公开(公告)号：JP2003155935A

公开(公告)日：2003-05-30

申请号：JP2002242854

申请日：2002-08-23

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DUCOTEY HOWARD S JR ,  ZUBER ROBERT J ,  DRAGHI PETER J

IPC: F01D5/18 ,  B23H9/10 ,  B23H9/14 ,  B23K31/00 ,  B23P6/00 ,  C23C4/02 ,  C23C4/18 ,  C23C28/04 ,  F01D5/00 ,  F01D5/28 ,  F02C7/00

Abstract: PROBLEM TO BE SOLVED: To provide a method for repairing defects in a gas turbine component comprising a substrate and a coating existing on the substrate. SOLUTION: An article includes cooling holes having a predetermined air flow requirement and an outer shaped portion and an inner metering portion. The method comprises removing the existing coating and recoating the surface of the article with a non-original coating. After the non-original coating is applied onto the component, the cooling holes that meet predetermined inspection criteria are reworked to remove the excess non-original coating deposited in the outer shaped portion of the cooling holes. The reworking is done by receiving an electrode, having only a shaped portion with a pre-selected shape, in the outer shaped portion of the cooling holes thus restoring the cooling holes to the predetermined air flow requirement.

公开(公告)号：JP2003269190A

公开(公告)日：2003-09-25

申请号：JP2003063986

申请日：2003-03-10

Applicant: UNITED TECHNOLOGIES CORP

Inventor： BOSE SUDHANGSHU ,  CETEL ALAN D ,  DRAGHI PETER J ,  PIETRUSKA NORMAN

IPC: F01D5/14 ,  B23P6/00 ,  C23C10/02 ,  C23G1/20 ,  F01D5/28 ,  F01D25/00 ,  F02C7/00

Abstract: PROBLEM TO BE SOLVED: To provide a repairing method of a turbine engine part. SOLUTION: This repairing method of the turbine engine part such as a vane and a blade having air foil comprises to remove an oxide deposit from respective parts of a part indicating damage by crushing or oxidation of heat insulating coating, to remove a ceramic heat insulating layer from the part, and to blend a surface of the part generating nicks, dents and cracks. When the part has a deteriorated aluminum area, the deteriorated area is removed or replenished. A tip part of the part is also recovered when the part is damaged, and cutting capacity of the part is restored by applying polishing to the tip part. Afterwards, ceramic coating is applied to the part. COPYRIGHT: (C)2003,JPO

公开(公告)号：JPH1061404A

公开(公告)日：1998-03-03

申请号：JP16706697

申请日：1997-06-24

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DRAGHI PETER J ,  SHURMAN BRIAN J ,  BORRUSO MICHAEL V

IPC: F01D5/18

Abstract: PROBLEM TO BE SOLVED: To keep extremely adjacent other holes opening for a test, by arranging a step for preparing an aerofoil having a plurality of cooling holes and a ultraviolet curing type material to the holes, so that desired holes out of the plurality of cooling holes can be closed. SOLUTION: The aerofoil 10 of a typical turbine blade is equipped with a front edge 12, a rear edge and a row of a plurality of cooling holes 16. The cooling holes 16 are communicated with a cooling passage in the inside of the aerofoil 10. A material 24 used for closing specific holes has sufficient tackiness that the end of the material 24 may not be lifted up during an air treatment process. Also, the material 24 is a ultraviolet curing type material, especially, a ultraviolet curing type acrylic material, has an edge supplementation as well as desired adhesive property and viscosity, and can be arranged to holes extremely adjacent the other holes which can not be closed. Hereby, under a condition that the material 24 does not completely exit for a text, a row 22 of holes can be coated with the material 24 while remaining a row 20 of holes.

公开(公告)号：WO9521042A2

公开(公告)日：1995-08-10

申请号：PCT/US9501310

申请日：1995-01-31

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DRAGHI PETER J ,  PIETRUSKA NORMAN ,  ARMSTRONG WAYNE F

IPC: F01D5/28 ,  B05D7/14 ,  B23K35/02 ,  B23K35/14 ,  B23K35/30 ,  B23P6/04 ,  C23C30/00 ,  C23G5/00 ,  F02C7/00 ,  B23K35/36

CPC classification number: B23P6/007 ,  B23K35/025 ,  B23K35/3033 ,  B23K35/3046 ,  B23K2201/001 ,  C23G5/00

Abstract: A repair coating for superalloy articles, such as gas turbine engine components, includes a volatile organic carrier or water-based carrier, a fluxing agent, a thickening agent, balance a filler mix. The filler mix consists of at least two distinct particulate components. The mix includes a first particulate component having a composition which approximates that of the article being repaired. The mix also includes a second particulate component having a composition approximating that of the article and a melting point depressant, such as boron. This melting point depressant is substantially in excess of that in the article and sufficient to provide melting of a portion of the mix at a processing temperature below the melting temperature of the article. The above filler mix is blended with the other constituents to form the repair coating which is applied to an article.

Abstract translation: 用于超级合金制品（例如燃气轮机发动机部件）的修补涂层包括挥发性有机载体或水基载体，助熔剂，增稠剂，平衡填料混合物。 填料混合物由至少两种不同的颗粒组分组成。 混合物包括具有近似于待修补物品的组成的第一颗粒组分。 混合物还包括具有接近制品的组成和熔点降低剂如硼的第二颗粒组分。 该熔点抑制剂基本上超过制品中的熔点降低剂，并且足以在低于制品的熔融温度的加工温度下提供一部分混合物的熔融。 将上述填料混合物与其它组分混合以形成施加到制品上的修补涂层。

公开(公告)号：DE60217590D1

公开(公告)日：2007-03-08

申请号：DE60217590

申请日：2002-06-21

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DUCOTEY HOWARD S JR ,  ZUBER ROBERT J ,  DRAGHI PETER J

IPC: F01D5/00 ,  F01D5/18 ,  B23H9/10 ,  B23H9/14 ,  B23K31/00 ,  B23P6/00 ,  C23C4/02 ,  C23C4/18 ,  C23C28/04 ,  F01D5/28 ,  F02C7/00

Abstract: A method is disclosed for repairing defects in a gas turbine component 10 that comprises a substrate 58 and an existing coating 44 on the substrate 58. The article 10 includes cooling holes 18 having a predetermined air flow requirement and an outer shaped portion 52 and an inner metering portion 60. The method comprises removing the existing coating 44 and recoating the surface of the article with a nonoriginal coating. After the nonoriginal coating is applied onto the component, the cooling holes 18 that meet a predetermined inspection criteria are reworked to remove the excess nonoriginal coating deposited in the outer shaped portion 52 of the cooling holes 18. The reworking is done by receiving an electrode 52, having only a shaped portion with a preselected shape, in the outer shaped portion 50 of the cooling holes 18 thus restoring the cooling holes to the predetermined air flow requirement.

公开(公告)号：DE602005021839D1

公开(公告)日：2010-07-29

申请号：DE602005021839

申请日：2005-03-16

Applicant: UNITED TECHNOLOGIES CORP

Inventor： VELEZ RAMON M JR ,  DRAGHI PETER J

IPC: B08B9/00 ,  B08B1/04 ,  B08B9/087 ,  F01D25/00 ,  F02C7/00

公开(公告)号：DE69714524D1

公开(公告)日：2002-09-12

申请号：DE69714524

申请日：1997-06-11

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DRAGHI PETER J ,  SHURMAN BRIAN J ,  BORRUSO MICHAEL V

IPC: F01D5/18

Abstract: A process for closing cooling holes of an airfoil includes the steps of providing an airfoil having a plurality of cooling holes, closing desired holes of said plurality of cooling holes by applying an ultraviolet curable material over the holes.

公开(公告)号：IE920793A1

公开(公告)日：1992-09-23

申请号：IE920793

申请日：1992-03-12

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SMOLINSKI JOHN J ,  DRAGHI PETER J ,  DANIELSEN JOHN R

IPC: B21D11/20 ,  B23K26/00 ,  B23K26/34 ,  C21D1/00 ,  F01D5/00 ,  F02C7/00

Abstract: A procedure is described for the repair of gas turbine engine turbine components which involves the repair of cracks and other defects and the replacement of worn or eroded material followed by the laser melting of a thin layer of metal on the surface of the component in those areas requiring reconfiguration to return to the original dimensions. The reconfiguration by laser melting is also useful for new articles which are out of tolerance, and generally for shaping objects from metal sheet or plate.

公开(公告)号：DE60217590T3

公开(公告)日：2013-10-10

申请号：DE60217590

申请日：2002-06-21

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DUCOTEY HOWARD S JR ,  ZUBER ROBERT J ,  DRAGHI PETER J

IPC: F01D5/00 ,  F01D5/18 ,  B23H9/10 ,  B23H9/14 ,  B23K31/00 ,  B23P6/00 ,  C23C4/02 ,  C23C4/18 ,  C23C28/04 ,  F01D5/28 ,  F02C7/00

公开(公告)号：DE60217590T2

公开(公告)日：2007-10-11

申请号：DE60217590

申请日：2002-06-21

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DUCOTEY HOWARD S JR ,  ZUBER ROBERT J ,  DRAGHI PETER J

IPC: F01D5/00 ,  F01D5/18 ,  B23H9/10 ,  B23H9/14 ,  B23K31/00 ,  B23P6/00 ,  C23C4/02 ,  C23C4/18 ,  C23C28/04 ,  F01D5/28 ,  F02C7/00

Abstract: A method is disclosed for repairing defects in a gas turbine component 10 that comprises a substrate 58 and an existing coating 44 on the substrate 58. The article 10 includes cooling holes 18 having a predetermined air flow requirement and an outer shaped portion 52 and an inner metering portion 60. The method comprises removing the existing coating 44 and recoating the surface of the article with a nonoriginal coating. After the nonoriginal coating is applied onto the component, the cooling holes 18 that meet a predetermined inspection criteria are reworked to remove the excess nonoriginal coating deposited in the outer shaped portion 52 of the cooling holes 18. The reworking is done by receiving an electrode 52, having only a shaped portion with a preselected shape, in the outer shaped portion 50 of the cooling holes 18 thus restoring the cooling holes to the predetermined air flow requirement.