Abstract: A casing of a turbine of a turbine engine includes an internal shroud, an external shroud extending around the internal shroud, and hollow arms connecting the external shroud to the internal shroud and each intended to receive a tubular auxiliary element, each hollow arm defining an inner housing connecting a first passage orifice passing through the internal shroud in the radial direction to a second passage orifice passing through the external shroud in the radial direction, and including an inner wall facing the inner housing. Each arm includes at least one protrusion on the inner wall of the arm protruding from the inner wall towards the inner housing and defining a constriction of the inner housing in a section plane orthogonal to the direction in which the arm extends.

Abstract: An assembly includes a supporting structure and a measuring device. The measuring device includes a first flexible coupling which is torsionally stiff and non-rotatably connected to the supporting structure, a rod having a longitudinal axis and being non-rotatably connected to the first flexible coupling, and an angle-measuring device including a first component group non-rotatably connected to the rod and a second component group non-rotatably connected to the supporting structure. The first component group is disposed to be rotatable about the longitudinal axis of the rod relative to the second component group, and the angle-measuring device is configured to allow measurement of a relative angular position between the two component groups. By such an assembly, a torsion of the supporting structure about the longitudinal axis of the rod caused by mechanical loading is determinable by measuring the relative angular position between the two component groups.

Abstract: An air handler blower assembly includes a blower housing containing a centrifugal fan and a motor mounted on the blower housing and connected to the fan. The blower housing has opposite first and second air inlet openings that are coaxial with the fan, and the first inlet opening is larger than the second inlet opening. The motor is mounted on the blower housing with the motor extending axially through the first inlet opening into the blower housing and into the interior of the fan. The positioning of the motor inside the blower housing and inside the fan reduces the overall axial dimension of the blower assembly. The larger first air inlet opening reduces the losses associated with placing the motor in the first air inlet opening while keeping the second air inlet opening at a smaller size than the first air inlet opening avoids creating buffeting noise and a power/efficiency loss from occurring.

Abstract: A rotating leaf spring seal is disclosed. In various embodiments, the rotating leaf spring seal includes a first annular ring configured for positioning against a support structure; a hook section having an outer surface configured for sealing engagement with a tie shaft and an inner surface configured for receiving a hold down ring; and a spring section disposed between the first annular ring and the hook section.

Abstract: A turbine shroud assembly for use with a gas turbine engine includes a blade track segment coupled to a carrier segment, and a sheet-metal seal that seals therebetween. The blade track segment includes a shroud wall that extends circumferentially partway around an axis and an attachment feature that extends radially outward from the shroud wall. The carrier is coupled with the attachment feature to support the blade track segment.

Abstract: A nested segment assembly and a method of additively manufacturing the same are provided. In one example aspect, the nested segment assembly includes a first component segment and a segment component segment positioned adjacent the first component segment. The first component segment has an end face and a tongue projecting outwardly from the end face. The second component segment defines a groove. The groove is defined at an end face of the second component segment that is adjacent the end face of the first component segment. The first component segment and the second component segment are additively printed such that at least a portion of the tongue of the first component segment is nested within the groove defined by the second component segment. Segmented components having a tesla valve formed therebetween are also provided.

Abstract: A fan includes: a housing; and an impeller with an axis and a plurality of blades, the impeller mounted inside the housing; and a plurality of outlets from the housing, each outlet including a cutoff with a top and a bottom. A line between the top and bottom of each cutoff is not parallel to the axis of the impeller.

Abstract: A centrifugal blower includes a centrifugal fan having a fan wheel that is configured to rotate about a rotational axis. The centrifugal blower includes a blower housing having a first side panel, a second side panel, and a wall extending about the rotational axis and between the first and second side panels. The centrifugal blower also includes a cutoff plate that is configured to extend about the rotational axis, where the cutoff plate includes a first end with a flange having a camber geometry and a second end that is configured to overlap with the wall such that an amount of overlap between the second end and the wall is adjustable to adjust a position of the flange relative to the fan wheel. The centrifugal blower further includes an exhaust port defined by the first side panel, the second side panel, the wall, and the flange.

Abstract: A flow path component assembly includes a support structure. A flow path component has a plurality of segments that are arranged circumferentially about an axis and are mounted in the support structure by a carrier. At least one of the segments have a first wall axially spaced from a second wall. The first wall has first and second hooks spaced apart from one another in a circumferential direction. The second wall has third and fourth hooks spaced apart from one another in the circumferential direction. The first, second, third, and fourth hooks are in engagement with the carrier.

Abstract: A gear assembly for a turbo machine is provided. The gear assembly includes a first input shaft, a second input shaft, an output shaft, a fixed member, and a spindle. The spindle is extended along a spindle centerline axis. The first input shaft is drivingly connected to the spindle at a first interface. The second input shaft is drivingly connected to the spindle at a second interface. The spindle is connected to the fixed member providing a reactive force at a third interface. The spindle is connected to the output shaft at a fourth interface.

Abstract: A stator vane angle system includes an engine case, a plurality of stator vanes located at an interior of the engine case. Each stator vane is rotatable about a stator vane axis. A synchronization ring is located at an exterior of the engine case. The synchronization ring is operably connected to each stator vane of the plurality of stator vanes such that movement of the synchronization ring urges rotation of each stator vane of the plurality of stator vanes about their respective stator vane axes. A plurality of impingement openings extend through the engine case from the interior of the engine case to the exterior of the engine case. The plurality of impingement openings are configured to direct flowpath gases from the interior of the engine case to impinge on the synchronization ring, thereby reducing a thermal mismatch between the engine case and the synchronization ring.

Abstract: The component of the turbomachine comprises a body of the component, a bond layer covering a base surface of the body, and a top layer covering the bond layer and made of abradable ceramic material. The base surface of the component has patterned protrusions and, through two covering steps used for forming the bond layer and the top layer, also the top surface of the component has patterned protrusions. The pattern protrusions of the base surface may be obtained in different ways, for example casting, milling, grinding, electric discharge machining or additive manufacturing. The patterned protrusions belong to an abradable seal of the turbomachine, and may be shaped and sized to maintain specified clearances and to reduce flow of a working fluid within turbomachinery equipment and/or it's components.

Abstract: A gas turbine engine includes an engine spool with a turbine section, a propeller, a motor, and a variable drive arrangement. The variable drive arrangement mechanically couples the engine spool to the propeller, and includes a first gear connection rotationally coupled to the propeller, a second gear connection rotationally coupled to the engine spool, and a sprag clutch rotationally coupled to the first gear connection. The sprag clutch is configured to passively decouple the motor from the first gear connection when a torque input from the engine spool exceeds a torque input from the motor, and is configured to passively couple the motor to the first gear connection when the torque input from motor exceeds a torque input from the engine spool.

Abstract: A turbine shroud assembly for use with a gas turbine engine includes a carrier assembly coupled to a blade track segment, and a sheet-metal seal that seals on axial and radial facing surfaces therebetween. The blade track segment includes a shroud wall that extends circumferentially partway around an axis and an attachment feature that extends radially outward from the shroud wall. The carrier is coupled with the attachment feature to support the blade track segment.

Abstract: An impeller for use in a pump assembly for a fluid circuit of an engine of a vehicle comprises a plurality of projections provided at radially spaced locations relative to a rotational axis of the impeller, the impeller being rotatable relative to a housing of the pump assembly. The projections extend axially from a surface of the impeller and circumferentially about the rotational axis of the impeller. At least one of the projections is configured to be at least partially received in a recess provided in the housing such that a flow path is provided by the projection and the respective recess, wherein the flow path provides a tortuous flow route for fluid between an inlet and outlet of the pump assembly so as to restrict flow of fluid along said flow path and thereby minimise flow of fluid from the outlet back towards the inlet in a direction opposite to the intended direction of flow.

Abstract: An assembly adapted for use in a gas turbine engine or other engine has a carrier component and a blade track segment. The assembly includes a mounting system for coupling the blade track segment to the carrier component. In an illustrative embodiment, the assembly is a turbine shroud segment for blocking gasses from passing over turbine blades included in the gas turbine engine.

Abstract: A turbine section of a gas turbine engine includes a vane assembly that redirects hot gases in the turbine section, a turbine shroud that extends around a turbine wheel to keep the hot gases from avoiding interaction with the turbine wheel, and a heat shield that provides parts of the vane assembly and the turbine shroud. The heat shield comprises ceramic matrix composite materials and is formed as a one piece component. The heat shield includes a vane portion that protects other vane assembly parts, a seal segment portion that protects other turbine shroud parts, and a forward turn-up and an aft turn-up. The forward turn-up and the aft turn-up couple the heat shield to other parts of the turbine section.

Abstract: A rotary machine includes damper pins and platforms each having a flat surface extending in an axial line direction. For each adjacent pair of the platforms, a damper abutting surface of a first of the adjacent pair of the platforms extends toward a damper abutting surface of a second of the adjacent pair of the platforms as approaching an outer side of a rotor blade stage in a radial direction while opposing each other in a peripheral direction. A damper accommodation space, which is defined by surfaces including the damper abutting surfaces, is defined between each adjacent pair of the platforms. Each of the damper pins defines a regular polygonal prism extending in the axial line direction and includes a damper pin main body in which an angle defined by two side surfaces corresponds to an angle defined by the damper abutting surfaces between the adjacent pair of the platforms.

Abstract: A fan backflow prevention structure includes a frame body, a first static blade assembly and a second static blade assembly. The frame body has a peripheral wall. Two end edges of the peripheral wall are respectively formed as an air inlet and as an air outlet. A base seat is correspondingly disposed at the air outlet. The first static blade assembly extends outward from the base seat and includes multiple static blade sections. Two ends of each static blade section are respectively connected with the base seat and the peripheral wall. The second static blade assembly is disposed at the air outlet and rotatably coupled to the base seat. The second static blade assembly has a connecting section and multiple stop sections extending outward from the connecting section.

Abstract: A blade track for a gas turbine engine includes segments and joints that couple the segments together. Each segment extends part-way around a central axis of the engine and the joints couple together adjacent segments to form a full hoop.