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 first wall, a second wall, a first case segment and a second case segment. The first wall extends axially along and circumferentially about an axial centerline. The second wall extends axially along and circumferentially about the axial centerline. The second wall is radially outboard of and axially overlaps the first wall. The first case segment is configured to form a first portion of the first wall and a first portion of the second wall. The second case segment is configured to form a second portion of the first wall and a second portion of the second wall. The second case segment is circumferentially adjacent and attached to the first case segment at a joint.

Methods, apparatus, systems and articles of manufacture are disclosed for a structure of an engine component, including a first plurality of unit cells offset from a neutral plane in a first direction, a second plurality of unit cells offset from the neutral plane in a second direction, a plurality of nodes joining ones of the first plurality of unit cells and ones of the second plurality of unit cells, wherein the first plurality of unit cells and the second plurality of unit cells are arranged in pairs such that ones of the first plurality of unit cells are laterally adjacent to and interconnected with ones of the second plurality of unit cells, and wherein the structure is a stiffened structure.

Methods, apparatus, systems and articles of manufacture are disclosed for a structure of an engine component, including a first plurality of unit cells offset from a neutral plane in a first direction, a second plurality of unit cells offset from the neutral plane in a second direction, a plurality of nodes joining ones of the first plurality of unit cells and ones of the second plurality of unit cells, wherein the first plurality of unit cells and the second plurality of unit cells are arranged in pairs such that ones of the first plurality of unit cells are laterally adjacent to and interconnected with ones of the second plurality of unit cells, and wherein the structure is a stiffened structure.

An assembly or disassembly method for a casing of a steam turbine in which an inner casing is installed in an outer casing, and the inner casing and the outer casing are fixed at a fixing position, wherein when the inner casing is assembled or disassembled in a state where the fixing position and a gravity center of the inner casing are at different positions in an axial direction of the inner casing, a tilt adjusting jig is interposed between the outer casing and the inner casing so that the assembly or disassembly of the casing is performed while maintaining a tilt of the inner casing with the tilt adjusting jig.

An assembly or disassembly method for a casing of a steam turbine in which an inner casing is installed in an outer casing, and the inner casing and the outer casing are fixed at a fixing position, wherein when the inner casing is assembled or disassembled in a state where the fixing position and a gravity center of the inner casing are at different positions in an axial direction of the inner casing, a tilt adjusting jig is interposed between the outer casing and the inner casing so that the assembly or disassembly of the casing is performed while maintaining a tilt of the inner casing with the tilt adjusting jig.

A modular flooring system comprises a modular floor surface and a plurality of stackable, three-dimensional modular interior design components (MIDCs). The modular door surface can comprise an array of discrete, raised, low-profile, receiving panels that can be rectangular in shape. MIDCs can be securely and interchangeably placed on any group of one or more adjacent unoccupied receiving panel and they east also be stackable, such that various different floor layouts can be created. Bach of the MIDCs may comprise a lower surface recess that fits over a group of one or more adjacent raised receiving panels. A first MIDC may have an raised lip on a top surface such that the lower surface recess of a second MIDC fits over, separately and interchangeably, one (or more) of the raised receiving panels and the raised lip on the top surface of the first MIDC. The MIDCs can comprise a storage cube MIDC (square or rectangular cube) as well as specialized MIDCs, such as a commode MIDC, a sink MIDC, a cooler MIDC, and a tile MIDC, etc. In such a manner, a user of the modular flooring system could locate the MIDCs on the floor surface and/or stack them to configure a preferred layout. Moreover, the MIDCs could be rearranged later to design a new layout.

A gas passage for a gas turbine engine, which allows for quicker and easier determination of the condition of a liner within the gas passage without the need for dismantling the entire gas passage, or irreparably damaging large sections of the liner. The gas passage comprises a casing with one or more plugs which are at least partly coated in a material matching the material composition of the lining, which can be removed from the gas passage in order to analyse the condition of the lining material.

A gas passage for a gas turbine engine, which allows for quicker and easier determination of the condition of a liner within the gas passage without the need for dismantling the entire gas passage, or irreparably damaging large sections of the liner. The gas passage comprises a casing with one or more plugs which are at least partly coated in a material matching the material composition of the lining, which can be removed from the gas passage in order to analyse the condition of the lining material.

A steam turbine includes a rotor, a casing, a partition plate, and a center guide pin. The center guide pin has a positioning portion. In a state of being attached to a pin attachment portion formed in one of the casing and the partition plate, the positioning portion is disposed in a groove portion formed in the other of the casing and the partition plate. The positioning portion includes a plurality of abutment portions capable of abutting on an inner side surface of the groove portion, around a pin axis. The plurality of abutment portions is formed to have different horizontal distances from the pin axis.

A strut cover for a gas turbine includes: a cylindrical sheet metal member having a hollow portion; and a flare member that is connected to one end of the cylindrical sheet metal member in an axial direction of the cylindrical sheet metal member and includes a curved portion having an outer surface such that a distance from a center axis of the cylindrical sheet metal member to the outer surface increases with increasing a distance from the cylindrical sheet metal member in the axial direction. The flare member has a thickness larger than a minimum thickness of the cylindrical sheet metal member at least in the curved portion.