scholarly journals Numerical and Theoretical Investigations Concerning the Continuous-Surface-Curvature Effect in Compressor Blades

Energies ◽  
2014 ◽  
Vol 7 (12) ◽  
pp. 8150-8177 ◽  
Author(s):  
Yin Song ◽  
Chun-Wei Gu ◽  
Yao-Bing Xiao
Keyword(s):  
Surface Curvature ◽  
Curvature Effect ◽  
Compressor Blades ◽  
Theoretical Investigations ◽  
Continuous Surface

The Surface Curvature Effect of Single-Walled Carbon Nanotube on Its Cation-π Interaction with Monovalent Cations

2012 ◽  
Vol 9 (12) ◽  
pp. 2107-2112
Author(s):  
Arthit Vongachariya ◽  
Chularat Iamsamai ◽  
Oraphan Saengsawang ◽  
Thanyada Rungrotmongkol ◽  
Stephan T. Dubas ◽  
...  
Keyword(s):  
Carbon Nanotube ◽  
Surface Curvature ◽  
Curvature Effect ◽  
Monovalent Cations ◽  
Single Walled Carbon Nanotube ◽  
Single Walled Carbon

Surface Curvature Effect on Slot-Air-Jet Impingement Cooling Flow and Heat Transfer Process

1991 ◽  
Vol 113 (4) ◽  
pp. 858-864 ◽  
Author(s):  
C. Gau ◽  
C. M. Chung
Keyword(s):  
Heat Transfer ◽  
Nusselt Number ◽  
Transfer Process ◽  
Convex Surface ◽  
Heat Transfer Process ◽  
Surface Curvature ◽  
Curvature Effect ◽  
Impingement Cooling ◽  
Cooling Flow ◽  
Air Jet

Experiments are performed to study surface curvature effects on the impingement cooling flow and the heat transfer processes over a concave and a convex surface. A single air jet issuing from different size slots continuously impinges normally on the concave side or the convexside of a heated semicylindrical surface. An electrical resistance wire is used to generate smoke, which allows us to visualize the impinging flow structure. The local heat transfer Nusselt number along the surfaces is measured. For impingement on a convex surface, three-dimensional counterrotating vortices on the stagnation point are initiated, which result in the enhancement of the heat transfer process. For impingement on a concave surface, the heat transfer Nusselt number increases with increasing surface curvature, which suggests the initiation of Taylor–Go¨rtler vortices along the surface. In the experiment, the Reynolds number ranges from 6000 to 350,000, the slot-to-plate spacing from 2 to 16, and the diameter-to-slot-width ratio D/b from 8 to 45.7. Correlations of both the stagnation point and the average Nusselt number over the curved surface, which account for the surface curvature effect, are presented.

Numerical investigation of surface curvature effect on the self-propelled capability of coalesced drops

2020 ◽  
Vol 32 (12) ◽  
pp. 122117
Author(s):  
Yan Chen ◽  
Ahmed Islam ◽  
Mark Sussman ◽  
Yongsheng Lian
Keyword(s):  
Numerical Investigation ◽  
Surface Curvature ◽  
The Self ◽  
Curvature Effect

Longitudinal surface curvature effect in magnetohydrodynamics

1975 ◽  
Vol 9 (4) ◽  
pp. 301-310
Author(s):  
N. G. Bodas ◽  
B. K. Gupta
Keyword(s):  
Surface Curvature ◽  
Curvature Effect

The Surface Curvature Effect on Performance of a Laboratory Scale Tidal Turbine

2019 ◽  
pp. 101-113
Author(s):  
Kaiming Ai ◽  
Eldad Avital ◽  
Xiang Shen ◽  
Abdus Samad ◽  
Nithya Venkatesan
Keyword(s):  
Surface Curvature ◽  
Laboratory Scale ◽  
Curvature Effect ◽  
Tidal Turbine

Two- and Three-Dimensional Prescribed Surface Curvature Distribution Blade Design (CIRCLE) Method for the Design of High Efficiency Turbines, Compressors, and Isolated Airfoils

2013 ◽  
Vol 135 (4) ◽  
Author(s):  
T. Korakianitis ◽  
M. A. Rezaienia ◽  
I. A. Hamakhan ◽  
A. P. S. Wheeler
Keyword(s):  
Turbine Blade ◽  
High Efficiency ◽  
Turbine Blades ◽  
Circle Method ◽  
Three Dimensional ◽  
Leading Edge ◽  
Surface Curvature ◽  
Blade Design ◽  
Compressor Blades ◽  
Curvature Distribution

The prescribed surface curvature distribution blade design (CIRCLE) method is presented for the design of two-dimensional (2D) and three-dimensional (3D) blades for axial compressors and turbines, and isolated blades or airfoils. The original axial turbine blade design method is improved, allowing it to use any leading-edge (LE) and trailing-edge (TE) shapes, such as circles and ellipses. The method to connect these LE and TE shapes to the remaining blade surfaces with curvature and slope of curvature continuity everywhere along the streamwise blade length, while concurrently overcoming the “wiggle” problems of higher-order polynomials is presented. This allows smooth surface pressure distributions, and easy integration of the CIRCLE method in heuristic blade-optimization methods. The method is further extended to 2D and 3D compressor blades and isolated airfoil geometries providing smooth variation of key blade parameters such as inlet and outlet flow angles, stagger angle, throat diameter, LE and TE radii, etc. from hub to tip. One sample 3D turbine blade geometry is presented. The efficacy of the method is examined by redesigning select blade geometries and numerically evaluating pressure-loss reduction at design and off-design conditions from the original blades: two typical 2D turbine blades; two typical 2D compressor blades; and one typical 2D isolated airfoil blade geometries are redesigned and evaluated with this method. Further extension of the method for centrifugal or mixed-flow impeller geometries is a coordinate transformation. It is concluded that the CIRCLE method is a robust tool for the design of high-efficiency turbomachinery blades.

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