A compression rod engagement apparatus is provided that includes an engagement feature, an engagement feature pin, and a mounting member. The engagement feature is attached to the engagement feature pin. The engagement feature pin is engaged with the mounting member in a home position and axial travel of the engagement feature pin along a lengthwise axis away from the home position in either axial direction is resisted by at least one spring force.

A split case assembly for a gas turbine engine includes an outer diameter case defining a partial case structure for a gas turbine engine and multiple fixed-variable vanes attached to an inner diameter surface of the outer diameter case. Each of the fixed-variable vanes protrudes radially inward from the outer diameter case. Each of the fixed-variable vanes in the plurality of fixed-variable vanes is interfaced with one of a plurality of inner diameter boxes at a radially inward end of the fixed-variable vane, such that the inner diameter boxes define an inner diameter of a flow path and the outer diameter case defines an outer diameter flow path. Each of the fixed-variable vanes are interfaced with the one of the plurality of inner diameter boxes through at least one inner diameter shoe in a plurality of inner diameter shoes.

The invention relates to a mid-frame (10) for a gas turbine, having at least one outer casing element (12) and having a plurality of duct segments (16), which are arranged in succession in the radial direction on the inside of the outer casing element (12) and in the peripheral direction of the casing element (12) and by which segments, in each case, at least one duct (18) through which a gas can flow is delimited at least in the radial direction at least partially, wherein a ring element (22) that is common to the duct segments (16) and is formed in one piece is provided, by means of which the duct segments (16) are held at the outer casing element (12).

A gas turbine engine assembly adapted to separate a high pressure zone from a low pressure zone includes a seal assembly configured to block gasses from passing through the interface of two adjacent components. The seal assembly includes a rod.

A modular flooring system comprises a modular floor surface and a plurality of stackable, three-dimensional modular interior design components (MIDCs). The modular floor 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 can also be stackable, such that various different floor layouts can be created. Each 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 case assembly for a gas turbine engine includes a case extending circumferentially about an engine central longitudinal axis and two or more components installed in the case at different axial and/or radial locations. A retainer is installed at a circumferential end of the case, the retainer configured to circumferentially retain the two or more components at the case. A circumferential retainer of a case assembly of a gas turbine engine includes a retainer pin configured for installation in retaining feature of a circumferential end of a case, and one or more retainer arms extending from the retainer pin. The one or more retainer arms are configured to extend at least partially across two or more components installed in the case at different axial and/or radial locations to circumferentially retain the two or more components at the case.

A casing assembly for a gas turbine engine includes a plurality of vane casing segments. Each vane casing segment includes an arcuate member and a pair of split-line flanges. Each split-line flange includes a first axial flange end and a second axial flange end. Each split-line flange is fixedly coupled to an adjacent split-line flange of an adjacent vane casing segment. Each vane casing segment includes at least one row of stator vanes welded to the arcuate member. Each split-line flange is at least partially and circumferentially inclined relative to a rotational axis of the gas turbine engine, such that the first axial flange end is circumferentially offset from the second axial-flange end. Further, each split-line flange includes an intersecting portion, such that at least the intersecting portion of each split-line flange is circumferentially inclined relative to the rotational axis.

A vertical joint coupling structure includes a first casing in which combustion gases flow, a second casing connected to the first casing, a vertical joint mounted on the second casing and coupled to the first casing, a plurality of bolt fasteners fastened to the vertical joint and the first casing, a plurality of jacking screws inserted into the vertical joint to secure a gap between the vertical joint and the first casing upon disassembly or assembly between the first casing and the second casing, and a shim member inserted into the gap between the vertical joint and the first casing.

A turbomachine inner housing for a radial turbomachine, wherein the turbomachine inner housing includes a partial joint along a longitudinal axis, in particular a rotor longitudinal axis, such that the turbomachine inner housing can be divided into a lower part and an upper part, wherein the turbomachine inner housing is designed for a radial turbomachine with at least two stages, wherein the turbomachine inner housing has a return stage in each case between two stages, wherein the lower part and/or the upper part is designed in one piece so as to span at least two stages at least in sections. In order to improve a turbomachine inner housing of this kind, the lower part and/or the upper part is designed in one piece so as span at least two stages at least in sections.

A compact axial turbine configured to operate with high density working fluid is described. The turbine comprises an axial majority cantilevered turbomachinery shaft. Rotor assemblies and nozzle spacers communicate torque through turbine shaft splines, allowing them to be slid off the shaft for quick replacement in the field. The compact axial turbine houses turbomachinery within a separable inner casing encircled by a cartridge sleeve, thereby forming a cartridge which can itself be removed as a single component.