Investigation of endwall effect on transitional flow inside compressor cascade passage at low Reynolds number

2021 ◽  
Vol 33 (11) ◽  
pp. 117108
Author(s):  
Zhihui Li ◽  
Ramesh K. Agarwal
Keyword(s):  
Reynolds Number ◽  
Low Reynolds Number ◽  
Transitional Flow ◽  
Compressor Cascade ◽  
Low Reynolds

scholarly journals Challenging low Reynolds - SWT blade aerodynamics

2018 ◽  
Vol 234 ◽  
pp. 01004 ◽  
Author(s):  
Damian Kądrowski ◽  
Michał Kulak ◽  
Michał Lipian ◽  
Małgorzata Stępień ◽  
Piotr Baszczyński ◽  
...  
Keyword(s):  
Reynolds Number ◽  
Low Reynolds Number ◽  
Model Performance ◽  
Transitional Flow ◽  
Flow Conditions ◽  
Scaled Model ◽  
Low Wind Speed ◽  
Speed Flow ◽  
Low Reynolds ◽  
Manufacturing Techniques

One of the main issues related to the design and development of small wind turbines (SWTs) is the low Reynolds number. Operation in the transitory regime makes the rotor aerodynamic analysis a challenging task. Project GUST (Generative Urban Small Turbine) realized currently at the Institute of Turbomachinery (Lodz University of Technology, Poland) is devoted to the development of SWT (D = 1.6 m) for low-Reynolds number (low wind speed) flow conditions. The emphasis is on the blade design, aiming at improving the rotor aerodynamic efficiency. The paper will highlight the rotor design process, based on contemporary methods of experiment-simulation integration approach and use of rapid manufacturing techniques. In-house wind tunnel measurements of a scaled model performance were executed. A numerical analysis using dedicated software (QBlade) was conducted in parallel. A comparison between the obtained results indicated that the chosen numerical tools are capable of providing a reliable output, even in complex, transitional flow conditions. Bearing in mind the above observations, QBlade was incorporated into the development process of a completely new blade geometry which would increase rotor performance. The selected design has indeed prove to show better power outcome in an additional experimental campaign.

J055031 Study on the Tip Leakage Flow in a Linear Compressor Cascade at a Low Reynolds Number : Verification of Shroud Effects

2013 ◽  
Vol 2013 (0) ◽  
pp. _J055031-1-_J055031-5
Author(s):  
Hideo TANIGUCHI ◽  
Ken-ichi FUNAZAKI ◽  
Masahiro KATO ◽  
Masafumi KUMAGAI ◽  
Ryutaro ISHIMURA ◽  
...  
Keyword(s):  
Reynolds Number ◽  
Low Reynolds Number ◽  
Leakage Flow ◽  
Compressor Cascade ◽  
Tip Leakage Flow ◽  
Linear Compressor ◽  
Tip Leakage ◽  
Low Reynolds ◽  
Linear Compressor Cascade

Investigation of Low Reynolds Number Experiment and Numerical Simulation on Compressor Cascade

2011 ◽  
Author(s):  
Anping Hou ◽  
Shujun Shan ◽  
Yu Wu ◽  
Daijun Ling ◽  
Zhengli Jiang
Keyword(s):  
Numerical Simulation ◽  
Reynolds Number ◽  
Low Reynolds Number ◽  
Gamma Transition ◽  
Compressor Cascade ◽  
Mach Number Distribution ◽  
Oil Flow ◽  
Negative Effect ◽  
Low Reynolds ◽  
High Reynolds

This paper focuses on the compressor cascade experiment and numerical simulation at order 105 Reynolds number. A cascade tunnel simulated low Reynolds number condition under high subsonic speed. In a series of experiments (Re = 0.9 × 105∼5.0 × 105), oil flow visualization tests were used to indicate boundary layer development of the cascade surface. The results show that the performance of cascades deteriorates rapidly when the Reynolds number decreases to a certain extent. Comparison of results between the tests and calculations demonstrates that the real cascade experimental environment must be considered, such as the effect of the end wall. Flow separation and transition can be predicted accurately by using SST turbulence and Gamma transition models. Through modifying parameters of the Gamma transition model, the profile Mach number distribution in numerical simulations exhibits good agreement with experiments. Response surface methodology was adopted for the design process to minimize the total pressure loss of cascades at the design point. In addition, the optimized result has little negative effect on the high Reynolds number region.

Airfoil Heat Transfer Calculation Using a Low Reynolds Number Version of a Two-Equation Turbulence Model

1985 ◽  
Vol 107 (1) ◽  
pp. 60-67 ◽  
Author(s):  
J. H. Wang ◽  
H. F. Jen ◽  
E. O. Hartel
Keyword(s):  
Heat Transfer ◽  
Experimental Data ◽  
Reynolds Number ◽  
Turbulence Model ◽  
Low Reynolds Number ◽  
Transitional Flow ◽  
Zone Model ◽  
Suction Surface ◽  
Free Stream Turbulence ◽  
Low Reynolds

A two-dimensional, boundary-layer program, STAN5, was modified to incorporate a low-Reynolds number version of the K-ε, two-equation turbulence model for the predictions of flow and heat transfer around turbine airfoils. The K-ε, two-equation model with optimized empirical correlations was used to account for the effects of free-stream turbulence and transitional flow. The model was compared with experimental flat plate data and then applied to turbine airfoil heat transfer prediction. A two-zone model was proposed for handling the turbulent kinetic energy and dissipation rate empirically at the airfoil leading edge region. The result showed that the predicted heat transfer coefficient on the airfoil agreed favorably with experimental data, especially for the pressure side. The discrepancy between predictions and experimental data of the suction surface normally occurred at transitional and fully turbulent flow regions.

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