Coating processes – Nonuniform coating – Applying superposed diverse coatings or coating a coated base
Reexamination Certificate
1999-06-30
2003-07-08
Barr, Michael (Department: 1762)
Coating processes
Nonuniform coating
Applying superposed diverse coatings or coating a coated base
C427S271000, C427S404000
Reexamination Certificate
active
06589600
ABSTRACT:
BACKGROUND OF THE INVENTION
The invention relates to components used in turbine engines. More particularly, the invention is directed to a turbine engine component that has a treated surface to enhance the heat transfer characteristics of the component, and methods forming such a component.
Various techniques have been devised to maintain the temperature of turbine engine components below critical levels. As an example, coolant air from the engine compressor is often directed through the component, along one or more component surfaces. Such flow is understood in the art as “backside air flow,” where coolant air is directed at a surface of an engine component that is not directly exposed to high temperature gases from combustion. In combination with backside air flow, turbulation has been used to enhance heat transfer. Turbulation has generally taken the form of protuberances or “bumps” on selected sections of the surface of the component, which functions to increase the heat transfer with the use of a coolant medium that is passed along the surface. Turbulation is formed by one of several techniques, including wire spraying and casting.
While turbulation has been found to improve the heat transfer characteristics of the treated component, further heat transfer improvements are continually sought in the art.
SUMMARY OF THE INVENTION
According to one aspect of the invention, a turbine engine component is provided that has a surface that contains a plurality of depressions that are effective to increase the surface area of the component. The depressions are generally concave in contour.
Another aspect of the invention calls for a method for forming a turbine engine component, including the steps of providing a substrate; applying a layer on the substrate, which includes a matrix phase and a discrete particulate phase; and then removing the discrete particulate phase. By removal of the discrete particulate phase, a plurality of depressions are left behind in the matrix phase.
Still another aspect of the present invention calls for a method of forming a turbine engine component, including the steps of providing a mold having a plurality of protrusions along a surface portion thereof, the protrusions forming a textured surface; injecting a molten alloy into the mold; cooling the molten alloy to form a turbine engine component; and removing the mold. The turbine engine component following removal of the mold has a textured surface that is complementary to the textured surface of the mold.
REFERENCES:
patent: 2220420 (1940-11-01), Meyer
patent: 2648519 (1953-08-01), Campini
patent: 3700418 (1972-10-01), Mayeda
patent: 3975165 (1976-08-01), Elbert et al.
patent: 4003716 (1977-01-01), Steigelman
patent: 4116723 (1978-09-01), Gell et al.
patent: 4689242 (1987-08-01), Pike
patent: 4749594 (1988-06-01), Malikowski et al.
patent: 4762462 (1988-08-01), Lardellier
patent: 4884820 (1989-12-01), Jackson et al.
patent: 4938991 (1990-07-01), Bird
patent: 5055032 (1991-10-01), Altemark et al.
patent: 5096375 (1992-03-01), Ciokailo
patent: 5210944 (1993-05-01), Monson et al.
patent: 5304032 (1994-04-01), Bosna et al.
patent: 5353865 (1994-10-01), Adiutori et al.
patent: 5399313 (1995-03-01), Ross et al.
patent: 5549927 (1996-08-01), Cottone et al.
patent: 5577555 (1996-11-01), Hisajima et al.
patent: 5590711 (1997-01-01), Ishida et al.
patent: 5858558 (1999-01-01), Zhao et al.
patent: 5951892 (1999-09-01), Wolfla et al.
patent: 6098397 (2000-08-01), Glezer et al.
patent: 6113347 (2000-09-01), Forrester
patent: 6142734 (2000-11-01), Lee
patent: 6155778 (2000-12-01), Lee et al.
patent: 54-108053 (1979-08-01), None
patent: 55-28483 (1980-02-01), None
patent: 59-113204 (1984-06-01), None
“Pastes, Transfer Tapes, Preforms”, Praxair product brochure (3 pages), no date.
“Drills & Cutters”, prints from website www.dremel.com, 3/99 (2 pages).
“Effects of Turbulator Profile and Spacing on Heat Transfer and Friction in a Channel” by M.E. Taslim and S.D. Spring, Journal of Thermophysics and Heat Transfere, vol. 8, No. 3, Jul.-Sep. 1994, pp. 555-562.
Abuaf Nesim
Hasz Wayne Charles
Johnson Robert Alan
Lee Ching-Pang
Barr Michael
General Electric Company
Johnson Noreen C.
Vo Toan P.
LandOfFree
Turbine engine component having enhanced heat transfer... does not yet have a rating. At this time, there are no reviews or comments for this patent.
If you have personal experience with Turbine engine component having enhanced heat transfer..., we encourage you to share that experience with our LandOfFree.com community. Your opinion is very important and Turbine engine component having enhanced heat transfer... will most certainly appreciate the feedback.
Profile ID: LFUS-PAI-O-3059016