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
Your Session has timed out. Please sign back in to continue.



Grahic Jump Location
Fig. 1

Sectional view of LE model. Measures are in mm.

Grahic Jump Location
Fig. 5

PIV reference system and investigated planes

Grahic Jump Location
Fig. 6

Average heat transfer coefficient uncertainty for the whole test matrix

Grahic Jump Location
Fig. 7

Average Nusselt results in static conditions

Grahic Jump Location
Fig. 8

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

Grahic Jump Location
Fig. 9

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

Grahic Jump Location
Fig. 10

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

Grahic Jump Location
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

Grahic Jump Location
Fig. 12

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

Grahic Jump Location
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

Grahic Jump Location
Fig. 14

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

Grahic Jump Location
Fig. 15

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

Grahic Jump Location
Fig. 16

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

Grahic Jump Location
Fig. 17

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




Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In