To provide a method of reducing crack propagation in an airfoil part 22.
This method includes steps of: preparing an airfoil part 22 having a root 36 spaced apart from a tip 34, spaced-apart leading and trailing edges 30 and 32, a negative-pressure side surface 40 extending from the leading edge 30 to the trailing edge 32, and an opposed positive-pressure side surface 38 extending from the leading edge 30 and the trailing edge 32; and supporting the airfoil part 22 against bending loads. The airfoil part 22 is burnished by using a burnishing element 42 to form at least one burnished section 68 of residual compressive stress. The at least one burnished section 68 is located adjacent the leading edge 30 and spaced from the leading edge 30 by an offset distance selected to avoid deformation of the leading edge 30.
MILLER JOSHUA L
DINGWELL WILLIAM TERENCE
BRUNCK MICHAEL JAY
IMHOFF WILLIAM LEE
MONCELLE PAUL
LOMBARDO DALE R
WOODFIELD ANDREW P
| JP2002526271A | 2002-08-20 | |||
| JPS5715609A | 1982-01-27 |
| US20060147311A1 | 2006-07-06 |
Hirokazu Ogura
Toshihisa Kurokawa
Arakawa Satoshi