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Research Papers

Aerothermodynamics and Exergy Analysis in Radial Turbine With Heat Transfer

[+] Author and Article Information
Shyang Maw Lim

Competence Center for Gas Exchange (CCGEx),
Department of Mechanics,
KTH Royal Institute of Technology,
Osquars Backe 18,
Stockholm 10044, Sweden
e-mail: smlim@kth.se

Anders Dahlkild

Linné Flow Center (FLOW),
Department of Mechanics,
KTH Royal Institute of Technology,
Osquars Backe 18,
Stockholm 10044, Sweden
e-mail: ad@mech.kth.se

Mihai Mihaescu

Competence Center for Gas Exchange (CCGEx),
Linné Flow Center (FLOW),
Department of Mechanics,
KTH Royal Institute of Technology,
Osquars Backe 18,
Stockholm 10044, Sweden
e-mail: mihai@mech.kth.se

1Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received September 28, 2017; final manuscript received July 9, 2018; published online August 28, 2018. Assoc. Editor: Anestis I. Kalfas.

J. Turbomach 140(9), 091007 (Aug 28, 2018) (11 pages) Paper No: TURBO-17-1179; doi: 10.1115/1.4040852 History: Received September 28, 2017; Revised July 09, 2018

This study was motivated by the difficulties to assess the aerothermodynamic effects of heat transfer on the performance of turbocharger turbine by only looking at the global performance parameters, and by the lack of efforts to quantify the physical mechanisms associated with heat transfer. In this study, we aimed to investigate the sensitivity of performance to heat loss, to quantify the aerothermodynamic mechanisms associated with heat transfer and to study the available energy utilization by a turbocharger turbine. Exergy analysis was performed based on the predicted three-dimensional flow field by detached eddy simulation (DES). Our study showed that at a specified mass flow rate, (1) pressure ratio drop is less sensitive to heat loss as compared to turbine power reduction, (2) turbine power drop due to heat loss is relatively insignificant as compared to the exergy lost via heat transfer and thermal irreversibilities, and (3) a single-stage turbine is not an effective machine to harvest all the available exhaust energy in the system.

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Figures

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Fig. 1

Computational model and grid. Measurements were conducted by industry partner at inlet boundary plane and plane zout in the hot gas stand experiment.

Grahic Jump Location
Fig. 2

Sensitivity of turbine global performances with heat loss. Circles are the polytropic reversible work with different heat loss level as denoted in Fig. 3. Both ordinates are normalized by the values of their respective parameters predicted by adiabatic CFD. Overline denotes statistical average.

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Fig. 3

pv diagram of polytropic process with different heat loss magnitude. Overline denotes statistical average.

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Fig. 4

Sensitivity of specific volume change to heat loss. Solid line represents the specific volume change for an isentropic process. Overline denotes statistical average.

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Fig. 5

Comparison of overall exergy budget for different heat loss levels. C is the turbine power; −D is the flow exergy lost by heat transfer; E is the flow exergy lost due to internal irreversibilities; (A−F): net unsteady flow, Adia: adiabatic CFD, Isen: isentropic. The values of Q˙¯loss/W˙¯T are taken from Fig. 2 Overline denotes statistical average.

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Fig. 6

Comparison of relative importance between viscous and thermal irreversibilities with Bejan number. Overline denotes statistical average.

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Fig. 7

Flow exergy (left) and Bejan number (right) contours in the scroll for (a) (Ttin−Tw)/Ttin= 0.15 and (b) (Ttin−Tw)/Ttin= 0.58. Overline denotes statistical average. See Fig.1 for the locations of the sectional planes.

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Fig. 8

Velocity magnitude (left) and temperature (right) contours in the scroll for (a) (Ttin−Tw)/Ttin=0.15 and (b) (Ttin−Tw)/Ttin=0.58. Overline denotes statistical average. See Fig. 1 for the locations of the sectional planes.

Grahic Jump Location
Fig. 9

Temperature contour in the rotor midspan for (a) adiabatic (b) (Ttin−Tw)/Ttin=0.06, and (c) (Ttin−Tw)/Ttin=0.15. Overline denotes statistical average. See Fig. 1 for the rotor midspan surface and the location of θ = 0 deg.

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Fig. 10

Comparison of internal irreversibilities S˙gen evaluated with different methods for (Ttin−Tw)/Ttin=0.58 by different grids. Overline denotes statistical average.

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Fig. 11

Exergetic utilization map derived from turbocharger manufacturer measured turbine performance maps. Different symbols depicts different speed lines.

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