Mark W Gorman, 569732 Turnbridge Ct, Brentwood, TN 37027

6571472, Jun 3, 2003

Aug 14, 2001

09/929185

Thomas Frederic Berry - Central Lake MI
Michael James Weimer - Loveland OH
David Edwin Budinger - Loveland OH
David John Dietz - Loveland OH
Mark Daniel Gorman - West Chester OH
Matthew Stewart - Cincinnati OH

General Electric Company - Schenectady NY

B23P 1500

298891, 298892, 2940218, 427455

A method for restoring thickness to load-bearing components of gas turbine engines, and for repairing a honeycomb structured gas turbine engine component. A surface of the component such as the backing surface of a honeycomb component after honeycomb removal is roughened and cleaned. A selected build-up material is deposited onto the substrate by high velocity oxy-fuel deposition or low pressure plasma spray. The component is heat treated to enhance the bond between the deposited material particles, and between the deposited material and the substrate by diffusion.

6702553, Mar 9, 2004

Oct 3, 2002

10/263870

Mark D. Gorman - West Chester OH

General Electric Company - Schenectady NY

B32B 1504

416241R, 416177, 416224, 4284722, 277423, 277652, 277650, 277345

A highly porous alumina material and a method for applying such material that is useful in the hot section of a jet aircraft engine. In order to manufacture the porous alumina, an aluminum-based metal/alumina material known in the art is first placed onto a metal alloy substrate. The aluminum-based metal is then dissolved using a solution that will not affect the alumina or the underlying substrate. The alumina is then washed with deionized water and dried. The resulting alumina has a porosity in the range of about 20% to about 45%. The alumina has globular interconnected surface features in the range of about 0. 5 m to about 20 m.

6838190, Jan 4, 2005

Dec 20, 2001

10/028109

Melvin Robert Jackson - Niskayuna NY, US
Stephen Joseph Ferrigno - Cincinnati OH, US
Gary Edward Trewiler - Loveland OH, US
Mark Daniel Gorman - West Chester OH, US

General Electric Company - Schenectady NY

B32B 1504
B32B 1520
F01D 514
B64C 1116

428670, 428666, 428669, 428652, 416241 R

A protected article includes a nickel-base superalloy substrate, an interlayer overlying the substrate, and a protective layer overlying the interlayer. The protective layer has a composition comprising at least one of rhodium, platinum, palladium, and ruthenium. In one composition, palladium is present in an amount of from about 1 to about 41 atomic percent; platinum is present in an amount of about (40+atomic percent palladium) atomic percent for palladium ranging from about 1 atomic percent to about 14 atomic percent and up to about 54 atomic percent for palladium ranging from about 15 atomic percent up to about 41 atomic percent; rhodium is present in an amount of at least about 24 atomic percent; zirconium, hafnium, titanium, and mixtures thereof are present in an amount of from zero up to about 5 atomic percent; and ruthenium is present in an amount of from zero up to about 5 atomic percent, balance impurities. The interlayer has a coefficient of thermal expansion intermediate between that of the substrate and that of the protective layer. The protected article is fabricated by furnishing the substrate, applying the interlayer over the substrate, and applying the protective layer over the interlayer.

6858334, Feb 22, 2005

Dec 30, 2003

10/748516

Mark Daniel Gorman - West Chester OH, US
Irene Spitsberg - Loveland OH, US
Brett Allen Boutwell - Liberty Township OH, US
Ramgopal Darolia - West Chester OH, US
Robert William Bruce - Loveland OH, US
Venkat Subramanian Venkataramani - Clifton Park NY, US
Anthony Mark Thompson - Niskayuna NY, US

General Electric Company - Schenectady NY

B32B015/04
F03B003/12
C23C004/10
C23C016/06

428701, 428702, 428699, 428632, 428633, 428336, 416241 B, 427453, 427596, 42725531

Zirconia-containing ceramic compositions having a c/a ratio of the zirconia lattice in the range of from about 1. 005 to about 1. 016. These compositions comprise a stabilizing amount up to about 10 mole % of the composition of a stabilizer component which comprises: (1) a first metal oxide selected from the group consisting of yttria, calcia, ceria, scandia, magnesia, india and mixtures thereof in an amount of from about 1. 5 to about 6 mole % of the composition of; (2) a second metal oxide selected from the group consisting of lanthana, neodymia and mixtures thereof in an amount of from about 0. 5 to about 4 mole % of the composition; and (3) optionally ytterbia in an amount of from about 0. 5 to about 4 mole % of the composition. These compositions further comprise hafnia in an amount of from about 0.

6884470, Apr 26, 2005

Oct 3, 2002

10/264052

Mark D. Gorman - West Chester OH, US

General Electric Company - Schenectady NY

B05D001/32
C23C004/02

427448, 427452, 427453, 427454, 427456, 4272481, 427287, 427282, 427259, 427343, 427352, 427354, 427355, 427405, 4274192, 4274193

A method for applying a highly porous alumina material that is useful in the hot section of a jet aircraft engine. In order to apply the porous alumina, an aluminum-based metal/alumina material known in the art is first placed onto an aircraft engine component substrate. The aluminum-based metal is then dissolved using a solution that will not affect the alumina or the underlying substrate. The alumina is then washed with deionized water and dried. The aircraft engine component may be first masked by applying a non-porous metal oxide material to the component or by oxidizing the surface of the component. The resulting alumina has a porosity in the range of about 20% to about 45%. The alumina has globular interconnected surface features in the range of about 0. 5 μm to about 20 μm.

6887595, May 3, 2005

Dec 30, 2003

10/748519

Ramgopal Darolia - West Chester OH, US
Irene Spitsberg - Loveland OH, US
Brett Allen Boutwell - Liberty Township OH, US
Mark Daniel Gorman - West Chester OH, US
Robert William Bruce - Loveland OH, US

General Electric Company - Schnectady NY

B32B015/04
C23C004/04

428701, 428702, 428697, 428699, 428632, 428633, 428336, 427453, 427585, 427584, 427250, 427421, 416241 B

A thermal barrier coatings for the underlying substrate of articles that operate at, or are exposed to, high temperatures. The thermal barrier coating includes a zirconia-containing upper layer wherein the zirconia is stabilized in the cubic crystalline phase to reduce the thermal conductivity of the coating. The thermal barrier coating further includes a zirconia-containing lower layer stabilized in the tetragonal crystalline phase that increases the adherence of the upper layer to the bond coat layer that overlies the substrate of the article to improve the resistance of the coating to spallation.

6933052, Aug 23, 2005

Oct 8, 2003

10/681433

Mark Daniel Gorman - West Chester OH, US
Bangalore Aswatha Nagaraj - West Chester OH, US
Ramgopal Darolia - West Chester OH, US

General Electric Company - Schenectady NY

B32B015/04
F03B003/12

428469, 428698, 428472, 428701, 428702, 416241 R, 416241 B

A turbine engine component comprising a substrate made of a nickel-base or cobalt-base superalloy, a non-metallic oxide or nitride diffusion barrier layer overlying the substrate, and a protective coating overlying the barrier layer, the protective coating comprising at least one platinum group metal selected from the group consisting of platinum, palladium, rhodium, ruthenium and iridium. The diffusion barrier layer may be a deposited or thermally grown oxide material, especially aluminum oxide. The protective coating may be heat treated to increase homogeneity of the coating and adherence with the substrate. The component typically further comprises a ceramic thermal barrier coating overlying the protective coating. Also disclosed are methods for forming a protective coating system on the turbine engine component by forming the non-metallic oxide or nitride diffusion barrier layer on the substrate and then depositing the platinum group metal on top of the barrier layer.

6935187, Aug 30, 2005

Mar 3, 2004

10/792158

Mark Daniel Gorman - West Chester OH, US
Shesh Krishna Srivatsa - Cincinnati OH, US
Christine Govern - Cincinnati OH, US

General Electric Company - Schenectady NY

G01N003/32

73811

A test method for testing the thermal mechanical fatigue performance of a test material includes preparing a test specimen of the test material, wherein the test specimen has a base, and a rib extending outwardly from the base. The test specimen is thermally cycled through at least one test cycle. In each test cycle the rib is heated to a higher rib temperature and thereafter cooled to a lower rib temperature. The test specimen is evaluated for thermal mechanical fatigue damage.