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research-article

EFFECT OF ROTATION ON A GAS TURBINE BLADE INTERNAL COOLING SYSTEM: EXPERIMENTAL INVESTIGATION

[+] Author and Article Information
Daniele Massini

DIEF - Dept of Industrial Engineering University of Florence via di Santa Marta 3, 50139 Florence, Italy
daniele.massini@htc.de.unifi.it

Emanuele Burberi

DIEF - Dept of Industrial Engineering University of Florence via di Santa Marta 3, 50139 Florence, Italy
emanuele.burberi@htc.de.unifi.it

Carlo Carcasci

DIEF - Dept of Industrial Engineering University of Florence via di Santa Marta 3, 50139 Florence, Italy
carlo.carcasci@unifi.it

Lorenzo Cocchi

DIEF - Dept of Industrial Engineering University of Florence via di Santa Marta 3, 50139 Florence, Italy
lorenzo.cocchi@htc.de.unifi.it

Bruno Facchini

DIEF - Dept of Industrial Engineering University of Florence via di Santa Marta 3, 50139 Florence, Italy
bruno.facchini@unifi.it

Alessandro Armellini

Department of Electrical Management and Mechanical Engineering University of Udine via delle Scienze 206, Udine, Italy
alessandro.armellini@uniud.it

Luca Casarsa

Department of Electrical Management and Mechanical Engineering University of Udine via delle Scienze 206, Udine, Italy
luca.casarsa@uniud.it

Luca Furlani

Department of Electrical Management and Mechanical Engineering University of Udine via delle Scienze 206, Udine, Italy
luca.furlani.89@gmail.com

1Corresponding author.

ASME doi:10.1115/1.4036576 History: Received February 22, 2017; Revised March 29, 2017

Abstract

A detailed aerothermal characterization of an advanced leading edge cooling system has been performed by means of experimental measurements. Heat transfer coefficient distribution has been evaluated exploiting a steady-state technique using Thermocromic Liquid Crystals (TLC), 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, which 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 10000 to 40000, and Rotation number (Roj) up to 0.05. Different cross-flow 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 cross-flow tests. Heat transfer pattern shape has been found to be substantially Reynolds-independent.

Copyright (c) 2017 by ASME
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