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Cooled blades for a gas turbine engine

  • US 5,700,131 A
  • Filed: 08/24/1988
  • Issued: 12/23/1997
  • Est. Priority Date: 08/24/1988
  • Status: Expired due to Term
First Claim
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1. A turbine blade surface for a gas turbine engine having internal passages for flowing cooling air therein, the blade having an airfoil surface defining a root section, a leading edge section, a trailing edge section, a mid chord section, and a tip section, a plurality of radial internal passages defined by internal wall means formed adjacent said trailing edge section and leading edge section extending from said root section to said tip section defining a feed channel, a plurality of radially spaced film cooling holes in said airfoil surface communicating with said feed channel to flow a film of cooling air adjacent said airfoil surface, a plurality of replenishment holes spaced radially in said wall means for flowing cooling air from said mid cord section to said feed channel to replenish the cooling air in said feed channel that is otherwise lost in supplying cooling air to said film cooling holes, and means for communicating cooling air from said root section to discharge from an orifice in said airfoil surface at said tip section, and a source of cooling air for feeding cooling air to said root section.

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