Michael Kirt Weimer

US Patent:

6219915, Apr 24, 2001

Filed:

Nov 18, 1999

Appl. No.:

9/443118

Inventors:

Jeffrey A. Conner - Hamilton OH
Michael J. Weimer - Loveland OH

Assignee:

General Electric Company - Cincinnati OH

International Classification:

B23P 600

US Classification:

298891

Abstract:

A gas turbine engine hot section component having a ceramic thermal barrier coating is repaired by removing the ceramic thermal barrier coating, removing oxidation products and corrosion products from the metallic bond coating beneath the ceramic thermal barrier coating, applying a noble metal to the component, diffusing the noble metal into the component substrate, and aluminiding the component to provide an outermost noble metal-Al layer.

US Patent:

6372321, Apr 16, 2002

Filed:

Mar 17, 2000

Appl. No.:

09/527661

Inventors:

Joseph D. Rigney - Milford OH
Elissa H. Lee - Cincinnati OH
Jeffrey A. Conner - Hamilton OH
Michael J. Weimer - Loveland OH

Assignee:

General Electric Company - Schenectady NY

International Classification:

B32B 512

US Classification:

428105, 428 358, 428 359, 428131, 428142, 428209, 428210, 427243, 427404, 427405

Abstract:

A coated article is provided with a coating stabilizing portion in a coating combination on a substrate of the article. The coating combination includes a coating diffusion portion on the substrate and an outer coating portion outwardly from the coating diffusion portion. The coating stabilizing portion is provided between the coating diffusion portion and the outer coating portion to inhibit diffusion of undesirable elements to an interface with the outer coating portion and to enhance mechanical properties.

US Patent:

6465040, Oct 15, 2002

Filed:

Feb 6, 2001

Appl. No.:

09/777636

Inventors:

Bhupendra Kumar Gupta - Cincinnati OH
Nripendra Nath Das - West Chester OH
Lyle Timothy Rasch - Fairfield OH
Jeffrey Allen Conner - Hamilton OH
Michael James Weimer - Loveland OH

Assignee:

General Electric Company - Schenectady NY

International Classification:

B05D 312

US Classification:

427142, 427140, 427242, 427328, 427307, 427309

Abstract:

A method is provided for refurbishing a service operated metallic coating on a substrate alloy, the coating including at least within a coating outer surface at least one oxide chemically grown from at least one coating element, for example Al, and chemically bonded with the coating outer surface as a result of thermal exposure during service operation. Growth of the oxide has depleted at least a portion of the coating element from the coating. The method comprises removing the oxide from the coating outer surface while substantially retaining the metallic coating, thereby exposing in the coating outer surface at least one surface void that had been occupied by the oxide. The retained metallic coating is mechanically worked, substantially without removal of the retained coating, to close the void, providing a treated metallic coating surface over which a refurbishing coating is applied. In one form, the mechanical working provides, concurrently, a compressive stress in the substrate alloy beneath the metallic coating.

US Patent:

6497920, Dec 24, 2002

Filed:

Sep 6, 2000

Appl. No.:

09/656287

Inventors:

Jeffrey Allan Pfaendtner - Blue Ash OH
Joseph David Rigney - Milford OH
Nripendra Nath Das - West Chester OH
Michael James Weimer - Loveland OH
John Lewis Lackman - Cincinnati OH

Assignee:

General Electric Company - Schenectady NY

International Classification:

B05D 302

US Classification:

427235, 427229, 427230, 4273766, 4273768, 427380, 4273831, 4273837

Abstract:

An internal passage of an article such as a gas turbine airfoil is coated with an aluminum-containing coating. To accomplish this coating process, a coating slurry of a mixture of a carrier component of water and a hectorite clay or a bentonite clay, together with a solids component of a source of aluminum, a halide activator, and an oxide dispersant, is prepared. The coating slurry is applied to the internal passage of the gas turbine airfoil and dried. The gas turbine airfoil and the applied coating slurry are heated to form an aluminum-containing coating bonded to the internal passage of the gas turbine airfoil. Excess coating material is removed from the article internal passage.

US Patent:

6521294, Feb 18, 2003

Filed:

Aug 11, 1999

Appl. No.:

09/373267

Inventors:

Joseph D. Rigney - Milford OH
Jeffrey A. Pfaendtner - Blue Ash OH
Michael J. Weimer - Loveland OH
Ramgopal Darolia - West Chester OH

Assignee:

General Electric Co. - Cincinnati OH

International Classification:

B05D 132

US Classification:

427253, 42725519, 42725521, 427259, 427261, 427282

Abstract:

A metallic substrate has a substrate surface having a substrate surface of nickel, a substrate aluminum content, and other alloying elements. A maskant is applied overlying the substrate surface to produce a masked substrate surface having an exposed region and a protected region. The maskant includes a plurality of maskant particles, each particle having a maskant particle composition comprising a maskant metal selected from the group of nickel, cobalt, titanium, chromium, iron, and combinations thereof, and a maskant aluminum content. The substrate is aluminided by contacting a source of aluminum to the masked substrate surface, whereby aluminum deposits on the exposed region and does not deposit on the protected region.

US Patent:

6532657, Mar 18, 2003

Filed:

Sep 21, 2001

Appl. No.:

09/957844

Inventors:

Michael James Weimer - Loveland OH
Bangalore Aswatha Nagaraj - West Chester OH
Jon Conrad Schaeffer - Simpsonville SC

Assignee:

General Electric Co., - Schnectedy NY

International Classification:

B21K 2500

US Classification:

298892, 298897

Abstract:

A gas turbine component, such as a turbine disk or a rotating seal, is fabricated by furnishing a substrate shaped as a gas turbine component made of a nickel-base superalloy, and oxidizing the substrate to produce an oxidized substrate having thereon a layer comprising an oxide and having a thickness of at least about 500 Angstroms. The step of oxidizing is performed prior to entry of the component into service and in an atmosphere that does not contain combustion gas. The oxidized gas turbine component is thereafter placed into service.

US Patent:

6533875, Mar 18, 2003

Filed:

Oct 20, 2000

Appl. No.:

09/693077

Inventors:

Jeffrey Allan Pfaendtner - Blue Ash OH
Joseph David Rigney - Milford OH
Michael James Weimer - Loveland OH

Assignee:

General Electric Co. - Cincinnati OH

International Classification:

B05D 722

US Classification:

148535, 427181, 427192, 427226, 427239

Abstract:

A surface of a nickel-base article such as an internal surface of a gas turbine airfoil is protected with a donor layer of aluminum and at least one other element. To form the protective layer, a donor alloy is contacted to the protected surface of the article, and simultaneously the article and the donor alloy are heated to a coating temperature that is greater than about 0. 7 of the absolute solidus temperature of the donor alloy but is such that the donor alloy remains in the form of a condensed phase contacting the protected surface of the article. The donor alloy is thereafter interdiffused into the protected surface of the article.

US Patent:

6607789, Aug 19, 2003

Filed:

Apr 26, 2001

Appl. No.:

09/842503

Inventors:

Joseph David Rigney - Milford OH
Michael James Weimer - Loveland OH
Bangalore Aswatha Nagaraj - West Chester OH

Assignee:

General Electric Company - Schenectady NY

International Classification:

C23C 404

US Classification:

427454, 427456, 427405, 4274192, 4274197

Abstract:

A method for forming a thermal barrier coating system on an article subjected to a hostile thermal environment, such as the hot gas path components of a gas turbine engine. The coating system is generally comprised of a ceramic layer and an environmentally resistant beta phase nickel aluminum intermetallic (-NiAl) bond coat that adheres the ceramic layer to the component surface. A thin aluminum oxide scale forms on the surface of the -NiAl during heat treatment. The -NiAl may contain alloying elements in addition to nickel and aluminum in order to increase the environmental resistance of the -NiAl. The -NiAl powder having a size in the range of 20-50 microns is applied using air plasma spray techniques to produce a surface having a roughness of 400 microinches or rougher. The ceramic top coat can be applied using inexpensive thermal spray techniques to greater thicknesses than achievable otherwise because of the rough surface finish of the underlying -NiAl bond coat.