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The rotor design variables are: chord and twist distribution, blade length, rated rotational speed and structural thicknesses along the span.
The purpose of this paper is to present the advantages of the direct presCrIbed suRface Curvature distribution bLade dEsign (CIRCLE) method for the design of high-efficiency turbomachinery blades.
The PresCrIbed suRface Curvature distribution bLade dEsign (CIRCLE) method, proposed by T Korakianitis, is a direct method for designing (or redesigning) high efficiency turbomachinery and fan blades, and isolated airfoils.
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The purpose of this paper is to illustrate the advantages of the direct surface-curvature distribution blade-design method, originally proposed by Korakianitis, for the leading-edge design of turbine blades, and by extension for other types of airfoil shapes.
The main emphasis of this study was on three dimensional behavior of the temperature distribution in blade of the 1st stage high pressure turbine.
In view of the fact that the substantial part of impeller power draw is due to pressure drag, pressure distribution across blades is a measure for impeller performance in food-blending operations.
As can be seen in Fig. 6, the pattern of fructan oligomer distribution in blades followed a comparable trend for both L. perenne lines and at both temperature regimes (Fig. 6).
Designed twist angle variation distributions along blades are then introduced to the baseline model to characterise the ATB nature.
When the deflections of the blades are plotted with respect to their position angle, distribution of the blade deflections has a sinusoidal shape.
The load distribution on the blade becomes well-proportioned due to the increased loading in the blade root, and it is advantageous to the reduction of the vibratory force and the blade tip vortex.
A process for numerical analysis of radial circulation distribution of propeller blade is proposed and presented.
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