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Gas turbine engine blade

  • US 6,554,572 B2
  • Filed: 05/17/2001
  • Issued: 04/29/2003
  • Est. Priority Date: 05/17/2001
  • Status: Expired due to Fees
First Claim
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1. A method of modifying a turbine blade in a gas turbine engine, comprising:

  • a) increasing tilt by 18.5 percent;

    b) decreasing lean by 40 percent; and

    c) reducing number of cooling holes, while increasing diameter of at least some holes, to maintain cooling airflow unchanged.

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