Subsonic Stall Flutter of a Linear Turbine Blade Cascade Using Experimental and CFD Analysis

2021 ◽  
Author(s):  
Vaclav Slama ◽  
Bartolomej Rudas ◽  
Jiri Ira ◽  
Ales Macalka ◽  
Petr Eret ◽  
...  
Keyword(s):  
Turbine Blade ◽  
Cfd Analysis ◽  
Blade Cascade ◽  
Stall Flutter

Subsonic Stall Flutter of a Linear Turbine Blade Cascade Using Experimental and CFD Analysis

2020 ◽  
Author(s):  
Vaclav Slama ◽  
Bartolomej Rudas ◽  
Jiri Ira ◽  
Ales Macalka ◽  
Petr Eret ◽  
...  
Keyword(s):  
Turbine Blade ◽  
Separation Bubble ◽  
Turbine Blades ◽  
Leading Edge ◽  
Travelling Wave ◽  
Computational Domain ◽  
Steam Turbines ◽  
Suction Surface ◽  
Blade Cascade ◽  
Stall Flutter

Abstract Stall flutter of long blades influences the operation safety of the large steam turbines in off-design conditions. As angles of attack are typically high, a partial or complete separation of the flow from the blade surface occurs. The prediction of stall flutter of turbine blades is a crucial task in the design and development of modern turbomachinery units and reliable design tools are necessary. In this work, aerodynamic stability of a linear turbine blade cascade is tested experimentally at high angle of attack +15°, Ma = 0.2 and the reduced frequency of 0.38. Controlled flutter testing has been performed in a travelling wave mode approach for the torsion with the motion amplitude of 0.5°. In addition, ANSYS CFX with SST k-ω turbulent model is used for URANS simulations of a full-scale computational domain. A separation bubble formed on suction surface near the leading edge has been found in CFD results for each blade. Excellent agreement between the experimental and numerical results in stability maps has been achieved for this case under investigation. This is encouraging and both experimental and numerical techniques will be tested further.

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

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

Wind Turbine Blade Design and Analysis With Tubercle Technology

2012 ◽  
Author(s):  
Sourabh Kumar ◽  
R. S. Amano
Keyword(s):  
Wind Turbine ◽  
Flow Pattern ◽  
Turbine Blade ◽  
Turbine Blades ◽  
Cad Model ◽  
Blade Design ◽  
Cfd Analysis ◽  
Straight Blade ◽  
Turbine Blade Design ◽  
Insight Into

The objective of this project is to construct a CAD model for tubercle wind turbine. Once the model is developed a complete CFD analysis of the flow pattern around the wind turbine will be carried out. The main objective of the study is to analyze and compare the performance of the tubercle wind turbine with the usual wind turbine. The power developed by both the turbine blades can be compared to support the use of tubercle. The tubercles are very effective for increasing the lift without stalling. The main objective of this project is to study the aerodynamic advantages of tubercle turbine blade. The effort will be to compare the obtained results with the straight blade of the same airfoil. This will provide insight into the advantages of using the tubercle blade. This technology being new the study is done numerically to study the overall effect of the tubercle.

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.

Numerical Analysis of Two-Dimensional Turbine Blade Cascade by Cartesian Mesh CFD

2018 ◽  
Vol 2018.55 (0) ◽  
pp. C023
Author(s):  
Yuki IMURA ◽  
Daisuke SASAKI ◽  
Takaya KOJIMA ◽  
Takashi MISAKA ◽  
Shigeru OBAYASHI
Keyword(s):  
Numerical Analysis ◽  
Turbine Blade ◽  
Two Dimensional ◽  
Cartesian Mesh ◽  
Blade Cascade
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