Investigation on the Aerodynamic Performance of the Compressor Cascade Using Blended Blade and End Wall
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Weilin Yi
Abstract
Corner separation limits the increase of the aerodynamic loading in the compressor. Previous numerical studies indicate that the Blended Blade and End Wall (BBEW) technology is useful in delaying, or reducing, or even eliminating the corner separation. This paper presents combined experimental and numerical investigations on a BBEW cascade and its prototype. The experimental results show that the design of Blended Blade and End Wall (BBEW) can improve the performance of the cascade when the incidence angle was positive or at the design point, and the total pressure loss coefficient was reduced by 7 %-8 %. The performance improvement mainly located from 10 %-25 % span heights. Compared with the experiment data, the SST turbulence model shows the best results of the flow field. Based on the numerical results, the details of the flow field and the effect of the Blended Blade and End Wall (BBEW) design on the corner separation are discussed and analyzed.
Acknowledgements
The authors would like to express their deep appreciations to the National Natural Science Foundation of China for funding this work, Project No. 51476010.
Nomenclature
- b
Chord length
- b/t
Chord/Pitch
- h
Span height
- h/b
Aspect ratio
- i
Incidence angle
- p
Static pressure
- B
Axial chord length
- P
Total pressure
- T
Total temperature
- β1P
Geometry angle at inlet
- β2P
Geometry angle at outlet
- βb
Setting angle
- θ
Blade turn angle
- ζ
Energy loss coefficient
- ω
Total pressure loss coefficient
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Articles in the same Issue
- Frontmatter
- Investigation of a High Pressure Ratio Centrifugal Compressor with Wedge Diffuser and Pipe Diffuser
- Qualification of a Small Gas Turbine Engine as a Starter Unit
- Creep Life Prediction of Aircraft Turbine Disc Alloy Using Continuum Damage Mechanics
- Obtaining Dynamic Responses of Rotor from a Synchronizing Derived System Driven by Responses of Some Elastic Supports
- Effect of Swirling Secondary Flow on the Under-expanded Non-circular Supersonic Jets
- Life enhancement of Nozzle Guide Vane of an Aero Gas Turbine Engine through Pack Aluminization
- Investigation on the Aerodynamic Performance of the Compressor Cascade Using Blended Blade and End Wall
- Numerical Simulation of Terminal Shock Oscillation in Over/Under Turbine-Based Combined-Cycle Inlet
- Model Simulation and Design Optimization of a Can Combustor with Methane/Syngas Fuels for a Micro Gas Turbine
- Matching Performance Prediction Between Core Driven Fan Stage and High Pressure Compressor
- Effect of Variable Geometry Guide-Vane with Cylindrical Endwalls on Turbine Stage Performance
Articles in the same Issue
- Frontmatter
- Investigation of a High Pressure Ratio Centrifugal Compressor with Wedge Diffuser and Pipe Diffuser
- Qualification of a Small Gas Turbine Engine as a Starter Unit
- Creep Life Prediction of Aircraft Turbine Disc Alloy Using Continuum Damage Mechanics
- Obtaining Dynamic Responses of Rotor from a Synchronizing Derived System Driven by Responses of Some Elastic Supports
- Effect of Swirling Secondary Flow on the Under-expanded Non-circular Supersonic Jets
- Life enhancement of Nozzle Guide Vane of an Aero Gas Turbine Engine through Pack Aluminization
- Investigation on the Aerodynamic Performance of the Compressor Cascade Using Blended Blade and End Wall
- Numerical Simulation of Terminal Shock Oscillation in Over/Under Turbine-Based Combined-Cycle Inlet
- Model Simulation and Design Optimization of a Can Combustor with Methane/Syngas Fuels for a Micro Gas Turbine
- Matching Performance Prediction Between Core Driven Fan Stage and High Pressure Compressor
- Effect of Variable Geometry Guide-Vane with Cylindrical Endwalls on Turbine Stage Performance
