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Experimental investigation of heat transfer and flow using V and broken V ribs within gas turbine blade cooling passage

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Abstract

Gas turbines are extensively used for aircraft propulsion, land-based power generation, and various industrial applications. With an increase in turbine rotor inlet temperatures, developments in innovative gas turbine cooling technology enhance the efficiency and power output; these advancements of turbine cooling have allowed engine designs to exceed normal material temperature limits. For internal cooling design, techniques for heat extraction from the surfaces exposed to hot stream of gas are based on an increase in the heat transfer areas and on the promotion of turbulence of the cooling flow. In this study, an improvement in performance is obtained by casting repeated continuous V- and broken V-shaped ribs on one side of the two pass square channels into the core of the blade. A detailed experimental investigation is done for two pass square channels with a 180° turn. Detailed heat transfer distribution occurring in the ribbed passage is reported for a steady state experiment. Four different combinations of 60° V- and broken 60° V-ribs in a channel are considered. A series of thermocouples are used to obtain the temperature on the channel surface and local heat transfer coefficients are obtained for Reynolds numbers 16,000, 56,000 and 85,000 within the turbulent flow regime. Area averaged data are calculated in order to compare the overall performance of the tested ribbed surface and to evaluate the degree of heat transfer enhancement induced by the rib. Flow within the channels is characterized by heat transfer enhancing ribs, bends, rotation and buoyancy effects. A series of experimental measurements is performed to predict the overall performance of the channel. This paper presents an attempt to collect information about the Nusselt number, the pressure drop and the overall performance of the eight different ribbed ducts at the specified Reynolds number. The main contribution of this study is to evaluate the best combination of rib arrangements throughout the two pass cooling channels. After a series of experiments, it can be concluded that the distribution of peaks in heat transfer in the case of inlet V and outlet inverted V is high. The overall performances for broken ribs are higher compared with the continuous ribs in two-pass cooling channels.

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Abbreviations

A:

Wall surface area

AR:

Channel aspect ratio

b :

Channel divider wall thickness

c p :

Specific heat at constant pressure

d :

Distance to the closest wall

D :

Channel width

DH :

Hydraulic diameter

e:

Rib height

E:

Exponent

°F:

Fahrenheit

f :

Friction factor

f o :

Fanning friction factor for turbulent flow

g :

Acceleration due to gravity

h :

Heat transfer coefficient

H:

Height of the channel

I :

Current

in2 :

Inch square

k :

Fluid thermal conductivity

K:

Kelvin

l t :

Test section length

L :

Channel length

∆L:

Distance between inlet and outlet

\( \dot{m} \) :

Mass flow rate

Nu :

Nusselt number

Nuo :

Theoretical Nusselt number

p :

Pressure

∆P:

Pressure drop across the channel

P:

Rib pitch

Pr :

Prandtl number = 0.71

qw :

Wall heat flux

Qel :

Electrical heat supplied

\( {\text{Q}}_{\text{el}}^{\prime \prime } \) :

Electrical heat flux

\( {\text{Q}}_{\text{con}}^{\prime \prime } \) :

Conduction heat flux

\( {\text{Q}}_{\text{dis}}^{\prime \prime } \) :

Dissipated heat flux

\( {\text{Q}}_{\text{net}}^{\prime \prime } \) :

Net heat flux

Re :

Reynolds number, Re = ρU in DH/μ

ReD :

Reynolds number based on hydraulic diameter

T w :

Wall temperature

T :

Temperature

T s :

Temperature surface across the channel

T bx :

Temperature bulk across the channel length

U in :

Mean inlet velocity

W :

Channel width

α:

Rib angle

μ :

Dynamic viscosity

v :

Kinematic viscosity

ρ :

Fluid density

Ω, R:

Resistance

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Authors and Affiliations

  1. Jacobs Technology Inc., Raymond, OH, USA

    Sourabh Kumar

  2. Department of Mechanical Engineering, University of Wisconsin-Milwaukee, Milwaukee, WI, 53201, USA

    R. S. Amano

Authors
  1. Sourabh Kumar
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Correspondence to R. S. Amano.

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Kumar, S., Amano, R.S. Experimental investigation of heat transfer and flow using V and broken V ribs within gas turbine blade cooling passage. Heat Mass Transfer 51, 631–647 (2015). https://doi.org/10.1007/s00231-014-1436-8

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  • DOI: https://doi.org/10.1007/s00231-014-1436-8

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