Abstract: Embodiments of the application disclose a fan and a mold for making a fan blade structure for the fan. An embodiment of the fan comprises a fan blade structure and the fan blade structure comprises a mounting ring and a plurality of fan blades provided on the mounting ring, wherein mounting ring and the fan blades are integrally formed. The mold comprises a mounting ring and a plurality of fan blades provided on the mounting ring, the mold comprising a cavity having a ring-shaped channel configured for forming the mounting ring and a plurality of fan blade channels configured for forming the plurality of fan blades, in order to integrally form the fan blade structure.

Abstract: This disclosure describes a removable flow control device which may be used in a rotating flow supply system in a gas turbine to optimize coolant flow by improving flow dynamics, reducing leakage of coolant, and reducing pressure loss in the flow supply system. The flow control device may be coupled to a blade and rotor assembly and may include a flow modifier for directing flow through a junction at which cooling channels intersect and are in fluid communication. The device may direct, control, meter, channel, or otherwise modify the flow of coolant, and may be coupled to the blade and rotor assembly independently of other blade components so that coupling and decoupling the flow control device does not require modification or de-stacking of the rotor assembly.

Abstract: A gas turbine engine comprises a main compressor section having a high pressure compressor with a downstream discharge, and more upstream locations. A turbine section has a high pressure turbine. A tap taps air from at least one of the more upstream locations in the compressor section, passes the tapped air through a heat exchanger and then to a cooling compressor. The cooling compressor compresses air downstream of the heat exchanger, and delivers air into the high pressure turbine. A core housing has an outer peripheral surface and a fan housing defining an inner peripheral surface. At least one bifurcation duct extends between the outer peripheral surface to the inner peripheral surface. The heat exchanger is received within the at least one bifurcation duct.

Abstract: An object is to provide a variable-geometry exhaust turbine whereby it is possible to prevent deformation and damage to a nozzle support under a high temperature. A variable-geometry exhaust turbine includes: a nozzle mount, a nozzle support including a first end portion joined to the first surface of the nozzle mount, a nozzle plate including the first surface joined to the second end portion of the nozzle support 6 and supported so as to face the nozzle mount at a distance, and the opposite second surface facing an exhaust—as channel through which exhaust gas flows, and a plurality of nozzle vanes supported rotatably between the nozzle mount and the nozzle plate. The nozzle support is capable of tilting along a radial direction so as to absorb a relative displacement in the radial direction between the nozzle mount and the nozzle plate due to thermal expansion.

Abstract: Disclosed is a gas turbine engine including a compressor section and a turbine section. The gas turbine engine includes a gas turbine engine component having a first wall providing an outer surface of the gas turbine engine component and a second wall spaced-apart from the first wall. The first wall is a gas-path wall exposed to a core flow path of the gas turbine engine. The second wall is a non-gas-path wall. A cooling passageway is provided between the second wall and the first wall. The second wall has a trip strip provided thereon.

Abstract: A turbine rotor blade includes a tip portion having a pressure tip wall and a suction tip wall, a tip leading edge and a tip trailing edge. Also included is a squealer cavity at least partially defined by the pressure tip wall and the suction tip wall. Further included is at least one hole defined by the suction tip wall, the at least one hole configured to bleed a cooling flow out of the squealer cavity into a hot gas path to reduce pressure within the squealer cavity. Yet further included is a main body having a suction side wall and a pressure side wall each extending from a root portion of the turbine rotor blade to the tip portion.

Abstract: A fan impeller includes a plurality of fan blade assembly members, each one of the fan blade assembly members respectively includes a metal ring bracket and a plurality of metal blades, one end of each one of the metal blades is respectively connected to the corresponding metal ring bracket and the plurality of metal blades of each one of the fan blade assembly members arranged radially to circumference the corresponding metal ring bracket. The metal ring brackets are configured to stack with each other and the metal blades are arranged in a radial centric row, a width of at least one portion of each one of the metal blades is not smaller than a distance between any two adjacent metal blades along a fan impeller circumferential direction. Accordingly, metal blades of a greater width can be densely arranged on the fan impeller.

Abstract: A cross-flow fan includes an impeller and a shaft. The impeller includes a plurality of support plates and a plurality of blades. The blades are different in a blade cross section orthogonal to an impeller rotational axis, and each have a plurality of regions arranged in a direction of the impeller rotational axis and a coupling portion formed so as to couple the plurality of regions to each other. A rib is formed on the coupling portion, or formed in a region adjacent to the coupling portion within a range separated away from the coupling portion by up to 20% of a length of the region adjacent to the coupling portion in the rotational axis direction.

Abstract: A fan comprising: (a) an impeller, (b) a motor connected to the impeller so that during operation the motor drives the impeller to move a fluid; (c) an instrumentation assembly that includes one or more components for controlling one or more operations of the fan; (d) an interface in communication with the instrumentation assembly; wherein the interface is configured so that one or more programs, one or more signals, or both can be input into the fan after a final assembly of the fan so that the fan can be configured to perform a desired function at the time of installation into a final product, reconfigured for a different purpose than originally programmed, or both.

Abstract: A system includes, in one example, a shroud configured to circumscribe a plurality of rotor blades of a gas rotor engine, and at least one rub button including a head portion having a height configured to extend into a flow path region of the shroud along a central axis of the rub button that extends radially into the flow path region. The head portion includes a profile, orthogonal to the central axis, that varies according to a defined function of the height of the head portion.

Abstract: Multiple guide claws are formed integrally on a right side surface of a first nozzle ring of a variable nozzle unit and radially at intervals in a circumferential direction. Each guide claw has a guide groove with a U-shaped cross section, which is formed by lathe turning. A projecting portion is formed at an inner edge portion on the right side surface of the first nozzle ring. The projecting portion is formed on base portions of the multiple guide claws.

Abstract: A wind turbine blade is described wherein at least on planar member is provided on the blade surface, where the planar member is arranged such that it extends at an angle to the chord of the blade. The planar member acts to re-direct airflow over the blade, to improve wind turbine performance. The planar member may be a stall fence provided towards the blade root end, further acting to divert airflow towards the root end of the blade to prevent separation of attached airflow. Additionally or alternatively, the planar member may be a flow diverter provided towards the blade tip end, to increase airflow in the tip region for increased performance and/or to disrupt the formation of tip vortices.

Abstract: A pivot for an air propeller blade, the pivot including a rotary support for mounting radially on a propeller hub while being suitable for pivoting about a pivot axis; and a blade support including a housing for receiving a blade root and at least one arm extending laterally relative to the pivot axis and carrying a flyweight forming a counterweight; the arm and its flyweight presenting the general geometrical shape of a spherical cap.

Abstract: A fan module comprises a frame and at least one filling component. The frame comprises a base plate and a plurality of partition plates. A plurality of air flow channels are formed by the base plate and the plurality of partition plates. Each partition plate has a first fixing slot, a second fixing slot, a third fixing slot and a fourth fixing slot that are located at a side away from the base plate in sequence. The first fixing slot has a first width. The second fixing slot has a second width. The third fixing slot has a third width, and the fourth fixing slot has a fourth width. The filling component is filled in the air flow channels. The first width is the same as the third width. The first width, the second width and the fourth width are different from one another.

Abstract: A cooling system for a turbomachine includes a vane having an outer diameter platform at one end and an inner diameter platform at another end opposite the outer diameter platform. The outer diameter platform includes outer diameter attachment structure operative to mount the vane to an outer diameter stationary structure. The inner diameter platform is operative to be disposed on an inner diameter stationary structure. The cooling system also includes an airfoil disposed between the outer diameter platform and the inner diameter platform and defining a first cross-passage. The first cross-passage defines a first outer diameter opening in the outer diameter platform. The first cross-passage defines a first inner diameter opening in the inner diameter platform such that a first leakage flow can pass through the vane from the inner diameter platform, through the airfoil, to the outer diameter platform, and into an outer diameter leakage path of the vane.

Abstract: A fluid seal structure of a heat engine including a steam turbine includes an inner case which houses a turbine rotor rotatably inside, an outer case which houses the inner case and forms a space through which a fluid can flow between the outer case and an exterior surface of the inner case, a protruding portion protruding into the space from one of the exterior surface of the inner case or an interior surface of the outer case, and a partitioning plate extending into the space from the other one of the exterior surface or the interior surface and being formed annularly in a circumferential direction of the surface. The partitioning plate partitions the space into first and second space sections, and is flexurally deformable in the axial direction of the turbine rotor by an internal fluid pressure difference between the first and second space sections.

Abstract: An example method of controlling a flow enhancement device includes providing a flow enhancement device that is configured stabilize a flow of air near a nacelle. The flow enhancement device has a first setting and a second setting that provides more stabilization than the first setting. The method includes monitoring parameters of a turbomachine to determine the stability of the flow of air near the nacelle. The method also adjusts the flow enhancement device between the first setting and the second setting based on the monitoring.

Abstract: A turbo-molecular pump comprises: a case having a suction port and a flange; a rotor assembly housed inside the case, the rotor assembly having a shaft and a rotor integrated with the shaft with a fastening bolt, the rotor having a plurality of rotor blades formed thereon; a plurality of stator blades housed inside the case and arranged to face the rotor blades; and a plurality of spacers stacked along a peripheral surface of the case, the spacer fixing the stator blades. An anti-corrosion treatment is applied to a gas contacting section in a component that is provided on an evacuation upstream side with respect to an evacuation downstream side end of the first rotor blade from the evacuation upstream side and made of an alloy containing Fe or Cr.

Abstract: A centrifugal fan assembly includes an impeller assembly which has a fixed stator and a rotating impeller having a base plate, a hub connected to the base plate a plurality of backward curved first blades, and a plurality of backward curved second blades. Each first blade has an inner end which is connected to the hub. Each second blade has an inner end which is spaced apart from the hub and which tapers to a point. The first and second blades have different profiles or shapes. The axial length of the first blades is different from the axial length of the second blades. Each second blade forms an apex which projects axially from the base plate.

Abstract: A turbine wheel (4) having a hub (29); a multiplicity of turbine wheel blades (30) arranged around the hub (29); a turbine wheel back wall (31) which is arranged on the hub (29) adjacent to an edge region (32) of the turbine wheel blades (30); wherein the wall thickness (W) of the turbine wheel (4) back wall is reduced in regions.