公开(公告)号：JPH11247615A

公开(公告)日：1999-09-14

申请号：JP36043198

申请日：1998-12-18

Applicant: UNITED TECHNOLOGIES CORP

Inventor： WALKER HERBERT L ,  HILTON STEPHEN A ,  BARBIERI JOANN ,  FOURNIER JOHN P ,  TRASK RICHARD D

IPC: F01D5/30 ,  B23K20/12

Abstract: PROBLEM TO BE SOLVED: To provide an improved method for connecting the base part of an airfoil to the disk of the blade integrated rotor assembly of a gas turbine engine. SOLUTION: In this method for connecting the base part 122 of an airfoil 120 to the disk of the blade integrated rotor stage of a gas turbine engine, a slot partitioned by a recessed surface 96 is arranged in the disk provided with a radial outside rim part 46, and the airfoil 120 is used which has a base part having a root part 126 provided with a root part surface 130 and extended in a longitudinal direction. The root part surface 130 and the recessed surface 96 are brought into contact with each other and pressed, and the base part 122 and the rim part 46 are relatively moved, thereby the root part 126 and the recessed surface 96 are substantially brought into contact with each other over the area of the recessed surface 96 during welding. Hereby, a successive linear frictional welding part can be obtained between the base part 122 and the rim part 46.