Accession Number : AD0781006

Title :   Lift Engine Advanced Turbine Blade Technology.

Descriptive Note : Final rept. 14 Jul 72-24 Mar 73.


Report Date : APR 1973

Pagination or Media Count : 169

Abstract : The objective of the program was to demonstrate the capability for a significant improvement in lift engine thrust-to-weight through an improvement in the turbine rotor blade design. The design was directed at a reduction in turbine weight coupled with an efficient blade cooling system which would reduce cooling bleed flow and provide a potential for increasing turbine inlet temperature. The approach combines the efficiency of an effusion-cooled system with a unique structural design which greatly reduces turbine blade weight. The blade shell design consists of an outer porous skin formed through diffusion bonded layers of Nichrome V screening material, a grid (plenum) plate which distributes air to the porous outer skin, and an orifice plate which controls the flow to the grid plate plenums. The orifice plate also acts as the primary structural member of the blade, avoiding the more common requirement for a central spar. (Modified author abstract)

Descriptors :   *Vertical takeoff aircraft, *Jet engines, *Turbine blades, Rotor blades(Turbomachinery), Cooling, Effusion, Composite materials, Diffusion bonding, Experimental design

Subject Categories : Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE