Impact of lower reaction on high aerodynamic load transonic fan inlet stage

[1] Farmakalides C D, McKenzie A B, Elder R L. The effects of reaction on axial flow compressor performance . ASME 94-GT-456,1994 [2] Voit C H. Investigation of a high pressure ratio eight stage axial flow research compressor with two transonic inlet stage-I: aerodynamic design . NACA RM E53I24, 1953 [3] Sandercock D M, Kovach K, Lieblein S. Experimental investigation of a five stage axial flow research compressor with transonic rotors in all stages -I: compressor design . NACA RM E54F24, 1954 [4] Yu Qing, Li Qiushi, Li Ling. The experimental researches on improving operating stability of a single-stage transonic fan . ASME GT-2002-30640, 2002 [5] Wennerstrom A J, Frost G R. Design of a 1500 ft/sec transonic high through flow axial flow compressor with low hub/tip ratio . AD-B016386, 1971 [6] Wennerstrom A J, Hearsey R M. The design of axial compressor stage for a total pressure ratio of 3 to 1 . ARL-71-TR-0061,1971 [7] Wennerstrom A J, Puterbaugh S L. A three-dimensional model for the prediction of shock losses in compressor blade rows[J]. ASME Journal of Eng For Gas Turbines and Power, 1984, 106(2):295-299 [8] Gummer V, Wenger U, Kau H P. Using sweep and dihedral to control three-dimensional flow in transonic stators of axial compressors[J]. Journal of Turbomachinery, 2001,123:40-48 [9] Friedrichs J, Baumgarten S, Kosyna G. Effect of stator design on stator boundary layer flow in a highly loaded single-stage axialvflow low-speed compressor[J]. Journal of Turbomachinery, 2001, 123:483-489