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Rotor for jet engines

  • US 4,277,225 A
  • Filed: 09/20/1978
  • Issued: 07/07/1981
  • Est. Priority Date: 09/23/1977
  • Status: Expired due to Term
First Claim
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1. An axial type rotor for jet engines, particularly for compressors, having an alternating stack of disks and of annular elements having external diameters smaller than those of said disks so as to provide spaces for stationary blades, each stage of said rotor comprising a number of identical blades, characterized in that in each disk two series, each comprising uniformly distributed axial grooves equal in number to that of the blades, are arranged, the grooves of a first series being aligned from one end of the rotor to the other, with the grooves of said first series having a configuration adapted to receive a root of a blade, the grooves of the second series, interspaced between those of said first series and having a configuration adapted to receive identical projections of braces equal in number to that of the blades, said projections insuring the axial immobilization of the blades by means of a platform carried by said braces and abutting said blades, the configuration of the grooves of the first and second series being such that said grooves cooperate respectively with the roots of the blades and the projections of the braces, to assure a joint impeding of all radial motion with respect to the rotor of the blades and of the braces.

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