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research-article

Flow Field and Hot Streak Migration through High Pressure Cooled Vanes with Representative Lean Burn Combustor Outflow

[+] Author and Article Information
Tommaso Bacci

DIEF, Department of Industrial Engineering, University of Florence, Florence, 50139, Italy
tommaso.bacci@htc.de.unifi.it

Tommaso Lenzi

DIEF, Department of Industrial Engineering, University of Florence, Florence, 50139, Italy
tommaso.lenzi@htc.de.unifi.it

Alessio Picchi

DIEF, Department of Industrial Engineering, University of Florence, Florence, 50139, Italy
alessio.picchi@htc.de.unifi.it

Lorenzo Mazzei

DIEF, Department of Industrial Engineering, University of Florence, Florence, 50139, Italy
lorenzo.mazzei@htc.de.unifi.it

Dr. Bruno Facchini

DIEF, Department of Industrial Engineering, University of Florence, Florence, 50139, Italy
bruno.facchini@unifi.it

1Corresponding author.

ASME doi:10.1115/1.4040714 History: Received June 22, 2018; Revised June 25, 2018

Abstract

Modern lean burn aero-engine combustors outflows are characterized by aggressive swirl fields, high turbulence intensities and strong hot streaks. In order to understand combustor-turbine interactions, it is mandatory to collect reliable experimental data at representative flow conditions. While the separated effects of temperature, swirl and turbulence on the first turbine stage have been widely investigated, reduced experimental data is available when it comes to consider all these factors together. An annular three-sector combustor simulator with fully cooled high pressure vanes has been installed at the THT Lab of University of Florence. The rig is equipped with three axial swirlers, effusion cooled liners and six film cooled high pressure vanes passages. In order to generate representative conditions, a heated mainstream passes though the axial swirlers of the combustor simulator, while the effusion cooled liners are fed by air at ambient temperature. The resulting flow field exiting from the combustor simulator and approaching the cooled vane can be considered representative of a modern Lean Burn aero engine combustor with swirl angles above ±50°, turbulence intensities up to about 28% and maximum-to-minimum temperature ratio of about 1.25. With the aim of investigating the hot streaks evolution through the cooled high pressure vane, the aerothermal field has been evaluated by means of a five hole probe equipped with a thermocouple and traversed upstream and downstream of the cascade.

Copyright (c) 2018 by ASME
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