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Near-Wall Flow in the Blade Cascades Representing Last Rotor Root Sections of Large Output Steam Turbines

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Abstract

This paper investigates the flow past two variants of root section profile cascades for a last stage rotor considering three-dimensional flow structures in the near-wall region. Analyses were drawn based on RANS numerical simulations of both variants and on the experimental data obtained by the 3D traversing in the exit flow field of one of the variants. Extent of 3D structures at two different regimes and its influence on aerodynamic characteristics of the blade cascades was assessed. The distributions of Mach number along the profiles were compared with 2D optical measurements and its distortion due to the presence of the sidewall was explored. The interaction between main vortical structures was described and its influence on the loading of the blades, mechanical energy losses and exit flow angle was discussed. The results showed that for a front loaded blade the vortical structures appeared earlier and at a larger extent than for an aft loaded variant. However, due to different Mach number distribution, contribution of end wall flow to the energy losses was lower in the case of the aft loaded variant. The influence of the near wall flow on the loading was found to be rather weak while the deviation of the exit flow angle appeared to be comparable for both of the variants.

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Abbreviations

AR :

aspect ratio

c :

chord/m

E :

specific total internal energy/J∙kg−1

H :

specific total enthalpy/J∙kg−1, shape parameter

h :

specific enthalpy/J∙kg−1

k :

turbulent kinetic energy/m2∙s−2

L :

width of the test section/m

M :

Mach number

M* :

nondimensional velocity (related to the critical speed of sound)

o :

throat opening/m

p :

static pressure/Pa

s :

specific produced entropy/J∙kg−1∙K−1

t :

pitch/m, time/s

u j :

components of velocity vector/m∙s−1

x :

coordinate/m

y :

coordinate/m

z :

coordinate/m

α :

cascade pitch angle/0

α eff :

effective thermal diffusivity/m2∙s−1

ß :

cascade yaw angle/0

y :

stagger angle/0

ζ :

kinetic energy loss coefficient

0i :

incidence angle/0

p :

density/kg∙m−3

τ ij eff :

effective stress tensor including the viscous and Reynolds stress tensors/Pa

1:

blade cascade inlet

2:

blade cascade outlet

D:

design

is:

isentropic

M:

metal, midspan

ref:

reference value

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Acknowledgement

Authors would like to thank the Technology Agency of the Czech Republic which supported this research under the grant No. TH02020057. The support by the Institute of Thermomechanics of the Czech Academy of Sciences under the internal research funding RVO 61388998 is also gratefully acknowledged. Thanks also belong to Doosan Skoda Power, Ltd. which made this research possible.

Access to computing and storage facilities owned by parties and projects contributing to the National Grid Infrastructure MetaCentrum provided under the programme “Projects of Large Research, Development, and Innovations Infrastructures” (CESNET LM2015042), is greatly appreciated.

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Authors and Affiliations

  1. Institute of Thermomechanics of the Czech Academy of Sciences, Prague, 18200, Czech Republic

    David Šimurda, Jindřich Hála & Martin Luxa

  2. Dpt. of Technical Mathematics, Faculty of Mechanical Engineering, CTU in Prague, Prague, 12000, Czech Republic

    Jiří Fürst

  3. Doosan Skoda Power, Pilsen, 30100, Czech Republic

    Marek Bobčík, Ondřej Novák & Jaroslav Synáč

Authors
  1. David Šimurda
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  2. Jiří Fürst
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  3. Jindřich Hála
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  4. Martin Luxa
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  5. Marek Bobčík
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  6. Ondřej Novák
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  7. Jaroslav Synáč
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Correspondence to David Šimurda.

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Šimurda, D., Fürst, J., Hála, J. et al. Near-Wall Flow in the Blade Cascades Representing Last Rotor Root Sections of Large Output Steam Turbines. J. Therm. Sci. 30, 220–230 (2021). https://doi.org/10.1007/s11630-020-1246-x

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  • DOI: https://doi.org/10.1007/s11630-020-1246-x

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