公开(公告)号：SG126092A1

公开(公告)日：2006-10-30

申请号：SG200601822

申请日：2006-03-20

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DEBICCARI ANDREW ,  FRELING MELVIN ,  HAYNES JEFFREY D

公开(公告)号：CA2252658A1

公开(公告)日：1999-05-26

申请号：CA2252658

申请日：1998-11-03

Applicant: UNITED TECHNOLOGIES CORP

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

IPC: F01D5/20 ,  F01D11/00 ,  F01D11/12 ,  F02C7/28 ,  F16J15/16 ,  F01D5/28 ,  F01D11/08 ,  F01D11/14 ,  C09K3/14 ,  C04B35/48

Abstract: A gas turbine engine seal system includes a rotating member having an abrasive tip disposed in rub relationship to a stationary, abradable seal surfac e. The abrasive tip comprises a zirconium oxide abrasive coat having a columnar structu re that is harder than the abradable seal surface such that the abrasive tip can cu t the abradable seal surface.

公开(公告)号：GB2310897B

公开(公告)日：1998-05-13

申请号：GB9708591

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 ,  F04D29/02 ,  F04D29/08 ,  F04D29/32 ,  F04D29/38

公开(公告)号：GB2286600B

公开(公告)日：1997-10-08

申请号：GB9503041

申请日：1995-02-16

Applicant: UNITED TECHNOLOGIES CORP

Inventor： FRELING MELVIN ,  GUPTA DINESH KUMAR

IPC: F02C7/00 ,  B64C1/40 ,  C23C4/02 ,  F01D21/04 ,  F02C7/24 ,  F02C7/25 ,  C23C4/04 ,  C23C28/00

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：GB2310897A

公开(公告)日：1997-09-10

申请号：GB9708591

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 ,  F04D29/02 ,  F04D29/08 ,  F04D29/32 ,  F04D29/38

公开(公告)号：FR2711181B1

公开(公告)日：1996-06-28

申请号：FR9412223

申请日：1994-10-13

Applicant: UNITED TECHNOLOGIES CORP

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

IPC: F01D5/20 ,  F01D5/28 ,  F04D29/02 ,  F04D29/08 ,  F01D5/14 ,  F04D29/32 ,  F04D29/38 ,  F01D11/12

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：GB2286600A

公开(公告)日：1995-08-23

申请号：GB9503041

申请日：1995-02-16

Applicant: UNITED TECHNOLOGIES CORP

Inventor： FRELING MELVIN ,  GUPTA DINESH KUMAR

IPC: F02C7/00 ,  B64C1/40 ,  C23C4/02 ,  F01D21/04 ,  F02C7/24 ,  F02C7/25 ,  C23C4/04 ,  C23C28/00

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：GB2282856A

公开(公告)日：1995-04-19

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: The blades 20 in the turbine engine are configured so as to reduced stress at the tip of the blades during operation of the turbine engine, thus helping to counteract the detrimental effect of abrasive tip coatings on blade fatigue strength. In one embodiment, the tip of the blade 20 is chamfered 30 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, (figs. 10, 11) an abrasive coating (68) 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：DE4021044A1

公开(公告)日：1991-01-17

申请号：DE4021044

申请日：1990-07-02

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ROUTSIS KOSTAS ,  PARKOS JUN JOSEPH JOHN ,  FRELING MELVIN

IPC: F01D5/28 ,  C25D5/14 ,  C25D15/02 ,  F01D5/20

Abstract: An abrasive layer is formed on the tip portion of a turbine engine blade made of Ti alloy by (a) electroplating a 12-18 microns thick first Ni layer onto the blade tip; (b) electroplating a max. 1 micron thick second Ni layer; (c) electroplating a third Ni layer, immersing the tip in a slurry of electrically non-conductive particles in an electroplating soln. present on a membrane which is permeable to electric current and the soln., and then contg. electroplating of the third Ni layer; (d) electroplating a fourth Ni layer such that the combined thickness of the third and fourth layers corresponds to 50-95% of the mean dimension of the embedded particles, and (e) heat treating the blade to cause diffusion between the first Ni layer and the blade tip.

公开(公告)号：DE3470569D1

公开(公告)日：1988-05-26

申请号：DE3470569

申请日：1984-07-06

Applicant: UNITED TECHNOLOGIES CORP

Inventor： RASHID JAMES MARK ,  FRELING MELVIN ,  FRIEDRICH LEONARD ALBERT

IPC: C23C12/02 ,  C23C12/00 ,  C23C10/40 ,  C23C8/70 ,  B32B15/01

Abstract: Chromium boron diffusion coatings on nickel iron alloys uniquely provide them with improvement in high cycle fatigue strength (up to 30%) and erosion resistance (up to 15 times), compared to uncoated alloy. The diffused chromium layer extends in two essential concentration zones to a total depth of about40 x 10 -6 m while the succeeding boron layer is limited to 50-90% of the depth of the richest Cr layer nearest the surface. Both coatings are applied using conventional pack diffusion processes.