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Effects of combustor-level high inlet turbulence on the endwall flow and heat/mass transfer of a high-turning turbine rotor cascade

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Abstract

Experimental data are presented which describe the effects of a combustor-level high free-stream turbulence on the near-wall flow structure and heat/mass transfer on the endwall of a linear high-turning turbine rotor cascade. The endwall flow structure is visualized by employing the partial- and total-coverage oil-film technique, and heat/mass transfer rate is measured by the naphthalene sublimation method. A turbulence generator is designed to provide a highly-turbulent flow which has free-stream turbulence intensity and integral length scale of 14.7% and 80mm, respectively, at the cascade entrance. The surface flow visualizations show that the high free-stream turbulence has little effect on the attachment line, but alters the separation line noticeably. Under high free-stream turbulence, the incoming near-wall flow upstream of the adjacent separation lines collides more obliquely with the suction surface. A weaker lift-up force arising from this more oblique collision results in the narrower suction-side corner vortex area in the high turbulence case. The high free-stream turbulence enhances the heat/mass transfer in the central area of the turbine passage, but only a slight augmentation is found in the endwall regions adjacent to the leading and trailing edges. Therefore, the high free-stream turbulence makes the endwall heat load more uniform. It is also observed that the heat/mass transfers along the locus of the pressure-side leg of the leading-edge horseshoe vortex and along the suctionside corner are influenced most strongly by the high free-stream turbulence. In this study, the endwall surface is classified into seven different regions based on the local heat/mass transfer distribution, and the effects of the high free-stream turbulence on the local heat/mass transfer in each region are discussed in detail.

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Abbreviations

b :

Axial chord length, Fig. 2

c :

Chord length, Fig. 2

C p :

Specific heat at constant-pressure

D :

Diffusion coefficient of naphthalene in air

h m :

Local mass transfer coefficient

I:

I-th measurement location in thex- direction, Fig. 4

J:

J-th measurement location in they- direction, Fig. 4

l :

Pitchwise distance between the pressure and suction surfaces

L ∞ :

Free-stream integral length scale

p :

Pitch, Fig. 2

Pr:

Prandtl number,v/α

Re∞ :

Inlet Reynolds number

U∞c/υS:

Span, Fig. 1

Sc:

Schmidt number, υ/D

St:

Local heat transfer Stanton number,h/(P U)

Stm :

Local mass transfer Stanton number,h m/U

\(\overline {St} _m \) :

Mass transfer Stanton number averaged in they-direction

\((\overline {St} _m )_{av} \) :

Mass transfer Stanton number averaged across the whole measurement area

Tu :

Free-stream turbulence intensity

U ∞ :

Inlet free-stream velocity

w :

Width of the inlet duct, Fig. 1

XD,yD,ZD:

Coordinates at the inlet duct, Fig. 1

x, y, z :

Cascade coordinates, Fig. 2

y s :

Distance in they-direction from the suction surface

α:

Thermal diffusivity of air

β1 :

Blade inlet angle, Fig. 2

β2 :

Blade outlet angle, Fig. 2

δ2 :

Displacement thickness

δ99 :

Boundary-layer thickness

δ* :

Momentum thickness

υ:

Kinematic viscosity of air

ρ:

Density of air

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Authors and Affiliations

  1. School of Mechanical Engineering Kumoh National Institute of Technology, 188 Shinpyong, Gumi, 730-701, Gyongbook, Korea

    Sang Woo Lee & Sang Bae Jun

  2. School of Mechanical and Aerospace Engineering Seoul National University, 151-742, Seoul, Korea

    Byung-Kyu Park & Joon Sik Lee

Authors
  1. Sang Woo Lee
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  2. Sang Bae Jun
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  3. Byung-Kyu Park
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  4. Joon Sik Lee
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Correspondence to Sang Woo Lee.

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Lee, S.W., Jun, S.B., Park, BK. et al. Effects of combustor-level high inlet turbulence on the endwall flow and heat/mass transfer of a high-turning turbine rotor cascade. KSME International Journal 18, 1435–1450 (2004). https://doi.org/10.1007/BF02984257

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