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Research Papers: Gas Turbines: Combustion, Fuels, and Emissions

Adiabatic Effectiveness and Flow Field Measurements in a Realistic Effusion Cooled Lean Burn Combustor

[+] Author and Article Information
Antonio Andreini

DIEF,
Department of Industrial Engineering,
University of Florence,
via S.Marta 3,
Firenze 50139, Italy
e-mail: antonio.andreini@htc.de.unifi.it

Riccardo Becchi

DIEF,
Department of Industrial Engineering,
University of Florence,
via S.Marta 3,
Firenze 50139, Italy
e-mail: riccardo.becchi@htc.de.unifi.it

Bruno Facchini

DIEF,
Department of Industrial Engineering,
University of Florence,
via S.Marta 3,
Firenze 50139, Italy
e-mail: bruno.facchini@unifi.it

Lorenzo Mazzei

DIEF,
Department of Industrial Engineering,
University of Florence,
via Santa Marta 3,
Firenze 50139, Italy
e-mail: lorenzo.mazzei@htc.de.unifi.it

Alessio Picchi

DIEF,
Department of Industrial Engineering,
University of Florence,
via S.Marta 3,
Firenze 50139, Italy
e-mail: alessio.picchi@unifi.it

Fabio Turrini

GE Avio S.r.l.,
Combustion Systems Office,
Rivalta di Torino (TO) 10040, Italy
e-mail: fabio.turrini@avioaero.it

1Corresponding author.

Contributed by the Combustion and Fuels Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received July 27, 2015; final manuscript received July 31, 2015; published online September 22, 2015. Editor: David Wisler.

J. Eng. Gas Turbines Power 138(3), 031506 (Sep 22, 2015) (11 pages) Paper No: GTP-15-1375; doi: 10.1115/1.4031309 History: Received July 27, 2015; Revised July 31, 2015

Over the last ten years, there have been significant technological advances toward the reduction of NOx emissions from civil aircraft engines, strongly aimed at meeting stricter and stricter legislation requirements. Nowadays, the most prominent way to meet the target of reducing NOx emissions in modern combustors is represented by lean burn swirl stabilized technology. The high amount of air admitted through a lean burn injection system is characterized by very complex flow structures such as recirculations, vortex breakdown, and precessing vortex core (PVC) that may deeply interact in the near wall region of the combustor liner. This interaction makes challenging the estimation of film cooling distribution, commonly generated by slot and effusion systems. The main purpose of the present work is the characterization of the flow field and the adiabatic effectiveness due to the interaction of swirling flow, generated by real geometry injectors, and a liner cooling scheme made up of a slot injection and an effusion array. The experimental apparatus has been developed within EU project LEMCOTEC (low emissions core-engine technologies) and consists of a nonreactive three-sectors planar rig; the test model is characterized by a complete cooling system and three swirlers, replicating the geometry of a GE Avio PERM (partially evaporated and rapid mixing) injector technology. Flow field measurements have been performed by means of a standard 2D PIV (particle image velocimetry) technique, while adiabatic effectiveness maps have been obtained using PSP (pressure sensitive paint) technique. PIV results show the effect of coolant injection in the corner vortex region, while the PSP measurements highlight the impact of swirled flow on the liner film protection separating the contribution of slot and effusion flows. Furthermore, an additional analysis, exploiting experimental results in terms of heat transfer coefficient, has been performed to estimate the net heat flux reduction (NHFR) on the cooled test plate.

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Figures

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Fig. 1

Cross-sectional view of the test rig with a detailed section of the PERM swirler

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Fig. 2

Position of the PIV measurement plane

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Fig. 3

Effusion test plate sprayed with PSP

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Fig. 4

Flow field on measurements plane (ΔP/P = 3.5%)

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Fig. 5

Adiabatic effectiveness distribution: effect of effusion system pressure drop (ΔP/P = 3.5%)

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Fig. 6

Detailed views of adiabatic effectiveness distribution ((ΔP/P)eff = 1%; no slot cooling)

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Fig. 7

Laterally averaged adiabatic effectiveness distribution: effect of effusion pressure drop

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Fig. 8

Adiabatic effectiveness distribution: effect of slot injection (ΔP/P = 3.5%)

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Fig. 9

Laterally averaged adiabatic effectiveness distribution: effect of slot injection (ΔP/Peff = 3%)

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Fig. 10

Adiabatic effectiveness profiles (ΔP/Peff=3%)

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Fig. 11

Laterally averaged NHFR distribution

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