James D Steibel

US Patent:

6397603, Jun 4, 2002

Filed:

May 5, 2000

Appl. No.:

09/567557

Inventors:

Wayne Garcia Edmondson - Xenia OH
James Dale Steibel - Hamilton OH
Harold Ray Hansel - Mason OH

Assignee:

The United States of America as represented by the Secretary of the Air Force - Washington DC

International Classification:

F23R 360

US Classification:

60753, 60 3932, 60746, 60760

Abstract:

A combustor having liners made from ceramic matrix composite materials (CMCs) that are capable of withstanding higher temperatures than metallic liners. The ceramic matrix composite liners are used in conjunction with mating components that are manufactured from superalloy materials. To permit the use of a combustor having liners made from CMC materials in conjunction with metallic materials used for the mating forward cowls, and aft seals with attached seal retainer over the broad range of temperatures of a combustor, the combustor is designed to allow for the differential thermal expansion of the differing materials at their interfaces in a manner that does not introduce stresses into the liner as a result of thermal expansion and also balances the flow of cooling air as a result of the thermal expansion.

US Patent:

6428740, Aug 6, 2002

Filed:

Aug 6, 2001

Appl. No.:

09/923195

Inventors:

Thomas J. Dunyak - West Chester OH
James D. Steibel - Hamilton OH
David R. Chang - Fairfield OH
Peggy E. Jones - Saginaw MI

Assignee:

General Electric Company - Schenectady NY

International Classification:

B28B 130

US Classification:

264635, 264 81, 2642711, 264317

Abstract:

A method of removing a core from a CMC component in which the core was used to form an internal cavity. According to one embodiment of the invention, the core is removed from a fully densified CMC component by heating the component and core to a temperature at which the core deteriorates but below a temperature at which the component would melt or otherwise be damaged. According to a second embodiment of this invention, the component is only partially densified, and then impregnated with a coating material that is resistant to a leaching compound capable of removing the core. The core can then be removed using the leaching compound without damage to the internal surfaces of the component defined by the core when the component was fabricated.

US Patent:

6441341, Aug 27, 2002

Filed:

Jun 16, 2000

Appl. No.:

09/595866

Inventors:

James Dale Steibel - Hamilton OH
Wayne Garcia Edmondson - Xenia OH
Wilbur Douglas Scheidt - Cincinnati OH

Assignee:

General Electric Company - Schenectady NY

International Classification:

B23K 2618

US Classification:

21912171, 21912166

Abstract:

A method for producing apertures in hot section components of gas turbine engines made from ceramic matrix composites that have at least one oxidizable component. The method involves forming the apertures using a laser beam controlled by parameters that ablate the ceramic matrix composite in the path of the beam, while simultaneously heating the matrix material, SiC or SiN, to a sufficient temperature to oxidize it to form a silica. Sufficient heat is supplied by the beam to melt the silica to cause it to flow. The melted silica is quickly solidified as recast silica along the walls of the newly created aperture before it has an opportunity to flow and form undesirable geometries. The wall of the aperture is formed of recast silica that is a smooth surface and that forms an oxidation barrier to inhibit any further oxidation of the underlying composite as it is exposed to the high temperatures and oxidative, corrosive atmosphere of an operating gas turbine.

US Patent:

6670026, Dec 30, 2003

Filed:

Jun 20, 2002

Appl. No.:

10/175756

Inventors:

James Dale Steibel - Hamilton OH
Wayne Garcia Edmondson - Xenia OH
Wilbur Douglas Scheidt - Cincinnati OH

Assignee:

General Electric Company - Schenectady NY

International Classification:

B23K 2618

US Classification:

4282934

Abstract:

A method for producing apertures in hot section components of gas turbine engines made from ceramic matrix composites that have at least one oxidizable component. The method involves forming the apertures using a laser beam controlled by parameters that ablate the ceramic matrix composite in the path of the beam, while simultaneously heating the matrix material, SiC or SiN, to a sufficient temperature to oxidize it to form a silica. Sufficient heat is supplied by the beam to melt the silica to cause it to flow. The melted silica is quickly solidified as recast silica along the walls of the newly created aperture before it has an opportunity to flow and form undesirable geometries. The wall of the aperture is formed of recast silica that is a smooth surface and that forms an oxidation barrier to inhibit any further oxidation of the underlying composite as it is exposed to the high temperatures and oxidative, corrosive atmosphere of an operating gas turbine.

US Patent:

7223465, May 29, 2007

Filed:

Dec 29, 2004

Appl. No.:

11/025510

Inventors:

Suresh Subramanian - Mason OH, US
James Dale Steibel - Mason OH, US
Douglas Melton Carper - Trenton OH, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

B32B 17/12
B32B 15/04
B32B 11/00
C04B 35/00

US Classification:

4282934, 4282937, 4282944, 442178, 501 952

Abstract:

The present invention is a ceramic matrix composite turbine engine component, wherein the component has a region of expected higher interlaminate stress during normal engine operation. The component includes both coated fiber tows and uncoated fiber tows arranged together into a preselected form, wherein the uncoated fiber tows are located at predetermined regions of expected high interlaminate stress. The invention further includes method of manufacturing a CMC such as a composite turbine engine component, wherein the component has a region of expected higher interlaminate stress during engine operation.

US Patent:

7306826, Dec 11, 2007

Filed:

Feb 23, 2004

Appl. No.:

10/784734

Inventors:

Suresh Subramanian - Mason OH, US
James Dale Steibel - Hamilton OH, US
Douglas Melton Carper - Trenton OH, US
Brian Keith Flandermeyer - Rocky Hill CT, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

C23C 16/00

US Classification:

4272492, 4272493, 4272494, 4272495, 42724915, 42724916, 42725512

Abstract:

A method for making a ceramic matrix composite turbine engine component, wherein the method includes providing a plurality of biased ceramic plies, wherein each biased ply comprises ceramic fiber tows, the tows being woven in a first warp direction and a second weft direction, the second weft direction lying at a preselected angular orientation with respect to the first warp direction, wherein a greater number of tows are woven in the first warp direction than in the second weft direction. The plurality of biased plies are laid up in a preselected arrangement to form the component, and a preselected number of the plurality of biased plies are oriented such that the orientation of the first warp direction of the plies lie about in the direction of maximum tensile stress during normal engine operation. A coating is applied to the plurality of biased plies. The coated component preform is then densified.

US Patent:

7507466, Mar 24, 2009

Filed:

Feb 22, 2006

Appl. No.:

11/359217

Inventors:

James D. Steibel - Mason OH, US
Stephen M. Whiteker - Covington KY, US
Douglas M. Carper - Trenton OH, US
Suresh Subramanian - Mason OH, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

B32B 17/12

US Classification:

4282934, 4282937, 501 952

Abstract:

The present invention is ceramic matrix composite gas turbine engine component comprising a plurality of cured ceramic matrix composite plies, each ply comprising ceramic fiber tows, each ceramic fiber tow comprising a plurality of ceramic fibers, the tows in each ply lying adjacent to one another such that each ply has a unidirectional orientation. The component further comprises a layer of a coating on the ceramic fibers. The component further comprises a ceramic matrix material lying in interstitial regions between the fibers and tows of each ply and the interstitial region between the plurality of plies, wherein at least a portion of the component is no greater than about 0. 021 inch thick. The present invention is also a method for making such a ceramic matrix composite component.

US Patent:

7510680, Mar 31, 2009

Filed:

Dec 13, 2002

Appl. No.:

10/318763

Inventors:

James Dale Steibel - Mason OH, US
Andrew Philip Woodfield - Madeira OH, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

B22F 1/00
C22C 1/10

US Classification:

419 34, 419 63

Abstract:

A metallic alloy having at least two metallic constituents is produced by first furnishing at least two non-oxide compounds, wherein the non-oxide compounds collectively comprise each of the metallic constituents, and wherein each of the non-oxide compounds is soluble in a mutual solvent. The method further includes dissolving the non-oxide compounds in the mutual solvent to produce a solution containing the metallic constituents, thereafter heating the solution to remove the mutual solvent and oxidize the metallic constituents to produce a mixed metallic oxide, thereafter cooling the mixed metallic oxide to form a substantially homogeneous mixed metallic oxide solid mass, and thereafter chemically reducing the mixed metallic oxide solid mass to produce a metallic alloy. The metallic alloy may be consolidated or otherwise processed.