WO2006045712A1 - Vorrichtung zur erzeugung von hochkomprimiertem gas - Google Patents
Vorrichtung zur erzeugung von hochkomprimiertem gas Download PDFInfo
- Publication number
- WO2006045712A1 WO2006045712A1 PCT/EP2005/055278 EP2005055278W WO2006045712A1 WO 2006045712 A1 WO2006045712 A1 WO 2006045712A1 EP 2005055278 W EP2005055278 W EP 2005055278W WO 2006045712 A1 WO2006045712 A1 WO 2006045712A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- gas
- compressor
- pressure
- vortex tube
- flow
- Prior art date
Links
- 238000001816 cooling Methods 0.000 claims description 30
- 230000009467 reduction Effects 0.000 claims description 14
- 230000000694 effects Effects 0.000 claims description 12
- 230000006835 compression Effects 0.000 claims description 10
- 238000007906 compression Methods 0.000 claims description 10
- 238000010438 heat treatment Methods 0.000 claims description 10
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 10
- 239000002826 coolant Substances 0.000 claims description 4
- 239000008236 heating water Substances 0.000 claims description 2
- 239000007789 gas Substances 0.000 abstract description 217
- 239000000112 cooling gas Substances 0.000 abstract 1
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 36
- 239000003345 natural gas Substances 0.000 description 16
- 238000000034 method Methods 0.000 description 14
- 230000008569 process Effects 0.000 description 9
- 238000012546 transfer Methods 0.000 description 6
- 238000000605 extraction Methods 0.000 description 5
- 230000002349 favourable effect Effects 0.000 description 4
- 238000003780 insertion Methods 0.000 description 4
- 230000037431 insertion Effects 0.000 description 4
- 238000000926 separation method Methods 0.000 description 4
- 238000010276 construction Methods 0.000 description 3
- 238000003860 storage Methods 0.000 description 3
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 description 2
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 238000002156 mixing Methods 0.000 description 2
- 239000007787 solid Substances 0.000 description 2
- 230000001960 triggered effect Effects 0.000 description 2
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 1
- 239000003570 air Substances 0.000 description 1
- 229910052786 argon Inorganic materials 0.000 description 1
- 230000001174 ascending effect Effects 0.000 description 1
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 239000003225 biodiesel Substances 0.000 description 1
- 230000033228 biological regulation Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000005352 clarification Methods 0.000 description 1
- 239000000498 cooling water Substances 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 238000004146 energy storage Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000011156 evaluation Methods 0.000 description 1
- 238000005429 filling process Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000003502 gasoline Substances 0.000 description 1
- 239000001257 hydrogen Substances 0.000 description 1
- 229910052739 hydrogen Inorganic materials 0.000 description 1
- 239000008235 industrial water Substances 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 229910052757 nitrogen Inorganic materials 0.000 description 1
- 239000001301 oxygen Substances 0.000 description 1
- 229910052760 oxygen Inorganic materials 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 238000013517 stratification Methods 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
- 238000010792 warming Methods 0.000 description 1
- 238000004804 winding Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F25—REFRIGERATION OR COOLING; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS; MANUFACTURE OR STORAGE OF ICE; LIQUEFACTION SOLIDIFICATION OF GASES
- F25B—REFRIGERATION MACHINES, PLANTS OR SYSTEMS; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS
- F25B9/00—Compression machines, plants or systems, in which the refrigerant is air or other gas of low boiling point
- F25B9/02—Compression machines, plants or systems, in which the refrigerant is air or other gas of low boiling point using Joule-Thompson effect; using vortex effect
- F25B9/04—Compression machines, plants or systems, in which the refrigerant is air or other gas of low boiling point using Joule-Thompson effect; using vortex effect using vortex effect
Definitions
- the invention relates to a device for producing highly compressed gas with a single-stage or multi-stage compressor.
- the device according to the invention can be used in addition to numerous other applications in a gas refueling system for refueling powered by natural gas, methane or similar gases and hydrogen-powered vehicles.
- DE 197 05 601 A1 describes a natural gas refueling process without cooling the gas, in which the refueling process of the pressurized gas container is carried out until the pressure in the line to the pressurized gas container exceeds a maximum pressure. Another possibility provides that the refueling process is aborted when the mass flow falls below a threshold value.
- WO 97/06383 Al describes a gas charging system for high-pressure bottles.
- the cooling of the gas takes place here by winding the high-pressure bottle to be filled, whereby two connections for flow and return are required.
- the gas is cooled by a heat exchanger or by mixing with the gas in the reservoir.
- EP 0 653 585 A1 discloses a system for refueling a compressed gas container. Therein, the carrying out of a test impact is described and the thermal equation of state for the real gas is used for its evaluation. There is also a switch over to reservoir with higher pressure (multiple bank method) during the refueling described. The reaction process takes place intermittently. There is no cooling device for the gas provided.
- This natural gas can be compressed in the garage by means of a compressor (natural gas compressor) during the night from the usual natural gas pressure level of 50 mbar to 200 bar at a reference temperature of 15 ° C. This can be refueled a motor vehicle.
- the invention has for its object to provide a device for the production of highly compressed gas, in which the compressed gas which is heated in the compression, is cooled in a cooling device, which is of simple construction, a high cooling performance and of small dimensions can be realized.
- the device according to the invention is defined by the patent claim 1.
- the compressor stage nachgeordncte cooling device is designed as a vortex tube.
- Vortex tubes are particularly well-suited for ultra-short temperature reductions. These temperature reductions can also be realized in contrast to conventional gas coolers on the shortest path length. Furthermore, the invention is based on the recognition that the pressure ratio in the compressor stages of the high-pressure compressor is greater than 3. This ensures that the vortex tubes in all compressor stages will be in the supercritical range, which is essential for proper functioning of the tuyere tubes.
- a particular embodiment of the invention envisages to maintain the reference temperature of 15 ° C at a pressure of 200 bar in the pressurized gas container to be filled even if the lowering of the gas temperature in the vortex tubes at unfavorable boundary and environmental conditions is no longer sufficient for a Dircktbetankung , Conveniently, after the last compressor stage with subsequent throttle point, the gas is not introduced into the pressurized gas container to be filled, but fed back to the compressor inlet after an adiabatic throttling (Joule-Thomson effect).
- the gas then undergoes a steady temperature reduction in isotropic compression and adiabatic throttling (cooling by adiabatic throttling, caused by the Joule-Thomson effect in real gases).
- the gas cycle then remains closed until the time required for filling the gas cylinder according to the technical rules temperature reduction is reached
- a particularly expedient embodiment of the invention provides for the heat produced in the vortex tubes to be used for heating industrial water or for heating a building.
- the output pressure of a multi-stage compressor is set so high that this pressure is above the critical pressure of the compressed gas container to be filled.
- these regulations do not apply to direct refueling with a high pressure compressor, provided the legal conditions for the compressed gas container are maintained.
- the gas stream leaving the final stage of the high-pressure compressor is brought to the permissible pressure in the pressure vessel via an expansion turbine by throttling.
- the mechanical work occurring at the expansion turbine is used to drive a compressor for pre-compression of the gas taken from the gas network.
- the outlet pressure at the high-pressure compressor can be used to vary the outlet pressure at the compressor.
- throttling a presettable output pressure can thus be received on the ambient conditions during refueling and indirectly acted on the gas temperature in the pressurized gas container.
- the invention further relates to a device for lowering the temperature of a gas from a reservoir containing pressurized gas, with a feed tube leading to a swirl generator, a filling tube leading to the compressed gas container and a vortex tube branching off from the swirl orifice for guiding a rotating swirl flow.
- a gas has a higher volume at a higher temperature. Therefore, it is often necessary for reasons of space to carry out a cooling of the gas, as at given space to accommodate more gas mass.
- a typical application! gas cooling are gas refueling operations.
- gases to be replenished may include natural gas or methane or similar gases as well as gases such as nitrogen, oxygen, argon, air or hydrogen.
- the energy supply to be applied leads to a heating of the gas in the compressed gas tank.
- the Joule-Thomson effect (temperature change of the gas through throttling) of the real gas counteracts this heating in general.
- the Joule-Thomson effect and the heat release to the environment are sufficient to compensate for the heating caused by insertion of the gas. If these favorable conditions are not met, it comes in gas filling plants without cooling device during fast transfer to a Unterfullung the gas cylinder.
- the invention is further based on the object to provide a device for lowering the temperature of a gas that is small-scale manufacturable and simple in construction and has a short response time with high Kuhlw ⁇ rkung.
- the device according to the invention for temperature reduction has the features of claim 17.
- the device is characterized in that the vortex tube is exposed on its outside of a cooling device, that in the vortex tube, a swirl brake for braking the swirl flow is arranged and that leads from the swirl brake, a flow path in the discharge pipe.
- the entire gas stream is made largely swirl-free after lowering the temperature of the swirl flow and fed to the compressed gas container.
- a throttle device for controlling a hot gas flow is not required.
- the gas at supercritical Druckver conceptionn ⁇ s ie at a speed lying slightly below the speed of sound, tangentially fed to a swirl generator.
- This initiates a rotating swirl flow into the vortex tube.
- the swirl flow propagates at high axial velocity in the vortex tube, whereby the tube wall heats up strongly.
- the highly turbulent mixing causes a Adiabatic stratification and the outer part of the swirl flow also has a higher static temperature than the inner part with the large centrifugal pressure.
- the swirl flow is cooled by the outside acting on the vortex tube cooling device and then braked by a swirl brake, the flow is then fed via a flow path to the filling tube, which leads to the compressed gas tank. In this way, the entire gas taken from the reservoir enters the compressed gas tank.
- the flow path runs centrally through the vortex tube within the swirl flow. While the swirl flow is rotating, a centric return flow forms along its axis. As the outer swirl flow heats up, the linear internal backflow is much colder.
- the full tube also branches off from the drainage generator and that the diameter of the full pipe is smaller than the diameter of the vortex tube.
- the swirl-free linear return flows again into the swirl generator and from there into the full pipe.
- the swirl brake preferably consists of a closure arranged in the vortex tube. Due to this, the swirl flow near the wall is decelerated because of the failure of the centrifugal forces, so that a radial inward flow results. For reasons of continuity, a centric backflow in the form of a core flow, which flows in the opposite direction to the rotating swirl flow, thus arises in the axial direction. The lower velocity of the return flow relative to the swirl flow has a further effect on the further decrease of the quiescent temperature of the inner flow to the surrounding swirl flow, whereby the temperature difference between these two flows is increased even more.
- the invention is based on the recognition that it is advantageous to dissipate the heat transferred from the rotational flow to the tube wall, which experience has shown there to be at a high temperature level.
- a designed as a coaxial tube water cooler is used for the countercurrent process for cooling the pipe wall of the vortex tube. It is thereby achieved that by cooling the pipe wall, which is the more effective, the greater the temperature difference between the object to be cooled and the Kuhlmedium, total of a temperature drop of the pipe outer flow is still an additional temperature reduction of the pipe - internal flow.
- a particularly advantageous embodiment of the invention provides that the closure forming the swirl brake is an axially adjustable piston in the vortex tube.
- the effective length of the vortex tube is made variable in order to optimize the filling process as a function of pressure and temperature of the gas in the storage container.
- the effective length of the vortex tube, d. H. the length of the effective vortex pipe section can be changed by adjusting the piston, for example by a threaded rod.
- FIG. 1 shows a schematic overview of the gas filling system with a high-pressure compressor using a Ranque-Hilsch whorl to reduce the temperature of the gas after compression, whereby a separation into cold gas and hot gas takes place in the vortex tube, - 1 L
- Fig. 2 shows the same gas refueling system as in Fig. 1, but under
- Fig. 5 is a longitudinal section through a device for lowering the temperature of gases
- Fig. 6 is a perspective view of the device of FIG. 5 for
- the gas refueling system shown in Fig. 1 has a withdrawal line 1, which leads to the series-connected compressor stages 10a, 10b, 10c and 10d.
- a check valve IIa, IIb, llc, Hd is arranged in the pipe 1.
- an inlet line 12a, 12b, 12c, 12d leads to the subsequent Verd ⁇ chtercase.
- the outlet of the compressor stage is connected via a removal line 13a, 13b, 13c, 13d to the inlet of a vortex tube 20a, 20b, 20c, 20d.
- the W ⁇ rbelrohre are generally formed in the manner described in DE 102 18 678 Al, so that a detailed explanation of the structure of the vortex tubes is unnecessary.
- the Wirbelrohrc 20a, 20b, 20c, 2Od serve to lower the gas temperature after the previous compression.
- the vortex tubes 20a, 20b, 20c, 20d operating according to the counterflow method are connected to the compressor stages 10a, 10b, 10c, 10d via the withdrawal lines 13a, 13b, 13c, 13d.
- the gas flow reaches the Einströmdusen, which form the narrowest flow-through cross-section 21a, 21b, 21c, 21d between two compressor stages.
- the gas passes at the speed of sound as a swirling flow in the central tube of the vortex tube, in which the separation into a cold gas flow and hot gas flow takes place.
- the cold core of the forming vortex is removed as Kaitgasströmung 22a, 22b, 22c, 22d and fed to the following compressor stage via the inlet ducts 12b, 12c, 12d.
- the hot gas flow 23a, 23b, 23c, 23d is removed and discharged via the pipes 24a, 24b, 24c, 24d.
- the throttling points 25a, 25b, 25c, 25d located in the pipes 24a, 24b, 24c, 24d serve to preset the mass ratio between cold gas and hot gas.
- the hot gas stream flows via the return lines 26a, 26b, 26c, 26d back into the same compressor stage, from which the gas was removed. It is achieved by the check valves 27a, 27b, 27c, 27d in the return lines 26a, 26b, 26c, 26d and the check valves IIa, IIb, 11c, Hd in the inlet lines 12a, 12b, 12c, 12d that the gas from the return lines 26a , 26b, 26c, 26d enters the inlet lines 12a, 12b, 12c, 12d.
- Each vortex tube generates a hot gas flow from the supplied gas
- Hot gas flow 23a, 23b, 23c, 23d becomes the respective compressor stage
- the cold gas flow 22d enters the pressure line 4. If there the gas temperature, which is measured with a temperature measuring device 100, above a predetermined reference value, then, triggered by a measurement signal, the Dre ⁇ wegephasehne 101,102 operated. In the normal case, these are adjusted so that the gas flow from the extraction line 1 to the series-connected compressor stages 10a, 10b, 10c, 10d leads and the cold gas flow 22d is introduced via the pressure line 6 into the compressed gas tank 7. If the cold gas temperature at the measuring point 100 has exceeded a predefined limit value, the cold gas flow 22d is diverted by means of the three-way cock 10.1 via the collecting return flow line 104.
- the cold gas flow at the throttle point 103 undergoes a further temperature reduction.
- the three-way cock 102 is actuated simultaneously with the three-way cock 101, so that no more gas supply takes place via the Entticianle ⁇ tung 1 and a closed gas cycle has arisen after actuation of the three-way valves 101,102 ,.
- a Mcsssignal is triggered, with which the three-way valves 101, 102 are actuated, so that the Ent fortunele ⁇ tung 1 again with the compressor stages 10a, 10b, 10c, 10d is connected and the cold gas flow 22d is introduced via the pressure line 6 into the compressed gas tank 7.
- the Gasbctankungssystem shown in Fig. 2 has over that in Fig. 1 to a supercharger 2, which is connected to the Ent.c réelle 1.
- a pipeline 3 leads to the series-connected compressor stages 10a, 10b, 10c, 10d.
- a check valve IIa, IIb, 11c is arranged in the pipeline 3.
- the last compressor stage 10d is not equipped with a check valve.
- an inlet line 12a, 12b, 12c leads to the following compressor stage.
- the outlet of the compressor stage is connected via a removal line 13a, 13b, 13c to the inlet of a vortex tube 20a, 20b, 20c.
- a pressure line 4 leads to an expansion turbine 5.
- the gas flow experiences a temperature decrease after the last compressor stage 10d, before the gas is introduced into the pressure vessel 7.
- the three-way valve 101 is set so that the pressure line 6a, 6b is continuously connected.
- the gas flow in the expansion turbine 5 mechanical work is taken, which is used to drive the supercharger 2.
- the expansion turbine 5 drives the supercharger 2.
- the gas compressed in the supercharger 2 is supplied through the pipe 3 to the first compressor stage 10a via the inlet pipe 12a provided with the check valve IIa.
- the after the countercurrent process working vortex raw rc 20a, 20b, 20c are connected via the extraction lines 13a, 13b, 13c to the compressor stages 10a, 10b, 10c.
- the gas flow reaches the inlet nozzles, which form the narrowest cross-section 21a, 21b, 21c between the compressor stages.
- the cold gas flow 22a, 22b, 22c of the vortex tubes 20a, 20b, 20c is fed to the following compressor stage via the inlet lines 12b, 12c, 12d and the hot gas flow 23a, 23b, 23c is discharged via the pipelines 24a, 24b, 24c.
- the Drosselstcllen 25a, 25b, 25c located in the pipes 24a, 24b, 24c are used for presetting the mass ratio between the cold gas and hot gas. After the throttle points 25a, 25b, 25c, the hot gas stream 23a, 23b, 23c flows back through the remindle ⁇ tache 26a, 26b, 26c in the same compressor stage, from which the gas was removed.
- Each vortex tube generates from the supplied gas a hot gas flow 23a, 23b, 23c and a cold gas flow 22a, 22b, 22c.
- the hot gas flow 23a, 23b, 23c is returned to the respective compressor stage 10a, 10b, 10c.
- the cold gas flow 22a, 22b, 22c is fed to the next following compressor stage.
- the check valves I Ia, IIb, l lc prevent jerkgeschreibtes gas from entering the cold gas outlet of the previous vortex tube
- the check valves 27a, 27b, 27c is avoided that the cold gas of the previous vortex tube does not get into the return line of the hot gas of the subsequent vortex tube.
- the closed gas circuit can be designed in accordance with that described in FIG. 1, in order to oppose the temperature measuring point 100 when the gas temperature is exceeded to initiate a temperature reduction of the gas at a predetermined reference temperature.
- Fig. 3 differs from that of Fig. 2 in that the hot gas flow 23a, 23b, 23c of the vortex tubes is supplied to a respective return line 26b, 26c, 26d leading to the inlet line 12a, 12b, 12c of the compressor stage 10a , 10b, 10c.
- the return flow lines 26a, 26b, 26c each include a gas cooler 30a, 30b, 30c for removing heat from the gas.
- a throttle point 25a, 25b, 25c is installed in the return flow line.
- the gas coolers 30a, 30b, 30c are water-cooled heat exchangers.
- the water is conveyed by a driven by the expansion turbine 5 circulating pump 8 in forced circulation via a line 31 to the gas coolers 30a, 30b, 30c, which are connected in parallel to corresponding supply lines 31a, 31b, 31c.
- the cooling medium flows in return lines 32a, 32b, 32c, which merge in a collecting pressure line 32.
- the collecting return line 32 leads to a heat exchanger 33.
- the cooling medium which acts as a heat carrier, transfers its heat absorbed in the gas coolers to a second heat carrier medium, which is supplied in an inlet 34-1 of the secondary circuit and through a drain 34-2 exits the heat exchanger.
- the conveyed in the secondary circuit heat transfer medium can be service water and / or heating water for a building brook. Mach exit from the heat exchanger 33 passes through the conveyed in the primary circuit heat transfer medium via a pipe 35 back to the suction side of the circulation pump eighth
- a vortex tube is used, which operates without gas separation.
- the gas taken from the extraction line 1 is brought to a higher pressure level in a supercharger 2, which is driven by the expansion turbine 5.
- a supercharger 2 which is driven by the expansion turbine 5.
- the precompressed gas is supplied to the inlet pipe 12a of the first compressor stage 10a of the high pressure compressor. After compression in the first compressor stage 10a, the gas passes through the removal line 13a for lowering the gas temperature in the Wbolrbolrohr 40a.
- the vortex tubes 40a, 40b, 40c are connected to the compressor stages 10a, 10b, 10c via the extraction lines 13a, 13b, 13c.
- the gas flow reaches the inflow nozzles, which form the narrowest cross-section 41a, 41b, 41c between two compressor stages. From the inflow nozzles, the gas passes at the speed of sound as a swirling flow into the central tube of the vortex tubes 40a, 40b, 40c, which are closed at one end 43a, 43b, 43c.
- the vortex tubes 40a, 40b, 40c are equipped with water chillers 44a, 44b, 44c, which surround the central tube of the vortex tubes 40a, 40b, 40c and are used in countercurrent for cooling the tube outer wall.
- the primary and secondary circuits can be designed in accordance with the cooling circuit described in FIG.
- the last compressor stage 10d is supplied with the gas via the inlet line 12d.
- the gas flow after the compressor stage 1Od undergoes a further decrease in temperature before the gas is introduced into the compressed gas tank 7.
- mechanical work is taken from the gas flow in the expansion turbine 5, which is used to drive the supercharger 2 and the circulating pump 8.
- the device for lowering the temperature shown in FIGS. 5 and 6 has a supply pipe 101 coming from a storage container, which leads to a swirl generator 102. Its functionally essential parts consist of an annular collecting space 103, are directed by the tangential Einströmdusen 104 inward and drove into the end of a Wirbeirohres 105. At the end of the vortex tube 105 is followed in the opposite direction to a pipe section 106, which is connected to a leading to the (not shown) compressed gas tank full pipe 107. The inner diameter of the tube section 106 is significantly smaller than that of the vortex tube 105.
- the rotating vortex flow 121 generated in the swirl generator 102 flows into the vortex tube to move away from the swirl generator 102 (to the left as viewed in FIG. 1).
- the throttle point with the narrowest flow-through cross section between the reservoir and the pressure gas container to be filled is formed by the Einströmdusen 104 of the swirl generator 102. From the inflow nozzles 104, the gas passes into the vortex tube 105 at almost sound velocity as a rotating drain flow 121.
- a cooling device 130 is arranged around the vortex tube 105.
- the vortex tube 105 is provided with a swirl brake 109.
- This consists of a piston 110 which is arranged in the vortex tube and seals it in a sealing manner and which is axially adjustable.
- a spindle 111 To adjust the piston 110 is a spindle 111, which can be rotated by hand.
- the swirl flow 121 is decelerated at the closure 110, so that, for reasons of continuity in the axial direction, a back-flowing core flow along a flow path 122, which flows in the opposite direction to the swirl flow 121, is produced.
- the flow path 122 extends coaxially within the swirl flow 121.
- the pressure difference between inner and outer flow in the vortex tube 105 has the effect that the core flow flowing along the inner flow path 122 flows through the tube section 106 into the fill tube 107 that is to be filled with the Compressed gas tank is connected.
- FIG. 6 shows the flow of the gas in the device, wherein the gas supply takes place through the feed tube 101 in the direction of the arrows 120. From here the gas passes, z. As natural gas, via the plenum 103 and the inlet nozzles 104 of the swirl generator 102 at supercritical pressure ratio with the speed of sound in the vortex tube 105. There, formed with the help of the swirl generator 102 generated in the swirl rotational flow 121 from. This rotational flow is slowed down so far on the solid bottom of the vortex tube closed by the closure 110 near the wall due to the failure of the centrifugal forces, that forms a running in the opposite direction core flow 122. The latter is then supplied via the pipe section 106 to the compressed gas container.
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- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Mechanical Engineering (AREA)
- Thermal Sciences (AREA)
- General Engineering & Computer Science (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
Abstract
Description
Claims
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US11/577,629 US20070248472A1 (en) | 2004-10-21 | 2005-10-14 | Device for Generating Highly Compressed Gas |
CA002583651A CA2583651A1 (en) | 2004-10-21 | 2005-10-14 | Device for generating highly compressed gas |
EP05799389A EP1802910A1 (de) | 2004-10-21 | 2005-10-14 | Vorrichtung zur erzeugung von hochkomprimiertem gas |
Applications Claiming Priority (8)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102004051189 | 2004-10-21 | ||
DE102004051191.8 | 2004-10-21 | ||
DE102004051189.6 | 2004-10-21 | ||
DE102004051191 | 2004-10-21 | ||
DE102005006751.4 | 2005-02-15 | ||
DE102005006751A DE102005006751B9 (de) | 2004-10-21 | 2005-02-15 | Vorrichtung zur Temperaturabsenkung eines Gases |
DE102005016114.6 | 2005-04-08 | ||
DE102005016114A DE102005016114A1 (de) | 2004-10-21 | 2005-04-08 | Vorrichtung zur Erzeugung von hochkomprimiertem Gas |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2006045712A1 true WO2006045712A1 (de) | 2006-05-04 |
Family
ID=35613763
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/EP2005/055278 WO2006045712A1 (de) | 2004-10-21 | 2005-10-14 | Vorrichtung zur erzeugung von hochkomprimiertem gas |
Country Status (4)
Country | Link |
---|---|
US (1) | US20070248472A1 (de) |
EP (1) | EP1802910A1 (de) |
CA (1) | CA2583651A1 (de) |
WO (1) | WO2006045712A1 (de) |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102006047313A1 (de) * | 2006-10-06 | 2008-04-10 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Vorrichtung zum schnellen Befüllen von Druckgasbehältern |
WO2011031576A1 (en) * | 2009-09-08 | 2011-03-17 | Questar Gas Company | Methods and systems for reducing pressure of natural gas and methods and systems of delivering natural gas |
WO2012123349A1 (en) * | 2011-03-11 | 2012-09-20 | Shell Internationale Research Maatschappij B.V. | Hydrogen dispensing process and system |
US8833088B2 (en) | 2009-09-08 | 2014-09-16 | Questar Gas Company | Methods and systems for reducing pressure of natural gas and methods and systems of delivering natural gas |
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Publication number | Priority date | Publication date | Assignee | Title |
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US20130019753A1 (en) * | 2011-07-19 | 2013-01-24 | Cornel Gleason | System and Method for Separation of Captured Gases from Exhaust |
KR101520858B1 (ko) * | 2013-11-08 | 2015-05-18 | 충남대학교산학협력단 | 다단 압축 장치 |
KR101683715B1 (ko) * | 2015-07-22 | 2016-12-09 | 충남대학교산학협력단 | 수소 충전기용 프리쿨러 |
CN109373627B (zh) * | 2018-09-28 | 2021-05-04 | 内蒙古科技大学 | 一种热端管长度可调节的轴向排气涡流管 |
CN117663680B (zh) * | 2023-12-16 | 2024-08-23 | 江苏永诚装备科技有限公司 | 一种带有预冷结构的船舶天然气液化装置 |
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DE102006047313A1 (de) * | 2006-10-06 | 2008-04-10 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Vorrichtung zum schnellen Befüllen von Druckgasbehältern |
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WO2011031576A1 (en) * | 2009-09-08 | 2011-03-17 | Questar Gas Company | Methods and systems for reducing pressure of natural gas and methods and systems of delivering natural gas |
US8613201B2 (en) | 2009-09-08 | 2013-12-24 | Questar Gas Company | Methods and systems for reducing pressure of natural gas and methods and systems of delivering natural gas |
US8833088B2 (en) | 2009-09-08 | 2014-09-16 | Questar Gas Company | Methods and systems for reducing pressure of natural gas and methods and systems of delivering natural gas |
WO2012123349A1 (en) * | 2011-03-11 | 2012-09-20 | Shell Internationale Research Maatschappij B.V. | Hydrogen dispensing process and system |
US20140110017A1 (en) * | 2011-03-11 | 2014-04-24 | Nikunj Gupta | Hydrogen dispensing process and system |
US9458968B2 (en) | 2011-03-11 | 2016-10-04 | Shell Oil Company | Hydrogen dispensing process and system |
Also Published As
Publication number | Publication date |
---|---|
EP1802910A1 (de) | 2007-07-04 |
US20070248472A1 (en) | 2007-10-25 |
CA2583651A1 (en) | 2006-05-04 |
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