EP2375000B1 - Shaft seal - Google Patents
Shaft seal Download PDFInfo
- Publication number
- EP2375000B1 EP2375000B1 EP11159510.4A EP11159510A EP2375000B1 EP 2375000 B1 EP2375000 B1 EP 2375000B1 EP 11159510 A EP11159510 A EP 11159510A EP 2375000 B1 EP2375000 B1 EP 2375000B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- shaft
- bearing housing
- oil
- seal
- shaft seal
- 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.)
- Active
Links
- 238000007789 sealing Methods 0.000 claims description 37
- 239000000463 material Substances 0.000 claims description 11
- 239000003921 oil Substances 0.000 description 81
- 239000007789 gas Substances 0.000 description 61
- 239000007921 spray Substances 0.000 description 11
- 238000004939 coking Methods 0.000 description 8
- 238000001816 cooling Methods 0.000 description 8
- 238000002485 combustion reaction Methods 0.000 description 6
- 230000000694 effects Effects 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 238000005461 lubrication Methods 0.000 description 3
- 238000004140 cleaning Methods 0.000 description 2
- 230000005484 gravity Effects 0.000 description 2
- 239000000314 lubricant Substances 0.000 description 2
- 239000010687 lubricating oil Substances 0.000 description 2
- 230000000149 penetrating effect Effects 0.000 description 2
- 229910001060 Gray iron Inorganic materials 0.000 description 1
- 230000004888 barrier function Effects 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 239000000571 coke Substances 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
- 239000004020 conductor Substances 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 238000002156 mixing Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000035515 penetration Effects 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
- 238000013022 venting Methods 0.000 description 1
Images
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
- F02B39/00—Component parts, details, or accessories relating to, driven charging or scavenging pumps, not provided for in groups F02B33/00 - F02B37/00
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- 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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/003—Preventing or minimising internal leakage of working-fluid, e.g. between stages by packing rings; Mechanical seals
-
- 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
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
- F01D25/125—Cooling of bearings
-
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/18—Lubricating arrangements
-
- 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
- F01D25/18—Lubricating arrangements
- F01D25/183—Sealing means
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
- F02B39/00—Component parts, details, or accessories relating to, driven charging or scavenging pumps, not provided for in groups F02B33/00 - F02B37/00
- F02B39/14—Lubrication of pumps; Safety measures therefor
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- 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
- F05D2240/00—Components
- F05D2240/55—Seals
- F05D2240/58—Piston ring seals
-
- 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
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/205—Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes
Definitions
- the invention relates to the field of turbomachines, in particular the exhaust gas turbochargers acted upon by exhaust gases from internal combustion engines.
- exhaust gas turbochargers are used by default, with a turbine in the exhaust system of the internal combustion engine and with the internal combustion engine upstream compressor, which is connected to the turbine via a common shaft.
- the energy bound in the exhaust gas of an internal combustion engine can be converted by means of a power turbine into electrical or mechanical energy.
- a generator or a mechanical consumer is connected to the turbine shaft.
- an exhaust gas turbocharger is composed of a rotor, consisting of a shaft, a compressor wheel and a turbine wheel, a bearing for the shaft, flow-guiding housing parts (compressor housing or turbine housing) and the bearing housing.
- the shaft of the exhaust gas turbocharger with respect to the cavity of the bearing housing with an appropriate sealing concept is sealed.
- the internal pressure in the cavity of the bearing housing usually corresponds to the atmospheric pressure.
- the gas pressure in the flow channel of the compressor or turbine side depends on the current operating point of the exhaust gas turbocharger and is in most Operating points above the pressure in the cavity of the bearing housing. In certain cases, however, is also to be expected with a negative pressure, for example, in partial load operation or at a standstill.
- a turbine-side shaft seal of an exhaust gas turbocharger which is composed of a simple oil catch chamber on the turbine side of the radial bearing and a piston ring with sealing action between the shaft and the bearing housing.
- the bearing oil exiting axially from the radial bearing sprays onto the outwardly offset and rotating shaft shoulder and is thrown by centrifugal forces into the oil-collecting chamber.
- the bearing oil thus thrown off then flows downwards in accordance with gravity within the oil catching chamber and then back into the oil circuit of the bearing lubrication.
- piston rings of metal such as gray cast iron, are used by default.
- the live piston ring is clamped in a radial groove with an axial stop shoulder in the bearing housing.
- the rotating shaft is provided with a radial groove, wherein the piston ring is axially caught within this groove and this covers radially. Due to the differential pressure between the exhaust pressure and the pressure inside the bearing housing, the piston ring is axially displaced in the direction of the existing pressure gradient within the groove to stop. Due to the axial support of the piston ring on one of the Nutinnen designs this grinds and seals the Lagergephase relative to the exhaust flow.
- a first seal in the form of a gap, a labyrinth or a piston ring and a second seal in the form of a narrow gap or a labyrinth are provided, which between them include an annularly around the circumference of the rotor shaft extending oil drain channel, which by means of a housing side ⁇ lablaufnut and arranged in a coaxial position shaft side ⁇ lablaufnut is constructed.
- oil drain passage in the radial direction of the rotor shaft is provided with one end freely projecting into the annular oil drain passage annular sealing ridge, which acts in the axial direction barrier for in represents the oil drain passage penetrating lubricant and radially overlaps the gap of the second seal.
- An exhaust-gas turbocharger which consists of a two-part bearing housing, in which oil is injected from a first part for cooling on the surface of the second part.
- An exhaust gas turbocharger which has an annular sealing plate as oil splash protection in the region of an axial bearing in the back of the compressor wheel.
- the present invention has for its object to provide a shaft seal mounted in a bearing housing shaft of a turbomachine in which the flow behavior of the lubricating oil improves and the risk of coking the piston ring seal can be minimized by active cooling of the seal section.
- the shaft seal according to the invention of a shaft of a turbomachine mounted in a bearing housing between a cavity in the bearing housing and a wheel back of an impeller of the turbomachine comprises a plurality of seals.
- a first, impeller-side seal which may be formed, for example in the form of at least one piston ring
- a second, bearing-side seal which may be formed, for example in the form of a sealing gap between the bearing housing and the shaft.
- an oil drain chamber is arranged, which is bounded by a third, middle seal, which is formed for example in the form of a sealing gap between the bearing housing and the shaft.
- a gas outlet chamber is arranged between the third seal and the first impeller-side seal.
- the third seal separates the two media oil from the oil drain chamber from the gas from the gas outlet chamber cleanly, whereby the risk of coking in the oil drain chamber can be minimized since the two media do not meet one another within the same collection chamber.
- Both media are separated by the third seal separated from each other by at least two drain channels in Lagergeophuseplenum.
- the inventive shaft seal is also actively cooled by at least one obliquely oriented spray oil device, with no spray oil to get into the drain chambers.
- the shaft seal is structurally designed so that as much spray oil keeps the material temperatures of the bearing housing and the optional insert and the built-in piston rings low and prevents coking of the oil in the various drain chambers.
- That region of the bearing housing which is part of the shaft seal formed according to the invention may be formed as an insert.
- the insert can be easily replaced during operational wear or removed but for cleaning purposes for a short time from the bearing housing.
- a material with the highest possible heat conduction property to choose as the material for this insert a material with the highest possible heat conduction property.
- that region of the shaft which is part of the shaft seal constructed in accordance with the invention and whose contour forms the oil drain chamber and the gas outlet chamber together with the bearing housing can be designed as a sleeve-shaped attachment rotating with the shaft.
- This essay can be up the shaft shrunk, screwed or otherwise connected positively and / or non-positively with the shaft.
- the attachment is optionally made of a material which compared to the material of the shaft has an improved thermal conductivity or an increased insulating effect. In this way, a potential ⁇ lverkokung can be prevented in the oil drainage grooves.
- Fig. 1 shows an exhaust gas turbocharger according to the prior art with a centrifugal compressor 90 and a radial turbine 10.
- the housing of the exhaust gas turbocharger shown is shown partially cut away to see the rotor with the compressor 91, the shaft 20 and the turbine wheel 11 can.
- the air flow from the air inlet 92 via the compressor wheel 91 to the air outlet 93 and the gas flow from the gas inlet 12 via the turbine wheel 11 to the gas outlet 13 are indicated by thick arrows.
- the shaft 20 is rotatably mounted in the bearing housing 30, usually by means of two radial bearings and at least one thrust bearing.
- Fig. 2 shows an enlarged view of an exhaust gas turbocharger or a power turbine in the region of the turbine-side radial bearing 34.
- the inventively designed shaft seal is arranged, which separates the cavity 50 in the bearing housing from the Radraum 15 of the turbine wheel 11.
- the bearing housing in the region of the shaft seal comprises an insert piece 31 (sealing bushing), which is realized as a separate component.
- the insert 31 is ring-shaped and comprises a radially outer oil drainage channel 52 for the projecting radially outward from the radial bearing 34 and laterally discharged spray oil. The insert is sprayed directly or indirectly with spray oil and thereby actively cooled.
- the spray oil is passed through the oil spray device 61 to the components to be cooled.
- the oil spray device 61 is performed and aligned in the illustrated embodiment as a bore such that the spray oil in the region of the bearing housing 30 on the inner contour 63 meets and the insert in the region of the oil drainage channel 52nd wetted.
- the insert 31 is optionally made of a material with the highest possible heat-conducting property.
- the components of the shaft seal 31, 30, 41, 42 can be separated from the hot turbine rear wall 11 and wheel back 15 by an additional heat plate 70.
- the heat sheet 70 is arranged in the region of the Radschreibraumes 15 between the hot turbine rear wall 11 and the insert piece 31 of the shaft seal.
- the heat sheet is in the radially inner region with a support surface 71 on the insert 31.
- the oil drainage channel 52 is bounded in the axial direction by a radially extended sealing plate 32, which in turn is itself cooled by the oil in the outlet channel 51.
- the insert further comprises recesses for receiving two series-arranged piston rings 41 and 42, which are known per se and whose operation is described in the beginning in the prior art.
- the insert further comprises in the radially inner region of an oil drain chamber 53, a separate gas outlet chamber 55 for the gas leakage from the two piston rings 41 and 42 and a sealing ridge 33 which the oil drain chamber 53 and the gas outlet chamber 55 separates from each other.
- the oil drainage channel 51 between the radial bearing 34 and the sealing plate 32 forms the first main drainage channel of the bearing oil emerging from the radial bearing.
- the sealing plate 32 forms with a radially opposite first web 21 of the shaft 20 has a first radial sealing gap 43, due to which penetration of the bearing oil from the oil drainage channel 51 is minimized in the oil drain chamber 53.
- the rotating wave contour of the oil drain chamber 53 is provided with a radially inwardly offset drainage groove, resulting in two drainage edges left and right of this groove within the oil drain chamber 53.
- the thrown by the Abspritzkanten in the formed by the groove in the insert 31, radially outer region of the oil drain chamber 53 thrown oil flows due to gravity within the oil drain chamber 53 along the contour of the insert 31 down.
- the bearing oil from the oil drain chamber 53 can be returned to the oil circuit of the bearing lubrication, the oil drain chamber 53 at the bottom of at least one oil drain passage 54.
- the insert 31 of the shaft seal according to the invention is characterized by a gas outlet chamber 55 arranged next to the oil drain chamber 53 and separated from the oil drain chamber 53 by a peripheral sealing ridge 33.
- the annular gas discharge chamber 55 is used for collecting the hot gas flowing through the piston rings 41 and 42.
- the sealing ridge 33 forms with a radially opposite second web 22 of the shaft 20 a second radial sealing gap 44.
- the sealing gap 44 separates the two media oil from the oil drain chamber 53 from the gas from the gas outlet chamber 55 cleanly.
- the gas collected in the gas outlet chamber 55 is in turn transferred through at least one separate gas outlet channel 56 within the insert 31 and separated from the oil drain channel 54 into the common volume of the cavity 50 in the bearing housing.
- the main portion of the bearing oil emerging from the radial bearing 34 is discharged to the outside through the large oil drainage channel 51 and the first sealing point 43 and kept away from the piston ring section via the oil drainage channel 52.
- the outlets of the at least one oil drain channel 54 and the gas outlet channel 56 are offset in the circumferential direction, as shown in the FIG. 3 and FIG. 4 is shown.
- Fig. 3 shows a bottom view of the insert 31 without shaft and adjacent housing parts.
- the bottom of the insert leading out openings of the two oil drain channels 54 and the gas outlet channel 56 are offset axially and in particular in the circumferential direction.
- Fig. 4 shows in the guided along IV-IV section, the drainage channels and the radially inwardly projecting sealing plate 32 and in the region of the gas outlet channel 56 also radially inwardly projecting sealing ridge 33.
- the offset channel outlets lead to greater strength of the insert.
- the seals 43 and 44 are designed as radial sealing gaps.
- these seals can be supplemented or replaced with piston ring seals or other sealing elements.
- the bearing housing may be formed in the region of the shaft seal designed according to the invention without a separate insert piece.
- the corresponding grooves, sealing plates and sealing webs are embedded directly in the bearing housing.
- the embodiment described in detail with separate insert has the advantage that the insert for the purpose of cooling the sealing part of a material with good thermal conductivity (eg Ck45) can be made and thus is independent of the bearing housing material used (eg GGG -40). Further, an insert is easy to replace in case of operational wear or remove it for cleaning purposes for a short time from the bearing housing.
- the rotating shaft contour of the turbine in the region of the shaft seal formed according to the invention are executed by a sleeve-shaped attachment 81.
- the attachment 81 is shrunk onto a seat 82 on the shaft, and an edge formed on the shaft serves as an axial stop 83 for the attachment.
- the attachment and the shaft seat are to be designed such that the heat discharge via the oil cooling maximizes and the heat input via the shrink fit on the Wave is minimized.
- the article is therefore to be made of a good heat conducting material.
- the attachment 81 can also be fastened in a non-positive and / or positive-locking manner on the shaft, for example by means of a screw connection (thread) between the attachment and the shaft.
- the shaft seal comprises two piston rings 41 and 42.
- only one piston ring may be provided, or further piston rings may be provided in the region or other locations of the shaft seal.
- the embodiment shown and described in detail shows the inventive shaft seal formed on the turbine side of an exhaust gas turbocharger or a power turbine.
- the shaft seal formed according to the invention can also be used analogously on the compressor side of an exhaust-gas turbocharger, or also in any other turbomachine.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Supercharger (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Description
Die Erfindung bezieht sich auf das Gebiet der Strömungsmaschinen, insbesondere der mit Abgasen von Brennkraftmaschinen beaufschlagten Abgasturboladern.The invention relates to the field of turbomachines, in particular the exhaust gas turbochargers acted upon by exhaust gases from internal combustion engines.
Sie betrifft eine Wellenabdichtung einer solchen Strömungsmaschine.It relates to a shaft seal of such a turbomachine.
Für die Leistungssteigerung einer Verbrennungskraftmaschine werden heutzutage standardmässig Abgasturbolader eingesetzt, mit einer Turbine im Abgastrakt der Verbrennungskraftmaschine und mit einem der Verbrennungskraftmaschine vorgelagerten Verdichter, welcher mit der Turbine über eine gemeinsame Welle verbunden ist. Mit der Aufladung eines Verbrennungsmotors mittels Abgasturbolader wird die Füllmenge und somit das Kraftstoffgemisch in den Zylindern erhöht und daraus ein merklicher Leistungsanstieg für den Motor gewonnen. Optional kann die im Abgas eines Verbrennungsmotors gebundene Energie mittels einer Nutzturbine in elektrische oder mechanische Energie gewandelt werden. Dabei ist anstelle eines Verdichters wie beim Abgasturbolader ein Generator oder ein mechanischer Verbraucher an der Turbinewelle angeschlossen.For the increase in performance of an internal combustion engine today exhaust gas turbochargers are used by default, with a turbine in the exhaust system of the internal combustion engine and with the internal combustion engine upstream compressor, which is connected to the turbine via a common shaft. With the charging of an internal combustion engine by means of an exhaust gas turbocharger, the filling quantity and thus the fuel mixture in the cylinders is increased, and from this a considerable increase in power for the engine is obtained. Optionally, the energy bound in the exhaust gas of an internal combustion engine can be converted by means of a power turbine into electrical or mechanical energy. In this case, instead of a compressor as in the exhaust gas turbocharger, a generator or a mechanical consumer is connected to the turbine shaft.
Ein Abgasturbolader setzt sich standardmässig aus einem Rotor, bestehend aus einer Welle, einem Verdichterrad und einem Turbinenrad, aus einer Lagerung für die Welle, aus strömungsführenden Gehäuseteilen (Verdichtergehäuse resp. Turbinengehäuse) und aus dem Lagergehäuse zusammen.As standard, an exhaust gas turbocharger is composed of a rotor, consisting of a shaft, a compressor wheel and a turbine wheel, a bearing for the shaft, flow-guiding housing parts (compressor housing or turbine housing) and the bearing housing.
Aufgrund des hohen Prozessdruckes im turbinen- wie auch verdichterseitigen Strömungsbereich ist die Welle des Abgasturboladers gegenüber dem Hohlraum des Lagergehäuses mit einem passenden Dichtkonzept abzudichten. Der Innendruck im Hohlraum des Lagergehäuses entspricht üblicherweise dem atmosphärischen Druck. Der Gasdruck im Strömungskanal der Verdichter- respektive Turbinenseite hängt dagegen vom aktuellen Betriebspunkt des Abgasturboladers ab und liegt in den meisten Betriebspunkten über dem Druck im Hohlraum des Lagergehäuses. In gewissen Fällen ist aber auch mit einem Unterdruck zu rechnen, z.B. im Teillastbetrieb oder bei Stillstand.Due to the high process pressure in the turbine as well as on the compressor side flow region, the shaft of the exhaust gas turbocharger with respect to the cavity of the bearing housing with an appropriate sealing concept is sealed. The internal pressure in the cavity of the bearing housing usually corresponds to the atmospheric pressure. The gas pressure in the flow channel of the compressor or turbine side, however, depends on the current operating point of the exhaust gas turbocharger and is in most Operating points above the pressure in the cavity of the bearing housing. In certain cases, however, is also to be expected with a negative pressure, for example, in partial load operation or at a standstill.
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Zur Reduktion der Gasleckage aus dem Strömungskanal durch den Radrückraum der Turbine in den Hohlraum des Lagergehäuses werden standardmässig Kolbenringe aus Metal, beispielsweise Grauguss, eingesetzt. Der unter Spannung stehende Kolbenring wird in einer radialen Nut mit axialer Anschlagschulter im Lagergehäuse verspannt. Als Gegenstück zum Kolbenring wird die rotierende Welle mit einer radialen Nut versehen, wobei der Kolbenring innerhalb dieser Nut axial gefangen ist und diese radial überdeckt. Aufgrund des Differenzdrucks zwischen dem Abgasdruck und dem Druck im Inneren des Lagergehäuses wird der Kolbenring in Richtung des vorhandenen Druckgradienten innerhalb der Nut axial auf Anschlag verschoben. Durch die axiale Auflage des Kolbenrings an einer der Nutinnenfläche schleift sich dieser ein und dichtet das Lagergehäuseplenum relativ zur Abgasströmung ab. Zur Verbesserung der Dichtwirkung können auch zwei oder mehr Kolbenringe eingesetzt werden, wie dies etwa in
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Dem entgegenzuwirken versucht die in
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Bei allen beschriebenen, turbinenseitigen Wellenabdichtkonzepten besteht unter gewissen Umständen die Gefahr, dass heisse Gase aus dem Radrückraum der Abgasturbine durch die Kolbenringabdichtung entweichen, und das im Kolbenringbereich sowie der Ölablaufnuten verbleibende Lageröl lokal verbrennt und dadurch eine starke Verkokung der Wellenabdichtung und damit verbundenem Verschleiss verursacht. Die Verkokungsgefahr nimmt mit steigender Abgastemperatur und erhöhter Gasleckage durch die Kolbenringe sowie schlechter Bauteilkühlung zu. So ist eine aktive Kühlung dieser Dichtungspartie entscheidend für die Betriebssicherheit der Wellenabdichtung.In all the turbine-side shaft sealing concepts described, under certain circumstances there is the danger that hot gases will escape from the wheel rear space of the exhaust gas turbine through the piston ring seal, burning the bearing oil remaining in the piston ring region and the oil drain grooves locally, thereby causing strong coking of the shaft seal and associated wear. The risk of coking increases with increasing exhaust gas temperature and increased gas leakage through the piston rings as well as poor component cooling. Thus, an active cooling of this seal section is crucial for the reliability of the shaft seal.
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Aus
Der vorliegenden Erfindung liegt die Aufgabe zugrunde, eine Wellenabdichtung einer in einem Lagergehäuse gelagerten Welle einer Strömungsmaschine zu schaffen bei welcher das Ablaufverhalten des Schmieröls verbessert sowie die Verkokungsgefahr der Kolbenringabdichtung durch aktive Kühlung der Dichtungspartie minimiert werden kann.The present invention has for its object to provide a shaft seal mounted in a bearing housing shaft of a turbomachine in which the flow behavior of the lubricating oil improves and the risk of coking the piston ring seal can be minimized by active cooling of the seal section.
Die erfindungsgemässe Wellenabdichtung einer in einem Lagergehäuse gelagerten Welle einer Strömungsmaschine zwischen einem Hohlraum im Lagergehäuse und einem Radrückraum eines Laufrades der Strömungsmaschine umfasst mehrere Dichtungen. Eine erste, laufradseitige Dichtung, welche beispielsweise in Form mindestens eines Kolbenrings ausgebildet sein kann, sowie eine zweite, lagerseitige Dichtung, welche beispielsweise in Form eines Dichtspaltes zwischen dem Lagergehäuse und der Welle ausgebildet sein kann. Zwischen der laufradseitigen Dichtung und der lagerseitigen Dichtung ist eine Ölablaufkammer angeordnet, welche von einer dritten, mittleren Dichtung, die beispielsweise in Form eines Dichtspaltes zwischen dem Lagergehäuse und der Welle ausgebildet ist, begrenzt ist. Zwischen der dritten Dichtung und der ersten, laufradseitigen Dichtung ist zudem erfindungsgemäss eine Gasaustrittskammer angeordnet. Die dritte Dichtung trennt erfindungsgemäss die beiden Medien Öl aus der Ölablaufkammer vom Gas aus der Gasaustrittskammer sauber ab wodurch die Verkokungsgefahr in der Ölablaufkammer minimiert werden kann, da die beiden Medien nicht innerhalb der gleichen Sammelkammer aufeinander treffen. Beide Medien werden durch die dritte Dichtung getrennt voneinander durch mindestens zwei Ablaufkanäle seitlich ins Lagergehäuseplenum abgeleitet. Die erfindungsgemässe Wellenabdichtung wird zudem durch mindestens eine schräg ausgerichtete Spritzölvorrichtung aktiv gekühlt, wobei kein Spritzöl in die Ablaufkammern gelangen soll. Die Wellenabdichtung ist konstruktiv so gestaltet, dass möglichst viel Spritzöl die Materialtemperaturen des Lagergehäuses sowie des optionalen Einsatzstücks und den darin eingebauten Kolbenringen gering hält und eine Verkokung des Öls in den diversen Ablaufkammern unterbindet.The shaft seal according to the invention of a shaft of a turbomachine mounted in a bearing housing between a cavity in the bearing housing and a wheel back of an impeller of the turbomachine comprises a plurality of seals. A first, impeller-side seal, which may be formed, for example in the form of at least one piston ring, and a second, bearing-side seal, which may be formed, for example in the form of a sealing gap between the bearing housing and the shaft. Between the impeller-side seal and the bearing-side seal, an oil drain chamber is arranged, which is bounded by a third, middle seal, which is formed for example in the form of a sealing gap between the bearing housing and the shaft. In addition, according to the invention, a gas outlet chamber is arranged between the third seal and the first impeller-side seal. According to the invention, the third seal separates the two media oil from the oil drain chamber from the gas from the gas outlet chamber cleanly, whereby the risk of coking in the oil drain chamber can be minimized since the two media do not meet one another within the same collection chamber. Both media are separated by the third seal separated from each other by at least two drain channels in Lagergehäuseplenum. The inventive shaft seal is also actively cooled by at least one obliquely oriented spray oil device, with no spray oil to get into the drain chambers. The shaft seal is structurally designed so that as much spray oil keeps the material temperatures of the bearing housing and the optional insert and the built-in piston rings low and prevents coking of the oil in the various drain chambers.
Optional kann derjenige Bereich des Lagergehäuses, welcher Teil der erfindungsgemäss ausgebildeten Wellenabdichtung ist, als ein Einsatzstück ausgebildet sein. Das Einsatzstück kann bei betriebsbedingter Abnutzung leicht ersetzt oder aber etwa zu Reinigungszwecken kurzzeitig aus dem Lagergehäuse ausgebaut werden. Zudem ist als Material für dieses Einsatzstück ein Werkstoff mit möglichst hoher Wärmeleiteigenschaft zu wählen.Optionally, that region of the bearing housing which is part of the shaft seal formed according to the invention may be formed as an insert. The insert can be easily replaced during operational wear or removed but for cleaning purposes for a short time from the bearing housing. In addition, to choose as the material for this insert a material with the highest possible heat conduction property.
Optional kann derjenige Bereich der Welle, welcher Teil der erfindungsgemäss ausgebildeten Wellenabdichtung ist und mit seiner Kontur zusammen mit dem Lagergehäuse die Ölablaufkammer sowie die Gasaustrittskammer bildet, als ein mit der Welle mitrotierender, hülsenförmiger Aufsatz ausgebildet sein. Dieser Aufsatz kann auf die Welle aufgeschrumpft, aufgeschraubt oder auf andere Weise form- und/ oder kraftschlüssig mit der Welle verbunden werden. Der Aufsatz ist optional aus einem Material gefertigt, welches gegenüber dem Material der Welle eine verbesserte Wärmeleitfähigkeit oder eine erhöhte isolierenden Wirkung aufweist. Auf diese Weise kann eine potentielle Ölverkokung in den Ölablaufrillen unterbunden werden kann.Optionally, that region of the shaft which is part of the shaft seal constructed in accordance with the invention and whose contour forms the oil drain chamber and the gas outlet chamber together with the bearing housing can be designed as a sleeve-shaped attachment rotating with the shaft. This essay can be up the shaft shrunk, screwed or otherwise connected positively and / or non-positively with the shaft. The attachment is optionally made of a material which compared to the material of the shaft has an improved thermal conductivity or an increased insulating effect. In this way, a potential Ölverkokung can be prevented in the oil drainage grooves.
Nachfolgend wird die erfindungsgemässe Wellenabdichtung anhand von Zeichnungen detailliert erläutert. Dabei zeigt
- Fig. 1
- eine teilweise aufgeschnittene Ansicht eines Abgasturboladers gemäss dem Stand der Technik mit einem Radialverdichter und einer Radialturbine,
- Fig. 2
- einen entlang der Welle geführten Schnitt durch eine erfindungsgemäss ausgebildete, turbinenseitige Wellenabdichtung eines Abgasturboladers nach
Fig. 1 , - Fig. 3
- eine Ansicht von unten auf ein Gehäuseteil einer zweiten Ausführungsform der Wellenabdichtung nach
Fig. 2 , - Fig. 4
- einen entlang IV-IV geführten Schnitt durch das Gehäuseteil nach
Fig. 3 , und - Fig. 5
- die Wellenabdichtung gemäss
Fig. 2 mit einem auf der Welle aufgeschrumpften Aufsatz.
- Fig. 1
- a partially cutaway view of an exhaust gas turbocharger according to the prior art with a centrifugal compressor and a radial turbine,
- Fig. 2
- a guided along the shaft section through an inventively designed, turbine-side shaft seal of an exhaust gas turbocharger after
Fig. 1 . - Fig. 3
- a view from below of a housing part of a second embodiment of the shaft seal according to
Fig. 2 . - Fig. 4
- a guided along IV-IV section through the housing part
Fig. 3 , and - Fig. 5
- the shaft seal according to
Fig. 2 with an essay shrunk on the shaft.
Die Ölablaufrinne 51 zwischen dem Radiallager 34 und der Dichtplatte 32 bildet den ersten Hauptablaufkanal des aus dem Radiallager austretenden Lageröls. Die Dichtplatte 32 bildet mit einem radial gegenüberliegenden ersten Steg 21 der Welle 20 einen ersten radialen Dichtspalt 43, aufgrund dessen ein Eindringen des Lageröls aus der Ölablaufrinne 51 in die Ölablaufkammer 53 minimiert wird. Die rotierende Wellenkontur der Ölablaufkammer 53 ist mit einer radial nach Innen versetzten Ablaufnut versehen, wodurch sich innerhalb der Ölablaufkammer 53 zwei Abspritzkanten links und rechts dieser Nut ergeben. Das durch die Abspritzkanten in den durch die Nut im Einsatzstück 31 gebildeten, radial äusseren Bereich der Ölablaufkammer 53 geschleuderte Öl fliesst aufgrund der Schwerkraft innerhalb der Ölablaufkammer 53 entlang der Kontur des Einsatzstücks 31 nach unten. Damit das Lageröl aus der Ölablaufkammer 53 in den Ölkreislauf der Lagerschmierung zurückgeführt werden kann, weist die Ölablaufkammer 53 im unteren Bereich mindestens einen Ölablaufkanal 54 auf.The oil drainage channel 51 between the
Das Einsatzstück 31 der erfindungsgemäss ausgebildeten Wellenabdichtung zeichnet sich durch eine neben der Ölablaufkammer 53 angeordnete Gasaustrittskammer 55 aus, die von der Ölablaufkammer 53 durch einen umlaufenden Dichtsteg 33 abgetrennt ist. Die ringförmig ausgebildete Gasaustrittskammer 55 wird für das Sammeln des durch die Kolbenringe 41 und 42 durchströmenden heissen Gases verwendet. Der Dichtsteg 33 bildet mit einem radial gegenüberliegenden zweiten Steg 22 der Welle 20 einen zweiten radialen Dichtspalt 44. Der Dichtspalt 44 trennt erfindungsgemäss die beiden Medien Öl aus der Ölablaufkammer 53 vom Gas aus der Gasaustrittskammer 55 sauber ab. Das in der Gasaustrittskammer 55 aufgefangene Gas wird wiederum durch mindestens einen separaten Gasablaufkanal 56 innerhalb des Einsatzstücks 31 und getrennt vom Ölablaufkanal 54 ins gemeinsame Volumen des Hohlraums 50 im Lagergehäuse überführt. Durch die gezielte Trennung der beiden Abläufe soll eine Vermischung der beiden Medien im Bereich der Ölablaufkammer 53 unterbunden und dadurch die Verkokungsgefahr im Dichtverbund reduziert werden. Zudem wird durch die grosse Ölablaufrinne 51 sowie der ersten Dichtstelle 43 der Hauptanteil des aus dem Radiallager 34 austretenden Lageröls nach Aussen hin abgeführt und über die Ölablaufrinne 52 von der Kolbenringpartie ferngehalten.The
Optional sind die Austritte des mindestens einen Ölablaufkanals 54 und des Gasablaufkanals 56 in Umfangsrichtung versetzt angeordnet, wie dies in der
In der dargestellten Ausführungsform sind die Dichtungen 43 und 44 als radiale Dichtspalte ausgeführt. Optional können diese Dichtungen mit Kolbenringdichtung oder anderen Dichtelementen ergänzt oder ersetzt werden.In the illustrated embodiment, the
Optional kann das Lagergehäuse im Bereich der erfindungsgemäss ausgebildeten Wellenabdichtung ohne separates Einsatzstück ausgebildet sein. In diesem Fall sind die entsprechenden Nuten, Dichtplatten und Dichtstege direkt ins Lagergehäuse eingelassen. Gegenüber der einteilig ausgebildeten Variante ohne separates Einsatzstück weist die ausführlich beschriebene Ausführungsform mit separatem Einsatzstück den Vorteil auf, dass das Einsatzstück zwecks Kühlung der Dichtungspartie aus einem Material mit guter Wärmeleitfähigkeit (z.B. Ck45) gefertigt werden kann und somit unabhängig ist vom verwendeten Lagergehäusematerial (z.B. GGG-40). Weiter ist ein Einsatzstück bei betriebsbedingter Abnutzung leicht zu ersetzen oder aber etwa zu Reinigungszwecken kurzzeitig aus dem Lagergehäuse auszubauen.Optionally, the bearing housing may be formed in the region of the shaft seal designed according to the invention without a separate insert piece. In this case, the corresponding grooves, sealing plates and sealing webs are embedded directly in the bearing housing. Compared to the one-piece variant without separate insert, the embodiment described in detail with separate insert has the advantage that the insert for the purpose of cooling the sealing part of a material with good thermal conductivity (eg Ck45) can be made and thus is independent of the bearing housing material used (eg GGG -40). Further, an insert is easy to replace in case of operational wear or remove it for cleaning purposes for a short time from the bearing housing.
Optional kann gemäss
In der dargestellten Ausführungsform umfasst die Wellenabdichtung zwei Kolbenringe 41 und 42. Alternativ kann auch nur ein Kolbenring vorgesehen sein oder es können in dem Bereich oder an anderen Stellen der Wellenabdichtung weitere Kolbenringe vorgesehen sein.In the illustrated embodiment, the shaft seal comprises two
Die dargestellte und detailliert beschriebene Ausführungsform zeigt die erfindungsgemäss ausgebildete Wellenabdichtung auf der Turbinenseite eines Abgasturboladers oder einer Nutzturbine. Natürlich kann die erfindungsgemäss ausgebildete Wellenabdichtung auch analog auf der Verdichterseite eines Abgasturboladers, oder auch bei einer beliebigen anderen Strömungsmaschine eingesetzt werden.The embodiment shown and described in detail shows the inventive shaft seal formed on the turbine side of an exhaust gas turbocharger or a power turbine. Of course, the shaft seal formed according to the invention can also be used analogously on the compressor side of an exhaust-gas turbocharger, or also in any other turbomachine.
- 1010
- Turbineturbine
- 1111
- Turbinenradturbine
- 1212
- Gaseinlassgas inlet
- 1313
- Gasaustrittgas outlet
- 1515
- Radrückraum des LaufradesRadraum of the impeller
- 2020
- Wellewave
- 21, 2221, 22
- Dichtstegsealing land
- 3030
- Lagergehäusebearing housing
- 3131
- Einsatzstück des LagergehäusesInsert of the bearing housing
- 3232
- Dichtplattesealing plate
- 3333
- Dichtstegsealing land
- 3434
- Radiallagerradial bearings
- 41, 4241, 42
- Kolbenringpiston ring
- 43, 4443, 44
- radialer Dichtspaltradial sealing gap
- 5050
- Hohlraum im LagergehäuseCavity in the bearing housing
- 51, 5251, 52
- ÖlablaufrinneOil drainage channel
- 5353
- ÖlablaufkammerOil drain chamber
- 5454
- ÖlablaufkanalOil drain passage
- 5555
- GasaustrittskammerGas outlet chamber
- 5656
- GasablaufkanalGas discharge channel
- 6060
- Ölkanaloil passage
- 6161
- ÖlspritzvorrichtungOil injection device
- 6262
- Turbinenseitiger LagerflanschTurbine side bearing flange
- 6363
- Innenkontur des LagergehäusesInner contour of the bearing housing
- 7070
- HitzeblechHitzeblech
- 7171
- Auflagestellesupport point
- 8181
- Mit der Welle mitrotierender AufsatzWith the shaft co-rotating attachment
- 8282
- Wellensitzshaft seat
- 8383
- Axialanschlagaxial stop
- 9090
- Verdichtercompressor
- 9191
- Verdichterradcompressor
- 9292
- Lufteinlassair intake
- 9393
- Luftaustrittair outlet
Claims (14)
- Shaft seal of a shaft (20), supported in a bearing housing (30), of a turbomachine between a cavity (50) in the bearing housing (30) and a wheel back space (15) of a rotating wheel (11) of the turbomachine, comprising a rotating wheel-side seal (41, 42) between the bearing housing (30, 31) and the shaft (20, 21) and also a bearing-side seal (43) between the bearing housing (30, 31) and the shaft (20, 21), wherein between the rotating wheel-side seal and the bearing-side seal provision is made for an oil outlet chamber (53),
characterized in that
the oil outlet chamber (53) is delimited by a third seal (44) between the bearing housing (30, 31) and the shaft (20, 22), and in that a gas discharge chamber (55) is arranged between the third seal and the rotating wheel-side seal, and
an oil drain channel (52) is let into the bearing housing radially outside the oil outlet chamber (53), wherein at least one oil splashing device (61) is arranged in the region of the oil drain channel (52), with which oil splashing device the region of the oil drain channel can be splashed with oil. - Shaft seal according to Claim 1, wherein the rotating wheel-side seal is designed in the form of at least one piston ring (41, 42).
- Shaft seal according to either of Claims 1 and 2, wherein the bearing-side seal is designed in the form of a sealing gap (43).
- Shaft seal according to Claims 1 to 3, wherein the third seal is designed in the form of a sealing gap (44) .
- Shaft seal according to Claim 1 to 4, wherein inside the wheel back space (15), a heat shield (70) protects the shaft seal from the hot turbine back wall (11).
- Shaft seal according to one of Claims 1 to 5, wherein the bearing housing, in the region of the shaft seal, comprises an insert piece (31), into which recesses are let in, forming the oil outlet chamber (53) and also the gas discharge chamber (55) .
- Shaft seal according to one of Claims 1 to 6, wherein the oil outlet chamber (53) and the gas discharge chamber (55) each comprise at least one separate outlet passage (54, 56).
- Shaft seal according to Claim 7, wherein the at least one outlet passage (54) of the oil outlet chamber (53) and the at least one outlet passage (56) of the gas discharge chamber (55) lead separately from each other into the cavity (50) in the bearing housing (30).
- Shaft seal according to Claim 8, wherein the at least one outlet passage (54) of the oil outlet chamber (53) and the at least one outlet passage (56) of the gas discharge chamber (55) lead into the cavity (50) in the bearing housing (30) in an offset manner in the circumferential direction.
- Shaft seal according to one of Claims 1 to 9, wherein the shaft, in the region of the shaft seal, comprises an attachment (81) which has a contour which together with the bearing housing forms the oil outlet chamber (53) and also the gas discharge chamber (55).
- Shaft seal according to Claim 10, wherein the attachment (81) is produced from a material which compared with the material of the shaft has higher heat conductivity.
- Turbomachine, comprising at least one rotating wheel (11) arranged on a shaft (20), and also a bearing housing (30) in which the shaft (20) is rotatably supported, wherein a shaft seal according to one of Claims 1 to 10 is arranged between the bearing housing (30) and the shaft (20).
- Exhaust gas turbocharger or power turbine, comprising at least one turbine rotating wheel (11) which is arranged on a shaft (20), and also a bearing housing (30) in which the shaft (20) is rotatably supported, wherein a shaft seal according to one of Claims 1 to 10 is arranged between the bearing housing (30) and the shaft (20).
- Exhaust gas turbocharger, comprising at least one compressor rotating wheel (11) which is arranged on a shaft (20), and also a bearing housing (30) in which the shaft (20) is rotatably supported, wherein a shaft seal according to one of Claims 1 to 10 is arranged between the bearing housing (30) and the shaft (20).
Applications Claiming Priority (1)
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DE102010003796A DE102010003796A1 (en) | 2010-04-09 | 2010-04-09 | shaft seal |
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EP2375000A3 EP2375000A3 (en) | 2017-06-28 |
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US (1) | US9169738B2 (en) |
EP (1) | EP2375000B2 (en) |
JP (1) | JP5259768B2 (en) |
KR (1) | KR101433817B1 (en) |
CN (1) | CN102213117B (en) |
DE (1) | DE102010003796A1 (en) |
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Also Published As
Publication number | Publication date |
---|---|
JP2011220338A (en) | 2011-11-04 |
US9169738B2 (en) | 2015-10-27 |
EP2375000A2 (en) | 2011-10-12 |
JP5259768B2 (en) | 2013-08-07 |
CN102213117A (en) | 2011-10-12 |
KR101433817B1 (en) | 2014-08-27 |
KR20110113569A (en) | 2011-10-17 |
EP2375000B2 (en) | 2022-12-14 |
EP2375000A3 (en) | 2017-06-28 |
CN102213117B (en) | 2014-08-27 |
US20110250067A1 (en) | 2011-10-13 |
DE102010003796A1 (en) | 2011-10-13 |
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