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.

公开(公告)号：JPH10193141A

公开(公告)日：1998-07-28

申请号：JP35432897

申请日：1997-12-24

Applicant: UNITED TECHNOLOGIES CORP

Inventor： TRASK RICHARD D ,  GOETSCHIUS SUSAN H ,  HILTON STEPHEN A

IPC: B23K20/12 ,  F01D5/30

Abstract: PROBLEM TO BE SOLVED: To prevent physical or chemical damage to the final shape, where one of the two members is a stub member, by providing a collar having a face to come into contact with the stub member, and executing welding without imparting a substantial restraint to the external surface of the stub member. SOLUTION: A stub to use is provided with a thickness in the radial direction and a width, with the thickness in the radial direction less than three times the width or thinner than the width, with the stub and the collar each provided with an external surface in the radial direction, and with the external surfaces essentially on the same plane. The stub 42 extends from the front edge 33 to the rear edge 34, while its thickness 43 in the radial direction, i.e., the height, is uniform. The stub 42 is provided with an external surface 44 in the radial direction, with linear friction welding executed in this part. The collar 46, 47 is installed on the front edge 33 and the rear edge 34 of the stub 42, and is each provided with a partial band 48, 49 and a band base 50, 51.

公开(公告)号：JP2003200277A

公开(公告)日：2003-07-15

申请号：JP2002369250

申请日：2002-12-20

Applicant: UNITED TECHNOLOGIES CORP

Inventor： TRASK RICHARD D

IPC: B23K20/12 ,  F01D5/30

Abstract: PROBLEM TO BE SOLVED: To provide a friction welding method and apparatus applicable to a curved workpiece. SOLUTION: An apparatus for friction-welding a workpiece to a substrate comprises an actuator 129 producing a linear oscillation motion, a platform 127 for supporting the workpiece, and a slide mechanism 235. The slide mechanism 235 converts the linear oscillating motion of the actuator 129 into an arcuate oscillating motion of the platform 127, making the workpiece oscillating arcuately relative to the substrate by the platform 127. COPYRIGHT: (C)2003,JPO

公开(公告)号：DE60226830D1

公开(公告)日：2008-07-10

申请号：DE60226830

申请日：2002-12-19

Applicant: UNITED TECHNOLOGIES CORP

Inventor： TRASK RICHARD D

IPC: B23K20/12 ,  F01D5/30

Abstract: An apparatus (100) for friction welding a workpiece (W) to a substrate (S), comprising an actuator (129) producing a linear oscillating motion, a platform (127) for supporting the workpiece (W), and a slide mechanism (235) between the actuator (129) and the platform (127). The slide mechanism (235) converts the linear oscillating motion of the actuator (129) into an arcuate oscillating motion of the platform (127). The slide (235) could comprise a base (237) and a guide engaging the platform. More specifically, the invention relates to friction welding blades to a rotor.

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

IPC: F01D5/30 ,  B23K20/12 ,  B23K9/12

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.

公开(公告)号：DE69734232D1

公开(公告)日：2005-10-27

申请号：DE69734232

申请日：1997-12-23

Applicant: UNITED TECHNOLOGIES CORP

Inventor： TRASK RICHARD D ,  GOETSCHIUS SUSAN H ,  HILTON STEPHEN A

IPC: B23K20/12 ,  F01D5/30

公开(公告)号：DE69734232T2

公开(公告)日：2006-03-16

申请号：DE69734232

申请日：1997-12-23

Applicant: UNITED TECHNOLOGIES CORP

Inventor： TRASK RICHARD D ,  GOETSCHIUS SUSAN H ,  HILTON STEPHEN A

IPC: B23K20/12 ,  F01D5/30

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

IPC: F01D5/30 ,  B23K20/12 ,  B23K9/12

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.