EP0086466B1 - Durchflussregelung für den Spiralgehäuse-einlass einer Radialturbine - Google Patents

Durchflussregelung für den Spiralgehäuse-einlass einer Radialturbine Download PDF

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Publication number
EP0086466B1
EP0086466B1 EP83101306A EP83101306A EP0086466B1 EP 0086466 B1 EP0086466 B1 EP 0086466B1 EP 83101306 A EP83101306 A EP 83101306A EP 83101306 A EP83101306 A EP 83101306A EP 0086466 B1 EP0086466 B1 EP 0086466B1
Authority
EP
European Patent Office
Prior art keywords
flow path
rotor
volute casing
casing portion
inner flow
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.)
Expired
Application number
EP83101306A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0086466A1 (de
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/de
Application granted granted Critical
Publication of EP0086466B1 publication Critical patent/EP0086466B1/de
Expired legal-status Critical Current

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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 present invention relates to an exhaust gas turbine with variable flow, in particular for driving turbochargers of internal combustion engines with the features of the preamble of claim 1.
  • a turbine of this type is known from FR-A-1337865.
  • the exhaust gases are fed through two separate lines to a straight inlet housing, to which the inlet section belonging to the turbine housing is connected and which, up to the connection point of the spiral housing section, is curved in a direction opposite to that of the spiral housing section.
  • a dividing wall begins in the inlet housing and extends through the inlet section into the spiral housing section and each has the same straight or curved shape as the inlet housing, the inlet section or the spiral housing section.
  • This forms inner and outer flow paths for the exhaust gases, which have approximately the same and constant cross sections in the inlet housing and in the inlet section.
  • the outer flow path also maintains its cross-sectional area essentially unchanged in the volute section up to the end of the partition.
  • the dividing wall and the inner surface of the volute section each end directly on the outer circumference of a fixed, uniform guide vane section, which surrounds the rotor.
  • the guide vane ring is designed in such a way that a guide vane has an extension which runs approximately tangentially to the circumference of the rotor for the end of the dividing wall which is continuously approaching the outer circumference of the guide vane ring within the spiral housing section.
  • a switchable valve-like member with an actuating device is provided in the straight inlet housing. In one position of this link, the outer flow path is closed, so that the gases from the two exhaust gas supply lines mix and are supplied exclusively to the inner flow path.
  • the separately supplied exhaust gas flows can enter the inner or outer flow path almost unmixed. Due to the course of the partition in the volute casing section and through the guide vane ring arranged in it, it follows that the inner flow path has an abrupt change in cross-section both at the transition point between the entry section and the volute casing section and in the area of the radially outer end of each vane, so that the cross-sectional areas become increasing approach of the partition to the circumference of the guide vane ring progressively reduces the cross-sectional area on average.
  • the outer flow channel within the volute casing section also experiences an abrupt widening of the cross section where the partition ends at the circumference of the guide vane ring.
  • the cross-sectional areas of the outer flow channel are abruptly changed by the guide blades at the level of the radially outer end of each guide blade.
  • FR-A-2465069 describes an exhaust gas turbine in which the end of the dividing wall, which forms the outer and the inner flow path in the spiral housing section, is designed in the form of a guide surface tip lying approximately tangentially on the circumference of the rotor.
  • the cross-sectional area of the outer flow path delimited by the dividing wall within the volute casing decreases in width and does so steadily in the direction of increasing flow path closer to the circumference of the rotor.
  • the spiral housing section is assigned a straight inlet section, through which the partition also runs straight up to its inlet cross section.
  • a turbine is also known with a straight inlet housing section with partition and valve-like member which is assigned to the turbine housing and which is assigned to the inner flow path (cf. US-A-41 77 006).
  • the inlet section and the spiral housing section of the turbine housing have a further partition wall which extends approximately perpendicular to the partition wall separating the inner and outer flow paths and to the axis of rotation of the rotor and extends from the entrance of the inlet section to the end of the first partition wall.
  • This additional partition section keeps the separately supplied exhaust gas streams strictly separate until they hit the rotor.
  • the dividing wall delimiting the outer and inner flow path ends at a considerable distance from the outer circumference of the rotor, so that the gas flow through this dividing wall also ends at a considerable distance from the circumference of the rotor.
  • a valve is provided which can close off the inner flow path.
  • the inner flow path has a discontinuous, that is to say a cross section which is initially decreasing, then increasing and then decreasing again.
  • the cross-sectional area of the fluid flow path can be changed by adjusting the valve and changing the size of the inlet opening of the one flow channel. This makes it possible to compensate for changes in the flow speed and the pressure which can occur as a result of operating the internal combustion engine at different speeds and under different loads.
  • variable flow turbine can increase the efficiency of the internal combustion engine by using compressors. These have a high effectiveness with limited speed and load and a low effectiveness with peak torque performances of the internal combustion engine. Compensation can be achieved by changing the power of the turbine with variable flow at peak torques. Variable flow turbines are also more effective in conditions below the maximum speed and load.
  • the aim is to enable a more precise adaptation of the operation of the turbine to the need and the operation of the internal combustion engine.
  • the gas flows are forced through the partition wall in the immediate vicinity of the outer periphery of the rotor.
  • a guide vane ring is not required.
  • the valve-like member to vary the efficiency of the turbine for a predetermined torque curve and over a desired large working range of the internal combustion engine. This leads to an increase in the performance of the internal combustion engine.
  • the new design also allows the use of a compressor with high efficiency at limited engine speeds. You also get a higher torque at lower speeds.
  • European patent application EP-A-86467 (Art. 54.3), which has the same priority, relates to the casing of a turbine for similar purposes to the present turbine, but the casing is also suitable for turbines with fixed geometry and constant flow.
  • the main concern is a continuously decreasing radius of curvature of the inlet section of the housing in such a way that the relatively uniform flow profile of the gases at the inlet of the curved inlet section is converted into a predetermined vortex velocity profile at the outlet of the curved inlet section.
  • the present invention relates to a turbine with variable geometry and thus variable flow conditions and a corresponding design and arrangement of the partition wall characteristic of these turbines, which extends over the inlet section and the volute casing section.
  • valve-like member is adjustable so that the exhaust gases flowing through the secondary inner flow path can be directed against the partition wall, since the maximum radius of curvature is particularly effective even with partial flow through the inner flow path.
  • the partition is arranged so that the outer flow path or paths and the inner flow path or areas in the region of the curved inlet section in the direction from the beginning of the partition wall to the entry into the spiral housing section each have a decreasing radius of curvature.
  • 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 circumferentially spaced turbine blades or blades 34 that 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 carried along, specifically via the connecting shaft 26.
  • the compressor wheel 30 thus 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 restricts the flow path of the gases through the curved housing section 14.
  • the valve 36 is actuated 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 control device 42 can also be designed differently, namely for essentially any linear or non-linear dependency on changes in machine parameters, e.g. B. the operating speed, the load, the manifold inlet pressure, the engine emissions, the smoke density of the exhaust gases exiting the machine and entering the atmosphere, the temperature of the exhaust gases, or any combination of these factors. In addition, the control device 42 can be set to parameters, e.g. B. the speed of the turbine rotor 28 and 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 formed in one piece with the turbine housing and serves to divide the turbine housing 13 into an inner or secondary fluid channel 54 and into an outer or primary fluid channel 56.
  • the cross-sectional area of the outer fluid channel 56 is greater than the cross-sectional area of the inner fluid channel 54.
  • the cross-sectional area of the outer fluid channel 56 is approximately three times the cross-sectional 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 a Inner surface 58 of the spiral housing section 16 together, as can be seen from FIG. 2. 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 of the 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 in a clockwise direction, 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 moves between the open position and the closed position. 5
  • the valve insert 67 is flush with the inner surface of the curved section 14 and permitted. that exhaust gases 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.
  • 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, e.g. B. in terms of 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.
  • the speed of the exhaust gases that strike the blades 34 of the turbine rotor 28 can be increased by partially or fully closing the control valve 36. This in turn leads to an increase in the energy surplus on the turbine rotor 28 in accordance with the well known Euler turbine equation:
  • 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 enables more fuel to be injected into the engine to achieve higher engine torques and to improve transient responsiveness without exceeding exhaust smoke density limits.
  • the control valve 36 can be modulated so that an optimal combination of air / fuel ratio and pressure differential across the engine can be achieved with maximum engine efficiency.
  • the cross-sectional area can be increased and the average radius of curvature of the mass flow can be reduced to monitor the speed of the turbocharger and the boost pressure of the engine.
  • vane-free, nozzle-like turbines according to the invention can process flows of exhaust gases whose speeds are above Mach I without encountering shock problems. This ability to process absolute speeds that exceed supersonic speeds is not available in turbines with guide vanes.

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  • 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 Durchflussregelung für den Spiralgehäuse-einlass einer Radialturbine Expired EP0086466B1 (de)

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 EP0086466A1 (de) 1983-08-24
EP0086466B1 true EP0086466B1 (de) 1987-05-27

Family

ID=23371688

Family Applications (1)

Application Number Title Priority Date Filing Date
EP83101306A Expired EP0086466B1 (de) 1982-02-16 1983-02-11 Durchflussregelung für den Spiralgehäuse-einlass einer Radialturbine

Country Status (10)

Country Link
EP (1) EP0086466B1 (pt)
JP (1) JPS58150028A (pt)
AT (1) ATE27474T1 (pt)
AU (1) AU550503B2 (pt)
BR (1) BR8300621A (pt)
CA (1) CA1206419A (pt)
DE (1) DE3371804D1 (pt)
ES (1) ES519793A0 (pt)
MX (1) MX156452A (pt)
ZA (1) ZA831015B (pt)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9932843B2 (en) 2011-06-10 2018-04-03 Borgwarner Inc. Double flow turbine housing turbocharger

Families Citing this family (12)

* 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
DE102006060907A1 (de) 2006-12-20 2008-06-26 Mp-Engineering Gmbh Abgasturbolader
US7694518B2 (en) * 2007-08-14 2010-04-13 Deere & Company Internal combustion engine system having a power turbine with a broad efficiency range
DE102008020406A1 (de) * 2008-04-24 2009-10-29 Daimler Ag Abgasturbolader für eine Brennkraftmaschine eines Kraftfahrzeugs und Brennkraftmaschine
DE102009056632A1 (de) * 2009-12-02 2011-06-09 Continental Automotive Gmbh Turbolader
KR101051016B1 (ko) 2010-12-14 2011-07-21 한국기계연구원 흡기분리형 터빈
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
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
US10301952B2 (en) * 2014-05-19 2019-05-28 Borgwarner Inc. Dual volute turbocharger to optimize pulse energy separation for fuel economy and EGR utilization via asymmetric dual volutes
WO2024179520A1 (en) * 2023-02-28 2024-09-06 Wuxi Cummins Turbo Technologies Company Ltd. Turbine housing

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1337864A (fr) * 1962-08-07 1963-09-20 Snecma Mode de régulation des turbo-compresseurs de suralimentation et dispositif de mise en oeuvre

Family Cites Families (8)

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CH239435A (de) * 1942-05-23 1945-10-15 Buechi Alfred Freifliegend gelagerte Turbine, insbesondere für heisse Gase.
CA1026234A (en) * 1972-12-06 1978-02-14 Cummins Engine Company Turbine housing
US4027994A (en) * 1975-08-08 1977-06-07 Roto-Master, Inc. Partially divided turbine housing for turbochargers and the like
US4177006A (en) * 1977-09-29 1979-12-04 The Garrett Corporation Turbocharger control
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
DE2934041C2 (de) * 1979-08-23 1983-08-11 Günther Prof. Dr.-Ing. 5100 Aachen Dibelius Gesteuerte Abgasturboladerturbine
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
DE3034271C2 (de) * 1979-09-17 1982-11-11 Ishikawajima-Harima Jukogyo K.K., Tokyo Turbinengehäuse für Turbolader

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1337864A (fr) * 1962-08-07 1963-09-20 Snecma Mode de régulation des turbo-compresseurs de suralimentation et dispositif de mise en oeuvre

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9932843B2 (en) 2011-06-10 2018-04-03 Borgwarner Inc. Double flow turbine housing turbocharger

Also Published As

Publication number Publication date
DE3371804D1 (en) 1987-07-02
ES8402637A1 (es) 1984-02-01
CA1206419A (en) 1986-06-24
BR8300621A (pt) 1983-11-08
JPS58150028A (ja) 1983-09-06
EP0086466A1 (de) 1983-08-24
MX156452A (es) 1988-08-23
ES519793A0 (es) 1984-02-01
ZA831015B (en) 1984-09-26
ATE27474T1 (de) 1987-06-15
AU550503B2 (en) 1986-03-20
AU9165882A (en) 1983-08-25

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