Print Email Facebook Twitter Turbine drives for VTOL turbofans: further investigations with a tip turbine drive Title Turbine drives for VTOL turbofans: further investigations with a tip turbine drive Author Levy, G.G. Cockshutt, E.P. Guthrie, T.E. Institution National Research Council Canada, Division of Mechanical Engineers, Engine Laboratory Date 1965-09-30 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. To reference this document use: http://resolver.tudelft.nl/uuid:6ded0caa-42b2-49e3-aa34-10180afced6c Publisher National Research Council Canada Access restriction Campus only Source National Research Council Aeronautical Report LR 443; NRC No. 8835 Part of collection Aerospace Engineering Reports Document type report Rights (c) 1965 National Research Council Canada Files PDF MET-439.pdf 4.65 MB Close viewer /islandora/object/uuid:6ded0caa-42b2-49e3-aa34-10180afced6c/datastream/OBJ/view