A gas turbine engine comprises a main gas path having an inner flow boundary wall and an outer flow boundary wall. A turbine exhaust case inner body defines a portion of the inner flow boundary wall of the main gas path. A lobed exhaust mixer defines a portion of the outer flow boundary wall of the main gas path. A stiffener ring is interconnected to at least a number lobes of the lobed exhaust mixer by a plurality of circumferentially spaced-apart struts extending through the main gas path. The stiffener ring is attached to the turbine exhaust case inner body by flexible features, such as circumferentially spaced-apart spring blades.

An inlet guide vane assembly is provided. The inlet guide vane assembly includes a housing, a rotating shaft rotatably located in the housing, a vane portion connected to the rotating shaft, a bushing portion located between the rotating shaft and the housing, and an elastic portion located between the bushing portion and the rotating shaft.

A turbocharger having a housing and a stator. The housing and/or the stator has an inner and an outer housing component. An inner section of the housing component lies directly against and covers a lateral section of the housing component. The lateral section and the inner section are formed such that they form a positive-locking connection, which fixes the inner housing component and the outer housing component against positional change along a longitudinal axis of the turbocharger and/or against a rotation about this longitudinal axis. The inner housing component and/or the outer housing component is at least partly produced by additive manufacturing.

A seal assembly for a fluid transfer tube in a gas turbine engine is disclosed. In various embodiments, the seal assembly includes a base member having a first side configured to mate with a casing and a second side opposite the first side, a housing configured to mate with the second side of the base member and to surround a portion of the fluid transfer tube, a bellows surrounding the fluid transfer tube and positioned between the housing and the casing, and a wear ring disposed between the housing and the bellows.

The invention relates to a semiconductor body revolving around a main axis (A) for a spark plug of a turbine engine, the semiconductor body comprising a baseplate and an upper portion extending from the baseplate along the main axis, the baseplate comprising a bottom surface substantially defined in a plane perpendicular to the main axis and a first conical surface intended to cooperate by form-fitting at least partially with a contact surface of an outer electrode of the spark plug. According to the invention, the upper portion comprises an interface located opposite the bottom surface along the main axis (A) and featuring a profile that is at least partially corrugated.

A flat reverse vortex ring is sized and shaped to either attach to or be formed as part of a distal end of a sleeve bearing or seal. The ring has a series of evenly spaced radial channels that extend from an inner diameter to an outer diameter of the ring. The channels have a depth. The ring has an upper surface with an alternating series of planar surfaces and openings located at an upper end of the channels. The ring may have an interior diameter equal to an interior diameter of the sleeve bearing or seal. The ring may have an exterior diameter equal to an exterior diameter the sleeve bearing or seal. The channels may be semi-cylindrical. The channels have a diameter and the depth is a predetermined portion of the diameter. The channels may be rectangular in cross-section with a height-to-width ratio of between 0.5 and 1.5.

A turbine engine duct assembly including a joint assembly having an outer shroud, a bellows, a flared tube, a backing ring, and a kinematic ring. The joint assembly provides for dynamic movement of the duct assembly during operation of the engine. Such dynamic movement can be resultant of vibrational forces or thermal expansion of the engine. The joint assembly permits such dynamic movement without excessive system stiffness.

An impeller for an exhaust gas turbocharger may include a hub main body and blades arranged thereon. The hub main body may be configured as a polygon with a number of segments that may be tilted with respect to one another, the number of the segments corresponding to a number of the blades. Alternatively, the hub main body may have a main surface that faces the blades and undulates in a circumferential direction, a number of the undulations corresponding to the number of the blades.

A gas turbine engine defines a radial direction and an axial centerline. The gas turbine engine includes a core turbine engine that defines a core inlet. The core inlet is oriented with respect to the axial centerline and positioned along the radial direction such that the area available to capture foreign object debris is minimized. In one aspect, the gas turbine engine defines a capture ratio less than about 35%, wherein the capture ratio is a ratio of an area between a splitter radius and a tangency radius to an area encompassed by the splitter radius. The splitter radius is defined as a radial distance between the axial centerline and an outer lip of a splitter of the core turbine engine. The tangency radius is defined as a radial distance between the axial centerline and a tangency point, which can be defined at an inner lip of the core inlet.

A compressor for a turbine engine includes an annular row of blades including a first blade with an extrados surface and a second blade with an intrados surface; and a connecting surface joining the intrados surface to the extrados surface, the connecting surface having a bulge of volume VB and a recess of volume VC, the bulge and recess forming a contouring 3D. The volume of the bulge VB is greater than four times the volume VC of the recess, the connecting surface includes a flat or axisymmetric band circumferentially separating the bulge from the recess, and the bottom of the recess being formed against the intrados surface.