𝔖 Bobbio Scriptorium
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Investigations into the performance of gas turbine rim seals

Publisher
Elsevier Science
Year
1997
Tongue
English
Weight
209 KB
Volume
1997
Category
Article
ISSN
1350-4789

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✦ Synopsis

In a large aircraft gas turbine, around 10% of the core airflow bypasses the high pressure turbine nozzle guide vanes. Half of this cools the blade and vane, and half is used for disc cooling and rim senllng -which latter half accounts for a 5% drain on fuel consnmption. Commercial pressure therefore is strong to enhance rim sealing and disc cooling efficiency without impacting on safety. This article describes work ongoing at the University of Sussex, UK, to address the issue.

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