Output details
15 - General Engineering
University of Cambridge
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Output 0 of 0 in the submission
Article title
Compressor Leading Edge Spikes: A New Performance Criterion
Type
D - Journal article
Title of journal
J TURBOMACH
Article number
021006
Volume number
133
Issue number
2
First page of article
021006
ISSN of journal
0889-504X
Year of publication
2011
URL
-
Number of additional authors
1
Additional information
The results of this paper led Rolls-Royce to introduce new leading edges onto compressor blades in the Trent 700. The result was a 1.3% reduction in fuel burn ("Rolling Enhancement", Guy Norris, Aviation Week, December 2008). A patent for an optimal leading edge geometry and its method of calculation was filed (WO 2010/057627).
Interdisciplinary
-
Cross-referral requested
-
Research group
None
Proposed double-weighted
No
Double-weighted statement
-
Reserve for a double-weighted output
No
Non-English
No
English abstract
-
