Experimental Investigation of the Loss Coefficients in a Linear Cascade
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Reza Taghavi-Zenouz
,
Majed Etemadi
Abstract
This paper reports results of experimental investigations on a linear cascade of axial compressor blades. Experiments were conducted in an open circuit subsonic wind tunnel of Aerodynamics Research Laboratory of the Iran University of Science and Technology. Different Reynolds numbers based on the blade chord length were examined, ranging from 80,000 to 500,000. Flow incidences were changed between −8 to +8 degrees with 2 degrees intervals. Freestream turbulence intensity was changed between 1.25 to 4 percent corresponding to different mesh screens mounted upstream of the test model. All the above flow conditions provided to establish various flow regimes, in terms of fully laminar and transitional flows, around the blades. At a specified range of Reynolds numbers laminar separation bubble/bubbles occurred over the blade solid walls. Surface pressure distributions were measured utilizing a computerized data acquisition system. Fluctuating velocities were also measured at various positions around the separation bubble zone, using hot film anemometry. Surface oil flow visualization was carried out for some selected flow conditions. Experimental results were used to study boundary layer characteristics and to determine variations of loss coefficient with each of Reynolds number, flow incidence and turbulence intensity parameters for the test model.
©2014 by Walter de Gruyter Berlin/Boston
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- Scramjet Propulsive Flowpath Design and Numerical Simulation
- Base Pressure Control with Annular Ribs
- Weighted Fuzzy Risk Priority Number Evaluation of Turbine and Compressor Blades Considering Failure Mode Correlations
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- Characteristics of Co-flow Jets from Orifices
- Experimental Investigation of the Loss Coefficients in a Linear Cascade
- Application of the Ultrasonic Oil Film Thickness Measurement System in Bearing Chambers
- Fatigue Lifetime Assessment of Aircraft Engine Disc via Multi-source Information Fusion
- Improvement on Main/backup Controller Switching Device of the Nozzle Throat Area Control System for a Turbofan Aero Engine
- Numerical and Experimental Investigation of Cavitating Characteristics in Centrifugal Pump with Gap Impeller
Articles in the same Issue
- Frontmatter
- Analysis on Impulse Characteristics of PDRE with Exhaust Measurements
- Scramjet Propulsive Flowpath Design and Numerical Simulation
- Base Pressure Control with Annular Ribs
- Weighted Fuzzy Risk Priority Number Evaluation of Turbine and Compressor Blades Considering Failure Mode Correlations
- Effect of Compressibility on Contrail Ice Particle Growth in an Engine Jet
- Characteristics of Co-flow Jets from Orifices
- Experimental Investigation of the Loss Coefficients in a Linear Cascade
- Application of the Ultrasonic Oil Film Thickness Measurement System in Bearing Chambers
- Fatigue Lifetime Assessment of Aircraft Engine Disc via Multi-source Information Fusion
- Improvement on Main/backup Controller Switching Device of the Nozzle Throat Area Control System for a Turbofan Aero Engine
- Numerical and Experimental Investigation of Cavitating Characteristics in Centrifugal Pump with Gap Impeller
