A Systematic Computational Design System for Turbine Cascades, Airfoil Geometry, and Blade-to-Blade Analysis

1984 ◽  
Vol 106 (3) ◽  
pp. 598-605 ◽  
Author(s):  
Z.-Q. Ye
Keyword(s):  
Boundary Layer ◽  
Leading Edge ◽  
Computational Design ◽  
Design System ◽  
Finite Area ◽  
Streamline Curvature ◽  
Boundary Layer Analysis ◽  
Curvature Analysis ◽  
Layer Analysis ◽  
Turbine Cascades

This paper describes a systematic computational design system for two-dimensional turbine cascades. The system includes a sequence of calculations in which airfoil profiles are designed from velocity diagram requirements and specified geometric parameters, followed by an inviscid global streamline curvature analysis, a magnified reanalysis around the leading edge, and a transitional profile boundary layer and wake mixing analysis. A finite area technique and a body-fitted mesh are used for the reanalysis. The boundary layer analysis is performed using the dissipation-integral method of Walz which has been modified in the present application. Several turbine airfoil profile geometry designs are presented. Also two sample cascade design cases and their calculated performance for a range of Mach numbers and incidence angles are given and discussed.

A Systematic Computational Design System for Turbine Cascades, Airfoil Geometry and Blade-to-Blade Analysis

1983 ◽  
Author(s):  
Z.-Q. Ye
Keyword(s):  
Boundary Layer ◽  
Leading Edge ◽  
Computational Design ◽  
Design System ◽  
Finite Area ◽  
Streamline Curvature ◽  
Boundary Layer Analysis ◽  
Curvature Analysis ◽  
Layer Analysis ◽  
Turbine Cascades

This paper describes a systematic computational design system for two-dimensional turbine cascades. The system includes a sequence of calculations in which airfoil profiles are designed from velocity diagram requirements and specified geometric parameters, followed by an inviscid global streamline curvature analysis, a magnified reanalysis around the leading edge, and a transitional profile boundary layer and wake mixing analysis. A finite area technique and a body-fitted mesh are used for the reanalysis. The boundary layer analysis is performed using the dissipation-integral method of Walz which has been modified in the present application. Several turbine airfoil profile geometry designs are presented. Also two sample cascade design cases and their calculated performance for a range of Mach numbers and incidence angles are given and discussed.

scholarly journals Boundary layer analysis and heat transfer of a nanofluid

2014 ◽  
Vol 17 (2) ◽  
pp. 401-412 ◽  
Author(s):  
M. M. MacDevette ◽  
T. G. Myers ◽  
B. Wetton
Keyword(s):  
Heat Transfer ◽  
Boundary Layer ◽  
Boundary Layer Analysis ◽  
Layer Analysis

Computational Design and Experimental Evaluation of Using a Leading Edge Fillet on a Gas Turbine Vane

2001 ◽  
Author(s):  
G. A. Zess ◽  
K. A. Thole
Keyword(s):  
Boundary Layer ◽  
Flow Field ◽  
Pressure Gradient ◽  
Gas Turbine ◽  
Total Pressure ◽  
Guide Vane ◽  
Leading Edge ◽  
Field Measurements ◽  
Computational Design ◽  
Horseshoe Vortex

With the desire for increased power output for a gas turbine engine comes the continual push to achieve higher turbine inlet temperatures. Higher temperatures result in large thermal and mechanical stresses particularly along the nozzle guide vane. One critical region along a vane is the leading edge-endwall juncture. Based on the assumption that the approaching flow to this juncture is similar to a two-dimensional boundary layer, previous studies have shown that a horseshoe vortex forms. This vortex forms because of a radial total pressure gradient from the approaching boundary layer. This paper documents the computational design and experimental validation of a fillet placed at the leading edge-endwall juncture of a guide vane to eliminate the horseshoe vortex. The fillet design effectively accelerated the incoming boundary layer thereby mitigating the effect of the total pressure gradient. To verify the CFD studies used to design the leading edge fillet, flow field measurements were performed in a large-scale, linear, vane cascade. The flow field measurements were performed with a laser Doppler velocimeter in four planes orientated orthogonal to the vane. Good agreement between the CFD predictions and the experimental measurements verified the effectiveness of the leading edge fillet at eliminating the horseshoe vortex. The flowfield results showed that the turbulent kinetic energy levels were significantly reduced in the endwall region because of the absence of the unsteady horseshoe vortex.

Boundary Layer Analysis of Exothermic and Endothermic Kind of Chemical Reaction in the Flow of Non-Darcian Unsteady Micropolar Fluid along an Infinite Vertical Surface

2017 ◽  
Vol 28 ◽  
pp. 90-101 ◽  
Author(s):  
O.K. Koriko ◽  
A.J. Omowaye ◽  
Isaac Lare Animasaun ◽  
Idris O. Babatunde
Keyword(s):  
Boundary Layer ◽  
Differential Equations ◽  
Chemical Reaction ◽  
Micropolar Fluid ◽  
Local Heat Transfer ◽  
Flow Region ◽  
Local Similarity ◽  
Suction Parameter ◽  
Boundary Layer Analysis ◽  
Layer Analysis

The problem of unsteady non – Newtonian flow past a vertical porous surface in the presence of thermal radiation is investigated. Using the theory of boundary layer analysis, the flow of micropolar fluid in the presence of exothermic and endothermic kind of chemical reaction is considered. It is assumed that the relationship between the flow rate and the pressure drop as the fluid flows over a porous medium is non – linear. Using local similarity transformation, the governing partial differential equations of the physical model are reduced to ordinary differential equations. The corresponding boundary value problem is solved numerically using shooting method along with Runge-Kutta Gill method together with quadratic interpolation. It is found that increase in micro-rotation parameter increases the velocity while the micro- rotation decreases across the flow region. Maximum micro-rotation of tiny particles is guaranteed at higher values of suction parameter. Local heat transfer rate decreases with an increase in exothermic /endothermic parameter.

Sign in / Sign up

Export Citation Format

Share Document