Stall Inception Measurements in a High-speed Multi-stage Compressor PDF Download
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Author: J. F. Escuret
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
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Presented at the International Gas Turbine and Aeroengine Congress & Exposition, Houston, Texas - June 5-8, 1995.
Author: J. F. Escuret
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
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Presented at the International Gas Turbine and Aeroengine Congress & Exposition, Houston, Texas - June 5-8, 1995.
Author: Donald A. Hoying
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author:
Publisher:
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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ISBN:
Category : Mechanical engineering
Languages : en
Pages : 444
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Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781721585373
Category :
Languages : en
Pages : 36
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Book Description
A computational model is presented for simulating axial compressor stall inception and development via disturbances with length scales on the order of several (typically about three) blade pitches. The model was designed for multi-stage compressors in which stall is initiated by these short wavelength disturbances, also referred to as spikes. The inception process described is fundamentally nonlinear, in contrast to the essentially linear behavior seen in so-called modal stall inception . The model was able to capture the following experimentally observed phenomena: (1) development of rotating stall via short wavelength disturbances, (2) formation and evolution of localized short wavelength stall cells in the first stage of a mismatched compressor, (3) the switch from long to short wavelength stall inception resulting from the re-staggering of the inlet guide vane, (4) the occurrence of rotating stall inception on the negatively sloped portion of the compressor characteristic. Parametric investigations indicated that (1) short wavelength disturbances were supported by the rotor blade row, (2) the disturbance strength was attenuated within the stators, and (3) the reduction of inter-blade row gaps can suppress the growth of short wavelength disturbances. It is argued that each local component group (rotor plus neighboring stators) has its own instability point (i.e. conditions at which disturbances are sustained) for short wavelength disturbances, with the instability point for the compressor set by the most unstable component group. Suder, Kenneth (Technical Monitor) and Tan, Choon-Sooi Glenn Research Center
Author: Keith M. Boyer (CAPT, USAF.)
Publisher:
ISBN:
Category : Compressors
Languages : en
Pages : 286
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Author: V. H. Garnier
Publisher:
ISBN:
Category : Compressors
Languages : en
Pages : 0
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Book Description
Stall inception has been studied in two low-speed compressors (a single-stage and a three-stage) and in a high-speed three-stage compressor, using temporally and spatially resolved measurements. In all three machines, rotating stall was preceded by a period in which small-amplitude waves were observed traveling around the circumference of the machine at a speed slightly less than the fully developed rotating stall cell speed. The waves evolved smoothly into rotating stall without sharp changes in phase or amplitude, implying that, in the machines tested, the prestall waves and the fully developed rotating stall are two stages of the same phenomenon. The growth rate of these disturbances was in accord with that predicted by current analytical models. The prestall waves were observed both with uniform and with distorted inflow, but were most readily discerned with uniform inflow. Engineering uses and limitations of these waves are discussed.
Author:
Publisher:
ISBN:
Category : Mechanical engineering
Languages : en
Pages : 466
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Author: K. M. Boyer
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: A. A. J. Demargne
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
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Book Description
Presented at the International Gas Turbine & Aeroegine Congress & Exhibition, Orlando, FL, Jun 2-Jun 5, 1997.
