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High pressure turbine blade airfoil profile

  • US 8,439,645 B2
  • Filed: 03/30/2010
  • Issued: 05/14/2013
  • Est. Priority Date: 03/30/2010
  • Status: Active Grant
First Claim
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1. A turbine blade of a gas turbine engine having a gaspath, the turbine blade comprising an airfoil having an intermediate portion contained within the gaspath and defined by a nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of Sections 3 to 14 set forth in Table 2, wherein the point of origin of the orthogonally related axes X, Y and Z is located at an intersection of a centerline of the gas turbine engine and a stacking line of the turbine blade, the Z values are radial distances measured along the stacking line, the X and Y are coordinate values defining the profile at each distance Z.

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