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CFD Study of Combined Impingement and Film Cooling Flow on the Internal Surface Temperature Distribution of a Vane

  • Arun Kumar Pujari EMAIL logo
Published/Copyright: May 15, 2019
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International Journal of Turbo & Jet-Engines
From the journal International Journal of Turbo & Jet-Engines Volume 38 Issue 4

Abstract

Conjugate heat transfer analysis is carried out on the internal surface of the first-stage nozzle guide vane of a gas turbine, which has both impingement and film cooling holes. The mainstream flow Reynolds number and internal coolant flow Reynolds number systematically changed and its effect on internal local surface temperature variation is studied. It is found that an increase in the coolant mass flow rate causes a non-uniform decrease in the local internal surface temperature. The external film coolant jet-lift off and internal impingement cross-flow are significant contributors to the non-uniform variation in surface temperature. It is also observed that the leading edge regions are prone to jet lift-off, whereas the tip regions of the suction surface are prone to self-induced cross-flow, due to which hot patches are formed in these regions. Hot patches are observed near the hub regions of a pressure surface due to the reduced film thickness on the external surface. From these observations it is concluded that local values of internal surface temperature are differently affected in different regions of the vane surface for a given combination of mainstream and coolant flow rates. Therefore, the conventional method of obtaining the internal temperature distributions by considering generalized geometries may not yield accurate solutions, in predicting the life of the nozzle guide vane.

Keywords: combined impingement and film cooling; nozzle guide vane; conjugate heat transfer; CFD
JEL Classification: Heat transfer: channel and internal; 44.15.+a

Nomenclature

C

Chord, m

d

Jet diameter, m

D

Film hole diameter, m

H

Distance between jet hole and target surface, m

L

Span length,, m

M

Mass flow, kg/s

M

Blowing ratio; (ρcVc/ρmVm)

Re

Reynolds number; (VC/υ)

P

Pressure; Pa

S

Distance along the vane surface from leading edge, m

Spmax

Distance along pressure surface from leading edge to trailing edge, m

Ssmax

Distance along suction surface from leading edge to trailing edge, m

T

Temperature, K

t

Vane thickness, m

V

Velocity, m/s

x

Non-dimensional axial distance; (Axial distance from vane leading edge/Axial chord)

Greek symbols

ρ

Density, kg/m3

κ

Turbulent kinetic energy, m2/s2

ω

Specific dissipation rate, 1/sec

θ

Non dimensional temperature; (T-Tc)/(Tm-Tc)

Subscripts

amb

Ambient

c

Coolant

f

Fluid

m

Mainstream

s

Solid

w

Wall

min

minimum

mod

moderate

max

maximum

Abbreviations

AIT

Aft Impingement Tube

DH

Hydraulic diameter

FIT

Front Impingement Tube

HTC

Heat Transfer Coefficient

LER

Leading Edge Region

NDL

Non-Dimensional length(S/Spmax or S/Ssmax)

NDT

Non-Dimensional Temperature

NGV

Nozzle Guide Vane

PS

Pressure Surface

PSIH

Pressure surface Impingement Hole

PSMS

Pressure Surface Mid Span

RANS

Reynolds Averaged Navier-Stokes

SSIH

Suction surface Impingement Hole

SH

Stagnation Hole

SS

Suction Surface

SSMS

Suction Surface Mid Span

SSFR

Suction Surface Fillet Region

SST

Shear Stress Transport

References

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Received: 2019-04-06
Accepted: 2019-04-28
Published Online: 2019-05-15
Published in Print: 2021-12-20

© 2019 Walter de Gruyter GmbH, Berlin/Boston

Articles in the same Issue

  1. Frontmatter
  2. Review
  3. Assessment of Exit Temperature Pattern Factors in an Annular Gas Turbine Combustor: An Overview
  4. Original Research Articles
  5. Optimization of Trenched Film Cooling Using RSM Coupled CFD
  6. Modeling of Relative Exergy Destruction for Turboprop Engine Components Using Deep Learning Artificial Neural Networks
  7. Direct Thrust Inverse Control of Aero-Engine Based on Deep Neural Network
  8. Entropy, Energy and Exergy for Measuring PW4000 Turbofan Sustainability
  9. A Centrifugal Compressor Performance Map Empirical Prediction Method for Automotive Turbochargers
  10. Unsteady Numerical Simulation in a Supersonic Compressor Cascade with a Strong Shock Wave
  11. CFD Study of Combined Impingement and Film Cooling Flow on the Internal Surface Temperature Distribution of a Vane
  12. CFD Analysis of Flow and Performance Characteristics of a 90°curved Rectangular Diffuser: Effects of Aspect Ratio and Reynolds Number
  13. Effects of the Recess Length of the Pilot Stage on the Lean Blowout Limits for the Multipoint Lean Direct Injection Combustors
  14. Stress and Vibration Analysis of a PDC (Pulse Detonation Chamber)
  15. Transverse Injection Experiments within an Axisymmetric Scramjet Combustor
https://doi.org/10.1515/tjj-2019-0010
Keywords for this article
combined impingement and film cooling; nozzle guide vane; conjugate heat transfer; CFD

Articles in the same Issue

  1. Frontmatter
  2. Review
  3. Assessment of Exit Temperature Pattern Factors in an Annular Gas Turbine Combustor: An Overview
  4. Original Research Articles
  5. Optimization of Trenched Film Cooling Using RSM Coupled CFD
  6. Modeling of Relative Exergy Destruction for Turboprop Engine Components Using Deep Learning Artificial Neural Networks
  7. Direct Thrust Inverse Control of Aero-Engine Based on Deep Neural Network
  8. Entropy, Energy and Exergy for Measuring PW4000 Turbofan Sustainability
  9. A Centrifugal Compressor Performance Map Empirical Prediction Method for Automotive Turbochargers
  10. Unsteady Numerical Simulation in a Supersonic Compressor Cascade with a Strong Shock Wave
  11. CFD Study of Combined Impingement and Film Cooling Flow on the Internal Surface Temperature Distribution of a Vane
  12. CFD Analysis of Flow and Performance Characteristics of a 90°curved Rectangular Diffuser: Effects of Aspect Ratio and Reynolds Number
  13. Effects of the Recess Length of the Pilot Stage on the Lean Blowout Limits for the Multipoint Lean Direct Injection Combustors
  14. Stress and Vibration Analysis of a PDC (Pulse Detonation Chamber)
  15. Transverse Injection Experiments within an Axisymmetric Scramjet Combustor
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