IGTC-18 Origin of the Vorticity of the Rotating Stall Cell of Centrifugal Compressors : Part I: Experimental Investigation of the Nature of the Reverse Flow(Session A-7 CENTRIFUGAL COMPRESSOR II)
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概要
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Rotating stall is introduced by the reverse flow issuing from the outlet of the impeller and travelling toward the inlet. The property of the reverse flow at the two operating points (1) on the onset of rotating stall, and (2) between the stall and the surge line was investigated experimentally by means of injection of colored dye through the shroud into the outlet region of the impeller. This method is justified, because the reverse flow in both these regions is stable in order to be visualized, but nevertheless still possesses all the behaviour as that reverse flow during the event of the rotating stall. The result shows that the reverse flow originates from the very flat discharge flow, bending from the pressure/hub corner over the outlet edge of the blade, and travelling backwards along the suction/shroud corner toward the inlet. It is shown that the reverse flow has the nature of a hollow longitudinal vortex with a shell composed of turbulent vortex rolls of the Ekman/Stewartson layers. These layers are formed on the pressure and suction surfaces of the blades, and on the shroud and the hub surface. In addition, it is found that this longitudinal vortex on the shroud surface is very resistant against disturbances caused by the passing-by of the blades. This resistance is further demonstrated on a laboratory experiment found in the literature, as will be given in Part II.
- 社団法人日本ガスタービン学会の論文
著者
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Seidel U.
Institute Of Turbomachinery University Of Hannover
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Chen Y.N.
Sulzer Brothers Ltd.
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Haupt U.
Institute of Turbomachinery, University of Hannover
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Rautenberg M.
Institute of Turbomachinery, University of Hannover
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Haupt U.
Institute For Turbomachinery University Of Hannover
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Rautenberg M.
Institut For Turbomachinery University Of Hannover
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Haupt U.
Inst. For Turbomachinery Univ. Of Hannover W.
関連論文
- IGTC-19 Origin of the Vorticity of the Rotating Stall Cell of Centrifugal Compressors : Part II: Reverse Flow as Rigid Turbulent Ekman Layer Vortex Roll(Session A-7 CENTRIFUGAL COMPRESSOR II)
- IGTC-18 Origin of the Vorticity of the Rotating Stall Cell of Centrifugal Compressors : Part I: Experimental Investigation of the Nature of the Reverse Flow(Session A-7 CENTRIFUGAL COMPRESSOR II)
- IGTC-91 The Rossby Waves of Rotating Stall in Impellers : Part I: Theoretical Background of the Rossby Waves in Blade Channels(Organized Session I ROTATING STALL AND SURGE IN COMPRESSORS)
- IGTC-91 On the Mechanism of Blade Excitation due to Surge on Centrifugal Compressors(Session C-6 STRENGTH AND VIBRATION)
- IGTC-23 On the Nature of Rotating Stall in Centrifugal Compressors with Vaned Diffusers : Part II: Karman Vortices as the Controlling Mechanism(Session A-7 UNSTEADY AERODYNAMICS I)
- IGTC-22 On the Nature of Rotating Stall in Centrifugal Compressors with Vaned Diffusers : Part I: Detection of Reverse Flow(Session A-7 UNSTEADY AERODYNAMICS I)
- IGTC-79 Prediction of Blade Vibration Stress in Centrifugal Compressors due to Engine Order Excitation(Session D-4 VIBRATION II)
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- IGTC-105 Adiabatic and Non-Adiabatic Efficiencies of Small Turbocharger Turbines(Organized Session II IMPROVEMENTS IN TURBOCHARGERS)
- IGTC-73 INFLUENCE OF HEAT TRANSFER BETWEEN TURBINE AND COMPRESSOR ON THE PERFORMANCE OF SMALL TURBOCHARGERS(Session B-9 Turbocharger I)
- IGTC-20 Evaluation of Unsteady Blade Loading Signals during Stall and its Inception in Centrifugal Compressors(Session A-7 CENTRIFUGAL COMPRESSOR II)
- IGTC-81 Investigation of the Solidity and the Blade Vibration Behaviour of Radial Compressor Impellers due to a Significant Reduction of the Hyperbolic Undercut in the Flankmilling Process(Session D-1 VIBRATION)