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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
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.
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Patent Agency Ranking
公开(公告)号：GB2234526B
公开(公告)日：1993-11-10
申请号：GB9014728
申请日：1990-07-03
Applicant: UNITED TECHNOLOGIES CORP
Inventor： ROUTSIS KOSTAS , PARKOS JR JOSEPH JOHN , FRELING MELVIN
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.
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公开(公告)号：GB2234526A
公开(公告)日：1991-02-06
申请号：GB9014728
申请日：1990-07-03
Applicant: UNITED TECHNOLOGIES CORP
Inventor： ROUTSIS KOSTAS , PARKOS JR JOSEPH JOHN
Abstract: A method for providing an abrasive layer on the surface of a turbine engine blade tips includes application of several layers of nickel; one layer including abrasive particulates and then heat-treating for bonding. The layer has good bond strength and has a thin cross section, thereby minimizing any effect on the fatigue strength of the component.
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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
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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
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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
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.
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