scholarly journals Solution of Turbine Blade Cascade Flow Using an Improved Panel Method

2015 ◽  
Vol 2015 ◽  
pp. 1-6 ◽  
Author(s):  
Zong-qi Lei ◽  
Guo-zhu Liang
Keyword(s):  
Turbine Blade ◽  
Inviscid Flow ◽  
Panel Method ◽  
Experiment Data ◽  
Blade Cascade ◽  
Comparison With Experiment ◽  
Cascade Flow ◽  
Mesh Free ◽  
Blade Row ◽  
Flow Through

An improved panel method has been developed to calculate compressible inviscid flow through a turbine blade row. The method is a combination of the panel method for infinite cascade, a deviation angle model, and a compressibility correction. The resulting solution provides a fast flexible mesh-free calculation for cascade flow. A VKI turbine blade cascade is used to evaluate the method, and the comparison with experiment data is presented.

3-D Numerical Simulation of the Flow Through a Turbine Blade Cascade With Cooling Injection at the Leading Edge

1996 ◽  
Author(s):  
Dieter Bohn ◽  
Karsten Kusterer ◽  
Harald Schönenborn
Keyword(s):  
Numerical Simulation ◽  
Turbine Blade ◽  
Gas Turbines ◽  
Stokes Equations ◽  
Leading Edge ◽  
Body Region ◽  
Gas Temperature ◽  
Hot Gas ◽  
Blade Cascade ◽  
Flow Through

High process efficiencies and high power-weight ratios are two major requirements for the economic operation of present day gas turbines. This development leads to extremely high turbine inlet temperatures and adjusted pressure ratios. The permissible hot gas temperature is limited by the material temperature of the blade. Intensive cooling is required to guarantee an economically acceptable life of the components which are in contact with the hot gas. Although film-cooling has been successfully in use for a couple of years along the suction side and pressure side, problems occur in the vicinity of the stagnation point due to high stagnation pressures and opposed momentum fluxes. In this area basic investigations are necessary to achieve a reliable design of the cooled blade. In the present calculations, a code for the coupled simulation of fluid flow and heat transfer in solid bodies is employed. The numerical scheme works on the basis of an implicit finite volume method combined with a multi-block technique. The full, compressible 3-D Navier-Stokes equations are solved within the fluid region and the Fourier equation for beat conduction is solved within the solid body region. An elliptic grid generator is used for the generation of the structured computational grid, which is a combination of various C-type and H-type grids. Results of a 3-D numerical simulation of the flow through a turbine blade cascade with and without cooling ejection at the leading edge through two slots are presented. The results are compared with 2-D numerical simulations and experimental results. It is shown that the distribution of the coolant on the blade surface is influenced by secondary flow phenomena which can not be taken into account by the 2-D simulations. Further coupled simulations with non-adiabatic walls in the leading edge region are performed with realistic temperature ratios and compared to the same case with adiabatic walls. It is shown that in the case of non-adiabatic walls the temperature on the blade wall is significantly lower than in the case of adiabatic walls.

Differential interferometry with adjustable spatial carrier fringes for turbine blade cascade flow investigations

1998 ◽  
Vol 24 (2) ◽  
pp. 102-109 ◽  
Author(s):  
J. Woisetschläger ◽  
G. Pretzler ◽  
H. Jericha ◽  
N. Mayrhofer ◽  
H. P. Pirker
Keyword(s):  
Turbine Blade ◽  
Blade Cascade ◽  
Cascade Flow ◽  
Differential Interferometry

scholarly journals Numerical simulations of the 2D supersonic flow through the tip-section turbine blade cascade with a flat profile

2021 ◽  
Vol 15 (2) ◽  
Author(s):  
Josef Musil ◽  
Jaromír Příhoda ◽  
Jiří Fürst
Keyword(s):  
Numerical Simulations ◽  
Turbine Blade ◽  
Stokes Equations ◽  
Transition To Turbulence ◽  
Navier Stokes ◽  
Bypass Transition ◽  
Flow Angle ◽  
Blade Cascade ◽  
Flow Through ◽  
Flat Profile

Numerical simulations of 2D compressible flow through the tip-section turbine blade cascade with a flat profile and the supersonic inlet were carried out by the OpenFOAM code using the Favre-averaged Navier-Stokes equations completed by the γ-Re_θt bypass transition model with the SST turbulence model. Predictions completed for nominal regimes were concentrated particularly on the effect of the shock-wave/boundary layer interaction on the transition to turbulence. Further, the link between the inlet Mach number and the inlet flow angle i.e. the so called unique incidence rule was studied. Obtained numerical results were compared with experimental data covering optical and pressure measurements.

scholarly journals Solution of Plane Cascade Flow Using Improved Surface Singularity Methods

1982 ◽  
Vol 104 (3) ◽  
pp. 668-674 ◽  
Author(s):  
E. R. McFarland
Keyword(s):  
Solution Method ◽  
Inviscid Flow ◽  
External Flow ◽  
Surface Singularity ◽  
Solution Technique ◽  
Linear Cascade ◽  
Cascade Flow ◽  
Flow Through

A solution method has been developed for calculating compressible inviscid flow through a linear cascade of arbitrary blade shapes. The method uses advanced surface singularity formulations which were adapted from those found in current external flow analyses. The resulting solution technique provides a fast flexible calculation for flows through turbomachinery blade rows. The solution method and some examples of the method’s capabilities are presented.

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