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Aircraft engine blades

Authors: MTU AERO ENGINES GMBH;

Aircraft engine blades

Abstract

The blading (10) has rotating vanes exhibiting split ratio of blade pitch and chord length (t/l) in a pointed-near section, where the split ratio amounts to 0.95. The rotating vanes exhibit an exit angle that amounts to 160 degree and an acceleration ratio that amounts to 1.5. The rotating vanes are formed as solid vanes and hollow vanes. The rotating vanes exhibit maximum profile thickness (d max) of 2 mm in the pointed-near section. Guide vanes exhibit maximum profile thickness of 9 mm in the pointed-near section. The acceleration ratio amounts to 1.5 in a foot-near section.

Country
Germany
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selected citations
These citations are derived from selected sources.
This is an alternative to the "Influence" indicator, which also reflects the overall/total impact of an article in the research community at large, based on the underlying citation network (diachronically).
BIP!Citations provided by BIP!
popularity
This indicator reflects the "current" impact/attention (the "hype") of an article in the research community at large, based on the underlying citation network.
BIP!Popularity provided by BIP!
influence
This indicator reflects the overall/total impact of an article in the research community at large, based on the underlying citation network (diachronically).
BIP!Influence provided by BIP!
impulse
This indicator reflects the initial momentum of an article directly after its publication, based on the underlying citation network.
BIP!Impulse provided by BIP!
0
Average
Average
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