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Rotor blade for a first phase of a gas turbine

  • US 7,530,794 B2
  • Filed: 09/15/2005
  • Issued: 05/12/2009
  • Est. Priority Date: 09/21/2004
  • Status: Expired due to Fees
First Claim
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1. A blade of a rotor for a first phase of a gas turbine having a profile identified by means of a series of closed intersection curves between the profile itself and planes X, Y lying at distances Z from the central axis of the gas turbine, each closed curve having a first rounded end and a second rounded end which connect a trace of a first surface with a trace of a second surface in depression, said first end first meets a gas flow of the turbine, each closed curve having an axial chord defined as a maximum distance of the first end from the second end along a reference axis X, each closed curve having a dimensionless thickness of said first end defined as a maximum diameter of a circle inscribed in the first end, wherein said dimensionless thickness divided by said axial chord, has a quadric distribution according to a curve of the fourth order along an axis defining the distance (Z).

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