公开(公告)号：NO873964L

公开(公告)日：1988-03-28

申请号：NO873964

申请日：1987-09-23

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DRAGHI PETER JON ,  ARRIGONI JOHN PETER

IPC: B22F7/04 ,  B22F7/06 ,  B23K35/02 ,  B23P6/00 ,  F01D5/00 ,  F01D

Abstract: A gas turbine vane (1) is subject to distortion and wear during operation or repair which results in an increase in the spacing between successive vanes (6 and 7) which define nozzle gas flow areas (8 and 9). During refurbishment, the nozzle spacing must be returned to the original dimension to insure optimum turbine performance. A build up of alloy in the wear area is accomplished by controllably applying layers of a tape (12) of uniform thickness to the vane. The tape includes a mixture of a binder and an alloy powder, which is compatible with the substrate alloy, with the mixture formed into a sheet of uniform thickness and having an adhesive backing. After applying the tape in layers to a desired thickness, the vane is heated to a temperature at which the binder and adhesive decompose and the alloy in the tape diffusion bonds with the substrate alloy. Utilization of this process reduces the cost of refurbishing used turbine vanes and avoids hot forming or bending processes which could damage the vanes.

公开(公告)号：NO873964A

公开(公告)日：1988-03-28

申请号：NO873964

申请日：1987-09-23

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DRAGHI PETER JON ,  ARRIGONI JOHN PETER

IPC: B22F7/04 ,  B22F7/06 ,  B23K35/02 ,  B23P6/00 ,  F01D5/00 ,  F01D

CPC classification number: B23P6/005 ,  B22F7/062 ,  B23K35/0233 ,  B23K35/0244 ,  B23P6/007 ,  F01D5/005 ,  Y10T29/49318 ,  Y10T29/49726 ,  Y10T29/49728 ,  Y10T29/4973 ,  Y10T29/49732 ,  Y10T29/49734 ,  Y10T29/49737 ,  Y10T29/49742 ,  Y10T29/4975 ,  Y10T403/479

公开(公告)号：NO873964D0

公开(公告)日：1987-09-23

申请号：NO873964

申请日：1987-09-23

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DRAGHI PETER JON ,  ARRIGONI JOHN PETER

IPC: B22F7/04 ,  B22F7/06 ,  B23K35/02 ,  B23P6/00 ,  F01D5/00 ,  F01D

Abstract: A gas turbine vane (1) is subject to distortion and wear during operation or repair which results in an increase in the spacing between successive vanes (6 and 7) which define nozzle gas flow areas (8 and 9). During refurbishment, the nozzle spacing must be returned to the original dimension to insure optimum turbine performance. A build up of alloy in the wear area is accomplished by controllably applying layers of a tape (12) of uniform thickness to the vane. The tape includes a mixture of a binder and an alloy powder, which is compatible with the substrate alloy, with the mixture formed into a sheet of uniform thickness and having an adhesive backing. After applying the tape in layers to a desired thickness, the vane is heated to a temperature at which the binder and adhesive decompose and the alloy in the tape diffusion bonds with the substrate alloy. Utilization of this process reduces the cost of refurbishing used turbine vanes and avoids hot forming or bending processes which could damage the vanes.