EP0086467A1 - Volute pour une turbine radiale - Google Patents

Volute pour une turbine radiale Download PDF

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Publication number
EP0086467A1
EP0086467A1 EP83101307A EP83101307A EP0086467A1 EP 0086467 A1 EP0086467 A1 EP 0086467A1 EP 83101307 A EP83101307 A EP 83101307A EP 83101307 A EP83101307 A EP 83101307A EP 0086467 A1 EP0086467 A1 EP 0086467A1
Authority
EP
European Patent Office
Prior art keywords
section
curved
inlet
turbine
inlet section
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP83101307A
Other languages
German (de)
English (en)
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
Publication of EP0086467A1 publication Critical patent/EP0086467A1/fr
Withdrawn legal-status Critical Current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

Definitions

  • the invention relates to a housing for turbines, in particular exhaust gas turbines for driving turbochargers for internal combustion engines, consisting of a spiral housing section oriented around the axis of rotation of the turbine rotor with an inlet end arranged at a distance from the axis of rotation, and an inlet section adjoining the inlet end.
  • nozzle-type turbines have a housing with a straight inlet section connected to a volute section.
  • the straight section decreases towards the inlet of the volute section so that the flowing exhaust gases are supplied to the volute section at an almost uniform velocity profile.
  • the uniform velocity profile is converted into a vortex profile.
  • the vortex profile is such that the magnitude of the velocities along adjacent flow lines is inversely proportional to the radius of curvature of the flow line in question.
  • the radius of curvature also decreases constantly along each of these flow lines within the volute casing section. The result is that the tangential Speed increases.
  • the speed of a given flow line entering the turbine rotor is dependent on the decrease in the length of the radius of curvature of this flow line from the inlet of the volute section to the periphery of the turbine rotor. This means that for a given flow line, the change in the radius of curvature before the flow line enters the turbine radius is greater, the longer the radius of curvature is when it enters the spiral housing section. This leads to a non-uniform speed and pressure distribution around the circumference of the turbine rotor, both of which are very disruptive to the effectiveness of the turbine.
  • the velocities along flow lines with a large change in the radius of curvature measured from the entrance to the volute section inwards to the periphery of the turbine rotor increase more than the velocities along flow lines with a smaller change in the radius of curvature. This leads to a non-uniform flow in the circumferential direction around the circumference of the turbine rotor.
  • This angle of incidence is the angle formed between a line that extends outward and parallel to the plane of a turbine blade and a vector that represents the velocity of the exhaust gases relative to the turbine blades. There may be a different angle of incidence for each flow line due to the non-uniform velocity profile of the exhaust gases around the circumference of the turbine rotor.
  • the inlet section of the housing is curved, has a continuously decreasing radius of curvature in the direction of flow and has a sufficient arc length to convert the relatively uniform flow profile of the gases at the inlet of the curved inlet section into a predetermined vortex speed profile at the outlet of the to convert curved inlet portion.
  • the new turbine housing provides an essentially uniform flow of the exhaust gases on the circumference of the turbine rotor.
  • the curved inlet section should have an arc length of at least about 30 °.
  • the curved inlet section expediently has a constant cross-sectional area shape of its flow path along its length. However, in some cases it can also have a changing cross-sectional area shape of its flow path along its length.
  • the cross-sectional area can either be constant over the entire length or converge, ie decrease, from the inlet end to the opposite end. It is important that the curved section has a continuously decreasing radius of curvature for each of the flow lines in the direction of the fluid flow.
  • the uniform velocity profile of the exhaust gases is converted to a swirl velocity profile upon entry of the curved inlet section, through the gases through the curved section and during the time that the fluid reaches the inlet of the volute section.
  • the new turbine housing is suitable both for turbines with a fixed geometry and with variable flow, in each case in the case of nozzle-free turbines that are free of guide vanes.
  • the new housing ensures that the velocity profile of the flowing exhaust gases is changed so that there is an essentially uniform flow on the circumference of the tube rotor.
  • the known turbine 10 shown in FIG. 1 has a housing 12 with a spiral housing section 14 and a straight inlet section 16.
  • the straight inlet section 16 has decreasing cross-sectional areas with a fluid inlet 18 at one end surrounded by a flange 20.
  • the flange 20 is used for screwing onto the exhaust manifold of an internal combustion engine.
  • the turbine 10 further includes a tongue 22 with a tip 24 that is near the entrance of the volute section 14 and near the periphery of the turbine rotor 26.
  • the turbine rotor 26 is connected in the volute casing section 14 and arranged on a rotatable connecting shaft 28, which also supports a compressor wheel (not shown) at the opposite end.
  • the turbine rotor 26 comprises a plurality of turbine blades 30 which receive the exhaust gases and guide them inwards to the center of the turbine 10. The exhaust gases then exit through an outlet, not shown.
  • the hot exhaust gases exit the various combustion chambers of an internal combustion engine they are passed through an exhaust manifold into the inlet 18 of the turbine 10, with a relatively uniform velocity profile, as indicated by the plurality of flow lines, the velocity vectors of which are all approximately the same length exhibit.
  • the exhaust gas flow through the straight inlet section 16 is accelerated by the converging cross section of the inlet section 16.
  • the relatively uniform velocity profile of the exhaust gases from the entrance to the entrance of the volute 14 is not affected.
  • This is also represented by the plurality of flow lines, each having a tangential velocity vector of the same length.
  • FIG. 2 This shows a turbine 40 which has an improved housing 42.
  • This consists of a spiral housing section 44 and a curved inlet section 46.
  • the curved inlet section 46 has a fluid inlet 48 at one end, which is surrounded by a flange 50. This is used to screw onto the exhaust manifold of an internal combustion engine.
  • the opposite end 51 of the curved housing section 46 is connected to the inlet of the spiral housing section 44.
  • the curved portion 46 includes an inner surface 52 which mates with the inner surface 45 of the volute section 44 to form a tongue 53 having a tip 54. This is located approximately at the entrance of the spiral housing section 46 and adjacent in the periphery of the turbine rotor 56.
  • the turbine rotor 56 is connected to a rotatable connecting shaft 58, which has a compressor wheel (not shown) on the opposite side End supported.
  • the turbine rotor 56 comprises a plurality of turbine blades 60 which receive the exhaust gases and guide them inwards to the center of the turbine 40. The exiting gases are led to an outlet, not shown.
  • the hot exhaust gases exit the various combustion chambers of the internal combustion engine they are passed through an exhaust manifold into the inlet 48 of the turbine 40 with a relatively uniform velocity profile.
  • This uniform speed profile is represented by a large number of flow lines with speed vectors, all of which have approximately the same length.
  • the velocity profile of the exhaust gases is converted into a vortex distribution, the exhaust gases being accelerated.
  • a sufficient length for the curved section 46 is an arc extension of at least 30 °. The extension is preferably between 30 and 180 °. Expansions over an angular range of 45 to 90 ° have proven effective. However, an angular extent of 60 0 is preferred.
  • the arcuate extension allows the flow lines near the inner surface 52 of the curved portion 46 to be accelerated to a greater extent than the outer flow lines. This means that the flow lines within the volute section 44 that run near the periphery of the turbine rotor 56 have a greater velocity value compared to other velocity values measured in a radial plane. This applies to any point around the circumference of the turbine rotor 56.
  • the curved housing section 46 has a cross-sectional flow area which, measured from the inlet 48 to the opposite end 51, is either constant or decreasing. A decreasing cross-sectional area is preferred, in which the inner surface 52 of the curved housing section 56 converges in such a way that the incoming exhaust gases can be accelerated.
  • the radius of curvature mentioned above can be calculated using the calculation method in HARothdart's "Mechanical design and systems handbook” (1964 McGraw-Hill Book Co. New York, page 58).
  • the continuously decreasing radius of curvature of each flow line leads to an acceleration of the speed along each flow line, according to the following equation:
  • Accelerating the velocity of the exhaust gases leads to a favorable pressure gradient for thin boundary layers and prevents the exhaust gas flow from lifting off from the inner walls of the curved housing section 46.
  • FIGS. 3 to 5 Here, three exemplary embodiments are selected for a curved housing section with an angular extent of approximately 90 and a continuously decreasing radius of curvature in the direction of FIG. Gas flow.
  • FIG. 3 A side view and two end views of the curved section are shown in the figures.
  • the cross-sectional area at the inlet 64 of the curved housing section 62 is the same in size and in shape similar to the cross-sectional area at the outlet 66.
  • the values h 1 and h 2 or b 1 and b 2 shown in the figure are each the same.
  • the cross-sectional area at the inlet 70 of the curved housing section 68 is larger than the cross-sectional area at the outlet 72.
  • One way of achieving this difference in area is to maintain a constant height and to reduce the width.
  • h l h 2
  • b 1 is greater than b 2 .
  • the curved housing section 74 has an axial divider 76, so that two flow channels 78 and 80 lying side by side are formed.
  • the axial divider 76 is particularly favorable when the turbine is connected to an internal combustion engine with an odd number of cylinders.
  • Two exhaust manifolds are connected to the exhaust ports of the internal combustion engine and to the curved housing portion 74 so that the exhaust gases are directed from one half of the cylinders into the channel 78 and the exhaust gases from the other cylinders into the channel 80.
  • the distribution of the cylinders is chosen depending on their firing order in such a way that the energy of the turbine is maximized. In Fig.
  • each channel 78 and 80 at inlet 82 is greater than at outlet 84.
  • the difference here can be achieved by reducing the inner area of curved portion 74 to provide channels 78 and 80 at outlet 84 to the desired size and convert form.
  • the inner shape of the curved portion 74 at the outlet 84 preferably matches the inner shape at the entrance of the volute section. It should be noted that although only three different embodiments are selected, other embodiments can be used as long as there are no abrupt changes to the interior walls.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP83101307A 1982-02-16 1983-02-11 Volute pour une turbine radiale Withdrawn EP0086467A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US34928782A 1982-02-16 1982-02-16
US349287 1982-02-16

Publications (1)

Publication Number Publication Date
EP0086467A1 true EP0086467A1 (fr) 1983-08-24

Family

ID=23371704

Family Applications (1)

Application Number Title Priority Date Filing Date
EP83101307A Withdrawn EP0086467A1 (fr) 1982-02-16 1983-02-11 Volute pour une turbine radiale

Country Status (6)

Country Link
EP (1) EP0086467A1 (fr)
JP (1) JPS58150007A (fr)
AU (1) AU9165782A (fr)
BR (1) BR8300622A (fr)
ES (1) ES281744Y (fr)
ZA (1) ZA831014B (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2533968A1 (fr) * 1982-09-30 1984-04-06 Household Mfg Inc Turbine a admission radiale du fluide et procede pour son utilisation
US4822242A (en) * 1987-06-09 1989-04-18 Yoichi Yamazaki Variable capacity turbo supercharger
DE102007025671A1 (de) * 2007-06-01 2008-12-04 Ecoenergy Patent Gmbh Entspannungsvorrichtung und Verfahren zur Energieumwandlung
WO2010100348A1 (fr) * 2009-03-03 2010-09-10 Melchior Jean F Moteur a combustion interne suralimente

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH10231706A (ja) * 1997-02-19 1998-09-02 Mitsubishi Heavy Ind Ltd タービンスクロール

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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

Non-Patent Citations (1)

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

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2533968A1 (fr) * 1982-09-30 1984-04-06 Household Mfg Inc Turbine a admission radiale du fluide et procede pour son utilisation
US4822242A (en) * 1987-06-09 1989-04-18 Yoichi Yamazaki Variable capacity turbo supercharger
DE102007025671A1 (de) * 2007-06-01 2008-12-04 Ecoenergy Patent Gmbh Entspannungsvorrichtung und Verfahren zur Energieumwandlung
DE102007025671B4 (de) * 2007-06-01 2010-07-29 Ecoenergy Patent Gmbh Entspannungsvorrichtung und Verfahren zur Energieumwandlung
WO2010100348A1 (fr) * 2009-03-03 2010-09-10 Melchior Jean F Moteur a combustion interne suralimente

Also Published As

Publication number Publication date
JPS58150007A (ja) 1983-09-06
ZA831014B (en) 1984-09-26
AU9165782A (en) 1983-09-01
BR8300622A (pt) 1983-11-08
ES281744Y (es) 1988-06-16
ES281744U (es) 1985-11-16

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PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

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AK Designated contracting states

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

17P Request for examination filed

Effective date: 19840210

ITCL It: translation for ep claims filed

Representative=s name: LENZI & C.

EL Fr: translation of claims filed
STAA Information on the status of an ep patent application or granted ep patent

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18W Application withdrawn

Withdrawal date: 19850625

RIN1 Information on inventor provided before grant (corrected)

Inventor name: KAESSER, MERLE LAVERN