EP1503042A1 - Bremssystem in einem Turbolader - Google Patents
Bremssystem in einem Turbolader Download PDFInfo
- Publication number
- EP1503042A1 EP1503042A1 EP03016650A EP03016650A EP1503042A1 EP 1503042 A1 EP1503042 A1 EP 1503042A1 EP 03016650 A EP03016650 A EP 03016650A EP 03016650 A EP03016650 A EP 03016650A EP 1503042 A1 EP1503042 A1 EP 1503042A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- rotor
- housing
- braking surface
- counter
- turbocharger
- 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- Withdrawn
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
- F04D27/02—Surge control
- F04D27/0292—Stop safety or alarm devices, e.g. stop-and-go control; Disposition of check-valves
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D25/00—Pumping installations or systems
- F04D25/02—Units comprising pumps and their driving means
- F04D25/04—Units comprising pumps and their driving means the pump being fluid-driven
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2220/00—Application
- F05B2220/40—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
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2260/00—Function
- F05B2260/90—Braking
Definitions
- the invention relates to a turbocharger with at least one turbine rotor and at least one sitting on the same shaft compressor rotor, which, each wing having rotors in each case in a housing portion of a turbocharger housing are housed.
- the invention is based on the object, a turbocharger of the aforementioned Art form so that a bursting of a rotor is obstructed from the outset.
- the turbocharger is provided with a kind of centrifugal brake, which is a rotating with a speed above a permissible and at most adjustable value prevented and thus also prevents it at all can burst.
- this brake can be provided on each of the rotors or both.
- this brake can be provided on both rotors, i. at the turbine engine and provide on the compressor rotor, so that under certain circumstances, the heat by the friction spread on two brakes.
- Turbine rotor It is preferred if at least one rotor connected to the counter-braking surface engages Turbine rotor is (the invention also includes the case that about several turbines and / or Compressor rotors are provided).
- the braking surface of the housing is provided on an insert part in the housing.
- This insert part can, in case the turbine rotor is provided with the counter-braking surface of one then usually anyway existing Hitzschild be formed.
- the part of the rotor may be a molded ring which forms the counter-braking surface carries on its circumference.
- a ring is preferably at the wings arranged side facing away from the respective rotor because he there the gas or Air flow least disturbs.
- the ring itself could consist of a slightly flexible material or with a be processed so that he - even without the vibration of the wave - under the effect of the centrifugal force can bend radially outward.
- this also requires a longer axial dimensioning, which is given the space in a turbocharger generally will not be desirable. That is why it is also production technology advantageous if the ring consists of the same material as the associated rotor and in particular integrally molded with it.
- braking surface and counter braking surface if desired something can be arranged obliquely to the axis of rotation of the shaft, so that the system of one surface to the other gently. However, it has turned out that it is cheaper if at least one of the braking or counter braking surfaces, preferably both, extending substantially parallel to the shaft.
- a turbocharger 1 in a conventional manner a turbine housing part 2 and an associated compressor housing part 3 along an axis of rotation R are arranged.
- the turbine housing part 2 is shown partially in section, so that the located on the axis R turbine rotor 4 visible with corresponding turbine blades is, which is attached to one end of a rotor shaft 5, which in a middle part of the housing or bearing housing 6 is mounted.
- the turbine housing 2 has a supply pipe 7 for exhaust gas, which opens into an approximately annular supply channel 9 for exhaust gas or itself in this continues to supply the turbine rotor 4 exhaust gas from an internal combustion engine.
- the supply takes place in the illustrated embodiment on the blades 8 on known (and therefore not described in detail here) Leitgitters variable Geometry, about in a blade bearing ring 10 mounted adjusting with respect their position (more radially to the rotor 4 or more tangentially) are adjustable.
- the location of this Blades 8 controls the supply amount of exhaust gas to the turbine rotor 4, but is out of the Literature, it is known that this feed rate is also controlled by other gas control devices, as the derivative of the exhaust gas via a turbine housing on the leading shunt can be controlled via a corresponding valve.
- more than one supply channel 9 may be provided, especially if about several Turbine rotors should be attached to the shaft 5.
- Fig. 1 it can also be seen that the respective rotor housing 2 or 3 leaves a space, in which the respective rotor 4 or 21 can rotate.
- This room is arranged in such a way that the respective rotor 4 and 21, the respective gas (exhaust gas or air) via its periphery receives or outputs, in the region of the respective supply channels 9 and 11 are arranged.
- the present invention takes a different route by indicating a possibility to prevent the bursting at all. It is the same at which of the rotors 4 or 21 (or both) the invention is realized because both rotors yes on sit the same rotor shaft 5.
- Fig. 1 is at the rear of the compressor rotor 21 a Centrifugal brake ring 12 integrally formed, the radially outer circumferential surface as a counter-braking surface G serves. This counter braking surface G opposite and from her only by a separated narrow gap is formed on the compressor housing 3 or mounted on it Brake ring 14 is provided, which has a braking surface B radially inwardly.
- the rotor 21 has a molded counter-brake ring 12, because it is in principle It would also be possible to use the outer circumferential surface 15 as a counter-braking surface and to work together with the surrounding housing wall. If a specially shaped Brake ring or counter-brake ring, as the ring 12, is present, then must this also not necessarily on the back of the respective rotor, ie against the bearing housing 6 too, but could also be at the front in the areas The rotor blades are where it may possibly obstruct the flow, which is why the attachment shown on the back is preferred.
- the arrangement can either be realized on the compressor rotor or on the turbine rotor or on both as already mentioned above. Also, the respective ring 12 or 14 would not necessarily an integral part, but could be on the housing or on the rotor, e.g. detachable, fastened.
- a turbine housing 2 is now shown, to which the present invention is realized.
- this embodiment is between a part 6 'of the bearing housing 6 (see Fig. 1) and the turbine housing 2 a, preferably relatively flexible, Insert part provided in the form of a heat shield 17.
- This heat shield 17 is in one angled between bearing housing part 6 'and the turbine rotor 4 space such that it forms a radially inner braking surface B, which with a - in a similar way as in the compressor rotor 21 of FIG. 1 - formed on the turbine rotor 4 counter-brake ring cooperates with counter-braking surface G.
- that is between the two Surfaces B and G existing gap g extremely small, because only the small game of Shaft 5 is available in the bearings 16 for determining the size of the centrifugal force.
- a heat shield 17 is generally anyway provided which can be used simultaneously for the purposes of the invention.
- Fig. 3 shows another embodiment with reference to an enlarged section of the Fig. 2, but it is understood that this embodiment is not to a turbine rotor 4, but also the compressor rotor 21 (FIG. 1) may be formed could.
- This embodiment differs from that of FIG. 2 by two peculiarities.
- wings 18 are formed on the radial inside of the brake ring 12, of which several are distributed over the inner circumference of the ring 12 ". These wings 18 serve on the one hand the enlargement of the with the ring 12 "in communication Surface, so that resulting brake heat can be dissipated better.
- the wings may be helically twisted in the manner of an airscrew Gas from the vicinity of the rotor 4 against and around the surfaces of the ring 12 "swirl to let and so also contribute to the distribution of brake heat.
- a mechanical brake is provided, the result is friction also some wear. On the one hand, this can be counteracted by one the brake and / or counter braking surface B or G with a replaceable brake layer provides, as will be explained later. On the other hand it is - even from production engineering Reasons - advantageous, an adjustment (for pre and / or readjustment) provided. Fig. 3 illustrates how this can be done.
- a screw (or a Pressure pin) 19 provided, for example, on the surface F of the folding of the heat shield 17 can press (in which case the approximately U-shaped fold total - related on Fig. 3 - is pressed down) or - as shown - the screw 19 passes the top of this fold and presses directly against the back of the braking surface B.
- the gap g see Fig. 2 be brought back to its desired size.
- this gap g has to be widened once, but it is once the desire to make such an expansion possible, so could the end the screw 19 on the braking surface B positively in the axial direction in known per se and be secured in any way. If one uses such a screw 19 as adjusting (wedges, cams, etc. would also be conceivable), so this must be for actuation Of course accessible in any way outside the housing 2 (or 3) be.
- Fig. 4 shows an embodiment in which instead of a rigid ring 12, 12 'or 12 "a is provided from individual segments 12a constructed counter brake ring.
- Each of the Segments 12a is attached to an approximately L-shaped support 20 which, in view of the high Rotational speeds is yielding enough so that held by him segment 12a below the influence of centrifugal force can be forced radially outward and to the Braking surface B applies.
- the respective brake ring consists of the same material as the associated rotor and in particular with it is integrally formed, so here can of course the choice of material be arbitrary.
- the counter braking surface G (and / or the braking surface B) to choose a little abrasive material, So for example, a softer metal than iron, such as a copper alloy. This can then, for example, as a counter-braking layer Gs to form the corresponding counter-braking surface be applied to the respective segments 12a. If necessary, leaves the deflection movement of the L-shaped carrier 20 and the counter-braking surface G in Limit radial direction by a more or less compliant stop 22. Since it comes just to a small radial deflection but could, the counter-braking surface G (and possibly also the braking surface B) is arranged somewhat obliquely to the axis of rotation R. be.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Supercharger (AREA)
Abstract
Description
- Fig. 1
- eine perspektivische Ansicht eines erfindungsgemäß ausgebildeten Turboladers;
- Fig. 2
- ein teilweiser Axialschnitt durch ein weiteres Ausführungsbeispiel eines Turboladers nach der Erfindung, und die
- Fig. 3 und 4
- jeweils einen vergrößerten Ausschnitt des Details X aus Fig. 2, jedoch in einer jeweils anderen Ausführungsform.
Claims (9)
- Turbolader mit mindestens einem Turbinenrotor (4) und mindestens einem auf gleicher Welle (5) sitzenden Kompressorrotor (21), welche, jeweils Flügeln aufweisenden, Rotoren (4, 21) jeweils in einem Gehäuseabschnitt (2, 3) eines Turboladergehäuses (2, 3, 6) untergebracht sind, dadurch gekennzeichnet, daß im Inneren des Gehäuses (2, 3, 6) eine wenigstens einem Rotor (4, 21) radial außen gegenüberliegende Bremsfläche (B) vorgesehen ist, und daß dieser Rotor (4, 21) mit einer fliehkraftabhängig wirksamen Gegenbremsfläche (G) verbunden ist.
- Turbolader nach Anspruch 1, dadurch gekennzeichnet, daß wenigstens ein mit der Gegenbremsfläche (G) verbundener Rotor (4, 21) ein Turbinenrotor (4) ist.
- Turbolader nach Anspruch 1 oder 2, dadurch gekennzeichnet, daß die Bremsfläche (B) des Gehäuses (2, 3) an einem, vorzugsweise gegenüber dem Material des Gehäuses relativ flexiblen, Einlageteil (17) im Gehäuse (2, 3) vorgesehen ist.
- Turbolader nach den Ansprüchen 2 und 3, dadurch gekennzeichnet, daß die Bremsfläche (B) des Gehäuses (2, 3) an einem Hitzeschild (17) des Gehäuses (2, 3) vorgesehen ist.
- Turbolader nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß die Gegenbremsfläche (G) am Umfang eines Teiles des Rotors (4, 21) vorgesehen ist.
- Turbolader nach Anspruch 5, dadurch gekennzeichnet, daß der Rotor (4, 21) einen, insbesondere angeformten, Ring (12; 12'; 12"; 12a) aufweist, der die Gegenbremsfläche (G) an seinem Umfange trägt.
- Turbolader nach Anspruch 6, dadurch gekennzeichnet, daß der Ring (12; 12'; 12"; 12a) an der den Flügeln abgewandten Seite des jeweiligen Rotors (4, 21) angeordnet ist.
- Turbolader nach Anspruch 6 oder 7, dadurch gekennzeichnet, daß der Ring (12; 12'; 12"; 12a) aus demselben Material besteht wie der zugehörige Rotor (4, 21) und insbesondere mit ihm einteilig geformt ist.
- Turbolader nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß wenigstens eine der Brems- bzw. Gegenbremsflächen (B bzw. G), vorzugsweise beide, sich im wesentlichen parallel zur Welle (5) erstreckt.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP03016650A EP1503042A1 (de) | 2003-07-31 | 2003-07-31 | Bremssystem in einem Turbolader |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP03016650A EP1503042A1 (de) | 2003-07-31 | 2003-07-31 | Bremssystem in einem Turbolader |
Publications (1)
Publication Number | Publication Date |
---|---|
EP1503042A1 true EP1503042A1 (de) | 2005-02-02 |
Family
ID=33522273
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP03016650A Withdrawn EP1503042A1 (de) | 2003-07-31 | 2003-07-31 | Bremssystem in einem Turbolader |
Country Status (1)
Country | Link |
---|---|
EP (1) | EP1503042A1 (de) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102008005404A1 (de) | 2008-01-21 | 2009-07-23 | Bosch Mahle Turbo Systems Gmbh & Co. Kg | Turbolader |
Citations (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1600346A (en) * | 1925-01-26 | 1926-09-21 | Westinghouse Electric & Mfg Co | Turbine overspeed device |
US2459519A (en) * | 1947-06-16 | 1949-01-18 | Gen Electric | Speed limiting arrangements for turbine rotors |
US2962257A (en) * | 1957-03-19 | 1960-11-29 | Boeing Co | Turbine overspeed controls |
US2987296A (en) * | 1957-12-02 | 1961-06-06 | Bendix Corp | Safety device for starter turbine |
US3495691A (en) * | 1968-05-20 | 1970-02-17 | Gen Motors Corp | Overspeed brake |
US3495919A (en) * | 1968-05-20 | 1970-02-17 | Gen Motors Corp | Turbine brake |
FR2050550A5 (en) * | 1969-06-17 | 1971-04-02 | Commissariat Energie Atomique | Governor for turbine rotors |
US20030115872A1 (en) * | 2001-06-23 | 2003-06-26 | Siegfried Sumser | Compressor in a turbocharger |
-
2003
- 2003-07-31 EP EP03016650A patent/EP1503042A1/de not_active Withdrawn
Patent Citations (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1600346A (en) * | 1925-01-26 | 1926-09-21 | Westinghouse Electric & Mfg Co | Turbine overspeed device |
US2459519A (en) * | 1947-06-16 | 1949-01-18 | Gen Electric | Speed limiting arrangements for turbine rotors |
US2962257A (en) * | 1957-03-19 | 1960-11-29 | Boeing Co | Turbine overspeed controls |
US2987296A (en) * | 1957-12-02 | 1961-06-06 | Bendix Corp | Safety device for starter turbine |
US3495691A (en) * | 1968-05-20 | 1970-02-17 | Gen Motors Corp | Overspeed brake |
US3495919A (en) * | 1968-05-20 | 1970-02-17 | Gen Motors Corp | Turbine brake |
FR2050550A5 (en) * | 1969-06-17 | 1971-04-02 | Commissariat Energie Atomique | Governor for turbine rotors |
US20030115872A1 (en) * | 2001-06-23 | 2003-06-26 | Siegfried Sumser | Compressor in a turbocharger |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102008005404A1 (de) | 2008-01-21 | 2009-07-23 | Bosch Mahle Turbo Systems Gmbh & Co. Kg | Turbolader |
US9163557B2 (en) | 2008-01-21 | 2015-10-20 | Bosch Mahle Turbo Systems Gmbh & Co. Kg | Turbocharger |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP2940324B1 (de) | Lagerkäfig und lagereinrichtung mit einem derartigen lagerkäfig sowie verfahren zum ausbilden, reparieren und/oder austauschen eines solchen lagerkäfigs | |
AT516029B1 (de) | Planetengetriebe für eine Windkraftanlage | |
DE10159670A1 (de) | Wirbelgleichrichter im Hochdruckverdichter einer Gasturbine | |
DE10259963A1 (de) | Wabendichtung | |
EP2209995A1 (de) | Mehrstufiger turbomolekularpumpen-pumpenrotor | |
DE2621485A1 (de) | Pneumatischer lamellenmotor | |
EP1445507A1 (de) | Innenbelüftete Bremsscheibe mit gekrümmten Kühlluftkanälen | |
DE102005027097A1 (de) | Statorscheibe für Turbomolekularpumpe | |
EP3573762B1 (de) | Rührwerksmühle | |
CH703064A2 (de) | Einsatzstück für eine Strömungsmaschine und damit ausgerüstete Strömungsmaschine. | |
DE1453730B2 (de) | Radialkreiselpumpenlaufrad | |
WO2009143920A1 (de) | Radiallüfter | |
EP1503042A1 (de) | Bremssystem in einem Turbolader | |
EP3312388A1 (de) | Pultdach dichtfin | |
DE3926152C2 (de) | ||
DE102012212483B4 (de) | Zahnärztliches Präparationsinstrument | |
DE19848493A1 (de) | Konditionierwalze und Verfahren zu deren Herstellung für Feldhäcksler | |
DE10056168C2 (de) | Rotor für einen Roots- oder Schraubenkompressor | |
DE2718389C2 (de) | Luftdrehfilter | |
DE19528727C2 (de) | Offen-End-Rotorspinnmaschine | |
DE10018005A1 (de) | Verfahren und Vorrichtung zum Pulverisieren von spanartigem Material | |
EP3844392B1 (de) | Lageranordnung eines rotors einer windkraftanlage und windkraftanlage | |
EP0734787A1 (de) | Zentrifugalkraftsichter, Lagerung der Rotorwelle | |
EP1398465B1 (de) | Turbolader und Rotorgehäuse hierfür | |
DE19643043C2 (de) | Schleuderrad-Windsichter mit radialem Feingutaustrag |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
|
AK | Designated contracting states |
Kind code of ref document: A1 Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IT LI LU MC NL PT RO SE SI SK TR |
|
AX | Request for extension of the european patent |
Extension state: AL LT LV MK |
|
RAP1 | Party data changed (applicant data changed or rights of an application transferred) |
Owner name: BORGWARNER INC. |
|
17P | Request for examination filed |
Effective date: 20050309 |
|
AKX | Designation fees paid |
Designated state(s): DE FR GB IT NL |
|
17Q | First examination report despatched |
Effective date: 20070214 |
|
RIN1 | Information on inventor provided before grant (corrected) |
Inventor name: SCHMALZL, HANS-PETER Inventor name: SIMON, VOLKER Inventor name: O'HARA, STEPHEN |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN |
|
18D | Application deemed to be withdrawn |
Effective date: 20100202 |