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TRANSONIC TURBINE BLADE TIP AERO-THERMAL PERFORMANCE WITH DIFFERENT TIP GAPS: PART II-TIP AERODYNAMIC LOSS

Abstract:

Blade tip aerodynamic loss results from experimental and numerical investigations are presented for engine representative conditions downstream of a blade row with an exit Mach number Mexit of 1.0, and an exit Reynolds number Reexit of 1.27x106 (based on axial chord). These results are presented for three different tip gaps of 0.5, 1.0, and 1.5 percent relative to engine-equivalent blade span. Experimental data are obtained by traversing a specially-made and calibrated three-hole pressure pro...

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Publication status:
Published

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Publisher copy:
10.1115/GT2010-22780

Authors


O'Dowd, DO More by this author
Usandizaga, I More by this author
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Institution:
University of Oxford
Department:
Oxford, MPLS, Engineering Science
Ligrani, PM More by this author
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Volume:
4
Issue:
PARTS A AND B
Pages:
347-356
Publication date:
2010
DOI:
URN:
uuid:3755e2b7-08e6-4201-a49a-086a0c231f2f
Source identifiers:
146762
Local pid:
pubs:146762
ISBN:
978-0-7918-4399-4

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