Abstract: The subject of the invention is a propeller blade that has minimal blade tip loss, has a pressure side, opposite to that a suction side, a blade root that can be attached to the propeller and opposite to the blade root a blade tip, where the pressure side is attached to the suction side with a slot that has an inlet opening on the pressure side and an outlet opening on the suction side, and the slot has a pressure equalizing element in it. Furthermore, the subject of the invention is a propeller that can be used for airplanes, helicopters, horizontal-axis wind turbines, fans and drones and that has at least one propeller blade which is designed according to the first aspect of the invention.

Abstract: The invention relates to a nubomachine with a longitudinal axis, comprising two, respectively upstream (122) and downstream, coaxial outer propellers (122), characterised in that at least some of the blades (148) of the upstream propeller (122) comprise at least one internal air circulation chimney (150) that communicates with air-bleeding openings (152) in tire boundary layers of the blades (148), and communicates with air outflow openings (158) on the radially outer end thereof, the air-bleeding openings (152) leading to opening inlets (152a) on tire passive surfaces (156) of the blades (148), the inlets (152a) of the air-bleeding openings being radially arranged in an area (H1) contained between 10% and 45% of the radial dimension (H2) of the blades (148), measured above turd from the radial height of the blades for which the tangent of the leading edge (138) of the blades is orthogonal to the longitudinal axis, and the inlets (152a) of the air bleeding openings being arranged in an area contained between

Abstract: A wind turbine system comprising a nacelle mounted on a tower, a rotor having a plurality of blades and a boundary layer control system configured to control airflow through blade surface openings in each of the blades. The wind turbine system includes a control system configured to perform at least one of the following: to monitor an operational speed parameter of the wind turbine, and to activate the boundary layer control system if it is determined that the 1 operational speed parameter exceeds a predetermined speed parameter threshold; to monitor tower motion and to activate the boundary layer control system based on a determination of excessive tower motion; to monitor for a wind turbine shutdown condition, and to activate the boundary layer control system if it is determined that a wind turbine shutdown condition has been identified; and to monitor the aerodynamic loads on the blades, and to activate the boundary layer control system also based on a determination of excessive blade loads.

Abstract: Systems and methods include providing an aircraft with a fuselage, a tail boom or empennage extending from the fuselage, a main rotor, a tail rotor, and at least one counter torque device. The counter torque device provides counter torque to the fuselage to prevent rotation of fuselage when the main rotor is operated, particularly in right sideward flight (RSF) for conventional helicopters with a counter-clockwise rotating (when viewed from above the helicopter) main rotor.

Abstract: A casting mold to cast a TiAl alloy includes a casting mold body formed into a bottomed shape and provided with a cavity. The casting mold body includes a reaction-resistant layer provided on the cavity side, formed from a refractory material containing at least one of cerium oxide, yttrium oxide, and zirconium oxide and a back-up layer formed on the reaction-resistant layer. The back-up layer includes a weakening layer formed from a refractory material including a silica material in a range from 80% by mass to 100% by mass inclusive, the silica material containing cristobalite in a range from 26% by mass to 34% by mass inclusive and the rest being fused silica, the weakening layer being designed to reduce casting mold strength and a shape-retention layer formed from a refractory material.

Abstract: A mixing apparatus includes a first shaft, second shaft, and third shaft. The first shaft of a first length has a first end and a second end. The second shaft of a second length is fixed with the second end of the first shaft at a midpoint of the second shaft. The third shaft of a third length is fixed with the first shaft proximate to the second end of the first shaft from one end. The first, second, and third longitudinal axis of the first, second, and third shafts, respectively, are mutually perpendicular to each other. Each of the two ends of the second shaft and other end of the third shaft are fixed with a circular member with a cavity therein such that a circular axis of the first and second circular members fixed at two ends of the second member which are parallel to third longitudinal axis.

Abstract: A modular gas-heat anti-icing method as well as a device for high-power wind turbine blades, wherein a modular heating system is provided on the blade root, a ventilation duct is provided inside the blade, a wind deflector is provided at the end of the ventilation duct, which divides the front edge of the blade into two parts, so that the hot air in the ventilation duct is only to be conducted to the blade tip and then circulates into the blade root via the rear edge of the blade, enabling the hot air to circulate inside the blade and form a “blade root to blade tip to blade root” closed loop, so that the purpose of heating the front edge of the blade is achieved, and it is ensured that the whole blade does not ice by preventing the front edge of the blade from icing.

Abstract: A blade includes a blade body having a surface and a hole extending through the surface of the blade body. The hole defines a hole axis and a plane perpendicular to the hole axis. The hole has an elongated hole perimeter within the plane. The hole perimeter includes a plurality of non-linear perimeter sections to minimize stress concentration around the elongated hole perimeter while maximizing the usable opening area. A rotor system includes a rotor hub and a blade as recited above. The blade extends radially outward from the rotor hub. The blade defines a root end proximate to the rotor hub, a tip end opposite the root end.

Abstract: A cooling fan structure with rotational cylindrical fan vanes includes a rotary body and multiple rotational cylindrical bodies. The rotary body includes a rotor assembly and a stator assembly corresponding to the rotor assembly for driving the rotor assembly to rotate. The rotor assembly includes a hub. The hub has a top section and a circumferential section. The rotational cylindrical bodies are rotatably disposed on the top section or the circumferential section of the hub. When the rotary body rotates, the rotational cylindrical bodies are driven by the rotary body to self-rotate.

Abstract: In a radial compressor stage for a radial compressor having a rotor side, the radial compressor stage includes a stator; and an impeller configured to rotate relative to the stator. The impeller has multiple impeller blades on the rotor side. Each of the multiple impeller blades has: a flow inlet edge, a flow outlet edge, a suction side extending between the flow inlet edge and the flow outlet edge, a pressure side, and an outer surface facing the stator. At least one groove is arranged in the outer surface of at least one of the multiple impeller blades, the at least one groove being bounded by a longitudinal web both on the suction side and on the pressure side. Each of the longitudinal webs forms a sealing tip of the respective impeller blade towards the stator.

Abstract: A fluid interface device, such as an airfoil assembly, can include a device structure and at least one movable band oriented such that the band moves in a direction of fluid flow. The at least one movable band can be supported on the device structure such that an outer surface of the movable band is exposed along the device structure and is capable of movement relative thereto such that a relative velocity can be maintained between the outer surface and the device structure. The fluid interface device can also include an edge extension disposed along the leading edge of the device structure. An airplane, a wind turbine and a method are also included.

Abstract: A rotating circular airfoil system that includes a disc body that has an airfoil shape in cross section. The air foil shape has an angle of attack that is symmetrical. The disc body's includes a circular inner edge which forms a circular center opening and the airfoil shape's leading edge. The disc body also includes an outer edge that forms the airfoil shape's trailing edge. Intersecting ribs extend across the center opening and include a shaft opening that attaches to a rotating shaft. Formed on the top and bottom surfaces of the disc body are evenly spaced apart, extending fins. The fins extend continuously from the inner edge to the outer edge. When a rotating shaft is inserted into the shaft opening and imparts sufficient rotation to the disc body, the fins contact the air forcing it to flow along disc body's top and bottom surfaces and creating a lifting force.

Abstract: A turbine airfoil comprises a suction sidewall, a pressure sidewall, a tip wall, and a tip leakage control channel. Each sidewall extends spanwise from an airfoil base and chordwise between a leading edge and a trailing edge. The tip wall extends chordwise from the leading edge to the trailing edge and joins respective outer spanwise ends of the suction and pressure sidewalls. The tip leakage control channel has an inlet and an outlet recessed into an outer surface of the tip wall. An inlet of the channel begins proximate a junction of the airfoil pressure sidewall and the tip wall. An outlet of the channel terminates at a recessed portion of the junction of the tip wall and the suction sidewall.

Abstract: A wind turbine blade forming a root at an inner end, a tip at an outer end, a plurality of power sections intermediate the root and the tip, and a plurality of aerodynamic section dividers located intermediate each of the other sections. The aerodynamic section dividers are configured to aerodynamically isolate their adjoining sections to limit the lateral flow of air between them while in use on the wind turbine. The blade has a low aspect ratio and is operated at a high advance rate. The aerodynamic section dividers are close enough together to soften the stall characteristics of the blade, and thus the blade can be operated at high angles of attack.

Abstract: A rotor blade for a rotary wing aircraft includes a component bay located substantially enclosed in the rotor blade and one or more components positioned in the component bay. An airflow is located at the component bay and an airflow outlet is located at the component bay radially outboard of the airflow inlet. The airflow inlet and airflow outlet allow a continuous airflow through the component bay via centrifugal forces of rotation of the rotor blade, the continuous airflow cooling the one or more components disposed at the component bay.

Abstract: A propulsion device using fluid flow quickly discharges the vortex flow generated on an upper surface of the propulsion device to the outside to improve the propulsion and thrust of transportation means provided with the propulsion device. For this purpose, the propulsion device includes a fluid storage unit in which a downwardly curved fluid storage surface is formed between a first inlet line and a first outlet line such that a fluid storage space is formed on the fluid storage surface. A fluid flow unit in which a downwardly curved fluid flow surface is formed between a second inlet line and a second outlet line which are outwardly and backwardly inclined such that a fluid flow space is formed on the fluid flow surface. The-fluid flow surface adjacent to the second outlet line becomes gradually flattened as it extends outwardly.

Abstract: Embodiments of a gas turbine engine rotor including stress relief features are provided, as are embodiments of method for producing a gas turbine engine rotor. In one embodiment, the method includes producing a hub preform in which a plurality of elongated sacrificial cores are embedded. Blades are attached to an outer circumference of the hub preform by, for example, bonding a blade ring to the outer circumference of the preform. The blades are spaced about the rotational axis of the gas turbine engine rotor and circumferentially interspersed with the plurality of elongated sacrificial cores. The plurality of elongated sacrificial cores are then removed from the hub preform to yield a plurality of stress distribution tunnels extending in the hub preform.

Abstract: A blade retention disk includes, on its external surface, a peripheral annular groove configured to receive a plurality of blade roots of the hammer attachment type, the peripheral annular groove including a loading orifice intended for the introduction of blade roots inside the peripheral annular groove. The retention disk also includes: a crown covering the peripheral annular groove; a crown centering device to center the crown, the crown centering device and the crown forming an air supply enclosure from the bottom of the peripheral annular groove; at least one orifice opening in the air supply enclosure, the orifice being configured to introduce cooling air into the air supply enclosure. The blade retention disk finds a direct application in the field of low pressure turbines for aircraft turbine engines.

Abstract: An airfoil active bleed system and related method. A housing includes an induction wall, an exhaust wall having one or more exhaust ports, and a chamber between the induction and exhaust walls. Zero-net-mass-flux actuators are located in the chamber and configured and positioned to collectively induct fluid through the induction wall and selectively exhaust fluid through the exhaust port(s).

Abstract: A low RPM permanent magnet generator mounted over the exhaust port of a HVAC condenser provides a direct drive generator that allows low cogging and low startup resistance to effectively produce electricity at low wind speeds.

Abstract: This wheel comprises a plurality of vanes (2) arranged on a crown (3) and is equipped with a tip-forming member (10) attached to a central region (32) of the crown or hub of the wheel (1), radially inside the vanes (2), the crown defining a wet surface (31) for guiding a flow (E) passing between the vanes. The tip-forming member (10) is provided with at least one opening (121) for diverting a fraction (E1) of the flow towards the internal volume (V10) of this member. This member comprises a frustoconical annular skirt (11) and at least one fin (15) arranged in its internal volume (V10) and able to modify the path of the flow fraction (E1) entering this volume through the opening (121). This fin (15) extends as far as the edge (112) of the skirt (11) which defines an outlet opening (14) of the member (10) for the flow fraction (E1).

Abstract: A mixing apparatus has a shaft, at least one arm radiating outwardly of the shaft, and a mixing element affixed to the arm away from the shaft. The mixing element has a generally frustoconical member with a wide opening at an end thereof and a narrow opening at an opposite end thereof. The mixing element also includes a throat section of a generally constant diameter connected to the narrow opening of the frustoconical member and a diffuser section having an end affixed to an end of the throat section opposite the frustoconical member. The mixing elements have a longitudinal axis extending at an acute angle to horizontal. A motor is cooperative with the shaft so as to rotate the shaft. Each of the mixing elements includes a Venturi.

Abstract: According to one embodiment of the present invention, a rotating blade, having a collision face that collides with fluid and is rotated by the flow of said fluid, has at least one flow path that has been caved in from said colliding face; said flow path is located forward with respect to said rotation direction so that it is located in the rear with respect to the inlet wherein said flow is introduced and said rotation direction, and it has an outlet from which said fluid exits. Here, the cross-sectional area of said inlet may be greater than the cross-sectional area of said outlet. In addition, the cross-sectional area of said inlet may gradually decrease toward said outlet.

Abstract: A high efficiency, adaptive control, compound ducted wind turbine capable of providing higher efficiency in energy extraction from a fluid. Performance of efficiency expressed as coefficient of performance (Cp) in accordance with the Lanchester-Betz-Joukowski limits is sustainable and significantly higher than an un-ducted, mono-propeller wind turbine of comparable diameter. Also an active circulation control wing technology is disclosed for increasing efficiency and performance and which is applicable to both wind and water turbines.

Abstract: A fan-turbine rotor assembly for a tip turbine engine includes a multiple of fan blades, which include an inducer section, a hollow fan blade section and a diffuser section. The hollow fan blade section defines an airflow passage. The core airflow is turned, spread and split toward opposite ends of the diffuser section by a multiple of internal turning vanes. The airflow streams are then further turned by discharge turning vanes before discharge from a diffuser discharge outlet. Along with turning and splitting the core airflow, the fan blade profile balances the mass of the diffuser section such that the center of mass thereof is over the hollow airfoil section structure.

Abstract: The strut is for use in a gas turbine engine has body, typically having an airfoil shape, having a leading edge and a trailing edge. The leading edge has at least one gas inlet in direct fluid communication with at least one outlet located in the trailing edge through which gas may be redirected from the leading edge to the trailing edge through the strut for injection back into a wake region downstream of the strut.

Abstract: A rotor blade for a gas turbine engine, comprising an aerofoil having pressure and suction surfaces, leading and trailing edges, and an array of passages at a tip region of the aerofoil. The passages extend from the pressure surface to the suction surface of the aerofoil and are disposed so that the array creates, in operation, a planar jet of gas issuing from the suction surface. The jet is inclined outwardly from the suction surface and towards the tip, and in the direction from the leading edge to the trailing edge. The jet inhibits migration away from the suction surface of a clearance vortex formed by leakage of air over the tip of the rotor blade.

Abstract: Various embodiments include a steam turbine nozzle and turbomachinery including such a nozzle. In various particular embodiments, a steam turbine nozzle includes: a body having: a first sidewall and a second sidewall opposite the first sidewall; a pressure side and a suction side each extending between the first sidewall and the second sidewall; and a leading edge section at a first junction of the pressure side and the suction side, and a trailing edge section at a second junction of the pressure side and the suction side; and a bypass fluid conduit including: a channel having an opening to at least one of the first sidewall or the second sidewall; and an outlet passageway fluidly connected with the channel between the first sidewall and the second sidewall, the outlet passageway including a first opening on at least one of the pressure side of the body, the suction side of the body or the trailing edge section.

Abstract: The invention comprises a turbulence sensor and sensor system for determining the condition of a wind turbine blade. A turbulence sensor comprises a sensor membrane provided in the surface of a wind turbine blade. A light source and light detector provided in a sensor cavity in the blade illuminate the sensor membrane and detect the light reflected back. The reflected light is mixed with non-reflected light to give an interference pattern indicative of the quality of the airflow, whether it is laminar or turbulent. The turbulence sensor can be used in a sensor system for detecting the accumulation of unwanted matter, such as dirt or ice, on the blade.

Abstract: A passive thrust enhancement system having a propeller, which includes a propeller hub, a first propeller blade, a second propeller blade, wherein each of the first and second propeller blades include a fluid flow channel within the first and second propeller blades, which is fluidly connected to a flow exit slot, and a flow capture device, which includes a plenum chamber, mounted on the propeller hub, wherein the plenum chamber is fluidly connected to the fluid flow channels.

Abstract: A system for removing moisture from a steam/water mixture engaging a stationary component of a steam turbine. The system includes an airfoil located within a flow path of a steam turbine. The airfoil is configured for removing moisture from a steam/water mixture traveling in the flow path. To this end, the airfoil includes a cavity in flow communication with the steam path through at least one inlet and outlet opening, near the leading and trailing edge of the airfoil, respectively. Moisture and steam are extracted from the surface through the inlet openings, the steam and water are separated in the cavity, the separated water flows towards the bottom end, and the dry steam flows through the outlet opening and returns to the steam path. The dry steam blowing out of the trailing edge reduces the size of secondary droplets, and thereby prevents erosion.

Abstract: A rotor blade for a wind turbine is disclosed. The rotor blade may generally include a body extending between a blade root and a blade tip. The body may include a pressure side and a suction side extending between a leading edge and a trailing edge. In addition, the rotor blade may include a nozzle mounted on or within the body. The nozzle may include an inlet, an outlet and a converging section between the inlet and the outlet. The converging section may be configured to accelerate a flow of air through the nozzle such that an ultrasonic sound emission is produced.

Abstract: A rotor disk for a gas turbine engine includes a hub; a rim with a forward portion and an aft portion; and a plurality of circumferentially spaced radial scallops in the rim to form cooling slots between two disks when the rotor disk is connected to another rotor disk.

Abstract: A method of assembling an air distribution system for use in a rotor blade of a wind turbine. The rotor blade includes a sidewall at least partially defining a cavity extending from a blade root towards a blade tip. The method includes positioning at least a portion of a manifold within the cavity and coupling the manifold to the sidewall. The manifold extends from the blade root towards the blade tip and has a root end and an opposing tip end. A passage is defined from the root end to the tip end. A flow control device is coupled to the manifold root end and configured to channel air through the manifold. A bypass flow assembly is coupled to the manifold and configured to channel air through the air distribution system with the flow control device in a non-operating configuration.

Abstract: A turbine impeller including a rotor; a blade extending from the rotor from a first end of the blade; and a squealer tip provided at a second end opposite to the first end of the blade, wherein at least one perforated portion penetrates through the squealer tip.

Abstract: An axial flow compressor blade with a cavity formed within the blade tip region and connected by an array of holes onto the pressure side surface of the blade in the tip region so that compressed gas will flow into the cavity, and the cavity is connected by a row of tip slots arranged along the blade tip along the pressure side tip corner to discharge the compressed gas from within the cavity out onto the blade tip toward the oncoming compressed gas flow over the blade tip to reduce or eliminate any boundary layer formation and to reduce blade tip leakage flow.

Abstract: A wind turbine blade system that includes blades with an internal airflow path that extends within the blade from a location at the tip of the blade to a location near the base or root of the blade. A ram air turbine positioned inside each of the blades, along the airflow path, the ram air turbine being adapted for generate electricity, and thus the current output may then be connected to an electric load, so that air is ingested at the tip of the blade as each blade rotates.

Abstract: A turbine blade includes an airfoil portion including a suction side having a suction side contour, a pressure side having a pressure side contour, a leading edge, a trailing edge and a tip portion, and a squeeler pocket formed in the tip portion. The squeeler pocket includes a first side wall and a second side wall. The first side wall includes a first internal surface having a first substantially continuous curvilinear profile and the second side wall includes a second internal surface having a second substantially continuous curvilinear profile. A bleed passage extends from the squeeler pocket towards the trailing edge. The first and second side walls are configured to deliver a substantially unobstructed fluid flow from the squeeler pocket to the bleed passage and limit the fluid flow spillage onto one of the pressure side and the suction side.

Abstract: A pelletizing machine for forming pellets from extruded material includes an extruder having at least one exit port and a body defining a cutting chamber through which high-temperature liquid flows, flooding the cutting chamber. The exit port of the extruder opens into the cutting chamber, which includes a cutting section defining a flow path for liquid through the cutting section. A cutter in the cutting section of the cutting chamber is mounted for rotation about an axis generally perpendicular to the first direction and disposed for cutting the extruded material exiting the exit port into the pellets. The axis of rotation of the cutter is parallel to or coincident with the flow path of the cutting section. A method for forming pellets of thermoplastic material with a foaming agent is also disclosed.

Abstract: A pressure relief device includes a main body and at least two air control units. The main body has at least one passage therein and two outlets formed at upper and lower ends of the passage. A lid is pivotally connected to each of the outlets. The two air control units are each disposed in the passage close to the lid. An air control device drives the air control units to open/close the lid which is adapted to open/close the passage.

Abstract: One embodiment of the present invention is a system for controlling flow through a rotor. The system includes an inlet port in the rotor and an outlet port in the rotor. The outlet port is in fluid communication with the inlet port. A fixed orifice is disposed in at least one of the inlet or outlet ports. A variable orifice is disposed in at least one of the inlet or outlet ports in a separate location from the fixed orifice.

Abstract: An airfoil for a gas turbine engine includes a first sidewall and a second sidewall coupled together at a leading edge and a trailing edge, such that a cavity is defined therebetween. A plurality of cooling circuits are defined within the cavity. Each cooling circuit channels cooling fluid through at least one cooling chamber to facilitate cooling the airfoil. More specifically, a cascade impingement circuit, a down pass circuit, a flag tip circuit, and a trailing edge circuit are provided. The cascade impingement circuit includes a central chamber and a plurality of impingement chambers.

Abstract: A method of operating a wind turbine having at least one rotor blade and an active flow control (AFC) system is provided. The at least one rotor blade has at least one aperture defined through a surface thereof, and the AFC system is configured to modify aerodynamic properties of the rotor blade by ejecting gas through the aperture. The method includes operating the wind turbine in a normal mode, determining whether an estimated insect density value surrounding the wind turbine is above an insect density threshold value based on a measured environmental condition, and changing a mode of the wind turbine from the normal mode to a cleaning mode different than the normal mode based on the estimated insect density value. The cleaning mode includes adjusting at least one operation parameter of the wind turbine based on the estimated insect density value such that fouling of the aperture is reduced.

Abstract: A method of assembling an air distribution system for use in a rotor blade of a wind turbine wherein the rotor blade includes a sidewall extending from a blade root towards a blade tip. The method includes coupling a manifold to the sidewall, wherein the manifold extends from the blade root towards the blade tip and has a root end and an opposing tip end defining a passage from the root end to the tip end. A plurality of apertures is defined through the sidewall. The apertures provide flow communication between the passage and ambient air. A debris collector is coupled to the tip end of the manifold and is configured to collect debris flowing through the air distribution system.

Abstract: A non-clogging type pump impeller (1) includes: a fluid passage (18) provided in an approximately cylindrical body (10) and connecting a suction port (13) to a discharge port (14). The fluid passage (18) has a vortex shape as viewed from the axial direction. A first recess (21), which is sunk downwardly in the axial direction, is formed on one end surface (11) of the body (10) so as to surround a boss (12). A second recess (22), which is sunk upwardly in the axial direction, is formed on the other end surface (15) of the body (10) so as to surround the suction port (13). One or more communication hole (23) provides fluid communication between the first recess (21) and the second recess (22). Sewage in the second recess (22) is introduced into the first recess (21) through the communication hole (23) to thereby effectively remove air pocket trapped on the upper end surface (11) of the impeller (1) and in the first recess (21).

Abstract: The invention relates to a blower wheel, especially a plastic blower wheel for a cylindrical rotor radial fan for the heating and air-conditioning systems of a motor vehicle. Said blower wheel comprises a plurality of blades (2), and the flow channel (3) between two blades (2) is embodied in such a way that it is convergent on the inflow side, divergent on the outflow side, and distinctively shaped.

Abstract: An active flow control system for manipulating a boundary layer of air across a wind turbine rotor blade. The wind turbine rotor blade has at least one sidewall defining a cavity therein. The sidewall extends between a leading edge and an axially spaced trailing edge. The active flow control system includes an air discharge assembly that is coupled to the sidewall. The air discharge assembly is configured to selectively discharge air from within the wind turbine rotor blade into the boundary layer. An air suction assembly is coupled to the sidewall and to the air discharge assembly. The air suction assembly is configured to channel air from the boundary layer to the air discharge assembly.

Abstract: An aerodynamic body with an aerodynamic body surface that creates a contoured surface for a fluid to stream around, with a device to influence the flow of the fluid streaming around the aerodynamic surface. The flow-influencing device includes a passage to link the fluid streaming around the aerodynamic surface with an actuator space of an aspirating and purging device situated in the aerodynamic body, and an indentation that is situated next to the passage, which is formed by a recessed section of the aerodynamic surface on a flow-influencing region within the contoured surface of the aerodynamic surface, so that a boundary wall is configured as part of the recessed surface lying opposite the indentation. The aspirating and purging device can generate a swirl in the flow of the fluid streaming around the aerodynamic surface, the rotational axis of which is directed along the assumed aerodynamic body chord direction.

Abstract: An insert and method for altering a through-hole in a body, such as a steam balance hole in a steam turbine rotor wheel. The insert has a body with oppositely-disposed first and second ends, a flange radially extending from the second end of the body, and an outer surface at a perimeter of the body between the first end and the flange. A first bore within the body defines a first opening at the first end, and the first bore and outer surface of the body cooperate to define therebetween a wall capable of being plastically deformed in a radially outward direction. A second bore within the body communicates with the first bore and has a smaller cross-section than the first bore. The installation method entails installing the insert in a through-hole and flaring the wall to clamp the axial thickness of the body between the flange and flared wall of the insert.

Abstract: The invention relates to a blower wheel, especially a plastic blower wheel for a cylindrical rotor radial fan for the heating and air-conditioning systems of a motor vehicle. Said blower wheel comprises a plurality of blades (2), and the flow channel (3) between two blades (2) is embodied in such a way that it is convergent on the inflow side, divergent on the outflow side, and distinctively shaped.