General Electric Company

Ronald L Sheranko

Thomas Joseph Kelly

Russell W Smashey

Gilbert Farmer

John H Snyder

Edward Lee Howard

James Hollice Poynter

Gregory Thomas Lucas

John Robert Staker

Eric J Boerger

Thomas Carl Mills

A method of fabricating a test model of a gas turbine engine combustor dome, and the test model produced thereby. The method entails individually stamping a plurality of dome wall segments and first and second mounting band segments. Each wall segment comprises at least one cup between radially inward and outward edges of the wall segment, and an opening in the cup. At least one wall segment and its two corresponding mounting band segments are placed on a fixture that locates the opening of the wall segment, locates the first and second mounting band segments at the radially-inward and outward edges of the wall segment, and orients the wall segment to establish a dome angle of the fixtured dome assembly. The wall segment and mounting band segments are then joined while the fixtured dome assembly remains on the fixture to form at least a unitary sector of the test model.

Test model for a gas turbine combustor dome and method of fabricating

A method for fabricating a three-dimensional turbine engine combustor liner model includes coupling at least a first member to a second member to form an assembly that has an inner surface. The assembly inner surface simulates an inner surface of the aircraft engine combustor liner. The first member is at least one of a pre-formed conical member and a pre-formed cylindrical member, and the second portion is at least one of a pre-formed conical member and a pre-formed cylindrical member. The method also includes coupling the assembly to a baseplate, and coupling a plurality of templates to the assembly.

Methods and apparatus for modeling gas turbine engine combustor liners

An article made of a nickel-base superalloy having a nil-ductility range from the solidus temperature of the alloy to about 600.degree. F. below the solidus temperature is welded, as for example in the weld repair of surface cracks, by removing foreign matter from the area to be welded, first stress relieving the article, adjusting the temperature of the article to a welding temperature of from about 1800.degree. F. to about 2100.degree. F., welding a preselected area in an inert atmosphere at the welding temperature, and second stress relieving the article. Welding is preferably accomplished by striking an arc in the preselected area so as to locally melt the alloy in the preselected area, providing a filler metal having the same composition as the nickel-based superalloy of the article, and feeding the filler metal into the arc so that the filler metal is melted and fused with the article to form a weldment upon solidification.

Welding of nickel-base superalloys having a nil-ductility range

A surface defect in a gamma titanium aluminide article is repaired by weld repairing the defect and thereafter sealing the surface-connected cracks in the weldment. The surface-connected cracks are repaired by applying to the region of the weldment a powder of a brazing filler metal that is compatible with the gamma titanium aluminide alloy and with the weldment, and thereafter heating the article to a brazing temperature above the liquidus of the brazing filler metal. The article is preferably hot isostatically pressed after the repair is completed to close internal defects that cannot otherwise be closed due to the surface connected cracks.

Repair of gamma titanium aluminide articles

An article made of a gamma titanium aluminide alloy is welded, as for example in the weld repair of surface cracks, by removing foreign matter from the area to be welded, first stress relieving the article, cooling the entire article to a welding temperature of from about 1000.degree. F. to about 1400.degree. F., welding a preselected region in an inert atmosphere at the welding temperature, and second stress relieving the article. Welding is preferably accomplished by striking an arc in the preselected region so as to locally melt the alloy in the preselected region, providing a filler metal having the same composition as the gamma titanium aluminide alloy of the article, and feeding the filler metal into the arc so that the filler metal is melted and fused with the article to form a weldment upon solidification.

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Cincinnati, OH, United States of America

Ronald L Sheranko