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Numerical study of the tip clearance flow in miniature gas turbine compressors

Version 2 2024-06-04, 05:49
Version 1 2019-09-05, 08:50
journal contribution
posted on 2024-06-04, 05:49 authored by J Xiang, Jorg SchluterJorg Schluter, F Duan
Miniature gas turbines struggle to obtain the efficiencies of the larger counterparts. One of the issues is the larger tip clearance in the compressor due to manufacturing tolerances. In this study, we have performed two numerical parametric studies to determine the influence of tip clearance on gas turbine compressors in the miniaturization process. Firstly, varied tip clearance values are applied when a constant Reynolds number is maintained to investigate the effect of tip clearance value on compressor performance. Thereafter, varied Reynolds numbers are applied when a fixed tip clearance value is used to investigate the effect of miniaturization on compressor performance. Our results quantify the compressor performance deterioration with the existence of tip clearance and show the performance loss amplifies with the increase of tip clearance value as well as with the miniaturization of the compressor. The flow field near the blade tip region has been studied in detail to identify the occurrence of fluid jet and the transition of fluid jet when tip clearance is applied. This study demonstrates the significant impact of tip clearance on compressor performance and quantitatively shows the effect of miniaturization on compressor performance when blade tip clearance exists.

History

Journal

Aerospace Science and Technology

Volume

93

Article number

ARTN 105352

Pagination

1 - 12

Location

Amsterdam, The Netherlands

ISSN

1270-9638

eISSN

1626-3219

Language

English

Publication classification

C Journal article, C1 Refereed article in a scholarly journal

Copyright notice

2019, Elsevier Masson SAS

Publisher

ELSEVIER FRANCE-EDITIONS SCIENTIFIQUES MEDICALES ELSEVIER