CN201810391U - Turbine composite gas compression system - Google Patents
Turbine composite gas compression system Download PDFInfo
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- CN201810391U CN201810391U CN2010205725921U CN201020572592U CN201810391U CN 201810391 U CN201810391 U CN 201810391U CN 2010205725921 U CN2010205725921 U CN 2010205725921U CN 201020572592 U CN201020572592 U CN 201020572592U CN 201810391 U CN201810391 U CN 201810391U
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- turbine
- gas
- gas compressor
- turbocompressor
- power turbine
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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 utility model discloses a turbine composite gas compression system, which comprises a gas compressor intake passage, a gas compressor exhaust passage, a gas compressor, a turbine gas compressor and a power turbine, wherein the compressed gas outlet of the turbine gas compressor is communicated with the gas compressor intake passage, the gas compressor intake passage is communicated with a cylinder of the gas compressor through an intake door, the cylinder is communicated with the gas compressor exhaust passage through an exhaust door, the gas compressor exhaust passage is provided with a turbine working medium export and a compressed gas import, the turbine working medium export is communicated with the gas working medium inlet of the power turbine through a power turbine working medium guide pipe, and the power turbine outputs power to the turbine gas compressor. The turbine composite gas compression system disclosed by the utility model fully exerts respective advantages of the turbine and the gas compressor, and the efficient gas compression system is realized.
Description
Technical field
The utility model relates to heat energy and power field, especially a kind of turbine composite gas compression system.
Background technique
The existing very long history of technology of utilizing turbine that the gas that will enter in the cylinder is carried out supercharging, turbine has the advantage that volume is little, in light weight, flow is big, thereby this technology is used widely.Yet up to now, the technology that turbine matches with gas compressor is also rarely found, its main cause is because the rotating speed of turbocompressor requires height, with machinery or electric mode is difficult to reach tens thousand of to its transmission even 100,000 change above (if the rotating speed of turbine is not high enough, turbine is calmed the anger and will be lost its advantage).The advantage of turbocompressor as mentioned above, the gas compressor gas compressor that to be piston gas compressor, screw type gas compressor, rotator type gas compressor etc. produce gas pressure by volume-variation all has and own vol and the weight little shortcoming of specific discharge mutually, but has the high advantage of output gas pressure.Therefore, be badly in need of a kind of turbine and gas compressor gas compression system of advantage separately of giving full play to of invention.
Summary of the invention
In order to address the above problem, the technological scheme that the utility model proposes is as follows:
A kind of turbine composite gas compression system, comprise the gas compressor intake duct, the gas compressor air outlet flue, gas compressor, turbocompressor and power turbine, the pressurized gas outlet of described turbocompressor is communicated with described gas compressor intake duct, described gas compressor intake duct is communicated with the cylinder of described gas compressor through intake valve, described cylinder is communicated with described gas compressor air outlet flue through exhaust valve, on described gas compressor air outlet flue, establish turbine working medium export mouth and pressurized gas export mouth, described turbine working medium export mouth is communicated with the gas working medium inlet of described power turbine through power turbine working medium ingress pipe, and described power turbine is to described turbocompressor outputting power.
On described gas compressor intake duct, establish the air inlet cooler, and/or on described gas compressor air outlet flue, establish the exhaust cooling device.
Described turbocompressor is made as the multistage turbine gas compressor, and/or described power turbine is made as multistage power turbine.
Described turbocompressor is made as the multistage turbocompressor of being made up of a plurality of single stage turbine gas compressors, and described power turbine is made as the multistage power turbine of being made up of a plurality of single-stage power turbines.
The coaxial setting of first single-stage power turbine in first single stage turbine gas compressor in the described multistage turbocompressor and the described multistage power turbine, the coaxial setting of second described power turbine of single-stage in second single stage turbine gas compressor in the described multistage turbocompressor and the described multistage power turbine, the rest may be inferred.
A coaxial setting of single-stage power turbine beyond first single-stage power turbine in first single stage turbine gas compressor in the described multistage turbocompressor and the described multistage power turbine.
On described turbocompressor, establish the heat extraction device.
On described turbocompressor, described gas compressor intake duct, described gas compressor air outlet flue, described gas compressor and/or described power turbine working medium ingress pipe, establish the heat extraction device.
The gas outlet of described power turbine is communicated with the cooling gas inlet of described heat extraction device, utilizes through the gas after the described power turbine cooling and uses as low-temperature receiver.
The gas outlet of described power turbine is communicated with the gas access of described turbocompressor, makes through the gas after the described power turbine cooling and reenters described turbocompressor.
Principle of the present utility model is to utilize power source to described gas compressor outputting power, described gas compressor produces pressurized gas, utilizing the part of the pressurized gas that described gas compressor produces to promote described power turbine makes described power turbine produce power, the power that utilizes described power turbine to produce makes described turbocompressor rotation and produces the pressurized gas with certain pressure, and the pressurized gas that is produced by described turbocompressor provides source of the gas for described gas compressor; In other words, gas at first enters described turbocompressor, enter described gas compressor after in described turbocompressor, being pressurized, further being compressed supercharging in described gas compressor after, gas discharges described gas compressor, the part of the gas of being discharged by described gas compressor removes to promote described power turbine makes described power turbine to described turbocompressor outputting power, and another part of the gas of being discharged by described gas compressor is as the high pressure compressed gas of system's output.
Turbine composite gas compression system disclosed in the utility model is owing to adopt pressurized gas to promote described power turbine as power source, again by the mode of described power turbine to described turbocompressor outputting power, so can make described power turbine and described turbocompressor be in work under the quite high rotating speed, give full play to the advantage of described power turbine and described turbocompressor.Moreover, in this system, if the pressurized gas that enters described power turbine is carried out certain cooling, just can make the temperature of the gas outlet of described power turbine be in lower even quite low level, for this reason, the gas that is come out by the gas outlet of described power turbine can be used as low-temperature receiver and is used for purposes such as refrigeration, also can be used as low-temperature receiver and uses with gas, working medium or parts to the cooling of the needs in the described turbine composite gas compression system and cool off.
So-called gas compressor is meant the gas compressing apparatus that is produced gas pressure by volume-variation in the utility model, can be piston gas compressor, screw type gas compressor or rotator type gas compressor; So-called gas compressor air outlet flue is meant the pressurized gas passage that is communicated with the pressurized gas outlet of described gas compressor; So-called gas compressor intake duct is meant the gas channel that is communicated with the gas access of described gas compressor; So-called exhaust is meant by the high pressure compressed gas after the described gas compressor compression; So-called exhaust cooling device is meant the device that the high pressure compressed gas after the compression is lowered the temperature, it can be radiator, also can be to be the heat exchanger of purpose with the cooling, it can also be the hybrid exhaust cooling device that the fluid that temperature is lower mixes with high pressure compressed gas, so-called hybrid exhaust cooling device is meant high pressure compressed gas and cryogen is directly mixed the cooler that conducts heat, its essence is a container, exhaust and cryogen are mixed in this container, in order to increase the uniformity of mixing, in this container, can establish flow guide structure, stirring mechanism or fluidic architecture; So-called air inlet cooler is meant the device that the gas that enters described gas compressor is lowered the temperature, with the exhaust cooling device; So-called heat extraction device is meant the device that heat is externally discharged, and it can be a radiator, also can be to be the heat exchanger of purpose with the cooling; So-called turbocompressor is meant the mechanism that utilizes rotation blade or rotating channel that gas is compressed, and it can be single-stage, multistage, also can be a plurality of single-stages or a plurality of multistage combining; So-called power turbine is meant and utilizes exhaust promotion blade or passage to rotate the mechanism of external work done; So-called multistage is meant a plurality of turbocompressor series connection or the series connection of a plurality of power turbine; Putting in order of so-called first single-stage and second single-stage is that starting point is foundation along the gas connection pipe road to leave the cylinder distance with the cylinder, apart from cylinder near be the first order, taking second place is the second level, the rest may be inferred.
In the utility model so-called be communicated be meant direct connection, through the indirect communication of several processes (comprise with other material mixing etc.) or through controlled connections such as pump, control valves.
In order to realize the proper functioning of turbine composite gas compression system disclosed in the utility model, pump and control valve etc. are set in position according to the needs that flow.
The beneficial effects of the utility model are as follows:
Turbine composite gas compression system disclosed in the utility model has been given full play to turbine and gas compressor advantage separately, has realized gas compression system efficiently.
Description of drawings
Fig. 1 is the utility model embodiment 1 a structural representation;
Fig. 2 is the utility model embodiment 2 a structural representation;
Fig. 3 is the utility model embodiment 3 a structural representation;
Fig. 4 is the utility model embodiment 4 a structural representation;
Fig. 5 is the utility model embodiment 5 a structural representation;
Fig. 6 is the utility model embodiment 6 a structural representation;
Fig. 7 is the utility model embodiment 7 a structural representation;
Fig. 8 is the utility model embodiment 8 a structural representation;
Fig. 9 is the utility model embodiment 9 a structural representation;
Figure 10 is the utility model embodiment 10 a structural representation.
Embodiment
Turbine composite gas compression system as shown in Figure 1, comprise gas compressor intake duct 1, gas compressor air outlet flue 2, gas compressor 3, turbocompressor 4 and power turbine 5, the pressurized gas outlet of turbocompressor 4 is communicated with gas compressor intake duct 1, gas compressor intake duct 1 is communicated with the cylinder 301 of gas compressor 3 through intake valve 7, cylinder 301 is communicated with gas compressor air outlet flue 2 through exhaust valve 8, on gas compressor air outlet flue 2, establish turbine working medium export mouth 221 and pressurized gas export mouth 222, turbine working medium export mouth 221 is communicated with the gas working medium inlet of power turbine 5 through power turbine working medium ingress pipe 224,5 pairs of turbocompressor 4 outputting powers of power turbine, the gas access of turbocompressor 4 is communicated with low-pressure gas source 6, so-called low-pressure gas source 6 is meant air can be provided, the system of low oxygen or low pressure oxygen-containing gas, gas handling system of motor etc. for example, gas compressor 3 is connected with power source 300,300 pairs of gas compressor 3 outputting powers of power source; Pressurized gas export mouth 222 is outlets of system's output high pressure compressed gas.Gas compressor 3 can be piston gas compressor, screw type gas compressor or rotator type gas compressor.In the disclosed scheme of present embodiment, gas at first enters turbocompressor 4, enter gas compressor 3 after in turbocompressor 4, being pressurized, further being compressed supercharging in gas compressor 3 after, gas discharges gas compressor 3, the part of the gas of being discharged by gas compressor 3 goes propulsion power turbine 5 to make 5 pairs of turbocompressor 4 outputting powers of power turbine, another part of the gas of being discharged by gas compressor 3 is as the high pressure compressed gas of system's output, so just give full play to turbocompressor 4 and gas compressor 3 advantage separately, realized gas compression system efficiently.
Turbine composite gas compression system as shown in Figure 2, itself and embodiment's 1 difference is: establish air inlet cooler 100 on gas compressor intake duct 1.The purpose of She Zhiing is that the gas that will enter gas compressor 3 cools off like this, increases the amount of the gas that enters gas compressor 3, improves the efficient of calming the anger of gas compressor 3.
Turbine composite gas compression system as shown in Figure 3, its difference with embodiment 1 is: establish exhaust cooling device 200 on the power turbine working medium ingress pipe 224 that is communicated with gas compressor air outlet flue 2, the purpose of She Zhiing is that the high pressure compressed gas that enters power turbine 5 is cooled off like this, increase the amount of the high pressure compressed gas that enters power turbine 5, improve the power of power turbine 5, and then improve the efficient of calming the anger of turbocompressor 4.
Turbine composite gas compression system as shown in Figure 4, itself and embodiment's 1 difference is: turbocompressor 4 is made as multistage turbine gas compressor 400, and power turbine 5 is made as multistage power turbine 500.The purpose of She Zhiing is in order to improve the power of power turbine 5 equally like this, and then improves the efficient of calming the anger of turbocompressor 4.
Turbine composite gas compression system as shown in Figure 5, itself and embodiment's 1 difference is: turbocompressor 4 is made as the multistage turbocompressor of being made up of a plurality of single stage turbine gas compressors 401, and power turbine 5 is made as the multistage power turbine of being made up of a plurality of single-stage power turbines 501.The coaxial setting of first single-stage power turbine in first single stage turbine gas compressor in the multistage turbocompressor 401 and the multistage power turbine 501, second coaxial setting of single-stage power turbine in second single stage turbine gas compressor in the multistage turbocompressor 401 and the multistage power turbine 501, the rest may be inferred.The purpose of She Zhiing is in order to improve the power of power turbine 5 equally like this, and then improves the efficient of calming the anger of turbocompressor 4.
Turbine composite gas compression system as shown in Figure 6, itself and embodiment's 5 difference is: a coaxial setting of single-stage power turbine beyond first single-stage power turbine in first single stage turbine gas compressor in the multistage turbocompressor 401 and the multistage power turbine 501.
Turbine composite gas compression system as shown in Figure 7, itself and embodiment's 1 difference is: establish heat extraction device 402 on turbocompressor 4.The purpose of She Zhiing is that the gas that will enter turbocompressor 4 cools off like this, increases the amount of the gas that enters turbocompressor 4, improves the efficient of calming the anger of turbocompressor 4.
Turbine composite gas compression system as shown in Figure 8, itself and embodiment's 1 difference is: on the passage between low-pressure gas source 6 and the turbocompressor 4, on the gas compressor intake duct 1, establishing heat extraction device 1234 respectively on the power turbine working medium ingress pipe 224 and on the pressurized gas delivery line 223, heat extraction device 1234 is made as radiator.The purpose of She Zhiing is for gas being cooled off, improving the compression efficiency of system like this.
In addition, can also on gas compressor air outlet flue 2, gas compressor 3, establish heat extraction device 1234.
Embodiment 9
Turbine composite gas compression system as shown in Figure 9, itself and embodiment's 1 difference is: establishing heat extraction device 1234 on the gas compressor intake duct 1 and on power turbine working medium ingress pipe 224, heat extraction device 1234 is made as to be cooled to the heat exchanger of purpose, the gas outlet of described power turbine 5 is communicated with the cooling gas inlet of described heat extraction device 1234, utilize through the gas after described power turbine 5 coolings and use as low-temperature receiver, gas is cooled off, improve the compression efficiency of system.
Embodiment 10
Turbine composite gas compression system as shown in figure 10, its difference with embodiment 1 is: the gas outlet of power turbine 5 is communicated with the gas access of turbocompressor 4, makes through the gas after power turbine 5 coolings and reenters turbocompressor 4.The purpose of She Zhiing is that air inlet is cooled off equally like this, increases the amount of the gas that enters turbocompressor 4, improves the efficient of calming the anger of turbocompressor 4, improves the utilization ratio of gas simultaneously.
Claims (10)
1. turbine composite gas compression system, comprise gas compressor intake duct (1), gas compressor air outlet flue (2), gas compressor (3), turbocompressor (4) and power turbine (5), it is characterized in that: the pressurized gas outlet of described turbocompressor (4) is communicated with described gas compressor intake duct (1), described gas compressor intake duct (1) is communicated with the cylinder (301) of described gas compressor (3) through intake valve (7), described cylinder (301) is communicated with described gas compressor air outlet flue (2) through exhaust valve (8), on described gas compressor air outlet flue (2), establish turbine working medium export mouth (221) and pressurized gas export mouth (222), described turbine working medium export mouth (221) is communicated with the gas working medium inlet of described power turbine (5) through power turbine working medium ingress pipe (224), and described power turbine (5) is to described turbocompressor (4) outputting power.
2. turbine composite gas compression system according to claim 1 is characterized in that: establish air inlet cooler (100) on described gas compressor intake duct (1), and/or establish exhaust cooling device (200) on described gas compressor air outlet flue (2).
3. turbine composite gas compression system according to claim 1, it is characterized in that: described turbocompressor (4) is made as multistage turbine gas compressor (400), and/or described power turbine (5) is made as multistage power turbine (500).
4. turbine composite gas compression system according to claim 1, it is characterized in that: described turbocompressor (4) is made as the multistage turbocompressor of being made up of a plurality of single stage turbine gas compressors (401), and described power turbine (5) is made as the multistage power turbine of being made up of a plurality of single-stage power turbines (501).
5. as turbine composite gas compression system as described in the claim 4, it is characterized in that: the coaxial setting of first single-stage power turbine in first single stage turbine gas compressor in the described multistage turbocompressor (401) and the described multistage power turbine (501), the coaxial setting of second described power turbine of single-stage in second single stage turbine gas compressor in the described multistage turbocompressor (401) and the described multistage power turbine (501), the rest may be inferred.
6. as turbine composite gas compression system as described in the claim 4, it is characterized in that: a coaxial setting of single-stage power turbine beyond first single-stage power turbine in first single stage turbine gas compressor in the described multistage turbocompressor (401) and the described multistage power turbine (501).
7. turbine composite gas compression system according to claim 1 is characterized in that: establish heat extraction device (402) on described turbocompressor (4).
8. turbine composite gas compression system according to claim 1 is characterized in that: establish heat extraction device (1234) on described turbocompressor (4), described gas compressor intake duct (1), described gas compressor air outlet flue (2), described gas compressor (3) and/or described power turbine working medium ingress pipe (224).
9. as turbine composite gas compression system as described in the claim 8, it is characterized in that: the gas outlet of described power turbine (5) and described heat extraction device 1234) cooling gas inlet be communicated with, utilize through the gas after described power turbine (5) cooling and use as low-temperature receiver.
10. turbine composite gas compression system according to claim 1, it is characterized in that: the gas outlet of described power turbine (5) is communicated with the gas access of described turbocompressor (4), makes through the gas after described power turbine (5) cooling and reenters described turbocompressor (4).
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| CN2010205725921U CN201810391U (en) | 2010-10-22 | 2010-10-22 | Turbine composite gas compression system |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010205725921U CN201810391U (en) | 2010-10-22 | 2010-10-22 | Turbine composite gas compression system |
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| CN201810391U true CN201810391U (en) | 2011-04-27 |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101988426A (en) * | 2010-10-22 | 2011-03-23 | 靳北彪 | Turbine composite gas compression system |
| CN102865139A (en) * | 2011-09-08 | 2013-01-09 | 摩尔动力(北京)技术股份有限公司 | Runoff jet flow heat power system |
| CN103061851A (en) * | 2012-01-13 | 2013-04-24 | 摩尔动力(北京)技术股份有限公司 | Hot gas self-cooling machine |
| CN103104369A (en) * | 2012-01-27 | 2013-05-15 | 摩尔动力(北京)技术股份有限公司 | Turbine distribution thermomotor |
| CN103195607A (en) * | 2012-03-28 | 2013-07-10 | 摩尔动力(北京)技术股份有限公司 | Heat source working hot air engine |
| CN103306846A (en) * | 2012-07-07 | 2013-09-18 | 摩尔动力(北京)技术股份有限公司 | Air flow circulating engine |
-
2010
- 2010-10-22 CN CN2010205725921U patent/CN201810391U/en not_active Expired - Fee Related
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101988426A (en) * | 2010-10-22 | 2011-03-23 | 靳北彪 | Turbine composite gas compression system |
| WO2012051785A1 (en) * | 2010-10-22 | 2012-04-26 | Jin Beibiao | Turbine-compounded gas compression system |
| CN102865139A (en) * | 2011-09-08 | 2013-01-09 | 摩尔动力(北京)技术股份有限公司 | Runoff jet flow heat power system |
| CN103061851A (en) * | 2012-01-13 | 2013-04-24 | 摩尔动力(北京)技术股份有限公司 | Hot gas self-cooling machine |
| CN103104369A (en) * | 2012-01-27 | 2013-05-15 | 摩尔动力(北京)技术股份有限公司 | Turbine distribution thermomotor |
| CN103104369B (en) * | 2012-01-27 | 2015-07-29 | 摩尔动力(北京)技术股份有限公司 | A kind of turbine distribution thermomotor |
| CN103195607A (en) * | 2012-03-28 | 2013-07-10 | 摩尔动力(北京)技术股份有限公司 | Heat source working hot air engine |
| CN103306846A (en) * | 2012-07-07 | 2013-09-18 | 摩尔动力(北京)技术股份有限公司 | Air flow circulating engine |
| CN103306846B (en) * | 2012-07-07 | 2015-05-20 | 摩尔动力(北京)技术股份有限公司 | Air flow circulating engine |
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| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20110427 Termination date: 20141022 |
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| EXPY | Termination of patent right or utility model |