 feet per second , 1973 .

[7]  R. Moore,et al.  Performance of a single-stage axial-flow transonic compressor stage with a blade tip solidity of 1.7 , 1972 .

[8]  D. C. Urasek,et al.  Effects of increased leading-edge thickness on performance of a transonic rotor blade. [in single stage transonic compressor] , 1972 .

[9]  D. C. Urasek,et al.  Performance of a single-stage transonic compressor with a blade-tip solidity of 1.3 , 1972 .

[10]  D. C. Urasek,et al.  Comparison of the effect of two damper sizes on the performance of a low-solidity axial-flow transonic compressor rotor , 1972 .

[11]  D. C. Urasek,et al.  Performance of tandem-bladed transonic compressor rotor with tip speed of 1375 feet per second , 1972 .

[12]  Melvin J. Hartmann,et al.  A preliminary analysis of the magnitude of shock losses in transonic compressors , 1957 .

[13]  W. A. Benser,et al.  Holographic Studies of Shock Waves Within Transonic Fan Rotors , 1975 .

[14]  G. V. Rao,et al.  IN A TWO STAGE FAN , 1975 .

[15]  D. M. Sandercock,et al.  Some observed effects of part-span dampers on rotating blade row performance near design point , 1973 .

[16]  C. L. Ball,et al.  Performance of a 1380-foot-per-second-tip-speed axial-flow compressor rotor with a blade tip solidity of 1.3 , 1972 .