CN1560441A - Supercharger for double axle two stage turbine of supercharged diesel engine - Google Patents
Supercharger for double axle two stage turbine of supercharged diesel engine Download PDFInfo
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- CN1560441A CN1560441A CNA2004100168795A CN200410016879A CN1560441A CN 1560441 A CN1560441 A CN 1560441A CN A2004100168795 A CNA2004100168795 A CN A2004100168795A CN 200410016879 A CN200410016879 A CN 200410016879A CN 1560441 A CN1560441 A CN 1560441A
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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
Abstract
The invention discloses a second-level turbine boosting system and the double-shaft second-level turbine booster in the middle and large power high boosting diesel engine applied to ship, naval vessels and vehicle and the electricity generation. The low and high pressure level are made up of a normal structure single shaft turbine booster and a single shaft radial fan turbine booster, which are connected together in series with a boosting pipe between the outlet of the high pressure turbine and the inlet of the low pressure level turbine. Compared with current device, the invention can be applied to the second turbine boosting system in high boosting diesel machine with middle and large power applied to the quality.
Description
Technical field:
The present invention relates to boats and ships, naval vessels, locomotive and generating usefulness in, the turbosupercharger in the high-power highly supercharged diesel engine technical field.
Background technique:
Nearly decades, along with the updating and develop of diesel engine structural design, material technology and pressurization system and oil-fired system, the power per cylinder of diesel engine (or mean effective pressure) is also improving constantly with the strong degree (product of mean effective pressure and mean piston speed) that carries always.Wherein, the acquisition of high mean effective pressure value mainly is to realize by the pressure ratio that improves constantly turbosupercharger.The middle and high fast diesel engine of the performance index advanced person's of recent development four-stroke, its mean effective pressure can have been attained the application limit that reaches single-stage turbocharging up to 2.5～2.7MPa.If will improve mean effective pressure again, just must seek help from two stage turbocharging system.So-called two-stage turbine supercharging is that air compresses through two stage compressor with the turbosupercharger series operation of two different sizes, and cools off by intercooler in low pressure stage compression back.Two stage compressor can be driven by coaxial or out-of-alignment two-stage turbine.Introduction and comparison about single stage turbocharger system and two stage turbocharging system, and the comparison each other of single, double axle two stage turbocharging system can be write turbosupercharging and turbosupercharger Beijing referring to Zhu Daxin: China Machine Press, 1992,478～486 pages and Lu Jiaxiang chief editor diesel turbocharging technology Beijing: China Machine Press, relevant commentary in 1999,171～173 pages.
Turbine stage in the high and low turbosupercharger of arbitrarily downgrading during prior art twin shaft two stage turbocharging system is formed is same-type (be high pressure stage turbine and low pressure stage turbine or be both axial-flow turbine, or be both radial turbine).Because the highest isentropic efficiency value (η that the axial-flow turbine level can reach
Tmax≈ 0.9) the highest isentropic efficiency value (η that can reach more than the radial turbine level
Tmax≈ 0.75) want high, consider that again axial-flow turbine only just can reach its highest isentropic efficiency value under the situation of gas flow quite big (flow passage component blade long enough), but under the situation of small flow (blade is very short), because of blade end loss (secondary flow loss) sharply increases, cause isentropic efficiency to descend significantly and the highest isentropic efficiency value that just can reach at small flow far below radial turbine.Therefore, in order to obtain high efficiency, the high and low twin shaft two-stage turbocharger of forming by axial turbo-blower of arbitrarily downgrading is suitable for the big high-power highly supercharged diesel engine of working medium flow, and the high and low twin shaft two-stage turbocharger of forming by radial-flow turbocharger of arbitrarily downgrading then is suitable for the little small-power highly supercharged diesel engine of working medium flow.
Summary of the invention:
The present invention for working medium flow medium sized in, the two stage turbocharging system used of high-power highly supercharged diesel engine provides a kind of high efficiency, high pressure ratio twin shaft two-stage turbocharger of new structure.The technical solution used in the present invention, its low pressure stage is the single shaft axial turbo-blower of prior art ordinary construction, high pressure stage is single shaft radial-flow type (or mixed-flow) turbosupercharger of prior art ordinary construction, is connected with a diffuser pipe between the import of the outlet of high pressure stage turbine and low pressure stage turbine.
Because centrifugal field weakens than the radial turbine impeller greatly to the adverse effect of gas flow in taking turns in the mixed flow type turbine vane, so the combined flow turbine level the highest isentropic efficiency value (η that can reach
Tmax≈ 0.85) far above the radial turbine level but still a shade below the axial-flow turbine level.Combined flow turbine should substitute the application of radial turbine in occasion as much as possible as a kind of improvement of radial turbine.
Notice in the twin shaft two-stage turbocharger, the pressure ratio of low pressure stage turbosupercharger generally all is higher than the pressure ratio of high pressure stage turbosupercharger, the air of adding the low pressure stage blower outlet also will cool off through intercooler, and this just makes the air density of high pressure stage gas compressor inlet more much bigger than the density of low press gas compressor ingress.This notable change of air volume flow cause the wheel footpath size of high pressure stage compressor impeller to be significantly less than the wheel footpath size of low pressure stage compressor impeller, and the pressure ratio of twin shaft two stage turbocharging system is high more, and the gap of the two is big more.Consider single shaft axial flow, radial-flow type and the combined flow turbine pressurized machine of prior art ordinary construction, turbine in same pressurized machine and the impeller of gas compressor wheel footpath size are more or less the same each other, therefore the wheel of available compressor impeller footpath dimension D
2cThe characteristic size of pressurized machine size as a token of.In view of the gas compressor blade wheel diameter of the minimum model of prior art ordinary construction single shaft axial turbo-blower is about 200mm, so the gas compressor blade wheel diameter minimum in the low pressure stage axial turbo-blower of the present invention should also not be D less than 200mm
2cmin〉=200mm.On the other hand, according to the performance comparison test of axial turbo-blower and radial-flow turbocharger as can be known, the turbine wheel diameter D that the two efficient is suitable
1tBe about about 400mm, so the turbine diameter in high pressure stage radial-flow type of the present invention (or mixed-flow) turbosupercharger should also be D greater than 400mm the most very much not
1tmax≤ 400mm.
Connect the diffuser pipe of high and low pressure turbine stage, it is not only a link that makes the supercharger structure compactness, still the important pneumatic element that can improve turbine efficiency, increase turbine power.It can reclaim the kinetic energy of the high-speed fuel gas air-flow that is flowed out by the high pressure stage turbine wheel, makes after its rising that is converted into pressure in diffuser pipe expansion working in the low pressure stage turbine again.For guide vane or the rectifier of implementing diffusion effectively in diffuser pipe, should install additional in diffuser pipe air-flow is flowed vertically, the diffuser pipe that design is good can make turbine efficiency improve 3～5%.
In order to improve the off design performance of low pressure stage gas compressor---the compressor efficiency when improving partial load condition; The range of flow of expansion steady working condition is avoided surge and obstruction; Increase the range of flow that high efficient area occupies: regulate the variation of boost pressure etc., should install an adjustable controlling device of prewhirling of blade angle in the place ahead of low pressure stage compressor impeller import additional, so that improved by the off design performance of the low pressure stage gas compressor that partial load condition has the greatest impact, thereby also improved the off design performance of whole twin shaft two-stage turbocharger
When the twin shaft two-stage turbocharger of the present invention and prior art be applied to working medium flow medium sized in, on the two stage turbocharging system used of high-power highly supercharged diesel engine the time, the comparable situation between them is summarized as follows:
● the comparison of efficient aspect
Because the type selecting of the high and low turbine of arbitrarily downgrading is reasonable with configuration, thereby makes them can both obtain the highest isentropic efficiency value that can reach separately under service condition, thereby turbocharger efficiency of the present invention is the highest.
● the diesel exhaust gas pulse energy is utilized the comparison of aspect
The present invention and prior art be high and low the arbitrarily downgrade combustion gas air inlet volute of high pressure stage turbine of the two-stage turbocharger that all is radial turbine, its structure resembles a pulse converter very much, help the utilization of diesel exhaust gas pulse energy and the even air inlet of full week of turbine, prior art is high and low arbitrarily downgrades all is that the combustion gas gas inlet shell of two-stage turbocharger of axial-flow turbine does not then generally possess this function.
● the comparison of structural compactness, cost aspect
High and low the arbitrarily downgrading of the present invention and prior art all is twin shaft two-stage turbochargers of axial-flow turbine, and the shaft axis of their high pressure stage turbosupercharger and low pressure stage turbosupercharger all is located along the same line, and such structural configuration is the compactest.The high and low pressure turbine stage all is twin shaft two-stage turbochargers of radial turbine, and the pipeline of itself connects and it is connected with pipeline between Diesel Engine Exhaust Pipe and the intercooler, makes its structural configuration very complicated, and the spatial volume that occupies is maximum also.Therefore only with regard to structural compactness, the best of the present invention, high and low arbitrarily downgrading all is that the two-stage supercharger of axial-flow turbine takes second place, high and low arbitrarily downgrading all is that the two-stage turbocharger of radial turbine is the poorest.The quality of structural compactness is most important to the application of high supercharging pressure level two-stage turbocharger.Because for highly supercharged diesel engine, even by the operation of cube roadability, low-load performance also can not meet the demands, more particularly press service conditions such as quadratic power roadability, skimming boat characteristic, hydro-jet propulsion system, two-shipper and car, low-load performance must take appropriate measure to improve.The high operating mode venting of in the past taking, intake and exhaust bypass, variable geometry turbocharger, Miller system, Gu Shi system etc. can not satisfy the requirement of low-load performance, so the high-power diesel engine of recent development adopts sequential pressurizing (STC) system morely.It adopts (2～4 of many pressurized machines, for example adopt 4), can make out of service by whole pressurized machine of turbine passage section when low operating mode like this, and 1/2,1/3 even 1/4 when being reduced to original many pressurized machine standard-sized sheets step by step improved low-load performance greatly by platform.Obviously, in the case, the structure of twin shaft two-stage turbocharger spatial volume must be very compact, that occupy is less.For in plateau operation recovering for the highly supercharged diesel engine that power is purpose, it is equally very strict to the restriction of the requirements of installation space of high supercharging pressure level turbosupercharger, the present invention is available, adopt.
In price, the present invention is placed in the middle, and prior art is high and low arbitrarily downgrades all is that the twin shaft two-stage turbocharger price of axial-flow turbine is the most expensive.
Description of drawings:
Fig. 1 is the single-stage axial turbosupercharger sectional arrangement drawing of prior art ordinary construction.Digital implication among the figure: 1---compressor casing combination, 2---gas compressor end axle envelope parts, 3---the screw lock iron wire, 4---bolt, 5---packing ring, 6---the Diffuser lid, 7---packing ring, 8---nut, 9---gas compressor step bearing parts, 10---gas compressor end thrust bearing, 11---the rotor combination, 12---the turbine end thrust bearing, 13---the turbine end bearing part, 14---the turbine end gasket seal, 15---turbine end axle envelope, 16---the turbine end gasket seal, 17---the sealing gland ring, 18---the carbon circle, 19---bolt, 20---the screw lock iron wire, 21---the turbine case combination, 22---middle case combination, 23---adjusting pad, 24---gas compressor end gasket seal.
Fig. 2 shows the sectional arrangement drawing of the small-sized single shaft combined flow turbine of prior art ordinary construction pressurized machine.Digital implication among the figure: 1---compressor casing, 2---the gas compressor end nut, 3---compressor impeller, 4---gas compressor end seal ring, 5---the axle envelope.6---tie-plate, 7---oil baffle disc, 8---pad, 9---thrust bearing, 10---the spacing thrust housing, 11---full-floating bearing, 12---the full-floating bearing back-up ring, 13---the turbine end seal ring, 14---thermal shield, 15---middle case, 16---turbine rotor shaft, 17---turbine volute, 18---nameplate, 19---rivet, 20---O type rubber seal, 21---bolt, 22---wave spring washer, 23---bolt, 24---screw, 25---bolt, 26---bolt.
Fig. 3 is the adjustable compressor inlet of the blade angle controlling device schematic representation of prewhirling.Digital implication among the figure: 1---rolling bearing, 2---goniometer, 3---gear, 4---gear piece, 5---sleeve pipe, 6---the rotation guide vane.
Fig. 4 shows the sectional arrangement drawing of prior art ordinary construction single shaft radial-flow turbocharger.Different with structure shown in Figure 2, the gas compressor of Fig. 4 high pressure stage has installed vane diffuser additional, and its turbine also increases has adorned nozzle ring.
Embodiment:
Fig. 5 is the schematic representation of the twin shaft two-stage turbocharger of structure of the present invention, it is low, the high pressure stage turbosupercharger is made up of the single shaft axial turbo-blower and single shaft radial-flow type (or mixed-flow) turbosupercharger of prior art ordinary construction respectively, and being connected in series by an axial diffuser pipe between high pressure stage turbine outlet and low pressure stage turbine inlet becomes one.
Fig. 6 is identical with Fig. 5 basic structure, but has installed the controlling device of prewhirling shown in Figure 3 additional at the low pressure stage compressor inlet, has increased straightener(stator) blade in addition in diffuser pipe.
Claims (3)
1, a kind of twin shaft two-stage turbocharger of using of highly supercharged diesel engine, it is characterized in that: its high pressure stage is single shaft radial-flow type (or mixed-flow) turbosupercharger of an ordinary construction, low pressure stage then is the single shaft axial turbo-blower of an ordinary construction, connects the formation one with a diffuser pipe polyphone between the import of the outlet of high pressure stage turbine and low pressure stage turbine;
2, by the described twin shaft two-stage turbocharger of claim 1, it is characterized in that: the gas compressor blade wheel diameter in the low pressure stage axial turbo-blower should be less than 200mm; Turbine wheel diameter in high pressure stage radial-flow type (or mixed-flow) turbosupercharger should be greater than 400mm.
3, by the described twin shaft two-stage turbocharger of claim 1, it is characterized in that: the compressor inlet of low pressure stage axial turbo-blower is equipped with the adjustable controlling device of prewhirling of blade angle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNA2004100168795A CN1560441A (en) | 2004-03-11 | 2004-03-11 | Supercharger for double axle two stage turbine of supercharged diesel engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNA2004100168795A CN1560441A (en) | 2004-03-11 | 2004-03-11 | Supercharger for double axle two stage turbine of supercharged diesel engine |
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| CN1560441A true CN1560441A (en) | 2005-01-05 |
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|---|---|---|---|
| CNA2004100168795A Pending CN1560441A (en) | 2004-03-11 | 2004-03-11 | Supercharger for double axle two stage turbine of supercharged diesel engine |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101523027B (en) * | 2006-10-17 | 2011-05-25 | 博格华纳公司 | Ring seals for gas sealing and vibration damping |
| CN102155288A (en) * | 2011-02-22 | 2011-08-17 | 潍柴动力股份有限公司 | Double-supercharged diesel engine gas circuit |
| CN102606285A (en) * | 2012-04-07 | 2012-07-25 | 潍坊富源增压器有限公司 | Turbocharger with two-stage supercharging function |
-
2004
- 2004-03-11 CN CNA2004100168795A patent/CN1560441A/en active Pending
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101523027B (en) * | 2006-10-17 | 2011-05-25 | 博格华纳公司 | Ring seals for gas sealing and vibration damping |
| CN102155288A (en) * | 2011-02-22 | 2011-08-17 | 潍柴动力股份有限公司 | Double-supercharged diesel engine gas circuit |
| CN102155288B (en) * | 2011-02-22 | 2012-10-24 | 潍柴动力股份有限公司 | Double-supercharged diesel engine gas circuit |
| CN102606285A (en) * | 2012-04-07 | 2012-07-25 | 潍坊富源增压器有限公司 | Turbocharger with two-stage supercharging function |
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