Filament wound drum compressor rotor
AssigneeWilliams International Corporation
InventorsWilliam P. Schimmel, Irvin J. Pollock, Lawrence T. Halstead
Life of this patent
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Abstract
A drum compressor rotor (10) for use in a gas turbine engine comprises a plurality of high strength, low density filaments (18a-d) which are covered with a high temperature adhesive resin and tightly wound around the hub (12) between rows of fan blades (14). The filaments allow an increase in the maximum compressor rotor operating speed thereby increasing the potential performance of the turbine engine. The filament windings (18a-d) are significantly lighter and less expensive than conventional welded metal support disks (106a-c).
Claims8
A drum compressor rotor for use in a turbine engine comprising:
- a means for supporting rotation of said rotor within said compressor;
- a rotor hub mounted to said support means, said hub having a plurality of rows of fan blades thereon;
- a plurality of high strength, low weight filaments tightly wound axially around said hub, said plurality of filaments tightly wound between said row of fan blades respectively, said plurality of filaments structurally reinforcing said hub.
A method of structurally reinforcing a rotor hub of a compressor rotor used in a turbine engine comprising the steps:
- covering at least one high strength, low weight filament with an adhesive resin;
- and tightly winding said at least one filament axially around said hub.
Dependencies are inferred from the claim text.