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research-article

Adiabatic Effectiveness on High Pressure Turbine Nozzle Guide Vanes under Realistic Swirling Conditions

[+] Author and Article Information
Tommaso Bacci

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

Riccardo Becchi

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

Alessio Picchi

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

Dr. Bruno Facchini

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

1Corresponding author.

ASME doi:10.1115/1.4041559 History: Received June 22, 2018; Revised September 22, 2018

Abstract

In modern lean burn aero-engine combustors, highly swirling flow structures are adopted to provide the correct flame stabilization mechanisms. Aggressive swirl fields and high turbulence intensities are hence expected in the combustor-turbine interface. Moreover, to maximize the engine cycle efficiency, an accurate design of the high pressure nozzle cooling system must be. In this context, the interactions between the swirling combustor outflow and the vane film cooling flows play a major role in the definition of a well performing cooling scheme, demanding for experimental campaigns at representative flow conditions. An annular three-sector combustor simulator with fully cooled high pressure vanes has been installed at THT Lab of University of Florence. It is equipped with three swirlers, effusion cooled liners and six film cooled NGV passages. The clocking position between swirlers and vanes has been chosen in order to have the leading edge of the central airfoil aligned with the central swirler. Adiabatic effectiveness measurements have been carried out, to characterize the film-cooling performance under swirling inflow conditions. The PSP technique has been exploited to catch highly detailed distributions. Turbulence and five hole probe measurements at inlet/outlet of the cascade have been carried out as well, to provide precise boundary conditions. Results have shown a relevant effect of the swirling mainflow on the film cooling behaviour. Differences have been found between the central airfoil and the adjacent ones, both in terms of leading edge stagnation point position and of pressure and suction side film coverage characteristics.

Copyright (c) 2018 by ASME
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