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A Novel Model for CFD-Based Throughflow Analysis of Film-Cooled Turbine Blade

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Abstract

This paper presents a novel approach of modeling the air-cooled turbine with CFD-based throughflow analysis. Starting from the basic equations of motion, governing equations and source terms for mass, momentum and energy are formulated in an analytical manner. These source terms are to mimic the authentic injection-mainstream interactions with easy implementation. The source terms in the aero-cooling scenario are related to corresponding sources in the aerodynamic-only analysis. Based on such formulations, a novel strategy is developed to estimate aerodynamic characteristics of a blade row under film cooling with known characteristics under no cooling. The model and the strategy are validated in the classic NASA E3 turbine guide vane under various operating conditions. Sensitivity studies of input parameters are conducted to evaluate the applicability of the proposed model. Specifically, the flow rate distributions of cooling flow at different cooling holes are crucial for accurate predictions.

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Abbreviations

C :

absolute velocity/m·s−1

c :

chord length/m

E :

kinetic energy/J·kg−1

F :

body force/N·m−3

h :

enthalpy/J·kg−1

L :

loss body force magnitude/N·m−3

l :

blade pitch/m

ṁ :

mass flow rate/kg·s−1

n :

normal vector

P :

perturbations/N·m−3

p :

pressure/Pa

q :

inside wall heat flux/W·m−2

R :

specific gas constant/J·kg−1·K−1

S :

source function

s :

entropy/J·kg−1·K−1

T :

temperature/K

u :

axial velocity/m·s−1

v :

lateral velocity/m·s−1

W :

Relative velocity/m·s−1

x :

axial coordinate/m

y :

lateral coordinate/m

β TE/β LE :

relative flow angle at the trailing edge (TE) or leading edge (LE)/(°)

ρ :

density/kg·m−3

—:

vectors

—:

moving averaged quantities

′:

fluctuation term of the moving-average decomposition

∼:

density-weighted moving averaged quantities

″:

fluctuation term of the density-weighted moving-average decomposition

*:

prescribed quantities

aero:

quantities due to aerodynamics (no cooling)

b:

blade body force

cooling:

quantities due to cooling injection

c:

cooling-flow quantities

i :

free index, x, y or z

m:

mainstream quantities

n:

normal direction component

p:

quantities on pressure surface

s:

quantities on suction surface

t:

total/stagnation quantities

total:

quantities due to both aerodynamics and cooling effects

x :

in axial direction

y :

in lateral direction

τ :

viscous body force

0:

reference quantities

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Acknowledgements

This work is funded by the National Natural Science Foundation of China (Project 51876098), the National Science and Technology Major Project (2017-III-0009-0035) and the National Natural Science Foundation of China (Project 51911540475).

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Authors and Affiliations

  1. Department of Energy and Power Engineering, Tsinghua University, Beijing, 100084, China

    Yinbo Mao, Ziyu Chen, Xinrong Su & Xin Yuan

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  1. Yinbo Mao
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Correspondence to Xinrong Su.

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Mao, Y., Chen, Z., Su, X. et al. A Novel Model for CFD-Based Throughflow Analysis of Film-Cooled Turbine Blade. J. Therm. Sci. 31, 1759–1772 (2022). https://doi.org/10.1007/s11630-022-1579-8

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  • DOI: https://doi.org/10.1007/s11630-022-1579-8

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