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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
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.
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公开(公告)号：DE69826970D1
公开(公告)日：2004-11-18
申请号：DE69826970
申请日：1998-12-18
Applicant: UNITED TECHNOLOGIES CORP
Inventor： WALKER HERBERT L , HILTON STEPHEN A , BARBIERI JO ANN , FOURNIER JOHN P , TRASK RICHARD D
Abstract: A process for joining a base (122) for an airfoil (44) to a disk (42) for an integrally bladed rotor stage (38) in a gas turbine engine (10) includes providing a disk (42) having a radially outer rim (46) with a slot (90) defined therein by a recessed surface (96), and further includes providing a base (122) having a longitudinally extending root portion (126) facing opposite a longitudinally extending support portion (124) for supporting the airfoil (120). The root portion has a root surface (130) and the support portion has an outer surface (128). The process further includes bringing the root surface of the root portion into contact with the recessed surface bounding the slot, applying pressure (134) and relative movement (136) between the base and the rim to achieve during welding, substantial contiguity between the root surface and the recessed surface over the area of the recessed surface, resulting in a substantially continuous linear friction weld between the base and the rim.
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公开(公告)号：DE69826970T2
公开(公告)日：2005-03-10
申请号：DE69826970
申请日：1998-12-18
Applicant: UNITED TECHNOLOGIES CORP
Inventor： WALKER HERBERT L , HILTON STEPHEN A , BARBIERI JO ANN , FOURNIER JOHN P , TRASK RICHARD D
Abstract: A process for joining a base (122) for an airfoil (44) to a disk (42) for an integrally bladed rotor stage (38) in a gas turbine engine (10) includes providing a disk (42) having a radially outer rim (46) with a slot (90) defined therein by a recessed surface (96), and further includes providing a base (122) having a longitudinally extending root portion (126) facing opposite a longitudinally extending support portion (124) for supporting the airfoil (120). The root portion has a root surface (130) and the support portion has an outer surface (128). The process further includes bringing the root surface of the root portion into contact with the recessed surface bounding the slot, applying pressure (134) and relative movement (136) between the base and the rim to achieve during welding, substantial contiguity between the root surface and the recessed surface over the area of the recessed surface, resulting in a substantially continuous linear friction weld between the base and the rim.
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