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Research Papers: Gas Turbines: Heat Transfer

Effect of Rotation on a Gas Turbine Blade Internal Cooling System: Experimental Investigation

[+] Author and Article Information
Daniele Massini

DIEF—Department of Industrial Engineering,
University of Florence,
Via di Santa Marta 3,
Florence 50139, Italy
e-mail: daniele.massini@htc.de.unifi.it

Emanuele Burberi, Carlo Carcasci, Lorenzo Cocchi, Bruno Facchini

DIEF—Department of Industrial Engineering,
University of Florence,
Via di Santa Marta 3,
Florence 50139, Italy

Alessandro Armellini, Luca Casarsa, Luca Furlani

Polytechnical Department of Engineering
and Architecture,
University of Udine,
Via delle Scienze 206,
Udine 33100, Italy

1Corresponding author.

Contributed by the Heat Transfer Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received February 22, 2017; final manuscript received March 29, 2017; published online June 1, 2017. Editor: David Wisler.

J. Eng. Gas Turbines Power 139(10), 101902 (Jun 01, 2017) (13 pages) Paper No: GTP-17-1076; doi: 10.1115/1.4036576 History: Received February 22, 2017; Revised March 29, 2017

A detailed aerothermal characterization of an advanced leading edge (LE) cooling system has been performed by means of experimental measurements. Heat transfer coefficient distribution has been evaluated exploiting a steady-state technique using thermochromic liquid crystals (TLCs), while flow field has been investigated by means of particle image velocimetry (PIV). The geometry key features are the multiple impinging jets and the four rows of coolant extraction holes, and their mass flow rate distribution is representative of real engine working conditions. Tests have been performed in both static and rotating conditions, replicating a typical range of jet Reynolds number (Rej), from 10,000 to 40,000, and rotation number (Roj) up to 0.05. Different crossflow conditions (CR) have been used to simulate the three main blade regions (i.e., tip, mid, and hub). The aerothermal field turned out to be rather complex, but a good agreement between heat transfer coefficient and flow field measurement has been found. In particular, jet bending strongly depends on crossflow intensity, while rotation has a weak effect on both jet velocity core and area-averaged Nusselt number. Rotational effects increase for the lower crossflow tests. Heat transfer pattern shape has been found to be substantially Reynolds independent.

Copyright © 2017 by ASME
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References

Figures

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Fig. 1

Sectional view of LE model. Measures are in mm.

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Fig. 5

PIV reference system and investigated planes

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Fig. 6

Average heat transfer coefficient uncertainty for the whole test matrix

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Fig. 7

Average Nusselt results in static conditions

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Fig. 8

2D Nuj distribution for a whole blade configuration at Rej = 10,000, Roj = 0 and Rej = 30,000, Roj = 0

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Fig. 9

Nuj,ave distribution comparison for different Rej in TIP condition: (a) Nuj,ave circumferential distribution and (b) Nuj,ave radial distribution

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Fig. 10

PIV velocity maps in static conditions for a whole blade configuration at Rej = 30,000

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Fig. 11

Average Nuj variation with Roj: (a) Effect of rotation on Nuj,ave for all the test points and (b) Nuj,ave percentage variation for all the test points

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Fig. 12

2D Nuj distributions at Rej = 10,000, Roj=0.02 and Rej = 10,000, Roj = 0.05

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Fig. 13

Nuj,ave circumferential distributions comparison between TIP and HUB conditions: (a) Nuj,ave circumferential distribution in TIP conditions and (b) Nuj,ave circumferential distribution in HUB conditions

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Fig. 14

2D Nuj distributions at Rej = 10,000 and Roj=0–0.05 for the TIP condition

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Fig. 15

Nuj differences between SS and PS at different Roj and crossflow conditions: (a) TIP, (b) MID, and (c) HUB

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Fig. 16

PIV velocity maps in rotating conditions for a whole blade configuration at Rej = 30,000 and Roj = 0.05

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Fig. 17

Velocity profiles for HUB and TIP conditions, effect of rotation at Rej = 30,000

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