DMZ Fracture Boundary Limit
AssigneeUnited Technologies Corporation
InventorsPaul D. Duesler, Paul Filewich
Life of this patent
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Abstract
A method of establishing a boundary for a material improvement process on a workpiece is disclosed. The method may include identifying a maximum allowable damage depth on the workpiece; identifying a maximum constant thickness line on the workpiece at an extent of the maximum allowable damage depth; identifying a peak vibratory stress gradient on the workpiece; identifying a peak combined engine stress on the workpiece; and specifying the boundary for the material improvement process on the workpiece relative to the maximum constant thickness line, peak vibratory stress gradient, and peak combined engine stress.
Claims20
A method of establishing a boundary for a material improvement process on a workpiece, comprising:
- identifying a maximum allowable damage depth on the workpiece;
- identifying a maximum constant thickness line on the workpiece at an extent of the maximum allowable damage depth;
- identifying a peak vibratory stress gradient on the workpiece;
- identifying a peak combined engine stress on the workpiece;
- and
- specifying the boundary for the material improvement process on the workpiece relative to the maximum constant thickness line, peak vibratory stress gradient, and peak combined engine stress.
A method of specifying a boundary for a material improvement process on an airfoil having a leading edge, a trailing edge downstream of the leading edge, a tip, and a base, the method comprising:
- identifying a maximum allowable damage depth from the leading edge of the airfoil;
- identifying a maximum constant thickness line at the maximum allowable damage depth, the constant thickness line extending from the base of the airfoil to the tip of the airfoil;
- identifying a peak vibratory stress gradient on the airfoil;
- identifying a peak combined engine stress along the maximum constant thickness line based in part on the peak vibratory stress gradient;
- and
- specifying a boundary of the material improvement process relative to the maximum allowable damage depth, maximum constant thickness line, peak vibratory stress gradient, and peak combined engine stress on the airfoil.
An airfoil for a gas turbine engine, comprising:
- a pair of opposing sides extending from a leading edge to a trailing edge and extending radially from a base to a tip;
- and
- at least one processed patch extending from the leading edge to a boundary extending from the base to the tip, the boundary positioned in relation to a maximum allowable damage depth, a maximum constant thickness line at an extent of the maximum allowable damage depth, a peak vibratory stress gradient, and a peak combined engine stress on the airfoil.
Dependencies are inferred from the claim text.