EP0086466A1 - Contrôle d'éntrée de la volute d'une turbine radiale - Google Patents

Contrôle d'éntrée de la volute d'une turbine radiale Download PDF

Info

Publication number
EP0086466A1
EP0086466A1 EP83101306A EP83101306A EP0086466A1 EP 0086466 A1 EP0086466 A1 EP 0086466A1 EP 83101306 A EP83101306 A EP 83101306A EP 83101306 A EP83101306 A EP 83101306A EP 0086466 A1 EP0086466 A1 EP 0086466A1
Authority
EP
European Patent Office
Prior art keywords
flow path
rotor
section
turbine
curved
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.)
Granted
Application number
EP83101306A
Other languages
German (de)
English (en)
Other versions
EP0086466B1 (fr
Inventor
Merle Lavern Kaesser
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.)
Deere and Co
Original Assignee
Deere and Co
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 Deere and Co filed Critical Deere and Co
Priority to AT83101306T priority Critical patent/ATE27474T1/de
Publication of EP0086466A1 publication Critical patent/EP0086466A1/fr
Application granted granted Critical
Publication of EP0086466B1 publication Critical patent/EP0086466B1/fr
Expired legal-status Critical Current

Links

Images

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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/026—Scrolls for radial machines or engines
    • 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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/146—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by throttling the volute inlet of radial machines or engines

Definitions

  • the invention relates to a turbine, in particular.
  • Exhaust gas turbine with variable flow in particular for driving turbochargers of internal combustion engines, consisting of a rotor which can be rotated about an axis and has a plurality of rotor blades or blades arranged at a mutual circumferential distance, from a housing with a Rotor coaxial outlet and a volute section with an inlet arranged at a distance from the axis, in which a primary outer and a secondary inner flow path are formed by a partition, and a valve-like member with an actuator for changing the inflow cross-section of the secondary inner flow path.
  • radially inflated turbines are known which are used in connection with turbochargers of internal combustion engines.
  • One type is known as a fixed geometry turbine. This is designed so that the shape and area of the flow channel or the flow channels, which extend from the fluid inlet to the turbine rotor, cannot be physically changed.
  • An example of a turbine with a fixed geometry is the turbine according to US Pat. No. 3,664,761.
  • the second type of turbine is known as a variable flow turbine.
  • the turbine is configured to have radially inner and radially outer fluid channels, with a valve positioned across one of the channels to allow fluid flow through that channel to be adjusted.
  • a valve By changing the size of the opening of one flow channel by adjusting the valve, one can change the cross-sectional area of the fluid flow path and thereby compensate for changes in the flow speed and the pressure, which can occur due to the operation of the internal combustion engine at different speeds and under different loads.
  • An example of a variable flow turbine is the turbine according to US Pat. No. 4,177,006.
  • the turbine housing has a straight fluid inlet section which merges into a spiral housing section. Both the fluid inlet section and the volute section are each divided into two flow paths.
  • Each of the flow paths is further divided into the volute section, primary and secondary flow paths, which are divided by a wall integral with the housing. Furthermore, a valve is arranged in the fluid inlet transversely to the second flow path. This can be rotated to direct the flow away from the wall and thus regulate the fluid flow.
  • variable flow turbine can increase the efficiency of the machine by using compressors that are highly effective at limited speed and charge and less effective when the machine is at peak torque. This is possible because the variable flow turbine power can be increased at peak torque to compensate for the lower efficiency of the compressor.
  • variable flow turbines are more effective at lower than the maximum speeds and loads at which a maximum boost pressure is not required. In these situations, variable flow turbines can increase the flow area so as to reduce the pressure in the exhaust manifold.
  • a more precise adaptation of the operation of the turbine to the need and the operation of the internal combustion engine should be possible.
  • the housing has a curved section between the inlet and the spiral housing section formed around the axis and that the partition extends through the curved section and into the volute section so that the primary outer flow path and the secondary inner flow path within the volute section each have cross-sectional areas that decrease steadily as the flow path approaches the rotor.
  • the valve-like member can be operated so that the flow through the secondary internal flow path is changed.
  • the moment of the exhaust gases can be adjusted by adjusting the valve member.
  • the curved housing section extends in the flow direction from the valve member in order to keep the throttle losses as small as possible.
  • the speed of the exhaust gases on their way to the blades or blades of the turbine rotor can be increased by rotating the valve member in the direction of the partition wall with partial or full blocking of the secondary internal flow path.
  • the new possibility of the turbine to vary the moment of the flowing exhaust gases over the curved housing section with the aid of the valve member improves the effectiveness of the turbine for a predetermined torque curve over a desired working range of the internal combustion engine.
  • the increase in the speed of the incoming exhaust gas fluids can be set precisely.
  • the valve member By adjusting the valve member, the incoming exhaust gases can be guided to the circumference of the turbine rotor better than before.
  • the new turbine makes it possible to use a compressor with high efficiency at limited engine speeds in order to increase the efficiency of this machine. You can also use the new turbine Achieve higher torque at lower speeds. Above all, the turbine makes it possible to improve the efficiency of the internal combustion engine at all speeds and loads, while at the same time the sensitivity of the internal combustion engine to the transition can be increased.
  • the curved housing section expediently extends over an arc length between 30 ° and 180 °.
  • the spiral housing section extends over an arc length of at least 270 °.
  • the inner surface of the curved housing section converges towards an inner surface of the volute housing section and. forms with this a tongue at the entrance to the volute section, which extends approximately tangentially to the rotor circumference.
  • the partition wall approaches from the inlet tangentially to the circumference of the rotor to a point which is offset by an arc length of approximately 90 ° from the end of the tongue.
  • the cross-sectional area of the primary outer flow path is expediently larger than that of the secondary inner flow path.
  • valve member is advantageously adjustable so that the exhaust gases flowing through the secondary internal flow path are deflected against the partition.
  • an axially extending partition section can also be provided which extends approximately perpendicular to the partition and projects axially from the inlet into the housing in order to divide it into two axially adjacent and separate flow paths, each of which has a primary outer flow path and one has secondary internal flow path.
  • the flow paths expediently point in the curved housing section from the inlet to the inlet occurs in the spiral housing section in each case a constantly decreasing cross-sectional area.
  • the arrangement 10 shown in the figures, in particular FIG. 3, comprises a variable flow turbine 11 which is connected to a compressor 12.
  • the whole arrangement 10 forms an exhaust gas turbocharger.
  • the turbine has a housing 13 which consists of a curved inlet section 14 and a spiral housing section 16.
  • the curved housing section 14 is an arcuate part that can be flanged to the exhaust manifold of an internal combustion engine by means of a flange end 18 via bolts and bolt holes 20.
  • the curved section 14 has an angular extent of at least 30 °, preferably an extent between 30 and 180 °. The preferred range for expansion is between 45 ° and 90 °.
  • the curved section 14 has an inlet 22 at the flange end 18 and is connected to the volute section 16 at the other end 24.
  • the spiral housing section 16 has a circumferential extent of at least 270 and preferably of approximately 360 °.
  • the arc of the volute section 16 extends around an axis that is perpendicular to the paper of FIG. 1.
  • a connecting shaft 26 rotatably connects a rotor 28 of the turbine to a compressor wheel 30.
  • the shaft 26 rotates about the axis of the volute casing.
  • the turbine rotor 28, which is enclosed in the housing 13, has a plurality of turbine blades or blades 34 which are arranged at intervals in the circumferential direction and extend radially outward from the central axis. The particular shape and shape of the blades 34 may vary in a known manner as desired.
  • the turbine housing 13 also has an outlet 32, which can be seen in FIG. 3.
  • the exhaust gases from an internal combustion engine are introduced into the turbine 11. They cause the turbine rotor 28 to rotate.
  • the compressor wheel 30 is taken along, specifically via the connecting shaft 26. Das In this way, compressor wheel 30 delivers a relatively high boost pressure for the internal combustion engine.
  • a control valve member 36 is disposed near the fluid inlet 22. This serves to control the gas flow in the turbine housing 13.
  • the control valve 36 is preferably a rotary valve which is fitted into the inner surface of the curved housing section 14.
  • the valve 36 has a valve insert 40 that is movable between an open position and a closed position to change and regulate the gas flow through the variable flow turbine. In the open position according to FIG. 2, the valve insert 40 lies flush with the inner surface of the curved housing section 14 and thus allows the exhaust gases to flow through the entire curved section 14. In the closed position, which is shown in broken lines in FIG. 2, the valve insert 40 pivots the flow path of the gases through the curved housing section 14.
  • the valve - 36 is operated by a control device 42 via pin 43 and linkage 44.
  • the control device 42 can be pivotally attached at one end 46 to a fixed support device 48, so that a linear movement of the linkage 44 is converted into a rotary movement of the control valve 36. It is noted that the control device 42 can be operated manually or automatically, as is known in the art. The controller 42 can also be configured differently, for essentially any linear or non-linear dependence on changes in machine parameters, e.g., the working speed, the load, the distributor inlet pressure, the machine emissions, the smoke density of the exhaust gases which leave the machine and into which Atmosphere, from the temperature of the exhaust gases or from any combination of these factors. In addition, the control device 42 can be set to parameters, for example the speed of the turbine rotors 28 and on the throttle position.
  • a divider wall or partition wall 50 extends from the control valve 36 into both sections of the turbine housing 13.
  • the partition wall 50 terminates in a tip 52 which lies approximately tangentially on the outer circumference of the turbine rotor 28.
  • This partition 50 is an arcuate member that can be integrally formed with the turbine housing and serves to divide the turbine housing 13 into an inner or secondary fluid channel 54 and an outer or primary fluid channel 56.
  • the area of the outer fluid channel 56 is larger than the area of the inner fluid channel 54.
  • the outer fluid channel 56 intersects approximately three times as much as the circumference of the turbine rotor 28 as the inner fluid channel 54.
  • the partition 50 works with an inner surface 58 of the volute casing section 16 together, as can be seen from FIG. This results in a decreasing cross-sectional area of the outer fluid channel 56.
  • the cross-sectional areas of both fluid channels 54 and 56 preferably decrease constantly over the entire curved housing section and over the spiral housing section 14 and 16, respectively. This feature provides a relatively uniform velocity of the exhaust gases as they strike the turbine blades 34.
  • Rotating the control valve 36 from the open position to a partially closed position results in the exhaust gases being deflected outward toward the divider wall 50. This increases the velocity of the exhaust gases that flow in the two inner and outer channels 54 and 56. The increased speed combined with the increased radius of curvature Mass flow of the exhaust gases leads to an increase in the power of the turbine 11.
  • the curved housing section 14 cooperates with an inner surface 58 of the spiral housing section 16 to form a tongue 60 with a tip 62.
  • the tip 62 lies at the opposite end 24 of the curved housing section 14, which is indicated by the dash-dotted line. It is in the immediate vicinity of the circumference of the turbine rotor 28 and preferably tangential to the outer circumference of the rotor.
  • the tongue tip 62 lies at an angular distance of approximately 90 ° from the tip 52 of the partition 50, so that approximately 75% of the peripheral region of the turbine rotor 28 is exposed to the outer fluid channel 56.
  • Tip 62 and inner surface 58 control the flow of exhaust gases between the outer periphery of turbine rotor 28 and tongue 60. Tip 62 also controls each flow of exhaust gases clockwise, which flow would have a pulsating effect on turbine rotor 28.
  • FIGS. 5 to 7. This shows an alternative embodiment for a variable flow turbine.
  • This also has a control valve 64 which is arranged across the inner flow channel 54.
  • the control valve 64 has a valve insert 67 which can be actuated within the curved housing section 14 on seals 65 via a control linkage 66 according to FIG. 7.
  • the Valve insert 67 When the control valve 64 is rotated, the Valve insert 67 between the open position and the closed position. 5, the valve insert 67 is flush with the inner surface of the curved portion 14 and allows exhaust gases to flow through both the inner and outer flow channels 54 and 56, respectively.
  • By rotating the valve insert 67 in the direction of the partition 51 into a partially closed position part of the inner channel 54 is blocked. In the fully closed position, which is indicated by dashed lines in FIG.
  • the alternative embodiment also shows an axial divider wall 68 which, according to FIGS. 6 and 7, is arranged approximately perpendicular to the partition wall 51 and extends inwards from the fluid inlet 22 in both sections 14 and 16 of the turbine housing 13.
  • the axial divider wall 68 divides the turbine housing 13 into two axially separated fluid flow paths 70 and 72, each of these flow paths having inner and outer flow channels 54 and 56.
  • Each of the flow paths 70 and 72 are aligned with a separate exhaust manifold to prevent the pulsating exhaust gases from mixing before striking the turbine blades 34.
  • the new turbine 11 works with the exhaust gases that are passed from the exhaust manifold of an internal combustion engine through the flow paths 54 and 56 and impinge on the blades 34 of the turbine rotor 28.
  • the turbine rotor 28 is driven at a speed that is adapted to the speed and mass flow of the exhaust gases.
  • the rotational speed of the turbine rotor 28 is related to the working conditions of the internal combustion engine, for example in Regarding their speed and load.
  • the cross-sectional flow area and shape of the flow channels 54 and 56 as well as the shape of the partition 50 affect the speed of the exhaust gases and thus also have an effect on the rotational speed of the turbine rotor 28.
  • Partially or fully closing the control valve 36 to increase the speed of the turbocharger increases the charge air flow to the internal combustion engine. This allows more fuel to be injected into the engine to achieve higher engine torques and to improve transition responsiveness without exceeding exhaust gas smoke density limits.
  • the control valve 36 can be modulated so that a optimal combination of air / fuel ratio and pressure differential can be achieved via the machine with maximum internal combustion engine efficiency.
  • the cross-sectional area can be increased and the average radius of curvature of the mass flow reduced to monitor the speed of the turbocharger and the boost pressure of the engine.
  • the j vaneless nozzle-type turbine according to the invention can process flows of exhaust gases whose velocities above Mach I, occur without impact problems. This ability to process absolute speeds that exceed supersonic speeds is not available in turbines with guide vanes.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)
  • Control Of Turbines (AREA)
  • Valve Device For Special Equipments (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Paper (AREA)
EP83101306A 1982-02-16 1983-02-11 Contrôle d'éntrée de la volute d'une turbine radiale Expired EP0086466B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AT83101306T ATE27474T1 (de) 1982-02-16 1983-02-11 Durchflussregelung fuer den spiralgehaeuse-einlass einer radialturbine.

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US34928382A 1982-02-16 1982-02-16
US349283 1982-02-16

Publications (2)

Publication Number Publication Date
EP0086466A1 true EP0086466A1 (fr) 1983-08-24
EP0086466B1 EP0086466B1 (fr) 1987-05-27

Family

ID=23371688

Family Applications (1)

Application Number Title Priority Date Filing Date
EP83101306A Expired EP0086466B1 (fr) 1982-02-16 1983-02-11 Contrôle d'éntrée de la volute d'une turbine radiale

Country Status (10)

Country Link
EP (1) EP0086466B1 (fr)
JP (1) JPS58150028A (fr)
AT (1) ATE27474T1 (fr)
AU (1) AU550503B2 (fr)
BR (1) BR8300621A (fr)
CA (1) CA1206419A (fr)
DE (1) DE3371804D1 (fr)
ES (1) ES8402637A1 (fr)
MX (1) MX156452A (fr)
ZA (1) ZA831015B (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1939427A2 (fr) 2006-12-20 2008-07-02 MP-Engineering GmbH Turbocompresseur d'échappement
WO2009129895A1 (fr) * 2008-04-24 2009-10-29 Daimler Ag Turbocompresseur pour un moteur à combustion interne d'un véhicule et moteur à combustion interne
WO2011067259A1 (fr) * 2009-12-02 2011-06-09 Continental Automotive Gmbh Turbocompresseur
CN103557069A (zh) * 2013-11-13 2014-02-05 中国北方发动机研究所(天津) 一种可切换双入口非对称涡轮箱
WO2015143261A1 (fr) * 2014-03-21 2015-09-24 Fluid Equipment Development Company, Llc Procédé et système de réglage d'une turbine à l'aide d'une vanne hydraulique

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS59144101U (ja) * 1983-03-18 1984-09-26 株式会社小松製作所 可変式ベ−ンレスハウジングの切換装置
JPS60128931A (ja) * 1983-12-16 1985-07-10 Mazda Motor Corp 排気タ−ビン過給装置
DE29716357U1 (de) 1997-09-11 1998-02-12 Ohra Regalanlagen GmbH, 50169 Kerpen Stahlbaubühne
US7694518B2 (en) * 2007-08-14 2010-04-13 Deere & Company Internal combustion engine system having a power turbine with a broad efficiency range
KR101051016B1 (ko) 2010-12-14 2011-07-21 한국기계연구원 흡기분리형 터빈
DE112012001912T5 (de) 2011-06-10 2014-01-30 Borgwarner Inc. Turbolader mit zweiflutigem Turbinengehäuse
WO2015179386A1 (fr) * 2014-05-19 2015-11-26 Borgwarner Inc. Turbocompresseur à double volute pour optimiser la séparation d'énergies d'impulsions pour l'économie de carburant, et utilisation de recirculation des gaz d'échappement par l'intermédiaire de doubles volutes asymétriques

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH239435A (de) * 1942-05-23 1945-10-15 Buechi Alfred Freifliegend gelagerte Turbine, insbesondere für heisse Gase.
FR2210220A5 (fr) * 1972-12-06 1974-07-05 Woollenweber William
FR2320440A1 (fr) * 1975-08-08 1977-03-04 Roto Master Cage d'une turbine partiellement divisee en deux compartiments
US4177006A (en) * 1977-09-29 1979-12-04 The Garrett Corporation Turbocharger control
FR2465069A1 (fr) * 1979-09-17 1981-03-20 Ishikawajima Harima Heavy Ind Carter de turbine pour turbocompresseur de moteur a explosion
GB2057063A (en) * 1979-08-23 1981-03-25 Dibelius G Turbocharger control

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
NL296316A (fr) * 1962-08-07
JPS5849682B2 (ja) * 1977-10-05 1983-11-05 三菱重工業株式会社 タ−ビンケ−シングの製造方法
JPS591332B2 (ja) * 1979-09-17 1984-01-11 石川島播磨重工業株式会社 過給機用タ−ビン車室

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH239435A (de) * 1942-05-23 1945-10-15 Buechi Alfred Freifliegend gelagerte Turbine, insbesondere für heisse Gase.
FR2210220A5 (fr) * 1972-12-06 1974-07-05 Woollenweber William
FR2320440A1 (fr) * 1975-08-08 1977-03-04 Roto Master Cage d'une turbine partiellement divisee en deux compartiments
US4177006A (en) * 1977-09-29 1979-12-04 The Garrett Corporation Turbocharger control
GB2057063A (en) * 1979-08-23 1981-03-25 Dibelius G Turbocharger control
FR2465069A1 (fr) * 1979-09-17 1981-03-20 Ishikawajima Harima Heavy Ind Carter de turbine pour turbocompresseur de moteur a explosion

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
ENGINEERING MATERIALS AND DESIGN, November 1982, Industrial Press, London, GB. *

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1939427A2 (fr) 2006-12-20 2008-07-02 MP-Engineering GmbH Turbocompresseur d'échappement
EP1939427A3 (fr) * 2006-12-20 2009-08-05 MP-Engineering GmbH Turbocompresseur d'échappement
WO2009129895A1 (fr) * 2008-04-24 2009-10-29 Daimler Ag Turbocompresseur pour un moteur à combustion interne d'un véhicule et moteur à combustion interne
WO2011067259A1 (fr) * 2009-12-02 2011-06-09 Continental Automotive Gmbh Turbocompresseur
CN103557069A (zh) * 2013-11-13 2014-02-05 中国北方发动机研究所(天津) 一种可切换双入口非对称涡轮箱
WO2015143261A1 (fr) * 2014-03-21 2015-09-24 Fluid Equipment Development Company, Llc Procédé et système de réglage d'une turbine à l'aide d'une vanne hydraulique
US10267318B2 (en) 2014-03-21 2019-04-23 Fluid Equipment Development Company, Llc Method and system for tuning a turbine using a secondary injection valve

Also Published As

Publication number Publication date
CA1206419A (fr) 1986-06-24
AU550503B2 (en) 1986-03-20
DE3371804D1 (en) 1987-07-02
MX156452A (es) 1988-08-23
ATE27474T1 (de) 1987-06-15
ES519793A0 (es) 1984-02-01
JPS58150028A (ja) 1983-09-06
BR8300621A (pt) 1983-11-08
EP0086466B1 (fr) 1987-05-27
ES8402637A1 (es) 1984-02-01
ZA831015B (en) 1984-09-26
AU9165882A (en) 1983-08-25

Similar Documents

Publication Publication Date Title
DE19717559C2 (de) Turbolader
DE4242494C1 (en) Adjustable flow-guide for engine exhaust turbocharger - has axially-adjustable annular insert in sectors forming different kinds of guide grilles supplied simultaneously by spiral passages
DE60133629T2 (de) Verfahren zum betrieb einer gasturbine mit verstellbaren leitschaufeln
DE102005019937B3 (de) Turbine mit einem Turbinenrad für einen Abgasturbolader einer Brennkraftmaschine und Abgasturbolader für eine Brennkraftmaschine
EP0243596B1 (fr) Régulateur de résistance axiale pour un turbocompresseur à gaz d'échappement pour machines à combustion interne
EP3542069B1 (fr) Compresseur, turbocompresseur et moteur a combustion interne
EP0433560A1 (fr) Turbochargeur à gaz pour un moteur à combustion interne
DE2500496A1 (de) Kompressorvorrichtung
EP0093462A1 (fr) Turbocompresseur avec une valve annulaire glissante
DE112012001912T5 (de) Turbolader mit zweiflutigem Turbinengehäuse
DE3833906C2 (fr)
DE3034271A1 (de) Turbinengehaeuse fuer turbolader
EP0735253A2 (fr) Méthode et dispositif pour la suralimentation par registre d'un moteur à combustion interne
DE4303521C1 (de) Verstellbarer Strömungsleitapparat für eine Abgasturbine
EP0086466B1 (fr) Contrôle d'éntrée de la volute d'une turbine radiale
DE10336994A1 (de) Brennkraftmaschine mit Aufladung sowie zugeordneter Luftverdichter
DE102018221812A1 (de) Abgasturbine mit einer Abgasleiteinrichtung für einen Abgasturbolader und Abgasturbolader
EP1530671B1 (fr) Turbocompresseur à gaz d'échappement pour moteur à combustion
DE69318242T2 (de) Einlassregelanlage einer Turbomaschine
DE60305011T2 (de) Verbesserte schaufelausführung zur verwendung in turboladern mit variabler geometrie
EP1673525B1 (fr) Compresseur monte dans le systeme d'admission d'un moteur a combustion interne
DE102011120167A1 (de) Verdichter für einen Abgasturbolader,insbesondere eines Kraftwagens
DE102008051980A1 (de) Luftversorgungsvorrichtung für eine Brennstoffzelle
DE102017110167A1 (de) Bewegbare Düseneinrichtung und Verfahren für einen Turbolader
EP3591185A1 (fr) Procédé de fonctionnement d'un moteur à combustion interne avec un dispositif de réglage de l'ouverture du compresseur

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

Designated state(s): AT BE CH DE FR GB IT LI SE

17P Request for examination filed

Effective date: 19830922

ITCL It: translation for ep claims filed

Representative=s name: LENZI & C.

EL Fr: translation of claims filed
ITF It: translation for a ep patent filed

Owner name: LENZI & C.

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AT BE CH DE FR GB IT LI SE

REF Corresponds to:

Ref document number: 27474

Country of ref document: AT

Date of ref document: 19870615

Kind code of ref document: T

REF Corresponds to:

Ref document number: 3371804

Country of ref document: DE

Date of ref document: 19870702

ET Fr: translation filed
PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AT

Effective date: 19880211

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed
ITTA It: last paid annual fee
PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: BE

Payment date: 19900221

Year of fee payment: 8

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 19910121

Year of fee payment: 9

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: CH

Payment date: 19910122

Year of fee payment: 9

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 19910207

Year of fee payment: 9

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: SE

Payment date: 19910211

Year of fee payment: 9

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BE

Effective date: 19910228

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 19910418

Year of fee payment: 9

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Effective date: 19920211

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SE

Effective date: 19920212

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LI

Effective date: 19920229

Ref country code: CH

Effective date: 19920229

GBPC Gb: european patent ceased through non-payment of renewal fee
PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Effective date: 19921030

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Effective date: 19921103

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

EUG Se: european patent has lapsed

Ref document number: 83101306.5

Effective date: 19920904