scholarly journals Calculation of transonic flow in radial turbine blade cascade

2017 ◽  
Author(s):  
Straka Petr
Keyword(s):  
Turbine Blade ◽  
Transonic Flow ◽  
Blade Cascade ◽  
Radial Turbine

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.

Loss Predictions in the High-Pressure Film-Cooled Turbine Blade Cascade T120D by Mean of Wall-Resolved Large Eddy Simulation

2020 ◽  
Author(s):  
Mael Harnieh ◽  
Nicolas Odier ◽  
Jérôme Dombard ◽  
Florent Duchaine ◽  
Laurent Gicquel
Keyword(s):  
High Pressure ◽  
Large Eddy Simulation ◽  
Turbine Blade ◽  
Film Cooling ◽  
Load Prediction ◽  
Loss Assessment ◽  
Film Cooling Effectiveness ◽  
Eddy Simulation ◽  
Blade Cascade ◽  
Large Eddy

Abstract Film cooling is commonly used to protect turbine vanes and blades from the hot gases produced in the combustion chamber. The design and optimization of these systems can however only be achieved if a precise prediction of the fluid mechanics and film efficiency is guaranteed at a level where induced losses are fully mastered. Such a prerequisite induces at the numerical level to be able to identify and assess losses. In this context, the present study addresses loss assessment in a wall-resolved Large Eddy Simulation (LES) of the film-cooled high-pressure turbine blade cascade T120D from the European project AITEB II. The objectives are twofolds: (1) to evaluate the capacity of LES to predict adiabatic film cooling effectiveness in a mastered academic case; and (2) to investigate loss generation mechanisms in a fully anisothermal configuration. When it comes to LES predictions of T120D, the flow structure around the blade and the coolant jet organization are coherent with literature findings. Satisfactory agreements are furthermore retrieved for the pressure load prediction as well as the adiabatic film effectiveness if compared to the experiment. Loss generation is then investigated illustrating the fact that aerodynamics losses dominate mixing losses which are mainly located in the coolant film. This is in line with the temperature difference between the hot and coolant flows that is low for this experimental condition. Distinct contributions can however be made available by studying the local loss generation maps by means of Second Law Analysis if recast in the specific context of anisothermal flows when simulated by LES.

The best angle of hot steam injection holes in the 3D steam turbine blade cascade

2022 ◽  
Vol 173 ◽  
pp. 107387
Author(s):  
Amir Kafaei ◽  
Fahime Salmani ◽  
Esmail Lakzian ◽  
Włodzimierz Wróblewski ◽  
Mikhail S. Vlaskin ◽  
...  
Keyword(s):  
Steam Turbine ◽  
Turbine Blade ◽  
Steam Injection ◽  
Blade Cascade ◽  
Steam Turbine Blade

Coupled aeroelastic oscillations of a turbine blade row in 3D transonic flow

2001 ◽  
Vol 10 (4) ◽  
pp. 318-324 ◽  
Author(s):  
Vitaly Gnesin ◽  
Lyubov Kolodyazhnaya ◽  
Romuald Rzadkowski
Keyword(s):  
Turbine Blade ◽  
Transonic Flow ◽  
Blade Row

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.

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