scholarly journals INVESTIGATION OF COMPRESSIBLE FLOW THROUGH A TURBINE BLADE CASCADE FOR VARIOUS TRANSONIC FLOW REGIMES

2021 ◽  
Vol 61 (SI) ◽  
pp. 110-116
Author(s):  
Petr Louda ◽  
Jaromír Příhoda ◽  
Pavel Šafařík
Keyword(s):  
Turbine Blade ◽  
Transonic Flow ◽  
Incidence Angle ◽  
Separated Flows ◽  
Transition To Turbulence ◽  
Bypass Transition ◽  
Flow Conditions ◽  
Blade Cascade ◽  
Flow Through ◽  
Transition Models

This paper deals with the numerical simulation of 2D transonic flow through the SE1050 turbine blade cascade at various flow conditions. The first one concerns the design operation with a zero incidence angle involved in the ERCOFTAC Database CFD-QNET and the second one with a +20° incidence angle corresponding to an off-design operation. Advanced mathematical models with two different models of the bypass transition to turbulence were applied for the simulation of different regimes of transonic flows as well as with attached and separated flows. Transition models proposed by Dick et al. [1] and by Menter and Smirnov [2] are based on transport equations for the intermittency coefficient. Numerical results were compared with experimental data based on the optical and pressure measurements.

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 Simulation of transitional flows through a turbine blade cascade with heat transfer for various flow conditions

2017 ◽  
Vol 143 ◽  
pp. 02118 ◽  
Author(s):  
Petr Straka ◽  
Jaromír Příhoda ◽  
Martin Kožíšek ◽  
Jiří Fürst
Keyword(s):  
Heat Transfer ◽  
Turbine Blade ◽  
Flow Conditions ◽  
Transitional Flows ◽  
Blade Cascade

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.

Assessment of Laminar-Turbulent Transition Models for Turbomachinery Flow Computations

2005 ◽  
Author(s):  
L. Cutrone ◽  
P. De Palma ◽  
G. Pascazio ◽  
M. Napolitano
Keyword(s):  
Incompressible Flows ◽  
Navier Stokes ◽  
Test Case ◽  
Bypass Transition ◽  
Turbine Cascade ◽  
Turbulent Transition ◽  
Complex Test ◽  
Flow Through ◽  
Transition Models ◽  
Intermittency Factor

This paper provides a thorough comparison of different laminar-to-turbulent bypass transition models. The models are based on combinations of two transition-onset correlations and three intermittency factor models. They have been embedded in a Reynolds averaged Navier–Stokes solver employing a low-Reynolds number k–ω turbulence model. The performance of the transition models have been validated by computing three well documented incompressible flows over a flat plate, namely, test T3A, T3B, and T3C2 of ERCOFTAC SIG 10, with different free-stream conditions, the latter being characterized by non-zero pressure gradient. Finally, a more complex test case, namely the two-dimensional compressible flow through a linear turbine cascade, has been considered, for which detailed experimental data are available in the literature.

scholarly journals Effect of inlet turbulence on compressible flow through the tip-section turbine blade cascade with supersonic inlet

2018 ◽  
Vol 168 ◽  
pp. 02007
Author(s):  
Petr Straka ◽  
Jaromír Příhoda ◽  
David Fenderl ◽  
Bartoloměj Rudas
Keyword(s):  
Compressible Flow ◽  
Turbine Blade ◽  
Reynolds Stress Model ◽  
Numerical Code ◽  
Bypass Transition ◽  
Free Stream Turbulence ◽  
Blade Cascade ◽  
Supersonic Inlet ◽  
Commercial Code ◽  
Inlet Conditions

The contribution deals with the numerical simulation of 2D compressible flow though the tip-section turbine blade cascade with the supersonic inlet boundary conditions. The simulation was carried out by the in-house numerical code using the explicit algebraic Reynolds stress model completed by the bypass transition model with the algebraic equation for the intermittency coefficient. The γ-Re model implemented in the commercial code Fluent was used for the comparison. Predictions carried out for the nominal conditions were focused on the effect of inlet free-stream turbulence on the flow structure in the blade cascade under supersonic inlet conditions. Numerical results were compared with experimental data.

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.

Sign in / Sign up

Export Citation Format

Share Document