Journal ArticleDOI
Experimental Evaluation of the Effects of a Blunt Leading Edge on the Performance of a Transonic Rotor
L. Reid,D. C. Urasek +1 more
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This article is published in Journal of Engineering for Power.The article was published on 1973-07-01. It has received 16 citations till now. The article focuses on the topics: Leading edge & Rotor (electric).read more
Citations
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Journal ArticleDOI
The effect of adding roughness and thickness to a transonic axial compressor rotor
TL;DR: In this article, the performance degradation of a high-speed axial compressor rotor due to surface roughness and airfoil thickness variations is reported, where a 0.025 mm (0.001 in) thick rough coating with a surface finish of 2.54-3.18 rms (100-125 rms μm) is applied to the rotor blades.
Proceedings ArticleDOI
The Effect of Adding Roughness and Thickness to a Transonic Axial Compressor Rotor
TL;DR: In this paper, the performance degradation of a high speed axial compressor rotor due to surface roughness and airfoil thickness variations is reported, where a 0.025 mm (0.001 in) thick rough coating with a surface finish of 2.54-3.18 RMS microns (100-125 RMS microinches) is applied to the pressure and suction surface of the rotor blades.
Dissertation
Probabilistic aerothermal design of compressor airfoils
TL;DR: Thesis (Ph. D.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2003 as discussed by the authors, was the first work to address the problem of space flight.
Journal ArticleDOI
The Effect of Variable Chord Length on Transonic Axial Rotor Performance
William B. Roberts,Albert Armin,George Kassaseya,Kenneth L. Suder,Scott A. Thorp,Anthony J. Strazisar +5 more
TL;DR: In this paper, the aerodynamic performance of a transonic compressor rotor operating with blades of varying chord length was measured in back-to-back compressor test rig entries, and it was found that blade chord variation is not important to aerodynamic performances above the stall chord limit if leading edges have the same shape.
Journal ArticleDOI
The Effect of an Eroded Leading Edge on the Aerodynamic Performance of a Transonic Fan Blade Cascade
Alexander Hergt,Joachim Klinner,Wolfgang Steinert,Sebastian Grund,Manfred Beversdorff,Angela Giebmanns,Rainer Schnell +6 more
TL;DR: In this article, the aerodynamic performance of an original fan profile geometry is compared to an eroded fan profile with a blunt leading edge (BLE) and a chord length reduced by about 1%.
Related Papers (5)
Experimental cascade analysis of a transonic compressor rotor blade section
H. A. Schreiber,H. Starken +1 more
Static-pressure contours in the blade passage at the tip of several high Mach number rotors
E. E. Bailey,G. R. Miller +1 more