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Experimental Study of Heat Transfer and Film Cooling Performance of Upstream Ejected Coolant on a Turbine Endwall

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Abstract

An upstream coolant injection that is different from the known leakage flow was introduced to protect the turbine endwall. This coolant is ejected tangentially from a row of cylindrical holes situated at the side of a backward-facing step. In this experiment, the effects of mass flow ratio and leakage slot width on the endwall heat transfer characteristics were investigated. The dimensionless heat transfer coefficient (Nu) and adiabatic film cooling effectiveness (η) on an axisymmetric turbine endwall were measured by the stable-state thermochromic liquid crystal (TLC) technique and the pressure sensitive paint (PSP) technique, respectively. Three mass flow ratios (MFR) of 0.64%, 0.85%, and 1.07%, as well as two leakage slot widths (W) of 3.93 mm, and 7.86 mm were considered. Results indicate that the injection film suppresses the strength of the passage vortex, which leads to the coolant covering almost the entire endwall. This result is more evident for the higher MFR cases, meanwhile, the corresponding averaged film cooling effectiveness is increased with the enhancement of the MFR. However, the case with a higher MFR produces a higher heat transfer coefficient distribution, especially in the region close to the leakage slot edge. Besides, when the W is lower, the endwall presents a higher η and a lower Nu for all the cases, which can guide the optimal design of the endwall.

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Abbreviations

C :

True chord length or oxygen concentration

C ax :

Axial chord length

D :

Hole diameter

h :

Heat transfer coefficient

I :

Light intensity

L :

Length of hole

MFR:

Coolant-to-mainstream mass flow ratio MFR/%=qc/qm

Nu :

Nusselt number

P :

Pressure or Pitch

PS:

Pressure surface

q c :

Coolant mass flux

q con :

Heat conduction loss

q m :

Mainstream mass flux

q net :

Net heat flux

q rad :

Radiation loss

q tot :

Total heat flux

Re :

Reynolds number

S :

Span

SS:

Suction surface

T :

Temperature

V :

Velocity

W :

Leakage slot width

X :

Axial direction

Y :

Pitchwise direction

Z :

Radial direction

η :

Adiabatic film cooling effectiveness

η ave :

Pitchwise averaged cooling effectiveness

ρ :

Fluid density

θ :

Dimensionless temperature

aw:

Adiabat condition

c:

Coolant property

w:

Endwall surface property

0:

Reference condition

∞:

Mainstream property \(\theta = {{T-{T_\infty}} \over {{T_{\rm{c}}}-{T_\infty}}}\)

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Acknowledge

The authors acknowledge gratefully the financial support from the National Natural Science Foundation of China (Grant No. U2241268) and the National Science and Technology Major Project (Grant No. J2019-III-0019-0063).

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Authors and Affiliations

  1. School of Power and Energy, Northwestern Polytechnical University, Xi’an, 710072, China

    Jie Zhang, Cunliang Liu, Li Zhang, Chunyi Yao & Lin Li

Authors
  1. Jie Zhang
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  2. Cunliang Liu
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  3. Li Zhang
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  4. Chunyi Yao
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  5. Lin Li
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Correspondence to Cunliang Liu.

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Zhang, J., Liu, C., Zhang, L. et al. Experimental Study of Heat Transfer and Film Cooling Performance of Upstream Ejected Coolant on a Turbine Endwall. J. Therm. Sci. 32, 718–728 (2023). https://doi.org/10.1007/s11630-023-1754-6

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  • DOI: https://doi.org/10.1007/s11630-023-1754-6

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