EP3877693A1 - A cryogenic fuel tank - Google Patents

A cryogenic fuel tank

Info

Publication number
EP3877693A1
EP3877693A1 EP18799756.4A EP18799756A EP3877693A1 EP 3877693 A1 EP3877693 A1 EP 3877693A1 EP 18799756 A EP18799756 A EP 18799756A EP 3877693 A1 EP3877693 A1 EP 3877693A1
Authority
EP
European Patent Office
Prior art keywords
fuel tank
guide pipe
instrument guide
tank
section
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
EP18799756.4A
Other languages
German (de)
French (fr)
Inventor
Andreas SNELLMAN
Rasmus NYBO
Ingvar ÖST
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Wartsila Finland Oy
Original Assignee
Wartsila Finland Oy
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Wartsila Finland Oy filed Critical Wartsila Finland Oy
Publication of EP3877693A1 publication Critical patent/EP3877693A1/en
Pending legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C13/00—Details of vessels or of the filling or discharging of vessels
    • F17C13/02—Special adaptations of indicating, measuring, or monitoring equipment
    • F17C13/021—Special adaptations of indicating, measuring, or monitoring equipment having the height as the parameter
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C13/00—Details of vessels or of the filling or discharging of vessels
    • F17C13/02—Special adaptations of indicating, measuring, or monitoring equipment
    • F17C13/026—Special adaptations of indicating, measuring, or monitoring equipment having the temperature as the parameter
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C2201/00—Vessel construction, in particular geometry, arrangement or size
    • F17C2201/01—Shape
    • F17C2201/0104—Shape cylindrical
    • F17C2201/0109—Shape cylindrical with exteriorly curved end-piece
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C2201/00—Vessel construction, in particular geometry, arrangement or size
    • F17C2201/03—Orientation
    • F17C2201/035—Orientation with substantially horizontal main axis
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C2201/00—Vessel construction, in particular geometry, arrangement or size
    • F17C2201/05—Size
    • F17C2201/054—Size medium (>1 m3)
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C2203/00—Vessel construction, in particular walls or details thereof
    • F17C2203/03—Thermal insulations
    • F17C2203/0304—Thermal insulations by solid means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C2203/00—Vessel construction, in particular walls or details thereof
    • F17C2203/03—Thermal insulations
    • F17C2203/0391—Thermal insulations by vacuum
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C2203/00—Vessel construction, in particular walls or details thereof
    • F17C2203/06—Materials for walls or layers thereof; Properties or structures of walls or their materials
    • F17C2203/0602—Wall structures; Special features thereof
    • F17C2203/0612—Wall structures
    • F17C2203/0626—Multiple walls
    • F17C2203/0629—Two walls
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C2203/00—Vessel construction, in particular walls or details thereof
    • F17C2203/06—Materials for walls or layers thereof; Properties or structures of walls or their materials
    • F17C2203/0634—Materials for walls or layers thereof
    • F17C2203/0636—Metals
    • F17C2203/0639—Steels
    • F17C2203/0643—Stainless steels
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C2205/00—Vessel construction, in particular mounting arrangements, attachments or identifications means
    • F17C2205/01—Mounting arrangements
    • F17C2205/0153—Details of mounting arrangements
    • F17C2205/0176—Details of mounting arrangements with ventilation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C2205/00—Vessel construction, in particular mounting arrangements, attachments or identifications means
    • F17C2205/01—Mounting arrangements
    • F17C2205/0153—Details of mounting arrangements
    • F17C2205/018—Supporting feet
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C2205/00—Vessel construction, in particular mounting arrangements, attachments or identifications means
    • F17C2205/03—Fluid connections, filters, valves, closure means or other attachments
    • F17C2205/0302—Fittings, valves, filters, or components in connection with the gas storage device
    • F17C2205/0352—Pipes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C2221/00—Handled fluid, in particular type of fluid
    • F17C2221/03—Mixtures
    • F17C2221/032—Hydrocarbons
    • F17C2221/033—Methane, e.g. natural gas, CNG, LNG, GNL, GNC, PLNG
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C2223/00—Handled fluid before transfer, i.e. state of fluid when stored in the vessel or before transfer from the vessel
    • F17C2223/01—Handled fluid before transfer, i.e. state of fluid when stored in the vessel or before transfer from the vessel characterised by the phase
    • F17C2223/0146—Two-phase
    • F17C2223/0153—Liquefied gas, e.g. LPG, GPL
    • F17C2223/0161—Liquefied gas, e.g. LPG, GPL cryogenic, e.g. LNG, GNL, PLNG
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C2223/00—Handled fluid before transfer, i.e. state of fluid when stored in the vessel or before transfer from the vessel
    • F17C2223/03—Handled fluid before transfer, i.e. state of fluid when stored in the vessel or before transfer from the vessel characterised by the pressure level
    • F17C2223/033—Small pressure, e.g. for liquefied gas
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C2250/00—Accessories; Control means; Indicating, measuring or monitoring of parameters
    • F17C2250/04—Indicating or measuring of parameters as input values
    • F17C2250/0404—Parameters indicated or measured
    • F17C2250/0408—Level of content in the vessel
    • F17C2250/0413—Level of content in the vessel with floats
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C2250/00—Accessories; Control means; Indicating, measuring or monitoring of parameters
    • F17C2250/04—Indicating or measuring of parameters as input values
    • F17C2250/0404—Parameters indicated or measured
    • F17C2250/0408—Level of content in the vessel
    • F17C2250/0417—Level of content in the vessel with electrical means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C2250/00—Accessories; Control means; Indicating, measuring or monitoring of parameters
    • F17C2250/04—Indicating or measuring of parameters as input values
    • F17C2250/0404—Parameters indicated or measured
    • F17C2250/0439—Temperature
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C2250/00—Accessories; Control means; Indicating, measuring or monitoring of parameters
    • F17C2250/04—Indicating or measuring of parameters as input values
    • F17C2250/0404—Parameters indicated or measured
    • F17C2250/0447—Composition; Humidity
    • F17C2250/0452—Concentration of a product
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C2250/00—Accessories; Control means; Indicating, measuring or monitoring of parameters
    • F17C2250/04—Indicating or measuring of parameters as input values
    • F17C2250/0404—Parameters indicated or measured
    • F17C2250/0482—Acceleration
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C2250/00—Accessories; Control means; Indicating, measuring or monitoring of parameters
    • F17C2250/04—Indicating or measuring of parameters as input values
    • F17C2250/0486—Indicating or measuring characterised by the location
    • F17C2250/0491—Parameters measured at or inside the vessel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C2250/00—Accessories; Control means; Indicating, measuring or monitoring of parameters
    • F17C2250/04—Indicating or measuring of parameters as input values
    • F17C2250/0486—Indicating or measuring characterised by the location
    • F17C2250/0495—Indicating or measuring characterised by the location the indicated parameter is a converted measured parameter
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C2260/00—Purposes of gas storage and gas handling
    • F17C2260/02—Improving properties related to fluid or fluid transfer
    • F17C2260/024—Improving metering
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C2270/00—Applications
    • F17C2270/01—Applications for fluid transport or storage
    • F17C2270/0102—Applications for fluid transport or storage on or in the water
    • F17C2270/0105—Ships

Definitions

  • a cryogenic fuel tank A cryogenic fuel tank
  • the present invention relates to a cryogenic fuel tank comprising an in- strumentation arrangement to measure and/or record one or more physical quan- tities of the fuel in the fuel tank, the fuel tank comprising an inner shell, an outer shell, in which the inner shell comprise a first cylindrical shell portion and end portions at both ends thereof, and the outer shell comprise a second cylindrical shell portion and end portions at both ends thereof, and an insulation cavity be- tween the inner shell and the outer shell.
  • Invention relates to a field of storing liquefied gas at cryogenic conditions in a pressure proof tank for use in a gas consumer, and instrumentation of the tank in an appropriate manner. By means of such instrumentation it is possible to measure and/or record the physical quantities of the gas in the tank.
  • One of the most interesting quantity is the amount of the gas in the liquid phase, although other quantities may be desired to measure as well.
  • Radar level instruments are known as such which measure the distance from the transmitter/sensor to the surface of a liquid located further below in much the same way as ultrasonic level sensors, by measuring the time-of-flight of a traveling wave and then determine the level of the process material. They are regarded as continuous level measurement devices because they continue to measure level even as the level of the liquid in the vessel changes.
  • the funda- mental difference between a radar level instrument and an ultrasonic level instru- ment is the type of wave used.
  • Radar level instruments use radio waves instead of sound waves used in ultrasonic instruments. Radio waves are electromagnetic in nature, with very high frequency in the microwave frequency range.
  • level radar instruments There are two basic types of level radar instruments: guided-wave radar and non-contact wave radar.
  • Guided-wave radar instruments use wave guide probe to guide the radio waves into the process liquid while non-contact radar instruments send radio waves out through open space to reflect off the process material.
  • the utility model CN206504772U discloses a radar level meter system in which a mounting pipe is provided, which mounting pipe is equipped with a radar level gauge. There is a float in the mounting pipe such that the radar wave reflects from the float improving the measurement accuracy.
  • the distance between the liquid level and the radar level gauge is equal to the reading of the radar level gauge and the thickness of the float. When the liquid level is high the float is pulled below the liquid level so that the float will not collide with the radar antenna.
  • WO2017042424A1 there is shown an LNG-fuel tank, which comprises an inner shell of stainless steel, an outer shell and a cavity 20 there- between with an insulation.
  • WO2017042424A1 there is disclosed a manner of determining the fuel level in the tank using radar-based detector.
  • the LNG-fuel tank is provided with a manhole construction in the cylindrical shell portion of the tank via which the access into the interior of the LNG-fuel tank is made possible.
  • the manhole is provided with means for determining the fuel level in the inner shell of the tank.
  • This kind of arrangement requires a lead through of the wiring through the outer shell which is a potential risk of jeopardizing the tightness of the tank.
  • An object of the invention is to provide a cryogenic fuel tank in which the instrumentation can be obtained in reliable and straightforward manner. Disclosure of the Invention
  • a cryogenic fuel tank comprises an instrumentation arrangement to measure and/or record one or more physical quantities of the fuel in the fuel tank, the fuel tank comprising an inner shell, an outer shell, in which the inner shell comprise a first cylindrical shell portion and end portions at both ends thereof, and the outer shell comprise a second cylin- drical shell portion and end portions at both ends thereof, and an insulation cavity between the inner shell and the outer shell.
  • the cryogenic fuel tank further corn- prising a tank connection space.
  • the instrumentation arrangement comprises an instrument guide pipe, and a measurement system configured to measure and/or record one or more physical quantities of the fuel in the fuel tank, the measurement system being coupled to the instrument guide pipe.
  • the instrument guide pipe is arranged to extend from the tank connection space to the tank space via the insulation cavity.
  • the tank connection space is a space for housing the end of the instru- ment guide pipe and the measurement system coupled to the instrument guide pipe.
  • the Tank connection space is arranged gas tight but also accessible e.g. for maintenance.
  • a first section of the instrument guide pipe is arranged to extend through the end portion of the outer shell, and a second section of the instrument guide pipe is arranged to extend along the insulation cavity between the end portion of the inner shell and the end portion of the outer shell to the insulation cavity between the first cylindrical portion and the second cylindrical portion, and further a third section of the instrument guide pipe is arranged to extend in the insulation cavity between the first cylindrical portion and the second cylindrical portion in longitudinal direction of the cryogenic fuel tank, and a fourth section of the instrument guide pipe arranged to extend into a tank space through the inner shell of the fuel tank.
  • a cryogenic fuel tank comprises an instrumentation arrangement to measure and/or record one or more physical quantities of the fuel in the fuel tank, the fuel tank comprising an inner shell, an outer shell, in which the inner shell comprise a first cylindrical shell portion and end portions at both ends thereof, and the outer shell comprise a second cylin- drical shell portion and end portions at both ends thereof, and an insulation cavity between the inner shell and the outer shell, wherein the instrumentation arrange- ment comprises an instrument guide pipe for a measurement system of one or more physical quantities of the fuel in the fuel tank which instrument guide pipe is arranged to extend from a tank connection space to the tank space via the insulation cavity.
  • the instrument guide pipe por- tion which in the tank space comprises openings in its outer wall.
  • the first cylindrical shell portion is provided with a lead-through, through which the fourth section of the instrument guide pipe is arranged to extend into the tank space, the fourth section of the instrument guide pipe is arranged to extend radially towards the center of the first cylindrical shell portion from the lead-through and further towards the first shell wall which is radially opposite to the lead-through.
  • the fourth section of the instru- ment guide pipe comprises openings in its side wall.
  • the lead-through comprises a radially inwardly extending cup having is rim attached to the inner shell, and wherein the instrument guide pipe is led through a bottom part of the cup.
  • the instrumentation arrange- ment comprises a radar-based measurement system and the fourth section of the instrument guide pipe comprises a float part arranged to reflect radar signal.
  • the instrumentation arrange- ment comprises a flexible temperature measurement probe which is arranged inside the instrument guide pipe.
  • the instrumentation arrange- ment comprises an inertial measurement unit for defining an inclination angle of the fuel tank.
  • the instrumentation arrange- ment comprises a temperature measurement system.
  • the instrumentation arrange- ment comprises a radar-based measurement system and the fourth section of the instrument guide pipe comprises a stationary reference reflector in the pipe.
  • the exemplary embodiments of the invention presented in this patent ap- plication are not to be interpreted to pose limitations to the applicability of the appended claims.
  • the verb "to comprise” is used in this patent application as an open limitation that does not exclude the existence of also unrecited features.
  • the features recited in depending claims are mutually freely combinable unless otherwise explicitly stated.
  • the novel features which are considered as charac- teristic of the invention are set forth in particular in the appended claims.
  • Figure 1 illustrates a cryogenic fuel tank according to an embodiment of the in- vention
  • Figure 2 illustrates a view ll-ll of the figure 1 according to an embodiment of the invention
  • Figure 3 illustrates a view ll-ll of the figure 1 according to another embodiment of the invention
  • FIG. 6 illustrates a cryogenic fuel tank according to another embodiment of the invention
  • Figure 7 illustrates a cryogenic fuel tank according to figure 6 in service stage
  • Figure 8 illustrates a cryogenic fuel tank according to another embodiment of the invention.
  • the insulation cavity 20 may be filled with a suitable insulating material or it may be, as it is the case in the figure 1 , a vacuum insulation space.
  • the inner shell 16 is supported on or to the outer shell 18 by means of supports arranged in the cavity 20.
  • the end portions 16.2 and 18.2 are preferably of dome shape and the inner and outer shells are configured to withhold pressures over 500 kPa.
  • the cryogenic fuel tank 10 as is shown in the figure 1 is provided with a room or space 22 welded to, or by some other appropriate means arranged in gas tight connection with, the outer shell 18 of the tank 10 forming a safety barrier against unintentional gas leak.
  • the space 22, which may be referred to as a tank connection space, is housing also e.g. a piping and instruments needed when filling or emptying the fuel tank 10 not shown here.
  • the tank connection space 22 is arranged in connection with an end portion of the cryogenic tank 10.
  • the cryogenic tank 10 comprises an instru- mentation arrangement 30 for measuring and/or recording one or more physical quantities of the fuel in the cryogenic fuel tank 10.
  • the instrumentation arrange- ment 30 comprises a measurement system 34 for measuring one or more phys- ical quantities of the fuel in the fuel tank and an instrument guide pipe 32 for use by the measurement system 34.
  • the instrument guide pipe 32 is arranged to extend from the tank connection space 22 to the tank space 1 1 via the insulation cavity 20, and further cross the tank space 11 in the first cylindrical shell portion 16.1 , substantially from a wall to a wall.
  • the measurement system 34 comprises its interface for measurements signal(s) and for controls in the tank connection space 22.
  • the tank connection space 22 is normally a gas tight enclosure containing all tank connections, fittings, flanges and tank valves. It is constructed of cryo- genic temperature resistant materials, it has a bilge well with a high level indicator and a low temperature sensor.
  • the tank connection space (TCS) is not normally accessible, it may not be entered by personnel unless checked for sufficient ox- ygen and absence of explosive atmosphere. For safety reasons the TCS is ad- vantageously provided with permanent gas detection, fixed fire detection and mechanical forced ventilation, which changes air at least 30 times an hour.
  • the instrument guide pipe 32 in the figure 1 comprises generally four sec- tions.
  • the first section 32.1 which may be also referred to as a first end of the instrument guide pipe 32 is arranged to extend through the end portion 18.2 of the outer shell 18 from the tank connection space 22 generally in longitudinal direction of the cryogenic fuel tank 10, which is parallel with the longitudinal cen- ter axes A1 , A2.
  • the first section 32.1 has its end in the gas tight tank connection space 22 increasing the safety of the cryogenic fuel tank 10.
  • the second section 32.2 is arranged to extend along the insulation cavity 20 between the end portion 16.2 of the inner shell 16 and the end portion 18.2 of the outer shell 18 at least in radial direction.
  • the second section 32.2 runs towards the radial periphery of the outer shell 18, but since the location of the first section 32.1 does not neces- sarily coincide with the second longitudinal center axis A2, and/or since the first section is not necessarily of straight pipe, as is shown in the figures 1 and 2, the direction need not to be exactly radial, nor straight. Thus, the second section may also be slightly curved.
  • Figure 1 also shows that the second section 32.2 has a longitudinal direction component.
  • the third section 32.3 of the instrument guide pipe 32 is arranged to extend generally in longitudinal direction along the insula- tion cavity 20 between the inner shell 16 and the outer shell 18 over a predeter- mined distance.
  • FIG 3 shows a view ll-ll of the figure 1 according to an another embod- iment of the invention where the cryogenic fuel tank 10 is provided with two sep- arate instrumentation arrangements 30 in order to measure at least two different physical quantities of the fuel in the cryogenic fuel tank 10 having dedicated in- strument guide pipes 32 for each measurement systems.
  • the measurement system 34 coupled to the first end of the instrument guide pipe 32 in the embodiment of figure 1 is a radar-based liquid level meas- urement system 34, or a liquid level indicator.
  • the instrument guide pipe 32 is a waveguide along which the radar waves are transmitted from the radar-based liquid level measurement system 34 and waves are reflected from the liquid surface are transmitted back to the radar-based liquid level meas- urement system 34.
  • the guide pipe 32 serves for guiding radar waves in the pipe.
  • the radar-based liquid level measure- ment system 34 may be provided with an integrated shut-off valve so as to give the possibility to remove the radar device easily if maintenance is needed, even when tank is in operation.
  • the radar-based liquid level measurement system 34 can also have an integrated pressure transmitter which measures the pressure in the gas phase of the tank 10.
  • the fourth section 32.4 is not neces- sarily arranged in a direction of normal of the liquid surface in the tank. If there is an angle between the normal of the liquid surface and fourth section 32.4 of the instrument piping, the actual position of the liquid level can be calculated based on the angle and dimensions of the tank. Also, when the cryogenic fuel tank is installed in a marine vessel it naturally changes its inclination angle along with the vessel which causes short or long term inclination of the of the liquid surface in respect to the longitudinal center axis A1 of the inner shell. According to an embodiment of the invention the cryogenic fuel tank comprises an Inertial Meas- urement Unit (IMU) 38 advantageously mounted in the tank connection space 22.
  • IMU Inertial Meas- urement Unit
  • the I MU uses 3-axis gyroscope, 3-axis accelerometer and 3-axis magnetom- eter to provide an accurate angle and orientation information of the fuel tank unit 10.
  • the distance from the fourth section 32.4 to the longitudinal center of the tank in combination with the angle of the tank can be used to calculate the actual liquid level in the tank since the measurement system 34 is configured use the infor- mation of the inertial measurement unit 38.
  • FIG 4 also shows another embodiment of the invention according to which the instrumentation arrangement 30 comprises a float part 40 which is ar- ranged slideably in the pipe in the fourth section 32.4 of the instrument guide pipe 30.
  • the float part 40 is provided with a surface which facilitate the reflecting of a radar signal from the float part.
  • the surface is advantageously perpendicular to the longitudinal direction of the fourth section 32.4 of the instrument guide pipe 30.
  • the surface of the float part 40 may be for example metal. This way, because the dielectric constant for example of liquefied natural gas is somewhat low (for methane 1.7) the liquid surface would result in weak reflections, and by means of the float part the sensitivity of the radar measurement can be improved giving a clear indication of the liquid surface.
  • the float part 40 is advantageously con- figured to float such that its upper surface is near the surface of the liquid.
  • the fourth section 32.4 of the instrument guide pipe 30 and the float part are config- ured such that the float part 40 may move, by floating along with the liquid level, all the way from one end of the fourth section to another end thereof.
  • Figure 5 discloses two further aspects of the invention.
  • An embodiment of the invention shown in the figure 5 comprises a stationary reference reflector 42 arranged into the fourth section 32.4 of the instrument guide pipe 32 to be used optionally with the radar based liquid level measurement system.
  • the ref- erence reflector 42 may be for example a pin arranged to extend radially into to the pipe 32.
  • the pin 42 extend only partially into the pipe, providing a reflection effect necessary for the radar system to identify the reference reflec- tor.
  • the reference reflector 42 may be obtained also by means of a suitable in- ternal extension in the instrument guide pipe 32 pipe, which may for example an orifice or a pin or a like led through the pipe.
  • the reference reflector Since the reference reflector is at a fixed position it results in a reference signal for the radar to provide accurate liquid level measurement. Since the inner shell may move in relation to the outer shell, and the pipe may bend, at least to some degree, an interference to the reflection time of the radar waves may occur. By means of the stationary refer- ence reflector 42, the interference can be compensated.
  • the stationary reference reflector 42 such as a pin, is advantageously assemble inside the guide pipe 32 at a location were the guide pipe runs through the inner shell 16. The reference reflector 42 will always give a small reflection, which can be used as a reference by the radar to increase the accuracy.
  • FIG. 5 shows also another embodiment of the invention.
  • the first cylin drical portion 16.1 of the inner shell 16 may be provided with a special lead- through 44 for optional use in connection with the instrument guide pipe 32.
  • the lead-through 44 comprises a radially inwardly extending cup 45 which has a rim 46 attached to the inner shell 16.1 of the cryogenic fuel tank 10.
  • the instrument guide pipe 32 is led through a bottom part of the cup.
  • the cup has depth and diameter suitably selected so that it is possible to arrange the bending radius of the angle part between the fourth section 32.4 and the third section 32.2 to be greater while the fourth section 32.4 penetrates the cup perpendicularly to the third section of the instrument guide pipe 32.3 which runs along the insulation cavity 20.
  • FIGs 6 and 7 depict an embodiment of the invention according to which the measurement system 34 coupled to the first end of the instrument guide pipe 32 is a temperature measurement system 34’.
  • the temperature measurement system comprises a flexible probe part and which is provided with several probe elements at different locations of the probe. This way the flexible probe can be inserted into the instrument guide pipe 32 and remove as well. In the figure 6 the flexible probe is fully inserted in to the guide pipe 32 and in the figure 7 the probe is partially removed, for example for service or replacement of the probe. In case the insertion of the probe in the tube is too difficult, a steel wire looping the end of the pipe 32 inside it, can be used to pull the probe in the pipe instead of pushing it.
  • the temperature measurement system 34’ can be used simultaneously to- gether with the liquid level measurement system in the embodiment described in the figure 3.
  • FIG. 8 there is shown an embodiment of the invention which oth- erwise corresponds to that shown in other figures but here the tank connection space 22 is separate to i.e. non-integral with the cryogenic tank 10.
  • the instru- ment guide pipe 32 extends through the end portion 18.2 of the outer shell 18 and into the tank connection space via barrier channel 19.
  • the instrument guide pipe 32 enclosed in gas tight manner by the barrier channel 19 between the end portion 18.2 of the outer shell 18 and the tank connection space 22.
  • the barrier channel 19 may be for example a pipe having diameter greater than the diameter of the instrument guide pipe 32.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Filling Or Discharging Of Gas Storage Vessels (AREA)

Abstract

Invention relates to a cryogenic fuel tank (10) comprising an instrumentation arrangement (30) to measure and/or record one or more physical quantities of the fuel in the fuel tank (10), the fuel tank (10) comprising an inner shell (16), and an outer shell (18), in which the inner shell (16) comprise a first cylindrical shell portion (16.1) and end portions (16.2) at both ends thereof, and the outer shell (18) comprise a second cylindrical shell portion (18.1) and end portions (18.2) at both ends thereof, and an insulation cavity (20) between the inner shell (16) and the outer shell (18), the cryogenic fuel tank (10) further comprising a tank connection space (22). The instrumentation arrangement (30) comprises an instrument guide pipe (32) for a measurement system (34) of one or more physical quantities of the fuel in the fuel tank (10), and a measurement system (34) coupled to the instrument guide pipe (32) wherein the instrument guide pipe (3) is arranged to extend from the tank connection space (22) to the tank space (11) via the insulation cavity (20).

Description

A cryogenic fuel tank
Technical field
[001] The present invention relates to a cryogenic fuel tank comprising an in- strumentation arrangement to measure and/or record one or more physical quan- tities of the fuel in the fuel tank, the fuel tank comprising an inner shell, an outer shell, in which the inner shell comprise a first cylindrical shell portion and end portions at both ends thereof, and the outer shell comprise a second cylindrical shell portion and end portions at both ends thereof, and an insulation cavity be- tween the inner shell and the outer shell.
Background art
[002] Invention relates to a field of storing liquefied gas at cryogenic conditions in a pressure proof tank for use in a gas consumer, and instrumentation of the tank in an appropriate manner. By means of such instrumentation it is possible to measure and/or record the physical quantities of the gas in the tank. One of the most interesting quantity is the amount of the gas in the liquid phase, although other quantities may be desired to measure as well.
[003] Radar level instruments are known as such which measure the distance from the transmitter/sensor to the surface of a liquid located further below in much the same way as ultrasonic level sensors, by measuring the time-of-flight of a traveling wave and then determine the level of the process material. They are regarded as continuous level measurement devices because they continue to measure level even as the level of the liquid in the vessel changes. The funda- mental difference between a radar level instrument and an ultrasonic level instru- ment is the type of wave used. Radar level instruments use radio waves instead of sound waves used in ultrasonic instruments. Radio waves are electromagnetic in nature, with very high frequency in the microwave frequency range.
[004] There are two basic types of level radar instruments: guided-wave radar and non-contact wave radar. Guided-wave radar instruments use wave guide probe to guide the radio waves into the process liquid while non-contact radar instruments send radio waves out through open space to reflect off the process material.
[005] In the utility model CN207379583U there is disclosed a non-contact radar level gauge system for confirming packing material level of article in storage tank.
[006] The utility model CN206504772U discloses a radar level meter system in which a mounting pipe is provided, which mounting pipe is equipped with a radar level gauge. There is a float in the mounting pipe such that the radar wave reflects from the float improving the measurement accuracy. The distance between the liquid level and the radar level gauge is equal to the reading of the radar level gauge and the thickness of the float. When the liquid level is high the float is pulled below the liquid level so that the float will not collide with the radar antenna.
[007] Since that invention concerns a fuel tank, operational safety is an ex tremely important aspect in handing easily flammable fuel, and in that respect, use of a double wall arrangement in a liquefied gas tank is known as such.
[008] In publication WO2017042424A1 there is shown an LNG-fuel tank, which comprises an inner shell of stainless steel, an outer shell and a cavity 20 there- between with an insulation. In WO2017042424A1 there is disclosed a manner of determining the fuel level in the tank using radar-based detector. For that purpose the LNG-fuel tank is provided with a manhole construction in the cylindrical shell portion of the tank via which the access into the interior of the LNG-fuel tank is made possible. The manhole is provided with means for determining the fuel level in the inner shell of the tank. This kind of arrangement requires a lead through of the wiring through the outer shell which is a potential risk of jeopardizing the tightness of the tank.
[009] An object of the invention is to provide a cryogenic fuel tank in which the instrumentation can be obtained in reliable and straightforward manner. Disclosure of the Invention
[0010] Objects of the invention can be met substantially as is disclosed in the independent claim and in the other claims describing more details of different embodiments of the invention. [0011] According to an embodiment of invention a cryogenic fuel tank comprises an instrumentation arrangement to measure and/or record one or more physical quantities of the fuel in the fuel tank, the fuel tank comprising an inner shell, an outer shell, in which the inner shell comprise a first cylindrical shell portion and end portions at both ends thereof, and the outer shell comprise a second cylin- drical shell portion and end portions at both ends thereof, and an insulation cavity between the inner shell and the outer shell. The cryogenic fuel tank further corn- prising a tank connection space. The instrumentation arrangement comprises an instrument guide pipe, and a measurement system configured to measure and/or record one or more physical quantities of the fuel in the fuel tank, the measurement system being coupled to the instrument guide pipe. The instrument guide pipe is arranged to extend from the tank connection space to the tank space via the insulation cavity.
[0012] The tank connection space is a space for housing the end of the instru- ment guide pipe and the measurement system coupled to the instrument guide pipe. The Tank connection space is arranged gas tight but also accessible e.g. for maintenance.
[0013] According to an embodiment of invention the instrument guide pipe is ar- ranged to extend through the end portion of the outer shell to the insulation cavity and the instrument guide pipe arranged to further extend from the insulation cav- ity into a tank space through the first cylindrical portion of the inner shell of the fuel tank.
[0014] According to an embodiment of invention a first section of the instrument guide pipe is arranged to extend through the end portion of the outer shell, and a second section of the instrument guide pipe is arranged to extend along the insulation cavity between the end portion of the inner shell and the end portion of the outer shell to the insulation cavity between the first cylindrical portion and the second cylindrical portion, and further a third section of the instrument guide pipe is arranged to extend in the insulation cavity between the first cylindrical portion and the second cylindrical portion in longitudinal direction of the cryogenic fuel tank, and a fourth section of the instrument guide pipe arranged to extend into a tank space through the inner shell of the fuel tank.
[0015] According to an embodiment of invention a cryogenic fuel tank comprises an instrumentation arrangement to measure and/or record one or more physical quantities of the fuel in the fuel tank, the fuel tank comprising an inner shell, an outer shell, in which the inner shell comprise a first cylindrical shell portion and end portions at both ends thereof, and the outer shell comprise a second cylin- drical shell portion and end portions at both ends thereof, and an insulation cavity between the inner shell and the outer shell, wherein the instrumentation arrange- ment comprises an instrument guide pipe for a measurement system of one or more physical quantities of the fuel in the fuel tank which instrument guide pipe is arranged to extend from a tank connection space to the tank space via the insulation cavity.
[0016] According to an embodiment of invention the instrument guide pipe por- tion which in the tank space comprises openings in its outer wall.
[0017] According to an embodiment of invention the first cylindrical shell portion is provided with a lead-through, through which the fourth section of the instrument guide pipe is arranged to extend into the tank space, the fourth section of the instrument guide pipe is arranged to extend radially towards the center of the first cylindrical shell portion from the lead-through and further towards the first shell wall which is radially opposite to the lead-through. [0018] According to an embodiment of invention the fourth section of the instru- ment guide pipe comprises openings in its side wall.
[0019] According to an embodiment of invention the lead-through comprises a radially inwardly extending cup having is rim attached to the inner shell, and wherein the instrument guide pipe is led through a bottom part of the cup. [0020] According to an embodiment of invention the instrumentation arrange- ment comprises a radar-based measurement system and the fourth section of the instrument guide pipe comprises a float part arranged to reflect radar signal.
[0021] According to an embodiment of invention the instrumentation arrange- ment comprises a flexible temperature measurement probe which is arranged inside the instrument guide pipe.
[0022] According to an embodiment of invention the instrumentation arrange- ment comprises an inertial measurement unit for defining an inclination angle of the fuel tank. [0023] According to an embodiment of invention the instrumentation arrange- ment comprises a temperature measurement system.
[0024] According to an embodiment of invention the instrumentation arrange- ment comprises a radar-based measurement system and the fourth section of the instrument guide pipe comprises a stationary reference reflector in the pipe. [0025] The exemplary embodiments of the invention presented in this patent ap- plication are not to be interpreted to pose limitations to the applicability of the appended claims. The verb "to comprise" is used in this patent application as an open limitation that does not exclude the existence of also unrecited features. The features recited in depending claims are mutually freely combinable unless otherwise explicitly stated. The novel features which are considered as charac- teristic of the invention are set forth in particular in the appended claims.
Brief Description of Drawings
[0026] In the following, the invention will be described with reference to the ac- companying exemplary, schematic drawings, in which
Figure 1 illustrates a cryogenic fuel tank according to an embodiment of the in- vention,
Figure 2 illustrates a view ll-ll of the figure 1 according to an embodiment of the invention, Figure 3 illustrates a view ll-ll of the figure 1 according to another embodiment of the invention,
Figure 4 illustrates a further embodiment of the invention,
Figure 5 illustrates still further embodiments of the invention,
Figure 5 illustrates still further embodiments of the invention,
Figure 6 illustrates a cryogenic fuel tank according to another embodiment of the invention,
Figure 7 illustrates a cryogenic fuel tank according to figure 6 in service stage and
Figure 8 illustrates a cryogenic fuel tank according to another embodiment of the invention.
Detailed Description of Drawings
[0027] Figure 1 illustrates a cryogenic fuel tank 10 arranged on a deck 12 of a marine vessel and Figure 2 shows a view ll-ll of the figure 1 according to an embodiment of the invention. The cryogenic fuel tank may serve, for example, as a liquefied natural gas fuel tank in accordance with a preferred embodiment of the present invention. The cryogenic fuel tank 10 is supported by means of sad- dles 14 on the deck 12. The cryogenic fuel tank 10 comprises an inner shell 16, which is of stainless steel to endure the circumstances in the tank. The tank space 11 within the inner shell forms the fuel storage space. The cryogenic fuel tank 10 comprises also an outer shell 18, which is also of stainless steel. The inner shell 16 comprise a first cylindrical shell portion 16.1 having a first longitu dinal center axis A1 and end portions 16.2 at both ends thereof, and the outer shell 18 comprise a second cylindrical shell portion 18.1 having a second longi- tudinal center axis A2 and respectively end portions 18.2 at both ends thereof. In the figure 1 the first and the second longitudinal axis coincide with each other, but that is only an optional feature. The longitudinal axes are parallel to the deck 12 i.e. substantially horizontally oriented. There is an insulation cavity 20 be- tween the inner shell 16 and the outer shell 18 which encloses the inner shell. The insulation cavity 20 may be filled with a suitable insulating material or it may be, as it is the case in the figure 1 , a vacuum insulation space. The inner shell 16 is supported on or to the outer shell 18 by means of supports arranged in the cavity 20. The end portions 16.2 and 18.2 are preferably of dome shape and the inner and outer shells are configured to withhold pressures over 500 kPa.
[0028] The cryogenic fuel tank 10 as is shown in the figure 1 is provided with a room or space 22 welded to, or by some other appropriate means arranged in gas tight connection with, the outer shell 18 of the tank 10 forming a safety barrier against unintentional gas leak. The space 22, which may be referred to as a tank connection space, is housing also e.g. a piping and instruments needed when filling or emptying the fuel tank 10 not shown here. The tank connection space 22 is arranged in connection with an end portion of the cryogenic tank 10.
[0029] The cryogenic tank 10 according to the invention comprises an instru- mentation arrangement 30 for measuring and/or recording one or more physical quantities of the fuel in the cryogenic fuel tank 10. The instrumentation arrange- ment 30 comprises a measurement system 34 for measuring one or more phys- ical quantities of the fuel in the fuel tank and an instrument guide pipe 32 for use by the measurement system 34. The instrument guide pipe 32 is arranged to extend from the tank connection space 22 to the tank space 1 1 via the insulation cavity 20, and further cross the tank space 11 in the first cylindrical shell portion 16.1 , substantially from a wall to a wall. The measurement system 34 comprises its interface for measurements signal(s) and for controls in the tank connection space 22.
[0030] The tank connection space 22 is normally a gas tight enclosure containing all tank connections, fittings, flanges and tank valves. It is constructed of cryo- genic temperature resistant materials, it has a bilge well with a high level indicator and a low temperature sensor. The tank connection space (TCS) is not normally accessible, it may not be entered by personnel unless checked for sufficient ox- ygen and absence of explosive atmosphere. For safety reasons the TCS is ad- vantageously provided with permanent gas detection, fixed fire detection and mechanical forced ventilation, which changes air at least 30 times an hour.
[0031 ] The instrument guide pipe 32 in the figure 1 comprises generally four sec- tions. The first section 32.1 , which may be also referred to as a first end of the instrument guide pipe 32 is arranged to extend through the end portion 18.2 of the outer shell 18 from the tank connection space 22 generally in longitudinal direction of the cryogenic fuel tank 10, which is parallel with the longitudinal cen- ter axes A1 , A2. The first section 32.1 has its end in the gas tight tank connection space 22 increasing the safety of the cryogenic fuel tank 10. The second section 32.2 is arranged to extend along the insulation cavity 20 between the end portion 16.2 of the inner shell 16 and the end portion 18.2 of the outer shell 18 at least in radial direction. The second section 32.2 runs towards the radial periphery of the outer shell 18, but since the location of the first section 32.1 does not neces- sarily coincide with the second longitudinal center axis A2, and/or since the first section is not necessarily of straight pipe, as is shown in the figures 1 and 2, the direction need not to be exactly radial, nor straight. Thus, the second section may also be slightly curved. Figure 1 also shows that the second section 32.2 has a longitudinal direction component. The third section 32.3 of the instrument guide pipe 32 is arranged to extend generally in longitudinal direction along the insula- tion cavity 20 between the inner shell 16 and the outer shell 18 over a predeter- mined distance. The fourth section 32.4 of the instrument guide pipe 32 is ar- ranged to extend into the fuel tank in substantially radial direction. The fourth section 32.4 of the instrument guide pipe 32 extends preferably from a wall to a wall through the tank space 1 1. The fourth section 32.4 and the third section 32.3 are advantageously substantially perpendicular to each other. The first, the sec- ond, the third and the fourth sections are arranged so as to provide a compensa- tion to any thermal expansion of the instrument guide pipe 32, the inner shell 16 and/or the outer shell 18. The instrument guide pipe 32 comprise angle parts between the first, the second, the third and the fourth sections, such that the instrument guide pipe 32 may bend without damages while the inner and outer shells move in respect with each other due to changes of temperature.
[0032] Figure 3 shows a view ll-ll of the figure 1 according to an another embod- iment of the invention where the cryogenic fuel tank 10 is provided with two sep- arate instrumentation arrangements 30 in order to measure at least two different physical quantities of the fuel in the cryogenic fuel tank 10 having dedicated in- strument guide pipes 32 for each measurement systems.
[0033] The measurement system 34 coupled to the first end of the instrument guide pipe 32 in the embodiment of figure 1 is a radar-based liquid level meas- urement system 34, or a liquid level indicator. In this embodiment the instrument guide pipe 32 is a waveguide along which the radar waves are transmitted from the radar-based liquid level measurement system 34 and waves are reflected from the liquid surface are transmitted back to the radar-based liquid level meas- urement system 34. Thus, the guide pipe 32 serves for guiding radar waves in the pipe. Even if not shown in the figure, the radar-based liquid level measure- ment system 34 may be provided with an integrated shut-off valve so as to give the possibility to remove the radar device easily if maintenance is needed, even when tank is in operation. The radar-based liquid level measurement system 34 can also have an integrated pressure transmitter which measures the pressure in the gas phase of the tank 10.
[0034] Figure 4 illustrates a feature relating to the fourth section 32.4 of the in- strument pipe according to which the pipe is provided with several openings 36 through the wall of the pipe. In other words, the instrument guide pipe portion which in the tank space 11 comprises openings 36 in its outer wall. The openings 36 are substantially evenly distributed over the length of the fourth section. This provides an effect of allowing the gaseous gas to flow in to or out from the pipe when the horizontal level of the liquefied fuel gas in the cryogenic fuel tank rises or lowers. Equalizing the pressure in and outside the instrument guide pipe 32 allows the liquid surface level inside the fourth section of the guide pipe 32.4 to follow the liquid surface level in the tank. By means of properly dimensioning the openings 36 it is also possible to even out sudden changes of the surface level in the pipe.
[0035] Even if it is advantageous as such, the fourth section 32.4 is not neces- sarily arranged in a direction of normal of the liquid surface in the tank. If there is an angle between the normal of the liquid surface and fourth section 32.4 of the instrument piping, the actual position of the liquid level can be calculated based on the angle and dimensions of the tank. Also, when the cryogenic fuel tank is installed in a marine vessel it naturally changes its inclination angle along with the vessel which causes short or long term inclination of the of the liquid surface in respect to the longitudinal center axis A1 of the inner shell. According to an embodiment of the invention the cryogenic fuel tank comprises an Inertial Meas- urement Unit (IMU) 38 advantageously mounted in the tank connection space 22. The I MU uses 3-axis gyroscope, 3-axis accelerometer and 3-axis magnetom- eter to provide an accurate angle and orientation information of the fuel tank unit 10. The distance from the fourth section 32.4 to the longitudinal center of the tank in combination with the angle of the tank can be used to calculate the actual liquid level in the tank since the measurement system 34 is configured use the infor- mation of the inertial measurement unit 38.
[0036] Figure 4 also shows another embodiment of the invention according to which the instrumentation arrangement 30 comprises a float part 40 which is ar- ranged slideably in the pipe in the fourth section 32.4 of the instrument guide pipe 30. The float part 40 is provided with a surface which facilitate the reflecting of a radar signal from the float part. The surface is advantageously perpendicular to the longitudinal direction of the fourth section 32.4 of the instrument guide pipe 30. The surface of the float part 40 may be for example metal. This way, because the dielectric constant for example of liquefied natural gas is somewhat low (for methane 1.7) the liquid surface would result in weak reflections, and by means of the float part the sensitivity of the radar measurement can be improved giving a clear indication of the liquid surface. The float part 40 is advantageously con- figured to float such that its upper surface is near the surface of the liquid. The fourth section 32.4 of the instrument guide pipe 30 and the float part are config- ured such that the float part 40 may move, by floating along with the liquid level, all the way from one end of the fourth section to another end thereof.
[0037] Figure 5 discloses two further aspects of the invention. An embodiment of the invention shown in the figure 5 comprises a stationary reference reflector 42 arranged into the fourth section 32.4 of the instrument guide pipe 32 to be used optionally with the radar based liquid level measurement system. The ref- erence reflector 42 may be for example a pin arranged to extend radially into to the pipe 32. In the figure 5 the pin 42 extend only partially into the pipe, providing a reflection effect necessary for the radar system to identify the reference reflec- tor. The reference reflector 42 may be obtained also by means of a suitable in- ternal extension in the instrument guide pipe 32 pipe, which may for example an orifice or a pin or a like led through the pipe. Since the reference reflector is at a fixed position it results in a reference signal for the radar to provide accurate liquid level measurement. Since the inner shell may move in relation to the outer shell, and the pipe may bend, at least to some degree, an interference to the reflection time of the radar waves may occur. By means of the stationary refer- ence reflector 42, the interference can be compensated. The stationary reference reflector 42, such as a pin, is advantageously assemble inside the guide pipe 32 at a location were the guide pipe runs through the inner shell 16. The reference reflector 42 will always give a small reflection, which can be used as a reference by the radar to increase the accuracy.
[0038] Instead of being a radar-based measurement system, the measurement system 34 coupled to the instrument guide pipe 32 in the embodiment of figure 1 may be an ultrasonic liquid level measurement system 34. Ultrasonic liquid level measurement system can be used in connection with similar instrument guide pipe 32 as the radar-based liquid level measurement system. The reference re- flector mounted inside the pipe 32 can be used to continually calibrate the sensor to compensate for the change in velocity of acoustic waves when the temperature changes. The ultrasonic device could also be used to indirectly measure temper- ature in gas.
[0039] Figure 5 shows also another embodiment of the invention. The first cylin drical portion 16.1 of the inner shell 16 may be provided with a special lead- through 44 for optional use in connection with the instrument guide pipe 32. The lead-through 44 comprises a radially inwardly extending cup 45 which has a rim 46 attached to the inner shell 16.1 of the cryogenic fuel tank 10. The instrument guide pipe 32 is led through a bottom part of the cup. The cup has depth and diameter suitably selected so that it is possible to arrange the bending radius of the angle part between the fourth section 32.4 and the third section 32.2 to be greater while the fourth section 32.4 penetrates the cup perpendicularly to the third section of the instrument guide pipe 32.3 which runs along the insulation cavity 20.
[0040] Figures 6 and 7 depict an embodiment of the invention according to which the measurement system 34 coupled to the first end of the instrument guide pipe 32 is a temperature measurement system 34’. The temperature measurement system comprises a flexible probe part and which is provided with several probe elements at different locations of the probe. This way the flexible probe can be inserted into the instrument guide pipe 32 and remove as well. In the figure 6 the flexible probe is fully inserted in to the guide pipe 32 and in the figure 7 the probe is partially removed, for example for service or replacement of the probe. In case the insertion of the probe in the tube is too difficult, a steel wire looping the end of the pipe 32 inside it, can be used to pull the probe in the pipe instead of pushing it. The temperature measurement system 34’ can be used simultaneously to- gether with the liquid level measurement system in the embodiment described in the figure 3.
[0041] In the Figure 8 there is shown an embodiment of the invention which oth- erwise corresponds to that shown in other figures but here the tank connection space 22 is separate to i.e. non-integral with the cryogenic tank 10. The instru- ment guide pipe 32 extends through the end portion 18.2 of the outer shell 18 and into the tank connection space via barrier channel 19. The instrument guide pipe 32 enclosed in gas tight manner by the barrier channel 19 between the end portion 18.2 of the outer shell 18 and the tank connection space 22. The barrier channel 19 may be for example a pipe having diameter greater than the diameter of the instrument guide pipe 32.
[0042] While the invention has been described herein by way of examples in connection with what are, at present, considered to be the most preferred em- bodiments, it is to be understood that the invention is not limited to the disclosed embodiments, but is intended to cover various combinations or modifications of its features, and several other applications included within the scope of the in- vention, as defined in the appended claims. The details and technical features mentioned in connection with any embodiment above may be used in connection with another embodiment when such combination is technically feasible.

Claims

Claims
1 . A cryogenic fuel tank (10) comprising an instrumentation arrangement (30) to measure and/or record one or more physical quantities of the fuel in the fuel tank (10), the fuel tank (10) comprising an inner shell (16), and an outer shell (18), in which the inner shell (16) comprise a first cylindrical shell portion (16.1 ) and end portions (16.2) at both ends thereof, and the outer shell (18) comprise a second cylindrical shell portion (18.1 ) and end portions (18.2) at both ends thereof, and an insulation cavity (20) between the inner shell (16) and the outer shell (18), the cryogenic fuel tank (10) further comprising a tank connection space (22), characterized in that the instrumentation arrangement (30) comprises an instrument guide pipe (32), and a measurement system (34) configured to meas- ure and/or record one or more physical quantities of the fuel in the fuel tank (10) coupled to the instrument guide pipe (32), wherein the instrument guide pipe (32) is arranged to extend from the tank connection space (22) to the tank space (1 1 ) via the insulation cavity (20).
2. A cryogenic fuel tank (10) according to claim 1 , characterized in that the instrument guide pipe (32) is arranged to extend through the end portion (18.2) of the outer shell (18) to the insulation cavity (20) and further from the insulation cavity (20) into a tank space (1 1 ) through the first cylindrical portion (16.1 ) of the inner shell (16) of the fuel tank (10).
3. A cryogenic fuel tank (10) according to claim 1 , characterized in that a first section (32.1 ) of the instrument guide pipe (32) is arranged to extend through the end portion (18.2) of the outer shell (18), and a second section (32.2) of the instrument guide pipe (32) is arranged to extend along the insulation cavity (20) between the end portion (16.2) of the inner shell (16) and the end portion (18.2) of the outer shell (18) to the insulation cavity (20) between the first cylindrical portion (16.1 ) and the second cylindrical portion (18.1 ), and further a third section (32.3) of the instrument guide pipe is arranged to extend in the insulation cavity (20) between the first cylindrical portion (16.1 ) and the second cylindrical portion (18.1 ) in longitudinal direction of the cryogenic fuel tank (10), and a fourth section (32.4) of the instrument guide pipe (32) arranged to extend into a tank space (11 ) through the inner shell(16) of the fuel tank (10).
4. A cryogenic fuel tank (10) according to claim 1 , characterized in that the first section (32.1 ) of the instrument guide pipe (32) is arranged to extend through the end portion (18.2) of the outer shell (18) in longitudinal direction of the cryo- genic fuel tank (10).
5. A cryogenic fuel tank (10) according to claim 3, characterized in that the first cylindrical shell portion (16.1 ) is provided with a lead-through (44), through which the fourth section (32.4) of the instrument guide pipe (32) is arranged to extend into the tank space (11 ).
6. A cryogenic fuel tank (10) according to claim 3 or 5, characterized in that the fourth section (32.4) of the instrument guide pipe (32) is arranged to extend radially towards the center of the first cylindrical shell portion (16.1 ) from the lead- through (44) and further towards the first shell (16.1 ) wall which is radially oppo- site to the lead-through (44).
7. A cryogenic fuel tank (10) according to claim 1 , characterized in that the instrument guide pipe portion which is in the tank space (11 ) comprises openings (36) in its outer wall.
8. A cryogenic fuel tank (10) according to claim 3, characterized in that the fourth section (32.4) of the instrument guide pipe (32) comprises openings (36) in its side wall.
9. A cryogenic fuel tank (10) according to claim 5, characterized in that the lead-through (44) comprises a radially inwardly extending cup (45) having is rim (46) attached to the inner shell (16), and wherein the instrument guide pipe (32) is led through a bottom part of the cup (45).
10. A cryogenic fuel tank (10) according to claim 1 and 6, characterized in that the instrumentation arrangement (30) comprises a radar-based measure- ment system (34) and the fourth section (32.4) of the instrument guide pipe (32) comprises a float part (40) arranged to reflect radar signal.
1 1. A cryogenic fuel tank (10) according to claim 1 and 5, characterized in that the instrumentation arrangement (30) comprises a flexible temperature measurement probe (34) which is arranged inside the instrument guide pipe (32).
12. A cryogenic fuel tank (10) according to claim 1 or 6, characterized in that the instrumentation arrangement (30) comprises an inertial measurement unit for defining an inclination angle of the fuel tank (10).
13. A cryogenic fuel tank (10) according to claim 1 and 6, characterized in that the instrumentation arrangement (30) comprises a temperature measure- ment system (34’).
14. A cryogenic fuel tank (10) according to claim 1 or 6, characterized in that the instrumentation arrangement (30) comprises a radar-based measurement system (34) and the fourth section (32.4) of the instrument guide pipe (32) corn- prises a stationary reference reflector (42) in the pipe (32).
EP18799756.4A 2018-11-07 2018-11-07 A cryogenic fuel tank Pending EP3877693A1 (en)

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PCT/EP2018/080408 WO2020094221A1 (en) 2018-11-07 2018-11-07 A cryogenic fuel tank

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KR20210083329A (en) 2021-07-06
CN112969883A (en) 2021-06-15

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