JP2008208734A - Two-stage compression type exhaust turbine supercharger - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide a two-stage compression type exhaust turbine supercharger capable of performing two-stage supercharging and reducing the size of the supercharger. <P>SOLUTION: The two-stage compression type exhaust turbine supercharger 1 includes a turbine part 3 driven by exhaust gas 2 introduced from an internal combustion engine, and a low pressure stage compressor part 5 and a high pressure stage compressor part 6 driven by the turbine part 3 for pressure feeding outside air to the internal combustion engine. The turbine part 3 and a rotary shaft 9 of the low pressure stage compressor part 5, or the turbine part 3 and a rotary shaft 12 of the high pressure stage compressor part 6, are coupled to the rotary shaft 12 of the high pressure stage compressor part 6, or the rotary shaft 9 of the low pressure stage compressor part 5, and are rotated as one rotary shaft. <P>COPYRIGHT: (C)2008,JPO&INPIT

Description

  The present invention relates to a two-stage compression type exhaust turbine supercharger, and more particularly to a two-stage compression type exhaust turbine supercharger mounted on a marine internal combustion engine, an onshore generator internal combustion engine, or the like.

As such a two-stage compression type exhaust turbine supercharger, one having one high-pressure stage and one low-pressure stage is known (for example, see Patent Document 1).
Japanese Utility Model Publication No. 58-47226

  However, what is disclosed in the above patent document is that each of the high-pressure stage and the low-pressure stage includes one compressor and one turbine, and these two compressors and two turbines are arranged in the axial direction. It is arranged on a straight line along. Therefore, the dimension of the whole turbocharger in the axial direction (longitudinal direction) inevitably increases, and there is a problem that the turbocharger becomes large.

  The present invention has been made in view of the above circumstances, and provides a two-stage compression exhaust turbine supercharger that can perform two-stage supercharging and can reduce the size of the supercharger. The purpose is to do.

In order to solve the above problems, the present invention employs the following means.
A two-stage compression type exhaust turbine supercharger according to the present invention includes a turbine section driven by exhaust gas guided from an internal combustion engine, and a low pressure stage compressor section driven by the turbine section to pump outside air to the internal combustion engine. And an exhaust turbine supercharger having a high-pressure compressor section, wherein the turbine shaft and the rotary shaft of the low-pressure compressor section, or the rotary shaft of the turbine section and the high-pressure compressor section are the high-pressure compressor section. The rotary shaft is connected to the rotary shaft of the low-pressure compressor unit or the rotary shaft of the low-pressure stage compressor unit, and is configured to rotate as a single rotary shaft.

According to the two-stage compression-type exhaust turbine supercharger according to the present invention, for example, the rotating shafts of the turbine section and the low-pressure stage compressor section and the rotating shaft of the high-pressure stage compressor section are connected via a flexible coupling. The rotating shaft and the flexible coupling rotate as one rotating shaft. That is, two compressor units (a low pressure compressor unit and a high pressure compressor unit) are driven by one turbine unit.
Thereby, the dimension of the axial direction (longitudinal direction) of the whole supercharger can be reduced, and size reduction of a supercharger can be achieved. Further, since the outside air compressed by the low-pressure stage compressor is further compressed by the high-pressure stage compressor, the pressure ratio of the outside air supplied to the internal combustion engine can be increased.

  In the above-described two-stage compression type exhaust turbine supercharger, if an intermediate cooler for cooling the outside air is provided in the middle of a pipe that guides the outside air discharged from the low-pressure stage compressor to the high-pressure stage compressor. Is preferred.

  According to such a two-stage compression exhaust turbine supercharger, the outside air discharged from the low-pressure stage compressor portion is cooled through the intermediate cooler and then guided to the high-pressure stage compressor portion. As a material for the high-pressure stage compressor, a relatively inexpensive aluminum alloy can be adopted, and the manufacturing cost can be reduced, and a large amount of outside air can be supplied to the internal combustion engine.

  In the two-stage compression type exhaust turbine supercharger, it is more preferable that a generator having a rotation shaft connected to the one rotation shaft is provided.

  According to such a two-stage compression type exhaust turbine supercharger, the driving force of the turbine section is also recovered by the generator, so that energy loss can be reduced. In addition, the load of other generators can be reduced by the amount of power generated by this generator, and the amount of power supplied from the power company can be reduced, so that other generators can be driven. The fuel cost required and the electricity bill paid to the power company can be reduced.

The internal combustion engine according to the present invention includes a small two-stage compression exhaust turbine supercharger in which the axial direction (longitudinal direction) of the entire turbocharger is reduced. The installation space for installing the supercharger can be reduced.
Moreover, since high pressure ratio outside air is supplied from the two-stage compression exhaust turbine supercharger, engine efficiency and engine output can be improved.

  According to the present invention, it is possible to perform two-stage supercharging and to achieve an effect that the supercharger can be reduced in size.

Hereinafter, an embodiment of a two-stage compression type exhaust turbine supercharger according to the present invention will be described with reference to FIGS. 1 and 2.
As shown in FIG. 1, a two-stage compression type exhaust turbine supercharger 1 according to the present embodiment includes an exhaust gas (combustion gas) 2 led from an internal combustion engine (for example, a diesel engine or a gas turbine engine) not shown. The turbine section 3 driven by the turbine section, the low-pressure stage compressor section 5 driven by the turbine section 3 to pump the outside air 4 to the high-pressure stage compressor section 6, and the outside air 4 fed from the low-pressure stage compressor section 5 by the internal combustion A high-pressure stage compressor section 6 that pumps the engine, a first casing 7 that is provided between and supports the turbine section 3 and the low-pressure stage compressor section 5, and a second casing that supports the high-pressure stage compressor section 6. 8 is the main element.

The first casing 7 is inserted with a rotary shaft 9 having one end protruding toward the turbine section 3 and the other end protruding toward the low-pressure compressor section 5. The rotating shaft 9 is supported by a bearing 10 provided in the first casing 7 so as to be rotatable around the axis. The first casing 7 is provided with a lubricating oil supply passage 11 for supplying lubricating oil from a lubricating oil reservoir (not shown) to the bearing 10.
On the other hand, the lower end portion of the first casing 7 supports the first casing 7 at one point in the axial direction of the rotating shaft 9 (in the case of supporting at two or more points in the direction orthogonal to the axial direction of the rotating shaft 9). There is also a leg portion 7a, and the leg portion 7a is fixed to a base (not shown) installed on the floor surface.
In addition, the code | symbol P1 in a figure is a punching plate. One end of the punching plate P1 is fixed to the lower end of the turbine section 3, and the other end is fixed to the base in the same manner as the leg 7a of the casing 7.

The second casing 8 is inserted with a rotating shaft 12 having one end projecting toward the low-pressure stage compressor unit 5 and the other end projecting toward the high-pressure stage compressor unit 6. The rotary shaft 12 is supported by a bearing 13 provided in the second casing 8 so as to be rotatable around the axis. The second casing 8 is provided with a lubricating oil supply passage 14 for supplying lubricating oil from a lubricating oil reservoir (not shown) to the bearing 13.
On the other hand, the lower end portion of the second casing 8 supports the second casing 8 at one point in the axial direction of the rotating shaft 12 (in the case of supporting at two or more points in the direction orthogonal to the axial direction of the rotating shaft 12). A leg portion 8a, which is fixed to a base (not shown) installed on the floor.

The turbine section 3 is connected to an exhaust system of the internal combustion engine and receives an exhaust gas passage 15 to which at least a part of the exhaust gas 2 is supplied, and a flow of the exhaust gas 2 supplied into the exhaust gas passage 15. And a turbine 16 that is rotationally driven.
The turbine 16 includes a turbine rotor 17 and a turbine nozzle 18. The turbine rotor 17 includes a disk-shaped turbine disk 17a provided at one end of the rotating shaft 9, and a plurality of turbine blades having an airfoil cross section attached on the outer periphery of the turbine disk 17a. 17b.
The turbine nozzle 18 is formed by annularly arranging a plurality of nozzle guide vanes 18a, and is arranged upstream of the turbine blade 17b.

  The exhaust gas passage 15 is connected to the exhaust system of the internal combustion engine and is provided toward the nozzle guide vane 18a and the turbine blade 17b to guide the exhaust gas 2 to the radially outer side of the turbine 16. And a delivery path 15b that guides the exhaust gas 2 that has passed through the turbine 16 to the outside of the system or to an exhaust purification device (not shown).

The low-pressure compressor unit 5 is driven to rotate and compresses the compressor impeller 19 that sends outside air 4 radially outward, and the outside air 4 that is surrounded by the compressor impeller 19 and sent by the compressor impeller 19. And a spiral chamber 20.
The compressor impeller 19 is attached to the other end of the rotary shaft 9 and has a substantially disc-shaped hub 19a. The compressor impeller 19 extends radially outward from the outer surface of the hub 19a and is provided in an annular shape along the circumferential direction. And a plurality of blades 19b.
A silencer (silencer) 21 is disposed adjacent to the upstream side of the low-pressure compressor unit 5, and the outside air 4 that has passed through the silencer 21 is guided to the blades 19 b of the compressor impeller 19 through the inflow path 22. It has come to be. Further, an intercooler (intercooler) 23 shown in FIG. 2 is provided on the downstream side of the low-pressure stage compressor unit 5, and the outside air 4 that has passed through the spiral chamber 20 passes through the intercooler 23, The high-pressure compressor unit 6 is supplied.

  A shell housing 24 having a recess 24a formed so as to taper toward the end surface of the hub 19a is provided in the center portion of the silencer 21, and in the recess 24a, A part of the second casing 8 that supports the rotating shaft 12 and a counterweight (balance weight) 25 attached to one end of the rotating shaft 12 are accommodated. The shell housing 24 is fixed to the low pressure compressor unit 5 (the radially outer wall surface forming the inflow path 22) via a plurality of (for example, 4) supports 26 provided in the inflow path 22. . The outer surface of the shell housing 24 constitutes a radially inner wall surface that forms the inflow path 22.

The rotating shaft 12 is disposed so as to be positioned on the same rotating axis as the rotating shaft 9, and has the other end of the rotating shaft 9 protruding through the hub 19 a toward the silencer 21, They are connected via a coupling 27. That is, the rotating shaft 12 rotates together with the rotating shaft 9.
One end of the flexible coupling 27 is detachably attached to the first coupling mounting boss 28 attached to the tip of one end of the rotary shaft 12, and the other end is the tip of the other end of the rotary shaft 9. It is detachably attached to the second coupling attachment boss 29 attached to.

The high-pressure compressor unit 6 is driven to rotate, and the compressor impeller 30 that sends outside air 4 after passing through the intercooler 23 to the outside in the radial direction and the compressor impeller 30 surrounds the compressor impeller 30. Has a spiral chamber 31 for compressing the outside air 4 sent out.
The compressor impeller 30 is attached to the other end of the rotating shaft 12 and has a substantially disc-shaped hub 30a. The compressor impeller 30 extends radially outward from the outer surface of the hub 30a, and is provided annularly along the circumferential direction. And a plurality of blades 30b.
A silencer (not shown) similar to that of the low-pressure stage compressor unit 5 is disposed adjacent to the upstream side of the high-pressure stage compressor unit 6, and the outside air 4 that has passed through the silencer passes through the inflow path 32 and is compressed into the compressor. It is guided to the blade 30 b of the impeller 30. Further, an aftercooler, a surge tank, etc. (not shown) are provided on the downstream side of the high-pressure compressor unit 6, and the outside air 4 that has passed through the spiral chamber 31 passes through the aftercooler, the surge tank, etc. It is supplied to an internal combustion engine.

According to the two-stage compression type exhaust turbine supercharger 1 according to the present embodiment, the rotating shaft 9 of the turbine section 3 and the low-pressure stage compressor section 5 and the rotating shaft 12 of the high-pressure stage compressor section 6 are flexible couplings 27. The rotary shafts 9 and 12 and the flexible coupling 27 are rotated as a single rotary shaft. That is, two compressor units (the low pressure compressor unit 5 and the high pressure compressor unit 6) are driven by one turbine unit 3.
Thereby, the dimension of the axial direction (longitudinal direction) of the whole supercharger can be reduced, and size reduction of a supercharger can be achieved. In addition, since the outside air compressed by the low-pressure compressor unit 5 is further compressed by the high-pressure compressor unit 6, the pressure ratio of the outside air supplied to the internal combustion engine can be increased.

  Further, according to the two-stage compression type exhaust turbine supercharger 1 according to the present embodiment, the outside air discharged from the low-pressure stage compressor unit 5 is cooled through the intermediate cooler 23 and then to the high-pressure stage compressor unit 6. Therefore, a relatively inexpensive aluminum alloy can be used as the material of the high-pressure compressor 6, and the manufacturing cost can be reduced, and a large amount of outside air can be supplied to the internal combustion engine. Can do.

Another embodiment of the two-stage compression type exhaust turbine supercharger according to the present invention will be described with reference to FIGS. 3 and 4.
As shown in FIG. 3, the two-stage compression exhaust turbine supercharger 41 according to this embodiment includes an exhaust gas (combustion gas) 42 led from an internal combustion engine (for example, a diesel engine or a gas turbine engine) not shown. The turbine section 43 driven by the turbine section, the low pressure stage compressor section 45 driven by the turbine section 43 to pump the outside air 44 to the high pressure compressor section 46, and the outside air 44 pumped from the low pressure stage compressor section 45 to the internal combustion A high-pressure compressor section 46 that pumps the engine, a generator 43 having a rotating shaft 49a connected to the rotating shaft 49 of the turbine section 43, the low-pressure compressor section 45, and the rotating shaft 52 of the high-pressure compressor section 46; 43 and a first casing 47 provided between and supporting the low pressure stage compressor section 45, and a high pressure stage A second casing 48 which supports the compressors 46 are those that are configured as a main component.

The first casing 47 is inserted with a rotating shaft 49 having one end protruding toward the turbine section 43 and the other end protruding toward the low-pressure compressor section 45. The rotary shaft 49 is supported by a bearing 50 provided in the first casing 47 so as to be rotatable around the axis. Further, the first casing 47 is provided with a lubricating oil supply passage 51 for supplying lubricating oil from a lubricating oil reservoir (not shown) to the bearing 50.
On the other hand, the lower end portion of the first casing 47 supports the first casing 47 at one point in the axial direction of the rotating shaft 49 (in the case of supporting at two or more points in the direction orthogonal to the axial direction of the rotating shaft 49). There are also leg portions 47a, and the leg portions 47a are fixed to a base (not shown) installed on the floor surface.
In addition, the code | symbol P2 in a figure is a punching plate. The punching plate P <b> 2 has one end fixed to the lower end of the turbine portion 43 and the other end fixed to the base in the same manner as the leg 47 a of the casing 47.

The second casing 48 is inserted with a rotating shaft 52 having one end projecting toward the low-pressure stage compressor unit 45 and the other end projecting toward the high-pressure stage compressor unit 46. The rotating shaft 52 is supported by a bearing 53 provided in the second casing 48 so as to be rotatable around the axis. The second casing 48 is provided with a lubricating oil supply passage 54 that supplies lubricating oil from a lubricating oil reservoir (not shown) to the bearing 53.
On the other hand, the lower end portion of the second casing 48 supports the second casing 48 at one point in the axial direction of the rotating shaft 52 (in the case of supporting at two or more points in the direction orthogonal to the axial direction of the rotating shaft 52). There is also a leg portion 48a, and the leg portion 48a is fixed to a base (not shown) installed on the floor surface.

The turbine section 43 is connected to the exhaust system of the internal combustion engine and receives an exhaust gas passage 55 to which at least a part of the exhaust gas 42 is supplied, and a flow of the exhaust gas 42 supplied into the exhaust gas passage 55. And a turbine 56 that is rotationally driven.
The turbine 56 includes a turbine rotor 57 and a turbine nozzle 58. The turbine rotor 57 includes a disc-shaped turbine disk 57a provided at one end of the rotating shaft 49, and a plurality of turbine blades having an airfoil cross section attached on the outer periphery of the turbine disk 57a. 57b.
The turbine nozzle 58 is configured by annularly arranging a plurality of nozzle guide vanes 58a, and is disposed upstream of the turbine blade 57b.

  The exhaust gas passage 55 is connected to the exhaust system of the internal combustion engine, and is provided toward the nozzle guide vane 58a and the turbine blade 57b to guide the exhaust gas 42 to the radially outer side of the turbine 56. And a delivery path 55b for guiding the exhaust gas 42 that has passed through the turbine 56 to the outside of the system or to an exhaust purification device (not shown).

The low-pressure stage compressor 45 compresses the compressor impeller 59 that sends the outside air 44 radially outward by being driven to rotate, and the outside air 44 that the compressor impeller 59 sends around the compressor impeller 59. And a spiral chamber 60.
The compressor impeller 59 is attached to the other end portion of the rotating shaft 49, has a substantially disc-shaped hub 59a, extends radially outward from the outer surface of the hub 59a, and is annularly provided along the circumferential direction. And a plurality of blades 59b.
A silencer (silencer) 61 is disposed adjacent to the upstream side of the low-pressure compressor unit 45, and the outside air 44 that has passed through the silencer 61 is guided to the blades 59 b of the compressor impeller 59 via the inflow passage 62. It has come to be. Further, an intercooler (intermediate cooler) 63 shown in FIG. 4 is provided on the downstream side of the low-pressure stage compressor unit 45, and the outside air 44 that has passed through the spiral chamber 60 passes through the intercooler 63. The high-pressure compressor unit 46 is supplied.

At the center of the silencer 61, a shell housing 64 having a recess 64a formed so as to taper toward the end surface of the hub 59a is provided, and in the recess 64a, A (high speed induction) generator 65 is accommodated. The shell housing 64 is fixed to the low-pressure compressor unit 45 (the radially outer wall surface forming the inflow passage 62) via a plurality of (for example, four) supports 66 provided in the inflow passage 62. . The outer surface of the shell housing 64 constitutes a radially inner wall surface that forms the inflow passage 62.
The generator 65 is disposed such that the rotation shaft 65a is positioned on the same rotation axis as the rotation shafts 49 and 52 described above, and one end of the rotation shaft 65a passes through the hub 59a. One end of the rotating shaft 49 protruding toward the silencer 61 is connected to the tip of the rotary shaft 49 via a flexible coupling 67, and the other end is penetrated through the second casing 48 to the low-pressure compressor unit 45 side. Is connected to a counterweight (balance weight) 68 attached to one end portion of the rotating shaft 52 protruding in the direction. That is, the rotating shaft 65 a of the generator 65 rotates with the rotating shafts 49 and 52.
One end of the flexible coupling 67 is detachably attached to the first coupling mounting boss 69 attached to the tip of one end of the rotary shaft 65 a, and the other end is the tip of the other end of the rotary shaft 49. It is detachably attached to the second coupling attachment boss 70 attached to the.

The high-pressure compressor unit 46 is driven to rotate, and sends a compressor impeller 71 that sends outside air 44 that has passed through the intercooler 63 to the outside in the radial direction. The compressor impeller 71 surrounds the periphery of the compressor impeller 71. Has a swirl chamber 72 for compressing the outside air 44 sent out.
The compressor impeller 71 is attached to the other end portion of the rotary shaft 52, and extends substantially radially outward from the outer surface of the hub 71a, and is provided annularly along the circumferential direction. And a plurality of blades 71b.
A silencer (not shown) similar to that of the low-pressure stage compressor unit 45 is disposed adjacent to the upstream side of the high-pressure stage compressor unit 46, and the outside air 44 that has passed through the silencer passes through the inflow path 73. It is guided to the blade 71 b of the impeller 71. Further, an aftercooler, a surge tank, etc. (not shown) are provided on the downstream side of the high-pressure compressor section 46, and the outside air 44 that has passed through the spiral chamber 72 passes through the aftercooler, the surge tank, etc. It is supplied to an internal combustion engine.

According to the two-stage compression type exhaust turbine supercharger 41 according to the present embodiment, the rotating shaft 49 of the turbine unit 43 and the low-pressure compressor unit 45 and the rotating shaft 65 a of the generator 65 are connected via the flexible coupling 67. The rotating shaft 65a of the generator 65 and the rotating shaft 52 of the high-pressure compressor unit 46 are connected, and these rotating shafts 49, 52, 65a and the flexible coupling 67 are used as one rotating shaft. It will rotate. That is, two compressor parts (low pressure stage compressor part 45 and high pressure stage compressor part 46) and one generator 65 are driven by one turbine part 43.
Thereby, the dimension of the axial direction (longitudinal direction) of the whole supercharger can be reduced, and size reduction of a supercharger can be achieved. In addition, since the outside air compressed by the low-pressure compressor unit 45 is further compressed by the high-pressure compressor unit 46, the pressure ratio of the outside air supplied to the internal combustion engine can be increased. Furthermore, since the driving force of the turbine unit 43 is also collected by the generator 65, energy loss can be reduced. Furthermore, the load of other generators can be reduced by the amount of electric power generated by the generator 65, and the amount of electric power supplied from the electric power company can be reduced, so that other generators are driven. It is possible to reduce the fuel cost required for the electricity and the electricity bill paid to the electric power company.

  In addition, according to the two-stage compression type exhaust turbine supercharger 41 according to the present embodiment, the outside air discharged from the low-pressure stage compressor unit 45 is cooled through the intermediate cooler 63 and then to the high-pressure stage compressor unit 46. Therefore, a relatively inexpensive aluminum alloy can be adopted as the material of the high-pressure compressor 46, and the manufacturing cost can be reduced, and a large amount of outside air can be supplied to the internal combustion engine. Can do.

1 is a longitudinal sectional view of a two-stage compression exhaust turbine supercharger according to an embodiment of the present invention. It is a schematic block diagram of the two-stage compression type exhaust turbine supercharger shown in FIG. It is a longitudinal cross-sectional view of the two-stage compression type exhaust turbine supercharger which concerns on other embodiment of this invention. It is a schematic block diagram of the two-stage compression type exhaust turbine supercharger shown in FIG.

Explanation of symbols

DESCRIPTION OF SYMBOLS 1 Two-stage compression type exhaust turbine supercharger 2 Exhaust gas 3 Turbine part 5 Low pressure stage compressor part 6 High pressure stage compressor part 9 Rotating shaft 12 Rotating shaft 23 Intermediate cooler 41 Two-stage compression type exhaust turbine supercharger 42 Exhaust gas 43 Turbine unit 45 Low-pressure stage compressor unit 46 High-pressure stage compressor unit 49 Rotating shaft 52 Rotating shaft 63 Intermediate cooler 65 Generator 65a Rotating shaft

Claims (4)

A two-stage compression exhaust turbine having a turbine section driven by exhaust gas guided from the internal combustion engine, and a low-pressure stage compressor section and a high-pressure stage compressor section that are driven by the turbine section to pump outside air to the internal combustion engine. A machine,
The rotating shaft of the turbine section and the low-pressure compressor section, or the rotating shaft of the turbine section and the high-pressure compressor section is connected to the rotating shaft of the high-pressure compressor section, or the rotating shaft of the low-pressure compressor section, A two-stage compression type exhaust turbine supercharger configured to rotate as a single rotating shaft.   2. The two-stage compression according to claim 1, wherein an intermediate cooler that cools the outside air is provided in the middle of a pipe that guides the outside air discharged from the low-pressure stage compressor to the high-pressure stage compressor. Type exhaust turbine supercharger.   The two-stage compression type exhaust turbine supercharger according to claim 1 or 2, wherein a generator having a rotation shaft connected to the one rotation shaft is provided.   An internal combustion engine comprising the two-stage compression exhaust turbine supercharger according to any one of claims 1 to 3.

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