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Series impingement cooled airfoil

  • US 6,036,441 A
  • Filed: 11/16/1998
  • Issued: 03/14/2000
  • Est. Priority Date: 11/16/1998
  • Status: Expired due to Term
First Claim
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1. A gas turbine engine airfoil comprising:

  • first and second sidewalls joined together at opposite leading and trailing edges, and extending from a root to a tip;

    said sidewalls being spaced apart from each other to define in part first and second adjoining flow chambers extending longitudinally therein, and defined in additional part by corresponding first and second partitions disposed between said sidewalls, with said second partition being in common with both said chambers, and obliquely joining said first partition; and

    said first and second partitions including a plurality of first and second inlet holes, respectively, sized to meter cooling air therethrough in series impingement in said chambers.

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