Compressor Surge and Stall
High efficiency axial and centrifugal compressors are important in fields as diverse as aircraft engines, superchargers and turbochargers, process and refrigeration compressors. Compressors must achieve high efficiency in blade rows in diffusing flow fields. Of equal and sometimes greater importance is the range os stable operation of the compressor. Blade row stall characteristics determine the limit os stable operation. Blading can stall uniformly with symmetric flow breakdown or asymmetrically in rotating stall, wich propagates around the periphery of the blade row. Depending on aerodynamic conditions, surge may occur instead of, in concert with, or subsequent to blade row stall. The transient breakdown and recovery of aerodynamic loading not only limits compressor performance but also leads to mechanical failures caused by the vibrational loads imposed on the blades. There is no need to know what initiates these performance limits so that surge and stall margins can be optimized and control strategies can be planned. the first step toward understanding is to be knowledgeable about he physical processes occurring during surge and stall. This will permit the designer to anticipate variable geometry needs such as variable inlet guide vanes, variable statuors, and bleed port strategies. Theoritical treatment is far from being well established, however, there are many approaches discussed in the literature. This book is a unique reference to the subject matter. Physical descriptions of the phenomena are given, test results are presented, and analytical studies are discussed. There has been much written about the experimental investigations and theoretical treatments related to surge and stall. To assist those who would pursue advancements in furthering ou knowledge of surge and stall, it seemed appropriate to have a resource that contains a compendium of information on this subject. That is the purpose of this book. [Source : d'après la 4e de couverture].
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Appendix 21 Symbols Lists A211
11 other sections not shown
4-stage Abdelhamid abrupt stall amplitude anemometer angle of attack axial compressor axial velocity Axial-Flow Compressor blade row blockage cascade cell number Centrifugal Compressor choke flow compressor map compressor performance Compressor Stall DESIGN SPEED downstream Engineering equation etal exit Figure flow angle flow coefficient flow fluctuation flow range full-span stall Greitzer Haupt hot-wire hub/tip ratio Huppert hysteresis impeller increase initiated inlet stages low speeds Ludwig mass flow NACA Nagano operation oscillation oscillogram part-span stall performance characteristics Permission of ASME perturbation plenum plot pressure coefficient pressure ratio progressive stall propagation velocity pulsations radius Rautenberg recovery reduced rotating stall rotor speed shown in Fig shows stall cell stall characteristics stall inception stall pattern stall zones static pressure Stator Stagger Angle surge and stall surge cycle surge line SWIRL ANGLE test results throttle tip stall total pressure transient unstalled upstream vaned diffuser vaneless diffuser variation velocity potential weight flow