EP3353383A1 - Turbine munie d'un rotor de turbine en céramique - Google Patents

Turbine munie d'un rotor de turbine en céramique

Info

Publication number
EP3353383A1
EP3353383A1 EP16770489.9A EP16770489A EP3353383A1 EP 3353383 A1 EP3353383 A1 EP 3353383A1 EP 16770489 A EP16770489 A EP 16770489A EP 3353383 A1 EP3353383 A1 EP 3353383A1
Authority
EP
European Patent Office
Prior art keywords
turbine
rotor
shaft
diameter
section
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP16770489.9A
Other languages
German (de)
English (en)
Inventor
Maximilian Wutzow
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Mp-Engineering GmbH
Original Assignee
Mp-Engineering GmbH
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Mp-Engineering GmbH filed Critical Mp-Engineering GmbH
Publication of EP3353383A1 publication Critical patent/EP3353383A1/fr
Withdrawn legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/025—Fixing blade carrying members on shafts
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/026—Shaft to shaft connections
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/284—Selection of ceramic materials
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/34—Rotor-blade aggregates of unitary construction, e.g. formed of sheet laminae
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/40—Application in turbochargers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/37—Retaining components in desired mutual position by a press fit connection

Definitions

  • the invention relates to a rotor for a turbine, in particular for a turbocharger, according to the preamble of claim 1 and a turbine with such a rotor and method for producing such a rotor and such a turbine.
  • the invention relates to a rotor which is suitable for use in a turbine.
  • the runner is thus to
  • the rotor comprises a turbine wheel and a shaft fixed against rotation on the turbine wheel.
  • a working element is pushed onto the shaft of the rotor and fixed thereto.
  • the basic principle of each turbine consists in that it has the turbine wheel on its turbine side and the working element on its working side, wherein the turbine wheel and the working element are connected to one another in a rotationally fixed manner via the shaft.
  • the turbine is arranged as intended to a gas flow, that the
  • Gas flow is passed over the turbine wheel.
  • the turbine wheel is designed to be rotated by the gas flow and the working element via the shaft
  • Turbine wheel is to be supplied in the radial direction and exits the turbine wheel in the axial direction for driving the turbine.
  • axial turbines are known in which the turbine wheel is designed so that the gas flow is to be directed in the axial direction of the turbine wheel for driving the turbine wheel.
  • radial-axial turbines are known in which the turbine wheel is designed so that for driving the turbine, the gas flow is to be directed in the radial direction of the turbine wheel and exits the turbine wheel with a significant axial component, wherein the turbine wheel by both the radial gas flow as well as by the axial component of the outflowing gas flow is driven.
  • the axial direction refers to the axis about which the turbine wheel is rotatably mounted.
  • the working element is often designed as a compressor wheel, can be compressed by the air, for example
  • Power generator may be formed.
  • the turbine can be considered a turbocharger
  • turbochargers are as a radial turbine
  • Exhaust gases are directed from the engine to the turbine wheel and drive the turbine wheel to a rotation. Accordingly, the compressor wheel connected to the turbine wheel rotates, thereby compressing the intake air supplied to the engine.
  • the turbocharger thus uses the energy contained in the engine exhaust gases by being converted by the turbine wheel into rotational energy, with which the compressor then improves the air supply to the engine and thus the efficiency / performance of the engine.
  • Generic turbines have a body group comprising a housing and a rotatably mounted to the housing running gear.
  • the running gear includes the runner and the
  • the runner includes shaft and turbine wheel.
  • Generic turbochargers have such a body group, a turbine housing and a compressor housing.
  • the turbine housing is on the turbine side of the
  • Hull group arranged and adapted to direct the exhaust gases flowing from the engine to the turbine wheel to ensure the most efficient drive of the
  • the compressor housing is on the working side, also called the compressor side, the
  • Turbochargers or other turbines high speeds, for example, at large diameters, z. B. of about 80 mm, speeds of over 50,000 revolutions per minute,
  • runners must be designed so that the extremely high gas temperatures, often well over 800 ° C, which rest against the turbine wheel, cause no damage to the turbine wheel.
  • turbines are known, for example, whose rotor is a shaft made of steel and a turbine wheel of a
  • high temperature resistant metal alloy such as
  • Inconel alloy eg Inconel 713C
  • MAR alloy an alloy known as MAR alloy
  • Tool z is rotatably mounted around housing, lubricated and thereby cooled.
  • housing lubricated and thereby cooled.
  • tool z usually is a separate
  • Water cooling provided for cooling the turbocharger. When switching off the engine cooling ends by the engine oil but abruptly. Therefore are appropriate
  • Cooling measures for example, a corresponding
  • the present invention has for its object to provide a rotor for a turbine, the
  • the present invention has for its object to provide a turbine, the at least one of at least partially corrects the above problems. Furthermore, the present invention is based on the object, a method for producing such a rotor and a method for producing such a turbine
  • the invention proposes a runner with the features of claim 1.
  • Runner is suitable for use in a turbine, in particular in a turbocharger.
  • the rotor comprises a turbine rotor made of ceramic and a shaft made of metal.
  • a silicon nitride ceramics Si 3 N 4
  • Si 3 N 4 silicon nitride ceramics
  • SN-Pu material designation
  • other suitable silicon nitride ceramics are known from other manufacturers with similar material properties.
  • the shaft can be made from metal used in conventional turbochargers for the shaft be made,
  • the shaft has a hollow cylinder section.
  • the turbine rotor has a turbine wheel and a cylinder section. The turbine wheel is arranged axially relative to the axis of the cylinder section adjacent to the cylinder section.
  • Cylinder portion of the turbine rotor is in the
  • Hollow cylinder section of the shaft arranged and fixed to this.
  • the axes of the cylinder portion and the hollow cylinder portion coincide.
  • the fixation between the cylinder portion and hollow cylinder portion is preferably formed so that cylinder portion and
  • Hollow cylinder section are fixed positionally fixed to each other, so that they can perform relative to each other in the intended use of the rotor no relative movement.
  • Cylinder section can, for example, by soldering
  • the rotor extends in an axial direction, which preferably coincides with the axes of the cylinder portion and the hollow cylinder portion, from its turbine side formed by the turbine rotor to its working side formed by the shaft.
  • the runner thus has one
  • Turbine side is formed by the turbine rotor, the axial end of the rotor at the working side by the shaft.
  • the runner has, from the working side, an external thread for screwing on a nut and a fixing device accessible from the working side, which is integrated in the shaft and for fixing the runner in a rotationally fixed manner from the working side during the operation
  • Screwing the nut is formed. Depending on
  • the external thread may be formed as a left or right-hand thread.
  • the fixing device has a length in the axial direction, which corresponds at least to the diameter of the external thread of the shaft, wherein here
  • the fixing device is in particular integrally manufactured in one piece with the shaft.
  • the axial fixing device is integrally manufactured in one piece with the shaft.
  • Extent of the external thread is limited to an area outside the fixing device.
  • the fixing device thus has in particular no external thread.
  • the external thread through the fixing of the Working side of the rotor axially spaced.
  • the fixing device rests on the working side and the external thread on the fixing device.
  • the maximum diameter perpendicular to the axial direction of the fixing device is smaller than the outer diameter of the
  • the fixing device may for example be designed as a pin, which is encompassed by the shaft and is arranged to the working side next to the external thread. At such a pin can then a corresponding
  • trained fixing tool can be attached, with which the shaft is held against rotation, while a nut is screwed onto the external thread.
  • a pin has a cross-section perpendicular to the axial
  • a polygonal shape a shape with regular polygon, in particular octagonal, hexagon or square, having, as a fixing tool, a tool with a recess with a corresponding cross section
  • the pin may also have a circular cross-section and by special fixing tools, such as
  • the fixing device can also be realized by a slot or Phillips on the working side of the shaft into which a corresponding screwdriver can engage.
  • the fixing device by a radially within the shaft and axially over a certain
  • Cross section for example, oval, polygonal, regular polygon, in particular octagonal, hexagonal or square cross-section, be realized, in which then a fixing tool with a corresponding cross-section can be introduced for rotationally fixed fixing the shaft from the working side, while the mother on the
  • Fixing device is provided on the working side of the shaft and is accessible from the working side, while the nut is screwed onto the external thread, so that the shaft and thus the rotor from the working side
  • rotationally fixed by a fixing tool can be fixed while the nut is screwed onto the external thread.
  • the inventor has realized that the provision of a ceramic turbine rotor has significant advantages.
  • ceramics have a much lower density than conventionally used high temperature resistant
  • Metal alloys in one embodiment, only about 60% of the density of a conventional inconel alloy, whereby the moment of inertia of the rotor is reduced and thus the response of a turbine with a rotor according to the invention can be significantly improved compared to the response of conventional turbines.
  • Turbine used metal alloys such as
  • Inconel or MAR have a temperature resistance up to a temperature of about 980 ° C (Inconel) or about 1050 ° C (MAR), ceramics have a significantly improved temperature resistance, in particular a temperature resistance up to temperatures of 1200 ° C.
  • Inventive runners can thus be exposed to much higher temperatures on their turbine side without the turbine wheel being damaged. This can For example, be particularly advantageous for the use of inventive rotor in turbochargers, since exhaust gas streams with significantly higher exhaust gas temperatures of up to 1200 ° C can be passed to the turbine wheel, whereby the
  • the invention thus relates both to a turbine rotor made of a highly thermally conductive ceramic as well as to a turbine rotor with a poor thermal conductivity ceramic, the latter brings the advantage of a lower heat input into the housing with it.
  • the invention is further based on the finding that it is particularly advantageous if such a fixation of the working element on the rotor is ensured that regardless of a temperature-dependent expansion behavior of the working element this working element is always fixed with a constant bias as possible on the rotor.
  • the inventor has recognized that for this purpose the provision of a shaft made of steel is particularly advantageous, since the temperature-dependent expansion behavior of the shaft made of steel, a temperature-dependent expansion behavior of the
  • Working elements such as a compressor wheel made of aluminum, can be compensated so that at least over a temperature range that is relevant for the intended use of a runner realized for this purpose, as constant as possible bias on the working element for fixing the working element to the rotor
  • the invention is thus further the special finding that the combination of a turbine rotor made of ceramic with a shaft made of steel brings particular advantages. Furthermore, lies the
  • the invention is based on the recognition that s s s for the mounting of a working element on the rotor of a turbine for
  • Fixation of the rotor takes place while the nut is screwed onto the external thread to the working element
  • the inventor has recognized that the rotationally fixed fixation of the rotor via the fixing device permits a substantially precise tightening of the nut for predefined fixing of a working element to the rotor, than with a fixing via a ceramic turbine rotor or
  • the turbine rotor has one between the turbine wheel and the cylinder portion
  • Turbine rotor increases to a maximum, then over a certain axial range, the value of the maximum retains and then decreases.
  • the axial region with the value of the maximum for the diameter preferably has an axial length of not more than 2 mm, in particular 1 mm.
  • Centrifugal force undergoes and because the edge forms a trailing edge, from which via the centrifugal force
  • Turbine rotor should flow towards the turbine wheel, can not get to the turbine side of the turbine wheel. As a result, contamination of the turbine wheel driving gases can be prevented by engine oil as best as possible. In addition, this can reduce oil consumption be minimized.
  • This contact point is usually formed by the sealing rings or the sealing ring, which are arranged in the receiving groove and abut the rotor and on the housing.
  • Turbine arranged sealing rings (or sealing ring), the heat input from the exhaust gases is kept as low as possible in the housing.
  • the described embodiment of a rotor according to the invention can contribute in particular to the fact that a turbine can be realized in which no separate water cooling in addition to cooling by the engine oil is provided, since the heat input into the housing of the turbine can be kept so low that even without the Provide a separate water cooling a Overheating of the bearing between rotor and housing, which is closest to the turbine side, can be prevented.
  • due to the good sliding properties of ceramic surfaces by providing the receiving groove in the turbine rotor made of ceramic, the friction between a fixed to the housing sealing ring and an inner wall of the
  • Receiving groove on which it rests for sealing be reduced. It should be noted that friction is generated by sealing rings, which are arranged in the receiving groove. These seals are mostly fixed in position in the
  • Housing held and lie with an axial end face on an inner wall of ahmenut on. Upon rotation of the tool relative to the housing thus turns the
  • Seal rings remain fixed to the housing. It thus creates friction on the contact surfaces between sealing rings and receiving groove.
  • Ceramic turbine rotor may be due to the good
  • the turbine rotor of the relatively light ceramic extends over a wide area in which it is forced to have a large diameter in the housing. This allows the turbine rotor
  • the diameter of the first lens is in one embodiment, the diameter of the first lens
  • Turbine rotor in a axially between the cylinder portion and the centrifuge section and axially adjacent to the centrifuge section portion in the axial direction to the turbine side down. This can be made possible that in the manufacturing process of the rotor, the rotor in an area which is axially adjacent to the working side
  • Centrifuge section is arranged, can be ground to adjust as exact as possible fit this area without this, the centrifuge section is damaged, which could lead to an impairment of the function of the centrifuge section.
  • the turbine rotor axially between the cylinder portion and the centrifuge portion on a bearing portion which is formed in the manner of a cylinder and having a diameter which is greater than the diameter of the cylinder portion and smaller than the diameter at the maximum.
  • a bearing portion which is formed in the manner of a cylinder and having a diameter which is greater than the diameter of the cylinder portion and smaller than the diameter at the maximum.
  • Embodiment allows the turbine rotor with its bearing portion in a conventional radial bearing, which may be formed, for example, as a bronze bearing, in particular as a bronze ring, inserted, so that with this embodiment of the rotor according to the invention, a turbine can be realized in which the bearing portion via a radial bearing directly to the housing of the
  • Turbocharger communicates.
  • the radial bearing can then be separated only by an oil film of the bearing portion and the housing, so that the housing and the
  • Turbine rotor over a wide axial range has a large diameter, whereby a fracture of the turbine rotor can be prevented as well as possible. In addition, this allows the moment of inertia be kept even lower, whereby the response of a turbine with such a rotor can be further improved.
  • Turbine rotor on the shaft can be made via the cylinder portion and a discharge of the oil running in the bearing can be carried out through the centrifuge section, so that leakage of oil into the gases on the turbine side of the
  • Oil consumption can be minimized and pollution of the gases be largely prevented by oil.
  • Cylinder section can also be ensured that the hollow cylinder portion of the shaft on the
  • Cylinder portion can be applied without the outer diameter of the hollow cylinder needs to be provided larger than the diameter of the bearing portion. In one embodiment, the diameter of the
  • Hollow cylinder section of the shaft This may be the special one
  • Hollow cylinder portion of the shaft can be arranged, wherein both radial bearings can be formed identically and thus can be arranged in a tube designed as a tube with a constant diameter tube portion of the housing.
  • Turbine rotor decreases starting from the bearing portion in the axial direction to the turbine side, which is then arranged in the axial direction of the centrifuge section in which the diameter increases toward the turbine side, brings with it a further particular advantage.
  • the rotor may be allowed to abut on the bearing portion and the rotor
  • Hollow cylinder section can be ground simultaneously, so that the realization of an identical diameter of bearing section and hollow cylinder section can be carried out particularly precisely and easily.
  • the diameter of the first lens is in one embodiment, the diameter of the first lens
  • Turbine rotor starting from the turned to the turbine side End of the hollow cylindrical portion such a course in the axial direction that the diameter first decreases in the axial direction toward the turbine side and then increases until it is greater than that of the
  • the end of the hollow cylinder section of the shaft facing the turbine side is therefore preferably axially of the shaft
  • the diameter of the turbine rotor starting from the end of the hollow cylinder section facing the turbine side, initially decreases in the axial direction toward the turbine side, in particular steadily until it reaches a minimum, whereafter it steadily increases until the formation of the turbine
  • the diameter thus reaches after its increase its maximum when reaching the diameter of the bearing portion and retains this maximum on the axial
  • Turbine rotor can be particularly effectively ensured that the wave with its turbine facing end of its hollow cylinder portion does not exert such a notch effect on the turbine rotor, which poses a risk of breakage of the turbine rotor in the manufacture and in particular in the use of the turbine rotor in a rotor or a turbine ,
  • the inventor has recognized that it is particularly advantageous for this purpose that in the ceramic of the
  • Diameter is provided so that the outer contour of the turbine rotor from the radial center to the Turbine side facing end of the hollow cylinder portion can extend.
  • Particularly preferred is thus the tangent of the course of the diameter of the shaft, d. H. the course of the outside of the shaft, at the transition between shaft and turbine rotor identical to the tangent of the course of the diameter, d. H. the course of the outside, the turbine rotor at this transition.
  • the transition refers to the point along the axial direction, on the outside of the rotor, the shaft and the turbine rotor adjacent to each other. Due to the configuration of the described embodiment, cracking in the ceramic of the turbine rotor due to an action of the shaft is particularly effectively prevented.
  • Centrifuge section is defined, is formed rotationally symmetrical about the axial direction.
  • the inventor has further recognized that it is particularly advantageous for the production of a rotor according to the invention that in one
  • Step of the hollow cylinder portion of the shaft is pushed onto the cylinder portion of the turbine rotor for connecting shaft and turbine rotor to each other until the hollow cylinder section with its facing the turbine side axial end against the turbine rotor, in particular against the bearing portion of the turbine rotor, presses, after the fixation of the turbine rotor and Shaft to each other by means of a grinding process, such an outer contour of the rotor is generated, that the diameter of the turbine rotor starting from the turbine side facing the end of the hollow cylinder portion has such a profile in the axial direction, that the
  • Turbine side decreases and then increases until it is greater than at the end facing the turbine side of the hollow cylindrical portion, in particular the profile of the diameter of the turbine rotor between the
  • Turbine side facing end of the hollow cylindrical portion and the bearing portion has a radius of curvature which is at least a quarter of the diameter of the turbine rotor in the bearing portion.
  • the hollow cylinder portion of the shaft with its facing the turbine side axial end axially on the bearing portion of the turbine rotor directly or indirectly.
  • the turbine rotor can, for example, during the first working step, a step between
  • Turbine rotor is applied, the axial position of the shaft and turbine rotor to each other can be determined very precisely.
  • the turbine rotor and just the
  • Hollow cylinder section during the first step a sufficient material thickness and thus strength, which is particularly advantageous for the precise determination of the axial position of the shaft and turbine rotor.
  • the hollow cylinder portion of the shaft has a very small cylinder wall thickness, in particular a cylinder wall thickness between 0.4 mm and 1 mm, so that it is of considerable importance that this
  • Cylinder section of the turbine rotor needs to be matched, since the achievable axial positioning of the shaft relative to the turbine rotor not by a stop the cylinder portion at the end of the hollow cylinder portion, but by a stop of the end face of
  • Hollow cylinder section is realized on the shaft.
  • the hollow cylinder portion or the hollow of the shaft for generating the hollow cylinder portion can thus be achieved in a simple manner by rubbing or honing, as at the end of the hollow cylinder portion, d. H. at the bottom of the
  • the hollow cylinder portion of the shaft is at least 0.5 times its clear
  • the hollow cylinder portion of the shaft in its portion with which it protrudes on the working side over the cylinder portion, a through its
  • two such grooves are provided, which are provided on opposite sides, so that no imbalance arises during a rotation of the rotor.
  • two vent holes be provided, which on opposite sides and thus mirror-symmetrical to the axial direction about the axis
  • Vent holes provided, wherein the grooves and / or the vent holes are arranged in pairs symmetrically about the axis.
  • the axially extending channel or the axially extending channels can be realized by suitable measures in the rotor.
  • an axially extending channel is realized in that the cylinder section does not have a circular cross-section but one on one side
  • An axially extending groove may also be formed, for example, as a groove spiral on the outside of the cylinder portion of the turbine rotor, d. H. as a groove, which runs spirally along the outside and thus extends axially.
  • Cylinder section in the hollow cylinder section to be particularly simplified, as a result of compression of air in the hollow cylinder portion in the insertion of the
  • Cylinder section can be prevented.
  • it is essential that the clear cross-section of the at least one vent hole provided or the at least one channel provided is so large that the air from the hollow cylinder section can escape sufficiently quickly when the cylinder section in the
  • Hollow cylinder section is introduced. This is especially in the high-precision production of a rotor according to the invention of particular advantage, since in the postponement of the Hollow cylinder section on the cylinder section of
  • Hollow cylinder section can escape. It goes without saying that this is of particular advantage in a particularly advantageous embodiment of the rotor according to the invention, in which the allowance during the sliding of the hollow cylinder portion on the cylinder portion is very small, whereby a corresponding precision in the manufacture of the rotor is accompanied.
  • To be particularly advantageous has been found to provide a clear cross-section of the at least one vent hole or the at least one channel, the at least one-seventh of the clear
  • Cross-section of the interior of the hollow cylinder portion is, in particular between a fifth and a
  • Hollow cylinder portion and the greatest possible stability of the hollow cylinder portion and the cylinder portion in the hollow cylinder portion allows.
  • a plurality of vent holes and / or a plurality of grooves corresponding to the common clear cross-section of all vent holes and / or grooves at least one-seventh of the clear cross-section of the interior of the
  • Hollow cylinder portion in particular between one fifth and one seventh of the clear cross section of the interior of the hollow cylinder portion.
  • the hollow cylinder portion surrounds the shaft the cylinder section of the turbine rotor
  • Section of the hollow cylinder can cover in particular the entire cylinder portion and thus uninterrupted
  • the rotor can be configured particularly robust.
  • the shaft has at least one axial
  • Expansion portion which is offset from the hollow cylinder portion axially to the working side, wherein the
  • Diameter and the axial length of the expansion section are coordinated so that over a
  • Such an axial expansion section may enable a nut to be screwed onto the external thread of the shaft, thereby creating an expansion in the expansion section of the shaft, so that a particularly reliable fixation of the rotor in a body group can be made possible.
  • the inventor has just recognized that the provision of an axial expansion section is particularly advantageous just when a ceramic turbine rotor is used, so that the combination of a metal-made shaft with an expansion section provided there and a Ceramic-made turbine rotor brings special benefits.
  • the cylinder portion of the turbine rotor has an axial length that is between 1.5 times and 3.5 times, in particular between 2 times and 3 times the diameter of the
  • Cylinder section is. As a result, a particularly good fixation of the turbine rotor on the shaft and the use of the smallest possible amount of material can be made possible.
  • the inventor has recognized that the ratio of the length of the
  • Cylinder section is particularly relevant to the diameter of the cylinder portion, since the fixing length over which the turbine rotor is fixed to the shaft, and which is predetermined over the length of the cylinder portion, is to be provided depending on the diameter of the cylinder portion to a stable coherent runner to
  • the embodiment described is particularly advantageous in a realization of the fixation between the turbine rotor and shaft by means of shrinking the hollow cylinder portion on the cylinder portion, since it can be ensured over the specified conditions by the resulting adjustment of the pressure that the cylinder portion are completely inserted into the hollow cylinder section can before the hollow cylinder section shrinks on the cylinder portion.
  • this can be a fixation by means of adhesive or soldering a
  • the invention further relates to a turbine, the one
  • Hull group comprising a runner according to the invention.
  • the fuselage group features the runner, a housing and a
  • the rotor is arranged axially in sections within the housing and over at least two Radial bearing rotatably guided to the housing.
  • Radial bearings are preferably axially spaced from each other.
  • the radial bearings can each be connected as separate individual pieces or alternatively via connecting sections
  • the working element is arranged on the working side of the rotor facing side of the housing and fixed to the shaft. It is essential that the
  • the housing may particularly preferably have a tubular portion in which the radial bearings are arranged, wherein the rotor in the realization of the turbine by the
  • Working element arranged on the other axial side of the housing.
  • a nut working element, housing and runners axially position fes.t are screwed to each other, with the running gear can rotate relative to the housing.
  • the thrust bearing may for example comprise an intermediate piece and a bronze disk, wherein the
  • Shaft axially offset to the working side of the hollow cylinder portion has a step with which they on the
  • Bronze disc has a central passage through which passes the intermediate piece, wherein the intermediate piece has a groove in which the bronze disc is arranged, so that the bronze disc through the guide in the groove with a game of up to - led mm to the intermediate piece
  • the turbine according to the invention has the particular advantage that it has a very good response thanks to the use of the rotor according to the invention and, moreover, when using a poorly heat-conducting ceramic a smaller
  • the housing has an access for engine oil for lubricating the radial bearings, wherein the housing is designed so that it can be cooled only by the engine oil.
  • the housing can thus for example be designed so that no connection and no
  • a first of the radial bearings between the housing and the shaft is provided, wherein a second of the radial bearings between the housing and the shaft
  • Storage section is provided. This is the first one
  • Radial bearings in particular each only by an oil film of the housing and shaft and the second radial bearing in particular only by an oil film of the housing and
  • At least one of the radial bearings may be formed as a ring which has on its outer side at its annular jacket a circumferential groove, wherein in the groove circumferentially offset from each other ⁇ lzu semiconductorlöcher are provided.
  • a radial bearing is axially fixed in the housing so that a
  • Oil supply hole opens into the housing in the channel.
  • Oil supply hole in the housing is fed to the radial bearing, be particularly easy.
  • At least one sealing ring is arranged, which rests directly on the turbine rotor and directly on the housing.
  • at least one sealing ring can be ensured that as possible no engine oil that has moved axially to the turbine side over the centrifuge section out in the on the turbine wheel can flow gases.
  • two sealing rings axially adjacent to each other in the
  • the at least one sealing ring, in particular all sealing rings be designed as a piston ring.
  • the at least one sealing ring, in particular all sealing rings be made of steel.
  • the at least one sealing ring, in particular all sealing rings made of ceramic, whereby a friction between
  • Seal and runner can be kept very low.
  • the turbine comprises a nut, which is screwed onto the external thread and over which the working element is fixed to the shaft, wherein in particular the working element through the nut to a for
  • Turbine side facing side of an intermediate piece is pressed, in particular, the shaft is pressed with a radially extending projection against a working side of the intermediate piece facing side of the intermediate piece.
  • the intermediate piece may for example consist of two parts, namely an axial disc, to which the shaft is pressed, and a main piece, to which the
  • the shaft is at its
  • the fixing device is provided as a cavity in the shaft, which extends in the axial direction by at least 1 times the diameter, which of course is based on the outer diameter of the external thread radially inside the shaft.
  • suitable components of the turbine can be done.
  • the invention further relates to a method for producing a rotor according to the invention.
  • the hollow cylinder section of the shaft is pushed onto the cylinder section of the turbine rotor for
  • the hollow cylinder portion of the shaft is at a temperature of at least 300 ° C
  • Turbine rotor at a temperature between 10 ° C and 50 ° C, in particular between 15 ° C and 40 ° C held.
  • the turbine rotor is thereby kept at room temperature, i. that no tempering adjustment measure to
  • a specific temperature of the turbine rotor is made while the hollow cylinder portion is pushed onto the cylinder portion.
  • the sliding of the hollow cylinder section onto the cylinder section is completed in less than 3 s
  • inventive method allows a special
  • the invention further relates to a method for producing a rotor according to the invention, in which the
  • Method for producing a rotor according to the invention can be combined.
  • the pressing can be done directly or indirectly via a fitting body between hollow cylinder section and bearing section.
  • Embodiment is then ground after the fixation of the turbine rotor and shaft to each other, the rotor in the region of the hollow cylindrical portion and the bearing portion by a single grinding operation to produce in this area a uniform diameter of the rotor.
  • this inventive method the realization of a rotor is possible, which has a very precise constant diameter over a range at the following radial bearings can be arranged to produce a turbocharger.
  • a further preferred embodiment which is combinable with the aforementioned, is after
  • Turbine rotor between the turbine side facing the end of the hollow cylindrical portion and the bearing portion has a radius of curvature which is at least a quarter of the diameter of the turbine rotor in the bearing portion.
  • Turbine rotor can cause, be prevented.
  • the turbine rotor is particularly preferably used in the first working step
  • the said profile of the outer diameter of the turbine rotor is ground and / or the rotor, as explained, is ground in the said region for producing a uniform diameter and / or the centrifuge section and / or the receiving groove for the
  • the turbine rotor particularly preferably has a rotationally symmetrical axis at its axial end facing the turbine side
  • Centering devices for example, by a conical centering, in particular a conical
  • Recess be realized with an opening angle between 40 ° and 70 ° in the turbine rotor or the shaft.
  • the turbine rotor at his to
  • the invention further relates to a method for producing a turbine according to the invention, in particular one
  • turbocharger according to the invention.
  • the rotor is introduced with its working side in the housing and performed by the housing in a first step.
  • the working element may be preferred be kept heated.
  • the fixing device is formed as a hexagon, which during the third step with a hex wrench
  • Fixing device designed as a thread, are bolted to the two lock nuts against each other and held during the third step by a fixing tool.
  • a turbine according to the invention in particular a turbocharger according to the invention, can be produced in a particularly simple, precise and cost-effective manner.
  • FIG. 1 shows a schematic diagram of an embodiment of a rotor according to the invention
  • Figure 2 in a schematic schematic diagram
  • Figure 1 comprising the figure la and Figure lb an inventive rotor 1 is shown.
  • Figure la shows the components of the illustrated rotor 1, namely the shaft 3 and the turbine rotor 2, before they are assembled to realize the rotor 1 and fixed together.
  • FIG. 1b shows the finished rotor 1.
  • the turbine rotor 2 has a
  • Turbine wheel 26 forms the turbine side A of the rotor 1.
  • the cylinder section 21 is arranged axially offset from the working side B toward the turbine wheel 26.
  • a bearing portion 22 abuts axially directly on the cylinder portion 21, wherein a step between the cylinder portion 21 and
  • Bearing portion 22 and the turbine 26 is also a Centrifuge section 23, an edge 24 and a receiving groove 25 are arranged. From the bearing portion 22 of the takes
  • Centrifuge section 23 with a rotation of the rotor radially thrown away and rips off at the edge 24, so that only a very small proportion of this oil can ever reach into an axial region between the edge 24 and the turbine wheel 26.
  • a receiving groove 25 is provided for receiving sealing rings, via which an escape of oil from a turbine 100 can be at least largely avoided.
  • the shaft 3 has a fixing device 33 on the working side B, which adjoins the working side B in an axial direction adjacent to
  • External thread 32 is arranged on the shaft 3.
  • Fixing device 33 is thus located directly on the working side B, and the external thread 32 is spaced from the working side B by the fixing device 33.
  • the rotor 1 can thus be held against rotation by means of the fixing device 33, while a nut 8 - as shown in FIGS. 2 and 3 - is screwed onto the rotor 1 or the external thread 32 of the rotor 1 to realize a turbine.
  • the shaft 3 has an expansion section 34, in which the shaft 3 has a smaller diameter, so that the shaft is deliberately provided via this
  • Expansion section 34 by appropriately screwing a Nut 8 can be stretched on the external thread 32, so that in the realization of a turbine - as shown in Figures 2 and 3 - a controlled tightening of the rotor 1 and the compressor wheel 5 to the housing 4 is made possible.
  • the shaft 3 has a hollow cylinder section 31, in which the cylinder section 21 of the turbine rotor 2
  • the arrangement of the cylinder section 21 in the hollow cylinder section 31 ensures a reliable fixation of the turbine rotor 2 to the shaft 3.
  • the hollow cylinder portion 31 further has a vent hole 35 through which air can escape while the
  • the hollow cylinder section 31 bears against the bearing section 22 with its axial end face.
  • FIG. 2 shows an embodiment of a turbocharger 100 according to the invention as an example of an inventive device
  • turbocharger 100 is shown in its assembled state. From Figure 2 it can be seen that the turbine wheel 26 is disposed on one axial side of the housing 4, while that as
  • Working element provided compressor wheel 5 is arranged on the other axial side of the housing 4.
  • the rotor 1 is rotatable relative to the housing 4 via the radial bearings 6, 7 stored.
  • the second radial bearing 7 is that of the turbine side A closest radial bearing.
  • the first radial bearing 6 is arranged between the housing 4 and the hollow cylinder section 31.
  • the second radial bearing 7 is between the
  • Turbine rotor 2 thus extends with a large
  • Turbocharger 100 is realized, and partly because of the poorly used in this embodiment
  • the rotor 1 is fixed relative to the housing 4 by a thrust bearing comprising a bronze disk 12 and an intermediate piece, which by a main piece 9 and an axial disc 11 is formed.
  • the bronze disk 12 extends in a groove formed by the axial disk 11 and the main piece 9 of the intermediate piece and is held by the rear wall 10 on the housing 4.
  • FIG. 3 shows a further embodiment of a
  • the turbocharger 100 according to the invention according to FIG. 3 differs from the turbocharger 100 according to the invention according to FIG. 2 exclusively in the design of the rotor 1
  • the rotor 1 used in the turbocharger 100 according to FIG. 3 has no bearing section 22. Instead, the turbine rotor 2 is formed so that its first axial end is formed by the cylinder portion 21, to which the centrifuge section 23 adjoins axially. Axially in the direction of the turbine side A toward the centrifuge section 23, the turbine rotor follows
  • sealing ring is not shown in the receiving groove 25 in Figure 2.
  • the cylinder section 21 is at the in FIG. 3
  • Hollow cylinder section 31 is arranged so that the fixation between the turbine rotor 2 and shaft 3 via the arrangement of the cylinder portion 21 in the hollow cylinder portion 31 and the relative fixing of these two sections takes place to each other.
  • the fixation between the turbine rotor 2 and shaft 3 via the arrangement of the cylinder portion 21 in the hollow cylinder portion 31 and the relative fixing of these two sections takes place to each other.
  • turbocharger 100 is suitable only for certain purposes.
  • a larger heat input into the second radial bearing 7 can take place since this second radial bearing 7 is not connected exclusively via ceramic as the only heat-conducting material.
  • the turbocharger 100 according to FIG. 3 can be realized in a simple manner such that the region in which the two axial bearings 6, 7 are located has one
  • Diameter can be adjusted only by the design of the metal-made shaft 3.
  • the turbocharger 100 shown in FIG. 1 is shown in FIG. 1
  • Water cooling 41 as known in conventional turbochargers, provided.
  • FIGS. 4a, 4b and 4c schematic cross-sectional views and enlarged sections of this cross-section of a further embodiment of a rotor 1 according to the invention are shown in FIGS.
  • FIG. 4 a shows the position of the enlarged detail shown in FIG
  • FIG. 4 differs from the embodiment according to FIG. 1 in that the end of the hollow cylinder section 31 facing the turbine side A of the shaft 3 extends axially from the bearing section 22 of FIG
  • Turbine rotor 2 is spaced. This spacing is evident in particular from FIG. 4b.
  • the rotor 1 according to Figure 4 is prepared by the shaft 3 in a first step with its hollow cylindrical portion 31 on the
  • Cylinder portion 21 of the turbine rotor 2 is pushed axially until the axial, the turbine side facing A
  • Step of the runner is ground below
  • the turbine rotor 2 is ground so that its final realized diameter, starting from the axial end of the hollow cylinder portion 31, which faces the turbine side A, first decreases over a portion away, until it by the radial distance u, d. H. relative to the diameter by the distance 2 u (u in the present case is about 0.05 mm), of the diameter at the
  • Turbine rotor 2 increases again.
  • a decrease in the radius of at least 0.05 mm, in particular between 0.05 mm and 0.15 mm is particularly advantageous, ie the decrease of the diameter by at least 0.1 mm, in particular between 0.1 and 0.3 mm, before the diameter increases again.
  • the profile of the diameter of the turbine rotor 2 between the end facing the turbine side A of the hollow cylindrical portion 31 and the bearing portion 22 has a radius of curvature which is continuously at least a quarter of the diameter D of the turbine rotor 2 in the
  • Bearing portion 22 of the turbine rotor is 12 mm.
  • the embodiment of the embodiment according to FIG. 4 has the particular advantage that a notch effect of the shaft 3 at the end of its
  • ⁇ show the shaft 3 at the end of its hollow cylinder portion 31 and the turbine rotor 2 each have a diameter which such changes in function of the position along the axial direction, that the courses of the
  • Diameter of shaft 3 and turbine rotor 2 at the transition from the shaft 3 to the turbine rotor 2 have the same tangent, thereby preventing the shaft 3 is pressed with a sharp edge against the turbine rotor 2 and thus exerts an adverse notch effect on the turbine rotor 2.
  • Centrifugal section 23 abutting portion in the axial direction toward the turbine side first decreases, after which then increases the diameter under Training of the centrifuge section 23 takes place.
  • the radius in the mentioned axial section decreases by the amount v, in the present case by 0.05 mm.
  • the decrease of the radius by at least 0.05 mm, in particular between 0.05 mm and 0.15 mm is particularly advantageous, ie the decrease in the
  • FIG. 4c shows the course of the diameter, in which the radius initially decreases from the bearing section 22 by the amount v, represents the profile of the diameter in the finally produced rotor 1 according to FIG. 4a.
  • Injection molding is produced from a ceramic and then processed in a grinding process by removing the drawn in Figure 5a dashed lines allowance for generating the cylinder portion 21 of the turbine rotor 2. From Figure 5a is already apparent that the turbine rotor 2 facing on its side B to work End a first
  • Centering device 202 which are each configured in the manner of a cone. These centering devices 201, 202 serve to guide the turbine rotor 2 during the
  • Hollow cylinder section 31 is pushed axially onto the cylinder section 21.
  • the shaft 3 is held with a first mounting tool 51 and axially thereto
  • Turbine rotor 2 is displaced, while the turbine rotor 2 is held with a second mounting tool 52 which is inserted in a recess of the turbine rotor 2, in which the second centering device 202 is located.
  • This embodiment consists in that the turbine rotor 2 has at its end facing the turbine side A a cylindrical portion in which a recess is provided. This cylinder-like section and the recess are shaped like this
  • Turbine rotor 2 is guided radially without it too
  • Turbine side A facing axial end abuts the bearing portion 22 of the turbine rotor 2. This condition is shown in FIG. 5c.
  • the shaft 3 is tensioned into a collet 53, while a centering tip 54 is arranged on the centering device 202 of the turbine rotor 2, after which a rotational movement of the collet 53 then takes place
  • Figure 6 comprising Figures 6a and 6b are two examples of the configuration of the turbine wheel 26 of a
  • the turbine wheel 26 according to FIG. 6a is designed as a radial turbine wheel, the turbine wheel 26 according to FIG. 6b as an axial turbine wheel.
  • the turbine wheel 26 may alternatively be designed, for example, as an axial-radial turbine wheel.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Ceramic Engineering (AREA)
  • Materials Engineering (AREA)
  • Supercharger (AREA)

Abstract

L'invention concerne un induit (1) pour une turbine, en particulier pour un turbocompresseur, ainsi qu'un procédé de fabrication dudit induit. L'induit comprend un rotor de turbine (2) en céramique ainsi qu'un arbre (3) en métal, l'arbre présente une section cylindrique creuse (31), le rotor de turbine présente une roue de turbine (26) et une section cylindrique (21) qui est agencée dans la section cylindrique creuse et y est fixée, et l'induit s'étend dans une direction axiale à partir de son côté turbine (A) qui est formé par le rotor de turbine jusqu'à son côté travail (B) qui est formé par l'arbre. L'induit présente au niveau de son côté travail un filetage extérieur (32) permettant de visser un écrou (8) ainsi qu'un dispositif de fixation (33) accessible par le côté travail, intégré à l'arbre et conçu pour la fixation de l'induit à partir du côté travail pendant le vissage de l'écrou, le dispositif de fixation présentant en particulier une longueur en direction axiale qui correspond au moins au diamètre du filetage extérieur de l'arbre.
EP16770489.9A 2015-09-22 2016-09-22 Turbine munie d'un rotor de turbine en céramique Withdrawn EP3353383A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102015116019.6A DE102015116019A1 (de) 2015-09-22 2015-09-22 Turbine mit Keramik-Turbinenrotor
PCT/EP2016/072601 WO2017050931A1 (fr) 2015-09-22 2016-09-22 Turbine munie d'un rotor de turbine en céramique

Publications (1)

Publication Number Publication Date
EP3353383A1 true EP3353383A1 (fr) 2018-08-01

Family

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Application Number Title Priority Date Filing Date
EP16770489.9A Withdrawn EP3353383A1 (fr) 2015-09-22 2016-09-22 Turbine munie d'un rotor de turbine en céramique

Country Status (3)

Country Link
EP (1) EP3353383A1 (fr)
DE (1) DE102015116019A1 (fr)
WO (1) WO2017050931A1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102022129324B3 (de) 2022-11-07 2024-02-08 Dr. Ing. H.C. F. Porsche Aktiengesellschaft Rotor für eine Ladeeinrichtung

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3039961A1 (de) * 1980-10-23 1982-06-03 Volkswagenwerk Ag, 3180 Wolfsburg Laufzeug fuer eine gasturbinenanlage, insbesondere fuer einen abgasturbolader eines fahrzeugantriebs
US4486147A (en) * 1982-04-20 1984-12-04 The Garrett Corporation Turbocharger and rotor shaft assembly
JPS6019915A (ja) * 1983-07-12 1985-02-01 Toyota Motor Corp セラミックスと金属の組合せよりなるタービン組立体
US4719074A (en) * 1984-03-29 1988-01-12 Ngk Insulators, Ltd. Metal-ceramic composite article and a method of producing the same
JPS618410A (ja) * 1984-06-25 1986-01-16 Toyota Central Res & Dev Lab Inc タ−ボチヤ−ジヤロ−タ
JPS6119903A (ja) * 1984-07-06 1986-01-28 Honda Motor Co Ltd 軸付タ−ビン翼車
JPS61286501A (ja) * 1985-06-12 1986-12-17 Ngk Insulators Ltd タ−ビンロ−タ−およびその製造法
JPS6278401A (ja) * 1985-10-02 1987-04-10 Ngk Spark Plug Co Ltd セラミツクロ−タ−
JPS62191478A (ja) * 1986-02-19 1987-08-21 日本碍子株式会社 セラミツクス・金属結合体
DE3625996A1 (de) * 1986-07-31 1988-02-04 Kuehnle Kopp Kausch Ag Laufzeug fuer einen abgasturbolader
DE3816796A1 (de) * 1988-05-17 1989-11-30 Kempten Elektroschmelz Gmbh Laufzeug mit mechanischer kupplung
US9051873B2 (en) * 2011-05-20 2015-06-09 Icr Turbine Engine Corporation Ceramic-to-metal turbine shaft attachment
DE102014200738A1 (de) * 2014-01-16 2015-07-16 Bosch Mahle Turbo Systems Gmbh & Co. Kg Turbinenrotor

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WO2017050931A1 (fr) 2017-03-30
DE102015116019A1 (de) 2017-03-23

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