A method for repairing composite components includes installing a plug within a feature defined by a composite component, with the plug being formed from one or more neutral materials. Furthermore, the method includes infiltrating the composite component with an infiltrant to densify a repair region of the composite component, with the plug blocking a flow of the infiltrant into the feature. Moreover, after infiltrating the composite component, the method includes removing the plug from the feature.

Disclosed is a repair method for guide blades of a gas turbine. The method comprises: providing at least one guide blade to be maintained; capturing the actual geometry of the guide blade to be maintained with application of at least one measuring method; comparing the actual geometry captured by the contactless measuring method to a predetermined desired geometry for a corresponding guide blade type; calculating a target geometry for the guide blade to be maintained, which corresponds as much as possible to the desired geometry, such that using optimization parameters, the desired geometry of the guide blade to be maintained is approximated at least in sections along its flow contour; applying material and removing material by machine on the guide blade, such that the calculated target geometry is produced.

A method and apparatus for maintaining integrally bladed rotors (IBR) includes using first vibration data from a IBR vibration apparatus of a first IBR to determine a set of values for a corresponding set of inherent vibratory properties based on a reduced order model for an IBR type to which the first IBR belongs. Shape data indicating an initial shape of a surface of a first blade is used, with repair data that indicates a candidate repair to form a restored shape, to determine a change in a value of an inherent blade section vibratory property of the set of inherent vibratory properties. A condition of the first IBR is determined based at least in part on the change in the value of the inherent blade section vibratory property. The first IBR is maintained based on the condition.

A method for detecting cracks in an aircraft or gas turbine component includes ascertaining geometric data about the component using an optical measurement method, analyzing the geometric data, using an electronic evaluation device, so as to automatically recognize and/or classify at least one of cracks and other damage and storing a position of the at least one of cracks and other damage.

A method of repairing a piston seal assembly comprises removing worn material from a piston seal groove to generate a worked seal groove, applying a groove buildup member to the worked seal groove, and disposing a seal member proximate the groove buildup member.

A reconfigurable maintenance apparatus includes a body configured to operate within a cavity. The body has a first shape in a first configuration and a second shape in a second configuration. The first configuration facilitates the body entering the cavity. The reconfigurable apparatus also includes at least one maintenance device operably coupled to the body. The second configuration facilitates the at least one maintenance device of the reconfigurable apparatus performing a maintenance operation.

A method of additively manufacturing is provided. The method may include successively depositing and fusing together layers of a superalloy powder mixture comprised of a base material powder and a eutectic powder, to build up an additive portion, which eutectic powder has a solidus temperature lower than the solidus temperature of the base material powder. The method may also include heat treating the additive portion at a temperature greater than 1200° C. to heal cracks and/or fill pores and to homogenize the alloy of which the additive portion is comprised. The additive portion alloy has a chemistry defined by the superalloy powder mixture. The base material powder may be formed of a nickel-base superalloy with an aluminum content by weight of at least 1.5%. The eutectic powder may be a nickel-base alloy including by weight about 6% to about 11% chromium, about 5% to about 9% titanium, and about 9% to about 13% zirconium, with balance nickel as its primary components.

A turbomachine diaphragm including a sealing section having a first end portion that extends to a second end portion through an intermediate portion; and at least one rail member including a first end section that extends from the first end portion of the sealing section to a second end section through an intermediate section having an inner surface section and an outer surface section, the second end section including multiple weld passes disposed on opposed sides of the second end section for mitigation of thermal tensions on the diaphragm, the multiple weld passes forming a cladding welded to the diaphragm, wherein the cladding includes a stainless austenitic steel.

A tool for machining an object including a first part including a rotatable member that is rotatable to cause rotation of a machine tool, a second part, a joint coupling the first part and the second part to enable relative movement between the first part and the second part, and a sensor to sense an object to be machined.

An insertion tool is provided for an engine defining an access opening and including a component defining at least in part a cavity. The insertion tool includes: an insertion tool arm having a plurality of segments, the insertion tool arm configured for insertion through the access opening into the cavity and the plurality of segments configured to be in a fixed position relative to one another within the cavity; and a base coupled to the insertion tool arm and configured to be positioned outside the cavity and to move the insertion tool arm along at least two degrees of freedom.