JP2015143504A - Exhaust turbine apparatus, supercharger, and exhaust energy recovery apparatus - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide an exhaust turbine apparatus capable of reducing an excitation force generated in turbine blades as much as possible even if a plurality of exhaust gas inlets is provided.SOLUTION: An exhaust turbine apparatus comprises: a partition member 40 for partitioning a channel that allows exhaust gas to pass through a turbine nozzle group into a first exhaust-turbine-nozzle-group channel located on an outer circumference side and formed on the entire circumference, and a second exhaust-turbine-nozzle-group channel located on an inner circumference side of the first exhaust-turbine-nozzle-group channel and formed on the entire circumference; a first exhaust gas introduction channel F1' formed so as to introduce the exhaust gas to the entire circumference of the first exhaust-turbine-nozzle-group channel; a second exhaust gas introduction channel F2' formed so as to introduce the exhaust gas to the entire circumference of the second exhaust-turbine-nozzle-group channel; a first exhaust gas inlet 30a for introducing the exhaust gas from an internal combustion engine to the first exhaust gas introduction channel F1'; and a second exhaust gas inlet 32a for introducing the exhaust gas from the internal combustion engine to the second exhaust gas introduction channel F2'.

Description

  The present invention relates to an exhaust turbine device, a supercharger, and an exhaust energy recovery device.

  This is a dynamic pressure type supercharger that mainly uses the kinetic energy of the exhaust gas of the internal combustion engine in contrast to the static pressure type supercharger that eliminates the pressure fluctuation of the exhaust gas of the internal combustion engine and makes the pressure constant. The machine is known. In such a dynamic pressure supercharger, as shown in Patent Document 1 below, in order to avoid performance degradation due to interference of exhaust gas pressure, a two-entry supercharger with two exhaust gas inlets of the supercharger is used. It ’s time. In this case, the exhaust gas passage is divided into two in the circumferential direction up to the turbine nozzle outlet.

  Patent Document 2 discloses a power turbine that is driven by exhaust gas extracted from two diesel engines. This power turbine is provided with two exhaust gas inlet portions for introducing exhaust gas led from each diesel engine. The exhaust gas guided from each exhaust gas inlet portion flows through the exhaust gas passage divided into two in the circumferential direction to the turbine nozzle outlet.

JP 2009-13873 A Japanese Patent No. 5336629

  Both of the above Patent Documents 1 and 2 are exhaust turbines configured such that exhaust gas guided from two exhaust gas inlet portions flows through an exhaust gas passage divided into two in the circumferential direction and is guided to a turbine nozzle. Therefore, a large velocity distribution is generated in the circumferential direction at the turbine nozzle outlet. For this reason, the turbine blade receives a large fluctuating pressure every rotation, and there is a problem that an excitation force is generated in the turbine blade.

In order to reduce the influence of the excitation force generated on the turbine rotor blades and to ensure the reliability of the turbine rotor blades, a measure for binding the turbine rotor blades with a damping wire can be considered. However, since the damping wire disturbs the flow around the blades, there is a problem that the turbine performance is deteriorated.
Furthermore, in recent years, wide cord turbine blades with increased cord length have become the mainstream, but wide cord turbine blades have a larger blade pitch and a greater distance between adjacent turbine blades. Becomes longer, and the damping wire itself may be deformed or broken. For this reason, it is difficult to employ a damping wire for the wide code turbine rotor blade.

  Moreover, in patent document 2, in order to equalize the pressure of the exhaust gas introduce | transduced from two exhaust-gas inlet parts, it is necessary to employ | adopt a pressure sensor and a control valve, and there exists a problem of causing a raise of cost.

  The present invention has been made in view of such circumstances, and even when a plurality of exhaust gas inlets are provided, the excitation force generated in the turbine rotor blade can be made as small as possible. An object is to provide an exhaust turbine device, a supercharger, and an exhaust energy recovery device.

In order to solve the above problems, the exhaust turbine apparatus, the supercharger, and the exhaust energy recovery apparatus of the present invention employ the following means.
That is, an exhaust turbine apparatus according to the present invention includes a rotor that is rotatable around a central axis, and a turbine blade group that includes a plurality of turbine blades attached at predetermined intervals over the entire circumference of the rotor. And a turbine nozzle group having a plurality of turbine nozzles attached at predetermined intervals around the entire circumference around the central axis so as to guide the exhaust gas discharged from the internal combustion engine to the turbine rotor blade group. In the exhaust turbine apparatus, a flow path through which the exhaust gas passes through the turbine nozzle group is located on the outer peripheral side and is formed over the entire circumference, and the first turbine nozzle group flow A partition member that is positioned on the inner peripheral side of the passage and that is partitioned into a second turbine nozzle group flow path formed over the entire circumference, and the exhaust gas is in the first turret A first exhaust gas introduction channel formed so as to be guided over the entire circumference of the second nozzle group channel, and a second exhaust gas formed so that the exhaust gas is guided over the entire circumference of the second turbine nozzle group channel. A gas introduction flow path, a first exhaust gas inlet that guides the exhaust gas from the internal combustion engine to the first exhaust gas introduction flow path, and the exhaust gas from the internal combustion engine to the second exhaust gas introduction flow path And a second exhaust gas inlet that leads to

The exhaust gas flowing in from the first exhaust gas inlet is guided over the entire circumference of the first turbine nozzle group flow path of the turbine nozzle group through the first exhaust gas introduction flow path. Further, the exhaust gas flowing in from the second exhaust gas inlet is guided over the entire circumference of the second turbine nozzle group flow path of the turbine nozzle group through the second exhaust gas introduction flow path. Since the first turbine nozzle group flow path and the second turbine nozzle group flow path are partitioned by the partition member, the exhaust gas flowing through each turbine nozzle group flow path is separately guided to the turbine rotor blade group.
As described above, the exhaust gas flowing in from the first exhaust gas inlet and the second exhaust gas inlet is guided over the entire circumference of the first turbine nozzle group flow path and the second turbine nozzle group flow path, respectively. The pressure distribution in the circumferential direction on the outlet side of the turbine nozzle group flow path, that is, on the inlet side of the turbine rotor blade group, can be made as small as possible. Therefore, the pressure fluctuation received every round when the turbine rotor blade rotates around the central axis can be reduced, and the excitation force generated in the turbine rotor blade can be reduced as much as possible. Thereby, it is possible to ensure the reliability of the turbine rotor blade without using a damping wire for connecting the turbine rotor blades. In particular, even in a dynamic pressure type exhaust turbine apparatus that uses the dynamic pressure of exhaust gas, the pressure distribution in the circumferential direction can be reduced, so that the exhaust turbine performance can be improved.

  Furthermore, according to the exhaust turbine apparatus of the present invention, the partition member includes a ratio of a flow rate of the exhaust gas guided to the first turbine nozzle group flow path and the second turbine nozzle group flow path, and the first turbine. The ratio of the first throat area on the outer peripheral side of the turbine blade group corresponding to the nozzle group flow path to the second throat area on the inner peripheral side of the turbine blade group corresponding to the second turbine nozzle group flow path is It is provided in the position which corresponds.

The ratio of the flow rate of the exhaust gas guided to the first turbine nozzle group flow path and the second turbine nozzle group flow path, and the ratio of the first throat area on the outer peripheral side and the second throat area on the inner peripheral side of the turbine rotor blade group By providing the partition member at a position where they coincide with each other, the exhaust gas can be appropriately distributed to the turbine rotor blade group, so that the exhaust turbine performance can be improved.
For example, when there are two exhaust gas inlet portions and the exhaust gas flow rates guided to the first turbine nozzle group flow path and the second turbine nozzle group flow path are equal, the partition member has a radius of the turbine nozzle group. It arrange | positions from the outer peripheral side from the center position in a direction.

  Furthermore, according to the exhaust turbine apparatus of the present invention, an outer peripheral wall part forming an outer periphery of the second exhaust gas introduction flow path is connected to the partition member, and the first exhaust gas introduction flow path is formed by the outer peripheral wall part. The inner circumference is formed.

  By connecting the outer peripheral wall forming the outer periphery of the second exhaust gas introduction flow path to the partition member, the exhaust gas passing through the second exhaust gas introduction flow path is guided to the inner peripheral side of the partition member. Furthermore, the inner periphery of the first exhaust gas introduction flow path is formed by the outer peripheral wall portion. Thereby, a simple structure can be realized and cost reduction can be achieved.

  Further, according to the exhaust turbine apparatus of the present invention, the first exhaust gas inlet portion and the second exhaust gas inlet portion are provided so as to introduce the exhaust gas from a direction bent with respect to the central axis. The relative positions of the first exhaust gas inlet and the second exhaust gas inlet can be changed around the central axis when viewed from the central axis.

  When each of the first exhaust gas inlet and the second exhaust gas inlet is provided so as to guide the exhaust gas from the direction bent with respect to the central axis, the first exhaust gas inlet and the second exhaust gas The relative position to the inlet portion can be changed around the central axis when viewed from the central axis side. Thereby, the arrangement | positioning freedom degree of piping connected to these exhaust-gas inlet_port | entrance parts can be increased. For example, when exhaust gas is introduced from two internal combustion engines, an exhaust turbine device is installed between the two internal combustion engines, and the extended lines of the first exhaust gas inlet portion and the second exhaust gas inlet portion are connected to V It can be arranged in a cross shape.

  According to another aspect of the present invention, there is provided a turbocharger comprising: the exhaust turbine apparatus according to any one of the above; and a compressor that is driven by the rotor of the exhaust turbine apparatus and compresses air supplied to the internal combustion engine. It is characterized by that.

  Since any one of the exhaust turbine apparatuses described above is provided, a supercharger having high exhaust turbine performance can be provided. In particular, the supercharger is preferably a dynamic pressure type.

  An exhaust energy recovery apparatus according to the present invention includes the exhaust turbine apparatus according to any one of the above and a driven machine driven by the rotor of the exhaust turbine apparatus.

  The exhaust turbine device is used as a so-called power turbine, and recovers energy obtained from the exhaust gas of the internal combustion engine by the rotational force of the rotor. The driving force recovered by the rotor is used to drive the driven machine. Since any one of the above exhaust turbine apparatuses is provided, an exhaust energy recovery apparatus having high exhaust turbine performance can be provided. The follower means a mechanical device that obtains driving force from the rotor and is used for a predetermined purpose. Examples thereof include a generator, a compressor that is used in a chemical plant or the like and compresses a predetermined process gas.

  According to the present invention, the exhaust gas flowing in from the first exhaust gas inlet and the second exhaust gas inlet is guided over the entire circumference of the first turbine nozzle group flow path and the second turbine nozzle group flow path, respectively. The pressure distribution in the circumferential direction on the outlet side of each turbine nozzle group flow path, that is, on the inlet side of the turbine rotor blade group, can be made as small as possible. Therefore, the pressure fluctuation received every round when the turbine rotor blade rotates around the central axis can be reduced, and the excitation force generated in the turbine rotor blade can be reduced as much as possible. Thereby, it is possible to ensure the reliability of the turbine rotor blade without using a damping wire for connecting the turbine rotor blades.

It is the longitudinal section showing the supercharger which is one embodiment using the exhaust turbine device of the present invention. It is the side view which showed the exhaust turbine nozzle of FIG. FIG. 2 is a longitudinal sectional view showing a state where a second exhaust gas inlet casing is separated from a first exhaust gas inlet casing of FIG. 1. It is the schematic block diagram which showed the exhaust gas system | strain supplied to the supercharger of FIG. FIG. 2 is a schematic configuration diagram showing an exhaust energy recovery device in which the exhaust turbine unit and the driven machine of FIG. 1 are combined.

Hereinafter, an embodiment of an exhaust turbine apparatus of the present invention will be described with reference to the drawings.
FIG. 1 shows an embodiment in which the exhaust turbine apparatus of the present invention is applied to a supercharger 1. The supercharger 1 is used in, for example, a diesel engine (internal combustion engine) which is a main engine of a ship, or a diesel engine (internal combustion engine) of a vehicle such as an automobile, and air is generated by driving force obtained by exhaust gas from the diesel engine. And compressed air is supplied to the combustion chamber of the diesel engine. The supercharger 1 of this embodiment is a dynamic pressure type that mainly uses the kinetic energy of exhaust gas from a diesel engine, and is a so-called two-entry supercharger having two exhaust gas inlets.

The supercharger 1 includes an exhaust turbine unit 3 as an exhaust turbine device and a compressor unit (compressor) 5 that compresses the sucked air.
The compressor unit 5 includes an air suction port 9 for taking in air from the outside, an air introduction path 11 for introducing the introduced air, a compressor impeller 13 for compressing air introduced from the air introduction path 11, and a compressor impeller 13. And a spiral chamber 15 arranged on the downstream side.
The compressor impeller 13 is an impeller of a centrifugal compressor, and a plurality of compressor blades 13a are attached to the outer periphery. The compressor impeller 13 is fixed to one end (left end in FIG. 1) of the rotor shaft 17 that rotates about the central axis L.

The rotor shaft 17 is supported in the thrust direction by a thrust bearing 21 provided inside the bearing base 19 and is rotatably supported by radial bearings 23 and 25 on both left and right sides. An exhaust turbine impeller 27 is fixed to the other end (right end in FIG. 1) of the rotor shaft 17.
The air guide casing 20 that houses the compressor impeller 13 and forms the air introduction path 11 is fixed to the bearing base 19 by bolts 18 or the like.

  The exhaust turbine section 3 includes a first exhaust gas inlet casing 30 and a second exhaust gas inlet casing 32 that take in exhaust gas from a diesel engine, and an exhaust turbine nozzle 34 disposed on the downstream side of the exhaust gas inlet casings 30 and 32. And an exhaust turbine impeller (rotor) 27 disposed on the downstream side of the exhaust turbine nozzle 34, and an exhaust gas outlet casing 36 for discharging exhaust gas.

  The exhaust gas outlet casing 36 is fixed to the bearing stand 19 by bolts 37 and the like, and the first exhaust gas inlet casing 30 is fixed to the exhaust gas outlet casing 36 by bolts 31 and the like, and the second exhaust gas inlet casing 32 is fixed to the first exhaust gas inlet casing 30 by bolts 33 or the like.

  The exhaust turbine impeller 27 is an impeller of an axial turbine that can rotate about the central axis L. A plurality of exhaust turbine rotor blades 27a are fixed to the outer periphery of the exhaust turbine impeller 27 at a predetermined interval over the entire periphery, and an exhaust turbine rotor blade group is configured by the exhaust turbine rotor blades 27a. The exhaust turbine impeller 27 is not limited to the axial flow type, and may be a centrifugal type.

  The exhaust turbine nozzle 34 is a stationary blade disposed on the upstream side of the exhaust turbine rotor blade 27a, and is fixed on the circumference around the central axis L with a predetermined interval over the entire circumference. These exhaust turbine nozzles 34 constitute an exhaust turbine nozzle group.

Each exhaust turbine nozzle 34 is provided with a partition member 40 that partitions an exhaust gas flow path into an outer peripheral side and an inner peripheral side. The partition member 40 is a plate-like body that extends over the entire chord length from the front edge to the rear edge of the exhaust turbine nozzle 34 in parallel with the central axis L. As shown in FIG. 2, the outer peripheral surface of the partition member 40 has an inclined surface 40a inclined from the outer peripheral side toward the inner peripheral side, and the downstream end (left end in FIG. 2) is thin. It has a tapered shape. Turbine efficiency can be improved by providing the partition member 40 with a tapered shape having an inclined surface 40a and introducing exhaust gas to the entire exhaust turbine rotor blade 27a. The inclined surface 40a is inclined from the outer peripheral side toward the inner peripheral side. However, the inclination direction is not limited to this, and the inclined surface 40a is inclined from the inner peripheral side to the outer peripheral side, or inclined from both sides. Also good.
The partition member 40 is provided between the adjacent exhaust turbine nozzles 34. With this, when the exhaust turbine nozzle group is viewed from the center axis L side, the partition member 40 is connected in the circumferential direction. It has become. The first exhaust turbine nozzle group flow path F1 (see FIG. 2) is formed so that the flow path through which the exhaust gas passes through the turbine nozzle group is located on the outer peripheral side and is formed over the entire circumference by the partition member 40 that is continuous in the ring shape. ) And a second exhaust turbine nozzle group flow path F2 (see FIG. 2) which is located on the inner peripheral side of the first exhaust turbine nozzle group flow path F1 and formed over the entire circumference.

  The first exhaust gas introduction flow path F1 ′ is connected to the upstream side of the first exhaust turbine nozzle group flow path F1, and the second exhaust gas introduction flow path is connected to the upstream side of the second exhaust turbine nozzle group flow path F2. F2 'is connected.

  As shown in FIG. 1, the first exhaust gas introduction flow path F <b> 1 ′ has an outer peripheral surface formed by the first exhaust gas inlet casing 30, and an inner peripheral surface by the outer peripheral wall portion 32 b of the second exhaust gas inlet casing 32. A surface is formed. The first exhaust gas inlet casing 30 is provided with a first exhaust gas inlet portion 30a as one exhaust gas inlet portion. The first exhaust gas inlet 30a is provided so as to introduce exhaust gas from a direction bent with respect to the central axis L, specifically, a direction orthogonal to the central axis L.

The second exhaust gas introduction flow path F2 ′ is formed by the second exhaust gas inlet casing 32. The second exhaust gas inlet casing 32 is provided with a second exhaust gas inlet portion 32a as one exhaust gas inlet. The second exhaust gas inlet portion 32a is provided so as to introduce exhaust gas from a direction bent with respect to the central axis L, specifically, a direction orthogonal to the central axis L.
The second exhaust gas inlet casing 32 has an outer peripheral wall portion 32b and an inner peripheral wall portion 32c on the downstream side of the second exhaust gas inlet portion 32a. The outer peripheral wall portion 32b and the inner peripheral wall portion 32c are fixed to each other by a plurality of support members 32d. A plurality of support members 32d are provided at predetermined intervals in the circumferential direction around the central axis L, and are plate-like bodies extending in the radial direction.
The inner peripheral wall portion 32c forms an inner peripheral surface of the second exhaust gas introduction flow path F2 ′, and has a truncated cone shape in which the upstream side of the exhaust gas flow is closed. The downstream end of the inner peripheral wall 32c is connected to the inner peripheral surface of the nozzle 34 on the blade root side so that the exhaust gas flow path is continuously connected.
The outer peripheral wall portion 32b not only forms the inner peripheral surface of the first exhaust gas introduction flow path F1 ′ described above, but also forms the outer peripheral surface of the second exhaust gas introduction flow path F2 ′. The downstream end of the outer peripheral wall portion 32b is connected to the inner peripheral surface and the outer peripheral surface of the partition member 40 so that the exhaust gas flow path is continuously connected.

  FIG. 3 shows a state where the second exhaust gas inlet casing 32 is separated from the first exhaust gas inlet casing 30. As shown in the figure, since the second exhaust gas inlet casing 32 is fixed to the first exhaust gas inlet casing 30 by using bolts 33, a plurality of circumferentially arranged plural parts are provided. The second exhaust gas inlet casing 32 can be attached to the first exhaust gas inlet casing 30 by being rotated by a predetermined angle around the central axis L at a pitch interval of the bolts 33. Accordingly, the relative angular position between the first exhaust gas inlet portion 30a and the second exhaust gas inlet portion 32a can be appropriately changed around the central axis L when viewed from the center axis L side. The arrangement | positioning freedom degree of piping connected to 30a, 32a can be increased.

  The supercharger 1 of the present embodiment is a two-entry supercharger as described above, and includes two independent exhaust gas inlets that are the first exhaust gas inlet 30a and the second exhaust gas inlet 32a. Have. Exhaust gas from each cylinder of one diesel engine is collected into two exhaust gas introduction pipes, exhaust gas is led from one exhaust gas introduction pipe to one exhaust gas inlet, and the other exhaust gas introduction pipe from the other The exhaust gas is led to the exhaust gas inlet. For example, when the diesel engine has six cylinders as shown in FIG. 4, the exhaust gas from the first cylinder # 1, the third cylinder # 3 and the fifth cylinder # 5 enters the first exhaust gas introduction pipe 42. After being collected, the exhaust gas is guided to the first exhaust gas inlet 30a, and the exhaust gas from the second cylinder # 2, the fourth cylinder # 4, and the sixth cylinder # 6 is collected into the second exhaust gas introduction pipe 44 and then 2 Guided to the exhaust gas inlet 32a.

  The attachment position of the partition member 40 fixed to the exhaust turbine nozzle 34 depends on the ratio of the flow rate of the exhaust gas guided to the first turbine nozzle group flow path F1 and the second turbine nozzle group flow path F2 and the first turbine nozzle group flow. The position where the ratio of the first throat area on the outer peripheral side of the exhaust turbine blade group corresponding to the path F1 and the second throat area on the inner peripheral side of the turbine blade group corresponding to the second turbine nozzle group flow path F2 coincides. It is said that. Therefore, as shown in FIG. 4, when the flow rate of the exhaust gas is equally divided, the partition member 40 is disposed from the outer peripheral side from the center position in the radial direction of the exhaust turbine nozzle group. .

The supercharger 1 configured as described above operates as follows.
As shown in FIG. 4, the exhaust gas discharged from the diesel engine is divided into a plurality of cylinders and divided into two, a first exhaust gas introduction pipe 42 and a second exhaust gas introduction pipe 44. As shown in FIG. 1, the exhaust gas collected in the first exhaust gas introduction pipe 42 is guided to the first exhaust gas inlet 30a, and the exhaust gas collected in the second exhaust gas introduction pipe 44 is 2 It is led to the exhaust gas inlet 32a.

The exhaust gas guided to the first exhaust gas inlet 30a passes through the first exhaust gas introduction flow path F1 ′ provided on the entire circumference in the circumferential direction centering on the central axis L, and is partitioned by the partition member 40. To the first exhaust turbine nozzle group flow path F1 (see FIG. 2) on the outer peripheral side.
The exhaust gas led to the second exhaust gas inlet portion 32a passes through a second exhaust gas introduction flow path F2 ′ provided on the entire circumference in the circumferential direction centering on the central axis L, and is partitioned by the partition member 40. The second exhaust turbine nozzle group flow path F2 (see FIG. 2) on the inner peripheral side.
The exhaust gas accelerated in the first exhaust turbine nozzle group flow path F1 and the second exhaust turbine nozzle group flow path F2 is guided to the corresponding outer peripheral side and inner peripheral side of the exhaust turbine rotor blade 27a, respectively. The exhaust turbine rotor blade 27a obtains the fluid energy of the exhaust gas and rotates the exhaust turbine impeller 27. The exhaust gas that has passed through the exhaust turbine rotor blade 27 a passes through the exhaust gas outlet casing 36 and is discharged to the outside of the supercharger 1.

  The rotational force of the exhaust turbine impeller 27 driven by the exhaust gas is transmitted to the compressor impeller 13 via the rotor shaft 17 and rotates the compressor impeller 13 around the central axis L. As a result, the air sucked from the air inlet 9 is compressed by the compressor rotor blade 13a, and the compressed air is sent to the combustion space of the diesel engine through the spiral chamber 15 and used as combustion air.

According to the supercharger 1 of this embodiment, there exist the following effects.
The exhaust gas flowing in from the first exhaust gas inlet 30a is guided over the entire circumference of the first exhaust turbine nozzle group flow path F1 of the exhaust turbine nozzle group through the first exhaust gas introduction flow path F1 ′. The exhaust gas flowing in from the second exhaust gas inlet 32a is guided over the entire circumference of the second exhaust turbine nozzle group flow path F2 of the exhaust turbine nozzle group through the second exhaust gas introduction flow path F2 ′. Since the first exhaust turbine nozzle group flow path F1 and the second exhaust turbine nozzle group flow path F2 are partitioned by the partition member 40, the exhaust gas flowing through the respective turbine nozzle group flow paths F1 and F2 is exhausted separately. Guided to the turbine blade group.
In this way, the exhaust gas flowing in from the first exhaust gas inlet 30a and the second exhaust gas inlet 32a is all around the first exhaust turbine nozzle group flow path F1 and the second exhaust turbine nozzle group flow path F2, respectively. Therefore, the pressure distribution in the circumferential direction on the outlet side of each turbine nozzle group flow path F1, F2, that is, on the inlet side of the turbine rotor blade group, can be made as small as possible. Therefore, the pressure fluctuation that is applied to each revolution when the exhaust turbine rotor blade 27a rotates around the central axis L can be reduced, and the excitation force generated in the exhaust turbine rotor blade 27a can be reduced as much as possible. As a result, the reliability of the exhaust turbine rotor blades can be ensured without employing a damping wire for connecting the exhaust turbine rotor blades. In particular, even in the dynamic pressure supercharger 1 that uses the dynamic pressure of the exhaust gas as in this embodiment, the pressure distribution in the circumferential direction can be reduced, so that the exhaust turbine performance and thus the turbocharger performance can be improved. Can do.

  The ratio of the flow rate of the exhaust gas guided to the first exhaust turbine nozzle group flow path F1 and the second exhaust turbine nozzle group flow path F2, the first throat area on the outer peripheral side of the exhaust turbine blade group, and the second on the inner peripheral side. Since the partition member 40 is provided at a position where the ratio of the throat area coincides, the exhaust gas can be appropriately distributed to the exhaust turbine rotor blade group, and the exhaust turbine performance and the supercharger performance are improved. be able to.

  By connecting the outer peripheral wall portion 32b forming the outer periphery of the second exhaust gas introduction flow path F2 ′ to the partition member 40, the exhaust gas passing through the second exhaust gas introduction flow path F2 ′ is moved to the inner peripheral side of the partition member 40. I decided to guide. Further, the outer peripheral wall portion 32b forms the inner periphery of the first exhaust gas introduction flow path F1 '. Thereby, a simple structure can be realized and cost reduction can be achieved.

  Each of the first exhaust gas inlet portion 30a and the second exhaust gas inlet portion 32a is provided so as to guide the exhaust gas from a direction bent with respect to the central axis L, and the first exhaust gas inlet portion 30a and the second exhaust gas are provided. Since the relative position with respect to the gas inlet portion 32a can be changed around the central axis L when viewed from the center axis L side, the degree of freedom of arrangement of pipes connected to the exhaust gas inlet portions 30a and 32a is increased. Can be made.

In the above-described embodiment, the dynamic pressure supercharger 1 has been described. However, the present invention is not limited to this and can be used for a static pressure supercharger.
In the above embodiment, the exhaust turbine unit 3 having two exhaust gas inlets is used. However, an exhaust turbine unit having three or more exhaust gas inlets may be used. In this case, there are two or more partition members, and three or more exhaust turbine nozzle group flow paths are provided concentrically.

  Moreover, in the said embodiment, although demonstrated using the supercharger 1 as an application example of an exhaust turbine apparatus, this invention is not limited to this. For example, instead of combining the turbocharger compressor unit 5 with the exhaust turbine unit 3 as in the supercharger shown in FIG. 1, as shown in FIG. The exhaust energy recovery device may be combined. Examples of the follower include a generator and a compressor that is used in a chemical plant or the like and compresses a predetermined process gas.

  Further, the exhaust turbine apparatus of the present invention is not limited to the one connected to one internal combustion engine as in the above embodiment, and may be connected to two or more internal combustion engines. For example, as shown in Patent Document 2, the exhaust turbine apparatus of the present invention can be applied to a power turbine that obtains exhaust gas from two internal combustion engines and drives a generator. Thus, when exhaust gas is introduced from two internal combustion engines, as shown in FIG. 3, the relative position between the first exhaust gas inlet portion 30a and the second exhaust gas inlet portion 32a is defined as the central axis L. If it can be changed around, an exhaust turbine device is installed between the two internal combustion engines, and the extended lines of the first exhaust gas inlet and the second exhaust gas inlet are crossed in a V shape. can do.

1 Supercharger 3 Exhaust turbine section (exhaust turbine device)
5 Compressor section (compressor)
DESCRIPTION OF SYMBOLS 9 Air inlet 11 Air introduction path 13 Compressor impeller 13a Compressor blade 15 Swirl chamber 17 Rotor shaft 18 Bolt 19 Bearing base 20 Air guide casing 21 Thrust bearing 23, 25 Radial bearing 27 Exhaust turbine impeller (rotor)
27a Exhaust turbine rotor blade 30 First exhaust gas inlet casing 30a First exhaust gas inlet portion 31 Bolt 32 Second exhaust gas inlet casing 32a Second exhaust gas inlet portion 32b Outer peripheral wall portion 32c Inner peripheral wall portion 33 Bolt 34 Exhaust turbine nozzle 36 Exhaust gas outlet casing 37 Bolt 40 Partition member 42 First exhaust gas introduction pipe 44 Second exhaust gas introduction pipe L Center axis F1 First exhaust turbine nozzle group flow path F2 Second exhaust turbine nozzle group flow path F1 ′ First exhaust gas Introduction flow path F2 'Second exhaust gas introduction flow path

Claims (6)

A rotor that is rotatable about a central axis,
A turbine blade group composed of a plurality of turbine blades attached over the entire circumference of the rotor;
A turbine nozzle group composed of a plurality of turbine nozzles attached over the entire circumference around the central axis so as to guide the exhaust gas discharged from the internal combustion engine to the turbine rotor blade group;
An exhaust turbine apparatus comprising:
A flow path through which the exhaust gas passes through the turbine nozzle group is located on the outer peripheral side, and is located on the inner peripheral side of the first turbine nozzle group flow path, which is formed over the entire circumference. And a partition member that partitions into a second turbine nozzle group flow path formed over the entire circumference,
A first exhaust gas introduction passage formed so that the exhaust gas is guided over the entire circumference of the first turbine nozzle group passage;
A second exhaust gas introduction passage formed so that the exhaust gas is guided over the entire circumference of the second turbine nozzle group passage;
A first exhaust gas inlet that guides the exhaust gas from the internal combustion engine to the first exhaust gas introduction flow path;
A second exhaust gas inlet for guiding the exhaust gas from the internal combustion engine to the second exhaust gas introduction flow path;
An exhaust turbine apparatus comprising:   The partition member includes a ratio of a flow rate of the exhaust gas guided to the first turbine nozzle group flow path and the second turbine nozzle group flow path, and the turbine blade group corresponding to the first turbine nozzle group flow path. The first throat area on the outer peripheral side of the turbine blade group is provided at a position where the ratio of the second throat area on the inner peripheral side of the turbine rotor blade group corresponding to the second turbine nozzle group flow path coincides. The exhaust turbine apparatus according to claim 1. An outer peripheral wall forming an outer periphery of the second exhaust gas introduction flow path is connected to the partition member;
The exhaust turbine apparatus according to claim 1 or 2, wherein an inner periphery of the first exhaust gas introduction flow path is formed by the outer peripheral wall portion. The first exhaust gas inlet and the second exhaust gas inlet are each provided to introduce the exhaust gas from a direction bent with respect to the central axis.
2. The relative position of the first exhaust gas inlet and the second exhaust gas inlet can be changed around the central axis when viewed from the front of the central axis. 4. The exhaust turbine device according to any one of items 1 to 3. An exhaust turbine device according to any one of claims 1 to 4,
A compressor that is driven by the rotor of the exhaust turbine device and compresses air supplied to the internal combustion engine;
A turbocharger characterized by comprising: An exhaust turbine device according to any one of claims 1 to 4,
A driven machine driven by the rotor of the exhaust turbine apparatus;
An exhaust energy recovery device comprising:

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