公开(公告)号：SG71165A1

公开(公告)日：2000-03-21

申请号：SG1998004201

申请日：1998-10-14

Applicant: UNITED TECHNOLOGIES CORP

Inventor： FRELING MELVIN ,  GUPTA DINESH K ,  LAGUEUX KEN ,  DEMASI-MARCIN JEANINE T

IPC: F01D5/20 ,  F01D11/00 ,  F01D11/12 ,  F02C7/28 ,  F16J15/16 ,  F01D5/28

Abstract: A gas turbine engine seal system includes a rotating member 12;30 having an abrasive tip 28 disposed in use in rub relationship to a stationary, abradable seal surface. The abrasive tip comprises a zirconium oxide abrasive coat 44 having a columnar structure that is harder than the abradable seal surface such that the abrasive tip can cut the abradable seal surface. The coat 44 comprises zirconium oxide and about 3% to 25% of a stabilizer selected from yttrium oxide, magnesium oxide, calcium oxide or mixtures thereof.

公开(公告)号：GB2282856B

公开(公告)日：1998-05-13

申请号：GB9420419

申请日：1994-10-11

Applicant: UNITED TECHNOLOGIES CORP

Inventor： FRELING MELVIN ,  GRUVER GARY A ,  PARKOS JR JOSEPH JOHN ,  WELCH DOUGLAS A

IPC: F01D5/20 ,  F01D5/28 ,  F01D5/14 ,  F04D29/02 ,  F04D29/08 ,  F04D29/32 ,  F04D29/38

Abstract: A method and apparatus for increasing blade fatigue strength in a turbine engine. The blades in the turbine engine are configured so as to reduce stress at the tip of the blades during operation of the turbine engine, thus increasing blade fatigue strength. This stress reduction helps to counteract the detrimental effect of abrasive tip coatings on blade fatigue strength. In one embodiment, the tip of the blade is chamfered in order to reduce the stress on the tip of the blade. An abrasive coating is then applied to the tip of the blade to assist the blade in seating into an abradable outer air seal. In another embodiment, an abrasive coating is applied to a center portion of the tip of the blade, with the periphery of the abrasive coating being set back from the opposing surfaces of the blade.

公开(公告)号：DE19505303C2

公开(公告)日：1998-02-26

申请号：DE19505303

申请日：1995-02-16

Applicant: UNITED TECHNOLOGIES CORP

Inventor： FRELING MELVIN ,  GUPTA DINESH K

IPC: F02C7/00 ,  B64C1/40 ,  C23C4/02 ,  F01D21/04 ,  F02C7/24 ,  F02C7/25 ,  C23C4/04 ,  F16L59/02

Abstract: In a gas turbine engine, a method and apparatus for containing molten materials and ignited titanium and titanium alloys within the confines of the turbine engine environment. The method includes the step of first applying a bond coating to the inner surface of the outer compressor casing. The bond coating is then plasma oversprayed with a non-reactive, thermally insulative ceramic top coating. The apparatus includes a substrate having a bond coating and a ceramic top coating, surrounding at least a portion of the gas turbine engine, for containing turbine engine fires within the turbine engine environment. Preferably, the bond coating is a Ni-Co-Cr-Al-Y alloy, and the top coat is stabilized zirconia.

公开(公告)号：DE19505303A1

公开(公告)日：1995-08-17

申请号：DE19505303

申请日：1995-02-16

Applicant: UNITED TECHNOLOGIES CORP

Inventor： FRELING MELVIN ,  GUPTA DINESH K

IPC: F02C7/00 ,  B64C1/40 ,  C23C4/02 ,  F01D21/04 ,  F02C7/24 ,  F02C7/25 ,  C23C4/04 ,  F16L59/02

Abstract: In a gas turbine engine, a method and apparatus for containing molten materials and ignited titanium and titanium alloys within the confines of the turbine engine environment. The method includes the step of first applying a bond coating 52 to the inner surface 44 of the outer compressor casing 36. The bond coating 52 is then plasma oversprayed with a non-reactive thermally insulative ceramic top coating 54. The apparatus includes a substrate 48 having a bond coating and a ceramic top coating, surrounding at least a portion of the gas turbine engine, for containing turbine engine fires within the turbine engine environment. Preferably, the bond coating 52 is a Ni-Co-Cr-Al-Y alloy, and the top coat 54 is stabilized zirconia.

公开(公告)号：DE69826096T3

公开(公告)日：2012-01-12

申请号：DE69826096

申请日：1998-11-24

Applicant: UNITED TECHNOLOGIES CORP

Inventor： FRELING MELVIN ,  GUPTA DINESH K ,  LAGUEUX KEN ,  DEMASI-MARCIN JEANINE T

IPC: F01D5/20 ,  F01D5/28 ,  F01D11/00 ,  F01D11/12 ,  F02C7/28 ,  F16J15/16

公开(公告)号：DE602006008847D1

公开(公告)日：2009-10-15

申请号：DE602006008847

申请日：2006-03-22

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DEBICCARI ANDREW ,  FRELING MELVIN ,  HAYNES JEFFREY D

IPC: C23C24/04 ,  F01D5/00

公开(公告)号：SG153768A1

公开(公告)日：2009-07-29

申请号：SG2008092439

申请日：2008-12-15

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SCHLICHTING KEVIN W ,  FRELING MELVIN

Abstract: A method for coating a substrate of a turbine engine component, the method comprising cold spray depositing a metal-based material onto a surface of the substrate, and heating the deposited metal-based material to increase the porosity of the deposited metal-based material.

公开(公告)号：SG143163A1

公开(公告)日：2008-06-27

申请号：SG2007176399

申请日：2007-11-09

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SCHLICHTING KEVIN W ,  LITTON DAVID A ,  PIETRASZKIEWICZ EDWARD F ,  FRELING MELVIN ,  DIERBERGER JAMES A

Abstract: THERMAL BARRIER COATING FOR COMBUSTOR PANELS A method is disclosed that selectively applies thermal barrier coatings that exhibit different degrees of thermal conductivity to different inner surface areas of engine combustor panels. Different types of TBCs are applied to predetermined inner surface areas of a combustor panel based on empirical observation or prediction. TBCs exhibiting low thermal conductivity are applied to combustor panel areas that are exposed to hotter temperatures and TBCs exhibiting higher thermal conductivity are applied to areas that are exposed to lower temperatures.

公开(公告)号：SG134217A1

公开(公告)日：2007-08-29

申请号：SG2006086789

申请日：2006-12-12

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MALONEY MICHAEL J ,  LITTON DAVID A ,  SCHLICHTING KEVIN W ,  FRELING MELVIN ,  SMEGGIL JOHN G ,  SNOW DAVID B

Abstract: A process of coating an article includes the steps of (1) forming a layer of a ceramic based compound on an article; (2) providing a solution containing a metal as a particulate having a diameter of about 10 nanometers to about 1000 nanometers and present in an amount of about 25 percent to about 50 percent by volume of the solution; (3) contacting the ceramic based compound layer with the solution; (4) drying the article; and (5) optionally repeating steps (3) and (4).

公开(公告)号：DE69826096T2

公开(公告)日：2005-09-29

申请号：DE69826096

申请日：1998-11-24

Applicant: UNITED TECHNOLOGIES CORP

Inventor： FRELING MELVIN ,  GUPTA DINESH K ,  LAGUEUX KEN ,  DEMASI-MARCIN JEANINE T

IPC: F01D5/20 ,  F01D11/00 ,  F01D11/12 ,  F02C7/28 ,  F16J15/16 ,  F01D5/28

Abstract: A gas turbine engine seal system includes a rotating member 12;30 having an abrasive tip 28 disposed in use in rub relationship to a stationary, abradable seal surface. The abrasive tip comprises a zirconium oxide abrasive coat 44 having a columnar structure that is harder than the abradable seal surface such that the abrasive tip can cut the abradable seal surface. The coat 44 comprises zirconium oxide and about 3% to 25% of a stabilizer selected from yttrium oxide, magnesium oxide, calcium oxide or mixtures thereof.