Accession Number : ADD011220
Title : Variable Inlet Vane Assembly for a Gas Turbine Combustion.
Descriptive Note : Patent,
Corporate Author : DEPARTMENT OF THE AIR FORCE WASHINGTON DC
Personal Author(s) : Marshall,C
Report Date : 17 Jul 1984
Pagination or Media Count : 7
Abstract : This patent discloses a variable inlet vane assembly for use within the inlet area of a combustor, the vane assembly having a plurality of rotatable vanes situated within an annular-shaped opening in the inlet area of the combustor. Each vane is operated by the rotation of a crank assembly and actuator. The actuator meshes with the crank assembly through a sliding interface in order to accommodate axial and/or radial growth of the combustor with no loss in the precision of the control of air entering the combustor during rotation of the vanes. Such as arrangement substantially enhances the relight capability of the combustor.
Descriptors : *Patents, *Inlet guide vanes, *Combustors, *Air intakes, Inlets, Rotation, Crankshafts, Actuators, Interfaces, Sliding, Ignition, High temperature, Gas turbines, Air flow, Control systems, Engine components
Subject Categories : Combustion and Ignition
Jet and Gas Turbine Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE