Experiments of transpiration cooling inspired panel cooling on a turbine blade yielding film effectiveness levels over 95%

Journal article

Abstract:: Panels were tested at different locations around the turbine blade, on both suction and pressure surfaces. Three different surface porosities were also tested. Results demonstrated that the approach can be very successful with high levels of film cooling effectiveness, exceeding 95%, achieved using low coolant mass flow rates. Increasing the surface porosity also proved to be an important parameter in the panel’s performance. Additionally, staggering the film holes lead to significant positive interactions between individual films, resulting in much improved panel performance.

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Publisher:: MDPI
Journal:: International Journal of Turbomachinery, Propulsion and Power More from this journal
Volume:: 6
Issue:: 2
Article number:: 16
Publication date:: 2021-06-04
Acceptance date:: 2021-05-26
DOI:: 10.3390/ijtpp6020016
EISSN:: 2504-186X

Language:: English
Keywords:: turbine blade

pressure sensitive paint

film cooling

transpiration cooling

FFR
Pubs id:: 1186074
Local pid:: pubs:1186074
Deposit date:: 2022-07-20

Copyright holder:: Wambersie et al
Rights statement:: © 2021 by the authors. Licensee MDPI, Basel, Switzerland. This article is an open access article distributed under the terms and conditions of the Creative Commons Attribution (CC BY-NC-ND) license (https://creativecommons.org/ licenses/by-nc-nd/4.0/).

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