190 results about "Radial turbine" patented technology

There has been invented a turbine engine with a single rotor which cools the engine, functions as a radial compressor, pushes air through the engine to the ignition point, and acts as an axial turbine for powering the compressor. The invention engine is designed to use a simple scheme of conventional passage shapes to provide both a radial and axial flow pattern through the single rotor, thereby allowing the radial intake air flow to cool the turbine blades and turbine exhaust gases in an axial flow to be used for energy transfer. In an alternative embodiment, an electric generator is incorporated in the engine to specifically adapt the invention for power generation. Magnets are embedded in the exhaust face of the single rotor proximate to a ring of stationary magnetic cores with windings to provide for the generation of electricity. In this alternative embodiment, the turbine is a radial inflow turbine rather than an axial turbine as used in the first embodiment. Radial inflow passages of conventional design are interleaved with radial compressor passages to allow the intake air to cool the turbine blades.

A turbocharger, having an axial compressor wheel and an axial turbine wheel mounted on a first shaft supported by a housing, and a radial compressor wheel and a radial turbine wheel mounted on a second shaft, the second shaft concentrically extending around the first shaft and being supported by the housing. The housing defines a first duct extending axially from the exducer of the axial compressor to the inducer of the radial compressor, and a second duct extending axially from the exducer of the radial turbine to the inducer of the axial turbine. A plurality of controllable compressor guide vanes extend through the first duct, and a plurality of controllable turbine stator vanes extend through the second duct. The housing is provided with variable diffuser vanes at the exducer of the radial compressor, and with variable turbine vanes at the inducer of the radial turbine. The variable turbine vanes and the turbine stator vanes are controlled to accurately control the rotation rate of the radial and axial turbines. The compressor guide vanes are controlled to minimize surge and maximize choke flow rate.

The present invention provides a turbine wheel with locally curved trailing edge blade tips on the blades of the turbine wheel. The locally curved trailing edge may increase the blade vibration mode natural frequency which may in turn result in longer blade fatigue lifetimes. It may also eliminate vortex shedding. Methods for increasing the blade vibration mode natural frequencies using the turbine wheel of the present invention are also provided.

A power tool with a housing (12) and a tool (18, 22) located thereon such that it is capable of being driven in a rotating and/or oscillating manner, the tool being operable as directed using vacuum flow, in particular using a vacuum cleaner. The power tool is made particularly powerful by the fact that a radial turbine wheel (34) with forward-guiding and rearward-guiding vane rows (44, 48) functions as the drive.

A radial turbomachine includes a radial diffuser channel with a diaphragm, a deflecting channel connecting to the radial diffuser channel downstream thereof, and a return flow channel connecting to the deflecting channel downstream thereof. The main flow direction of the radial diffuser channel runs radially from inside to outside. The main flow direction of the deflecting channel is deflected from radially outward to radially inward. The main flow direction of the return channel runs radially from outside to inside. The diaphragm comprises first, second and third outer surface sections. The first outer surface section has a convex shape for delimiting the deflecting channel. At least one consumption-gas removal channel is provided in the diaphragm so that, if the main flow in the deflecting channel comprises solid or liquid particles, a consumption gas can be discharged therefrom through the consumption-gas removal channel as low-particulate gas of a main flow.

A radial turbine includes a radial turbine wheel provided with a main pathway in which blade height progressively increases while curving toward an axial direction from a radial direction. A sub-let is formed on a shroud side of the radial turbine wheel at a position separated from the main inlet in the radial direction and the axial direction. Also, a blade shape that forms the sub-inlet is such that, in a plane orthogonal to the axial line of the radial turbine wheel, a center line of the blade is inclined at a predetermined angle toward the rotation direction with respect to the radial direction.

The invention discloses a turbine combined pulse detonation engine (PDE). An air inlet device is positioned at the front tip of an engine shell; a gas compressor is positioned at the lower reaches of the air inlet device and is coaxial with the air inlet device; the gas compressor is coaxial with a radial turbine; a flow-guide casing is a smooth transition case between the gas compressor and the radial turbine; a guider is positioned between the flow-guide casing and the radial turbine; an inlet valve is positioned between the flow-guide casing and the inner wall of the engine shell; a diffusion cushion chamber ranges from the lower reaches of the gas compressor to the upper reaches of the inlet valve; a multi-tube detonation chamber is positioned at the lower reaches of the inlet valve; the outer annular wall surface of the multi-tube detonation chamber is part of the engine shell and the inner annular wall surface forms an inner annular wall; an inner flow passage is positioned at the lower reaches of the radial turbine; an ignition system is an ignition device of the multi-tube detonation chamber and the exit of the multi-tube detonation chamber is connected with a nozzle. The PDE is no longer than the length corresponding to the maximum external profile diameter of the gas compressor, thus greatly reducing coupling of detonation circulation and turbine operation, having high working frequency and conducing to power extraction.

A turbine wheel for a radial turbine includes a rotationally symmetrical base plate and a flow chamber delimited by a hub disk and a cover disk, wherein the flow chamber connects an axial inner opening to a radial outer opening and is subdivided by turbine blades into flow channels. In a method for producing such a turbine wheel, the hub disk, the turbine blades and the cover disk are integrally formed on the base plate using additive production methods.

A volute for a radial turbomachine is proposed. The turbomachine includes a radial compressor or a radial turbine. The volute is in particular for a radial compressor. The volute has a substantially annular cavity which is delimited at least by a first radial side surface. At least one substantially annularly circumferential groove is formed in the side surface.

The disclosure relates to a cylinder head having at least one cylinder. The cylinder head comprises a radial turbine including a rotor arranged in a turbine casing and rotatably mounted on a shaft, an overall exhaust line which opens into an inlet zone of the radial turbine, said zone merging into a flow duct which carries exhaust gas, and at least one coolant duct integrated into the turbine casing to form a cooling system, the at least one coolant duct extending in a spiral around the shaft in the casing, wherein the at least one coolant duct extends circumferentially around and at a distance from the flow duct over an angle α, where α≦45°.

Cooling air to the blades and disks of a gas turbine may be modulated to provide a variable turbine cooling flow. A bellows may be extended by providing a high pressure compressor discharge flow to an interior of the bellows. The bellows may be compressed when the interior of the bellows communicates with ambient pressure air. The extension/compression of the bellows moves an arm over orifices in a cooling air flow path. The pressure inside of the bellows is metered to move the arm over at least one orifice, thereby restricting cooling air flow when the engine is running at low power. The pressure inside of the bellows is metered to move the arm to uncover all of the slots to provide maximum cooling flow when the engine is running at high power. The resulting variable cooling flow system results in less need for cooling air at low powers, thus reducing engine fuel consumption.

An axially-split radial turbine includes a forward rotor section and an aft rotor section being mechanically and abuttingly coupled to one another along an annular interface that resides within a plane generally orthogonal to a rotational axis of the axially-split radial turbine. The axially-split radial turbine can be provided as part of a gas turbine engine.

A compact, single shaft gas turbine gas generator uses a high pressure ratio dual-entry single stage centrifugal compressor, can combustors, and a radial inflow turbine with the compressor configured to achieve an overall pressure ratio of about 12:1 or greater and Mach Numbers less than or equal to about 1.4. The radial inflow turbine is configured to provide an expansion ratio of about 4:1 to about 5:1, to provide partially expanded combustion gases to a free-power turbine or an expansion nozzle, in a work-producing engine configuration. A ball bearing assembly in front of the compressor is used in conjunction with a thrust piston assembly to take up turbine thrust load, while a radial tilt pad bearing assembly is used in front of the turbine. A collector with scroll-shaped sector portions collects compressed air from an annular vaned diffuser, and respective crossover ducts channel the collected diffused compressed air from each sector portion to a plenum feeding can combustors. Bleed systems at each compressor inlet provide increased diffuser stability margins. Gas turbine engines configured with the above gas generator may provide 30% thermal efficiency or more in a rated power range of about 4 Mw or less.

Intended is to provide a mixed flow turbine or a radial turbine, which can suppress an abrupt increase in a load to be applied to the front edge portion of a blade, thereby to reduce an incidence loss. The mixed flow turbine or the radial turbine comprises a hub (3), and a plurality of blades (7) arranged at substantially equal interval on the outer circumference (5) of the hub (3) and having a warpage (23) curved convexly in the rotating direction, as entirely viewed from the front edge side to the back edge side. Each blade (7) is provided, at its front edge portion, with an inflection point (K), at which the warpage (23) in the section along the outer circumference is curved concavely in the rotating direction.

A radial turbine nozzle of a turbine engine rotating about a central axis includes a first annular array of fixed blades and a second annular array with a same number of variable-pitch blades. The blades have pressure and suction surfaces. Each variable-pitch blade is connected to cups and is configured to be rotated by a controller about a geometric axis connecting centers of the cups. Each variable-pitch blade is mounted at a distance from the axis of the cups such that this axis of rotation is positioned facing the suction surface of the blade and substantially closer to a trailing edge than to a leading edge of that blade. The nozzle can modify the reduced flow admitted by a radial turbine in accordance with requirements of a thermodynamic cycle and produce a seal in an area of maximum load of the nozzle blades.

The invention relates to an integrated cantilever rotor structure, which comprises a generator rotor, a centrifugal compressor impeller, sealed grate teeth and a radial turbine impeller which are arranged on a central pull rod in sequence. One side of the centrifugal compressor impeller is connected with the radial turbine impeller through the sealed grate teeth in end face matching mode, the centrifugal compressor impeller and the radial turbine impeller are arranged in back-to-back mode, and the other end of the centrifugal compressor impeller is connected with the generator rotor. The integrated cantilever rotor structure has the advantages of being simple in structure, small in volume and capable of enabling a unit structure to be simple, usage to be reliable, failure rate to be low and both manufacture cost and maintenance cost to be reduced.

[Problem] To provide a radial turbine rotor blade whereby, even if a variable nozzle mechanism in a variable-geometry turbocharger is closed down, resulting in a flow field with a low turbine velocity ratio (U/C0), inflowing-gas impact losses at the leading edge of the rotor blade are reduced, improving turbine efficiency. [Solution] This radial turbine rotor blade is characterized in that: with respect to the direction of rotation (R) of the rotor blade (50), the hub-side corner (Pa) of the leading edge (51) of the rotor blade (50) is behind the shroud-side corner (Sc) of said leading edge (51); and in a radial view of the rotor blade (50), a line that connects the aforementioned shroud-side corner (Sc) to the hub-side corner (Pa) forms a 30-70° angle with a line that extends in the direction of the axis of rotation from the shroud-side corner (Sc) of the leading edge (51) to the surface of the hub (17).