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Loss Analysis of Unsteady Turbomachinery Flows Based on the Mechanical Work Potential

Loss Analysis of Unsteady Turbomachinery Flows Based on the Mechanical Work Potential
Loss Analysis of Unsteady Turbomachinery Flows Based on the Mechanical Work Potential
Loss analysis is a valuable technique for improving the thermodynamic performance of turbomachines. Analyzing loss in terms of the “mechanical work potential” (Miller, R.J., ASME Turbo Expo 2013, GT2013-95488) provides an instantaneous and local account of the thermal and aerodynamic mechanisms contributing to the loss of thermodynamic performance. This study develops the practical application of mechanical work potential loss analysis, providing the mathematical formulations necessary to perform loss analysis using practical Reynolds-averaged Navier–Stokes (RANS) or large eddy simulations (LES). The analysis approach is demonstrated using RANS and LES of a linear compressor cascade, both with and without incoming wakes. Spatial segmentation is used to attribute loss contributions to specific regions of the flow, and phase-averaging is performed in order to associate the variation of different loss contributions with the periodic passage of wakes through the cascade. For this un-cooled linear cascade, viscous dissipation is the dominant source of loss. The analysis shows that the contribution of the viscous reheat effect depends on the operating pressure of the compressor stage relative to the ambient “dead state” pressure—implying that the optimal blade profile for a low-pressure compressor stage may be different from the optimal profile for a high-pressure compressor stage in the same engine, even if the operating conditions for both stages are dynamically similar.
0889-504X
111009
Leggett, John
31ece775-d118-4dab-a6ae-c66317e012ac
Richardson, Edward
a8357516-e871-40d8-8a53-de7847aa2d08
Priebe, Stephan
95a77449-156a-459d-991a-bec7d4a600b3
Shabbir, Aamir
0ea0da57-8989-4119-a8ed-09cc0db0ec79
Michelassi, Vittorio
af56628e-485c-4fce-a48a-3ddcd914b51c
Sandberg, Richard D
41d03f60-5d12-4f2d-a40a-8ff89ef01cfa
Leggett, John
31ece775-d118-4dab-a6ae-c66317e012ac
Richardson, Edward
a8357516-e871-40d8-8a53-de7847aa2d08
Priebe, Stephan
95a77449-156a-459d-991a-bec7d4a600b3
Shabbir, Aamir
0ea0da57-8989-4119-a8ed-09cc0db0ec79
Michelassi, Vittorio
af56628e-485c-4fce-a48a-3ddcd914b51c
Sandberg, Richard D
41d03f60-5d12-4f2d-a40a-8ff89ef01cfa

Leggett, John, Richardson, Edward, Priebe, Stephan, Shabbir, Aamir, Michelassi, Vittorio and Sandberg, Richard D (2020) Loss Analysis of Unsteady Turbomachinery Flows Based on the Mechanical Work Potential. Journal of Turbomachinery, 142 (11), 111009, [TURBO-20-1041]. (doi:10.1115/1.4048162).

Record type: Article

Abstract

Loss analysis is a valuable technique for improving the thermodynamic performance of turbomachines. Analyzing loss in terms of the “mechanical work potential” (Miller, R.J., ASME Turbo Expo 2013, GT2013-95488) provides an instantaneous and local account of the thermal and aerodynamic mechanisms contributing to the loss of thermodynamic performance. This study develops the practical application of mechanical work potential loss analysis, providing the mathematical formulations necessary to perform loss analysis using practical Reynolds-averaged Navier–Stokes (RANS) or large eddy simulations (LES). The analysis approach is demonstrated using RANS and LES of a linear compressor cascade, both with and without incoming wakes. Spatial segmentation is used to attribute loss contributions to specific regions of the flow, and phase-averaging is performed in order to associate the variation of different loss contributions with the periodic passage of wakes through the cascade. For this un-cooled linear cascade, viscous dissipation is the dominant source of loss. The analysis shows that the contribution of the viscous reheat effect depends on the operating pressure of the compressor stage relative to the ambient “dead state” pressure—implying that the optimal blade profile for a low-pressure compressor stage may be different from the optimal profile for a high-pressure compressor stage in the same engine, even if the operating conditions for both stages are dynamically similar.

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turbo_142_11_111009 - Accepted Manuscript
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Accepted/In Press date: 7 May 2020
e-pub ahead of print date: 10 October 2020
Published date: November 2020

Identifiers

Local EPrints ID: 453752
URI: http://eprints.soton.ac.uk/id/eprint/453752
ISSN: 0889-504X
PURE UUID: 6c009187-0fec-4d19-8348-506823359510
ORCID for Edward Richardson: ORCID iD orcid.org/0000-0002-7631-0377
ORCID for Richard D Sandberg: ORCID iD orcid.org/0000-0001-5199-3944

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Date deposited: 24 Jan 2022 17:35
Last modified: 28 Apr 2022 02:04

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Contributors

Author: John Leggett
Author: Stephan Priebe
Author: Aamir Shabbir
Author: Vittorio Michelassi
Author: Richard D Sandberg ORCID iD

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