An assembly is provided for a gas turbine engine. This gas turbine engine assembly includes a split case structure. The split case structure includes a plurality of walls and a plurality of case segments. Each of the walls extends axially along and circumferentially about an axial centerline. The walls include a first wall and a second wall radially outboard of and axially overlapping the first wall. Each of the case segments is configured to form a respective portion of the first wall and a respective portion of the second wall. The case segments include a first case segment and a second case segment circumferentially adjacent and attached to the first case segment at a joint.

A method for establishing a geometrical imperfection database of aerospace thin-walled structures is disclosed. The method comprises the following steps: 1) design the shell quality inspection card that is suitable and convenient to measure the geometrical imperfections for field workers. Obtain the parameters and geometrical imperfections of shells by filling data of measurement points in the shell quality inspection card; 2) perform characteristics combing, mathematical description and component analysis for the geometrical imperfections obtained in the first step; 3) collect and analyze the geometrical imperfection information of multiple aerospace thin-walled shells and establish the geometrical imperfection database based on the first step and second step. The method will effectively serve the development of aerospace equipment, shorten the design cycle and provide guidance and specifications for the design of the thin-walled components carrying main load.

A process for manufacturing a turbomachine part coated with a thermal barrier, includes manufacturing the part by additive manufacture; electrophoretic depositing the part of a layer including particles of a ceramic material; consolidating the layer by heat treatment to obtain a ceramic coating.

An article has a body having: a first face; and a first bevel surface extending from the first face. A plurality of first channels along the first bevel surface extending from the first face. A ceramic coating is along the inner diameter surface and the first bevel surface.

One aspect of the present disclosure includes a turbine vane assembly comprising a vane made from ceramic matrix composite material having an outer wall extending between a leading edge and a trailing edge and between a first end and an opposing second end; an endwall made at least partially from a ceramic matrix composite material configured to engage the first end of the vane; and a retaining region including corresponding bi-cast grooves formed adjacent the first end of the vane and a receiving aperture formed in the endwall; wherein a bond is formed in the retaining region to join the vane and endwall together.

An acoustic core has a plurality of cell walls formed of an additive-manufacturing material and a resonant space defined by the plurality of cell walls. At least some of the resonant cells have a multitude of sound-attenuating protuberances formed of the additive-manufacturing material of the cell walls protruding into the resonant space with a random or semi-random orientation and/or size. The sound-attenuating protuberances may be formed by orienting an additive-manufacturing tool with respect to a toolpath to form a contour of a workpart, in which the toolpath includes a plurality of overlapping toolpath passes configured so as to intentionally introduce an amount of additive-manufacturing material to the workpart that exceeds a domain occupied by the contour. As the amount of additive-manufacturing material intentionally introduced exceeds the domain occupied by the contour, a portion of the additive-manufacturing material may incidentally form the plurality of sound-attenuating protuberances.

A hanging device of a component of a turbine includes: a bridge member that bridges upper ends of a pair of side wall plates facing each other with the turbine interposed therebetween, among plates which constitute an enclosure surrounding an outer periphery of the turbine, and has a traveling path; and a hanging tool that hangs the component of the turbine and travels along the traveling path.

A retaining ring anti-migration system and method. A retaining ring anti-migration system for a centrifugal pump shaft includes a pair of trap sleeves that enclose a pair of retaining rings, one retaining ring around each end of the shaft enclosed by one trap sleeve, the pair of retaining rings configured to bound axial migration of the shaft both upwards and downwards. A retaining ring anti-migration system includes a retaining ring seated in a shaft groove extending circumferentially around an electric submersible pump (ESP) shaft, a trap sleeve extending around the ESP shaft adjacent to the retaining ring, the trap sleeve including a sleeve body secured to the ESP shaft such that the trap sleeve rotates with the ESP shaft, and a jacket extending axially from the sleeve body over an outer diameter of the retaining ring with a clearance between the shaft and the jacket.

An acoustic core has a plurality of cell walls formed of an additive-manufacturing material and a resonant space defined by the plurality of cell walls. At least some of the resonant cells have sound-attenuating protuberances formed of an excess amount of the additive-manufacturing material having been intentionally introduced to the cell walls and protruding into the resonant space with a semi-random orientation and/or size.

In a method for manufacturing an article, the article has a body having: a first face; and a first bevel surface extending from the first face. A plurality of first channels along the first bevel surface extending from the first face. A ceramic coating is along the inner diameter surface and the first bevel surface. Each of the first channels are machined in the body by plunging a rotating bit into the first surface and drawing the rotating bit down the bevel surface. The coating is thereafter applied.