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Research Papers

Experimental and Theoretical Investigation of Thermal Effectiveness in Multiperforated Plates for Combustor Liner Effusion Cooling

[+] Author and Article Information
Antonio Andreini

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

Bruno Facchini

DIEF,
Department of Industrial Engineering,
University of Florence,
Florence 50139, Italy
e-mail: bruno.facchini@htc.de.unifi.it

Alessio Picchi

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

Lorenzo Tarchi

DIEF,
Department of Industrial Engineering,
University of Florence,
Florence 50139, Italy
e-mail: lorenzo.tarchi@htc.de.unifi.it

Fabio Turrini

Avio Aero,
Turin 10040, Italy
e-mail: fabio.turrini@avioaero.com

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received August 8, 2013; final manuscript received January 14, 2014; published online March 11, 2014. Editor: Ronald Bunker.

J. Turbomach 136(9), 091003 (Mar 11, 2014) (13 pages) Paper No: TURBO-13-1184; doi: 10.1115/1.4026846 History: Received August 08, 2013; Revised January 14, 2014

State-of-the-art liner cooling technology for modern combustors is represented by effusion cooling (or full-coverage film cooling). Effusion is a very efficient cooling strategy based on the use of multiperforated liners, where the metal temperature is lowered by the combined protective effect of the coolant film and heat removal through forced convection inside each hole. The aim of this experimental campaign is the evaluation of the thermal performance of multiperforated liners with geometrical and fluid-dynamic parameters ranging among typical combustor engine values. Results were obtained as the adiabatic film effectiveness following the mass transfer analogy by the use of pressure sensitive paint, while the local values of the overall effectiveness were obtained by eight thermocouples housed in as many dead holes about 2 mm below the investigated surface. Concerning the tested geometries, different porosity levels were considered: such values were obtained by both increasing the hole diameter and pattern spacing. Then the effect of the hole inclination and aspect ratio pattern shape were tested to assess the impact of typical cooling system features. Seven multiperforated planar plates, reproducing the effusion arrays of real combustor liners, were tested, imposing six blowing ratios in the range 0.5–5. Additional experiments were performed in order to explore the effect of the density ratio (DR=1;1.5) on the film effectiveness. Test samples were made of stainless steel (AISI304) in order to achieve the Biot number similitude for the overall effectiveness tests. To extend the validity of the survey a correlative analysis was performed to point out, in an indirect way, the augmentation of the hot side heat transfer coefficient due to effusion jets. Finallyv,in order to address the thermal behavior of the different geometries in the presence of gas side radiation, additional simulations were performed considering different levels of radiative heat flux.

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Figures

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Fig. 2

Liners effusion array

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Fig. 3

PSP calibration curve

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Fig. 4

Adiabatic effectiveness: effect of the freestream turbulence on geometry G2 (DR = 1)

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Fig. 5

Spatially averaged adiabatic effectiveness: effect of the freestream turbulence on geometry G2 (DR = 1)

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Fig. 13

Distribution of the laterally averaged adiabatic effectiveness for geometries G3 and G4 at different BRs as a function of the number of rows (Tu = 17%; DR = 1)

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Fig. 6

Adiabatic effectiveness distributions for geometry G1 (Tu = 17%; DR = 1)

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Fig. 7

Lateral averaged adiabatic effectiveness: geometry G1 (Tu = 17%; DR = 1)

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Fig. 8

Overall effectiveness distribution: geometry G1 (Tu = 17%; DR = 1)

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Fig. 9

Spatially averaged overall and adiabatic effectiveness: comparison between geometries G2 and G7 (Tu = 17%; DR = 1)

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Fig. 10

Adiabatic effectiveness distribution for G7 (Tu = 17%; DR = 1)

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Fig. 11

Spatially averaged adiabatic and overall effectiveness for tilted geometries (Tu = 17%; DR = 1)

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Fig. 12

Spatially averaged adiabatic and overall effectiveness for tilted geometries (Tu = 17%; DR = 1)

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Fig. 14

Distribution of the overall effectiveness for geometries G3 and G4 at different BRs as a function of the number of rows (Tu = 17%; DR = 1)

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Fig. 18

Spatially averaged adiabatic effectiveness for geometries G2 and G7 as a function of the MR

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Fig. 19

Lateral averaged adiabatic effectiveness: geometry G4 compared with the available literature (DR = 1)

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Fig. 20

Heat transfer augmentation for geometries G2 and G7 (Tu = 17%; DR = 1)

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Fig. 21

Effect of the radiative heat load on geometries G2 and G7 for BR = 2

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Fig. 15

Effect of the DR on geometry G2

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Fig. 16

Bidimensional view of the effect of the DR on geometry G2 (Tu = 17%)

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Fig. 17

Effect of the DR on geometry G7

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Fig. 22

Data reduction for the spatially averaged overall effectiveness for tilted geometries (Tu = 17%; DR = 1)

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