WO1982000686A1 - Turbine avec restriction variable dans l'admission de la turbine - Google Patents

Turbine avec restriction variable dans l'admission de la turbine Download PDF

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Publication number
WO1982000686A1
WO1982000686A1 PCT/SE1981/000197 SE8100197W WO8200686A1 WO 1982000686 A1 WO1982000686 A1 WO 1982000686A1 SE 8100197 W SE8100197 W SE 8100197W WO 8200686 A1 WO8200686 A1 WO 8200686A1
Authority
WO
WIPO (PCT)
Prior art keywords
turbine
turbine casing
casing
accordance
wall
Prior art date
Application number
PCT/SE1981/000197
Other languages
English (en)
Inventor
Scania Ab Saab
Original Assignee
Johansson A
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 Johansson A filed Critical Johansson A
Priority to DE19813152261 priority Critical patent/DE3152261A1/de
Publication of WO1982000686A1 publication Critical patent/WO1982000686A1/fr

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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
    • 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 a turbine, preferably an exhaust- driven turbine forming part of the supercharger of an internal combustion engine provided with a mechanism for variable restriction in a peripheral inflow duct leading to a turbine rotor rotatably located within the turbine casing.
  • exhaust gas pulsations may lead to mechanical stresses, whereby the said stresses may give rise to vibration problems in respect of the flap which is rotatably supported at one end.
  • the flap and in particular its end part is subject to high thermal stresses owing to difficulties in dissipating heat from the flap.
  • the heat problem is especially noticeable with turbines forming part of petrol engine superchargers since in the application the turbine is driven by exhaust gases which are hotter than the exhaust gases from a diesel engine.
  • the object of the present invention consists in designing a turbine, preferably an exhaust-driven turbine, which is free from the said disadvantages.
  • the turbine in accordance with the invention is provided with a mechanism to bring about a variable restriction within a peripheral inflow duct leading to a turbine rotor rotatably located in the turbine casing, whereby the invention is in the main characterised in that the restriction can be adjusted by radial displacement of an outer wall section in the turbine casing forming a boundary of the inflow duct, in that the said wall section comprises a number of wall elements connected with one another in an articulated manner, with at least two wall elements being supported, in respect of the turbine casing, in an articulated and/or displaceable manner, and in that the wall section is arranged, at its respective ends, for connection to fixed wall sections in the turbine casing, the area of the flow duct being substantially unchanged and so as to form, in conjunction with the said fixed wall sections, a helical inlet.
  • the design in accordance with the invention comprises a number of co-operating wall elements throttling the flow in lengthwise direction is enabled, as a result of which losses of energy due to abrupt changes in throughput are largely eliminated. This in turn causes also the thermal and mechanical stresses to which the design in accordance with the invention is subject to be reduced by comparison with restricting devices according to known technology.
  • the wall elements are connected to fixed inlet surfaces of the turbine casing enables relatively efficient heat transfer to the surrounding turbine casing as well as evenly distributed absorption of external forces.
  • one wall element is rotatably supported in respect of the turbine casing whereas a wall element connected in an articulated manner with the former is displaceably and rotatably arranged in respect of the turbine casing.
  • the said features constitute prerequisites for designing, with only two wall elements, a simple mechanism in accordance with the invention.
  • at least one wall element is fixed in an articulated manner within the turbine casing, with at least one wall element being linked in an articulated manner with an arm or similar device rotatably supported within the turbine casing, whereby the said am or similar device is so arranged as to be acted upon by rotary movements for adjusting the wall elements and, accordingly, the restriction of the turbine inlet.
  • FIG. 2 corresponding substantially to a section A-A in figure 1.
  • a specimen turbine in accordance with the figures is intended to form part of a supercharger not shown of an internal combustion engine of petrol engine type.
  • the said turbine consists in the main of a turbine casing 2 and a turbine rotor 4 rotatably supported therein.
  • the turbine has a tangential inlet 1 , with the said inlet 1 passing into a helical inflow duct 3 which is provided in turbine casing 2 and leads to turbine rotor 4.
  • exhaust gases are fed in known manner from the internal combustion engine via inflow duct 3 towards a number of blades (not shown) of turbine rotor 4, whereupon the exhaust gases are conducted radially inward giving off energy at this stage.
  • inflow duct 3 consists of a mechanism 10 in accordance with the invention for adjusting the inflow restriction.
  • Mechanism 10 consists substantially of three parts, i.e. a sector-shaped lever 16 and two flaps 17 and 18 respectively located one after the other in the direction of flow and connected with one another in an articulated manner, the said flaps constituting wall elements and jointly forming an outer wall section adjustable in respect of inflow duct 3.
  • the sector-shaped lever 16 is connected in a torsionally rigid manner with a shaft 15 rotatably supported within the turbine casing, and to the sector-shaped shaft ⁇ G is secured a journal 19 with flap 17 being rotatably located about the latter.
  • the other end of flap 17 is, as previously stated, connected with flap 18 by a common bearing 20 which constitutes a displaceable pivot for the flaps 17,18.
  • the other end of flap 18 is, via a shaft 21, rotatably supported in respect of turbine casing 2.
  • Mechanism 10 is controlled by an external actuator 11 so as to take up various positions capable of being adjusted in the radial direction.
  • Actuator 11 conveniently consists in an ordinary pressure cell in which a diaphragm and a spring (not shown) act, subject to the influence of a pressure medium such as the prevailing gas pressure in the engine intake system and/or exhaust system, on a control rod 12 imparting to it an axial displacement.
  • Control rod 12 is connected in an articulated manner with a lever 13 secured to shaft 15, the displacement of rod 12 imparting a rotary movement to lever 13, which is transmitted, via shaft 15 supported in turbine casing 2, to the adjusting mechanism 10.
  • projection 25 comprises two substantially plane side walls 26, 27 in which flaps 17,18 are arranged, the said flaps having straight lateral edges.
  • flaps 17,18 are designed with a curvature matching the curvatures of the fixed sections in turbine casing 2.
  • Figure 2 shows the design of end part 28 of flap 18 projecting in the direction of flow.
  • the sector-shaped lever 16 is provided with an outer surface 29 covering the transition between the throat-shaped turbine inlet 1 and mechanism 10.
  • the gaps between surfaces capable of dis- placement in respect of one another are minimised by overlapping at the bearings 19, 20. Gaps shown in the figures are enlarged in order to facilitate their illustration.
  • Projection 25 is provided with a special space beneath mechanism 10, in which exhaust gases collect during operation of the engine thus forming a damping cushion of gas which counteracts flap vibrations and flutter.
  • Mechanism 10 In order to make them resistant to high exhaust temperatures components forming part of mechanism 10 are advantageously constructed with the aid of a ceramic material. The tolerance requirements in respect of bearings and gaps can be kept low, which facilitates the co-operation of materials having different coefficients of linear expansion.
  • casing 2 is made separable in two halves, preferably in cross-section at right angles to turbine shaft 5.
  • projection 25 is provided with sections capable of being opened thus enabling the said assembly.
  • the dashed lines in figure 1 show mechanism 10 in a position corresponding to maximum flow area. In this case too the radial distance between flaps 17, 18 and turbine shaft 5 is substantially subject to gradual reduction in the direction of flow.
  • mechanism 10 in accordance with the invention may comprise only two flaps 17,18, with the second flap 17 rotatably supported in respect of casing 2 and connected with the outer actuator 11 in a torsionally rigid manner.
  • the power-transmitting action of the latter on mechanism 10 in accordance with the invention can be brought about by a shaft connected to any wall element and rotatably supported in casing 2 or by applying a force direct to the mechanism in a position between the bearing points and in substance radially in respect of the turbine shaft.
  • Both the maximum and minimum restriction inflow areas can be made adjustable from outside, depending on the end position of mechanism 10. The said end position can be regulated with the aid of staybolts etc., which the wall elements of the mechanism are made to abut.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)

Abstract

Turbine, de preference une turbine entrainee par les gaz d'echappement faisant partie du surcompresseur d'un moteur a combustion interne, pourvue d'un mecanisme (10) de restriction variable dans la conduite d'admission peripherique (3) debouchant sur un rotor de turbine (4) monte de maniere rotative dans l'enveloppe (2) de la turbine. Le but de l'invention est d'empecher que, lorsque l'on procede a une regulation par etranglement de l'admission d'air dans la turbine, des perturbations ne se produisent dans l'ecoulement d'admission provoquant une perte d'energie et d'empecher ou au moins de reduire le developpement de contraintes mecaniques et thermiques dans le dispositif commandant l'action d'etranglement. A cet effet, la turbine de l'invention se caracterise en ce que la restriction peut etre ajustee par deplacement radial d'une section de paroi externe dans l'enveloppe (2) de la turbine formant une separation de la conduite d'admission (3), en ce que cette section de paroi comprend plusieurs elements de paroi (16, 17, 18) relies les uns aux autres de maniere articulee, au moins deux d'entre eux etant supportes de maniere articulee et/ou deplacable par rapport au corps (2) de la turbine, et en ce que la section de paroi est concue a ses extremites respectives de maniere a se connecter, lorsqu'elle est soumise a une surface sensiblement inchangee de la conduite d'ecoulement, aux sections de paroi fixes du corps de turbine (2) et a former avec ce dernier une admission helicoidale debouchant sur le rotor de turbine (4).
PCT/SE1981/000197 1980-08-14 1981-06-30 Turbine avec restriction variable dans l'admission de la turbine WO1982000686A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
DE19813152261 DE3152261A1 (de) 1980-08-14 1981-06-30 Turbine with variable restriction in turbine inlet

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
SE8005747A SE8005747L (sv) 1980-08-14 1980-08-14 Turbin med variabel kontraktion i turbininlopp
SE8005747800814 1980-08-14

Publications (1)

Publication Number Publication Date
WO1982000686A1 true WO1982000686A1 (fr) 1982-03-04

Family

ID=20341558

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/SE1981/000197 WO1982000686A1 (fr) 1980-08-14 1981-06-30 Turbine avec restriction variable dans l'admission de la turbine

Country Status (3)

Country Link
GB (1) GB2094409B (fr)
SE (1) SE8005747L (fr)
WO (1) WO1982000686A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0212834A2 (fr) * 1985-07-17 1987-03-04 Geoffrey Light Wilde Admission variable pour une turbine radiale
US4664594A (en) * 1985-02-06 1987-05-12 Societe Nationale D'etude Et De Construction De Moteur D'aviation (S.N.E.C.M.A.) Device for varying the fluid passage area between adjacent turbine stator vanes
US4728259A (en) * 1985-06-25 1988-03-01 Rohren- Und Pumpenwerk Rudolf Bauer Gesellschaft M.B.H. Adjustable turbine
US4799856A (en) * 1986-09-17 1989-01-24 Mitsubishi Jukogyo Kabushiki Kaisha Variable capacity radial flow turbine

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2178111B (en) * 1985-07-17 1990-02-28 Geoffrey Light Wilde Improvements in or relating to a variable inlet for a radial turbine

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1577168A (fr) * 1967-08-29 1969-08-01
DE2151658A1 (de) * 1971-10-16 1973-04-19 Daimler Benz Ag Zentripetalturbine eines abgasturboladers

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1577168A (fr) * 1967-08-29 1969-08-01
DE2151658A1 (de) * 1971-10-16 1973-04-19 Daimler Benz Ag Zentripetalturbine eines abgasturboladers

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4664594A (en) * 1985-02-06 1987-05-12 Societe Nationale D'etude Et De Construction De Moteur D'aviation (S.N.E.C.M.A.) Device for varying the fluid passage area between adjacent turbine stator vanes
US4728259A (en) * 1985-06-25 1988-03-01 Rohren- Und Pumpenwerk Rudolf Bauer Gesellschaft M.B.H. Adjustable turbine
EP0212834A2 (fr) * 1985-07-17 1987-03-04 Geoffrey Light Wilde Admission variable pour une turbine radiale
EP0212834A3 (en) * 1985-07-17 1987-10-14 Geoffrey Light Wilde Variable inlet for a radial turbine
US4729715A (en) * 1985-07-17 1988-03-08 Wilde Geoffrey L Variable inlet for a radial turbine
US4799856A (en) * 1986-09-17 1989-01-24 Mitsubishi Jukogyo Kabushiki Kaisha Variable capacity radial flow turbine

Also Published As

Publication number Publication date
GB2094409B (en) 1984-07-18
GB2094409A (en) 1982-09-15
SE8005747L (sv) 1982-02-15

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