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Reduced-stress compressor blisk flowpath

  • US 6,511,294 B1
  • Filed: 09/23/1999
  • Issued: 01/28/2003
  • Est. Priority Date: 09/23/1999
  • Status: Expired due to Term
First Claim
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1. A method of reducing circumferential rim stress concentration in a gas turbine engine, the engine including a rotor including a radially outer rim, a radially inner hub, and a web extending therebetween, a plurality of circumferentially spaced apart rotor blades extending radially outwardly from the rim, said method comprising the step of:

  • providing an outer surface of the outer rim with a shape including a compound radius that defines at least one apex within the outer rim outer surface, and that reduces circumferential rim stress concentration between each of the blades and the rim; and

    operating the gas turbine engine such that airflow is directed over the outer rim outer surface.

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