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Research Papers

A Study of Trailing-Edge Losses in Organic Rankine Cycle Turbines

[+] Author and Article Information
Francisco J. Durá Galiana

Aerodynamics and Flight Mechanics Group,
Faculty of Engineering and the Environment,
University of Southampton,
Southampton SO17 1BJ, UK
e-mail: fjdg1g08@soton.ac.uk

Andrew P.S. Wheeler

Whittle Laboratory,
Engineering Department,
University of Cambridge,
Cambridge CB3 0DY, UK

Jonathan Ong

GE Global Research,
Munich 85748, Germany

1Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received April 4, 2016; final manuscript received April 11, 2016; published online June 1, 2016. Editor: Kenneth C. Hall.

J. Turbomach 138(12), 121003 (Jun 01, 2016) (9 pages) Paper No: TURBO-16-1080; doi: 10.1115/1.4033473 History: Received April 04, 2016; Revised April 11, 2016

In this paper, vane trailing-edge losses which occur in organic rankine cycle (ORC) turbines are investigated. Experiments are performed to study the influence of dense gas effects on trailing-edge loss in supersonic flows using a novel Ludwieg tube facility for the study of dense-gas flows. The data is also used to validate a computational fluid dynamics (CFD) flow solver. The computational simulations are then used to determine the contributions to loss from shocks and viscous effects which occur at the vane trailing edge. The results show that dense gas effects play a vital role in the structure of the trailing-edge flow, and control the extent of shock and viscous losses.

Copyright © 2016 by ASME
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References

Figures

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Fig. 1

Flow structure around a trailing edge in a supersonic flow

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Fig. 2

Change in fundamental derivative, Γ, and Prandtl—Meyer function, ν, along supercritical po=2pc, To=1.025Tc (left) and subcritical po=0.9pc, To=1.01Tc (right) expansions for several gases

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Fig. 3

Schematic of Ludwieg tube

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Fig. 4

Schematic of the test section

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Fig. 5

Pressure response for the different runs nondimentionalized over the charge pressure

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Fig. 6

Nozzle with plate mesh

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Fig. 8

Total pressure measurements in wake of several gases at 1.5t.e. from trailing edge

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Fig. 9

Predicted Mach contours from RANS simulations at RE ≈1.5 M and M ≈2.0

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Fig. 10

Comparison of shocked total pressure from experimental data and RANS simulations at 1.5tt.e. from trailing edge

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Fig. 11

Comparison of shocked total pressure from experimental data and LES simulations at 1.5tt.e. from trailing edge

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Fig. 12

LES predicted Mach number contours of (from top to bottom) air, CO2, and SF6 wakes at RE ≈1.5 M and M ≈2.0

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Fig. 13

RANS (■) and LES (•) comparison of mass-weighted averaged loss coefficient at 1.5tt.e. from trailing edge and base pressure

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Fig. 14

Predicted Mach number contours of pentane through radial vanes

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Fig. 15

Predicted Mach number contours of pentane at the trailing edge

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Fig. 16

Entropy contours of pentane

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Fig. 17

Loss coefficient distribution at exit plane of turbine vane

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