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Research Papers: Gas Turbines: Heat Transfer

Use of Rib Turbulators to Enhance Postimpingement Heat Transfer for Curved Surface

[+] Author and Article Information
Jahed Hossain

Center for Advanced Turbomachinery
and Energy Research,
Laboratory for Turbine Aerodynamics,
Heat Transfer and Durability,
University of Central Florida,
12761 Ara Drive,
Orlando, FL 32826
e-mail: Jahed.hossain@knights.ucf.edu

Andres Curbelo

Center for Advanced Turbomachinery
and Energy Research,
Laboratory for Turbine Aerodynamics,
Heat Transfer and Durability,
University of Central Florida,
12761 Ara Drive,
Orlando, FL 32826
e-mail: acurbelo1@knights.ucf.edu

Christian Garrett

Center for Advanced Turbomachinery
and Energy Research,
Laboratory for Turbine Aerodynamics,
Heat Transfer and Durability,
University of Central Florida,
12761 Ara Drive,
Orlando, FL 32826
e-mail: chrisgarrett10@knights.ucf.edu

Wenping Wang

Center for Advanced Turbomachinery and
Energy Research,
Laboratory for Turbine Aerodynamics,
Heat Transfer and Durability,
University of Central Florida,
12761 Ara Drive,
Orlando, FL 32826
e-mail: Wenping.wang@ucf.edu

Jayanta Kapat

Center for Advanced Turbomachinery
and Energy Research,
Laboratory for Turbine Aerodynamics,
Heat Transfer and Durability,
University of Central Florida,
12761 Ara Drive,
Orlando, FL 32826
e-mail: Jayanta.kapat@ucf.edu

Steven Thorpe

Ansaldo Energia Switzerland,
Roemerstrasse 36,
Baden 5401, Switzerland
e-mail: steven.thorpe@ansaldoenergia.com

Michael Maurer

Ansaldo Energia Switzerland,
Roemerstrasse 36,
Baden 5401, Switzerland
e-mail: Michaelthomas.maurer@ansaldoenergia.com

Contributed by the Heat Transfer Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received September 23, 2016; final manuscript received December 15, 2016; published online March 7, 2017. Editor: David Wisler.

J. Eng. Gas Turbines Power 139(7), 071901 (Mar 07, 2017) (16 pages) Paper No: GTP-16-1464; doi: 10.1115/1.4035659 History: Received September 23, 2016; Revised December 15, 2016

The present study aims to investigate the heat transfer and pressure loss characteristics for multiple rows of jets impinging on a curved surface in the presence of rib turbulators. The target plate contains a straight section downstream of the impingement section. The rib turbulators are added only over the straight section, in an attempt to enhance the heat transfer while minimizing the pressure loss. The jet plate configuration in this study has fixed jet hole diameters and hole spacing. For the curved plate, the radius of the target plate is 32 times the diameter of the impingement holes. Impingement array configuration was chosen such that validation and comparison can be made with the open literature. For all the configurations, crossflow air is drawn out in the streamwise direction. Average jet Reynolds numbers ranging from 55,000 to 125,000 were tested. Heat transfer characteristics are measured using steady-state temperature-sensitive paint (TSP) to obtain local heat transfer distribution. The experimental results are compared with computational fluid dynamics (CFD) simulations. CFD results show that CFD simulations predict the heat transfer distribution well in the postimpingement area with turbulators.

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Figures

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Fig. 4

Nusselt number uncertainty tree

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Fig. 5

Turbulator design (90 deg rib)

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Fig. 3

Pressure tap location

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Fig. 2

Detailed side view of the curved configuration

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Fig. 1

Schematic of the test section

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Fig. 14

Experimetal local Gc/GJ distribution for Rej = 55,000

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Fig. 15

Pressure ratio distribution

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Fig. 6

Turbulator design (W-1 shaped rib)

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Fig. 7

Turbulator design (W-2 shaped rib)

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Fig. 8

Computational domain

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Fig. 9

Mesh of the 90 deg turbulators

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Fig. 10

Mesh of the W-1 shaped turbulators

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Fig. 11

Mesh of the W-2 shaped turbulators

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Fig. 12

Grid convergence study

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Fig. 13

Array-averaged discharge coefficients

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Fig. 16

Nusselt number profile for the baseline configuration: upstream curved section (left) and downstream flat section (right)

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Fig. 17

Heat transfer distribution in the postimpingement area for Rej = 125 K

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Fig. 18

Laterally averaged Nusselt numbers for baseline curved surface (Note: The Florschuetz correlation is prescribed for the Reynolds number range of 2500–70,000)

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Fig. 19

Laterally averaged Nusselt numbers at the downstream section (baseline, 90 deg turbulators, and W-shaped turbulators)

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Fig. 20

Heat transfer enhancement

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Fig. 21

CFD comparison of Nusselt number for Rej = 125 K

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Fig. 22

CFD versus experiment: impingement heat transfer (upstream)

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Fig. 23

Computational and experimental results of the laterally averaged Nusselt numbers for 90 deg turbulators (Rej = 125 K)

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Fig. 24

Computational and experimental results of the laterally averaged Nusselt numbers for W-1 shaped turbulators (Rej = 125 K)

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Fig. 25

Computational and experimental results of the laterally averaged Nusselt numbers for W-2 shaped turbulators (Rej = 125 K)

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Fig. 26

Flow streamlines: (a) 90 deg turbulator, (b) W-1 shaped turbulator, (c) primary recirculation zone for the 90 deg turbulator, and (d) primary recirculation zone for the W-1 shaped turbulator

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