CN102966428A - Peripheral gas path system of marine engine - Google Patents
Peripheral gas path system of marine engine Download PDFInfo
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- CN102966428A CN102966428A CN2012104512781A CN201210451278A CN102966428A CN 102966428 A CN102966428 A CN 102966428A CN 2012104512781 A CN2012104512781 A CN 2012104512781A CN 201210451278 A CN201210451278 A CN 201210451278A CN 102966428 A CN102966428 A CN 102966428A
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/12—Improving ICE efficiencies
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Abstract
The invention relates to a peripheral gas path system of a marine engine. The peripheral gas path system of the marine engine comprises gas compressors, a gas inlet pipe, an engine, a gas exhaust pipe, turbines, a volume chamber, connecting pipes, a movable body, a spring and a through pipe, wherein the movable body is installed in the volume chamber and is in hermetical contact with the inner wall surface of the volume chamber, the through pipe penetrates through the upper wall surface and the lower wall surface of the movable body, and the right wall surface of the movable body is connected with the right wall surface of the volume chamber through the spring. When the engine is under a high-speed working condition, the movable body moves leftwards, a first gas compressor, a second gas compressor, a first turbine and a second turbine work at the same time, the pumping loss of the engine is smaller and the performance of the entire engine is better; and when the engine is under a low-speed working condition, the movable body moves rightwards, only the first gas compressor and the first turbine work, the pulse energy is fully utilized, the gas inlet pressure of the engine is higher and the performance of the entire engine is better. The peripheral gas path system of the marine engine has the advantages of reasonable design and simple structure, and is suitable for a turbine supercharging system with double turbines and double gas compressors.
Description
Technical field
What the present invention relates to is a kind of turbo charge system of field of internal combustion engine, particularly the peripheral air-channel system of a kind of marine engine.
Background technique
Along with the development of society and the raising of environmental requirement, the application of engine booster technology is more and more extensive, in powerful motor mostly adopt turbocharging technology, to improve power and Reduce fuel consuming rate.Two kinds of basic patterns of turbo charge system are constant pressure charging system and impulse pressure charging system.Constant pressure charging system, each cylinder shares the outlet pipe that volume is larger, exhaust piping is relatively simple for structure, turbine equivalent circulation area is larger, it is constant that the outlet pipe internal pressure keeps basically, the pressure size is only relevant with load and the rotating speed of motor, and the pressurization system that different cylinders are counted diesel engine can be designed for uniformity.Constant pressure charging system is when high-speed working condition, and pumping loss is less, and turbine efficiency is higher, and performance is more excellent; But when the low speed operating mode, can not take full advantage of the exhaust pulses energy.Impulse pressure charging system, according to each cylinder firing order, two cylinders or three cylinders that exhaust is not disturbed are connected with same outlet pipe, the exhaust piping caliber is less, turbine equivalent circulation area is also less, the exhaust pulses energy can take full advantage of, low speed operating mode and instantaneous conditions better performances; But when high-speed working condition, pumping loss is larger.This shows, if the turbine equivalent circulation area of a motor can change along with the conversion of operating mode, make turbine equivalent circulation area become large during high-speed working condition, turbine equivalent circulation area is diminished, this is comparatively desirable.
Find through the retrieval to the prior art document, China Patent No. ZL200820226936.6, patent name: a kind of gas compressor of turbosupercharger supercharging device in parallel, this patented technology provides a kind of compressor housings variable device, can take into account preferably the high and low rotating speed operating mode of motor; But the variation of its housing needs the special control mechanism of a cover, thereby the more complicated that the pressurization system structure is become.
Summary of the invention
The present invention is directed to above-mentioned the deficiencies in the prior art, provide a kind of marine engine peripheral air-channel system, make the pressurization system can self-control, take into account preferably the high and low rotating speed operating mode of motor, and simple in structure, do not need special control mechanism.
The present invention is achieved through the following technical solutions, the present invention includes: the first sucking pipe, the first gas compressor, the first steam outlet pipe, the first turbine, the second sucking pipe, the second gas compressor, the second steam outlet pipe, the second turbine, engine air inlet tube, motor, engine exhaust pipe, coupling shaft, cavity volume, the cavity volume upper wall surface, the cavity volume lower wall surface, the left wall of cavity volume, the right wall of cavity volume, the cavity volume front face, the cavity volume rear surface, moving body, spring, the first connecting tube, the second connecting tube, the 3rd connecting tube, the 4th connecting tube and run through pipe, the air inlet/outlet of the first gas compressor respectively with the air outlet of the first sucking pipe, the suction port of engine air inlet tube is connected, the suction port of the second gas compressor is connected with the air outlet of the second sucking pipe, the air inlet/outlet of the first turbine respectively with the air outlet of engine exhaust pipe, the suction port of the first steam outlet pipe is connected, the second turbine air outlet is connected with the suction port of the second steam outlet pipe, the air inlet/outlet of motor respectively with the air outlet of engine air inlet tube, the suction port of engine exhaust pipe is connected, the first gas compressor, the second gas compressor, the second turbine, the first turbine links to each other by coupling shaft is coaxial, the cross section of cavity volume is rectangular, the cavity volume upper wall surface, the cavity volume lower wall surface, the left wall of cavity volume, the right wall of cavity volume, the cavity volume front face, the cavity volume rear surface fixes as one, the two ends of the first connecting tube respectively with engine air inlet tube, the cavity volume upper wall surface is connected, the two ends of the second connecting tube respectively with the air outlet of the second gas compressor, the cavity volume lower wall surface is connected, the two ends of the 3rd connecting tube respectively with the suction port of the second turbine, the cavity volume lower wall surface is connected, the two ends of the 4th connecting tube respectively with engine exhaust pipe, the right wall of cavity volume is connected, moving body is installed in the cavity volume and with the internal face sealing of cavity volume and contacts, run through up and down two walls that pipe runs through moving body, the right wall of moving body is connected by the right wall of spring and cavity volume.
Further, in the present invention the first connecting tube, the second connecting tube, run through that pipe is the straight pipe of uniform section and internal diameter is all identical, the dead in line of the axis of the first connecting tube and the second connecting tube, the axis of the first connecting tube and the axis that runs through pipe are at grade.
In the present invention, moving body can be in cavity volume move left and right.When motor is in high-speed working condition, the engine exhaust overpressure is higher, the right-hand cavity volume internal pressure of moving body is also higher, moving body is moved to the left and extension spring, thereby the first connecting tube is connected with the second connecting tube, and the 3rd connecting tube is connected with the 4th connecting tube, the first gas compressor, the second gas compressor, the first turbine and the second turbine are all simultaneously in work in whole pressurization system, turbine equivalent inlet area is larger, and the motor pumping loss is less, and the motor overall performance is more excellent; When motor is in the low speed operating mode, the engine exhaust overpressure is lower, the right-hand cavity volume internal pressure of moving body is also lower, under the stretching action of spring, moving body moves right, thereby the first connecting tube and the second connecting tube are cut off mutually, the 3rd connecting tube cuts off mutually with the 4th connecting tube, the first gas compressor and the first turbine are only arranged in work in whole pressurization system, turbine equivalent inlet area is less, pulse energy can take full advantage of, and engine charge pressure is larger, and the motor overall performance is more excellent.
Compared with prior art, the present invention has following beneficial effect and is: the present invention is reasonable in design, and is simple in structure, can take into account the high and low rotating speed operating mode of motor, can make again pressurization system not need special control mechanism.
Description of drawings
Fig. 1 is the structural representation of the peripheral air-channel system of marine engine of the present invention;
Fig. 2 is the structural representation of AA section among Fig. 1;
Wherein: 1, the first sucking pipe, 2, the first gas compressor, 3, the first steam outlet pipe, 4, the first turbine, 5, the second sucking pipe, 6, the second gas compressor, 7, the second steam outlet pipe, 8, the second turbine, 9, engine air inlet tube, 10, motor, 11, engine exhaust pipe, 12, coupling shaft, 13, cavity volume, 14, the cavity volume upper wall surface, 15, the cavity volume lower wall surface, 16, the left wall of cavity volume, 17, the right wall of cavity volume, 18, the cavity volume front face, 19, the cavity volume rear surface, 20, moving body, 21, spring, 22, the first connecting tube, 23, the second connecting tube, 24, the 3rd connecting tube, 25, the 4th connecting tube, 26, run through pipe.
Embodiment
Below in conjunction with accompanying drawing embodiments of the invention are elaborated, present embodiment provided detailed mode of execution and concrete operating process, but protection scope of the present invention is not limited to following embodiment take technical solution of the present invention as prerequisite.
Embodiment
As depicted in figs. 1 and 2, the present invention includes: the first sucking pipe 1, the first gas compressor 2, the first steam outlet pipe 3, the first turbine 4, the second sucking pipe 5, the second gas compressor 6, the second steam outlet pipe 7, the second turbine 8, engine air inlet tube 9, motor 10, engine exhaust pipe 11, coupling shaft 12, cavity volume 13, cavity volume upper wall surface 14, cavity volume lower wall surface 15, the left wall 16 of cavity volume, the right wall 17 of cavity volume, cavity volume front face 18, cavity volume rear surface 19, moving body 20, spring 21, the first connecting tube 22, the second connecting tube 23, the 3rd connecting tube 24, the 4th connecting tube 25 manages 26 with running through, the air inlet/outlet of the first gas compressor 2 respectively with the air outlet of the first sucking pipe 1, the suction port of engine air inlet tube 9 is connected, the suction port of the second gas compressor 6 is connected with the air outlet of the second sucking pipe 5, the air inlet/outlet of the first turbine 4 respectively with the air outlet of engine exhaust pipe 11, the suction port of the first steam outlet pipe 3 is connected, the second turbine 8 air outlets are connected with the suction port of the second steam outlet pipe 7, the air inlet/outlet of motor 10 respectively with the air outlet of engine air inlet tube 9, the suction port of engine exhaust pipe 11 is connected, the first gas compressor 2, the second gas compressor 6, the second turbine 8, the first turbine 4 is by 12 coaxial linking to each other of coupling shaft, the cross section of cavity volume 13 is rectangular, cavity volume upper wall surface 14, cavity volume lower wall surface 15, the left wall 16 of cavity volume, the right wall 17 of cavity volume, cavity volume front face 18, cavity volume rear surface 19 fixes as one, the two ends of the first connecting tube 22 respectively with engine air inlet tube 9, cavity volume upper wall surface 14 is connected, the two ends of the second connecting tube 23 respectively with the air outlet of the second gas compressor 6, cavity volume lower wall surface 15 is connected, the two ends of the 3rd connecting tube 24 respectively with the suction port of the second turbine 8, cavity volume lower wall surface 15 is connected, the two ends of the 4th connecting tube 25 respectively with engine exhaust pipe 11, the right wall 17 of cavity volume is connected, moving body 20 is installed in the cavity volume 13 and with the internal face sealing of cavity volume 13 and contacts, run through up and down two walls that pipe 26 runs through moving body 20, the right wall of moving body 20 is connected by the right wall 17 of spring 21 and cavity volume, the first connecting tube 22, the second connecting tube 23, run through the pipe 26 be the straight pipe of uniform section and internal diameter all identical, the dead in line of the axis of the first connecting tube 22 and the second connecting tube 23, the axis of the first connecting tube 22 with run through pipe 26 axis at grade.
In the present invention, moving body 20 can be in cavity volume 13 interior move left and right.When motor 10 is in high-speed working condition, engine exhaust pipe 11 internal pressures are higher, right-hand cavity volume 13 internal pressures of moving body 20 are also higher, moving body 20 is moved to the left and extension spring 21, thereby the first connecting tube 22 is connected with the second connecting tube 23, the 3rd connecting tube 24 is connected with the 4th connecting tube 25, the first gas compressor 2, the second gas compressor 6, the first turbine 4 and the second turbine 8 are all simultaneously in work in whole pressurization system, turbine equivalent inlet area is larger, the pumping loss of motor 10 is less, and the overall performance of motor 10 is more excellent; When motor 10 is in the low speed operating mode, engine exhaust pipe 11 internal pressures are lower, right-hand cavity volume 13 internal pressures of moving body 20 are also lower, under the stretching action of spring 21, moving body 20 moves right, thereby the first connecting tube 22 and the second connecting tube 23 are cut off mutually, the 3rd connecting tube 24 cuts off mutually with the 4th connecting tube 25, the first gas compressor 2 and the first turbine 4 are only arranged in work in whole pressurization system, turbine equivalent inlet area is less, pulse energy can take full advantage of, and the suction pressure of motor 10 is larger, and the overall performance of motor 10 is more excellent.Therefore, the present invention can take into account the high and low rotating speed operating mode of motor 10 preferably.
Claims (2)
1. the peripheral air-channel system of a marine engine, comprise: the first sucking pipe (1), the first gas compressor (2), the first steam outlet pipe (3), the first turbine (4), the second sucking pipe (5), the second gas compressor (6), the second steam outlet pipe (7), the second turbine (8), engine air inlet tube (9), motor (10), engine exhaust pipe (11) and coupling shaft (12), the air inlet/outlet of the first gas compressor (2) respectively with the air outlet of the first sucking pipe (1), the suction port of engine air inlet tube (9) is connected, the suction port of the second gas compressor (6) is connected with the air outlet of the second sucking pipe (5), the air inlet/outlet of the first turbine (4) respectively with the air outlet of engine exhaust pipe (11), the suction port of the first steam outlet pipe (3) is connected, the second turbine (8) air outlet is connected with the suction port of the second steam outlet pipe (7), the air inlet/outlet of motor (10) respectively with the air outlet of engine air inlet tube (9), the suction port of engine exhaust pipe (11) is connected, the first gas compressor (2), the second gas compressor (6), the second turbine (8), the first turbine (4) links to each other by coupling shaft (12) is coaxial, characterized by further comprising cavity volume (13), cavity volume upper wall surface (14), cavity volume lower wall surface (15), the left wall of cavity volume (16), the right wall of cavity volume (17), cavity volume front face (18), cavity volume rear surface (19), moving body (20), spring (21), the first connecting tube (22), the second connecting tube (23), the 3rd connecting tube (24), the 4th connecting tube (25) and run through pipe (26), the cross section of cavity volume (13) is rectangular, cavity volume upper wall surface (14), cavity volume lower wall surface (15), the left wall of cavity volume (16), the right wall of cavity volume (17), cavity volume front face (18), cavity volume rear surface (19) fixes as one, the two ends of the first connecting tube (22) respectively with engine air inlet tube (9), cavity volume upper wall surface (14) is connected, the two ends of the second connecting tube (23) respectively with the air outlet of the second gas compressor (6), cavity volume lower wall surface (15) is connected, the two ends of the 3rd connecting tube (24) respectively with the suction port of the second turbine (8), cavity volume lower wall surface (15) is connected, the two ends of the 4th connecting tube (25) respectively with engine exhaust pipe (11), the right wall of cavity volume (17) is connected, moving body (20) is installed in the cavity volume (13) and with the internal face sealing of cavity volume (13) and contacts, run through up and down two walls that pipe (26) runs through moving body (20), the right wall of moving body (20) is connected with the right wall of cavity volume (17) by spring (21).
2. the peripheral air-channel system of marine engine according to claim 1, it is characterized in that described the first connecting tube (22), the second connecting tube (23), run through that pipe (26) is the straight pipe of uniform section and internal diameter is all identical, the dead in line of the axis of the first connecting tube (22) and the second connecting tube (23), the axis of the first connecting tube (22) and the axis that runs through pipe (26) are at grade.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012104512781A CN102966428A (en) | 2012-11-12 | 2012-11-12 | Peripheral gas path system of marine engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012104512781A CN102966428A (en) | 2012-11-12 | 2012-11-12 | Peripheral gas path system of marine engine |
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| Publication Number | Publication Date |
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| CN102966428A true CN102966428A (en) | 2013-03-13 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2012104512781A Pending CN102966428A (en) | 2012-11-12 | 2012-11-12 | Peripheral gas path system of marine engine |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105569823A (en) * | 2016-02-16 | 2016-05-11 | 大连依勒斯涡轮增压技术有限公司 | Engine system and turbocharger thereof |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE19816840A1 (en) * | 1998-04-16 | 1999-10-21 | Mtu Friedrichshafen Gmbh | Internal combustion engine with several exhaust gas turbochargers which can be optionally switched on and off |
| CN201314254Y (en) * | 2008-12-18 | 2009-09-23 | 上海交通大学 | Parallel connection three-stage adjustable turbocharger of double turbocharger |
| EP2492458A1 (en) * | 2009-10-23 | 2012-08-29 | Mitsubishi Heavy Industries, Ltd. | Turbo compound system and method for operating same |
| CN102767420A (en) * | 2012-07-16 | 2012-11-07 | 上海交通大学 | Partitioning device for connecting pipes |
| CN102889121A (en) * | 2012-09-19 | 2013-01-23 | 上海交通大学 | Air inlet pressure main control type pipeline device |
-
2012
- 2012-11-12 CN CN2012104512781A patent/CN102966428A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE19816840A1 (en) * | 1998-04-16 | 1999-10-21 | Mtu Friedrichshafen Gmbh | Internal combustion engine with several exhaust gas turbochargers which can be optionally switched on and off |
| CN201314254Y (en) * | 2008-12-18 | 2009-09-23 | 上海交通大学 | Parallel connection three-stage adjustable turbocharger of double turbocharger |
| EP2492458A1 (en) * | 2009-10-23 | 2012-08-29 | Mitsubishi Heavy Industries, Ltd. | Turbo compound system and method for operating same |
| CN102767420A (en) * | 2012-07-16 | 2012-11-07 | 上海交通大学 | Partitioning device for connecting pipes |
| CN102889121A (en) * | 2012-09-19 | 2013-01-23 | 上海交通大学 | Air inlet pressure main control type pipeline device |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105569823A (en) * | 2016-02-16 | 2016-05-11 | 大连依勒斯涡轮增压技术有限公司 | Engine system and turbocharger thereof |
| CN105569823B (en) * | 2016-02-16 | 2018-07-06 | 大连依勒斯涡轮增压技术有限公司 | A kind of engine system and its turbocharger |
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Application publication date: 20130313 |