Numerical investigation of intercoupling vibration of a mistuned turbomachinery compressor rotor wheel

1997 ◽  
Vol 29 (2) ◽  
pp. 150-158
Author(s):  
A. P. Zin'kovskii
Keyword(s):  
Numerical Investigation ◽  
Rotor Wheel ◽  
Compressor Rotor

Turbulence Model Influence on Numerical Investigation of Transonic Axial Compressor Rotor

2011 ◽  
Vol 308-310 ◽  
pp. 1519-1522
Author(s):  
Fang Xie ◽  
Chang Jiang Liu ◽  
You Jun Wang
Keyword(s):  
Experimental Data ◽  
Numerical Investigation ◽  
Turbulence Model ◽  
Characteristic Curve ◽  
Axial Compressor ◽  
Internal Flow ◽  
Turbulent Model ◽  
Compressor Rotor ◽  
Transonic Axial Compressor ◽  
Point Forecast

Numerical method using HI and HOH meshing combined B - L turbulent model and S - A turbulent model separately based on the Rotor 37 compressor Rotor was applied to the steady flow. results on pressure characteristic curve, stall point forecast etc were compared with related experimental data. This paper discussed calculation precision influenced by the turbulence model and numerical computation grid. This numerical investigation was basis for subsequent compressor internal flow field study.

Numerical investigation of a high-subsonic axial-flow compressor rotor with non-axisymmetric hub endwall

2010 ◽  
Vol 19 (1) ◽  
pp. 14-20 ◽  
Author(s):  
Shuzhen Hu ◽  
Xingen Lu ◽  
Hongwu Zhang ◽  
Junqiang Zhu ◽  
Qiang Xu
Keyword(s):  
Numerical Investigation ◽  
Axial Flow ◽  
Axial Flow Compressor ◽  
Compressor Rotor ◽  
Flow Compressor

3D Numerical Investigation of Tandem Airfoils for a Core Compressor Rotor

2008 ◽  
Author(s):  
Jonathan McGlumphy ◽  
Wing-Fai Ng ◽  
Steven R. Wellborn ◽  
Severin Kempf
Keyword(s):  
Turbulent Flow ◽  
Fluid Mechanics ◽  
Numerical Investigation ◽  
Boundary Layers ◽  
Three Dimensional ◽  
Compressor Blade ◽  
Stall Margin ◽  
Compressor Rotor ◽  
Blade Geometry

The tandem airfoil has potential to do more work as a compressor blade than a single airfoil without incurring higher losses. The goal of this work is to evaluate the fluid mechanics of a tandem rotor in the rear stages of a core compressor. As such, the results are constrained to shock-free, fully turbulent flow with thick endwall boundary layers at the inlet. A high hub-to-tip ratio 3D blade geometry was developed based upon the best-case tandem airfoil configuration from a previous 2D study. The 3D tandem rotor was simulated in isolation in order to scrutinize the fluid mechanisms of the rotor, which had not previously been well documented. A geometrically similar single blade rotor was also simulated under the same conditions for a baseline comparison. The tandem rotor was found to outperform its single blade counterpart by attaining a higher work coefficient, polytropic efficiency and numerical stall margin. An examination of the tandem rotor fluid mechanics revealed that the forward blade acts in a similar manner to a conventional rotor. The aft blade is strongly dependent upon the flow it receives from the forward blade, and tends to be more three-dimensional and non-uniform than the forward blade.

Parametric Investigation of Circumferential Grooves on Compressor Rotor Performance

2010 ◽  
Vol 132 (12) ◽  
Author(s):  
Yanhui Wu ◽  
Wuli Chu ◽  
Haoguang Zhang ◽  
Qingpeng Li
Keyword(s):  
Numerical Investigation ◽  
High Speed ◽  
Orthogonal Experiment ◽  
Experimental Investigations ◽  
Small Scale ◽  
Stall Margin ◽  
Compressor Rotor ◽  
Set Up ◽  
Compound Effect ◽  
Unloading Effect

This paper presents numerical and experimental investigations about grooved casing treatment with the help of a high-speed small-scale compressor rotor. First, the numerical investigation seeks to offer a contribution of understanding the working mechanism by which circumferential grooves improve stall margin. It is found that stall margin gain due to the presence of circumferential grooves arises from the suction-injection effect and the near-tip unloading effect. Based on that, the philosophy of design of experiment is then set up. Finally, parametric studies are carried out through systematical experiments. It is found that the orthogonal experiment and the factorial analyses are successful in identifying the “best casing configuration” in terms of stall margin improvement. However, the ineffectiveness of the deduction from simulations suggests that the secondary flow circulations on stall margin gain should not be neglected, and the overall contribution of each groove to stall margin gain depends on its unloading effect and the compound effect of suction-injection. Further numerical investigation will focus on how to set up quantitative criteria to evaluate the compound effect of suction-injection and the unloading effect on stall margin gain respectively in each groove.

3D Numerical Investigation of Tandem Airfoils for a Core Compressor Rotor

2010 ◽  
Vol 132 (3) ◽  
Author(s):  
Jonathan McGlumphy ◽  
Wing-Fai Ng ◽  
Steven R. Wellborn ◽  
Severin Kempf
Keyword(s):  
Turbulent Flow ◽  
Fluid Mechanics ◽  
Numerical Investigation ◽  
Boundary Layers ◽  
Three Dimensional ◽  
Compressor Blade ◽  
Stall Margin ◽  
Compressor Rotor ◽  
Blade Geometry

The tandem airfoil has potential to do more work as a compressor blade than a single airfoil without incurring higher losses. The goal of this work is to evaluate the fluid mechanics of a tandem rotor in the rear stages of a core compressor. As such, the results are constrained to shock-free fully turbulent flow with thick endwall boundary layers at the inlet. A high hub-to-tip ratio 3D blade geometry was developed based on the best-case tandem airfoil configuration from a previous 2D study. The 3D tandem rotor was simulated in isolation, in order to scrutinize the fluid mechanisms of the rotor, which had not been previously well documented. A geometrically similar single blade rotor was also simulated under the same conditions for a baseline comparison. The tandem rotor was found to outperform its single blade counterpart by attaining a higher work coefficient, polytropic efficiency, and numerical stall margin. An examination of the tandem rotor fluid mechanics revealed that the forward blade acts in a similar manner to a conventional rotor. The aft blade is strongly dependent on the flow it receives from the forward blade, and tends to be more three-dimensional and nonuniform than the forward blade.

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