US20110253346A1 - Auxilliary reservoir for a liquid system - Google Patents
Auxilliary reservoir for a liquid system Download PDFInfo
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- US20110253346A1 US20110253346A1 US12/760,723 US76072310A US2011253346A1 US 20110253346 A1 US20110253346 A1 US 20110253346A1 US 76072310 A US76072310 A US 76072310A US 2011253346 A1 US2011253346 A1 US 2011253346A1
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- Prior art keywords
- liquid
- reservoir
- volume
- fluid
- circulation loop
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F28—HEAT EXCHANGE IN GENERAL
- F28D—HEAT-EXCHANGE APPARATUS, NOT PROVIDED FOR IN ANOTHER SUBCLASS, IN WHICH THE HEAT-EXCHANGE MEDIA DO NOT COME INTO DIRECT CONTACT
- F28D15/00—Heat-exchange apparatus with the intermediate heat-transfer medium in closed tubes passing into or through the conduit walls ; Heat-exchange apparatus employing intermediate heat-transfer medium or bodies
- F28D15/02—Heat-exchange apparatus with the intermediate heat-transfer medium in closed tubes passing into or through the conduit walls ; Heat-exchange apparatus employing intermediate heat-transfer medium or bodies in which the medium condenses and evaporates, e.g. heat pipes
- F28D15/04—Heat-exchange apparatus with the intermediate heat-transfer medium in closed tubes passing into or through the conduit walls ; Heat-exchange apparatus employing intermediate heat-transfer medium or bodies in which the medium condenses and evaporates, e.g. heat pipes with tubes having a capillary structure
- F28D15/043—Heat-exchange apparatus with the intermediate heat-transfer medium in closed tubes passing into or through the conduit walls ; Heat-exchange apparatus employing intermediate heat-transfer medium or bodies in which the medium condenses and evaporates, e.g. heat pipes with tubes having a capillary structure forming loops, e.g. capillary pumped loops
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F28—HEAT EXCHANGE IN GENERAL
- F28D—HEAT-EXCHANGE APPARATUS, NOT PROVIDED FOR IN ANOTHER SUBCLASS, IN WHICH THE HEAT-EXCHANGE MEDIA DO NOT COME INTO DIRECT CONTACT
- F28D15/00—Heat-exchange apparatus with the intermediate heat-transfer medium in closed tubes passing into or through the conduit walls ; Heat-exchange apparatus employing intermediate heat-transfer medium or bodies
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- 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
- F25D—REFRIGERATORS; COLD ROOMS; ICE-BOXES; COOLING OR FREEZING APPARATUS NOT OTHERWISE PROVIDED FOR
- F25D17/00—Arrangements for circulating cooling fluids; Arrangements for circulating gas, e.g. air, within refrigerated spaces
- F25D17/02—Arrangements for circulating cooling fluids; Arrangements for circulating gas, e.g. air, within refrigerated spaces for circulating liquids, e.g. brine
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- A—HUMAN NECESSITIES
- A47—FURNITURE; DOMESTIC ARTICLES OR APPLIANCES; COFFEE MILLS; SPICE MILLS; SUCTION CLEANERS IN GENERAL
- A47F—SPECIAL FURNITURE, FITTINGS, OR ACCESSORIES FOR SHOPS, STOREHOUSES, BARS, RESTAURANTS OR THE LIKE; PAYING COUNTERS
- A47F3/00—Show cases or show cabinets
- A47F3/04—Show cases or show cabinets air-conditioned, refrigerated
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
- B64D2013/0603—Environmental Control Systems
- B64D2013/0614—Environmental Control Systems with subsystems for cooling avionics
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
- B64D2013/0603—Environmental Control Systems
- B64D2013/0629—Environmental Control Systems with subsystems for cooling food, catering or special loads
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
- B64D2013/0603—Environmental Control Systems
- B64D2013/0674—Environmental Control Systems comprising liquid subsystems
Definitions
- the present invention relates to liquid circulation systems and more particularly to reservoirs for liquid cooling systems used in aircraft.
- Modern aircraft include many complex systems that include liquid circulation systems, such as environmental control systems, galley cooling systems and electronics systems. These systems are interconnected through a network that circulates various fluids and gases between the systems using components such as valves, pumps and electric motors. Some of these liquid systems generate heat that is carried away by other fluid systems to be dumped overboard from the aircraft. For example, the components are controlled by power electronics that consume large amounts of electric power and therefore generate heat that must be removed.
- Typical cooling systems used in these liquid systems involve closed loops that circulate a liquid coolant, such as a mixture of water and glycol, through heat exchangers using pumps.
- the cooling systems are subject to temperature extremes ranging from the extreme cold of the upper atmosphere to the high temperatures generated within the systems.
- the liquid coolant therefore undergoes wide ranging temperature changes, which varies the volume of the liquid coolant due to thermal expansion.
- liquid cooling systems are provided with accumulators or reservoirs that provide an overflow volume.
- the reservoir holds a volume of coolant when temperatures are hot and the coolant is expanded.
- the reservoir returns the coolant to circulation when the coolant cools and contracts.
- the reservoir is often incorporated into a package with the pump.
- bootstrap reservoirs use pump inlet and outlet pressures to adjust the reservoir volume with system pressure changes.
- the capacity of the reservoir is typically sized for the requirements of a particular cooling system and aircraft platform. As such, redesign or scaling of pump-integrated accumulators is not a cost-effective option when designing liquid systems for new aircraft platforms.
- the present invention is directed to a liquid system for circulating a liquid through a circulation loop, such as liquid cooling loops used in aircraft.
- the liquid system comprises a liquid pump, a primary liquid reservoir and an auxiliary liquid reservoir.
- the liquid pump pressurizes liquid within the circulation loop.
- the primary liquid reservoir has a primary variable volume expandable to accommodate volumetric expansion of pressurized liquid up to a threshold volume.
- the auxiliary liquid reservoir has an auxiliary variable volume expandable only after the threshold volume is exceeded up to a maximum volume.
- FIG. 1 shows a schematic of a liquid cooling system having a liquid load, a pump and reservoir package and an auxiliary reservoir of the present invention.
- FIG. 2 shows a diagrammatic illustration of the pump and reservoir package and the auxiliary reservoir of FIG. 1 .
- FIG. 1 shows a schematic of liquid system 10 having pump package 12 , liquid loads 14 , 16 and 18 , and auxiliary reservoir 20 .
- Pump package 12 includes pump 22 , primary reservoir 24 and valve 26 .
- Liquid loads 14 and 16 include heat exchangers 28 and 30 , respectively, and liquid load 14 includes check valve 32 and diverter valve 34 .
- Liquid load 18 includes cooling circuits 36 A and 36 B (which include evaporators 38 A and 38 B and condensers 40 A and 40 B, respectively), pressure sensor 42 and temperature sensor 44 .
- Liquid loads 14 , 16 and 18 and auxiliary reservoir 20 are connected to pump package 12 with liquid lines 46 A- 46 F.
- Liquid system 10 comprises a system for circulating fluid through a closed circulation loop.
- system 10 may comprise a cooling system integrated into an aircraft environmental control system (ECS) that circulates a cooling fluid.
- ECS aircraft environmental control system
- system 10 is typically incorporated into an aircraft airframe.
- Liquid loads 14 , 16 and 18 represent areas or spaces within the airframe that demand different levels and types of cooling.
- liquid load 18 comprises a pressurized cargo bay portion of the airframe where aircraft electronics, such as power electronics or avionics, are stored.
- Liquid loads 14 and 16 comprise unpressurized regions of the airframe such as pack bays where ECS equipment is stowed.
- any space within an aircraft, such as the cabin may be connected to system 10 .
- Liquid system 10 provides a fluid medium that transfers heat to and from various places within system 10 .
- Cooling circuits 36 A and 36 B of liquid load 18 are in thermal communication with lines 46 A and 46 B through evaporators 38 A and 38 B, and with lines 48 A and 48 B through condensers 40 A and 40 B. Although two circuits are shown, additional circuits may be added as provided by design requirements. Cooling fluid in lines 48 A and 48 B is heated by circulating through hot electronics (or heat exchangers in thermal communication with the electronics) and cooled by circulating through cooled heat exchangers in communication with ram air ducts (not shown).
- Evaporators 38 A and 38 B unload heat from system 10 and condensers 40 A and 40 B impart the heat into lines 48 A and 48 B for removal from circuits 36 A and 36 B by the ram air ducts.
- the fluid of system 10 is cooled by circuits 36 A and 36 B before flowing into liquid loads 14 and 16 through line 46 C.
- the pack bays of liquid loads 14 and 16 contain environmental control systems that provide conditioned air to passenger areas of the aircraft cabin.
- Fluid line 46 E connects liquid load 16 in parallel with liquid load 14 .
- the chilled cooling fluid of system 10 absorbs heat from heat exchangers 28 and 30 , through which a separate fluid flows in lines 50 and 52 , respectively.
- Liquid system 10 may include other systems that dump heat to or take heat from fluid of lines 46 A- 46 D either directly or through conduction.
- system 10 may be linked to galley cooling systems of the aircraft between liquid loads 18 and 14 . Examples of various liquid loads used in conjunction with liquid circulation loops are described in U.S. Pat. No. 4,550,573, which is assigned to United Technologies Corporation, and U.S. Pat. Nos. 6,415,595 and 7,334,422, which are assigned to Hamilton Sundstrand Corporation, all of which are incorporated by reference.
- a liquid circulates through a closed loop system that transfers and removes heat from the system.
- System 10 includes various other components, including valves and sensors, for maintaining operation of system 10 .
- Valves 32 and 34 operate to bring liquid loads 14 and 16 into fluid communication with liquid system 10 properly. Diverter valve 34 can be closed to bypass loads 14 and 16 such as for safety, maintenance or performance issues.
- Check valve 32 prevents fluid within lines 46 A- 46 E from flowing backwards through system 10 .
- Relief valve 26 which may be placed anywhere along fluid lines 46 A- 46 D, allows fluid to escape from line 46 D when pressure within system 10 exceeds a maximum pressure.
- Pressure sensor 42 and temperature sensor 44 provide input signals to an aircraft controller to monitor the performance of system 10 . For example, the speed of pump 22 can be adjusted based on the pressures and temperatures of system 10 . Also, sensors 42 and 44 allow calculations to be performed to determine fluid levels in system 10 .
- Reservoir 24 comprises a variable enclosed volume that allows the fluid within system 10 to expand.
- cooling fluid within system 10 retains heat from liquid loads 14 - 18 , which thermally expands the fluid.
- ambient heat from atmospheric conditions expands the volume of the fluid within system 10 .
- the thermal expansion of the fluid exceeds the total system volume provided by lines 46 A- 46 F and pump 22 .
- system 10 operates optimally when fluid fills the system and air is omitted from the system.
- reservoir 24 provides extra system volume that adjusts so system 10 is always operating optimally. Without a reservoir, thermal expansion of the fluid would increase the pressure of system 10 to operate valve 26 . Fluid would thus be expelled from system 10 as valve 26 opens at the maximum pressure.
- Reservoir 24 thus allows system 10 to operate optimally during widely varying ranges of conditions.
- the capacity of reservoir 24 is closely matched to the expected operating conditions of system 10 and the particular liquid loads to which system 10 is connected.
- system 10 It is sometimes desirable to change the configuration of system 10 . For example, more cooling loops, similar to circuits 36 A and 36 B, may be added to liquid load 18 . These loads may require system 10 to carry a greater volume of cooling fluid, as might be needed for greater lengths of fluid lines or for increases in cooling performance. Additionally, the configuration of system 10 may change as system 10 is incorporated into a different aircraft airframe. It is, however, desirable to maintain system 10 as close as possible to original design specifications to avoid the need to have to recertify existing components to performance and safety specifications. In particular, it is difficult to redesign pump package 12 because pump 22 and reservoir 24 are incorporated into a single housing, as is described in more detail with reference to FIG. 2 .
- Auxiliary reservoir 20 of the present invention provides system 10 with additional volumetric capacity beyond what is provided by reservoir 24 .
- Auxiliary reservoir 20 can be linked into system 10 along any portion of lines 46 A- 46 E.
- system 10 can be reconfigured and repackaged for easy incorporation into other airframes.
- the construction of pump package 12 need not be disturbed to do so.
- Auxiliary reservoir 20 is also designed to not disturb the performance of reservoir 24 until auxiliary capacity is needed, as is described with reference to FIG. 2 .
- FIG. 2 shows a diagrammatic illustration of pump package 12 , separate auxiliary reservoir 20 , pump 22 , primary reservoir 24 , liquid load 14 and valve 26 .
- Auxiliary reservoir 20 includes housing 54 , bellows 56 , spring 58 and cap 60 .
- Pump package 12 includes housing 62 , reservoir cylinder 64 , piston 66 , inlet chamber 68 , outlet chamber 70 and level sensor 71 .
- FIG. 2 is shown to illustrate the present invention including the various volumes within each component and is not shown to scale.
- Low pressure system fluid F LP enters liquid load 14 through fluid line 46 C after having passed through liquid load 18 ( FIG. 1 ). Within liquid load 14 , F LP is in thermal communication with heat exchanger 28 ( FIG. 1 ) whereby heat is absorbed into fluid F LP . After passing through liquid load 14 , low pressure fluid F LP is ready to be re-circulated through system 10 to continue the cycle of heat removal. Low pressure fluid F LP flows from liquid load 14 to pump package 12 through liquid line 46 D. Along the way to pump package 12 , fluid F LP passes valve 26 and auxiliary reservoir 20 and exerts pressure on valve 26 and reservoir 20 commensurate with system pressure at that point. As discussed below, valve 26 and reservoir 20 open at specific pressures to ensure functionality of system 10 . As shown in FIG. 2 , auxiliary reservoir 20 is shown in an evacuated state where no fluid is stored.
- low pressure fluid F LP enters inlet chamber 68 within housing 62 .
- low pressure fluid F LP enters cylinder 64 where piston 66 exerts atmospheric pressure P A on chamber 68 .
- the lowest pressure within system 10 occurs at inlet chamber 68 .
- fluid within inlet chamber 68 exerts a force on piston 66 .
- Fluid continues into pump 22 from chamber 68 .
- the fluid becomes pressurized using any conventional compression means.
- pump 22 may comprise rotary vane pump or a centrifugal pump.
- pump 22 may comprise a tandem pump unit for reasons of redundancy and safety.
- primary reservoir 24 comprises a bootstrap reservoir as is known in the art.
- U.S. Pat. No. 4,691,739 to Gooden describes a typical bootstrap reservoir configuration.
- any pump reservoir combination may be used.
- an integrated pump and gas-charged reservoir is described in U.S. Pat. No. 4,906,166, which is assigned to Sundstrand Corporation.
- pump 22 and primary reservoir 24 are not integrated.
- the highest pressure in system 10 occurs at the outlet of pump 22 , which is outlet chamber 70 for the described embodiment. From outlet chamber 70 , high pressure fluid F HP leaves reservoir 24 and enters fluid line 46 A for circulation through system 10 and returning to liquid load 14 as low pressure fluid F LP .
- System 10 As heat accumulates in low pressure fluid F LP due to system operation and increases in ambient temperature, the volume of F LP increases.
- System 10 is designed to operate fully charged, i.e. with no empty space in lines 46 A- 46 E or pump 22 .
- volumetric expansion of F LP due to temperature increases causes the pressure within system 10 to increase.
- Primary reservoir 24 and auxiliary reservoir 20 provide extra volumetric capacity to system 10 to accommodate thermal expansion of fluid F LP .
- primary reservoir 24 and auxiliary reservoir 20 provide active or real-time increases in system capacity so that system 10 is always fully charged.
- activation of primary reservoir 24 and auxiliary reservoir 20 is staged such that utilization of the volumetric capacity of auxiliary reservoir 20 occurs only after the volumetric capacity of primary reservoir 24 is maxed out.
- Piston 66 thus rises (as shown in FIG. 2 ) within cylinder 64 such that more space within cylinder 64 is allocated to inlet chamber 68 and less space is allocated to outlet chamber 70 .
- Level sensor 71 provides input to a system controller that indicates the position of piston 55 and/or the liquid level in cylinder 64 . The input can be referenced with pressure and temperature data sensed by pressure sensor 42 and temperature sensor 44 ( FIG. 1 ) to verify operation of system 10 . However, piston 66 can only traverse cylinder 64 until piston flange 72 engages cylinder stops 74 .
- primary reservoir 24 has an operating range extending from the minimum operating pressure of system 10 to a pressure below the maximum operating pressure of system 10 .
- pressure at inlet chamber 68 will rise to the minimum system operating pressure.
- Atmospheric pressure P A and the pressure of high pressure fluid F HP will maintain piston 66 in a collapsed or fully downward position within cylinder 64 , insofar as the liquid level in the primary reservoir 24 will allow.
- piston 66 rises until the threshold pressure is reached.
- Auxiliary reservoir 20 comprises a spring-charged reservoir in which spring 58 biases the position of cap 60 against housing 54 .
- Spring 58 maintains the volumetric capacity within housing 54 , the space between cap 60 and fluid line 46 F, closed until the threshold pressure is reached.
- Spring 58 pushes downward on cap 60 such that low pressure fluid F LP is not able to enter housing 54 through line 46 F.
- Spring 58 has a spring force set to yield at or above the threshold pressure of primary reservoir 24 .
- spring 58 will not allow cap 60 to move, making the volumetric capacity within housing 54 unavailable, until the threshold level is exceeded and the volumetric capacity of primary reservoir 24 is full.
- bellows 56 expands and cap 60 rises within housing 54 .
- Bellows 56 comprises a flexible metal sleeve that hermetically seals low pressure fluid F LP within housing 54 , preventing the fluid from moving to the back side of cap 60 .
- Cap 60 can continue to retreat until spring 58 is fully compressed.
- system 10 reaches its maximum volumetric capacity, as both primary reservoir 24 and auxiliary reservoir 20 are full. After reservoirs 20 and 24 fill up, any further increase in volume of low pressure fluid F LP will cause valve 26 to release fluid from system 10 .
- Valve 26 may comprise any pressure relief valve as is know in the art.
- System 10 returns to lower operating pressures in reverse order, with auxiliary reservoir 20 emptying completely before primary reservoir 24 reduces fluid volume. Spring 58 ensures that any fluid within housing 54 is recharged into lines 46 A- 46 F for circulation through the system 10 .
- auxiliary reservoir 20 may comprise a gas-charged reservoir where the back side of cap 60 within housing 54 is charged with a compressible gas that acts as a spring force.
- Auxiliary reservoir 20 may also be provided with additional features such as de-aeration and bleed ports, level sensors, temperature sensors and pressure sensors.
- auxiliary reservoir 20 need not have a dedicated level sensor so long as reservoir 24 is provided with level sensor 71 .
- auxiliary reservoir 20 can be sized to provide volume for the extreme upper limit of the operating pressure range of system 10 . Thus, auxiliary reservoir 20 need only be engaged by system 10 a small amount of time. When level sensor 71 indicates primary reservoir 24 is at full capacity, a system controller will be able to determine that auxiliary reservoir 20 went into use.
- the system controller can verify fluid levels in system 10 by rechecking data from level sensor 71 , pressure sensor 42 and temperature sensor 44 . If fluid levels are indicated as being low, the controller can determine that pressures within system 10 exceeded the maximum pressure such that valve 26 was activated and fluid was lost. Thus, a system operator can be alerted by the controller to the fact that system 10 may need maintenance.
- Auxiliary reservoir 20 increases the volumetric fluid capacity of system 10 without interfering with the installation or operation of system 10 and pump package 12 .
- Auxiliary reservoir 20 can be spliced into fluid line 46 D at any position. Any space within an airframe available may be used to accommodate auxiliary reservoir 20 . Thus, the addition of additional cooling demands, such as an additional cooling circuit being connected to liquid load 18 , can be easily accommodated. Furthermore, the packaging of pump 22 and 24 need not be disturbed to increase capacity of system 10 .
- System 10 including auxiliary reservoir 20 , can be filled by simply filling system 10 with fluid until valve 26 releases fluid such that all air is purged from system 10 , as would be done without auxiliary reservoir 20 .
- the timing of the activation of auxiliary reservoir 20 allows pump package 12 to function as if auxiliary reservoir 20 were not part of the system when operating below the threshold level. Thus, the pumping performance of pump 22 will remain unaffected below the threshold level.
Abstract
A liquid system for circulating a liquid through a circulation loop includes a liquid pump, a primary liquid reservoir and an auxiliary liquid reservoir. The liquid pump pressurizes liquid within the circulation loop. The primary liquid reservoir has a primary variable volume expandable to accommodate volumetric expansion of pressurized liquid up to a threshold volume. The auxiliary liquid reservoir has an auxiliary variable volume expandable only after the threshold volume is exceeded up to a maximum volume.
Description
- The present invention relates to liquid circulation systems and more particularly to reservoirs for liquid cooling systems used in aircraft.
- Modern aircraft include many complex systems that include liquid circulation systems, such as environmental control systems, galley cooling systems and electronics systems. These systems are interconnected through a network that circulates various fluids and gases between the systems using components such as valves, pumps and electric motors. Some of these liquid systems generate heat that is carried away by other fluid systems to be dumped overboard from the aircraft. For example, the components are controlled by power electronics that consume large amounts of electric power and therefore generate heat that must be removed. Typical cooling systems used in these liquid systems involve closed loops that circulate a liquid coolant, such as a mixture of water and glycol, through heat exchangers using pumps.
- The cooling systems are subject to temperature extremes ranging from the extreme cold of the upper atmosphere to the high temperatures generated within the systems. The liquid coolant therefore undergoes wide ranging temperature changes, which varies the volume of the liquid coolant due to thermal expansion. In order to absorb the volumetric expansion of the coolant throughout the operating cycle of the system, liquid cooling systems are provided with accumulators or reservoirs that provide an overflow volume. The reservoir holds a volume of coolant when temperatures are hot and the coolant is expanded. The reservoir returns the coolant to circulation when the coolant cools and contracts. In order to reduce the size of the cooling system and the space occupied in the aircraft, the reservoir is often incorporated into a package with the pump. For example, bootstrap reservoirs use pump inlet and outlet pressures to adjust the reservoir volume with system pressure changes. Furthermore, the capacity of the reservoir is typically sized for the requirements of a particular cooling system and aircraft platform. As such, redesign or scaling of pump-integrated accumulators is not a cost-effective option when designing liquid systems for new aircraft platforms.
- The present invention is directed to a liquid system for circulating a liquid through a circulation loop, such as liquid cooling loops used in aircraft. The liquid system comprises a liquid pump, a primary liquid reservoir and an auxiliary liquid reservoir. The liquid pump pressurizes liquid within the circulation loop. The primary liquid reservoir has a primary variable volume expandable to accommodate volumetric expansion of pressurized liquid up to a threshold volume. The auxiliary liquid reservoir has an auxiliary variable volume expandable only after the threshold volume is exceeded up to a maximum volume.
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FIG. 1 shows a schematic of a liquid cooling system having a liquid load, a pump and reservoir package and an auxiliary reservoir of the present invention. -
FIG. 2 shows a diagrammatic illustration of the pump and reservoir package and the auxiliary reservoir ofFIG. 1 . -
FIG. 1 shows a schematic ofliquid system 10 havingpump package 12,liquid loads auxiliary reservoir 20.Pump package 12 includespump 22,primary reservoir 24 andvalve 26.Liquid loads heat exchangers liquid load 14 includescheck valve 32 anddiverter valve 34.Liquid load 18 includescooling circuits condensers pressure sensor 42 andtemperature sensor 44.Liquid loads auxiliary reservoir 20 are connected topump package 12 withliquid lines 46A-46F. -
Liquid system 10 comprises a system for circulating fluid through a closed circulation loop. For example,system 10 may comprise a cooling system integrated into an aircraft environmental control system (ECS) that circulates a cooling fluid. As such,system 10 is typically incorporated into an aircraft airframe.Liquid loads liquid load 18 comprises a pressurized cargo bay portion of the airframe where aircraft electronics, such as power electronics or avionics, are stored.Liquid loads system 10.Liquid system 10 provides a fluid medium that transfers heat to and from various places withinsystem 10. -
Pump 22 ofpump package 12 pressurizes a cooling fluid withinloop lines 46A-46F. The fluid flows frompump package 12 toliquid load 18 throughline 46A.Cooling circuits liquid load 18 are in thermal communication withlines lines condensers lines system 10 and condensers 40A and 40B impart the heat intolines circuits system 10 is cooled bycircuits liquid loads line 46C. - The pack bays of
liquid loads Fluid line 46E connectsliquid load 16 in parallel withliquid load 14. The chilled cooling fluid ofsystem 10 absorbs heat fromheat exchangers lines Liquid system 10 may include other systems that dump heat to or take heat from fluid oflines 46A-46D either directly or through conduction. For example,system 10 may be linked to galley cooling systems of the aircraft betweenliquid loads -
System 10 includes various other components, including valves and sensors, for maintaining operation ofsystem 10.Valves liquid loads liquid system 10 properly.Diverter valve 34 can be closed tobypass loads Check valve 32 prevents fluid withinlines 46A-46E from flowing backwards throughsystem 10.Relief valve 26, which may be placed anywhere alongfluid lines 46A-46D, allows fluid to escape fromline 46D when pressure withinsystem 10 exceeds a maximum pressure.Pressure sensor 42 andtemperature sensor 44 provide input signals to an aircraft controller to monitor the performance ofsystem 10. For example, the speed ofpump 22 can be adjusted based on the pressures and temperatures ofsystem 10. Also,sensors system 10. -
Reservoir 24 comprises a variable enclosed volume that allows the fluid withinsystem 10 to expand. For example, cooling fluid withinsystem 10 retains heat from liquid loads 14-18, which thermally expands the fluid. Furthermore, ambient heat from atmospheric conditions expands the volume of the fluid withinsystem 10. The thermal expansion of the fluid exceeds the total system volume provided bylines 46A-46F and pump 22. Specifically,system 10 operates optimally when fluid fills the system and air is omitted from the system. Thus, when the fluid expands,reservoir 24 provides extra system volume that adjusts sosystem 10 is always operating optimally. Without a reservoir, thermal expansion of the fluid would increase the pressure ofsystem 10 to operatevalve 26. Fluid would thus be expelled fromsystem 10 asvalve 26 opens at the maximum pressure. However, the expelled fluid would be lost such that upon a reduction in the temperature of the fluid,system 10 would not be full and would be operating below optimum conditions.Reservoir 24 thus allowssystem 10 to operate optimally during widely varying ranges of conditions. Thus, the capacity ofreservoir 24 is closely matched to the expected operating conditions ofsystem 10 and the particular liquid loads to whichsystem 10 is connected. - It is sometimes desirable to change the configuration of
system 10. For example, more cooling loops, similar tocircuits liquid load 18. These loads may requiresystem 10 to carry a greater volume of cooling fluid, as might be needed for greater lengths of fluid lines or for increases in cooling performance. Additionally, the configuration ofsystem 10 may change assystem 10 is incorporated into a different aircraft airframe. It is, however, desirable to maintainsystem 10 as close as possible to original design specifications to avoid the need to have to recertify existing components to performance and safety specifications. In particular, it is difficult to redesignpump package 12 becausepump 22 andreservoir 24 are incorporated into a single housing, as is described in more detail with reference toFIG. 2 . Thus, it is not possible to simply expand the capacity ofreservoir 24 without redesigningpump package 12.Auxiliary reservoir 20 of the present invention providessystem 10 with additional volumetric capacity beyond what is provided byreservoir 24.Auxiliary reservoir 20 can be linked intosystem 10 along any portion oflines 46A-46E. Thus,system 10 can be reconfigured and repackaged for easy incorporation into other airframes. Furthermore, the construction ofpump package 12 need not be disturbed to do so.Auxiliary reservoir 20 is also designed to not disturb the performance ofreservoir 24 until auxiliary capacity is needed, as is described with reference toFIG. 2 . -
FIG. 2 shows a diagrammatic illustration ofpump package 12, separateauxiliary reservoir 20, pump 22,primary reservoir 24,liquid load 14 andvalve 26.Auxiliary reservoir 20 includeshousing 54, bellows 56,spring 58 andcap 60.Pump package 12 includeshousing 62,reservoir cylinder 64,piston 66,inlet chamber 68,outlet chamber 70 andlevel sensor 71.FIG. 2 is shown to illustrate the present invention including the various volumes within each component and is not shown to scale. - Low pressure system fluid FLP enters
liquid load 14 throughfluid line 46C after having passed through liquid load 18 (FIG. 1 ). Withinliquid load 14, FLP is in thermal communication with heat exchanger 28 (FIG. 1 ) whereby heat is absorbed into fluid FLP. After passing throughliquid load 14, low pressure fluid FLP is ready to be re-circulated throughsystem 10 to continue the cycle of heat removal. Low pressure fluid FLP flows fromliquid load 14 to pumppackage 12 throughliquid line 46D. Along the way to pumppackage 12, fluid FLP passesvalve 26 andauxiliary reservoir 20 and exerts pressure onvalve 26 andreservoir 20 commensurate with system pressure at that point. As discussed below,valve 26 andreservoir 20 open at specific pressures to ensure functionality ofsystem 10. As shown inFIG. 2 ,auxiliary reservoir 20 is shown in an evacuated state where no fluid is stored. - At
pump package 12, low pressure fluid FLP entersinlet chamber 68 withinhousing 62. Specifically, low pressure fluid FLP enterscylinder 64 wherepiston 66 exerts atmospheric pressure PA onchamber 68. The lowest pressure withinsystem 10 occurs atinlet chamber 68. As pressure withinsystem 10 rises due to increased temperature of fluid FLP, fluid withininlet chamber 68 exerts a force onpiston 66. Fluid continues intopump 22 fromchamber 68. Withinpump 22, the fluid becomes pressurized using any conventional compression means. For example, pump 22 may comprise rotary vane pump or a centrifugal pump. Furthermore, pump 22 may comprise a tandem pump unit for reasons of redundancy and safety. - Fluid pressurized within
pump 22 is discharged intooutlet chamber 70. High pressure fluid FHP exerts a force onpiston 66 such that pressurization ofreservoir 24 is provided by operation ofpump 22. Thus,primary reservoir 24 comprises a bootstrap reservoir as is known in the art. For example, U.S. Pat. No. 4,691,739 to Gooden describes a typical bootstrap reservoir configuration. Although described with respect to an integrated pump and bootstrap-charged reservoir, any pump reservoir combination may be used. For example, an integrated pump and gas-charged reservoir is described in U.S. Pat. No. 4,906,166, which is assigned to Sundstrand Corporation. In yet other embodiments, pump 22 andprimary reservoir 24 are not integrated. In any embodiment, the highest pressure insystem 10 occurs at the outlet ofpump 22, which isoutlet chamber 70 for the described embodiment. Fromoutlet chamber 70, high pressure fluid FHP leavesreservoir 24 and entersfluid line 46A for circulation throughsystem 10 and returning toliquid load 14 as low pressure fluid FLP. - As heat accumulates in low pressure fluid FLP due to system operation and increases in ambient temperature, the volume of FLP increases.
System 10 is designed to operate fully charged, i.e. with no empty space inlines 46A-46E or pump 22. As such, volumetric expansion of FLP due to temperature increases causes the pressure withinsystem 10 to increase.Primary reservoir 24 andauxiliary reservoir 20 provide extra volumetric capacity tosystem 10 to accommodate thermal expansion of fluid FLP. In particular,primary reservoir 24 andauxiliary reservoir 20 provide active or real-time increases in system capacity so thatsystem 10 is always fully charged. Furthermore, activation ofprimary reservoir 24 andauxiliary reservoir 20 is staged such that utilization of the volumetric capacity ofauxiliary reservoir 20 occurs only after the volumetric capacity ofprimary reservoir 24 is maxed out. - As pressure within
system 10 rises, pressure withininlet chamber 68 rises, overcoming atmospheric pressure PA and pressure of high pressure fluid FHP onpiston 66.Piston 66 thus rises (as shown inFIG. 2 ) withincylinder 64 such that more space withincylinder 64 is allocated toinlet chamber 68 and less space is allocated tooutlet chamber 70.Level sensor 71 provides input to a system controller that indicates the position of piston 55 and/or the liquid level incylinder 64. The input can be referenced with pressure and temperature data sensed bypressure sensor 42 and temperature sensor 44 (FIG. 1 ) to verify operation ofsystem 10. However,piston 66 can only traversecylinder 64 untilpiston flange 72 engages cylinder stops 74. At such point, the volumetric capacity ofprimary reservoir 24 becomes maxed out, or reaches a threshold level where utilization ofauxiliary reservoir 20 is initiated. Thus,primary reservoir 24 has an operating range extending from the minimum operating pressure ofsystem 10 to a pressure below the maximum operating pressure ofsystem 10. Upon initiation ofsystem 10, pressure atinlet chamber 68 will rise to the minimum system operating pressure. Atmospheric pressure PA and the pressure of high pressure fluid FHP will maintainpiston 66 in a collapsed or fully downward position withincylinder 64, insofar as the liquid level in theprimary reservoir 24 will allow. Assystem 10 increases operating temperature above the minimum due to operating or ambient conditions,piston 66 rises until the threshold pressure is reached. -
Auxiliary reservoir 20 comprises a spring-charged reservoir in which spring 58 biases the position ofcap 60 againsthousing 54.Spring 58 maintains the volumetric capacity withinhousing 54, the space betweencap 60 andfluid line 46F, closed until the threshold pressure is reached.Spring 58 pushes downward oncap 60 such that low pressure fluid FLP is not able to enterhousing 54 throughline 46F.Spring 58 has a spring force set to yield at or above the threshold pressure ofprimary reservoir 24. Thus,spring 58 will not allowcap 60 to move, making the volumetric capacity withinhousing 54 unavailable, until the threshold level is exceeded and the volumetric capacity ofprimary reservoir 24 is full. Asauxiliary reservoir 20 fills with fluid, bellows 56 expands and cap 60 rises withinhousing 54.Bellows 56 comprises a flexible metal sleeve that hermetically seals low pressure fluid FLP withinhousing 54, preventing the fluid from moving to the back side ofcap 60.Cap 60 can continue to retreat untilspring 58 is fully compressed. At such point,system 10 reaches its maximum volumetric capacity, as bothprimary reservoir 24 andauxiliary reservoir 20 are full. Afterreservoirs valve 26 to release fluid fromsystem 10.Valve 26 may comprise any pressure relief valve as is know in the art.System 10 returns to lower operating pressures in reverse order, withauxiliary reservoir 20 emptying completely beforeprimary reservoir 24 reduces fluid volume.Spring 58 ensures that any fluid withinhousing 54 is recharged intolines 46A-46F for circulation through thesystem 10. - In other embodiments,
auxiliary reservoir 20 may comprise a gas-charged reservoir where the back side ofcap 60 withinhousing 54 is charged with a compressible gas that acts as a spring force.Auxiliary reservoir 20 may also be provided with additional features such as de-aeration and bleed ports, level sensors, temperature sensors and pressure sensors. However,auxiliary reservoir 20 need not have a dedicated level sensor so long asreservoir 24 is provided withlevel sensor 71. For example,auxiliary reservoir 20 can be sized to provide volume for the extreme upper limit of the operating pressure range ofsystem 10. Thus,auxiliary reservoir 20 need only be engaged by system 10 a small amount of time. Whenlevel sensor 71 indicatesprimary reservoir 24 is at full capacity, a system controller will be able to determine thatauxiliary reservoir 20 went into use. After returning to pressures within the operating range ofprimary reservoir 24, the system controller can verify fluid levels insystem 10 by rechecking data fromlevel sensor 71,pressure sensor 42 andtemperature sensor 44. If fluid levels are indicated as being low, the controller can determine that pressures withinsystem 10 exceeded the maximum pressure such thatvalve 26 was activated and fluid was lost. Thus, a system operator can be alerted by the controller to the fact thatsystem 10 may need maintenance. -
Auxiliary reservoir 20 increases the volumetric fluid capacity ofsystem 10 without interfering with the installation or operation ofsystem 10 andpump package 12.Auxiliary reservoir 20 can be spliced intofluid line 46D at any position. Any space within an airframe available may be used to accommodateauxiliary reservoir 20. Thus, the addition of additional cooling demands, such as an additional cooling circuit being connected toliquid load 18, can be easily accommodated. Furthermore, the packaging ofpump system 10.System 10, includingauxiliary reservoir 20, can be filled by simply fillingsystem 10 with fluid untilvalve 26 releases fluid such that all air is purged fromsystem 10, as would be done withoutauxiliary reservoir 20. The timing of the activation ofauxiliary reservoir 20 allowspump package 12 to function as ifauxiliary reservoir 20 were not part of the system when operating below the threshold level. Thus, the pumping performance ofpump 22 will remain unaffected below the threshold level. - While the invention has been described with reference to an exemplary embodiment(s), it will be understood by those skilled in the art that various changes may be made and equivalents may be substituted for elements thereof without departing from the scope of the invention. In addition, many modifications may be made to adapt a particular situation or material to the teachings of the invention without departing from the essential scope thereof. Therefore, it is intended that the invention not be limited to the particular embodiment(s) disclosed, but that the invention will include all embodiments falling within the scope of the appended claims.
Claims (20)
1. A liquid system for circulating a liquid through a circulation loop, the liquid system comprising:
a liquid pump for pressurizing liquid within the circulation loop;
a primary liquid reservoir in fluid communication with the circulation loop and having a primary variable volume expandable to accommodate volumetric expansion of pressurized liquid up to a threshold volume; and
an auxiliary liquid reservoir in fluid communication with the circulation loop and having an auxiliary variable volume expandable only after the threshold volume is exceeded up to a maximum volume.
2. The liquid system of claim 1 wherein the primary variable volume accommodates volumetric expansion of the liquid across operating pressures of the liquid pump up to a threshold pressure.
3. The liquid system of claim 2 wherein the auxiliary variable volume accommodates volumetric expansion of the liquid above the threshold pressure up to a maximum pressure.
4. The liquid system of claim 3 and further comprising:
a relief valve connected to the circulation loop and configured to open above the maximum pressure.
5. The liquid system of claim 3 wherein the auxiliary liquid reservoir comprises a spring-charged bellows having a spring with a spring force that yields above the threshold pressure.
6. The liquid system of claim 5 wherein the primary liquid reservoir comprises a bootstrap reservoir.
7. The liquid system of claim 6 wherein the liquid pump and the primary liquid reservoir are packaged in a common housing and the auxiliary liquid reservoir is packaged in a separate housing.
8. The liquid system of claim 6 wherein the primary liquid reservoir includes a level sensor for determining a volume of fluid within the primary liquid reservoir.
9. The liquid system of claim 1 and further comprising:
a liquid circulating through the circulation loop; and
a liquid load connected to the liquid pump through the circulation loop;
wherein the liquid load imparts a thermal input to the liquid.
10. A liquid system comprising:
a circulation loop;
a fluid pump configured to pressurize fluid within the circulation loop;
a primary reservoir in fluid communication with the circulation loop and configured to expand in volume under pressure within the circulation loop up to a threshold pressure; and
an auxiliary reservoir in fluid communication with the circulation loop and configured to expand in volume once the threshold pressure is exceeded.
11. The liquid system of claim 10 and further comprising:
a liquid circulating through the circulation loop; and
a liquid load connected to the liquid pump through the circulation loop;
wherein the liquid load imparts a thermal input to the liquid.
12. The liquid system of claim 11 wherein the auxiliary reservoir comprises a spring charged bellows having a spring with a spring force that yields above the threshold pressure.
13. The liquid system of claim 12 wherein the primary reservoir comprises a bootstrap reservoir integrated into a housing of the fluid pump, and the auxiliary reservoir is packaged in a separate housing.
14. The liquid system of claim 12 wherein the primary reservoir includes a level sensor for determining a volume of fluid within the primary reservoir.
15. The liquid system of claim 10 wherein the auxiliary reservoir expands to a maximum volume after the primary reservoir expands to a threshold volume.
16. A method of accommodating expanding fluid in a closed fluid circulation loop, the method comprising:
circulating pressurized fluid in a closed fluid circulation loop using a pump;
expanding a volume of a primary reservoir connected to the closed fluid circulation loop up to a threshold volume to accommodate expansion of the pressurized fluid to a threshold level; and
expanding a volume of an auxiliary reservoir connected to the closed fluid circulation loop up to a maximum volume to accommodate expansion of the pressurized fluid from the threshold level to a maximum level.
17. The method of claim 16 wherein the volume of the primary reservoir and the volume of the auxiliary reservoir are expanded sequentially.
18. The method of claim 16 wherein the volume of the primary reservoir is expanded to a threshold pressure and the volume of the auxiliary reservoir is expended after the threshold pressure is reached.
19. The method of claim 18 wherein the step of expanding the volume of the primary reservoir comprises expanding a bootstrap reservoir integrated with the pump.
20. The method of claim 19 wherein the step of expanding the volume of the auxiliary reservoir comprises expanding a bellow-type reservoir having a spring that yields at the threshold pressure.
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
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US12/760,723 US20110253346A1 (en) | 2010-04-15 | 2010-04-15 | Auxilliary reservoir for a liquid system |
US15/606,790 US20170261267A1 (en) | 2010-04-15 | 2017-05-26 | Auxilliary reservoir for a liquid system |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
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US12/760,723 US20110253346A1 (en) | 2010-04-15 | 2010-04-15 | Auxilliary reservoir for a liquid system |
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US15/606,790 Continuation US20170261267A1 (en) | 2010-04-15 | 2017-05-26 | Auxilliary reservoir for a liquid system |
Publications (1)
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US20110253346A1 true US20110253346A1 (en) | 2011-10-20 |
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US12/760,723 Abandoned US20110253346A1 (en) | 2010-04-15 | 2010-04-15 | Auxilliary reservoir for a liquid system |
US15/606,790 Abandoned US20170261267A1 (en) | 2010-04-15 | 2017-05-26 | Auxilliary reservoir for a liquid system |
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US15/606,790 Abandoned US20170261267A1 (en) | 2010-04-15 | 2017-05-26 | Auxilliary reservoir for a liquid system |
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US (2) | US20110253346A1 (en) |
Cited By (4)
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US9086154B2 (en) | 2013-04-04 | 2015-07-21 | Hamilton Sundstrand Corporation | Ball shaft for a liquid coolant valve |
US20160366786A1 (en) * | 2015-06-10 | 2016-12-15 | Cooler Master Co., Ltd. | Liquid supply mechanism and liquid cooling system |
US9992910B2 (en) | 2015-06-11 | 2018-06-05 | Cooler Master Co., Ltd. | Liquid supply mechanism and liquid cooling system |
US20180283284A1 (en) * | 2017-04-03 | 2018-10-04 | Hamilton Sundstrand Corporation | Aircraft fluid control system having a pressure sensor |
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US4510893A (en) * | 1982-07-15 | 1985-04-16 | Bayerische Motoren Werke Ag | Cooling circuit for internal combustion engines |
US5947375A (en) * | 1996-07-22 | 1999-09-07 | Matsushita Electric Industrial Co., Ltd. | Liquid heating and circulating apparatus for use in an automotive vehicle |
US6871670B2 (en) * | 2002-05-29 | 2005-03-29 | Advics Co., Ltd. | Metal bellows accumulator |
US20100319902A1 (en) * | 2009-06-19 | 2010-12-23 | Wan Ching Chou | Auxiliary apparatus for vehicle water tank |
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US3559727A (en) * | 1968-12-20 | 1971-02-02 | United Aircraft Prod | Accumulator-reservoir in a cooling system |
US4691739A (en) * | 1986-09-02 | 1987-09-08 | United Aircraft Products, Inc. | Bootstrap reservoir |
US4906166A (en) * | 1987-11-04 | 1990-03-06 | Sundstrand Corporation | Liquid coolant circulating system employing intergrated pump/accumulator |
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2010
- 2010-04-15 US US12/760,723 patent/US20110253346A1/en not_active Abandoned
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2017
- 2017-05-26 US US15/606,790 patent/US20170261267A1/en not_active Abandoned
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US4510893A (en) * | 1982-07-15 | 1985-04-16 | Bayerische Motoren Werke Ag | Cooling circuit for internal combustion engines |
US5947375A (en) * | 1996-07-22 | 1999-09-07 | Matsushita Electric Industrial Co., Ltd. | Liquid heating and circulating apparatus for use in an automotive vehicle |
US6871670B2 (en) * | 2002-05-29 | 2005-03-29 | Advics Co., Ltd. | Metal bellows accumulator |
US20100319902A1 (en) * | 2009-06-19 | 2010-12-23 | Wan Ching Chou | Auxiliary apparatus for vehicle water tank |
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US9086154B2 (en) | 2013-04-04 | 2015-07-21 | Hamilton Sundstrand Corporation | Ball shaft for a liquid coolant valve |
US20160366786A1 (en) * | 2015-06-10 | 2016-12-15 | Cooler Master Co., Ltd. | Liquid supply mechanism and liquid cooling system |
US9992910B2 (en) | 2015-06-11 | 2018-06-05 | Cooler Master Co., Ltd. | Liquid supply mechanism and liquid cooling system |
US20180283284A1 (en) * | 2017-04-03 | 2018-10-04 | Hamilton Sundstrand Corporation | Aircraft fluid control system having a pressure sensor |
US10465612B2 (en) * | 2017-04-03 | 2019-11-05 | Hamilton Sundstrand Corporation | Aircraft fluid control system having a pressure sensor |
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US20170261267A1 (en) | 2017-09-14 |
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