A turbine casing divided in an axial direction into a first casing and a second casing coupled to each other by flanges of the first casing and the second casing. The first casing and the second casing are divided into two parts as viewed from the axial direction, the two parts being an upper half casing and a lower half casing. The turbine casing having three or more sets of a first radial reference surface and a second radial reference surface in a circumferential direction, the first radial reference surface being disposed in a flange peripheral portion of the first casing, and the second radial reference surface being disposed in a flange peripheral portion of the second casing. Each first radial reference surface is located at an equal distance from a turbine central axis. Each second radial reference surface is located at an equal distance from the turbine central axis.

A first cylinder is configured to receive a gas turbine. A second cylinder surrounds an outer circumference of the first cylinder. Retainers extend from the second cylinder towards the first cylinder. Each of the retainers includes a central stalk that extends from the second cylinder towards the first cylinder and a branches extending radially from the central stalk.

An electric coolant pump includes a pump house, a motor connected to the pump house, and an impeller housed in the pump house and driven by the motor. The motor includes a stator and a movable unit rotatably mounted within the stator. The stator is provided with a central shaft. The movable unit includes a support body, a bearing assembly fixedly embedded in the support body, a rotor core fixed to the support body, and a plurality of permanent magnets attached to the rotor core. The bearing assembly includes at least one bearing rotatably sleeved on the central shaft. The support body is formed by an injection-molding process to wrap the bearing assembly and fixed connecting bearing assembly and the rotor core.

A turbine exhaust case (TEC) has an outer case and an inner case structurally interconnected by a plurality of circumferentially spaced-apart struts. At least one of the struts has an airfoil body with a hollow core. The airfoil body has opposed pressure and suction sides extending chordwise from a leading edge to a trailing edge and spanwise from a radially inner end to a radially outer end. The radially inner end of the strut has a strut wall extension that extends through the inner case to a location radially inward of the inner case relative to the central axis.

An integrated propulsion system according to an example of the present disclosure includes, among other things, a fan section, a gas turbine engine, a geared architecture, a nacelle assembly and a mounting assembly. The nacelle assembly includes a fan nacelle and an aft nacelle, the fan nacelle arranged at least partially about a fan and the engine, and the fan nacelle arranged at least partially about a core cowling to define a bypass flow path.

A turbine casing divided in an axial direction into a first casing and a second casing coupled to each other by flanges of the first casing and the second casing. The first casing and the second casing are divided into two parts as viewed from the axial direction, the two parts being an upper half casing and a lower half casing. The turbine casing having three or more sets of a first radial reference surface and a second radial reference surface in a circumferential direction, the first radial reference surface being disposed in a flange peripheral portion of the first casing, and the second radial reference surface being disposed in a flange peripheral portion of the second casing. Each first radial reference surface is located at an equal distance from a turbine central axis. Each second radial reference surface is located at an equal distance from the turbine central axis.

A centrifugal compressor includes: a housing accommodating an impeller; a diffuser flow path formed radially outside the impeller in the housing; and a scroll flow path formed in the housing and connected to the diffuser flow path from a radially-outer side, the scroll flow path extending in a rotational axis direction and a rotational direction of the impeller with respect to the diffuser flow path, the scroll flow path including a radially-inner end located at the radially-innermost position, and the radially-inner end being spaced apart from the diffuser flow path with respect to a middle point of the maximum flow path width of the scroll flow path in the rotational axis direction.

An assembly is provided for a gas turbine engine. This gas turbine engine assembly includes a stationary engine structure. The stationary engine structure includes a diffuser, a combustor, an engine case and a plenum. The combustor is disposed within the plenum. The engine case forms a peripheral boundary of the plenum. A gas path extends sequentially through the diffuser, the plenum and the combustor. A first section of the stationary engine structure is formed as a first monolithic body. The first section includes the diffuser and the combustor. A second section of the stationary structure is formed as a second monolithic body. The second section is configured as or otherwise includes the engine case.

A gas turbine engine component has a component body configured to be positioned within a flow path of a gas turbine engine having an external pressure, and wherein the component body includes at least one internal cavity having an internal pressure. At least one inlet opening is formed in an outer surface of the component body to direct hot exhaust gas flow into the at least one internal cavity, and there is at least one outlet from the internal cavity. The internal pressure is less than an inlet external pressure at the inlet opening and the internal pressure is greater than an outlet external pressure at the outlet opening to controllably ingest hot exhaust gas via the inlet opening and expel the hot exhaust gas via the outlet opening to maintain a laminar boundary layer along the outer surface of the component body.

A method is provided involving a fairing for a turbine engine. During this method, a detail is provided. The detail includes a carrier and an exterior layer bonded to the carrier. The carrier is configured from or otherwise includes fiber-reinforced composite material. The exterior layer is configured from or otherwise includes polymer material. The detail is arranged with the fairing. The fairing includes an exterior side and an edge. The detail covers and extends along at least a portion of the exterior side. The detail wraps at least partially around the edge. The carrier and at least a first overhang portion of the exterior layer are bonded to the fairing.