Stall Inception in Single Stage, High-speed Compressors with Straight and Swept Leading Edges PDF Download
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Author: K. M. Boyer
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Category :
Languages : en
Pages :
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Author: K. M. Boyer
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Category :
Languages : en
Pages :
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Author: B. J. Frank
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Category :
Languages : en
Pages :
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Author: Keith M. Boyer (CAPT, USAF.)
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Category : Compressors
Languages : en
Pages : 286
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Author:
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Category : Mechanical engineering
Languages : en
Pages : 444
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Author:
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ISBN:
Category :
Languages : en
Pages : 157
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Two single-stage, transonic compressor designs were tested under various undistorted operating conditions to characterize the process leading up to aerodynamic stall. The rig case was instrumented with eight high-response static pressure transducers equally spaced around the annulus for stall development detection. High-response measurements were low-pass filtered and both spatially and temporally analyzed using discrete Fourier techniques. At all speeds tested for both designs, stall inception was characterized by growth of a small amplitude' rotating wave. The waves did not grow significantly until just prior to the instability, when exponential growth into fully-developed rotating stall occurred very rapidly, within 6-10 rotor revolutions. The amount of time the rotating waves could be detected prior to stall varied considerably with compressor operating condition and was largely dependent on the local slope of the compressor speedline characteristics. Stall warning times ranged from less than one-tenth of a second to more than two seconds for the same machine operated at different high speeds (above 60% design speed). The influence of compressibility effects are also discussed.
Author:
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Category : Mechanical engineering
Languages : en
Pages : 452
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Author:
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Category :
Languages : en
Pages : 125
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The stall characteristic of four single-stage transonic compressor rotors were investigated as they were throttled to stall. Forward-swept, backward-swept, and straight leading edge rotors were examined. Three methods of analysis (1) windowed power spectrum densities of pressure and spatial Fourier coefficients, (2) phase tracking analysis, and (3) system identification were used to identify the first appearance of modal waves and their accompanying frequencies in order to identify a stall warning time. A direct correlation between the amount of stall warning time and the shape of the compressor characteristic was found. Specifically, if the compressor characteristic had a significant period of flat or positive slope, more stall warning was noted. It was also found that the forward-swept rotor consistently provided more stall warning time than the backward-swept and straight leading edge rotors.
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Category : Airplanes
Languages : en
Pages : 728
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Author: James Donald Paduano
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Category : Technology & Engineering
Languages : en
Pages : 242
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Author: Alexander Kimberley Simpson
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Category :
Languages : en
Pages :
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