Abstract: Methods for cleaning a superalloy substrate having engine deposits on its surface are provided. The method may include applying a permanganate solution onto the surface of the superalloy substrate, and applying a ferric chloride based cleaning composition onto the surface of the superalloy substrate. The ferric chloride based cleaning composition includes ferric chloride and at least one of nitric acid and phosphoric acid, such as within a solvent system (e.g., an aqueous solution including water).

Abstract: Methods for cleaning a superalloy substrate having engine deposits on its surface are provided. The method may include applying a permanganate solution onto the surface of the superalloy substrate, and applying a ferric chloride based cleaning composition onto the surface of the superalloy substrate. The ferric chloride based cleaning composition includes ferric chloride and at least one of nitric acid and phosphoric acid, such as within a solvent system (e.g., an aqueous solution including water).

Abstract: A cleaning composition, and method for use of the cleaning composition to clean metal surfaces, such as the surfaces of turbomachinery components, is presented. For example, a method includes contacting a surface of an article with a cleaning composition, wherein the article comprises a metal and wherein the surface includes an oxide; and removing the cleaning composition from the surface. The cleaning composition has a viscosity of at least 104 poise, and comprises a thickening agent and an acidic matrix having selective reactivity with the oxide.

Abstract: A method for repairing a turbine blade for a gas turbine engine is provided. The method includes securing the blade into a clamping fixture, obtaining a zero reference from a gauging surface on the clamping fixture, coupling the clamping fixture to a grinding machine, and grinding the blade based on the zero reference.

Abstract: An undersize repair region of a gas turbine engine stationary shroud is repaired with a sufficient mass of a repair material. The repair region includes a protruding portion that is undersized, and the repair includes machining of the protruding portion, grooving the resulting rub surface, inserting a replacement element, applying a brazing repair material, and brazing the article to form a repaired article. The repair material preferably includes a first fraction of a first powder of a first alloy component, and a second fraction of a second powder of a second alloy component. The first alloy component and the second alloy component have different solidus temperatures. The repair material is placed in the repair region. The repair material and the repair region are heated to melt the repair material but not the repair region, and thereafter the repair material and the repair region are cooled to solidify the repair material.

Abstract: A method for repairing a turbine blade for a gas turbine engine is provided. The method includes securing the blade into a clamping fixture, obtaining a zero reference from a gauging surface on the clamping fixture, coupling the clamping fixture to a grinding machine, and grinding the blade based on the zero reference.

Abstract: A method and cleaning composition for removing engine deposits from turbine components, in particular turbine disks and turbine shafts. This method comprises the following steps: (a) providing a turbine component having a surface with engine deposits thereon, wherein the turbine component comprises a nickel and/or cobalt-containing base metal; and (b) treating the surface of the turbine component with a cleaning composition to convert the engine deposits thereon to a removable smut without substantially etching the base metal of the turbine component. The cleaning composition comprises an aqueous solution that is substantially free of acetic acid and comprising: a nitrate ion source in an amount, by weight of the nitrate ion, of from about 470 to about 710 grams/liter; and a bifluoride ion source in an amount, by weight of the bifluoride ion, of from about 0.5 to about 15 grams/liter.

Abstract: A method and cleaning composition for removing engine deposits from turbine components, in particular turbine disks and turbine shafts. This method comprises the following steps: (a) providing a turbine component having a surface with engine deposits thereon, wherein the turbine component comprises a nickel and/or cobalt-containing base metal; and (b) treating the surface of the turbine component with a cleaning composition to convert the engine deposits thereon to a removable smut without substantially etching the base metal of the turbine component. The cleaning composition comprises an aqueous solution that is substantially free of acetic acid and comprising: a nitrate ion source in an amount, by weight of the nitrate ion, of from about 470 to about 710 grams/liter; and a bifluoride ion source in an amount, by weight of the bifluoride ion, of from about 0.5 to about 15 grams/liter.

Abstract: An undersize repair region of a gas turbine engine stationary shroud is repaired with a sufficient mass of a repair material. The repair region includes a protruding portion that is undersized, and the repair includes machining of the protruding portion, grooving the resulting rub surface, inserting a replacement element, applying a brazing repair material, and brazing the article to form a repaired article. The repair material preferably includes a first fraction of a first powder of a first alloy component, and a second fraction of a second powder of a second alloy component. The first alloy component and the second alloy component have different solidus temperatures. The repair material is placed in the repair region. The repair material and the repair region are heated to melt the repair material but not the repair region, and thereafter the repair material and the repair region are cooled to solidify the repair material.

Abstract: An undersize repair region of a gas turbine engine stationary shroud is repaired with a sufficient mass of a repair material. The repair region includes a protruding portion that is undersized, and the repair includes machining of the protruding portion, grooving the resulting rub surface, inserting a replacement element, applying a brazing repair material, and brazing the article to form a repaired article. The repair material preferably includes a first fraction of a first powder of a first alloy component, and a second fraction of a second powder of a second alloy component. The first alloy component and the second alloy component have different solidus temperatures. The repair material is placed in the repair region. The repair material and the repair region are heated to melt the repair material but not the repair region, and thereafter the repair material and the repair region are cooled to solidify the repair material.

Abstract: An apparatus for aligning a gas turbine engine blade including an airfoil and a dovetail is provided. The apparatus includes at least one locator pin configured to engage a serration formed on the blade dovetail, a locator block supporting said locator pin where said locator block comprises at least one groove sized to receive said locator pin therein, and a slide block assembly for engaging a dovetail surface opposite the serration where said slide block assembly is configured to position the blade dovetail against said locator pin. The apparatus also includes a base member comprising a platform comprising an end plate, a bottom surface, and an opposite upper surface for supporting said slide block assembly and said locator block, said slide block assembly is slidably coupled to said platform upper surface, said platform upper surface defining a slotted opening extending through said bottom surface, said opening configured to receive the blade airfoil.

Abstract: A method and cleaning composition for removing engine deposits from turbine components, in particular turbine disks and turbine shafts. This method comprises the following steps: (a) providing a turbine component having a surface with engine deposits thereon, wherein the turbine component comprises a nickel and/or cobalt-containing base metal; and (b) treating the surface of the turbine component with a cleaning composition to convert the engine deposits thereon to a removable smut without substantially etching the base metal of the turbine component. The cleaning composition comprises an aqueous solution that is substantially free of acetic acid and comprising: a nitrate ion source in an amount, by weight of the nitrate ion, of from about 470 to about 710 grams/liter; and a bifluoride ion source in an amount, by weight of the bifluoride ion, of from about 0.5 to about 15 grams/liter.

Abstract: A fixture for holding a gas turbine engine blade having an airfoil extending outward from a shank and a dovetail extending inward from the shank for attaching the blade to a disk of the engine. The dovetail includes at least one pair of protrusions extending fore and aft along opposite sides of the blade. Each of the protrusions including a pressure face generally facing the airfoil of the blade for engaging the disk to retain the blade in the disk during operation of the engine. The fixture includes a support for receiving the dovetail and a clamp mounted adjacent the support for movement between a clamped position in which the clamp engages the dovetail to hold the dovetail against the support and a released position in which the clamp disengages the dovetail to permit removal of the blade from the fixture.

Abstract: A fixture for holding a gas turbine engine blade having an airfoil extending outward from a shank and a dovetail extending inward from the shank for attaching the blade to a disk of the engine. The dovetail includes at least one pair of protrusions extending fore and aft along opposite sides of the blade. Each of the protrusions including a pressure face generally facing the airfoil of the blade for engaging the disk to retain the blade in the disk during operation of the engine. The fixture includes a support for receiving the dovetail and a clamp mounted adjacent the support for movement between a clamped position in which the clamp engages the dovetail to hold the dovetail against the support and a released position in which the clamp disengages the dovetail to permit removal of the blade from the fixture.