Aerodynamic Performance and Flow Characteristics of an Industrial Centrifugal Blower Volute with Varied Cross-Sectional Shapes/Area Ratios
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and
Abstract
An industrial centrifugal blower with different volutes is investigated numerically for its aerodynamic performance and flow characteristics. Towards this, six different volutes are designed from a combination of three cross sectional shapes (parallel, rectangular and circular) and two area ratios (ratio 4.0 and ratio 5.0). A detailed analysis is carried out at design and off-design mass flow rates. Parallel wall volutes not only perform better but also improve stage performance among all cross sectional shapes explored. Parallel and rectangular volutes with ratio 4.0 exhibit higher stage performance, while, circular volute performs better with ratio 5.0. Flow inside the volutes is characterized in terms of circumferential pressure distribution at volute inlet, pressure recovery coefficients and velocity distribution across different cross sections. This detailed flow field investigation revealed the underlying physics behind the loss mechanism inside different volutes. The overall investigations suggest that the parallel wall volute is most compact and efficient one.
Nomenclature
- Aθ
volute area of cross-section (m2)
- Cp
static pressure recovery coefficient
- Cω
total pressure loss coefficient
- Cm
meridional velocity (m/s)
- Cm R 5.0
meridional velocity (m/s) of R 5.0 volute
- CU
tangential velocity (m/s)
- CU R 5.0
tangential velocity (m/s) of R 5.0 volute
- CT
velocity perpendicular to volute cross section (m/s)
- Cs
velocity parallel to volute cross section (m/s)
- Ip
input power to impeller (W)
- m
mass flow rate (kg/s)
- P
static pressure (N/m2)
- P0
total pressure (N/m2)
- PU
- R/R2
normalized volute radius
- R
volute radius (R=Rθ for parallel wall and rectangular volute; R=Rθ−Rce for circular volute)
- U2
impeller tip velocity (m/s)
- W
isentropic specific work (m2/s2)
- Z/B2
ratio of axial position to blade height
- η
total to total isentropic efficiency of stage (%)
- Ψ
- φ
- Subscripts
- 0
inlet of suction duct
- 1
exit of suction duct
- 2
inlet of impeller
- 3
exit of impeller
- 4
inlet to volute
- 5
exit of volute
- d
design value
- Abbreviations
- B2
impeller exit width (m)
- B5
volute width (m)
- R2
impeller exit radius (m)
- BW
bottom wall of the volute
- H
hub of the impeller
- I
inlet of the volute
- IW
inlet duct wall
- PW
partition wall of the volute
- PS
pressure side
- S
shroud of the impeller
- SS
suction side
- SW
side wall of the volute
- T
tongue of the volute
- TW
top wall of the volute
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© 2019 Walter de Gruyter GmbH, Berlin/Boston
Articles in the same Issue
- Frontmatter
- Original Research Articles
- Optimization Design and Experimental Study of a Two-disk Rotor System Based on Multi-Island Genetic Algorithm
- Experimental Investigation of the Effect of the Probe Support Tail Structure on the Compressor Cascade Flow Field
- Investigation on Rotor-Labyrinth Seal System with Variable Rotating speed
- Numerical Prediction of Impact of Clearance on Rotordynamic Coefficients for Labyrinth Brush Seal
- CH* Luminance Distribution Application and a One-Dimensional Model of the Supersonic Combustor Heat Release Quantization
- Bleeding Control for Improving Internal Waverider Inlet Self-Starting ability
- Soot Formation and Its Effect in an Aero Gas Turbine Combustor
- Studies on the Effect of Staggering the Rear Rotor in a Counter Rotating Turbine with Respect to Flow and Performance Parameters
- Aerodynamic Performance and Flow Characteristics of an Industrial Centrifugal Blower Volute with Varied Cross-Sectional Shapes/Area Ratios
- CFD Design Study of a Pressure Probe for Centerline Static Pressure Measurement in Supersonic Ejectors
- The Performance of the Self-Supplying Vortex Generator Jets on a High-Speed Compressor Cascade
Articles in the same Issue
- Frontmatter
- Original Research Articles
- Optimization Design and Experimental Study of a Two-disk Rotor System Based on Multi-Island Genetic Algorithm
- Experimental Investigation of the Effect of the Probe Support Tail Structure on the Compressor Cascade Flow Field
- Investigation on Rotor-Labyrinth Seal System with Variable Rotating speed
- Numerical Prediction of Impact of Clearance on Rotordynamic Coefficients for Labyrinth Brush Seal
- CH* Luminance Distribution Application and a One-Dimensional Model of the Supersonic Combustor Heat Release Quantization
- Bleeding Control for Improving Internal Waverider Inlet Self-Starting ability
- Soot Formation and Its Effect in an Aero Gas Turbine Combustor
- Studies on the Effect of Staggering the Rear Rotor in a Counter Rotating Turbine with Respect to Flow and Performance Parameters
- Aerodynamic Performance and Flow Characteristics of an Industrial Centrifugal Blower Volute with Varied Cross-Sectional Shapes/Area Ratios
- CFD Design Study of a Pressure Probe for Centerline Static Pressure Measurement in Supersonic Ejectors
- The Performance of the Self-Supplying Vortex Generator Jets on a High-Speed Compressor Cascade
