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7 EP 2 657 481 A1 8 In addition, when the width ratio is set to a value larger than 2 (in a case where the cross-sectional area is not changed, the width B is reduced), the surface area of the flow path is increased so that the flow resistance of the exhaust gas is increased, the performance of the turbo charger is degraded, and the weight thereof is increased. Further, when the length in the radial direction is in- creased, the entire size of the turbo charger is increased and mountability on the engine is deteriorated. [0025] Furthermore, the axial length of the exhaust gas flow cross section of the scroll portion is reduced, and hence the depth of a concave portion formed between a turbine chamber wall and the scroll portion is reduced so that it is possible to increase the size of an opening of the concave portion and it becomes easier to make the thickness on the housing side equal to that of the sur- rounding area. As a result, solidification rejection during formation (in a case where the thickness is significantly uneven, a portion having a small thickness is solidified early. However, in the case of a portion having a large thickness, the solidification of the central portion thereof is slow, and a shallow concave portion tends to be formed in the surface portion thereof due to the solidification of the central portion. Deformation is caused in some cas- es.) is prevented and product accuracy is stabilized. [0026] With the above arrangement, it is possible to increase the size of an opening R of a shroud portion 11 formed of the inner peripheral wall 18 of the tongue por- tion 45, a rotor blade side rear wall 19, and a turbine chamber wall 20 of the turbine housing 1, and the occur- rence of the flow of outside air that comes in contact with the opening R is facilitated so that it is possible to radiate heat accumulated not only in the tongue portion 45 but also in the entire circumference of the shroud through the opening R. By suppressing the accumulation of the heat in the tongue portion and the entire circumference of the shroud, it is possible to downgrade the heat resistance of the material used for the turbine housing 5 to achieve a reduction in cost. (Second Embodiment) [0027] In the present embodiment, the description of the same components as those in the first embodiment is omitted by retaining the same reference numerals. On the basis of FIG. 3, a turbine scroll portion according to a second embodiment of the present invention is de- scribed. FIG. 2 is a cross-sectional view in a direction orthogonal to the axis of a turbine rotor of a tongue portion according to the second embodiment of the present invention. 76 denotes a flow path formed of a turbine housing 5 which causes the exhaust gas from an exhaust gas inlet 74 to flow into the scroll portion 4. 75 denotes a connec- tion portion between the flow path 76 and the scroll por- tion 7, and is a tongue portion which separates a rotor blade side passage 77. [0028] In the tongue portion 75, an inclined portion in an exhaust gas flow direction leading to the scroll portion 7 is formed into a shape along a logarithmic spiral. The range of the shape along the logarithmic spiral is from a line S which joins the axis L1 and the tip of the tongue portion to a portion where a line M obtained by inclining the line S toward the exhaust gas inlet 74 by an angle of β about the axis L1 intersects the surface of the tongue portion 75, and the portion in the range is set as a logarithmic spiral portion 78. Although β is set to about 30 degrees in the present em- bodiment, the range of the logarithmic spiral portion 78 may be any range as long as an exhaust gas flow-out angle of the exhaust gas flowing toward the scroll portion 7 from the tongue portion is along the logarithmic spiral, and β may be increased or decreased depending on the situation. The logarithmic spiral is one of spirals often seen in the natural world and is also called an equiangular spiral. As the nature of the logarithmic spiral, as shown in FIG. 3, an angle b formed between a line drawn from the rotation center at an angle θ and a tangent at an intersection point of the line and the spiral is always constant. [0029] By having the above structure, a flow-out angle γ from the tongue portion 75 and an exhaust gas flow-out angle γ to the rotor blade 3 match with each other so that it is possible to facilitate the exhaust gas flow in the scroll portion to fully deliver the performance of the turbo charg- er. The intersection angle of the flow path of the tongue por- tion and the scroll portion is increased, a cooling space 79 can be provided at the corresponding portion, and a part of the tongue portion 75 is exposed to outside air so that it is possible to effectively suppress an increase in the temperature of the tongue portion. INDUSTRIAL APPLICABILITY [0030] The present invention is suitably used in a radial turbine which is used in an internal combustion engine or the like in order to improve the output of the internal combustion engine, and is configured such that a turbine rotor is rotationally driven by causing exhaust gas to flow in from a spiral scroll portion in a radial direction, act on a rotor blade, and then flow out in an axial direction. Claims 1. A scroll structure for a radial turbine or a diagonal flow turbine configured such that a turbine rotor is rotationally driven by causing exhaust gas to flow from a spiral scroll portion formed in a turbine hous- ing toward a rotor blade of the scroll portion in a radial direction, and act on the rotor blade, then flow out in an axial direction, wherein a concave portion as a heat radiation space is formed in a shroud portion formed between the scroll portion 5 10 15 20 25 30 35 40 45 50 55 5PDF Image | EP 2 657 481 A1 EUROPEAN PATENT APP
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