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Gas turbine test airfoil

  • US 5,314,307 A
  • Filed: 12/18/1992
  • Issued: 05/24/1994
  • Est. Priority Date: 12/18/1992
  • Status: Expired due to Fees
First Claim
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1. A gas turbine engine airfoil designed for failure, comprising:

  • an aerodynamic blade adapted to be placed in momentum exchange relationship with a fluid stream;

    a platform from which said blade extends radially outwardly;

    a dovetail shaped root extending radially inwardly from said platform and adapted to be received in a generally complementally shaped groove at the outer periphery of a rotary wheel, said dovetail root having radially outwardly facing, axially extending, load carrying faces, and a radially innermost, axially extending bottom face, said dovetail further having an internal bore extending through its axial length and a radial slot between said bore and said bottom face; and

    a tubular insert within said internal bore, said insert being of a material having strength characteristics such that said insert fails under preselected conditions to cause release of the airfoil from the rotary wheel.

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