Abstract: A balance system for an assembled engine includes a rotor mounted on a shaft for rotation within an engine casing having an inner case and an outer case; and a weight system mounted on the shaft of the rotor and having at least one weight positionable relative to the rotor around a circumference of the shaft; wherein the inner case has an inner access port, the outer case has an outer access port, and the inner access port, the outer access port and the weight system are positioned on the same radial plane of the rotor, whereby the weight system can be accessed through the outer port and the inner port to adjust circumferential position of the at least one weight relative to the rotor.

Abstract: A balance system for an assembled engine includes a rotor mounted on a shaft for rotation within an engine casing having an inner case and an outer case; and a weight system mounted on the shaft of the rotor and having at least one weight positionable relative to the rotor around a circumference of the shaft; wherein the inner case has an inner access port, the outer case has an outer access port, and the inner access port, the outer access port and the weight system are positioned on the same radial plane of the rotor, whereby the weight system can be accessed through the outer port and the inner port to adjust circumferential position of the at least one weight relative to the rotor.

Abstract: A method of maintaining a gas-turbine engine is provided. The method includes the steps of removing a conduit from the gas-turbine engine, installing a temporary oil filter in place of the conduit in the gas-turbine engine, and starting the gas-turbine engine with the temporary oil filter installed. A fan-drive gear system is also provided and comprises a journal bearing, a main oil pump fluidly coupled to the journal bearing, a main oil filter fluidly coupled between the journal bearing and the main oil pump, and an auxiliary oil pump fluidly coupled to the journal bearing. The auxiliary oil pump may be configured to supply oil to the journal bearing on startup. An auxiliary oil filter may also be installed between the auxiliary oil pump and the journal bearing.

Abstract: Aspects of the disclosure are directed to a cover configured to substantially conform to a profile of a first assembly of an engine in terms of the dimensions of the first assembly and hermetically seal the first assembly such that a second assembly of the engine that is external to the cover is accessible, a container containing a desiccant, and a screen coupled to the container.

Abstract: A method of maintaining a gas-turbine engine is provided. The method includes the steps of removing a conduit from the gas-turbine engine, installing a temporary oil filter in place of the conduit in the gas-turbine engine, and starting the gas-turbine engine with the temporary oil filter installed. A fan-drive gear system is also provided and comprises a journal bearing, a main oil pump fluidly coupled to the journal bearing, a main oil filter fluidly coupled between the journal bearing and the main oil pump, and an auxiliary oil pump fluidly coupled to the journal bearing. The auxiliary oil pump may be configured to supply oil to the journal bearing on startup. An auxiliary oil filter may also be installed between the auxiliary oil pump and the journal bearing.

Abstract: A method of maintaining a gas-turbine engine is provided. The method includes the steps of removing a conduit from the gas-turbine engine, installing a temporary oil filter in place of the conduit in the gas-turbine engine, and starting the gas-turbine engine with the temporary oil filter installed. A fan-drive gear system is also provided and comprises a journal bearing, a main oil pump fluidly coupled to the journal bearing, a main oil filter fluidly coupled between the journal bearing and the main oil pump, and an auxiliary oil pump fluidly coupled to the journal bearing. The auxiliary oil pump may be configured to supply oil to the journal bearing on startup. An auxiliary oil filter may also be installed between the auxiliary oil pump and the journal bearing.

Abstract: Aspects of the disclosure are directed to a cover configured to substantially conform to a profile of a first assembly of an engine in terms of the dimensions of the first assembly and hermetically seal the first assembly such that a second assembly of the engine that is external to the cover is accessible, a container containing a desiccant, and a screen coupled to the container.

Abstract: A method of repairing an integrally bladed rotor includes removing a portion of the integrally bladed rotor to create a void in an airfoil, completely filling the void with a single replacement material, and laser shock peening the replacement material. Laser shock peening the replacement material imparts mechanical properties in the replacement material substantially the same as those in the forged material.

Abstract: A method of maintaining a gas-turbine engine is provided. The method includes the steps of removing a conduit from the gas-turbine engine, installing a temporary oil filter in place of the conduit in the gas-turbine engine, and starting the gas-turbine engine with the temporary oil filter installed. A fan-drive gear system is also provided and comprises a journal bearing, a main oil pump fluidly coupled to the journal bearing, a main oil filter fluidly coupled between the journal bearing and the main oil pump, and an auxiliary oil pump fluidly coupled to the journal bearing. The auxiliary oil pump may be configured to supply oil to the journal bearing on startup. An auxiliary oil filter may also be installed between the auxiliary oil pump and the journal bearing.

Abstract: A method of repairing an integrally bladed rotor includes removing a portion of the integrally bladed rotor to create a void in an airfoil, completely filling the void with a single replacement material, and laser shock peening the replacement material. Laser shock peening the replacement material imparts mechanical properties in the replacement material substantially the same as those in the forged material.

Abstract: A method for defining an airfoil with a radiused shape edge includes joining a filler material to the airfoil such that the filler material defines excess material that extends beyond an operational condition edge location of the edge of the airfoil, placing the airfoil within a barrel, providing an abrasive finishing media in the barrel with the airfoil, rotating the barrel to produce relative motion between the abrasive finishing media and the airfoil. Contact between the abrasive finishing material and the airfoil facilitates removing the excess material that extended beyond the operational condition edge location of the edge of the airfoil.

Abstract: A component blending tool assembly, includes a material removing surface that is moved to provide a blended area in a component, the material removing surface having a spherical contour mimicking a predetermined depth ratio of the blended area.

Abstract: A fixture assembly for retaining a workpiece during a coining process includes a mounting block. The workpiece includes an airfoil portion, a platform, and feet extending from the platform opposite the airfoil portion configured to engage a retention slot in a gas turbine engine, each foot defining a substantially arcuate engagement surface. The mounting block includes a first portion having a slot defined therein between opposite first and second lateral edges and having an exposed front face, first and second retaining structures positioned adjacent to the first and second lateral edges, respectively. Each of the first and second retaining structures overhangs the slot and defines an engagement surface facing the slot, such that during engagement of the workpiece the substantially arcuate engagement surfaces of the feet contact the engagement surfaces of the first and second retaining structures to provide a pivotable engagement.

Abstract: A fixture assembly for retaining a workpiece during a coining process includes a mounting block. The workpiece includes an airfoil portion, a platform, and feet extending from the platform opposite the airfoil portion configured to engage a retention slot in a gas turbine engine, each foot defining a substantially arcuate engagement surface. The mounting block includes a first portion having a slot defined therein between opposite first and second lateral edges and having an exposed front face, first and second retaining structures positioned adjacent to the first and second lateral edges, respectively. Each of the first and second retaining structures overhangs the slot and defines an engagement surface facing the slot, such that during engagement of the workpiece the substantially arcuate engagement surfaces of the feet contact the engagement surfaces of the first and second retaining structures to provide a pivotable engagement.

Abstract: A method for defining an airfoil with a radiused shape edge includes joining a filler material to the airfoil such that the filler material defines excess material that extends beyond an operational condition edge location of the edge of the airfoil, placing the airfoil within a barrel, providing an abrasive finishing media in the barrel with the airfoil, rotating the barrel to produce relative motion between the abrasive finishing media and the airfoil. Contact between the abrasive finishing material and the airfoil facilitates removing the excess material that extended beyond the operational condition edge location of the edge of the airfoil.

Abstract: The invention is a penetration resistant turbine engine fan casing (12) for containing separated fragments of a fan blade (16). The casing includes a penetration susceptible support case (14), a penetrable covering (32) circumscribing an impact zone (I) of the support case and an optional, but highly recommended collapsible support covering (34) circumscribing the case but axially offset from the impact zone. A containment covering (36) circumscribes both the penetrable covering (32) and the support covering (34). In a preferred embodiment, the coverings are aromatic polyamide fiber fabrics and the support covering is a collapsible cellular array. In operation, a detached fragment of a fan blade penetrates through the case (14) and the penetrable covering (32), and is plastically deformed by the penetrable covering to reduce the fragment's potential for damaging the containment covering (36).