Assessment of Rotor-Stator Interface Boundary Condition Techniques for Modeling Axial Flow Turbines

Zaki, Mina; Iyengar, Vishwas; Sankar, Lakshmi N.

doi:10.2514/6.2006-4619

Cited by 7 publications

(3 citation statements)

References 5 publications

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“…The use of fence in secondary wall treatment has a promising use in the secondary flow loss treatment when compared with suction, blowing and air injection [12]. Software's like GT TURO3D(ttsGeorgia Tech Turbo machinery 3D), ANSYS CFX, NUMECA, MATLAB and ICEM CFD was used to model the axial flow turbine [5,6,8].…”

Section: Literature Reviewmentioning

confidence: 99%

The Performance Enhancement of Axial Flow Turbine Using Numerical Technique

al.¹

2019

IJMPERD

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This paper aims to study the performance enhancement of subsonic axial flow turbine using numerical technique. R123 Organic Rankine Cycle (ORC) with high density is considered as the working fluid. A single stage axial flow turbine consisting of stator and rotor is used to carry out the analysis. The numerical analysis is carried out using ANSYS R18.1 version. The parameters considered to design the turbine geometry are tip diameter, hub diameter, blade height, half wedge angle of leading and trailing edge and number of blades of the stator and rotor. The design and study of axial flow turbine is mainly focused for engineers and technical researchers working in the field of ORC and engine design. Grid independence test performed with different mesh size to keep the computational economy intact. The experimental results are later compared with the theoretical calculation for verification.

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Section: Literature Reviewmentioning

confidence: 99%

The Performance Enhancement of Axial Flow Turbine Using Numerical Technique

al.¹

2019

IJMPERD

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“…Recently an isolated blade row three dimensional compressible unsteady flow solver initially developed by Niazi et al 33 was successfully modified to include multistage capabilities by Zaki et al 34 .…”

Section: Computational Studies On Compressor Performancementioning

confidence: 99%

“…Other types of rotor-stator interface boundary conditions have been investigated by Zaki and Iyengar 34 , but it was found that the presently used characteristics boundary conditions ensure the information propagates correctly between blade rows.…”

Section: Rotor-stator Interface Boundary Conditionsmentioning

confidence: 99%

A First-Principles Based Methodology for Design of Axial Compressor Configurations

Iyengar

Sankar

Denney

2007

Volume 6: Turbo Expo 2007, Parts a and B

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A multi-objective technique for designing single stage compressors is described. The blade geometry is defined as a function of known parametric equations, and the coefficient multipliers are viewed as design variables. A design of experiment approach is used to reduce the large combinations of design variables into a smaller subset. A response surface method is used to approximate the performance (total pressure rise, and adiabatic efficiency) as a function of design variables, and an optimum configuration is determined. This method has been applied to a rotor-stator combination similar to NASA Stage 35 with encouraging results.

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