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 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.

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

A Comparison Between Full and Simplified Navier-Stokes Equation Solutions for Rotating Blade Cascade Flow on S1 Stream Surface of Revolution

1985 ◽  
Author(s):  
Chen Naixing ◽  
Zhang Fengxian
Keyword(s):  
Stokes Equation ◽  
Stokes Equations ◽  
Navier Stokes ◽  
Navier Stokes Equation ◽  
Navier Stokes Equations ◽  
Stream Surface ◽  
Surface Of Revolution ◽  
Rotating Blade ◽  
Blade Cascade ◽  
Cascade Flow

A method for solving the Navier-Stokes equations of the rotating blade cascade flow on S1 stream surface of revolution is developed in the present paper. In this paper a complete set of full and simplified Navier-Stokes equations is given which includes stream-function equation, energy equation and entropy equation, equation of state for a perfect gas, formula for estimating density and formulas for calculating viscous forces, work done by viscous force, dissipation function and heat-transfer term. A comparison between the full and the simplified Navier-Stokes equations is made. The viscous terms of both full and simplified Navier-Stokes equation solutions are also compared in the present paper. The comparison shows that the simplified Navier-Stokes equations are applicable.

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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