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公开(公告)号：KR840002484B1
公开(公告)日：1984-12-31
申请号：KR800000733
申请日：1980-02-22
Applicant: UNITED TECHNOLOGIES CORP
Inventor： ARRIGONI JOHN PETER
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公开(公告)号：AU598173B2
公开(公告)日：1990-06-14
申请号：AU7905187
申请日：1987-09-25
Applicant: UNITED TECHNOLOGIES CORP
Inventor： DRAGHI PETER JON , ARRIGONI JOHN PETER
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.
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公开(公告)号：GB2195357A
公开(公告)日：1988-04-07
申请号：GB8721091
申请日：1987-09-08
Applicant: UNITED TECHNOLOGIES CORP
Inventor： DRAGHI PETER JON , ARRIGONI JOHN PETER
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.
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公开(公告)号：BE1002420A3
公开(公告)日：1991-02-05
申请号：BE8701083
申请日：1987-09-24
Applicant: UNITED TECHNOLOGIES CORP
Inventor： DRAGHI PETER JON , ARRIGONI JOHN PETER
Abstract: L'invention concerne la reclassification des zones de distribution définies entre des aubes fixes d'une turbine. Lorsqu'une aube fixe (1) d'une turbine à gaz a subi des déformations et une usure, l'écartement entre des aubes fixes successives (6, 7) définissant des zones de distribution (8, 9) du flux de gaz, augmente. On recharge la zone d'usure en appliquant, sur l'aube, des couches d'un ruban (12) d'une épaisseur uniforme. Ce ruban comprend un mélange d'un agent liant et d'une poudre d'alliage, qui est compatible avec l'alliage du substrat. L'invention est utilisée pour réduire les coûts de remise en état des aubes fixes usées des turbines en évitant tout procédé de cintrage ou de formage à chaud.
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公开(公告)号：ES2008233A6
公开(公告)日：1989-07-16
申请号：ES8702740
申请日：1987-09-24
Applicant: UNITED TECHNOLOGIES CORP
Inventor： DRAGHI PETER JON , ARRIGONI JOHN PETER
IPC: B22F7/04 , B22F7/06 , B23K35/02 , B23P6/00 , F01D5/00 , F01D5/28 , C23C24/08 , C23C10/28 , B23K20/16
Abstract: UN METODO PARA RECLASIFICAR EL AREA DE TOBERA ENTRE PALETAS DE TURBINA ADYACENTES. UNA PALETA DE TURBINA DE GAS (1) SE SOMETE A DISTORSION Y DESGASTE DURANTE EL FUNCIONAMIENTO O REPARACION QUE RESULTA EN UN AUMENTO EN EL ESPACIAMIENTO ENTRE PALETAS SUCESIVAS (6 Y 7) QUE DEFINEN LAS AREAS DE FLUJO DE GAS DE TOBERA (8 Y 9). DURANTE LA RESTAURACION EL ESPACIAMIENTO DE TOBERA DEBE DEVOLVERSE A LA DIMENSION ORIGINAL PARA ASEGURAR EL FUNCIONAMIENTO OPTIMO DE LA TURBINA. UN DESARROLLO DE ALEACION EN EL AREA DE DESGASTE SE LLEVA A CABO APLICANDO DE FORMA CONTROLABLE CAPAS DE UNA CINTA (12) DE ESPESOR UNIFORME A LA PALETA. LA CINTA INCLUYE UNA MEZCLA DE UN LIGANTE Y UN POLVO DE ALEACION, QUE ES COMPATIBLE CON LA ALEACION DE SUSTRATO, ADOPTANDO LA MEZCLA FORMA DE UNA LAMINA DE ESPESOR UNIFORME Y CON UN RESPALDO DE ADHESIVO. DESPUES DE APLICAR LA CINTA EN CAPAS HASTA UN ESPESOR DESEADO SE CALIENTA LA PALETA HASTA UNA TEMPERATURA EN LA QUE SE DESCOMPONEN EL LIGANTE Y ADHESIVO Y LA ALEACION EN LA DIFUSION DE CINTA SE UNE CON LA ALEACION DE SUSTRATO. LA UTILIZACION DE ESTE PROCESO REDUCE EL COSTO DE RESTAURACION DE PALETAS DE TURBINA UTILIZADAS Y EVITA LOS PROCESOS DE FORMACION O DOBLADO EN CALIENTE QUE PUEDEN DETERIORAR LAS PALETAS.
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Patent Agency Ranking
公开(公告)号：MX153216A
公开(公告)日：1986-08-22
申请号：MX18612281
申请日：1981-02-25
Applicant: UNITED TECHNOLOGIES CORP
Inventor： ARRIGONI JOHN PETER
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公开(公告)号：NO169793C
公开(公告)日：1992-08-05
申请号：NO873964
申请日：1987-09-23
Applicant: UNITED TECHNOLOGIES CORP
Inventor： DRAGHI PETER JON , ARRIGONI JOHN PETER
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.
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公开(公告)号：GB2195357B
公开(公告)日：1991-03-27
申请号：GB8721091
申请日：1987-09-08
Applicant: UNITED TECHNOLOGIES CORP
Inventor： DRAGHI PETER JON , ARRIGONI JOHN PETER
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.
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公开(公告)号：CH672641A5
公开(公告)日：1989-12-15
申请号：CH358287
申请日：1987-09-17
Applicant: UNITED TECHNOLOGIES CORP
Inventor： DRAGHI PETER JON , ARRIGONI JOHN PETER
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公开(公告)号：DE3730266A1
公开(公告)日：1988-03-31
申请号：DE3730266
申请日：1987-09-09
Applicant: UNITED TECHNOLOGIES CORP
Inventor： DRAGHI PETER JON , ARRIGONI JOHN PETER
IPC: B22F7/04 , B22F7/06 , B23K35/02 , B23P6/00 , F01D5/00 , C23C24/08 , C23C10/28 , B23K20/16 , F01D5/28
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.
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