Abstract: An impeller attach mechanism for a turbocharger including a stud extending from a central bore of a compressor impeller toward a turbine wheel, the stud having a first threaded region and a second threaded region; a shaft coupled to the turbine wheel and extending toward the compressor impeller, the shaft having a leading portion, the leading portion having a threaded interior configured to engage the second threaded region of the stud; and an insert having an internal portion and an external portion, the internal portion having a threaded external surface to engage the compressor impeller, the internal portion having a threaded internal surface to engage the first threaded region of the stud, the external portion configured to surround the leading portion of the shaft.

Abstract: Methods, apparatus, and systems for trapped rotatable weights to improve rotor balance are disclosed. An example apparatus includes a lock nut; a rotor assembly; a channel defined by the lock nut and the rotor assembly, the channel wrapped circumferentially around a geometric center of the rotor assembly; and a weight trapped within the channel.

Abstract: A gas turbine engine actuation system includes a gas turbine engine, an actuation device, an actuator, and a power source. The gas turbine engine includes a compressor section, a combustion section, a turbine section, and a rotating shaft. The actuation device is operable with the compressor section, combustion section, turbine section, or a combination thereof. The actuator is operationally coupled to the actuation device and includes an electric actuator configured to convert electrical current into mechanical power. The power source is configured to supply electrical current to the actuator, alone or in tandem with a hydraulic actuator.

Abstract: A fan case assembly adapted for use with a gas turbine engine includes a fan track liner and an annular case. The fan track liner extends circumferentially at least partway about a central axis of the gas turbine engine. The annular case is configured to support the fan track liner at a radial position relative to the central axis. The fan case assembly further includes an air recirculation duct configured to redirect air around the fan track liner.

Abstract: A compressor section for a gas turbine engine according to an example of the present disclosure includes, among other things, a low pressure compressor including a plurality of rotor blades arranged about an axis, a high pressure compressor, and a core flowpath passing through the low pressure compressor. The core flowpath at the low pressure compressor defines an inner diameter and an outer diameter relative to the axis. The outer diameter has a slope angle relative to the axis.

Abstract: An airfoil includes an airfoil section that has an airfoil wall that defines leading and trailing ends and first and second sides that join the leading and trailing ends. The first and second sides span in a longitudinal direction between first and second ends. The airfoil wall circumscribes an internal core cavity. A platform is attached with the first end of the airfoil wall. The platform includes an opening that opens into the internal core cavity and a land region that circumscribes the opening. A baffle is formed of a tube and an attachment portion. The tube extends in the internal core cavity and the attachment portion has a flange ring that is affixed to the platform at the land region.

Abstract: A shroud segment including a forward radial wall, an aft radial wall and at least one interlocking subcomponent. The forward radial wall, an aft radial wall and the at least one interlocking subcomponent are each formed of a ceramic matrix composite (CMC) including reinforcing fibers embedded in a matrix. The shroud segment further including an interlocking mechanical joint joining each of the forward radial wall and the aft radial wall to the at least one interlocking subcomponent. Methods are also provided for joining the forward radial wall and the aft radial wall to the at least one interlocking subcomponent using an interlocking mechanical joint.

Abstract: A turbine for a turbo-machine is proposed in which, at a gas inlet for a turbine wheel, vanes extend from a nozzle ring though slots in a shroud. The nozzle ring and shroud are relatively rotatable about a rotational axis of the turbine by at least 0.1 degrees. In use, the nozzle ring and shroud are relatively rotated to bring one side of the vane into close contact with one surface of the slot, to inhibit leakage of gas between the vane and the slot surface. For this purpose the respective surfaces of the nozzle and slot can be configured to closely conform to each other. If there is differential thermal expansion of the shroud and nozzle ring, the nozzle ring and shroud can relatively rotate, to withdraw the vane from the edge of the slot to relieve the pressure between them.

Abstract: Methods, apparatus, systems, and articles of manufacture are disclosed to adjust a pitch axis of a blade of an engine. An example blade apparatus includes: a hub to facilitate movement of blades in an engine, the engine having a radial center line; and a trunnion connected to the hub. The example trunnion includes a slot to accommodate a first blade, and at least one of the trunnion or the first blade is positioned with at least one of a tilt or a lean with respect to the radial center line to form a pitch axis offset from the radial center line such that the pitch axis is not parallel to or co-linear with the radial center line. The example hub is to rotate the first blade about the pitch axis.

Abstract: In some aspects, the techniques described herein relate to a refrigerant compressor, including: a stator; a rotor configured to rotate with respect to the stator; and at least one step seal between the rotor and the stator, wherein the step seal includes a first tooth and a second tooth extending from the rotor toward the stator, wherein a downstream surface of the first tooth and an upstream surface of the second tooth are arranged at an angle relative to one another, wherein the angle is less than 90°.

Abstract: A component assembly for a gas turbine engine defining a core air flowpath is provided. The component assembly includes an outer shell comprising a first array of integral outer shell airfoils that extend inward from an outer shell periphery; and an inner shell comprising a second array of integral inner shell airfoils that extend outward from an inner shell periphery, wherein the outer shell and the inner shell are one or both of translatable and rotatable relative to one another between a first position and a second position.

Abstract: A construction machine includes a centrifugal fan, and a bell mouth arranged on the suction side of the centrifugal fan. The centrifugal fan has a rotatable hub, an annular shroud arranged so as to face the hub and having a suction port, and multiple blades provided between the hub and the shroud. An outlet of the bell mouth is arranged on the radially inner side of the suction port of the shroud. Each blade is formed such that: a leading edge has a convex shape protruding toward a suction surface relative to a line segment linking a connection of the leading edge with the hub and a connection of the leading edge with the shroud; and a vertex of the convex shape of the leading edge is positioned on a radially inner side of a wall surface of the outlet of the bell mouth when the suction side of the centrifugal fan is seen in an axis direction.

Abstract: A compact respiratory therapy device suitable for use by a patient during sleep to provide respiratory pressure therapy such as at a pressure between 4-30 cmH2O includes a housing, an inlet, an outlet, a motor including a rotor, and an impeller configured to be rotated by the rotor to deliver a flow of air from the inlet toward the outlet. The impeller includes a set of impeller blades, each impeller blade comprising a leading edge and a trailing edge; and a first shroud and a second shroud, each shroud at least partly defining a flow passage through the impeller, the first shroud comprising a wall defining a periphery of an impeller inlet. The compact respiratory therapy device is configured to deliver the flow of air from the outlet for delivery to the patient at a pressure between 4-30 cmH2O at an overall sound power level of less than 50 dB(A) thereby reducing any disturbance to a quality of sleep for the patient. A diameter of the impeller is less than 50 mm.

Abstract: A ducted fan assembly has a central axis, a duct having an outer wall and an inner wall, a fan hub at least partially disposed on the central axis, a plurality of fan blades coupled to the fan hub, and a first stator. The first stator has a first end coupled to the inner wall, a second end coupled to the inner wall, and a hub interface disposed between the first end and the second end, wherein the hub interface is coupled to the fan hub.

Abstract: A shroud assembly including a shroud support and an annular shroud is provided. The shroud assembly includes one or more pins for securing the annular shroud to the shroud support. The pins having a block capable of translating radially to allowing the shroud to expand and contract in the radial direction. A gas turbine engine having a compressor section, a combustion section, a turbine section and a shroud assembly is also provided. The shroud assembly includes one or more pins for securing the continuous shroud to the shroud support. The pins having a block capable of translating radially to allowing the shroud to expand and contract in the radial direction. Methods for assembling a shroud assembly structure in a gas turbine engine are also provided.

Abstract: A gas turbine engine including a frame assembly; a turbine assembly; and a nozzle disposed in the turbine assembly, wherein the nozzle defines an inner end along a radial direction and an outer end along the radial direction, wherein the outer end of the nozzle is supported by the frame assembly, wherein the inner end of the nozzle is supported by the frame assembly, and wherein the inner end of the nozzle is displaceable relative to the frame assembly in at least the radial direction.

Abstract: A rotor for a machine under this disclosure could be said to include a hub having a plurality of blades extending radially outwardly of the hub. At least one of the hub and the plurality of blades is formed of at least two metal materials. The two metal materials are selected to have different thermal expansion coefficients such that the overall rotor will be more resistant to forces it may experience as temperature or speed increases. There are layers of each of the two metal materials, with an intermediate gradient wherein the two materials are mixed. Alternatively, a shape memory alloy may be used. A method is also disclosed.

Abstract: An airflow-doubling vane structure includes an axle, an inner vane unit, and an outer vane unit. The inner vane unit includes a plurality of vanes provided around a center defined by the axle and can be rotated along with the axle. The vanes of the inner vane unit are centrifugal vanes. The outer vane unit includes a plurality of vanes provided around the center defined by the axle and around the inner vane unit and can be rotated along with the axle. The vanes of the outer vane unit are axial-flow vanes and extend a certain radial distance from the vanes of the inner vane unit.

Abstract: A gas turbine engine includes a plurality of fan blades rotatable about an axis, wherein each of the plurality of fan blades includes a leading edge. The gas turbine engine also includes turbine section includes an aft most turbine blade having a trailing edge and a geared architecture driven by the turbine section for rotating the plurality of fan blades about the axis. A center of gravity of the gas turbine engine is located a first axial distance from the trailing edge of the aft most turbine blade that is between about 35% and about 75% of a total length between the leading edge of the plurality of fan blades and the trailing edge of the aft most turbine blade.

Abstract: A bladeless fan with multiple air ducts is disclosed. The bladeless fan has a fan housing, a control system arranged in the fan housing, a blower system connected with the control system, an intermediate air duct communicating with the blower system and a rotation component connected with the control system. The intermediate air duct is provided with a side air duct at its both sides, the rotation component is connected with the side air duct to drive the side air duct to fold and unfold with the intermediate air duct as a center shaft. The side air duct is driven by the rotation component to fold and unfold with the intermediate air duct as a center shaft. The fold and unfold of the side air duct can achieve different effects, satisfy the user's requirement and improve the user experience.