Abstract: A rotational duct blocker for a gas turbine engine includes a duct blocker rotor and a duct blocker stator. The duct blocker rotor includes a plurality of first flow apertures extending axially therethrough, and a plurality of roller elements connected to an inner rotor platform. The first flow apertures are arranged circumferentially around the inner rotor platform. The duct blocker stator includes a plurality of second flow apertures extending axially therethrough, and a roller element track located radially within the inner rotor platform and in rolling contact with the roller elements. The second flow apertures are arranged circumferentially around an inner stator platform that is located axially adjacent to the inner rotor platform. The duct blocker rotor rotates relative to the duct blocker stator to regulate fluid flowing between the first flow apertures and the second flow apertures.

Abstract: A shaft cover support for a gas turbine engine is disclosed. The shaft cover support not only provides enhanced support to a shaft cover of the gas turbine engine, but also includes a cooling fluid chamber for passing fluids from a rotor air cooling supply conduit to an inner ring cooling manifold. As such, the shaft cover support accomplishes in a single component what was only partially accomplished in two components in conventional configurations. The shaft cover support may also provide additional stiffness and reduce interference of the flow from the compressor. In addition, the shaft cover support accommodates a transition section extending between compressor and turbine sections of the engine. The shaft cover support has a radially extending region that is offset from the inlet and outlet that enables the shaft cover support to surround the transition, thereby reducing the overall length of this section of the engine.

Abstract: A bucket assembly is disclosed. The bucket assembly includes an airfoil having a generally aerodynamic contour and defining a tip, and a lower body portion extending generally radially inward from the airfoil. The bucket assembly further includes a tip shroud disposed on the tip of the airfoil and comprising a main body and a rail. The rail includes an exterior surface. The exterior surface defines a microchannel. The bucket assembly further includes a cover layer configured on the exterior surface.

Abstract: A gas turbine component for example a turbine blade or a rotor disk is provided. In order to extend the service life of the corresponding component by reducing the thermally or mechanically induced stress concentration in the direct surroundings of a duct opening onto a surface, at least one groove-like recess is provided near the effective zone of the opening.

Abstract: A multilayer-type fan device has a base, a major blade group and at least one minor blade group. The base is circular and has a top, a bottom, an external surface, an axle hole and at least one inclined plane. The external surface is formed around the base at the bottom of the base. The axle hole is formed through the base from the top to the bottom of the base. The at least one inclined plane is formed on the base between the external surface and the top of the base. The major blade group is mounted on the base and has multiple blades mounted on the external surface of the base at intervals. The at least one minor blade group is mounted on the base and has multiple blades mounted on one of the at least one inclined plane of the base.

Abstract: A welded rotor, a steam turbine having a welded rotor, and a method of producing a welded rotor are disclosed. The welded rotor includes a high pressure section and an intermediate pressure section. The high pressure section includes a high temperature material section joined to a low temperature material section.

Abstract: A rotor disk for a gas turbine engine includes a CMC hub and a rail integrated with the CMC hub opposite the multiple of CMC airfoils, the rail defines a rail platform section that tapers to a rail inner bore.

Abstract: An assembly for reducing compressor noise includes a compressor and an acoustic shield. The compressor has a rotor with a plurality of blades mounted thereto. Additionally, the compressor has one or more bleed slots therein. The acoustic shield is disposed adjacent to the one more bleed slots and spaced at a distance therefrom.

Abstract: A vane structure for a gas turbine engine according includes a multiple of CMC airfoil sections integrated between a CMC outer ring and a CMC inner ring.

Abstract: A turbomachine is disclosed that has a main fluid flowpath extending axially along the turbomachine with a rotating shaft partly enclosed in a casing, wherein the rotating shaft and casing are moveable relative to each other and define a clearance opening about the rotating shaft, whereby the main fluid flowpath fluidly communicates with an outside region, and an annular seal body defining a fluid passage having a primary fluid inlet configured to receive a pressurized fluid, a fluid outlet disposed proximate to the clearance opening, and a convergent chamber interposed therebetween, wherein the convergent chamber is configured to accelerate the pressurized fluid out of the fluid outlet so as to create a local reduced pressure at the clearance opening.

Abstract: A clearance control arrangement includes first and second components defining a clearance therebetween. The first component includes a surface portion having at least a layer of material that changes thickness when actuated. The clearance control arrangement also includes an actuator to actuate the layer of material.

Abstract: An exhaust gas turbocharger includes a waste gate valve and an adjusting device for adjusting the waste gate valve. The adjusting device is connected to the waste gate valve and disposed on a housing of the exhaust gas turbocharger. The adjusting device is fastened to the housing of the exhaust gas turbocharger via an adjusting template.

Abstract: A turbo-machine with blade wheels, comprises a body, a rotor which is held in a rotatable manner by the body, at least two rotatably arranged blades which are distributed uniformly along a circular line of the rotor and which are mounted with their axis parallel to the axis of the rotor, transmission members between each axis of the blade and a sleeve which is rotatable on the shaft of the blade wheel. The first rotor is assigned a second rotor which is held in a rotatable manner by the first rotor, wherein the second rotor comprises at least two rotatably arranged blades which are distributed uniformly along a circular line of the rotor and which are mounted with their axis parallel to the rotor, transmission members between each axis of the blade and the sleeve which is rotatable on the shaft of the rotor.

Abstract: A centrifugal impeller includes a body of antistatic plastic and a back plate made of metal, preferably aluminum. The back plate is fixed to the body is such a way that the back plate can not make accidental contact with a volute of a blower in which the impeller is deployed.

Abstract: A turbine wheel including: a plurality of first and second blades, at least one of the first blades being adjacent to at least one of the second blades; a disk presenting an axis of rotation and a periphery having the blades mounted thereat, each of the blades including a head solid with a root engaged in a housing that opens to the periphery of the disk, each of the blades including a keying mechanism including a respective shelf arranged between the head and the root of the blade, the shelves of the first blades presenting an azimuth length different from the azimuth length of the shelves of the second blades; and a damper device arranged at least between the adjacent blades, the damper device being arranged between the shelves of the blades and the periphery of the disk.

Abstract: A large span industrial engine turbine rotor blade with a radial extending cooling air passage having a series of turbulence air mixers along the passage, where the turbulence mixers each have an inlet end and a curved and tapered surface such that cooling air is drawn into the inlet end of the mixer and then discharged from the curved and tapered surface into a middle of the passage. The cooling air flows through the passage along a series of these turbulence mixers from one mixer to another mixer along the spanwise length of the passage.

Abstract: The invention concerns a propeller device with a flow profile body assigned to a propeller and a multiple eccentric arrangement functionally coupled to the flow profile body, which has two eccentric components coupled with one another and able to rotate in opposite directions, and which is configured so as to convert a common rotational movement of the eccentric components in opposite directions into an oscillating movement of the flow profile body along a movement path between two end positions, and vice versa. Furthermore the invention concerns a vehicle drive unit with a propeller device, and also an energy conversion unit with a propeller device.

Abstract: A centrifugal multiblade fan includes a rotatable shaft, blades, a side shroud, and a main shroud. A front edge has a shape inclined radially outward in a direction from the main shroud toward the side shroud. When viewed from an axial direction, a corner part on a positive pressure surface-side is located on a tangential line of a positive pressure surface reference curve at a positive pressure surface side reference corner part, and when viewed from the axial direction, a curvature radius of a negative pressure surface becomes larger in a direction from the side shroud toward the main shroud.

Abstract: An interstage seal is provided for installation between forward and aft stage discs of a turbine section of a gas turbine engine. The seal has a forward annular portion, which extends forward to contribute to an air seal at the outer periphery of the forward stage disc, and an aft annular portion, which extends rearward to contribute to an air seal at the outer periphery of the aft stage disc. The seal has a peripheral slot into which static vane inner rails are loadable. The seal includes a first component, which provides the forward annular portion, and a second component, which provides the aft annular portion. The second component is separably connectable to the first component such that the first and second components, when connected, cooperate to form the peripheral slot. Loading the static vane inner rails into the slot prevents the second component separating from the first component.

Abstract: A rotating fan with a transmission mechanism and a blade deployment mechanism. In an energized state, an electromagnetic coil generates a magnetic force that causes a clutch plate to be in contact with a contact surface, thereby engaging a planetary gear system. In a de-energized state, the clutch plate is not in contact with the contact surface, thereby disengaging the planetary gear system. In a deployed configuration, a drive link activated by the planetary gear system rotates a blade link to cause a fan blade to pivot. The result is that the fan blade tip is farther from the motor shaft than the fan blade root. In a retracted configuration, the drive link rotates the blade link to cause the fan blade to pivot and retract. The result is that the fan blade tip is equidistant from the motor shaft as the fan blade root.