Elliptic trailing edge for a turbine blade: Aerodynamic and aerothermal effects

Mahmoud Moustafa El-Gendi; Sang Wook Lee; Chang Yeol Joh; Geun Sik Lee; Chang Ho Son; Wui Jun Chung

doi:10.2322/tjsass.56.82

Elliptic trailing edge for a turbine blade: Aerodynamic and aerothermal effects

Mahmoud Moustafa El-Gendi, Sang Wook Lee, Chang Yeol Joh, Geun Sik Lee, Chang Ho Son, Wui Jun Chung

Research output: Contribution to journal › Article › peer-review

9 Citations (Scopus)

Abstract

Three-dimensional flow simulations through a turbine cascade are carried out for an exit isentropic Mach number of 0.79. The objective of the present study is to qualitatively and quantitatively clarify the effect of using an elliptic trailing edge (TE) instead of a circular one on the flow. Calculations are carried out using a parallel, turbulent, structured, singleblock code and the delayed detached eddy simulation is employed for turbulence. We maintain the TE thickness (minor axis) and modify the other axis (major axis). Time-averaged pressure and heat transfer coefficient distributions along the blade are presented with more attention paid to the TE region. The results show that increasing the major-to-minor axis ratio decreases both the heat transfer coefficient and loss. Therefore, designers can adjust this ratio according to application needs.

Original language	English
Pages (from-to)	82-89
Number of pages	8
Journal	Transactions of the Japan Society for Aeronautical and Space Sciences
Volume	56
Issue number	2
DOIs	https://doi.org/10.2322/tjsass.56.82
Publication status	Published - Mar 2013
Externally published	Yes

Keywords

Base Pressure
CFD
Heat Transfer
Trailing Edge
Turbine Flow

ASJC Scopus subject areas

Aerospace Engineering
Space and Planetary Science

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10.2322/tjsass.56.82

Cite this

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title = "Elliptic trailing edge for a turbine blade: Aerodynamic and aerothermal effects",

abstract = "Three-dimensional flow simulations through a turbine cascade are carried out for an exit isentropic Mach number of 0.79. The objective of the present study is to qualitatively and quantitatively clarify the effect of using an elliptic trailing edge (TE) instead of a circular one on the flow. Calculations are carried out using a parallel, turbulent, structured, singleblock code and the delayed detached eddy simulation is employed for turbulence. We maintain the TE thickness (minor axis) and modify the other axis (major axis). Time-averaged pressure and heat transfer coefficient distributions along the blade are presented with more attention paid to the TE region. The results show that increasing the major-to-minor axis ratio decreases both the heat transfer coefficient and loss. Therefore, designers can adjust this ratio according to application needs.",

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T2 - Aerodynamic and aerothermal effects

AU - El-Gendi, Mahmoud Moustafa

AU - Lee, Sang Wook

AU - Joh, Chang Yeol

AU - Lee, Geun Sik

AU - Son, Chang Ho

AU - Chung, Wui Jun

PY - 2013/3

Y1 - 2013/3

N2 - Three-dimensional flow simulations through a turbine cascade are carried out for an exit isentropic Mach number of 0.79. The objective of the present study is to qualitatively and quantitatively clarify the effect of using an elliptic trailing edge (TE) instead of a circular one on the flow. Calculations are carried out using a parallel, turbulent, structured, singleblock code and the delayed detached eddy simulation is employed for turbulence. We maintain the TE thickness (minor axis) and modify the other axis (major axis). Time-averaged pressure and heat transfer coefficient distributions along the blade are presented with more attention paid to the TE region. The results show that increasing the major-to-minor axis ratio decreases both the heat transfer coefficient and loss. Therefore, designers can adjust this ratio according to application needs.

AB - Three-dimensional flow simulations through a turbine cascade are carried out for an exit isentropic Mach number of 0.79. The objective of the present study is to qualitatively and quantitatively clarify the effect of using an elliptic trailing edge (TE) instead of a circular one on the flow. Calculations are carried out using a parallel, turbulent, structured, singleblock code and the delayed detached eddy simulation is employed for turbulence. We maintain the TE thickness (minor axis) and modify the other axis (major axis). Time-averaged pressure and heat transfer coefficient distributions along the blade are presented with more attention paid to the TE region. The results show that increasing the major-to-minor axis ratio decreases both the heat transfer coefficient and loss. Therefore, designers can adjust this ratio according to application needs.

KW - Base Pressure

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KW - Heat Transfer

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KW - Turbine Flow

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Elliptic trailing edge for a turbine blade: Aerodynamic and aerothermal effects

Abstract

Keywords

ASJC Scopus subject areas

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