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The effect of turbulence intensity on film cooling of gas turbine blade from trenched shaped holes

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Abstract

This paper reports a computational investigation on the effects of mainstream turbulence intensity on film cooling effectiveness from trenched holes over a symmetrical blade. Computational solutions of the steady, Reynolds-Averaged Navier–Stokes equations are obtained using a finite volume method with k − ε Turbulence model. Whenever possible, computational results are compared with experimental ones from data found in the open literature. Computational results are presented for a row of 25° forward-diffused film hole within transverse slot injected at 35° to AGTB symmetrical blade. Four blowing ratios, M = 0.3, 0.5, 0.9 and 1.3 are studied together with four mainstream turbulence intensities of Tu = 0.5, 2, 4 and 10%. Results indicate that the trenched shaped holes tend to give better film cooling effectiveness than that obtained from discrete shaped holes for all blowing ratios and all turbulence intensities. The trenching of shaped holes has changed the optimum blowing ratio and also the location of re-attachment of separated jet at high blowing ratios. Moreover, it has been found that the effect of mainstream turbulence intensity for trenched shaped holes is similar to that obtained for discrete shaped holes with the exception that the sensitivity of film cooling effectiveness to turbulence intensity has decreased for trenched shaped holes.

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Abbreviations

D:

Diameter of coolant channel cross section at throat

k:

Turbulent kinetic energy

L/D:

Length-to-diameter ratio of film hole

M:

Blowing ratio = \( (\rho U)_{c} /(\rho U)_{\infty } \)

P/D:

Pitch-to-diameter ratio of film hole

Re:

Reynolds number

s:

Axial surface coordinate

T:

Local fluid temperature

Tu:

Turbulence level

U:

Velocity

u* :

Friction velocity = \( \sqrt {\tau_{w} /\rho } \)

W/D:

Slot width to hole diameter ratio

x:

Coordinate in the streamwise direction

y:

Coordinate normal to the test surface

y+ :

The normalized distance = \( \frac{{yu_{*} }}{\nu } \)

z:

Coordinate in the lateral direction

β:

Streamwise injection angle

ϕ:

Lateral injection angle

ε:

Dissipation rate of turbulent kinetic energy

η:

Adiabatic film effectiveness

ν:

Kinematic viscosity

ρ:

Density of the fluid

τW :

Wall shear stress

c:

Coolant

w:

Wall

∞:

Mainstream

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Correspondence to S. Baheri Islami.

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Baheri Islami, S., Jubran, B.A. The effect of turbulence intensity on film cooling of gas turbine blade from trenched shaped holes. Heat Mass Transfer 48, 831–840 (2012). https://doi.org/10.1007/s00231-011-0938-x

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  • DOI: https://doi.org/10.1007/s00231-011-0938-x

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