A nozzle ring (10) for a radial turbine is described. The nozzle ring includes a disc-shaped main body (11) having a central opening (12) for passing a shaft there through. Additionally, the nozzle ring includes guide vanes (14) disposed circumferentially in a radially outer portion on a first surface (11A) of the main body (11). Two or more bores (17) are provided in a radially inner portion of the main body (11). Further, a groove (171) is provided in the first surface (11A) of the main body (11), the groove (171) connecting at least two of the two of more bores (17).
A cleaning device (10) for a turbine is described. The cleaning device (10) includes an injector main body (11) for injecting cleaning liquid into a flow channel of the turbine. The injector main body (11) includes a main flow channel (12). The main flow channel (12) is connected to one or more first flow channels (121) of respective one or more first injectors (13). At least one of the one or more first flow channels (121) includes a curved channel portion (125).
The invention relates to a turbocharger which contains a bearing device which is arranged between a compressor and a turbine and which is designed to support a shaft. This bearing device has a bearing housing, in which an oil-lubricated bearing for supporting the shaft is arranged. The shaft has a slinger element extending in the circumferential direction for centrifugally dispersing lubricating oil. The bearing housing has an oil drainage channel for discharging the lubricating oil from the bearing housing. The inner region of the bearing housing forms an oil delimitation chamber, which is sealed off by seals arranged between the shaft and the bearing housing. The oil delimitation chamber has a deflection means which is formed in such a way that, during operation of the turbocharger, lubricating oil that is centrifugally dispersed by the slinger element is deflected by the deflection means and is conducted in the opposite direction to the seals. The oil delimitation chamber is formed in the vicinity of the slinger element in such a way that the lubricating oil centrifugally dispersed by the slinger element during operation of the turbocharger can be transferred directly from said slinger element to the deflection means. A collection channel prevents lubricating oil centrifugally dispersed from the slinger element from flowing back into the seal region. The slinger element is formed in such a way that the lubricating oil sprayed away from the slinger element has a radial and an axial directional component, and the axial directional component runs in the opposite direction to the seals.
The invention relates to an exhaust turbocharger, which contains a modular bearing, which is designed for bearing a shaft and is arranged between a compressor and a turbine, wherein the bearing has a bearing housing having a receptacle chamber, wherein a bearing assembly module can be or is installed in the receptacle chamber and can be non-destructively removed, the receptacle chamber being sized such that optionally either a bearing assembly module having a rolling bearing or a bearing assembly module having a slide bearing can be installed, the receptacle chamber having an interface, which is designed to contact the bearing flange of a bearing assembly module inserted into the receptacle chamber, the interface being designed to connect an oil gallery passing through the bearing housing to one or more oil galleries passing through a bearing flange of the bearing assembly module.
F16C 17/26 - Systems consisting of a plurality of sliding-contact bearings
F01D 25/16 - Arrangement of bearingsSupporting or mounting bearings in casings
F16C 19/18 - Bearings with rolling contact, for exclusively rotary movement with bearing balls essentially of the same size in one or more circular rows for both radial and axial load with two or more rows of balls
F16C 19/54 - Systems consisting of a plurality of bearings with rolling friction
The invention relates to a multistage turbocharger device (1), which has a high-pressure turbine (2), a low-pressure turbine (3), a low-pressure compressor (4), a high-pressure compressor (5), a first shaft (6) and a second shaft (7), wherein one of the turbines and one of the compressors are arranged on the first shaft and the other turbine and the other compressor are arranged on the second shaft, the two shafts have the same axis of rotation, the two shafts are arranged one behind the other in the axial direction and the two shafts rotate in opposite directions.
F02B 37/013 - Engines characterised by provision of pumps driven at least for part of the time by exhaust with exhaust-driven pumps arranged in series
F02C 6/12 - Turbochargers, i.e. plants for augmenting mechanical power output of internal-combustion piston engines by increase of charge pressure
F01D 1/24 - Non-positive-displacement machines or engines, e.g. steam turbines characterised by counter-rotating rotors subjected to same working-fluid stream without intermediate stator blades or the like
The invention relates to a filter muffler (10) comprising a front element (11), a rear element (12), and a plurality of damping elements (20) which are arranged between the front element (11) and the rear element (12). The damping elements (20) are arranged radially about a central axis (16) of the filter muffler such that a flow channel (30) is formed between each pair of adjacent damping elements. The respective downstream ends (22) of the damping elements (20) each have a diffuser element (23) which has a downstream tapering. An angle α between two opposing sides of the diffuser element (23) is selected from a range of 1° ≤α ≤ 8°.
The invention relates to a filter silencer (10), comprising a front element (11), a rear element (12), and a multiplicity of damping elements (20). The multiplicity of damping elements (20) is arranged between the front element (11) and the rear element (12). At least one damping element of the multiplicity of damping elements has a connecting opening (25) through which a connecting element (13) extends which connects the front element (11) to the rear element (12). A first guide device (27A) for the damping elements (20) is provided on one side of the front element (11) that faces the rear element (12), and/or a second guide device (27B) for the damping elements (20) is provided on one side of the rear element (12) that faces the front element (11).
The invention relates to an exhaust gas turbine, comprising a turbine rotor (12) having a plurality of turbine rotor blades (2) with a turbine rotor blade height H. The exhaust gas turbine further comprises a diffuser arrangement (20) having a transverse diffuser (1) and an exhaust gas collection chamber (9). The transverse diffuser (1) is arranged downstream of the turbine rotor blades (2). The transverse diffuser (1) has a curved diffuser channel (13) which opens into the exhaust gas collection chamber (9) at a diffuser channel outlet (17). A M/H ratio between an axial extension M of the exhaust gas collection chamber (9) and the turbine rotor blade height H has a value of 1.0 ≤ M/H ≤ 4.6 and a P/H ratio between a radial extension P of the diffuser arrangement (20) and the turbine rotor blade height H has a value of 2.7 ≤ P/H ≤ 4.9. A D/H ratio between a radial expansion D of the diffuser channel section (13) and the turbine rotor blade height H has a value of 2.5 ≤ D/H ≤ 3.0 and a R/H ratio between a turbine hub radius R and the turbine rotor blade height H has a value of 1.1 ≤ R/H ≤ 1.5.
The invention relates to a diffuser for a compressor, comprising - a flow channel which is delimited in the flow direction by a first lateral wall and a second lateral wall, wherein the lateral walls run at least partly divergent relative to each other, and one of the lateral walls has a diffuser base (23a), the outer surface of which facing the flow channel (23) does not run in the radial direction, - a diffuser blade ring with a number of mutually spaced diffuser blades, which are arranged at least partly in the flow channel, each of the diffuser blades having a pressure side and a suction side, and - a number of diffuser passages, each of which is arranged between two adjacent diffuser blades and has a base area between the two adjacent diffuser blades. A non-tangentially constant transition is provided between a first level formed by the base area of a first diffuser passage and a second level formed by the base area of a second adjacent diffuser passage, or a non-tangentially constant transition is provided in the diffuser passage base area formed between the two adjacent diffuser blades.
The invention relates to an exhaust gas turbine, comprising a turbine wheel (7) with a multiplicity of moving blades (8) and an exhaust-gas outlet duct (15), which is arranged downstream of the moving blades of the turbine wheel. The exhaust-gas outlet duct (15) is delimited radially on the outside by an axial turbine diffuser (1) and radially on the inside, at least partially, by a spinner (2). The axial turbine diffuser (1) is formed by a number N>1 of successive conical diffuser segments. An axial diffuser opening angle A between successive diffuser segments is A>1.0°. A ratio L/H between an axial diffuser segment length L and an entry height H of the exhaust-gas outlet duct (15) is L/H>0.01. A ratio H/S between the entry height H of the exhaust-gas outlet duct and a maximum radius S of the spinner (2) is H/S>1.0. The spinner (2) is formed by a number P>1 of successive conical spinner segments. An axial spinner opening angle B between successive spinner segments is B>1.0°. A ratio M/H between an axial spinner segment length M and the entry height H of the exhaust-gas outlet duct (15) is M/H>0.01.
The invention relates to a diffuser for a radial compressor, comprising a flow channel defined by a first side wall and a second side wall, a diffuser vane ring with a plurality of diffuser vanes that are at least partially arranged in the flow channel, each of the diffuser vanes having a pressure side and a suction side, a plurality of diffuser passages, said diffuser passages being formed between every two adjacent diffuser vanes of the plurality of diffuser vanes, and circuation openings, each circulation opening connecting the flow channel to a diffuser cavity, at least two circulation openings being associated with one diffuser passage, and a circulation opening associated with a diffuser passage being fluidically connected to another circulation opening associated with the same diffuser passage or to a circulation opening associated with another diffuser passage, via the diffuser cavity.
The invention relates to a turbocharging system (100) for a combustion engine. The turbocharging system comprises a turbocharging stage, comprising an exhaust gas turbocharger (101) with a compressor (110), a charge air feed (111) for feeding air to an air manifold (121) of the combustion engine (122), and an exhaust gas turbine (130) in an exhaust gas path (112) at the exhaust gas manifold (123) of the combustion engine. The turbocharging system also comprises a safety device (150) for monitoring an exhaust gas turbocharger speed. The safety device comprises a speed sensor (151) for measuring the exhaust gas turbocharger speed, a control unit (152) for determining an acceleration of the exhaust gas turbocharger on the basis of a measurement signal (SI) of the speed sensor (151), and a closing mechanism (153) for interrupting an air feed to the exhaust gas manifold (123) in event that a critical acceleration of the exhaust gas turbocharger is detected. At the same time, a bypass can be opened, which is designed to feed air back into a gas flow downstream of an exhaust gas turbine (130).
The invention relates to a nozzle ring (10) for a radial turbine. The nozzle ring comprises a rotationally symmetrical disc-shaped main part (11) with a central opening (12) for the passage of a shaft (20). The nozzle ring further comprises guide vanes (14) which are arranged in a radially outer region of the main part (11) in the circumferential direction and are designed so as to guide exhaust gases towards guide vanes (31) of a turbine wheel (30). The main part (11) of the nozzle ring is designed to form a heat shield between a bearing chamber (40) of a bearing housing (41) and a turbine chamber (50) in the assembled state.
The invention relates to a compressor (100) of an exhaust gas turbocharger, comprising a compressor wheel (110) that can rotate about an axis (111), a main flow channel (120) for supplying a medium to be compressed to the compressor wheel (110), an outer compressor housing (125), and an element (130) arranged radially between the compressor wheel (110) and the compressor housing (125). In the installed state, the element (130) is configured for forming an annular stabiliser channel (135) surrounding the main flow channel, wherein a number (V) of V≥ mco + jB identical struts (140) are provided in the stabiliser channel (135), which are arranged periodically around the perimeter, wherein mco is the first circulating mode, wherein j is the order of the harmonics, and wherein B is the number of rotor blades of the compressor wheel.
The invention relates to a radial bearing arrangement (110) of an exhaust gas turbocharger (100) for mounting a shaft (120) in a bearing housing (130). The radial bearing arrangement (110) comprises a radial bearing bush (140) which is arranged between the shaft (120) and the bearing housing (130), wherein the radial bearing bush (140) comprises a radially outwardly projecting collar (141) which interacts in the axial direction with an axial stop (131) on the bearing housing (130). The geometry of the radially outwardly projecting collar (141) is interrupted by way of cut-outs, with the result that a force which acts on the collar (141) as a result of an oil feed pressure is minimized, and wherein the radial bearing bush (140) is configured in such a way that a lubricating film can be formed between an end surface of the radial bearing bush (140) and a counterpiece (160) which is arranged on the shaft (120).
F16C 17/18 - Sliding-contact bearings for exclusively rotary movement characterised by features not related to the direction of the load with floating brasses or bushes, rotatable at a reduced speed
F16C 17/02 - Sliding-contact bearings for exclusively rotary movement for radial load only
F16C 35/02 - Rigid support of bearing unitsHousings, e.g. caps, covers in the case of sliding-contact bearings
F16C 17/10 - Sliding-contact bearings for exclusively rotary movement for both radial and axial load
A cylinder head (5) for a four-stroke internal combustion engine with supercharging is proposed. It comprises a cylinder head main body (10), at least one inlet valve (14) and an inlet duct (16) which is connected to it, wherein the inlet valve (14) has a valve head (15) and is provided in the stem region with a valve spring (18) which is supported on the cylinder head main body (10); a first pressure equalization duct (22) between the inlet duct (16) and a chamber (17) in the region of the valve stem (24) of the inlet valve (14), as a result of which boost pressure is guided into the chamber (17) during operation, which boost pressure exerts a force on the inlet valve (14) in the closing direction; wherein the inlet duct (16) has, on the valve seat, a cylindrical opening (23) which at least partially receives the valve head (15) of the inlet valve (14) in the closed state of the inlet valve (14), and wherein the inlet duct (16) remains closed during a first part of an opening movement of the inlet valve (14).
The invention relates to a method for the low nitrogen-oxide combustion of a gaseous fuel in the combustion chamber of an internal combustion engine with an internal mixture formation. The method consists of injecting a first amount of gas during the drawing process; compressing the gas-air mixture; injecting a second amount of gas at the beginning, during or at the end of compression, the first and second amount of gas being selected such that a predetermined value of NO-x emission is not exceeded; igniting the gas-air mixture; and combusting the entire amount of gas from the first amount of gas and the second amount of gas, wherein the first amount of gas amount undergoes combustion prior to mixing, and the second amount of gas is predominantly converted in a mixing controlled combustion. The invention also relates to a corresponding internal combustion engine.
F02D 19/02 - Controlling engines characterised by their use of non-liquid fuels, pluralities of fuels, or non-fuel substances added to the combustible mixtures peculiar to engines working with gaseous fuels
F02D 19/06 - Controlling engines characterised by their use of non-liquid fuels, pluralities of fuels, or non-fuel substances added to the combustible mixtures peculiar to engines working with pluralities of fuels, e.g. alternatively with light and heavy fuel oil, other than engines indifferent to the fuel consumed
F02D 41/00 - Electrical control of supply of combustible mixture or its constituents
F02D 41/40 - Controlling fuel injection of the high pressure type with means for controlling injection timing or duration
F02D 19/10 - Controlling engines characterised by their use of non-liquid fuels, pluralities of fuels, or non-fuel substances added to the combustible mixtures peculiar to engines working with pluralities of fuels, e.g. alternatively with light and heavy fuel oil, other than engines indifferent to the fuel consumed simultaneously using pluralities of fuels peculiar to compression-ignition engines in which the main fuel is gaseous
18.
GAS-OPERATED INTERNAL COMBUSTION ENGINE AND METHOD FOR THE OPERATION THEREOF
The invention relates to a method for the combustion of a gaseous fuel in the combustion chamber of an internal combustion engine with internal mixture formation. The method consists of injecting a first amount of gas during the drawing process wherein the air ratio of the thus formed gas-air mixture in the lean region is above the ignition limit; compressing the gas-air mixture; injecting a second amount of gas at the beginning, during or at the end of compression; igniting the gas-air mixture; and combusting the entire amount of gas from the first amount of gas and the second amount of gas, wherein the first amount of gas undergoes combustion prior to mixing, and the second amount of gas is predominantly converted in a mixing controlled combustion. The invention also relates to a corresponding internal combustion engine.
F02D 41/00 - Electrical control of supply of combustible mixture or its constituents
F02D 41/40 - Controlling fuel injection of the high pressure type with means for controlling injection timing or duration
F02D 19/10 - Controlling engines characterised by their use of non-liquid fuels, pluralities of fuels, or non-fuel substances added to the combustible mixtures peculiar to engines working with pluralities of fuels, e.g. alternatively with light and heavy fuel oil, other than engines indifferent to the fuel consumed simultaneously using pluralities of fuels peculiar to compression-ignition engines in which the main fuel is gaseous
19.
PISTON RING, TURBOCHARGER WITH PISTON RING, AND METHOD FOR PRODUCING A PISTON RING
The invention relates to a piston ring for sealing at least one component of a turbocharger. The piston ring comprises a first ring body which is a base body of the piston ring. The first ring body is formed and designed such that it is prestressed when installed in a turbocharger. The piston ring also comprises a second ring body, the second ring body being formed and designed such that it is prestressed when installed in a turbocharger. The first ring body and the second ring body are bonded. The invention also relates to a turbocharger with a piston ring and to a method for producing a piston ring.
F16J 15/24 - Sealings between relatively-moving surfaces with stuffing-boxes for elastic or plastic packings with radially or tangentially compressed packing
F16J 15/28 - Sealings between relatively-moving surfaces with stuffing-boxes for rigid sealing rings with sealing rings made of metal
F16J 15/3272 - Mounting of sealing rings the rings having a break or opening, e.g. to enable mounting on a shaft otherwise than from a shaft end
B23P 15/08 - Making specific metal objects by operations not covered by a single other subclass or a group in this subclass piston rings from several pieces
F16J 9/20 - Rings with special cross-sectionOil-scraping rings
F16J 9/26 - Piston-rings, seats thereforRing sealings of similar construction in general characterised by the use of particular materials
F16J 15/34 - Sealings between relatively-moving surfaces with slip-ring pressed against a more or less radial face on one member
The duct cross-section in the diffuser of a radial-flow compressor is significantly larger in the inlet region of the diffuser section. This increases the space available to the flow upstream of the actual diffusor duct, resulting in a rapid deceleration and thus a rapid increase in pressure. The flow velocity is thus reduced in the downstream components of the compressor and flow losses are reduced accordingly.
The device serves for sealing off a bearing housing (10), which accommodates a lubricating oil, of an exhaust-gas turbocharger having a rotor (2) which is led through the bearing housing in the direction of an adjoining compressor housing. The device comprises an intermediate wall (11), an axially extending wall extension (111) of the intermediate wall, and a sealing disk (5) fastened to the shaft (20) of the rotor (2). Furthermore, seals (4) are arranged between the rotor (2) and the wall extension (111) or the intermediate wall (11). The intermediate wall (11) separates a large oil chamber (12) arranged in the bearing housing from the wheel rear-side chamber (13) of the compressor wheel (21). A predominantly axially extending cover (6), which leads in at least partially ring-shaped form around the rotor, projects into the large oil chamber from the intermediate wall (11). In particular, the large oil chamber (12) is divided by the cover (6), and by the sealing disk (5) extending in the radial direction, into an outer oil collecting chamber (121) and an inner oil collecting chamber (122). A major part of the lubricating oil conveyed in the direction of the large oil chamber (12) by the bearings (3) of the turbocharger can be collected by the outer oil collecting chamber (121). Lubricating oil that has entered the inner oil collecting chamber (122) is conveyed by gravitational force to an outlet (61) at a large axial distance from the sealing disk (5). The oil quantity that advances further radially inward from the inner oil collecting chamber (122) along the sealing disk (5) in the direction of the seals (4) can be considerably reduced by means of said device, and the sealing action of the bearing housing can be considerably increased. An exhaust-gas turbocharger having a device of said type is likewise presented.
The device is used to separate lubricating oil streams within a bearing housing (10), which receives lubricating oil, of a turbocharger, which comprises an axial turbine and which has a shaft (11) that is led from a compressor housing to a turbine housing through the bearing housing, two radial bearings (12, 13) arranged along the shaft, and a shaft axial bearing (14) which can be found between the radial bearings. The device comprises at least one wall projection (40) which projects from an inner wall of the bearing housing radially inwards in the direction of the shaft into an intermediate space (17) of the bearing housing. The intermediate space (17) extends between the axial bearing (14) and the turbine-side radial bearing (13) and tapers in the axial direction towards the turbine side. Lubricating oil which is transported from the axial bearing (14) and which strikes bearing housing wall sections surrounding the axial bearing is redirected by the wall protrustion and is guided in the direction of the space which can be found below the shaft. In this manner, large quantities of lubricating oil transported from the axial bearing (14) are prevented from flowing to the seat of the turbine-side radial bearing (13) and there, at the location of the sharpest taper of the intermediate space (17), blocking the discharge of the smaller oil quantities transported through the turbine-side radial bearing. The invention likewise relates to a turbocharger comprising such a device.
The invention relates to a compressor assembly for a turbocharger. The compressor assembly (1) comprises: a spiral housing (2), which has a flow channel (12) designed to convey a fluid that can be sucked in from outside of the compressor assembly (1); a compressor outlet flange (3, 11, 16), which is fluidically connected to the spiral housing (2) by means of the flow channel (12), a blow-in device (4, 13, 20), wherein the blow-in device (4, 13, 20) is designed to conduct a fluid into the flow channel (12) from outside of the compressor assembly (1), wherein the blow-in device (4) is arranged outside of the flow channel (12) of the spiral housing (2).
F02B 37/10 - Engines with exhaust drive and other drive of pumps, e.g. with exhaust-driven pump and mechanically-driven second pump at least one pump being alternately driven by exhaust and other drive
F04D 17/10 - Centrifugal pumps for compressing or evacuating
The diffuser (1) for a radial compressor (100) comprises: – a diffuser duct section (2) which is formed of a first side wall (3) and a second side wall (4), wherein the first side wall (3) and the second side wall (4) are arranged so as to diverge at least partially with respect to one another in the flow direction, – a blade disk (5) with a number of blades (6, 6') wherein the blades (6, 6') are arranged at least partially in the diffuser duct section (2), wherein each of the blades (6, 6') has a pressure side (22) and a suction side (23), and wherein the pressure side (22) and the suction side (23) of each one of the blades (6, 6') is bounded by a blade leading edge (8) and by a blade trailing edge (8') of these blades (6, 6'), – a number of pressure-equalizing openings (7, 7') which are machined into at least one of the two side walls (3, 4) of the diffuser duct section (2), wherein each one of the number of pressure-equalizing openings (7, 7') is arranged between the pressure side (22) of one blade (6) and the suction side (23) of the adjacent blade (6') of the blade disk (5), – a first annular duct (10) which is arranged behind the pressure-equalizing openings (7, 7'), wherein the first annular duct (10) is fluidically connected to the diffuser duct section (2) via at least two of the pressure-equalizing openings (7, 7'), whereby a number of diffuser passages of the diffuser (1) can be fluidically connected to one another, wherein a diffuser passage is a region between two adjacent blades (6, 6') of the blade disk (5) in the diffuser duct section (2), characterized in that the first annular duct (10) can be connected to a pressure plenum (31) via a connecting duct (30), whereby a fluid can flow from the pressure plenum (31) into the first annular duct (10) in order that the first annular duct (10) is flushed with the fluid.
A flow straightener consisting of profiled guiding elements (31) on the interior inner wall (6) of the flow channel in the diffusor region of an axial turbine prevents flow separation on the contour of the inner wall of the diffusor.
According to the invention, the resonant vibration of the compressor can be reduced by varying the angular distances between two adjoining guide vanes (21) of the diffuser along the circumference. Additionally, the throat area between adjoining guide vanes is kept constant, which increases efficiency and positively affects the surge margin.
The inventive compressor for high specific suction capacity has a compressor wheel (1) with rotor blades (11, 12). In the region of the smallest distance (TL) between two adjacent rotor blades (11, 12), the respective rotor blades (11, 12) are formed so as to increase the area (20', 20'') bounded by the two rotor blades (11, 12) in the region of the narrowest point. In that context, the blade leading edge (FE) is configured in a sickle shape (20'), that is to say the leading edge (FE) is curved counter to the direction of rotation of the blades (11, 12). The curvature is reduced in the flow direction, as far as the region of the smallest distance (TL) between two adjacent rotor blades (11, 12), at least to a flat shape, and is preferably even curved in the direction of rotation (20'').
The compressor housing (10) of a centrifugal compressor has an annular stabiliser space (15) which is separated from the flow duct (14) by an annular web (102). The stabiliser space (15) is connected to the flow duct (14) via an inlet gap (12) upstream of the compressor rotor inlet and via a stabiliser gap (11) downstream of the compressor rotor inlet. The annular web (102) is further connected to the compressor housing (10) via multiple radial holding ribs (103). In order to hold the annular web (102) axially in the event of rupture of the compressor rotor, it is proposed to arrange, on the annular web axially between the holding ribs (103) and the stabiliser gap (11), a radially projecting retaining element (105). If, in the event of rupture, the holding ribs fail in the root region, this retaining element will retain the annular web axially by means of a form fit with the holding ribs.
F01D 21/04 - Shutting-down of machines or engines, e.g. in emergencyRegulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator, e.g. indicating such position
F04D 29/42 - CasingsConnections for working fluid for radial or helico-centrifugal pumps
The invention relates to a high-temperature air bearing for a turbocharger, wherein two outer bearing rings (51, 52) of a dual-cone air bearing assembly can be moved elastically in relation to each other and are prestressed.
Backup bearing arrangement (50, 51, 52, 53, 54) for turbochargers that is located between the points of support (40, 45) on the rotatably mounted shaft (30) which connects the compressor impeller (1) to the turbine wheel (20). The backup bearings can optionally also be located outside the points of support on the shaft. As another option, the backup bearings can be located outside the compressor impeller and the turbine wheel, on the shaft extension at the turbine end and on the shaft extension at the compressor end. The point of support of each backup bearing can be located in any axial or radial position on the shaft.
F01D 21/04 - Shutting-down of machines or engines, e.g. in emergencyRegulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator, e.g. indicating such position
F01D 25/16 - Arrangement of bearingsSupporting or mounting bearings in casings
The compressor wheel of a centrifugal compressor has a hub the radial length of which is reduced in the region of a hub rear wall. The rotor blades project over the outer hub contour. The hub rear wall of the compressor wheel can additionally have cut-out sections between the individual rotor blades. According to the invention, axial thrust, temperature of the compressor wheel and leakage flow can thus be reduced.
The invention relates to are deductible in the computation of the profits of the payer of this income. According to the invention an injection nozzle (101) is arranged in addition to a conventional injection nozzles to reduce NOx. At a first injection time, a first fuel amount (121) is applied to a vaporization surface of a flame ring (119) by means of the additional injection nozzle such that a lean combustion mixture is produced. Furthermore, at a second injection time, a fuel amount is introduced in the combustion chamber such that a rich combustion mixture is produced.
F02D 41/40 - Controlling fuel injection of the high pressure type with means for controlling injection timing or duration
F02B 23/06 - Other engines characterised by special shape or construction of combustion chambers to improve operation with compression ignition the combustion space being arranged in working piston
The invention relates to a bearing housing ventilation system for a turbocharger arrangement. The bearing housing ventilation system for a turbocharger arrangement (10) comprises a compressor-side housing (12) through which a compressor-side working medium flows, a turbine-side housing (13) through which a turbine-side working medium flows, and a bearing housing (11). The bearing housing (11) is arranged between the compressor-side housing (12) and the turbine-side housing (13), and a leakage flow from one or both of the two housings (12, 13) enters the bearing housing. The bearing housing ventilation system comprises at least one jet pump (2) with which a suction medium can be suctioned and conducted by means of a propellant jet, the working medium of one or both housings being used as the propellant in order to suction the leakage flow as the suction medium from the bearing housing (11).
The invention relates to an exhaust gas turbocharger comprising a turbine having a turbine wheel, and a compressor having a compressor wheel. The turbine wheel and the compressor wheel are connected to one another by way of a shaft that is pivotably mounted in a bearing housing. Preferably, the bearings are arranged between the turbine wheel and the compressor wheel. Between the compressor wheel and the turbine wheel, a means for axially securing the shaft and the turbine wheel connected thereto is provided. In the event the compressor wheel bursts, said means for axial securing prevents an axial movement of the shaft and of the turbine wheel connected thereto in the direction of the turbine. The means for axially securing the shaft and the turbine wheel connected thereto comprises a structural element, which is connected to the shaft or is mounted on the shaft, and is fixed in the housing in an axial direction. According to the invention, said structural element for axial securing is screwed onto the shaft during assembly. For this purpose, said structural element has an internal thread. Fitting thereto, the shaft has a corresponding external thread having an undercut, which allows the screwing of the structural element onto the shaft. The smallest inner diameter of the internal thread of the structural elements is hereby smaller than the largest outer diameter of the external thread of the shaft.
F02C 6/12 - Turbochargers, i.e. plants for augmenting mechanical power output of internal-combustion piston engines by increase of charge pressure
F02D 21/04 - Controlling engines characterised by their being supplied with non-airborne oxygen or other non-fuel gas peculiar to oxygen-fed engines with circulation of exhaust gases in closed or semi-closed circuits
F01D 25/16 - Arrangement of bearingsSupporting or mounting bearings in casings
The subject of the invention is, in the case of a multistage turbocharger (2), that of an increase in relative air humidity owing to a temperature reduction in an intercooler (7) being counteracted by extraction of moisture. Here, a dehumidification device (8) is arranged between the intercooler (7) and a compressor (41) of the high-pressure stage (4). The dehumidification device (8) has a swirl-generating element (82) such as, for example, a centrifugal separator. In this way, the air flow, which substantially follows the direction of the air line, has a swirling motion imparted to it. Owing to this swirling motion, centrifugal forces are generated within the flow, by means of which centrifugal forces water droplets that are present in the air flow are transported outward in the direction of the internal wall of the air line (81). Accordingly, water vapour can be condensed and the water droplets can be separated out of the flow, and thus the relative air humidity can be reduced, even if the cooling in the intercooler (7) takes place to a temperature at which the air flow has already fallen below the dewpoint.
B01D 45/16 - Separating dispersed particles from gases or vapours by gravity, inertia, or centrifugal forces by centrifugal forces generated by the winding course of the gas stream
The invention relates to a lifting device and an associated method which enable a simplified removal of a rotor block (2) from the housing (14) of an exhaust gas turbocharger in an axial direction along the axis of rotation of the rotor. The lifting device comprises a cantilever (5), which is fastened to a vertical stop, thus to an axial end face of the housing (14), and on which a superstructure (6) that can be displaced along the cantilever is arranged, which superstructure is likewise fastened to a vertical stop, thus to an axial end face of the rotor block (2). The cantilever (5) comprises a support frame (51), which has rails (52) arranged thereon, and a slide (53), which is guided on the rails and has mounting devices (531, 532) for fastening the superstructure.
A wear-resistant layer for a component comprises a filler material and a binder material. The binder material comprises a metallic matrix and the filler material comprises an oxide-ceramic compound, which contains Al2O3 - ZrO2 or Al2O3 - TiO2. The metallic matrix forms a hard matrix with a hardness of 400 HV0.1 to 850 HV0.1. The filler material has a hardness of 1400 HV0.1 to 1800 HV0.1.
C23C 28/00 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and
C23C 30/00 - Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process
The invention relates to an exhaust gas turbine having a shaft (1) and a turbine wheel (2), and which has an internally closed nozzle ring (3). The nozzle ring (3) has guide blades (33) and an inner ring (31) that lies radially inside in relation to the guide blade (33). An inner surface of the nozzle ring (3) bounded by the inner ring (31) is filled out by a cover (34) and sealed in regard to the exhaust gas flow, such that the inner surface is closed in regard to a throughflow of the exhaust gas. Thus, the sealing point between the nozzle ring (3) and an inner gas inlet housing (42) is omitted and is transferred to a technically simpler seal between the nozzle ring (3) and the cover (34).
The gas bearing is arranged between the turbine wheel (2) and the compressor impeller (1) and is preferably arranged in the radially inner region in the case of an attached rotor. In one design variant, the gas bearing is realized by means of two bearing rings (5) which in each case have at least one axial bearing surface and one radial bearing surface. Said bearing surfaces correspond with the corresponding axial running surfaces (43) and radial running surfaces (42) of the bearing comb (4) which is clamped between the compressor and turbine or is connected integrally to the rotor, the compressor and/or the turbine. A compact, low-friction and contamination-free bearing of a turbocharger is realized in this way.
F01D 25/22 - Lubricating arrangements using working fluid or other gaseous fluid as lubricant
F16C 32/06 - Bearings not otherwise provided for with moving member supported by a fluid cushion formed, at least to a large extent, otherwise than by movement of the shaft, e.g. hydrostatic air-cushion bearings
A hydrodynamic axial bearing for the mounting of a shaft (40) which is mounted rotatably in a bearing housing (20), comprising an axial stop (21) of the bearing housing and a bearing collar (10) rotating with the shaft. A lubricating gap (52) which is delimited by a profiled circular ring surface (31) and a sliding surface (11) and is acted upon by lubricating oil is formed between the axial stop (21) and the bearing collar (10). The profiled circular ring surface (31) and the sliding surface (11) are formed in such a manner that the lubricating gap (52) tapers radially outwards with respect to the axial direction. As a result, temperature deformations occurring during operation and deformation because of centrifugal forces, shearing forces and other forces in the bearing collar can be compensated for.
The subject matter of the invention is to connect a nozzle ring (5) of an exhaust gas turbine to an inner gas inlet housing (10) of the exhaust gas turbine in a supporting manner. Owing to the supporting connection to the nozzle ring (5), the inner gas inlet housing (10) has no additional bracing on an outer gas inlet housing (9) of the exhaust gas turbine since such a bracing would influence an exhaust gas flow in a flow channel of the exhaust gas turbine.
The invention relates to a turbine housing (1) of a two-stage exhaust-gas turbocharger, said housing surrounding the entire exhaust ducting of the high-pressure turbocharger (2) and the low-pressure turbocharger (3). Said turbine housing is designed as a solid housing block used as a base for the other components of the two turbochargers (2, 3). The connection of the charge-air cooler (4) to the two-stage exhaust gas turbocharger is simplified as a result of equidirectional flow guidance.
Depending on the concrete operating situation and the composition of the fuels used for driving the internal combustion engine, the rotor blades, the guide device and the turbine housing parts of the exhaust gas turbine are soiled sooner or later. According to the cleaning method of the invention for wet cleaning an exhaust gas turbine, the amount of cleaning liquid injected into the flow channel of the turbine via a nozzle is varied over time by a defined, average amount of cleaning liquid.
The compressor of an exhaust gas turbocharger comprises a compressor wheel (14), an outer compressor housing (101), and a housing insert (102, 103) arranged radially outside of the compressor wheel (14), wherein the housing insert has an insert wall contour, which together with a hub of the compressor wheel (1) delimits a flow channel, and the housing insert (10) is fastened to the outer compressor housing (20) in the axial direction. According to the invention, the housing insert piece comprises an absorption element in the form of a circumferential bellows (105) for securing (106, 109) to the outer compressor housing (101) in order to transfer axial forces from the insert wall contour (11). The kinetic energy released during failure is absorbed by the elastic and plastic deformation bellows-shaped absorption element. The claimed absorption element thus requires the smallest possible installation space for high axial unloading of the housing connection between the inner and outer compressor housing parts and/or between the compressor housing and the bearing housing in the event that the compressor wheel bursts.
F01D 21/04 - Shutting-down of machines or engines, e.g. in emergencyRegulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator, e.g. indicating such position
F02C 6/12 - Turbochargers, i.e. plants for augmenting mechanical power output of internal-combustion piston engines by increase of charge pressure
F04D 29/42 - CasingsConnections for working fluid for radial or helico-centrifugal pumps
45.
EXHAUST GAS TURBOCHARGER WITH MEANS FOR AXIALLY SECURING THE SHAFT WHEN THE COMPRESSOR WHEEL RUPTURES
The system for securing the shaft of an exhaust gas turbocharger comprises a housing element (2) designed as a retaining ring with a central opening and a radial projection on the shaft (1). The retaining ring (2) is provided with an inner contour (22, 24) in the region of the central opening. The radial projection on the shaft is provided with an outer contour (11, 12). The inner contour on the retaining ring (2) and the outer contour on the shaft are designed so as to match, such that the radially outwardly projecting projection on the shaft can be pushed in the axial direction through the central opening in the housing element (2) in at least one specific angular position of the shaft relative to the housing when the shaft and the turbine wheel (4) that is connected thereto are assembled, whereas the outwardly projecting projection bears against the housing element (2) with the central opening in the axial direction in any angular position other than the at least one specific angular position of the shaft relative to the housing. The advantage of the device according to the invention lies in the simple assembly and disassembly of the shaft (1) at a standstill. The shaft-securing system is active only in the event of a rupture. The device does not affect the rotating behavior of the rotor during normal operation.
F02C 6/12 - Turbochargers, i.e. plants for augmenting mechanical power output of internal-combustion piston engines by increase of charge pressure
F01D 21/04 - Shutting-down of machines or engines, e.g. in emergencyRegulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator, e.g. indicating such position
The exhaust-gas turbine comprises a turbine wheel with a multiplicity of moving blades (2), the moving blades (2) each comprising at the radially outer ends a shroud segment with an inflow-side inner shroud edge (22) and an outflow-side inner shroud edge (21) and, between the inflow-side shroud edge (22) and the outflow-side shroud edge (21), a sealing web segment (23), protruding radially beyond the shroud segment. According to the invention, the outflow-side inner shroud edge (21) has a diameter (DK) which is at least 99.5% of the greatest outside diameter (DT) of the moving blades. Alternatively, an axially running housing portion that bounds the flow duct for the exhaust gases runs radially outside the moving blades (2), characterized in that, between the outflow-side inner shroud edge (22) and the outflow-side inner shroud edge (21), the shroud is arranged at an angle of at least 10° in relation to the surrounding housing wall.
The invention relates to a two-stage exhaust gas turbocharger of an internal combustion engine (2), comprising a high-pressure stage having a high-pressure turbine (15) acted on by the high-pressure exhaust gases (5) of the internal combustion engine and a high-pressure compressor (18) drivingly connected to the high-pressure turbine, a low-pressure stage having a low-pressure turbine (7) connected in series to the high-pressure turbine (15) by means of a low-pressure exhaust gas line (16, 6) connected to the high-pressure turbine (15) and having a low-pressure compressor (10) connected upstream of the high-pressure compressor (18) by means of a low-pressure charge air line (11) and drivingly connected to the low-pressure turbine (7), and means (20, 25) for recapturing energy disposed in parallel to the high-pressure stage, characterized in that the pressure ratio πV,ND across the low-pressure compressor is at least 50 percent greater than the pressure ratio πV,HD across the high-pressure compressor.
F02B 37/007 - Engines characterised by provision of pumps driven at least for part of the time by exhaust with exhaust-driven pumps arranged in parallel
F02B 37/013 - Engines characterised by provision of pumps driven at least for part of the time by exhaust with exhaust-driven pumps arranged in series
F02B 41/10 - Engines with prolonged expansion using exhaust turbines
F02D 13/02 - Controlling the engine output power by varying inlet or exhaust valve operating characteristics, e.g. timing during engine operation
F02D 41/00 - Electrical control of supply of combustible mixture or its constituents
F02D 29/00 - Controlling engines, such controlling being peculiar to the devices driven thereby, the devices being other than parts or accessories essential to engine operation, e.g. controlling of engines by signals external thereto
F01N 5/04 - Exhaust or silencing apparatus combined or associated with devices profiting by exhaust energy the devices using kinetic energy
The seal of the compressor impeller (7) relative to the bearing housing (9) comprises an annular sealing element (4) that forms a seal boundary together with a shaft edge (10) and that is acted upon by a spring force in the direction of the shaft edge (10). The pressure forces that act on the sealing element are either compensated or enhanced by the external spring force, depending on the direction of the pressure difference. In this way, the seal of the oil chamber in the bearing housing of the exhaust gas turbocharger, said seal being in the direction of the shaft, is not affected by the pressure fluctuations in the impeller rear chamber of the compressor, or is only very slightly affected thereby.
The invention relates to a device (D) that is used to seal a bearing housing (10) holding lubricating oil, wherein a rotor (2) of an exhaust gas turbocharger supported in the housing interior is led from the bearing housing into a compressor housing of the turbocharger that can be loaded with a mass flow. The device comprises a stationary partitioning wall (4) having a wall projection (40), a sealing disk (5) fastened to a shaft (2) of the rotor (2), a separating gap (7) arranged between the sealing disk (5) and the wall projection (40), and a dripping device (8) that is connected to an oil catching groove (42) and that conducts lubricating oil collected in the oil catching groove (42) into an oil drain (13) with the help of the force of gravity. The dripping device (8) contains a draining surface (80) for lubricating oil that has a large axial distance (b) from a rotating sealing disk (5) that bounds the separating gap (7). Lubricating oil possibly penetrating into the separating gap (7) can now be led into an oil drain (13) of the bearing housing (10) without interaction with the sealing disk (5). Even if the separating gap (7) is suctioned by vacuum, as is the case, for example, when the turbocharger is in standstill or partial-load operation, the intake of an impermissible oil amount into the compressor through the separating gap (7) is thus effectively prevented.
According to an exemplary embodiment of the invention, a charging system for an internal combustion engine is provided in which the charging is adapted to be in two stages, wherein the EGR turbocharger operates in parallel with the high pressure turbochargers. The two-stage charging brings about an improvement in the charging efficiency, whereby the EGR compressor has to overcome a higher pressure difference.
The device serves to seal off a bearing housing (4) of an exhaust-gas turbocharger, out of which a rotor (R) is guided into a chamber of the charger which is subjected to a mass flow. The device has a seal ring (5) arranged in a groove (22) of the rotor, a seat (43) which is arranged on the bearing housing (4) and to which the preloaded seal ring (5) is fixed with an outwardly pointing lateral surface, and a radially extending separating gap guided annularly around the rotational axis of the rotor, which separating gap is delimited by two sliding surfaces which bear against one another and of which the first is arranged on a first end side (51) of the seal ring (5) and the second is arranged on a first flank (21) of the groove (22). To reduce the introduction of heat into the sealing ring (5) caused by the rubbing of the seal ring (5) during the operation of the exhaust-gas turbocharger, the second flank (23) of the groove (22) has formed in it a depression (26) which is guided annularly around the axis (A), the depression (26) is delimited radially to the outside by an annular body (24) which is formed into the rotor (R), the annular body (24) forms a section of an outer surface of the rotor (R), and the annular body has a radially aligned annular edge (25) which adjoins the outer surface and which serves to reduce the size of a rubbing surface generated when the seal ring (5) abuts against the second groove flank (23).
It is the object of the invention to create a simple exhaust system with improved operational reliability and an increased service life for a turbocharged internal combustion engine, in which system both the advantages of shock-wave charging and those of pulse-converter charging are used, depending on the operating state of the internal combustion engine according to the invention, this is achieved by virtue of the fact that extension pieces (12, 13) are formed for the shock pipes (6, 7) and are arranged upstream of the connection line (8, 9) furthest away from the exhaust turbine (5). Each shock pipe (6, 7) is connected to a corresponding extension piece (12, 13) The interconnection conduit/s (14) is/are formed between the extension pieces (12, 13)
The simplified cleaning device for a compressor comprises a cavity (51) for a cleaning medium, said cavity being integrated into the housing (41) of a sound absorber (4), the cleaning medium able to be fed from said cavity to the flow channel via a feed (52).
F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
F02C 6/12 - Turbochargers, i.e. plants for augmenting mechanical power output of internal-combustion piston engines by increase of charge pressure
F02C 7/045 - Air intakes for gas-turbine plants or jet-propulsion plants having provisions for noise suppression
F02C 7/143 - Cooling of plants of fluids in the plant of working fluid before or between the compressor stages
F02C 7/30 - Preventing corrosion in gas-swept spaces
F02B 37/00 - Engines characterised by provision of pumps driven at least for part of the time by exhaust
F02B 77/04 - Cleaning of, preventing corrosion or erosion in, or preventing unwanted deposits in, combustion engines
F02M 25/00 - Engine-pertinent apparatus for adding non-fuel substances or small quantities of secondary fuel to combustion-air, main fuel or fuel-air mixture
A cleaning module is used for injecting the cleaning liquid at a certain location in front of the nozzle ring (26) at a predetermined angle and with steady or also periodically varying water pressure into the flow channel. With the cleaning device according to the invention, steady water distribution is achieved at the nozzle ring (26) or at the rotor blades (25) of the turbine impeller (24).
The sealing air channel (46) embedded in an axial front side of the carrier ring (40) is sealed by the gas outlet housing (22) on the open side thereof. Due to the arrangement, the sealing air channel can have such a large cross-section in the outer region of the cross-sectional profile that all sealing air can be fed along the circumference only at one point.
F01D 17/16 - Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
F01D 11/04 - Preventing or minimising internal leakage of working fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type using sealing fluid, e.g. steam
The sliding block (17) is clamped between the fastening foot (10) and the bracket (30). Here, the fastening bore (12) in the fastening extension (11) is designed such that the fastening extension (11) can move on the sliding block (17) relative to the screw (18). In contrast, the bores in the sliding block (17) and in the bracket (30) surround the screw (18) in a positively locking fashion. In this way, it is ensured that the screw (18), the sliding block (17) and the bracket (30) cannot be moved relative to one another. The only permitted movement takes place between the contact surface (A) of the fastening extension (11) of the fastening foot (10) and the sliding block (17).
A rotation lock (30) in the area of the connection between the compressor housing (10) and the bearing housing (20) prevents the rotation of the compressor housing (10) relative to the bearing housing (20).
F01D 21/04 - Shutting-down of machines or engines, e.g. in emergencyRegulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator, e.g. indicating such position
F02C 6/12 - Turbochargers, i.e. plants for augmenting mechanical power output of internal-combustion piston engines by increase of charge pressure
F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
A sealing air channel conducts sealing air (54) from the entry into the turbine housing up to the exit into the main flow of the exhaust gas. The geometric design of the sealing air channel (56) in the area between the cover band segment (22) at the tips of the turbine rotor blades (2) and the stationary housing parts (42) has the result that even with chronologically and/or spatially uneven distribution of the exhaust gas flow, a chronologically uniform sealing action, which is uniform around the circumference of the turbine, is achieved relative to the exhaust gases penetrating via the cover band.
F01D 11/10 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator using sealing fluid, e.g. steam
F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
The fastening for the attachment of the control device (40) to the gas outlet housing (20) is positioned in the region radially outside the guide blades (41, 42). The circumferential position of the guide blades may thereby be freely selected within the predefined angle. No collisions occur between the guide blades (41, 42) and the fastening means (50).
Exhaust gas turbocharger, comprising a compressor with an air outlet (22), a storage space (11), and a device for energy matching between the air outlet and the storage space, wherein the device for energy matching comprises a junction line (50) between the air outlet and the storage space, wherein a non-return valve is arranged in the junction line, which closes when there is excess pressure at the air outlet of the compressor relative to the storage space.
To reduce the peripheral asymmetry in compressor outlet housings, a collecting chamber having two sections of differing cross-sectional area design (21, 22) is proposed. In this way, an improved flow through the upstream components of radial diffuser and rotor and more homogeneous collection of the volume flow around the circumference are achieved, whereby an efficiency increase results.
The invention relates, in one embodiment, to the regulation of the positioning of the adjustable turbine guide blades (variable turbine geometry; VTG), which sets a desired position of the operating line, in particular also under changed operating conditions. Here, a characteristic curve is used which, at every rotational speed of the turbocharger, indicates the positioning of the adjustable turbine guide blades which results in the desired position of the operating line. The positioning of the adjustable turbine guide blades is a non-linear function of the turbocharger state (or the turbocharger rotational speed); it is therefore a non-linear regulation. In one configured system, the rotational speed of the turbocharger is measured and the desired VTG positioning is determined via the characteristic curve. A regulator ensures that the VTG is moved into the desired position.
The hydrodynamic axial bearing having a floating disk (30) is optimized in regard to waste power and oil throughput in that the two lubrication gaps on the two sides of the floating disk (30) are formed by supporting surfaces of different sizes. Equal lubrication gaps may thus be set for both sides in spite of differing rotational velocities between the floating disk (30) and bearing housing (20), or the floating disk (30) and bearing collar (11).
F16C 17/18 - Sliding-contact bearings for exclusively rotary movement characterised by features not related to the direction of the load with floating brasses or bushes, rotatable at a reduced speed
F16C 17/04 - Sliding-contact bearings for exclusively rotary movement for axial load only
F16C 17/10 - Sliding-contact bearings for exclusively rotary movement for both radial and axial load
F01D 25/16 - Arrangement of bearingsSupporting or mounting bearings in casings
Since the angular intervals between two guide vanes (21), which are arranged adjacent, in the diffuser vary along the circumference, the resonant oscillation of the compressor can be reduced.
If a turbocharger comprising a compressor and a turbine is combined with an engine/generator and is at the same time equipped with adjustable guide blades, the pressure in the air receiver (pRec) and scavenging of the engine (ﶴpeng) can be independently controlled within certain limits exclusively by means of the turbocharger. Three variables should be brought to a desired state: the pressure in the air receiver (pRec), the scavenging pressure difference (ﶴpeng), and the electric power(Pel). There are two manipulated variables: Pel and the position of the adjustable turbine guiding device. Two of the variables (pRec, ﶴpeng, Pel) can be independently selected while the third variable is automatically adjusted.
F02D 41/00 - Electrical control of supply of combustible mixture or its constituents
F02B 37/10 - Engines with exhaust drive and other drive of pumps, e.g. with exhaust-driven pump and mechanically-driven second pump at least one pump being alternately driven by exhaust and other drive
F02B 39/10 - Non-mechanical drives, e.g. fluid drives having variable gear ratio electric
F02B 37/22 - Control of the pumps by varying the cross-section of exhaust passages or air passages
F01N 3/20 - Exhaust or silencing apparatus having means for purifying, rendering innocuous, or otherwise treating exhaust for rendering innocuous by thermal or catalytic conversion of noxious components of exhaust characterised by methods of operationControl specially adapted for catalytic conversion
66.
SUPERCHARGING SYSTEM FOR AN INTERNAL COMBUSTION ENGINE
In a supercharging system for internal combustion engines (10) having a plurality of exhaust-gas turbochargers, electric machines (M), which are coupled to the exhaust-gas turbochargers, and adjustable distributors of the turbocharger turbines (31) are combined. As a result, the number of required electric machines and adjustable distributors can be reduced.
F02B 37/007 - Engines characterised by provision of pumps driven at least for part of the time by exhaust with exhaust-driven pumps arranged in parallel
F02B 37/04 - Engines with exhaust drive and other drive of pumps, e.g. with exhaust-driven pump and mechanically-driven second pump
F02B 37/10 - Engines with exhaust drive and other drive of pumps, e.g. with exhaust-driven pump and mechanically-driven second pump at least one pump being alternately driven by exhaust and other drive
F02B 37/24 - Control of the pumps by using pumps or turbines with adjustable guide vanes
F02B 39/10 - Non-mechanical drives, e.g. fluid drives having variable gear ratio electric
F02B 37/22 - Control of the pumps by varying the cross-section of exhaust passages or air passages
67.
REGULATION OF A SUPERCHARGING SYSTEM FOR INTERNAL COMBUSITON ENGINES
The supercharging system for an internal combustion engine comprises a plurality of exhaust-gas turbochargers which are connected in parallel to one another. One of the exhaust-gas turbochargers has an adjustable turbine guide geometry and is connected to an electric motor/generator. This results in two regulated systems, wherein the first regulated system regulates the motor/generator and the second regulated system regulates the adjustable guide geometry. A reference operating point of one exhaust-gas turbocharger is set by way of one of the two regulated systems, and the operating point of said exhaust-gas turbocharger is approximated or adapted to that of the other exhaust-gas turbochargers by way of the second regulated system.
F02B 37/007 - Engines characterised by provision of pumps driven at least for part of the time by exhaust with exhaust-driven pumps arranged in parallel
F02B 37/04 - Engines with exhaust drive and other drive of pumps, e.g. with exhaust-driven pump and mechanically-driven second pump
F02B 37/14 - Control of the pumps of the alternation between exhaust drive and other drive of a pump, e.g. dependent on speed
According to the invention, the threaded spindle (52) engages in a spindle groove (53) that is secured to an element (54) that can be displaced in a translatory manner. The element is pushed into the desired position by rotating the spindle. The adjusting ring (30) is driven by means of a sliding piston (41) having milled grooves that are arranged in parallel and that are rotationally arranged in both fish plates (33) of the groove ring.
The position control of a prerotation guide device for producing a prerotation in the suction area of a compressor, comprises an actuator (50) for displacing guide elements (20) of said prerotation guide device, and a sensor (60) that determines the current angular position of at least one guide element (20). This allows a precise, sturdy and economical detection of the angular position of the guide blades of the prerotation guide device and the guiding back thereof into a closed control circuit.
The support element is embodied as a separating wall (15), running transversely through the asymmetric flow channel. The turbine housing (10) is thus just as stable as it would be with a symmetrical shape.
The turbine housing connection includes a transition between two housing parts (10, 20) connected to one another in a detachable fashion and housing insulators (11, 22) surrounding the two housing parts. The turbine housing connection comprises a transition ring (30) surrounding the transition and disposed in a detachable fashion between the housing insulators (11, 22) of the two housing parts (20, 10) connected to one another in a detachable fashion. By removing the transition ring (30), the screws connecting the gas inlet housing (20) to the gas outlet housing (10) become accessible without the housing insulator (22) surrounding the gas inlet housing (20) needing to be removed.
The invention relates to a cleaning device for an exhaust gas turbine, comprising a cleaning receptacle (20) and a mounting device (30) for fastening the cleaning receptacle (20) to the turbine housing (10). The cleaning receptacle (20) is rotatable about an axis (A) along the mounting device (30). In this manner, the function of the cleaning device for various positions of the gas inlet connection (10) may be ensured in that said cleaning device is always as vertical as possible.
The turbine blade comprises a plurality of rotating blades (10), arranged on a hub that can be rotated about an axis. Said rotating blades comprise covering plates (20) at the radial outer ends thereof. The transition between two rotating blades arranged next to each other in the region of the covering plates is formed by a first, uneven contact surface (21) and a second, even contact surface (25). The uneven contact surface comprises a toroidal elevation with a radius of curvature R and a cross-sectional radius r, wherein R is greater than r. The contact between an uneven surface and an even surface provides for better control of the contact position and undesired stress concentrations can be avoided.
The transition between the moving blades (10) of a turbine wheel disposed next to each other between the shroud segments is divided in two regions, a simple contact region (18), which is cost-effective to machine, and a cast remaining region (19) - with arbitrary complexity. In the contact region, the power is transmitted between the moving blade ends (13). The remaining region of the transition has a gap (19) between the shroud segments (12) of the respectively adjoining moving blades, so that no contact occurs between the moving blades in this region.
The sealing assembly comprises a bore (25) in a housing (20), a plurality of seal rings (31, 32, 33) and a shaft (10). The bore (25) comprises a plurality of seats (21, 22, 23) disposed at different seat radius for the seal rings. The bore comprises for each pair of adjacent seats axially inward of an inner end of the outward seat and proximate to the inward seat a chamfer (221, 231) extending radially inwardly over an inward axial distance. The chamfer between each pair of seats allows for the radial contraction of the seal rings (31, 32, 33) upon assembly.
The invention relates to a compressor of an exhaust gas turbocharger, comprising a compressor wheel (10), a bearing housing (31), an intermediate wall (32) between the compressor wheel (10) and the bearing housing (31) and an axial bearing (33). The axial bearing (33) is fastened directly on the intermediate wall (32). Thus the assembly with the intermediate wall (32), sealing disk (22) and axial bearing (33) can be preassembled, reducing the assembly effort of the compressor.
The invention relates to a radial bearing of an exhaust gas turbocharger, said bearing being used to mount a shaft (20) in a bearing housing (30) and comprising a radial bearing bush (40) arranged between the shaft (20) and the bearing housing (30). The radial bearing bush (40, 50) is provided with a contour (45) which engages in a corresponding contour of the bearing housing (30) and interconnects the radial bearing bush (40, 50) and the bearing housing (30) in the peripheral direction in a form-fitting manner.
In order to be able to safely absorb the energy in the event of a punctured compressor wheel of an exhaust gas turbocharger, it is advantageous if the screws are as long as possible and embodied as anti-fatigue screws, thereby being able to store more energy and reduce the force peaks in all of the related turbocharger parts due to a more even spring characteristic. The aim of the invention is to provide a fixing connection which is as long as possible. To this end, the screws (5) are arranged inside the bearing housing (3), and the compressor housing (1) is directly connected to the gas outlet housing (2) of the turbine.
F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
F01D 21/04 - Shutting-down of machines or engines, e.g. in emergencyRegulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator, e.g. indicating such position
The guide apparatus of a turbine has guide vanes (31) which are mounted rotatably in the turbine housing (22, 23). A sealing sleeve (80) is arranged between the turbine housing (22) and the guide-vane stem (32). The additional axial compression spring (90) ensures that the sealing sleeve (80) is pressed continuously against the guide-vane corresponding contour (34) and the axial gap and leakage flow are suppressed as a result.
The aim of the invention is to create an optimized compressor stage for exhaust gas turbocharger applications. In particular, the connection between the muffler, the inner and outer compressor housing should be improved. Said aim is achieved by creating separate connections between the filter muffler (2) and the external compressor housing (11) as well as between the internal compressor housing (12) and the external compressor housing (11). The two separate connections are arranged on the same flange of the external compressor housing while being separated from one another.
F04B 39/00 - Component parts, details, or accessories, of pumps or pumping systems specially adapted for elastic fluids, not otherwise provided for in, or of interest apart from, groups
F16M 1/04 - Frames or casings of engines, machines, or apparatusFrames serving as machinery beds for rotary engines or similar machines
F04C 29/12 - Arrangements for admission or discharge of the working fluid, e.g. constructional features of the inlet or outlet
The aim of the invention is to integrate an emergency oil tank into a bearing housing such that in the event of an emergency stop of the motor due to a failure in the oil supply, the turbocharger rotor can be securely slowed down at any time. The emergency oil tank (2) is arranged directly over radial bearings (51, 52) enabling the compressor side radial bearing (51) and the turbine side radial bearing (52) to be supplied by a respective opening (21,22) in the tank directly under the bearing thus greatly reducing the length of the supply lines.
It is an object of the invention to improve the outflow region of an axial turbine in terms of flow using simple means. According to the invention, this is achieved in that, in an axial turbine, the housing is formed, in the outflow region from the diffuser to the gas outlet housing, as one component with a combined inner and outer flow duct. As a result of the integration of the diffuser into the gas outlet housing, a housing is created which is aerodynamically optimized and ensures a maximum flow deceleration with minimum pressure loss.
The object of the invention is to provide a compressor stage for more stringent efficiency requirements. To this end, the design of the diffusor/spiral section has been modified. In detail, a high stabilizer area (60) and integration of the insert wall and of the compressor housing are provided.
The aim of the invention is to create an optimized compressor stage for exhaust gas turbocharger applications. Said aim is achieved by a diffuser which is composed of individual blades and is mounted within the housing wall.
The aim of the invention is to improve sealing of a storage chamber of turbochargers in relation to the rear chamber of a compressor. The seal is extended about a collecting chamber (51) in the bearing housing (5). Subsequently, the seal comprises, adjacent to the collecting chamber, a type of labyrinth which is formed, for example, by at least one protruding projection (42). Finally, the seal system comprises a collecting groove (52) in the bearing housing.
The cover ring (5) radially outside the turbine blades (12) of the turbine wheel (10) is divided by slots (57) into several ring segments separated from one another in the circumferential direction. The individual segments (51) are connected via ribs (52, 53) to two peripheral rings (54, 55). The cover ring thereby loses its tangential cohesion. The cover ring thus no longer contracts in the radial direction with a sudden cooling, such as occurs during turbine washing. The turbine blades (12) can thereby be prevented from grazing the cover ring (5).
F01D 11/18 - Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion
F01D 9/04 - NozzlesNozzle boxesStator bladesGuide conduits forming ring or sector
F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
In a turbocharger multiple hollow spaces (31) occur resulting from its construction. If such hollow spaces are filled with particles, inexpensive particle vibration damper can be realized. Further, there are advantages with regard to further containment safety with possible ruptures of the compressor wheel, as well as noise reduction.
Turbine of an exhaust gas turbocharger comprising a turbine disk (11) with rotor blades (12), a nozzle ring (31) with rotor blades, and a secondary ventilation system for the cooling of turbine components (31, 32, 33) which are exposed to a primary stream (61) through the turbine, the components (31, 32, 33) of the turbine to be cooled having cooling channels (41) through which cooling air can be fed as a secondary (62) stream. The turbine is characterized in that the secondary ventilation system comprises a collecting chamber (23), the cooling channels (41) emerge from the collecting chamber (23), and cooling channels (41) are set into the rotor blades of the nozzle ring (31).
A guide device for a diffuser at the compressor wheel outlet of a radial compressor has guide blades (10, 20) with stepped inlet edges (11, 21). The step is realized by recessing the hub-side inlet edge (21). Said meridional stepping divides the guide blades into two partial blades (10, 20), of which a first partial blade (10) is longer than the second partial blade (20). The recessing of the inlet edge of the hub-side partial blade, and the associated superposition of the sound fields which are generated at the front and rear inlet edge of the diffuser, leads to an improvement of the acoustic properties of the compressor.
F01D 9/04 - NozzlesNozzle boxesStator bladesGuide conduits forming ring or sector
F02C 6/12 - Turbochargers, i.e. plants for augmenting mechanical power output of internal-combustion piston engines by increase of charge pressure
F02C 3/08 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising at least one radial stage
The preswirl guide device for generating a preswirl in the intake region of a compressor comprises a multiplicity of guide vanes (10) which can be pivoted in each case about a vane shank (12) which is connected to the guide vane, and a pivotable adjusting ring (30) and adjusting levers (13) for transmitting torque from the adjusting ring (30) to the vane shank (12) of each guide vane. The vane shank (12) and the adjusting lever (13) of each guide vane are of single-piece configuration. The housing, in which the guide vanes (10) are mounted rotatably, comprises at least two parts (41, 42) which are joined together in the region of the bearings of the guide vane. The single-piece configuration of the guide vane reduces the number of components which are to be fitted. This simplifies the fitting and possible service work on the guide device.
According to the invention, the guiding device comprising adjustable guide vanes is provided with a drive for the adjustable guide vanes. Said drive comprises a cylindrical tappet pin (6) and an adjustable lever (5) both of which are equipped with a pair of co-ordinated contact surfaces (62, 52) which, when in operation, slide onto each other when the guide vanes are adjusted. The adjusting ring (4) is displaced in order to adjust the guide vane, whereby the tappet pin which is secured to the adjusting ring slides into a longitdudinal groove (51) of the adjusting lever and exerts a force upon said adjusting lever. As a result, an easy to mount, economical and robust construction is provided, resulting in a bearing surface that has correspondingly low surface pressures and consequently greatly reduced wear and tear.
The invention relates to guide vanes which are arranged in a two or multi-part housing (32, 33). The housing separation takes place in a radial manner in the region of the bearing point (25) of the vane shaft, such that the separation joint (36) extends between the housing parts (32, 33) through the bearing openings (34) which are provided in order to receive the vane shaft. The completely round opening (34) is configured in such a manner that the bearing point of the vane shaft has a large bearing surface in each position. As a result, high surface pressures are prevented.
Depending on the actual operating situation and the composition of the fuels used for driving the internal combustion engine, contamination of the moving blades, of the guide device and of the turbine casing parts occurs sooner or later in the exhaust gas turbine. According to the invention, a small quantity of cleaning fluid is fed continuously or cyclically into the exhaust gas flow of an exhaust gas turbine and is directed onto the components to be cleaned. The small quantity of cleaning fluid can be fed in with unchanged operation of the internal combustion engine, such that the exhaust gas turbine can be cleaned or kept clean within the entire operating range of the internal combustion engine. Fluctuations in the power output of the internal combustion engine on account of requisite cleaning of the exhaust gas turbine therefore do not occur. Furthermore, the formation of thermostress cracks in the critical turbine casing parts is largely avoided.
The inventive compressor for high, specific suction capacity, comprises a compressor wheel (10) having several intermediate running blades (12, 13) per main running blade (11). As a result, the suction capacity of the compressor is increased without modifying the external dimensions. Meridional inclined inlet edges (23) of the guide vanes (21) of the diffuser support the very good aerodynamic performances, during which they maintain the strict edge mechanical and acoustic conditions. The mechanical load can be reduced on the diffuser by oscillations, and by the noise produced by the oscillations.
The rotor blades (11) and hub (10) of the compressor wheel (1) are cleaned by means of a cleaning fluid stream (72) directed along the rotational axis (A) of the compressor wheel onto the compressor wheel. The cleaning fluid stream is run towards or sprayed at the compressor wheel by a supply nozzle (51) arranged on the axis and directed along the axis in the direction of the compressor wheel. The supply stream (72) thus follows the axis and hits the rotational centre of the compressor wheel on the hub of the compressor wheel. The cleaning fluid is thus introduced on the compressor wheel at the rotational centre of the compressor wheel. The cleaning fluid thus runs along the surface of the hub and is carried radially to the radially outer regions by the centrifugal forces.
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