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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

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Institution:
University of Oxford
Division:
MPLS
Department:
Engineering Science
Role:
Author
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Volume:
4
Issue:
PARTS A AND B
Pages:
347-356
Host title:
PROCEEDINGS OF THE ASME TURBO EXPO 2010, VOL 4, PTS A AND B
Publication date:
2010-01-01
DOI:
Source identifiers:
146762
ISBN:
9780791843994
Pubs id:
pubs:146762
UUID:
uuid:3755e2b7-08e6-4201-a49a-086a0c231f2f
Local pid:
pubs:146762
Deposit date:
2013-11-17

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