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Asymmetrically shaped trailing edge cooling holes

  • US 9,145,773 B2
  • Filed: 05/14/2012
  • Issued: 09/29/2015
  • Est. Priority Date: 05/09/2012
  • Status: Active Grant
First Claim
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1. A gas turbine engine turbine airfoil comprising:

  • widthwise spaced apart pressure and suction sidewalls extending outwardly along a span from an airfoil base to an airfoil tip;

    the pressure and suction sidewalls extending chordwise between opposite leading and trailing edges;

    a spanwise row of spanwise spaced apart trailing edge cooling holes encased in the airfoil between the pressure and suction sidewalls and ending at corresponding spanwise spaced apart trailing edge cooling slots extending chordally substantially to the trailing edge;

    each of the cooling holes including one or more asymmetric intermediate sections leading into the trailing edge cooling slot;

    an asymmetric flow cross section in the one or more asymmetric intermediate sections;

    the asymmetric flow cross section being asymmetric with respect to a mid-plane extending axially and spanwise through the one or more asymmetric intermediate sections; and

    at least one raised floor extending away from one or both of the pressure or suction sidewalls and extending downstream in and at least partially through the one or more asymmetric intermediate sections or extending downstream in and at least partially through the one or more asymmetric intermediate sections and least partially through the cooling slot, the raised floor including in downstream serial relationship an up ramp, a down ramp, and a flat transition section between the up and down ramps.

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