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Turbine drives for VTOL turbofans further investigations with a tip turbine drive

From National Research Council Canada

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DOIResolve DOI: https://doi.org/10.4224/40003694
AuthorSearch for: 1; Search for: 1; Search for: 1
Affiliation
  1. National Research Council Canada. Division of Mechanical Engineering
FormatText, Technical Report
Physical description38 p.
Abstract
A tip turbine drive suitable for VTOL lifting fans is described and test results are presented. The measured total head efficiency of the turbine was about 82 percent. A substantial proportion of the turbine losses was attributed to the unconventional stator vanes. A stepped labyrinth seal provided a reduction in hot gas leakage from the turbine annulus as compared with the plain seal configuration used previously. The mechanical performance of the segmented blade carrier ring was satisfactory during a test running period of 49 hours. The stresses measured in the titanium segments were lower than predicted.
Publication date
PublisherNational Research Council Canada
Series
  • Aeronautical Report (National Research Council Canada. Division of Mechanical Engineering. Engine Laboratory), no. LR-443 (September 1965).
LanguageEnglish
Peer reviewedNo
NRC numberNRCC-0008835
NRC-8835
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Record identifierae3932e3-49ee-4f43-8a03-7c80c06ee4d9
Record created2025-09-05
Record modified2025-11-03
Date modified: