A study of axial compressor blade optimization for operation in the low Reynolds number regime

1978 ◽  
Author(s):  
W. ROBERTS
Keyword(s):  
Reynolds Number ◽  
Low Reynolds Number ◽  
Axial Compressor ◽  
Compressor Blade ◽  
Blade Optimization ◽  
Low Reynolds

A Numerical Investigation of Transonic Axial Compressor Rotor Flow Using a Low-Reynolds-Number k–ε Turbulence Model

1999 ◽  
Vol 121 (1) ◽  
pp. 44-58 ◽  
Author(s):  
T. Arima ◽  
T. Sonoda ◽  
M. Shirotori ◽  
A. Tamura ◽  
K. Kikuchi
Keyword(s):  
Experimental Data ◽  
Reynolds Number ◽  
Turbulence Model ◽  
Low Reynolds Number ◽  
Axial Compressor ◽  
Numerical Results ◽  
Speed Condition ◽  
Transonic Axial Compressor ◽  
Low Reynolds ◽  
Design Speed

We have developed a computer simulation code for three-dimensional viscous flow in turbomachinery based on the time-averaged compressible Navier–Stokes equations and a low-Reynolds-number k–ε turbulence model. It is described in detail in this paper. The code is used to compute the flow fields for two types of rotor (a transonic fan NASA Rotor 67 and a transonic axial compressor NASA rotor 37), and numerical results are compared to experimental data based on aerodynamic probe and laser anemometer measurements. In the case of Rotor 67, calculated and experimental results are compared under the design speed to validate the code. The calculated results show good agreement with the experimental data, such as the rotor performance map and the spanwise distribution of total pressure, total temperature, and flow angle downstream of the rotor. In the case of Rotor 37, detailed comparisons between the numerical results and the experimental data are made under the design speed condition to assess the overall quality of the numerical solution. Furthermore, comparisons under the part-speed condition are used to investigate a flow field without passage shock. The results are well predicted qualitatively. However, considerable quantitative discrepancies remain in predicting the flow near the tip. In order to assess the predictive capabilities of the developed code, computed flow structures are presented with the experimental data for each rotor and the cause of the discrepancies is discussed.

Numerical Study About the Effect of the Low Reynolds Number on the Performance in an Axial Compressor

2008 ◽  
Vol 32 (2) ◽  
pp. 83-91
Author(s):  
Min-Suk Choi ◽  
Hee-Taeg Chung ◽  
Seong-Hwan Oh ◽  
Han-Young Ko ◽  
Je-Hyun Baek
Keyword(s):  
Reynolds Number ◽  
Numerical Study ◽  
Low Reynolds Number ◽  
Axial Compressor ◽  
Low Reynolds

scholarly journals Effects of Low Reynolds Number on Loss Characteristics in Transonic Axial Compressor

2010 ◽  
Vol 53 (181) ◽  
pp. 162-170 ◽  
Author(s):  
Minsuk CHOI ◽  
Je Hyun BAEK ◽  
Jun Young PARK ◽  
Seong Hwan OH ◽  
Han Young KO
Keyword(s):  
Reynolds Number ◽  
Low Reynolds Number ◽  
Axial Compressor ◽  
Transonic Axial Compressor ◽  
Low Reynolds

Numerical and Experimental Investigation of Low Reynolds Number Effects on Laminar Flow Separation and Transition in a Cascade of Compressor Blades

2000 ◽  
Author(s):  
Shunji Enomoto ◽  
C. Hah ◽  
G. V. Hobson
Keyword(s):  
Reynolds Number ◽  
Laminar Flow ◽  
Flow Separation ◽  
Low Reynolds Number ◽  
Numerical Procedure ◽  
Compressor Blade ◽  
Navier Stokes ◽  
Flow Transition ◽  
Reynolds Number Effects ◽  
Low Reynolds

The results of an experimental and numerical comparison of the effects of low Reynolds number on flow separation and transition in a controlled-diffusion compressor cascade are presented. The flow separation and subsequent flow transition are associated with low Reynolds number effects in the compressor blade rows. Current steady-state Reynolds-averaged Navier-Stokes codes with available turbulence and transition models do not calculate the current flow phenomena properly. An unsteady three-dimensional Navier-Stokes calculation that applies a third-order accurate upwind method has been performed and the numerical results are compared to the measurements in detail. The results from the current numerical procedure agree very well with the measurements in terms of laminar flow separation, reattachment, and subsequent flow transition at low Reynolds numbers. The present study indicates that flow separation and flow transition inside compressor blade rows at low Reynolds number are phenomena dominated by relatively larger eddies near the wall and can be simulated with the current type of unsteady numerical procedure.

scholarly journals A Numerical Investigation of Transonic Axial Compressor Rotor Flow Using a Low Reynolds Number k-ε Turbulence Model

1997 ◽  
Author(s):  
Toshiyuki Arima ◽  
Toyotaka Sonoda ◽  
Masatoshi Shirotori ◽  
Atsuhiro Tamura ◽  
Kazuo Kikuchi
Keyword(s):  
Experimental Data ◽  
Reynolds Number ◽  
Turbulence Model ◽  
Low Reynolds Number ◽  
Axial Compressor ◽  
Numerical Results ◽  
Speed Condition ◽  
Transonic Axial Compressor ◽  
Low Reynolds ◽  
Design Speed

We have developed a computer simulation code for three-dimensional viscous flow in turbomachinery based on the time-averaged compressible Navier-Stokes equations and a low Reynolds number k-ε turbulence model. It is described in detail in this paper. The code is used to compute the flow fields for two types of rotor (a transonic fan NASA Rotor 67 and a transonic axial compressor NASA rotor 37), and numerical results are compared to experimental data based on aerodynamic probe and laser anemometer measurements. In the case of Rotor 67, calculated and experimental results are compared under the design speed to validate the code. The calculated results show good agreement with the experimental data, such as the rotor performance map and the spanwise distribution of total pressure, total temperature, and flow angle downstream of the rotor. In the case of Rotor 37, detailed comparisons between the numerical results and the experimental data are made under the design speed condition to assess the overall quality of the numerical solution. Furthermore, comparisons under the part speed condition are used to investigate a flow field without passage shock. The results are well predicted qualitatively. However, considerable quantitative discrepancies remain in predicting the flow near the tip. In order to assess the predictive capabilities of the developed code, computed flow structures are presented with the experimental data for each rotor and the cause of the discrepancies is discussed.

scholarly journals 104 Studies on Tip Leakage Flow of Axial Compressor at a Low-Reynolds Number

2011 ◽  
Vol 2011.46 (0) ◽  
pp. 12-13
Author(s):  
Ken-ichi FUNAZAKI ◽  
Masafumi KUMAGAI ◽  
Kazunari MATUDA ◽  
Dai KADO ◽  
Guillaume PALLOT
Keyword(s):  
Reynolds Number ◽  
Low Reynolds Number ◽  
Axial Compressor ◽  
Leakage Flow ◽  
Tip Leakage Flow ◽  
Tip Leakage ◽  
Low Reynolds

scholarly journals Computation of Subsonic and Transonic Compressor Rotor Flow Taking Account of Reynolds Stress Anisotropy

1998 ◽  
Author(s):  
Toshiyuki Arima ◽  
Toyotaka Sonoda ◽  
Masatoshi Shirotori ◽  
Yoshihiro Yamaguchi
Keyword(s):  
Experimental Data ◽  
Reynolds Number ◽  
Reynolds Stress ◽  
Centrifugal Compressor ◽  
Low Reynolds Number ◽  
Axial Compressor ◽  
Compressor Rotor ◽  
Compressor Impeller ◽  
Overall Performance ◽  
Low Reynolds

A two-layer k-ε/algebraic Reynolds stress model (ARSM) has been adopted to the three-dimensional, Reynolds-averaged, Navier-Stokes code to include explicitly the Reynolds stress anisotropy. The code has been used to study the complex flow fields of a transonic axial compressor rotor (i.e., NASA Rotor 37) and a subsonic centrifugal compressor impeller (i.e., the backswept impeller of Krain, first reported in 1988). The computed results have been compared with those from a Baldwin-Lomax model, a low-Reynolds number k-ε turbulence model and actual experimental data. Calculated results for the axial compressor are compared with data reported by Suder in 1994. The suitability of the turbulence model to predict accurately the overall performance of the rotor, spanwise distributions of aerodynamic characteristics, and the wake flow profiles is assessed. Calculations for the centrifugal compressor impeller are compared with the experimental data reported by Hah and Krain in 1989. The usefulness of the turbulence models to predict accurately the overall performance of the impeller, the impeller-exit-velocity profile, and the meridional velocity and flow angle profiles at the cross-channel planes (via L2F measurements) has also been investigated. For modeling the turbulence of both the rotor and the impeller, reasonably good predictions have been obtained with the ARSM and the low-Reynolds number k-ε models, but have not been attainable using the Baldwin-Lomax model. The solutions obtained with the ARSM show better agreement with experimental data than those obtained with the other models. However, in some cases, the predicted differences between the ARSM and the low-Reynolds number k-ε models are not significant. The computed secondary flow and the relative helicity have also been used to investigate the effect of wall curvature and frame rotation on the flow field inside the centrifugal impeller for three operating conditions (i.e., design point, choke, and near surge) and the results are discussed.

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