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research-article

Numerical and experimental investigation on an effusion-cooled lean burn aeronautical combustor: aerothermal field and emissions

[+] Author and Article Information
Lorenzo Mazzei

Department of Industrial Engineering, University of Florence, 50139, via S. Marta 3, Florence, Italy
lorenzo.mazzei@htc.unifi.it

Stefano Puggelli

Department of Industrial Engineering, University of Florence, 50139, via S. Marta 3, Florence, Italy
stefano.puggelli@htc.unifi.it

Davide Bertini

Department of Industrial Engineering, University of Florence, 50139, via S. Marta 3, Florence, Italy
davide.bertini@htc.unifi.it

Antonio Andreini

Department of Industrial Engineering, University of Florence, 50139, via S. Marta 3, Florence, Italy
antonio.andreini@htc.unifi.it

Bruno Facchini

Department of Industrial Engineering, University of Florence, 50139, via S. Marta 3, Florence, Italy
bruno.facchini@htc.unifi.it

Ignazio Vitale

GE Avio S.r.l., 10040, via Primo Maggio 56, Rivalta di Torino (TO), Italy
ignazio.vitale@avioaero.it

Antonio Santoriello

GE Avio S.r.l., 10040, via Primo Maggio 56, Rivalta di Torino (TO), Italy
antonio.santoriello@avioaero.it

1Corresponding author.

ASME doi:10.1115/1.4041676 History: Received August 29, 2018; Revised October 01, 2018

Abstract

Lean burn combustion is increasing its popularity in the aeronautical framework due to its potential in reducing drastically pollutant emissions (NOx and soot in particular). Its implementation however involves significant issues related to the increased amount of air dedicated to the combustion process, demanding the redesign of injection and cooling systems. Also the conditions at the combustor exit are a concern, as high turbulence, residual swirl and the impossibility to adjust the temperature profile with dilution holes determine a harsher environment for nozzle guide vanes. This work describes the final stages of the design of an aeronautical effusion-cooled lean burn combustor. Full annular tests were carried out to measure temperature profiles and emissions (CO and NOx) at the combustor exit. Different operating conditions of the ICAO cycle were tested, considering Idle, Cruise, Approach and Take-Off. Scale-adaptive simulations with the Flamelet Generated Manifold combustion model were performed to extend the validation of the employed CFD methodology and to reproduce the experimental data in terms of RTDF/OTDF profiles as well as emission indexes. The satisfactory agreement paved the way to an exploitation of the methodology to provide a deeper understanding of the flow physics within the combustion chamber, highlighting the impact of the different operating conditions on flame, spray evolution and pollutant formation.

Copyright (c) 2018 by ASME
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