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Varying cross-sectional area guide blade

  • US 8,459,934 B2
  • Filed: 09/23/2010
  • Issued: 06/11/2013
  • Est. Priority Date: 03/28/2008
  • Status: Expired due to Fees
First Claim
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1. A guide blade for a gas turbine, comprising:

  • an inner platform;

    an outer platform;

    an airfoil extending in a radial direction between the inner platform and the outer platform and having a height in the radial direction; and

    at least one cooling channel disposed in an interior of the airfoil and configured to receive a cooling medium flowing through the at least one cooling channel configured to cool the guide blade, wherein a blade material cross-sectional area of the airfoil varies over the height, wherein the blade material cross-sectional area is a difference between an entire guide blade cross-section of the at least one cooling channel, and wherein the blade material cross-sectional area includes a minimum cross-sectional area disposed in a region between 20% and 40% of the height from the inner platform.

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