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

Investigation on the Effect of a Realistic Flow Field on the Adiabatic Effectiveness of an Effusion-Cooled Combustor

[+] Author and Article Information
Luca Andrei

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

Antonio Andreini

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

Cosimo Bianchini

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

Bruno Facchini

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

Lorenzo Mazzei

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

Fabio Turrini

Combustors Product Engineering,
Avio Aero,
via Primo Maggio 56,
Rivalta di Torino 10040, Italy
e-mail: fabio.turrini@avioaero.com

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 16, 2014; final manuscript received August 27, 2014; published online November 18, 2014. Editor: David Wisler.

J. Eng. Gas Turbines Power 137(5), 051501 (May 01, 2015) (9 pages) Paper No: GTP-14-1402; doi: 10.1115/1.4028676 History: Received July 16, 2014; Revised August 27, 2014; Online November 18, 2014

Effusion cooling represents the state of the art of liner cooling technology for modern combustors. This technique consists of an array of closely spaced discrete film cooling holes and contributes to lower the metal temperature by the combined protective effect of coolant film and heat removal through forced convection inside each hole. Despite many efforts reported in literature to characterize the cooling performance of these devices, detailed analyses of the mixing process between coolant and hot gas are difficult to perform, especially when superposition and density ratio effects as well as the interaction with complex gas side flow field become significant. Furthermore, recent investigations on the acoustic properties of these perforations pointed out the challenge to maintain optimal cooling performance also with orthogonal holes, which showed higher sound absorption. The objective of this paper is to investigate the impact of a realistic flow field on the adiabatic effectiveness performance of effusion cooling liners to verify the findings available in literature, which are mostly based on effusion flat plates with aligned cross flow, in case of swirled hot gas flow. The geometry consists of a tubular combustion chamber, equipped with a double swirler injection system and characterized by 22 rows of cooling holes on the liner. The liner cooling system employs slot cooling as well: its interactions with the cold gas injected through the effusion plate are investigated too. Taking advantage of the rotational periodicity of the effusion geometry and assuming axisymmetric conditions at the combustor inlet, steady state RANS calculations have been performed with the commercial code Ansys® CFX simulating a single circumferential pitch. Obtained results show how the effusion perforation angle deeply affects the flow-field around the corner of the combustor, in particular, with a strong reduction of slot effectiveness in case of 90 deg angle value.

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References

Figures

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Fig. 1

Test case geometries and computational grid: (a) no slot geometry, (b) slot geometry, and (c) computational grid

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Fig. 2

Influence of perforation angle (DR = 1). (a) V = Vref distribution on meridional plane and (b) EffCool distribution on meridional plane.

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Fig. 3

Laterally averaged adiabatic effectiveness profile on liner wall: perforation angle influence (DR = 1)

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Fig. 4

Density ratio effect on adiabatic effectiveness distribution on liner wall

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Fig. 5

Laterally averaged adiabatic effectiveness profile on liner wall: DR influence. (a) G2 geometry and (b) G7 geometry.

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Fig. 6

Local blowing ratio along the liner: influence of DR and perforation

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Fig. 7

Laterally averaged adiabatic effectiveness profile on liner wall: comparison between flat plate and tubular combustor (DR = 1, BR = 2)

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Fig. 8

Slot coolant effect on adiabatic effectiveness distribution on liner wall

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Fig. 9

Slot coolant distribution on meridional plane

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Fig. 10

Laterally averaged adiabatic effectiveness profile on liner wall: slot cooling injection influence. (a) G2 geometry and (b) G7 geometry.

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Fig. 11

Laterally averaged adiabatic effectiveness profile on liner wall: slot cooling mass flow rate influence

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