70 results about "Radial turbine" patented technology

A method of assembling a radial turbine rotor includes manufacturing turbine blades, a flowpath ring, and a hub. The method includes fixing the turbine blades circumferentially around the flowpath ring by a blade joint between the turbine blades and the flowpath ring to form a ring assembly. The method includes spinning the hub and moving the hub into engagement with the flowpath ring to locate the hub radially inwardly of the flowpath ring and to form a hub joint between the flowpath ring and the hub.

A cooling structure for a radial turbine is equipped with a partition wall arranged between a compressor and the radial turbine, and a through hole formed in the partition wall supplying a part of air compressed by the compressor to the rear surface of the radial turbine as cooling air. The through hole is inclined in a rotational direction of the radial turbine in the range of 40° to 80° with respect to a rotation axis of the radial turbine.

A ducted turbine (10) includes a turbine (12) having a plurality of blades (14) extending from a hub (36) that rotate together about a turbine axis (X). The turbine (12) is surrounded by a coaxial duct (16) having an inner surface (22) radially outboard of the turbine. The duct (16) has a diameter (D) that changes along the axial direction such that its inner surface (22) has a curvilinear profile in an axially extending plane. The duct (16) accelerates and conditions fluid flowing past the turbine blades (14) to enhance energy extraction efficiency. The geometry of the duct (16) and the turbine blades (12) can be optimized using computational fluid dynamics (CFD) with a blade-resolved Reynolds-averaged Navier-Stokes (RANS) solver. To handle the high-dimensional design space of the blade and duct geometry, a gradient-based optimization can be performed with gradients computed by the adjoint method. The optimized geometries can provide the ducted turbine (10) with an efficiency significantly higher than that of a typical unducted turbine.

A turbocharger heat management structure relates to the technical field of internal combustion engine supercharging devices and comprises a radial flow turbine, a centrifugal compressor and a bearing system which are connected, and the heat management structure is arranged between the radial flow turbine and the bearing system. The heat management structure comprises a first heat insulation cover, a second heat insulation cover and a third heat insulation cover which are in a revolving body metal sheet shape and arranged at the turbine back disc, a first heat insulation cavity is formed between the first heat insulation cover and the second heat insulation cover, a second heat insulation cavity is formed between the second heat insulation cover and the third heat insulation cover, and a third heat insulation cavity is formed between the third heat insulation cover and the annular cooling groove. The first heat insulation cavity communicates with a gap in the turbine back disc, and the third heat insulation cavity is connected with a cold air hole. The third heat insulation cavity, the second heat insulation cavity and the first heat insulation cavity are sequentially communicated through an air guide structure. On the premise that the weight and the size are not greatly increased, the heat insulation efficiency is greatly improved, and the purpose of actively and efficiently cooling a key area is achieved.

The invention relates to a nozzle ring (10) for a radial turbine. The nozzle ring (10) comprises a first annular element (11), a second annular element (12) and a plurality of guide vanes (12) arranged between the first annular element (11) and the second annular element (12). The second ring element (12) comprises an end region (12E) extending only inwards in the radial direction, and the end region (12E) has a convex bend (141) on a side (121) facing the first ring element (11). The invention also relates to an exhaust gas turbine and to a turbocharger.

The present invention relates to a nozzle ring (10) for a radial turbine. The nozzle ring (10) comprises a first ring element (11), a second ring element (12) and a number of guide vanes (13) arranged between the first ring element (11) and the second ring element (12). The second ring element (12) comprises an end region (12E) which extends exclusively radially inward and has a convex curvature (141) on the side surface (121) facing the first ring element (11). The present invention also relates to an exhaust turbine and a turbocharger.

The invention discloses a radial flow type turbine correcting and cleaning device which aims at solving the problems that correcting and cleaning procedures are separated, efficiency is low, cleaning is not accurate, and equipment adaptability is poor. The multi-station rotary table is at least provided with a back disc correcting station and a cleaning station, and each station is provided with a rotating seat structure; the back disc correction station is provided with a correction chuck formed by splicing two semicircular correction half pieces, a correction sleeve with an avoiding opening and a roll-out platform, and accurate correction of the turbine disc can be achieved without circulation interference. The cleaning station is provided with an intermittent driving mechanism, the intermittent driving mechanism comprises a stirring part and a maintaining part, and through meshing fit of an incomplete gear and a missing gear and limiting of a lever arm driven by a cam, turbine fixed-angle rotation is achieved, and gaps between blades face a cleaning spray head one by one; and the shifting part and the retaining part are adjustable in position through the adjusting arm, so as to adapt to turbines of different specifications. And correction and cleaning integrated operation is achieved, the machining efficiency and precision are improved, universality is high, and the device is suitable for production of various radial flow type turbines.

A single-stage high-speed pipeline turbine generator set for natural gas pipeline and design method, the invention relates to a single-stage high-speed pipeline turbine generator set and design method, and belongs to the technical field of turbine expander power generation. In order to solve the problem that the auxiliary system of the natural gas overpressure turbine generator set in the prior art occupies a large proportion of the land area, the natural gas radial turbine expander and the high-speed permanent magnet synchronous generator are coaxially arranged, the natural gas radial turbine expander cooperates with the high-speed permanent magnet synchronous generator through a rotating shaft to generate power, and the natural gas radial turbine expander and the high-speed permanent magnet synchronous generator are installed on the natural gas pipeline. Natural gas turbine expander: thermal calculation is carried out, then three-dimensional modeling of the impeller is completed, analysis and optimization are carried out through CFD software, the key component impeller is made of titanium alloy, five-axis linkage high-speed milling is adopted for forming, motor selection is carried out according to the parameters of the expander, iteration optimization is carried out, and the generator design is completed.

A centrifugal radial turbine with parallel flows comprises a case (2), a single rigid shaft (6) mounted in the case (2) and having a first end and a second end supported in the case (2), a rotor disk (9; 9A, 9B) mounted solidly on the single rigid shaft (6). First rotor vanes (13) are arranged on a first face (11) of the rotor disk (9; 9A, 9B) and in a first volume delimited in the case (2) and second rotor vanes (14) are arranged on a second face (12) of the rotor disk (9; 9A, 9B) and in a second volume delimited in the case (2). A working fluid entering through an inlet duct (39) or through a first inlet duct (25) and a second inlet duct (26) flows according to parallel flows through the first volume and the second volume and exits through an outlet duct (28) or through a first outlet duct (28A) and a second outlet duct (28B).

A rotor (20) for a radial turbine (1), comprising: a hub (22); and a plurality of turbine blades (24), extending from or affixed to at least part of the hub (22), providing a plurality of combustion gas passageways (28) between respective turbine blades (24) along which combustion gases may pass so as to rotate the rotor (20). The one or more of the plurality of turbine blades (24) comprise at least part of a cooling passageway (31), the combustion gas passageways (28) and cooling passageway (31) being separate passageways configured to provide movement of combustion and cooling gases. The rotor further comprises a shroud (23), the plurality of turbine blades (24) extending between at least part of the hub (22) and at least part of the shroud (23), providing a plurality of enclosed combustion gas passageways through which combustion gases may pass so as to rotate the rotor (20).

A multi-piece radial turbine rotor includes a hub, a plurality of turbine blades, and a flowpath ring that couples the turbine blades to the hub. The flowpath ring is coupled with each of the plurality of turbine blades and the hub to locate the flowpath ring radially between the hub and each of the plurality of turbine blades. The flowpath ring is formed to include a plurality of apertures spaced apart from one another about the flowpath ring and extending radially through the flowpath ring. Each of the plurality of apertures receives a corresponding one of the plurality of turbine blades therein. The hub is fixed to the flowpath ring by a friction weld joint and each of the plurality of turbine blades is fixed to the flowpath ring by a blade joint.

A radial turbine rotor incorporating ceramic matrix composite turbine blades is disclosed. The radial turbine rotor can include an axially-extending lug features for coupling the ceramic matrix composite turbine blades to a central hub.

The present invention relates to an impeller (14) for a turbine (10), in particular a radial turbine. The impeller (14) has a plurality of blades (16), which are received on the circumference of the impeller (14) at intervals from one another. The blades (16) are configured to have a radially extending S-shaped profile (26).

A device for liquefying a fluid is disclosed, the device comprising a fluid circuit (3) to be cooled, the device (1) comprising a heat exchanger assembly (6, 7, 8, 9, 10, 11, 12, 13) in heat exchange with the fluid circuit (3) to be cooled, at least one first cooling system (20) in heat exchange with at least one portion of the heat exchanger assembly (6, 7, 8, 9, 10, 11, 12, 13), the first cooling system (20) being a refrigerator having a cycle for refrigerating a cycle gas mainly comprising helium, said refrigerator (20) comprising, in series in a cycle circuit (14): a mechanism (15) for compressing the cycle gas, at least one member (16, 5, 6, 8, 10, 12) for cooling the cycle gas, a mechanism (17) for expanding the cycle gas and at least one member (13, 12, 11, 10, 9, 8, 7, 6, 5) for reheating the expanded cycle gas, wherein the compression mechanism comprises at least four compression stages (15) in series made up of a centrifugal compressor assembly (15), the compression stages (15) being mounted on a shaft (19, 190) driven in rotation by an electric machine assembly (18), the expansion mechanism comprises at least three expansion stages in series made up of a set of radial turbines (17), the at least one member (16, 5, 6, 8, 10, 12) for cooling the cycle gas is configured to cool the cycle gas at the outlet of at least one of the turbines (17), and wherein at least one of the turbines (17) is coupled to the same shaft (19) as at least one compression stage (15) in order to supply the compression stage (15) with mechanical work produced during expansion.

A radial turbine impeller includes full blades and splitter blades arranged alternately in the rotational direction of the radial turbine impeller, the splitter blades having a shorter blade length in a fluid flow direction in the radial turbine impeller than the full blades. A throat is provided between each two of the full blades adjacent to each other in the rotational direction. A part of a downstream edge of each splitter blade on a side of a base edge which is joined to an outer peripheral surface of a hub is positioned upstream of the throat, and a part of the downstream edge of each splitter blade on a side of a tip edge which is remote from the outer peripheral surface of the hub is positioned downstream of the part of the downstream edge on the side of the base edge.

A radial turbine rotor incorporating ceramic matrix composite turbine blades is disclosed. The radial turbine rotor can include a dovetail shape retention features for coupling the ceramic matrix composite turbine blades to a central hub.

The invention relates to a turbine (1) for a radial turbomachine, the turbine (1) having a hub (2) with a turbine disc (3) connected thereto and a plurality of turbine blades (4) connected to the hub (2) by means of a blade root (6), the turbine blades (4) each having a curvature following a line of curvature (KL), the curvature of the turbine blades (4) being substantially parallel to the axis of curvature (KL), and the curvature of the turbine blades (4) being substantially parallel to the axis of curvature (KL). Each of the turbine blades (4) has a distribution of thickness (Sd) with respect to the height (Sh) of the turbine blade (4) above the hub (2) when viewing the orthogonal cross-section of the turbine blade (4), the thickness (Sd) of the turbine blade (4) at a small height (Sh) being greater than the thickness at a trapezoidal structure in which the thickness (Sd) of the turbine blade (4) at a small height (Sh) is greater than the thickness at a small height (Sh). The thickness (Sd) decreases uniformly from the blade root (6), and the thickness (Sd) of the turbine blade (4) at the large height (Sh) of the turbine blade (4) is smaller than the thickness at the trapezoidal structure.

This invention belongs to the field of radial turbines, specifically relating to a leakage prevention structure and a radial turbine. One leakage prevention structure includes a first inlet pipe, a first outlet pipe, and a second outlet pipe; the outlet of the first inlet pipe is connected to the inlet of the first outlet pipe and the inlet of the second outlet pipe, respectively; the leakage prevention structure is installed at the tip of the moving blade, allowing pressure-side fluid to enter the first inlet pipe, fluid ejected from the first outlet pipe to act within the gap, and fluid ejected from the second outlet pipe to act on the suction side. The leakage prevention structure of this invention can introduce pressure-side fluid into the gap and suction side, thereby reducing blade load; on the other hand, the fluid flowing into the gap significantly increases the leakage flow resistance, reducing the leakage flow rate; the fluid flowing into the suction side impacts the leakage vortex, weakening the leakage vortex intensity and further reducing the leakage flow rate; thus, it has the effect of weakening the leakage vortex intensity, reducing losses, and improving turbine efficiency.

This application relates to the field of turbocharger efficiency prediction technology, and discloses a turbocharger efficiency evaluation method and device based on variable structure turbine data. The method first establishes a reliable radial turbine numerical model through high-precision three-dimensional simulation and experimental verification; then, it uses sensitivity analysis and Latin hypercube sampling to screen key impeller geometric parameters and construct an efficient sample dataset; the core is the application of a neural network algorithm to establish a nonlinear prediction model with turbine reduced speed and key geometric parameters as input and turbine efficiency as output, thereby quickly and accurately obtaining the variable structure turbine efficiency characteristics under all operating conditions; finally, by dynamically identifying the real-time operating conditions of the turbocharger, and combining the turbine efficiency predicted by the neural network with the compressor efficiency calculated by actual measurements, an accurate and efficient evaluation of the overall efficiency of the variable structure turbocharger is achieved, effectively solving the problems of high prediction difficulty and low accuracy of traditional methods.

An impeller (58) for a radial turbine comprises a substantially conical hub (70), and a plurality of impeller blades (80) arranged along an outer periphery of the hub at regular intervals, wherein a tip end (80D) of each impeller blade is provided with a fin (82) projecting in a thickness-wise direction of the impeller blade over a prescribed region (X) extending along a chord length thereof from a first point (P1) at a first distance from an upstream end (80A) of the tip end to a second point (P2) at a second distance from a downstream end (80D) of the tip end.

A multi-piece radial turbine rotor includes a hub, turbine blades, and an intermediate ring that couples the turbine blades to the hub. Joints between the components of the rotor are adapted for inspection during manufacture to identify potential defects in the joints.

A flow control method for suppressing vibration of a radial turbine blade based on wall surface grooving is provided. Inclined grooves are formed in a casing wall surface by uniformly arranging them in a circumferential direction and by adjusting the dimension and number of the inclined grooves and a relative location between each of the inclined grooves and the scroll, whereby aerodynamic excitation forces generated by each of the inclined grooves and the scroll cancel each other out. Consequently, vibration stress on the blade is reduced, improving the operational reliability of the radial turbine and maintaining the aerodynamic performance of the turbine substantially unchanged.

The lubricating oil monitoring device comprises an oil filtering tank, a first connecting pipeline and a third connecting pipeline are arranged on the two sides of the oil filtering tank respectively, the first connecting pipeline is connected with a flange plate at one end of a flow meter through a flange plate arranged at one end of the first connecting pipeline, and the third connecting pipeline is connected with a second connecting pipeline through a flange plate arranged at the other end of the second connecting pipeline. A flange plate arranged at the other end of the flowmeter is connected with a flange plate arranged at one end of a second connecting pipeline, a second pressure transmitter is arranged on the first connecting pipeline, a first pressure transmitter is arranged on the second connecting pipeline, and a flange plate arranged at one end of a third connecting pipeline is connected with a flange plate arranged at one end of a fourth connecting pipeline. A pressure transmitter III is arranged on the connecting pipeline III, a pressure transmitter IV is arranged on the connecting pipeline IV, a filter screen plate is longitudinally inserted into the oil filter tank, and a temperature sensor is arranged on the left side of the top of the oil filter tank. The lubricating oil safety monitoring device can realize multi-aspect safety monitoring of lubricating oil.

The invention relates to a turbine wheel (11, 11') for a turbine (10) of a turbocharger of a vehicle, having a single-piece wheel body (13, 13') which is designed to be rotatably arranged in a turbine housing (12) and to be connected to a shaft (31) at least for conjoint rotation, wherein the single-piece wheel body (13, 13') has a central shaft region (14), a blade root region (15) and a number of turbine blades (16). According to the invention, at least the shaft region (14) and the blade root region (15) have a cavity (21) delimited by a wheel body wall (18) which defines the outer structure of the wheel body (13, 13'), and a number of ribs (19, 19') of a gyroidal structure (20) extend through said cavity, wherein the ribs (19, 19') within the cavity (21) have a rib wall thickness (SB) and the wheel body wall (18) has a wheel body wall thickness (RB), wherein the wall thicknesses (SB, RB) thereof and / or the density of the gyroidal structure (20) are defined in accordance with forces that act on the wheel body (13, 25 13') during the operation of the turbine wheel (11).

A variable inlet radial flow turbine is provided. The variable inlet radial flow turbine includes an impeller, a first partial inlet ring, and a second partial inlet ring. The first partial inlet ring includes a first inlet portion. The first inlet portion connects the radial inner side of the first partial inlet ring and the radial outer side of the first partial inlet ring, and extends non-circumferentially in the circumference of the first partial inlet ring. The second partial inlet ring includes a second inlet portion. The second inlet portion connects the radial inner side of the second partial inlet ring and the radial outer side of the second partial inlet ring, and extends non-circumferentially in the circumference of the second partial inlet ring. The second partial inlet ring and the first partial inlet ring can rotate relative to each other, so that the second inlet portion and the first inlet portion can overlap in the radial direction. In this way, by making the first partial inlet ring and the second partial inlet ring cooperate with each other, the variable inlet radial flow turbine can adapt to working conditions under different flow rates.

A multi-piece radial turbine rotor includes a hub, turbine blades, and a flowpath ring that couples the turbine blades to the hub. Joints between the components of the rotor are adapted for inspection during manufacture to identify potential defects in the joints.

The invention relates to a turbine wheel (11, 11') for a turbine (10), in particular a radial turbine, of a turbocharger of a vehicle, in particular a motor vehicle, with a one-piece, in particular additively manufactured, wheel body (13, 13') which is designed for rotatable arrangement in a turbine housing (12), in particular a radial housing, and at least rotationally fixed connection to a shaft (31), wherein the one-piece wheel body (13, 13') has a central shaft region (14), a blade root region (15) and a number of turbine blades (16), wherein the blade root region has a number of radial extensions (17) assigned to the turbine blades (16), which each radially adjoin the central shaft region (14) extending around a central axis (M) of the wheel body (13, 13') and are integrally connected to the shaft region (14), wherein a turbine blade (16) is integrally adjoined to each radial extension (17). According to the invention, at least the shaft region (14) and the blade root region (15) have a cavity (21) which is delimited by a wheel body wall (18) defining the outer structure of the wheel body (13, 13') and is traversed by a number of webs (19, 19') of a gyroidal structure (20), wherein the webs (19, 19') within the cavity (21) have a web wall thickness (S B ) and the wheel body wall (18) has a wheel body wall thickness (R B ), where the wall thickness (S B , R B) of the webs (19, 19') and / or the wheel body wall (18) and / or the density of the gyroidal structure (20) running in the cavity (21) are defined as a function of forces acting on the wheel body (13, 13') during operation of the turbine wheel (11).

The utility model provides a multi-stage heterogeneous turbine coupling type composite cascade power generation system which comprises a low-temperature preheater, a medium-temperature evaporator, a high-temperature heat absorber, a high-pressure radial turbine, a generator I, a low-pressure axial turbine, a generator II, a working medium pump I, a gas-liquid separator, a condenser, a working medium pump II and working medium pipelines among all the components. High-pressure supercritical heat absorption and low-pressure subcritical heat absorption of a working medium are coupled to form a dual-pressure heat absorption organic Rankine cycle, the design of coupling multi-stage heterogeneous turbines is adopted in the expansion power generation process of the system, and higher expansion efficiency can be achieved through all-stage cooperative expansion, so that the working efficiency and the heat utilization rate of the system are effectively improved; and efficient gradient utilization of medium and low temperature heat energy is facilitated.

The centrifugal radial turbine comprises a shell, a cavity is formed in the shell, a rotating shaft is rotatably connected in the cavity, an open groove is formed in one end of the outer surface of the shell, one end of the rotating shaft penetrates through the open groove and is rotatably connected with a sealing assembly, and the other end of the rotating shaft is rotatably connected with the blade top bearing. The sealing assembly comprises a mounting frame fixedly mounted at one end of the outer surface of the shell, a sealing groove is formed in the inner surface of the mounting frame, sealing gaskets are symmetrically arranged at the two ends, away from the sealing groove, of the inner surface of the mounting frame, and an air inlet is formed in one end of the outer surface of the mounting frame. Sealing gas is injected into the sealing groove, so that a gas working medium can be isolated from the outside, the gas working medium is effectively prevented from leaking outwards, meanwhile, external gas is prevented from entering the shell to pollute components in the shell, and normal use of the centrifugal radial turbine is prevented from being affected.

The invention relates to a nozzle ring for a radial turbine. The nozzle ring comprises a first ring element, a second ring element, and a plurality of guide vanes arranged between the first ring element and the second ring element. The second ring element comprises an end region, which extends inwards exclusively in the radial direction and has a convex curvature on a side facing the first ring element. The invention also relates to an exhaust turbine and to a turbocharger.