Variable geometry exhaust turbocharger

Abstract

An object is to provide a variable-geometry exhaust turbocharger including a variable nozzle mechanism in which nozzle supports may not deform under a high-temperature condition. A variable-geometry exhaust turbocharger (1) includes: a nozzle mount (2); a nozzle support (6) having a first end coupled to a first face (2a) of the nozzle mount; a nozzle plate (4) coupled to the second end of the nozzle support and supported to be separated from the first face (2aa) of the nozzle mount, the nozzle plate having a first face (4a) coupled to the nozzle support and a second face (4b) which is opposite to the first face and which faces an exhaust gas channel (20) through which exhaust gas flows: a plurality of nozzle vanes (8) rotatably supported between the nozzle mount and the nozzle plate; and a variable nozzle mechanism (10) configured to change vane angles of the nozzle vanes to control a flow of the exhaust gas flowing between the nozzle mount and the nozzle plate. The nozzle plate is formed of a material having a smaller linear expansion coefficient than that of a material forming the nozzle mount.

Claims

1. A variable-geometry exhaust turbocharger, comprising: a nozzle mount fixed to a housing, the nozzle mount having a first face and a second face; a nozzle support having a first end coupled to the first face of the nozzle mount, the nozzle support being a cylindrical member; a nozzle plate coupled to a second end of the nozzle support and supported to be separated from the first face of the nozzle mount, the nozzle plate having a first face coupled to the nozzle support and a second face which is opposite to the first face; a plurality of nozzle vanes rotatably supported between the first face of the nozzle mount and the first face of the nozzle plate; and a variable nozzle mechanism configured to change vane angles of the nozzle vanes to control a flow of an exhaust gas flowing between the first face of the nozzle mount and the first face of the nozzle plate, wherein the nozzle support is capable of tilting along a radial direction due to a difference in an amount of thermal deformation between the nozzle mount and the nozzle plate, wherein the nozzle mount is exposed to the exhaust gas only at the first face, and wherein the nozzle plate is exposed to the exhaust gas at both the first face and the second face and is formed of a material having a smaller linear expansion coefficient than that of a material forming the nozzle mount.

2. The variable-geometry exhaust turbocharger according to claim 1, wherein the nozzle plate is formed of heat-resistant Ni-base alloy, and wherein the nozzle mount is formed of stainless steel.

3. The variable-geometry exhaust turbocharger according to claim 1, wherein the nozzle plate and the nozzle mount are formed of different kinds of heat-resistant Ni-base alloy having different linear expansion coefficients.

4. The variable-geometry exhaust turbocharger according to claim 1, wherein the materials forming the nozzle plate and the nozzle mount are each selected so that an absolute value of an extension rate difference A defined by the following equation (1) is not greater than 0.20%:
A={α1×(T1−T)−α2(T2−T)}×100  Equation (1), where: α1 is a linear expansion coefficient of the material forming the nozzle plate; α2 is a linear expansion coefficient of the material forming the nozzle mount; T1 is a temperature of the nozzle plate during operation of an engine; T2 is a temperature of the nozzle mount during operation of the engine; and T is a reference temperature.

5. The variable-geometry exhaust turbocharger according to claim 1, wherein the variable-geometry exhaust turbocharger is used in a gasoline engine.

Description

BRIEF DESCRIPTION OF DRAWINGS

(1) FIG. 1 is a cross-sectional view of a variable-geometry exhaust turbocharger according to one embodiment of the present invention.

(2) FIG. 2 is a cross-sectional view taken along line B-B of FIG. 1.

(3) FIG. 3 is a cross-sectional view taken along line A-A of FIG. 2.

(4) FIG. 4 is a graph of a relationship between linear expansion coefficients and temperature of stainless steel and heat-resistant Ni-base alloy A, B.

(5) FIG. 5 is a chart of linear expansion coefficients of stainless steel and two kinds of heat-resistant Ni-base alloy A, B at temperatures of 900° C. and 1000° C.

(6) FIG. 6 is a chart of differences (extension ratio differences) in the amount of thermal deformation of a nozzle mount and a nozzle plate in cases where stainless steel and the heat-resistant Ni-base alloy A, B are used in the nozzle mount and the nozzle plate.

(7) FIG. 7 is a graph of FIG. 6.

(8) FIG. 8 is a graph of a relationship between proof strength and temperature of stainless steel and heat-resistant Ni-base alloy.

(9) FIG. 9 is a diagram of a state where a nozzle plate and a nozzle mount are deformed to extend, and a shear force or a bending moment is applied to nozzle supports which couple the nozzle plate and the nozzle mount.

(10) FIG. 10 is a chart of linear expansion coefficients of stainless steel at temperatures of 850° C. and 760° C.

(11) FIG. 11 is a chart of extension rates of stainless steel at temperatures of 850° C. and 760° C., and an extension rate difference between the temperatures.

DETAILED DESCRIPTION

(12) Embodiments of the present invention will now be described in detail with reference to the accompanying drawings. It is intended, however, that unless particularly specified, dimensions, materials, shapes, relative positions and the like of components described in the embodiments shall be interpreted as illustrative only and not limitative of the scope of the present invention.

(13) FIG. 1 is a cross-sectional view of a variable-geometry exhaust turbocharger according to one embodiment of the present invention. FIG. 2 is a cross-sectional view taken along line B-B of FIG. 1. FIG. 3 is a cross-sectional view taken along line A-A of FIG. 2. First, the basic configuration of a variable nozzle mechanism 10 of a variable-geometry exhaust turbocharger 1 according to one embodiment of the present invention will be described in reference to FIGS. 1 to 3.

(14) As illustrated in FIG. 1, the variable-geometry exhaust turbocharger 1 according to one embodiment of the present invention includes a turbine housing 16 for accommodating a turbine rotor 12, and a bearing housing 18 for accommodating a bearing 22 rotatably supporting a rotational shaft 12a of the turbine rotor 12. The turbine housing 16 and the bearing housing 18 are fastened to each other via bolts, for instance. Although not illustrated, a compressor housing for accommodating a compressor rotor coupled to the rotational shaft 12a is coupled to the bearing housing 18 at the opposite side of the turbine housing 16 across the bearing housing 18.

(15) On the outer circumferential side of the turbine housing 16, an exhaust gas channel 20 of a scroll shape is formed. The exhaust gas channel 20 communicates with an exhaust-gas manifold (not illustrated), and exhaust gas discharged from an engine flows through the exhaust gas channel 20. Further, a variable nozzle mechanism 10 for controlling the flow of the exhaust gas acting on the turbine rotor 12 is disposed between the exhaust gas channel 20 of a scroll shape and the turbine rotor 12.

(16) As illustrated in FIG. 1, the variable nozzle mechanism 10 is fixed to the bearing housing 18 by the nozzle mount 2 being fastened to the bearing housing 18 by bolts or the like while the variable nozzle mechanism 10 is interposed between the turbine housing 16 and the bearing housing 18. Also, as illustrated in FIG. 3, the variable nozzle mechanism 10 includes a plurality of nozzle supports 6 each of which is a cylindrical member and has the first end coupled to a first face 2a of the nozzle mount 2. Moreover, the first face 4a of the nozzle plate 4 is coupled to the second end of each nozzle support 6. The plurality of nozzle supports 6 are coupled to the first face 2a of the nozzle mount 2 and to the first face 4a of the nozzle plate 4 in a circumferential fashion in the planar view. In this way, the nozzle plate 4 is supported at a position spaced away from the first face 2a of the nozzle mount 2.

(17) As illustrated in FIGS. 2 and 3, a drive ring 5 formed into a disc-like shape is disposed rotatably on the second face 2b of the nozzle mount 2. An end of each lever plate 3 is coupled to the drive ring 5. The opposite end of each lever plate 3 is coupled to a nozzle vane 8 via a nozzle shaft 8a, so that each lever plate 3 rotates and the vane angle of each nozzle vane 8 varies in response to rotation of the drive ring 5.

(18) In the variable-geometry exhaust turbocharger 1 including the variable nozzle mechanism 10 with the above configuration, the exhaust gas having flowed through the exhaust gas channel 20 of a scroll shape flows into a gap between the nozzle mount 2 and the nozzle plate 4, and then to the central portion of the turbine housing 16 as the nozzle vanes 8 control the flow direction, as indicated by the arrow “f” of FIG. 1. Then, after acting on the turbine rotor 12, the exhaust gas is discharged to the outside from the exhaust gas outlet 24.

(19) At this point, as illustrated in FIG. 1, the nozzle plate 4 is disposed so that the second face 4b, disposed on the opposite side of the first face 4a to which the nozzle supports 8 are coupled, faces the exhaust gas channel 20 thorough which the exhaust gas flows. That is, the nozzle plate 4 is exposed to the exhaust gas at both of the first face 4a and the second face 4b. In contrast, the nozzle mount 2 is in contact with the exhaust gas only at the first face 2a, so that the second face 2b is oriented to face the bearing housing 18 side and not exposed to the exhaust gas.

(20) As described above, since the nozzle plate 4 is exposed to the exhaust gas at both faces 4a, 4b while the nozzle mount 2 is in contact with the exhaust gas only at the first face 2a, the temperature of the nozzle plate 4 becomes higher than that of the nozzle mount 2 while the engine is in operation. According to the research of the inventors, the temperature of the nozzle plate 4 rises as high as 850° C. in the case of a diesel engine with the exhaust gas temperature of approximately 850° C., while the temperature of the nozzle mount 2 only rises to 760° C. Further, in the case of a gasoline engine with the exhaust gas temperature of approximately 1000° C., the temperature of the nozzle plate 4 rises as high as 1000° C. while the temperature of the nozzle mount 2 only rises to 850° C.

(21) When the nozzle mount 2 and the nozzle plate 4 have different temperatures as described above, a shear force or a bending moment acts on the nozzle support 6 coupling the nozzle mount 2 and the nozzle plate 4 under a high-temperature condition due to the difference in the amount of thermal deformation between the nozzle mount 2 and the nozzle plate 4, thereby possibly deforming the nozzle support 6. Thus, in at least one embodiment of the present invention, the nozzle plate 4 is formed of a material having a linear expansion coefficient smaller than that of a material forming the nozzle mount 2 so as to reduce the difference between the amount of thermal deformation between the nozzle mount 2 and the nozzle plate 4 under a high-temperature condition as will be described below.

(22) In one embodiment of the present invention, as materials of the nozzle mount 2 and the nozzle plate 4, stainless steel and heat-resistance Ni-base alloy including Inconel (Registered trademark) such as Inconel 600, Inconel 625, Inconel 718, and Inconel 750X and Hastelloy (Registered trademark) such as Hastelloy C22, Hastelloy C276, and Hastelloy B may be used suitably.

(23) FIG. 4 is a graph of a relationship between linear expansion coefficients and temperature of stainless steel and two kinds of heat-resistant Ni-base alloy A, B. FIG. 5 is a chart of linear expansion coefficients of stainless steel and two kinds of heat-resistant Ni-base alloy A, B at temperatures of 900° C. and 1000° C. As illustrated in FIGS. 4 and 5, the two kinds of heat-resistant Ni-base alloy A, B have linear expansion coefficients smaller than that of stainless steel. Also, from among the two kinds of heat-resistant Ni-base alloy A, B, the heat-resistant Ni-base alloy B has a linear expansion coefficient smaller than that of the heat-resistant Ni-base alloy A. In the present description, “a liner expansion coefficient is small” means that a linear expansion coefficient is small when compared between two kinds of materials under a predetermined temperature condition during operation of an engine (for instance, 1000° C. which is an exhaust gas temperature during operation of a gasoline engine).

(24) FIG. 6 is a chart of differences (extension ratio differences) in the amount of thermal deformation between the nozzle mount 2 and the nozzle plate 4 in cases where stainless steel and two kinds of heat-resistant Ni-base alloy A, B having different linear expansion coefficients are used in the nozzle mount 2 and the nozzle plate 4. FIG. 7 is a graph of FIG. 6.

(25) Here, the extension rate difference (A) is calculated by the following equation (1):
A=α1×(T1−T0)−α2(T2−T0)  Equation (1),

(26) where:

(27) α1 is the linear expansion coefficient of a material forming the nozzle plate 4;

(28) α2 is the linear expansion coefficient of a material forming the nozzle mount 2;

(29) T1 is the temperature of the nozzle plate 4 during operation of the engine;

(30) T2 is the temperature of the nozzle mount 2 during operation of the engine; and

(31) T0 is the reference temperature (20° C. herein).

(32) Also, in FIGS. 6 and 7, T1 is set to 1000° C. and T2 is set to 900° C. assuming that the variable-geometry exhaust turbocharger 1 is employed in a gasoline engine.

(33) As illustrated in FIGS. 6 and 7, when using heat-resistant Ni-base alloy A for the nozzle plate 4 and stainless steel for the nozzle mount 2, the extension rate difference is minus 0.05% (the first working example). Further, when using heat-resistant Ni-base alloy B for the nozzle plate 4 and stainless steel for the nozzle mount 2, the extension rate difference is 0.02% (the second working example). Still further, when using heat-resistant Ni-base alloy A for the nozzle plate 4 and heat-resistant Ni-base alloy B for the nozzle mount 2, the extension rate difference is 0.14% (the third working example).

(34) On the other hand, when the same material having the same linear expansion coefficient is used for the nozzle mount 2 and the nozzle plate 4, the extension rate difference is 0.21% to 0.27% (the first to third reference examples).

(35) In order to reduce the difference (extension rate difference) in the amount of thermal deformation between the nozzle mount 2 and the nozzle plate 4 under a high-temperature condition to prevent a large shear force and bending moment from being applied to the nozzle supports 6, it is desirable to reduce the difference (extension rate difference) in the amount of thermal deformation between the nozzle mount 2 and the nozzle plate 4 to be small. Preferably, in order to reduce the extension rate difference (A) to a value approximately not greater than the conventional value (see FIG. 11), a material may be selected for each of the nozzle mount 2 and the nozzle plate 4 so that the absolute value of the extension rate difference (A) is not greater than 0.20%.

(36) Further, as illustrated in the first and second working examples, the nozzle plate 4, which is exposed to the exhaust gas at both sides so that the temperature rises higher, is formed of heat-resistant Ni-base alloy having a small linear expansion coefficient, while the nozzle mount 2 is formed of stainless steel which is relatively low cost. In this way, it is possible to reduce the difference (extension rate difference) in the amount of thermal deformation between the nozzle mount 2 and the nozzle plate 4 under a high-temperature condition and also to reduce the material cost.

(37) Further, as illustrated in FIG. 8, heat-resistant Ni-base alloy has high proof strength under a high-temperature condition as compared to stainless steel. Thus, as illustrated in the third working example, the nozzle plate 4 and the nozzle mount 2 may be both formed of heat-resistant Ni-base alloy, using the heat-resistant Ni-base alloy A having a relatively small linear expansion coefficient for the nozzle plate 4 and the heat-resistant Ni-base alloy B having a relatively large linear expansion coefficient for the nozzle mount 2. In this way, it is possible to reduce the difference (extension rate difference) in the amount of thermal deformation between the nozzle mount 2 and the nozzle plate 4 under a high-temperature condition and to achieve a variable nozzle mechanism 10 with high heat-resistance.

(38) Further, in one embodiment of the present invention, the nozzle supports 6 which are the cylindrical members for coupling the nozzle mount 2 and the nozzle plate 4 may be formed of heat-resistant Ni-base alloy. In this way, it is possible to achieve a variable nozzle mechanism 10 with high proof strength under a high-temperature condition.

(39) Embodiments of the present invention were described in detail above, but the present invention is not limited thereto, and various amendments and modifications may be implemented within a scope that does not depart from the present invention.

INDUSTRIAL APPLICABILITY

(40) At least one embodiment of the present invention may be preferably used as a variable-geometry exhaust turbocharger used in an engine, preferably in a gasoline engine for a vehicle.

REFERENCE SIGNS LIST

(41) 1 Variable-geometry exhaust turbocharger 2 Nozzle mount 3 Lever plate 4 Nozzle plate 5 Drive ring 6 Nozzle support 8 Nozzle vane 8a Nozzle shaft 10 Variable nozzle mechanism 12 Turbine rotor 12a Rotational shaft 16 Turbine housing 18 Bearing housing 20 Exhaust gas channel 22 Bearing 24 Exhaust-gas outlet