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Title:
IMPARTING DEEP COMPRESSIVE RESIDUAL STRESSES INTO A GAS TURBINE ENGINE AIRFOIL PERIPHERAL REPAIR WELDMENT
Document Type and Number:
WIPO Patent Application WO/2010/036430
Kind Code:
A3
Abstract:
A gas turbine engine airfoil (34) is repaired by machining away airfoil material (50) along at least a portion of at least one of leading (LE) and trailing edges (TE) and a radially outer tip (38) forming at least one cut-back (80) area and forming a weldment by welding successive beads (70) of welding material (72) into the cut -back area (80). Desired finished dimensions of the repaired airfoil are obtained by machining away some of the weld bead material in the weldment and then deep compressive residual stresses are imparted in a pre-stressed region (56) extending into and encompassing the weldment (82) and a portion (26) of the airfoil adjacent the weldment (82). The compressive residual stresses may be imparted after either rough machining or final finishing thereafter of the weldment (82). The cut -back area (80) may extend up to about 90% of the airfoil's span (5) and have a maximum cut-back depth (L) up to about.22 inches.

Inventors:
ROCKSTROCH TODD JAY (US)
MANNAVA SEETHA RAMAIAH (US)
BARBE ROGER OWEN (US)
LAWRENCE WAYNE LEE (US)
Application Number:
PCT/US2009/047974
Publication Date:
June 17, 2010
Filing Date:
June 19, 2009
Export Citation:
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Assignee:
GEN ELECTRIC (US)
ROCKSTROCH TODD JAY (US)
MANNAVA SEETHA RAMAIAH (US)
BARBE ROGER OWEN (US)
LAWRENCE WAYNE LEE (US)
International Classes:
F01D5/00; B23P6/00
Domestic Patent References:
WO2007081924A22007-07-19
Foreign References:
US6238187B12001-05-29
EP1153699A22001-11-14
US5846057A1998-12-08
US20030066192A12003-04-10
Attorney, Agent or Firm:
PHILLIPS, Roger C. et al. (Global Patent Operation Po Box 861,2 Corporate Drive, Suite 64, Shelton CT, US)
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