US20130048134A1 - Stagnant Fuel Thermal Insulation System - Google Patents
Stagnant Fuel Thermal Insulation System Download PDFInfo
- Publication number
- US20130048134A1 US20130048134A1 US13/217,523 US201113217523A US2013048134A1 US 20130048134 A1 US20130048134 A1 US 20130048134A1 US 201113217523 A US201113217523 A US 201113217523A US 2013048134 A1 US2013048134 A1 US 2013048134A1
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- United States
- Prior art keywords
- fluid
- fluid line
- volume
- fuel
- container
- 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.)
- Abandoned
Links
- 239000000446 fuel Substances 0.000 title claims description 73
- 238000009413 insulation Methods 0.000 title claims description 68
- 239000012530 fluid Substances 0.000 claims abstract description 462
- 238000000034 method Methods 0.000 claims abstract description 33
- 239000006260 foam Substances 0.000 claims description 72
- 239000002828 fuel tank Substances 0.000 claims description 58
- 239000011148 porous material Substances 0.000 claims description 29
- 238000004519 manufacturing process Methods 0.000 claims description 16
- 238000012546 transfer Methods 0.000 claims description 10
- 230000000717 retained effect Effects 0.000 claims description 9
- 230000008569 process Effects 0.000 description 12
- 239000000463 material Substances 0.000 description 9
- 238000010586 diagram Methods 0.000 description 6
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- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
- 239000004593 Epoxy Substances 0.000 description 1
- 101150032569 Grpr gene Proteins 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 239000002826 coolant Substances 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
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- 230000000694 effects Effects 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 239000012212 insulator Substances 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 230000008520 organization Effects 0.000 description 1
- 229920001021 polysulfide Polymers 0.000 description 1
- 239000005077 polysulfide Substances 0.000 description 1
- 150000008117 polysulfides Polymers 0.000 description 1
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Images
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
- F17D—PIPE-LINE SYSTEMS; PIPE-LINES
- F17D1/00—Pipe-line systems
- F17D1/08—Pipe-line systems for liquids or viscous products
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D37/00—Arrangements in connection with fuel supply for power plant
- B64D37/34—Conditioning fuel, e.g. heating
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
- F16L59/00—Thermal insulation in general
- F16L59/02—Shape or form of insulating materials, with or without coverings integral with the insulating materials
- F16L59/021—Shape or form of insulating materials, with or without coverings integral with the insulating materials comprising a single piece or sleeve, e.g. split sleeve, two half sleeves
- F16L59/022—Shape or form of insulating materials, with or without coverings integral with the insulating materials comprising a single piece or sleeve, e.g. split sleeve, two half sleeves with a single slit
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
- F16L59/00—Thermal insulation in general
- F16L59/14—Arrangements for the insulation of pipes or pipe systems
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T137/00—Fluid handling
- Y10T137/2496—Self-proportioning or correlating systems
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49826—Assembling or joining
Definitions
- Aircraft are complex structures containing many different systems.
- an aircraft may include an airframe that provides support for various systems. These systems may include, for example, without limitation, a propulsion system, an electrical system, an environmental system, a hydraulic system, a fuel system, and other suitable types of systems. Further, many electrical lines and fluid lines for these and other systems are also present in an aircraft. For example, an aircraft may have several miles of electrical and fluid lines.
- the phrase “at least one of”, when used with a list of items, means different combinations of one or more of the listed items may be used and only one of each item in the list may be needed.
- “at least one of item A, item B, and item C” may include, for example, without limitation, item A or item A and item B. This example also may include item A, item B, and item C, or item B and item C.
- Structure 220 is configured to be placed around one or more of number of fluid lines 202 .
- fluid line 224 is an example of one of number of fluid lines 202 in container 204 .
- structure 220 may be configured to be placed around fluid line 224 in container 204 .
- porous material 230 is also configured to allow second fluid 214 to flow out of volume 226 of porous material 230 .
- second fluid 214 may drain out of volume 226 of porous material 230 as the level of second fluid 214 in container 204 lowers.
- an apparatus comprises a structure configured to be placed around a fluid line.
- the structure is configured to reduce the flow of fluid in a volume within the structure. This reduction of flow of fluid provides a substantially stagnant pool of fluid adjacent to the fluid line. This substantially stagnant pool of fluid insulates the fluid line.
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Health & Medical Sciences (AREA)
- Public Health (AREA)
- Water Supply & Treatment (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
- Thermal Insulation (AREA)
Abstract
A method and apparatus comprising a structure. The structure is configured to be placed around a fluid line in a container that is configured to hold a fluid. The structure is further configured to reduce a flow of the fluid within a volume of the structure such that the fluid in the volume insulates the fluid line.
Description
- 1. Field
- The present disclosure relates generally to insulating systems and in particular to insulating fluid lines in an aircraft. Still more particularly, the present disclosure relates to a method and apparatus for insulating hydraulic fluid in a fluid line within a fuel tank of an aircraft.
- 2. Background
- Aircraft are complex structures containing many different systems. For example, an aircraft may include an airframe that provides support for various systems. These systems may include, for example, without limitation, a propulsion system, an electrical system, an environmental system, a hydraulic system, a fuel system, and other suitable types of systems. Further, many electrical lines and fluid lines for these and other systems are also present in an aircraft. For example, an aircraft may have several miles of electrical and fluid lines.
- In one illustrative example, a fluid line for a hydraulic system may carry a hydraulic fluid. This fluid line may extend through the wing of an aircraft to provide hydraulic fluid to various components in the aircraft, such as control surfaces. For example, the hydraulic fluid may be used to operate control surfaces, such as flaps and ailerons, and other components, such as landing gear, as well as other suitable types of components.
- Fluids carried by the different fluid lines in an aircraft may include fuel, hydraulic fluid, water, and other suitable fluids. These different types of fluids have different temperature ranges that are desired for operation. For example, operating different devices with hydraulic fluid in a hydraulic system may require the hydraulic fluid to flow through a fluid line in the hydraulic system with a desired level of pressure. If the temperature of the hydraulic fluid falls out of a desired range, then the hydraulic fluid may not flow through the fluid line with the desired level of pressure and/or the desired flow rate.
- Insulation systems may be added to the aircraft to maintain a desired temperature range for different fluids flowing through fluid lines in the aircraft. The different types of insulation systems may be more complex, costly, or difficult to use than desired.
- Therefore, it would be advantageous to have a method and apparatus that takes into account at least some of the issues discussed above as well as possibly other issues.
- In one advantageous embodiment, an apparatus comprises a structure. The structure is configured to be placed around a fluid line in a container that is configured to hold a fluid. The structure is further configured to reduce a flow of the fluid within a volume of the structure such that the fluid in the volume insulates the fluid line.
- In another advantageous embodiment, a fluid line insulation system for an aircraft comprises a structure. The structure is configured to be placed around a fluid line in a fuel tank of the aircraft that is configured to hold fuel. The structure is further configured to reduce a flow of the fuel in a volume within the structure such that a transfer of heat between a fluid in the fluid line and the fuel in the fuel tank outside of the structure is reduced.
- In yet another advantageous embodiment, a method for insulating a fluid line is provided. A structure is positioned around the fluid line. The structure is configured to retain a fluid within a volume of the structure. A flow of the fluid is reduced within the volume of the structure such that the fluid within the volume of the structure insulates the fluid line.
- The features, functions, and advantages can be achieved independently in various embodiments of the present disclosure or may be combined in yet other embodiments in which further details can be seen with reference to the following description and drawings.
- The novel features believed characteristic of the advantageous embodiments are set forth in the appended claims. The advantageous embodiments, however, as well as a preferred mode of use, further objectives, and advantages thereof, will best be understood by reference to the following detailed description of an advantageous embodiment of the present disclosure when read in conjunction with the accompanying drawings, wherein:
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FIG. 1 is an illustration of an aircraft in accordance with an advantageous embodiment; -
FIG. 2 is an illustration of an insulation system in the form of a block diagram in accordance with an advantageous embodiment; -
FIG. 3 is an illustration of an insulation system for a fluid line in accordance with an advantageous embodiment; -
FIG. 4 is an illustration of another type of insulation system in accordance with an advantageous embodiment; -
FIG. 5 is an illustration of another insulation system in accordance with an advantageous embodiment; -
FIG. 6 is an illustration of an interior view of a fuel tank in accordance with an advantageous embodiment; -
FIG. 7 is an illustration of an interior view of another fuel tank in accordance with an advantageous embodiment; -
FIG. 8 is an illustration of a changing level of fluid inside a container in accordance with an advantageous embodiment; -
FIG. 9 is another illustration of a changing level of fluid inside a container in accordance with an advantageous embodiment; -
FIG. 10 is another illustration of a changing level of fluid inside a container in accordance with an advantageous embodiment; -
FIG. 11 is an illustration for a process for insulating a fluid line in accordance with an advantageous embodiment; -
FIG. 12 is another illustration for a process for insulating a fluid line in accordance with an advantageous embodiment; -
FIG. 13 is another illustration for a process for insulating a fluid line in accordance with an advantageous embodiment; -
FIG. 14 is another illustration for a process for insulating a fluid line in accordance with an advantageous embodiment; -
FIG. 15 is an illustration of a flowchart of a process for insulating a fluid line in accordance with an advantageous embodiment; -
FIG. 16 is an illustration of an aircraft manufacturing and service method in accordance with an advantageous embodiment; and -
FIG. 17 is an illustration of an aircraft which an advantageous embodiment may be implemented. - The different advantageous embodiments recognize and take into account one or more different considerations. For example, the different advantageous embodiments recognize and take into account that a fluid line for a particular system may extend through other systems in an aircraft. For example, without limitation, a fluid line carrying hydraulic fluid may extend through the wing of an aircraft. The fluid line may be connected to various components associated with the wing. These components may include, for example, an aileron, a flap, a landing gear assembly, and other suitable components.
- The different advantageous embodiments recognize and take into account that the fluid line also may extend through a fuel tank in the aircraft. The different advantageous embodiments recognize and take into account that the fuel in the fuel tank may have temperatures as low as about −40 degrees during flight or when the fuel sits within the fuel tank overnight. The different advantageous embodiments recognize and take into account that if the temperature of the hydraulic fluid in the hydraulic line becomes too low, the hydraulic fluid may not flow as desired.
- Additionally, the different advantageous embodiments recognize and take into account that one solution may be to use fluid lines with a larger diameter. The different advantageous embodiments also recognize and take into account that another solution may be to include structures that may fill with fluid to provide an insulator. In these examples, the fluid may be fuel in the fuel tank. However, the different advantageous embodiments recognize and take into account that using fluid lines with a larger diameter and/or structures that may fill with fuel may reduce the amount of usable fuel held within the fuel tank.
- Thus, the different advantageous embodiments provide a method and apparatus for insulating fluid lines. In one advantageous embodiment, an apparatus comprises a structure configured to be placed around a fluid line. The structure is configured to reduce the flow of fluid in a volume within the structure. This reduction of the flow of fluid is such that the fluid in the volume insulates the fluid line.
- In particular, this reduction of the flow of the fluid reduces convective currents in the fluid around the fluid line. This reduction of convective currents in the fluid reduces the transfer of heat from a second fluid flowing in the fluid line to the fluid outside of the fluid line.
- With reference now to the figures and, in particular, with reference to
FIG. 1 , an illustration of an aircraft is depicted in accordance with an advantageous embodiment. In this illustrative example,aircraft 100 is an example of one platform in which the different advantageous embodiments may be implemented. As depicted,aircraft 100 haswing 102 andwing 104 attached tofuselage 106.Aircraft 100 includes wing mountedengine 108, wing mountedengine 110, andtail 112. - Further, in this illustrative example,
aircraft 100 hashydraulics system 114 andfuel system 116.Fuel system 116 includesfuel tanks 118 located withinwing 102 andwing 104 andfuel lines 120 withinwing 102 andwing 104.Hydraulics system 114 includes hydraulicfluid lines 122 also withinwing 102 andwing 104. As depicted,hydraulic fluid lines 122 extend throughfuel tanks 118. - In this illustrative example,
fuel tanks 118 are configured to hold fuel foraircraft 100. The fuel infuel tanks 118 may have a temperature that is different from the temperature of hydraulic fluid flowing through hydraulic fluid lines 122. For example, the fuel may have a temperature of about minus 40 degrees Fahrenheit. As a result, fuel infuel tanks 118 may change the temperature of the hydraulic fluid. In one advantageous embodiment, an insulation system is provided that may be used to insulatehydraulic fluid lines 122 inhydraulics system 114. In particular, the insulation system may reduce a transfer of heat between the hydraulic fluid inhydraulic fluid lines 122 and the fuel infuel tanks 118. This type of insulation is referred to as thermal insulation. - With reference now to
FIG. 2 , an illustration of an insulation system in the form of a block diagram is depicted in accordance with an advantageous embodiment. In these illustrative examples,insulation system 200 may be used to insulate number offluid lines 202. As used herein, a number of items means one or more items. For example, a number of fluid lines means one or more fluid lines. - In one illustrative example, number of
fluid lines 202 is located inside ofcontainer 204. Number offluid lines 202 andcontainer 204 may be located inplatform 206. In these illustrative examples,platform 206 takes the form ofaircraft 208. Further, in one illustrative example, number offluid lines 202 may be implemented inhydraulics system 210 inaircraft 208.Hydraulics system 114 inaircraft 100 inFIG. 1 may be an example of one implementation forhydraulics system 210 inaircraft 208. - As depicted, number of
fluid lines 202 is configured to carryfirst fluid 212. When number offluid lines 202 is inhydraulics system 210,first fluid 212 takes the form ofhydraulic fluid 211. In other illustrative examples,first fluid 212 may take the form of water, air, a gas, a coolant, or some other suitable type of fluid. - Further,
container 204 is configured to holdsecond fluid 214. In one illustrative example,container 204 may take the form offuel tank 216 inaircraft 208 in these illustrative examples.Fuel tanks 118 inFIG. 1 may be an example of one implementation forfuel tank 216. Whencontainer 204 isfuel tank 216,second fluid 214 takes the form offuel 218. - In these illustrative examples,
insulation system 200 is configured to insulate number offluid lines 202 inside ofcontainer 204. As depicted,insulation system 200 includes at least one ofstructure 220 and retainingsystem 222. - As used herein, the phrase “at least one of”, when used with a list of items, means different combinations of one or more of the listed items may be used and only one of each item in the list may be needed. For example, “at least one of item A, item B, and item C” may include, for example, without limitation, item A or item A and item B. This example also may include item A, item B, and item C, or item B and item C.
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Structure 220 is configured to be placed around one or more of number offluid lines 202. For example,fluid line 224 is an example of one of number offluid lines 202 incontainer 204. In one illustrative example,structure 220 may be configured to be placed aroundfluid line 224 incontainer 204. - When
second fluid 214 is present incontainer 204,structure 220 may be immersed insecond fluid 214, depending on the level ofsecond fluid 214 withincontainer 204. Whenstructure 220 is at least partially immersed insecond fluid 214 incontainer 204,structure 220 retainssecond fluid 214. In particular,structure 220 retainssecond fluid 214 withinvolume 226 ofstructure 220. - In these illustrative examples,
structure 220 may have a shape configured such that at least a portion ofsecond fluid 214 withinvolume 226 ofstructure 220 and/or at least a portion ofstructure 220 is in direct contact withfluid line 224. This direct contact may occur whenstructure 220 is placed aroundfluid line 224 and at least partially immersed insecond fluid 214 incontainer 204. - Further, when
second fluid 214 is present withinvolume 226 ofstructure 220,second fluid 214 insulatesfluid line 224. In this manner,second fluid 214 may have a secondary purpose in addition to its primary purpose incontainer 204. - For example, when
second fluid 214 takes the form offuel 218, the primary purpose ofsecond fluid 214 is additional fuel for the operation ofaircraft 208.Structure 220 may take advantage of the presence ofsecond fluid 214 withincontainer 204 and usesecond fluid 214 for the secondary purpose of insulatingfluid line 224. - For example, when
second fluid 214 incontainer 204 isfuel 218 having a temperature of about minus 40 degrees Fahrenheit,structure 220 is configured to holdsecond fluid 214 withinvolume 226 such thatsecond fluid 214 involume 226 ofstructure 220 insulatesfluid line 224 to maintain a desired temperature forfluid line 224. - Additionally,
structure 220 is configured such thatsecond fluid 214 may flow out ofvolume 226 when the level ofsecond fluid 214 incontainer 204 is lowered. In this manner, substantially all ofsecond fluid 214 may flow out ofvolume 226 ofstructure 220 whenstructure 220 is no longer immersed insecond fluid 214 incontainer 204. As a result,second fluid 214 involume 226 may be usable for its primary purpose. - As one illustrative example, when
second fluid 214 isfuel 218 insidecontainer 204 in the form offuel tank 216 insideaircraft 208,fuel 218 may flow intovolume 226 ofstructure 220 whilefuel tank 216 is being refueled. Further,fuel 218 may be retained withinvolume 226 during operation ofaircraft 208. As the level offuel 218 withinfuel tank 216 lowers during operation ofaircraft 208,fuel 218 withinvolume 226 may flow out ofvolume 226 ofstructure 220 and into the rest offuel 218 infuel tank 216. - In this manner,
fuel 218 that is held withinvolume 226 ofstructure 220 may be used both for insulatingfluid line 224 andoperating aircraft 208. As a result, additional amounts offuel 218 do not need to be added tofuel tank 216 ofaircraft 208 for the purpose of insulatingfluid line 224. -
Structure 220 is configured to enclose and/or trap a portion ofsecond fluid 214 withinvolume 226 ofstructure 220 such thatsecond fluid 214 insulatesfluid line 224. Further,structure 220 may reduce a flow of this portion ofsecond fluid 214 withinvolume 226 ofstructure 220. This flow may be measured as, for example, a flow rate. The flow ofsecond fluid 214 withinvolume 226 may be caused by a convective current throughsecond fluid 214 incontainer 204. In particular, the flow ofsecond fluid 214 involume 226 ofstructure 220 may be reduced such thatsecond fluid 214 involume 226 aroundfluid line 224 provides desired level ofinsulation 225. - In one illustrative example, this reduction in the flow may be such that the flow of
second fluid 214 is substantially stagnant. In these illustrative examples, when a fluid is substantially stagnant, the flow of the fluid may be substantially absent and/or slow enough to provide desired level ofinsulation 225 forfluid line 224. For example, when the flow ofsecond fluid 214 withinvolume 226 is reduced, the transfer of heat between first fluid 212 influid line 224 andsecond fluid 214 outside ofstructure 220 may also be reduced. - In these illustrative examples, when the flow of
second fluid 214 withinvolume 226 is reduced,second fluid 214 insidevolume 226 instructure 220 aroundfluid line 224 reduces the transfer of heat fromfirst fluid 212 tosecond fluid 214 outside ofstructure 220 withincontainer 204. Of course, in other illustrative examples, the flow ofsecond fluid 214 may be reduced such thatsecond fluid 214 insidevolume 226 instructure 220 aroundfluid line 224 reduces the transfer of heat fromsecond fluid 214 outside ofstructure 220 incontainer 204 tofirst fluid 212 insidefluid line 224. -
Structure 220 may take a number of different forms in these illustrative examples. For example, in one illustrative example,structure 220 may take the form ofporous material 230.Porous material 230 may be any material configured to holdsecond fluid 214 withinvolume 226 ofporous material 230.Porous material 230 may be comprised of cells that may be filled with a fluid, such assecond fluid 214. In particular, whenporous material 230 is at least partially immersed insecond fluid 214,second fluid 214 may fill at least part ofvolume 226 withinporous material 230. - Additionally,
porous material 230 may be configured to retainsecond fluid 214 withinvolume 226 such thatsecond fluid 214 has a flow that is slow enough to provide desired level ofinsulation 225 forfluid line 224. For example,second fluid 214 withinvolume 226 ofporous material 230 may be considered substantially stagnant. In this manner, a convective current insecond fluid 214 withinvolume 226 ofporous material 230 may be reduced and/or eliminated to provide desired level ofinsulation 225 forfluid line 224. - In some illustrative examples, the convective current may be tailored to provide desired level of
insulation 225 forfluid line 224. In other words, the type ofporous material 230 used,volume 226 selected forporous material 230, and/or other parameters may be selected such that the convective current insecond fluid 214 is low enough to provide desired level ofinsulation 225 forfluid line 224. - Further, in these illustrative examples,
porous material 230 is also configured to allowsecond fluid 214 to flow out ofvolume 226 ofporous material 230. For example, when a level ofsecond fluid 214 incontainer 204 lowers, less ofporous material 230 may be immersed insecond fluid 214. As a result,second fluid 214 may drain out ofvolume 226 ofporous material 230 as the level ofsecond fluid 214 incontainer 204 lowers. - In one illustrative example,
porous material 230 may take the form offoam 232.Foam 232 may have a matrix structure of cells that allowssecond fluid 214 to flow intofoam 232, fillvolume 226 withinfoam 232, and flow out offoam 232. When used withhydraulics system 210 inaircraft 208,foam 232 may have an open cell structure with about 45 cells per inch and a porosity of about 93 percent. Further, in this illustrative example,foam 232 may have a thickness of about 0.2 inches. - In these illustrative examples,
porous material 230 may be comprised of any material that is configured to allowsecond fluid 214 to flow intovolume 226 ofporous material 230, be retained withinvolume 226 ofporous material 230, and flow out ofvolume 226 ofporous material 230. For example,porous material 230 may be comprised of a material selected from at least one of a foamed polyurethane, a polysulfide, epoxy plastic, a metallic mesh screen, a plastic expandable mesh, a woven fabric, and other suitable types of materials. - Additionally, in other illustrative examples,
structure 220 may take the form oftube 234.Tube 234 is configured to be placed aroundfluid line 224. As one illustrative example,tube 234 hasshape 236 and defineschannel 238. Shape 236 may be selected to allowfluid line 224 to fit withinchannel 238. - In one illustrative example,
shape 236 may be a C-shape, a U-shape, or some other suitable shape that allowschannel 238 to be formed outside of a surface oftube 234. For example, a portion of the surface oftube 234 may be bent inwards oftube 234 to formchannel 238 that is capable of receivingfluid line 224 withinchannel 238. For example,channel 238 may function as a guide forfluid line 224. - In particular,
tube 234 with this type of shape may be comprised of a flexible material that allowstube 234 to be placed aroundfluid line 224 without needing to slide aroundfluid line 224. For example, the material oftube 234 and shape 236 oftube 234 may be selected such thattube 234 may be, for example, clipped or otherwise attached tofluid line 224. - Additionally, with this type of shape,
tube 234 also hasfluid channel 240 insidetube 234.Fluid channel 240 may be configured to allowsecond fluid 214 to flow intovolume 226 withinfluid channel 240. The openings tofluid channel 240 at the ends oftube 234 may be at least partially closed and/or blocked such thatsecond fluid 214 withinvolume 226 influid channel 240 may have a flow that is slow enough to provide desired level ofinsulation 225. - In another illustrative example,
tube 234 may haveshape 236 that allowstube 234 to be placed aroundfluid line 224 from an end offluid line 224.Tube 234 may then be slid down the length offluid line 224 to positiontube 234 with respect tofluid line 224 to provide desired level ofinsulation 225 forfluid line 224. - In some illustrative examples,
structure 220 may be positioned with respect tofluid line 224 usingretaining system 222. Retainingsystem 222 may include, for example,cover 242. Cover 242 may be any structure or material configured to holdstructure 220 in a desired position aroundfluid line 224. - For example, cover 242 may take the form of a plastic skin that may be wrapped around
porous material 230 onceporous material 230 has been placed aroundfluid line 224. This plastic skin may holdporous material 230 in substantially the same position aroundfluid line 224. - In another illustrative example, retaining
system 222 may include number ofclamps 244. Number ofclamps 244 may be configured to holdstructure 220 aroundfluid line 224. For example, number ofclamps 244 may be configured to holdporous material 230 in place aroundstructure 220. In some illustrative examples, number ofclamps 244 may be placed aroundfluid line 224 and configured to substantially preventstructure 220 from moving along a length offluid line 224. - In these illustrative examples,
second fluid 214 in the form offuel 218 has desiredthermal conductivity 246. Desiredthermal conductivity 246 may be low enough such that the transfer of heat between first fluid 212 influid line 224 andsecond fluid 214 involume 226 ofstructure 220 is reduced and/or eliminated. Of course, in other illustrative examples,second fluid 214 may be some other suitable type of fluid selected such that the thermal conductivity ofsecond fluid 214 is desiredthermal conductivity 246.Second fluid 214 may be selected such that the thermal conductivity ofsecond fluid 214 provides desired level ofinsulation 225 forfluid line 224. - The illustration of
insulation system 200 inFIG. 2 is not meant to imply physical or architectural limitations to the manner in which an advantageous embodiment may be implemented. Other components in addition to and/or in place of the ones illustrated may be used. Some components may be unnecessary. Also, the blocks are presented to illustrate some functional components. One or more of these blocks may be combined and/or divided into different blocks when implemented in an advantageous embodiment. - For example, in other illustrative examples,
insulation system 200 may include additional structures in addition to, and/or in place of,structure 220 for insulating number offluid lines 202 incontainer 204. In some illustrative examples,structure 220 may be configured to insulate more than one fluid line in number offluid lines 202. For example,structure 220 may be placed aroundfluid line 224 and another fluid line, as well as around a joint between these two fluid lines. - Further,
platform 206 may take other forms other thanaircraft 208. For example,platform 206 may be selected from one of a mobile platform, a stationary platform, a land-based structure, an aquatic-based structure, a space-based structure, an aircraft, an unmanned aerial vehicle, a helicopter, a submarine, a bus, a personnel carrier, a tank, a train, an automobile, a spacecraft, a space station, a satellite, a surface ship, a power plant, a dam, a manufacturing facility, a piece of equipment, a building and/or some other suitable type of platform. - In particular,
platform 206 may be any platform that requires insulation of a first type of fluid in a number or fluid lines from thermal effects in response to the immersion of the number of fluid lines in a second type of fluid. For example,platform 206 may be any piece of equipment or machinery in which fluid lines are used. - The different components shown in FIGS. 1 and 3-14 may be combined with components in
FIG. 2 , used with components inFIG. 2 , or a combination of the two. Additionally, some of the components in FIGS. 1 and 3-14 may be illustrative examples of how components shown in block form inFIG. 2 can be implemented as physical structures. - With reference now to
FIG. 3 , an illustration of an insulation system for a fluid line is depicted in accordance with an advantageous embodiment. In this illustrative example,insulation system 300 is configured to insulatefluid line 302.Fluid line 302 is an example one implementation forfluid line 224 inFIG. 2 .Fluid line 302 haschannel 304 that may be configured to carry a fluid, such asfirst fluid 212 inFIG. 2 . -
Insulation system 300 is an example of one implementation forinsulation system 200 inFIG. 2 . As depicted,insulation system 300 comprisesstructure 306 and retainingsystem 308. In this illustrative example,structure 306 takes the form offoam 310.Foam 310 is an example of one implementation forfoam 232 inFIG. 2 . -
Foam 310 may have a shape that is substantially conformal tofluid line 302. In particular,inner surface 311 offoam 310 is substantially conformal tofluid line 302. In other words, whenfoam 310 is placed aroundfluid line 302, substantially all ofinner surface 311 offoam 310 comes into contact withfluid line 302. - Additionally,
foam 310 is a porous material that may allow a fluid, such assecond fluid 214 inFIG. 2 , to flow intofoam 310 and be retained within cells offoam 310. Whenfoam 310 is placed aroundfluid line 302 andinner surface 311 offoam 310 is in contact withfluid line 302, at least a portion of the fluid retained within the cells offoam 310 is also in contact withfluid line 302. - In this illustrative example, retaining
system 308 takes the form ofsupport structure 312.Support structure 312, in this example, is a spiral-shaped plastic structure configured to wrap aroundfoam 310. In particular,support structure 312 keepsfoam 310 wrapped aroundfluid line 302. Further,support structure 312 holdsfoam 310 in its current position aroundfluid line 302. - With reference now to
FIG. 4 , an illustration of another type of insulation system is depicted in accordance with an advantageous embodiment. In this illustrative example,insulation system 400 includesstructure 401.Structure 401 takes the form oftube 402.Tube 402 is an example of one implementation fortube 234 inFIG. 2 . - As depicted,
tube 402 hasshape 404.Shape 404 is a C-shape in this illustrative example. Shape 404 fortube 402forms channel 406 andfluid channel 408.Channel 406 is configured to receive a fluid line, such asfluid line 302 inFIG. 3 . For example,tube 402 may be comprised of a material that has a flexibility that allowstube 402 to be placed around the fluid line. In particular, the fluid line may be received bychannel 406 throughopening 412. As depicted, whentube 402 is placed around the fluid line,inner surface 413 ofchannel 406 comes into contact with the fluid line. - Further,
fluid channel 408 is located inside oftube 402.Fluid channel 408 is configured to carry a fluid, such assecond fluid 214 inFIG. 2 . As one illustrative example,fluid channel 408 may allow fuel in a fuel tank to flow intofluid channel 408 whentube 402 is placed around a fluid line in the fuel. In this example, whentube 402 is placed around the fluid line,end 414 and/or end 416 may be at least partially closed or blocked such that the flow of the fuel is reduced to provide a desired level of insulation for the fluid line. - With reference now to
FIG. 5 , an illustration of an insulation system is depicted in accordance with an advantageous embodiment. In this illustrative example,insulation system 500 includesstructure 502.Structure 502 takes the form oftube 504 in this depicted example.Tube 504 is an example of one implementation fortube 234 inFIG. 2 . - As depicted,
tube 504 hasshape 506.Shape 506 is configured to allow a fluid line, such asfluid line 302 inFIG. 3 , to be placed withinchannel 508 oftube 504. For example, end 510 or end 512 oftube 504 may be placed at an end of the fluid line and slid down the length of the fluid line to a desired position. - In this illustrative example,
tube 504 has convolutedshape 514.Convoluted shape 514 comprises a series of coils or folds intube 504.Convoluted shape 514 providestube 504 with flexibility. In this manner,tube 504 may be placed around a fluid line and slid down the length of the fluid line, even around bends and/or turns in the fluid line. - When
tube 504 is placed around the fluid line, a volume is formed between an inner surface oftube 504 and the fluid line. In one illustrative example, fuel in a fuel tank may flow into this volume whentube 504 is placed around a fluid line in the fuel. In this depicted example, whentube 504 is placed around the fluid line,end 510 and/or end 512 may be at least partially blocked such that the flow of the fuel is reduced to provide a desired level of insulation for the fluid line. However, end 510 and/or end 512 also may be left at least partially unblocked such that the fuel may flow into and out of the volume. - The illustrations of
insulation system 300 inFIG. 3 ,insulation system 400 inFIG. 4 , andinsulation system 500 inFIG. 5 are not meant to imply physical or architectural limitations to the manner in which an advantageous embodiment may be implemented. For example, in other illustrative examples, a different type of retaining system may be used to holdfoam 310 inFIG. 3 in place aroundfluid line 302. For example, retainingsystem 308 may take the form of a plastic cover instead ofsupport structure 312. - With reference now to
FIG. 6 , an illustration of an interior view of a fuel tank is depicted in accordance with an advantageous embodiment. In this illustrative example, an interior view offuel tank 600 is depicted.Fuel tank 600 is an example of one implementation forfuel tank 216 inFIG. 2 .Fuel tank 600 is configured to hold fuel for an aircraft, such asaircraft 208 inFIG. 2 . - As depicted, a portion of
hydraulics system 602 is located insidefuel tank 600. In particular,fluid line 604 andfluid line 606 ofhydraulics system 602 are located insidefuel tank 600.Fluid line 604 andfluid line 606 are configured to carry hydraulic fluid. - In this illustrative example,
insulation system 608 has been placed aroundportion 609 offluid line 606. As depicted,insulation system 608 includesstructure 610 and retainingsystem 612.Structure 610 takes the form offoam 614 in this illustrative example. As depicted,foam 614 coversportion 609 offluid line 606, which includescoupling 611. In this manner,foam 614 provides insulation forportion 609 offluid line 606. - As illustrated, retaining
system 612 includesspiral structure 616 andclamp 618.Spiral structure 616 is configured to holdfoam 614 in place aroundfluid line 606. Further,clamp 618 preventsfoam 614 from moving in the direction ofarrow 620 aroundfluid line 606. In this manner, retainingsystem 612 holdsfoam 614 in place aroundportion 609 offluid line 606 to provide a desired level of insulation aroundportion 609 offluid line 606. - Although, in this illustrative example,
insulation system 608 has only been placed aroundportion 609 offluid line 606, additional structures, such asstructure 610 may be placed around other portions offluid line 606 to insulate these other portions offluid line 606. Further, structures similar to structure 610 may also be placed aroundfluid line 604. - With reference now to
FIG. 7 , an illustration of an interior view of another fuel tank is depicted in accordance with an advantageous embodiment. In this illustrative example, an interior view offuel tank 700 is depicted.Fuel tank 700 is an example of one implementation forfuel tank 216 inFIG. 2 .Fuel tank 700 is configured to hold fuel for an aircraft, such asaircraft 208 inFIG. 2 . - As depicted, a portion of
hydraulics system 702 is located insidefuel tank 700.Fluid line 704 inhydraulics system 702 is located insidefuel tank 700.Fluid line 704 is configured to carry hydraulic fluid. - In this illustrative example,
insulation system 706 has been placed aroundfluid line 704. As depicted,insulation system 706 includestubes shape 404 inFIG. 4 . - In this illustrative example, not all of
fluid line 704 is covered bytubes fuel tank 700 may flow into fluid channels (not shown) insidetubes fluid line 704. Although not all offluid line 704 is covered bytubes fluid line 704. - As depicted, clamps 720, 722, and 724 have been placed around
fluid line 704. In some illustrative examples, these clamps may be part ofinsulation system 706. For example, clamps 720, 722, and 724 may be part of a retaining system configured to preventtubes fluid line 704. In other illustrative examples, clamps 720, 722, and 724 may be part ofhydraulics system 702. When these clamps are part ofhydraulics system 702, the lengths oftubes - With reference now to
FIGS. 8-10 , illustrations of a changing level of fluid inside a container are depicted in accordance with an advantageous embodiment. In these illustrative examples,container 800 is an example of one implementation forcontainer 204 inFIG. 2 .Container 800 holdsfluid 802.Fluid 802 is an example of one implementation forsecond fluid 214 inFIG. 2 . - With reference now to
FIG. 8 ,fluid line 804 is present insidecontainer 800.Fluid line 804 is configured to carry a fluid, such as hydraulic fluid.Insulation system 806 has been placed aroundfluid line 804 to insulatefluid line 804. In this illustrative example,insulation system 806 may be implemented usinginsulation system 300 fromFIG. 3 . In particular,insulation system 806 includesfoam 808 andsupport structure 810. - As depicted, fluid 802 in
container 800 is atlevel 812. When fluid 802 is atlevel 812,foam 808 is completely immersed influid 802. With this type of immersion offoam 808 influid 802, some offluid 802 insidecontainer 800 flows into the cells offoam 808. In this manner,fluid 802 fills at least a part of the volume offoam 808. Further,foam 808 is configured to retainfluid 802 and reduce a flow offluid 802 in the volume offoam 808 to provide a desired level of insulation forfluid line 804. - With reference now to
FIG. 9 , the level offluid 802 incontainer 800 has been lowered fromlevel 812 inFIG. 8 tolevel 900. When fluid 802 is atlevel 900,foam 808 is only partially immersed influid 802 incontainer 800. In these illustrative examples, as the level offluid 802 incontainer 800 is lowered fromlevel 812 inFIG. 8 tolevel 900 inFIG. 9 , the portion offoam 808 not immersed influid 802 may increase. - As the portion of
foam 808 not immersed influid 802 increases, fluid 802 retained infoam 808 flows out offoam 808. In particular, fluid 802 retained in the upper portion offoam 808 that is no longer immersed influid 802 incontainer 800 may flow into the lower portion offoam 808 and/or out offoam 808 and intofluid 802 incontainer 800.Fluid 802 that flows fromfoam 808 and intofluid 802 remains usable for the primary purpose for whichfluid 802 was intended. - With reference now to
FIG. 10 , the level offluid 802 incontainer 800 has been lowered fromlevel 900 inFIG. 9 tolevel 1000. When fluid 802 is atlevel 1000,foam 808 is no longer immersed influid 802 incontainer 800. As a result, any offluid 802 that is still retained withinfoam 808 drains out offoam 808 intofluid 802 that is incontainer 800. In this manner, substantially all offluid 802 that flows intofoam 808 remains usable for its primary purpose. - With reference now to
FIGS. 11-14 , illustrations for a process for insulating a fluid line are depicted in accordance with an advantageous embodiment. These steps may be implemented to insulate a fluid line, such asfluid line 224 inFIG. 2 , using an insulation system, such asinsulation system 200 inFIG. 2 . - Turning now to
FIG. 11 , components used to insulate a fluid line are depicted in accordance with an advantageous embodiment. In this illustrative example,fluid line 1100 may be insulated usingfoam 1102,cover 1104,clamp 1106, andclamp 1108. -
Foam 1102 is an example of one implementation forfoam 232 inFIG. 2 .Cover 1104 is an example of one implementation forcover 242 inFIG. 2 . Further,clamp 1106 andclamp 1108 are an example of one implementation for number ofclamps 244 inFIG. 2 . When assembled,foam 1102,cover 1104,clamp 1106, andclamp 1108 may form an insulation system forfluid line 1100. - With reference now to
FIG. 12 ,foam 1102 has been placed aroundfluid line 1100. As depicted,foam 1102 has slit 1200 that allowsfoam 1102 to be placed aroundfluid line 1100. For example,foam 1102 may receivefluid line 1100 throughslit 1200. - In
FIG. 13 , a portion ofcover 1104 has been wrapped aroundfoam 1102. As depicted,cover 1104 hashelical shape 1300.Helical shape 1300 forcover 1104 allowscover 1104 to be wrapped aroundfoam 1102.Cover 1104 is wrapped aroundfoam 1102 to holdfoam 1102 in place aroundfluid line 1100. Further,cover 1104 wraps aroundfoam 1102 such thatfluid line 1100 does not slip out ofslit 1200. - Turning now to
FIG. 14 ,cover 1104 has been completely wrapped aroundfoam 1102. Further,clamp 1106 andclamp 1108 have been placed aroundfluid line 1100 atend 1400 andend 1402, respectively, offoam 1102.Clamp 1106 andclamp 1108hold foam 1102 in place aroundfluid line 1100 such thatfoam 1102 does not move in a direction along the length offluid line 1100. - With reference now to
FIG. 15 , an illustration of a flowchart of a process for insulating a fluid line is depicted in accordance with an advantageous embodiment. The process illustrated inFIG. 15 may be implemented usinginsulation system 200 inFIG. 2 . For example,insulation system 200 may be used to insulatefluid line 224 inFIG. 2 . - The process begins by collecting a fluid within a volume of a structure surrounding a fluid line (operation 1500). The fluid in the structure may be collected from fluid in a container in which the fluid line is located. This fluid may be, for example, fuel. The structure may collect the fluid by allowing the fluid to flow into the volume of the structure.
- Thereafter, the process reduces a flow of the fluid within the volume of the structure such that the fluid within the volume of the structure insulates the fluid line (operation 1502), with the process terminating thereafter. In
operation 1502, the flow of the fluid within the volume of the structure is reduced such that a desired level of insulation is provided for the fluid line. For example, in some cases, the flow of the fluid in the volume of the structure is reduced such that the fluid is substantially stagnant within the volume of the structure. - The flowcharts and block diagrams in the different depicted embodiments illustrate the architecture, functionality, and operation of some possible implementations of apparatus and methods in an advantageous embodiment. In this regard, each block in the flowcharts or block diagrams may represent a module, a segment, a function, and/or a portion of an operation or step. For example, one or more of the blocks may be implemented as program code, in hardware, or a combination of the program code and hardware. When implemented in hardware, the hardware may, for example, take the form of integrated circuits that are manufactured or configured to perform one or more operations in the flowcharts or block diagrams.
- In some alternative implementations of an advantageous embodiment, the function or functions noted in the block may occur out of the order noted in the figures. For example, in some cases, two blocks shown in succession may be executed substantially concurrently, or the blocks may sometimes be performed in the reverse order, depending upon the functionality involved. Also, other blocks may be added in addition to the illustrated blocks in a flowchart or block diagram.
- With reference to the different advantageous embodiments, an example of the reduction in the transfer of heat between a first fluid in a fluid line and a second fluid outside of the fluid line when using a structure, such as
structure 220 fromFIG. 2 is described below. In this illustrative example,hydraulic fluid 211 is flowing throughfluid line 224 fromFIG. 2 .Fluid line 224 is located infuel tank 216 and is fully immersed infuel 218 fromFIG. 2 . - In this illustrative example, the following assumptions are made:
- L=0.375 in=0.375 inches
- Tf=−40° F.=−40 degrees Fahrenheit
- Tls=0° F.=0° F.=0 degrees Fahrenheit
- where, L is the outside diameter of
fluid line 224, Tf is the temperature offuel 218, and Tls is the temperature of the outer surface offluid line 224. - Further, the following assumptions are made about the characteristics of
fuel 218. - Fuel Characteristics:
-
- where Cp is specific heat, k is thermal conductivity, v is kinematic viscosity, β is the volumetric coefficient of expansion, and ρ is the mass density for
fuel 218. - Heat loss from the outer surface of
fluid line 224 to fuel 218 infuel tank 216 occurs in response to convective currents at the outer surface offluid line 224. The amount of heat loss per foot length offluid line 224 is given by the following equation: -
Q=h(T S −T f)πd, where (1) -
h=Nu(k/d), (2) -
Nu=0.53(GrPr)0.25, (3) -
Pr=C p vρ/k, (4) -
Gr d =[L 3 gβρ 2(T s −T f)]/μ2, and (5) - where Q is heat loss, h is the Film coefficient, Nu is the Nusselt Equation, π is the number pi, d is the diameter at which convective currents in
fuel 218 infuel tank 216 are encountered, Gr is the Grashof number, Pr is the Prandtl number, g is gravity, Ts is the temperature of the surface at which convective currents infuel 218 infuel tank 216 are encountered, and μ is the viscosity offuel 218. In this case, d is the outer diameter offluid line 224, L, while Ts is the temperature of the outer surface offluid line 224, Tls. - Given the assumptions listed above, the heat loss from the outer surface of
fluid line 224 to fuel 218 per foot length offluid line 224 is about 126 British Thermal Units per hour-feet (BTU/hr-ft). In other words, about 126 British Thermal Units of heat are transferred from the outer surface offluid line 224 to fuel 218 infuel tank 216 every hour for each foot in length offluid line 224. - However, when
structure 220 fromFIG. 2 is placed aroundfluid line 224, this heat loss is reduced. In particular,structure 220 reduces the convective currents infuel 218 at the outer surface offluid line 224 such that the heat transferred tofuel 218 infuel tank 216 is reduced. - For example, with
structure 220,fuel 218 is retained withinvolume 226 instructure 220.Fuel 218 involume 226 forms a pool offuel 218 aroundfluid line 224 in which a flow offuel 218 in this pool is reduced. In other words,structure 220 is configured such thatfuel 218 withinvolume 226 is substantially stagnant in this illustrative example. Whenfuel 218 withinvolume 226 instructure 220 aroundfluid line 224 is reduced, the convective currents infuel 218 aroundfluid line 224 are also reduced. As a result, the amount of heat transferred from the outer surface offluid line 224 to fuel 218 withinvolume 226 ofstructure 220 is reduced. In this manner, the heat transferred from the outer surface offluid line 224 to fuel 218 withinfuel tank 216 outside ofstructure 220 is also reduced. - In particular, the amount of heat loss from the outer surface of
fluid line 224 throughstructure 220 is given by the following equation: -
Q=2πL(ΔT)k/ln(OD/ID), (6) - where Q is heat loss, ΔT is the difference between the temperature at the outer surface of
fluid line 224 and the outer surface ofstructure 220, OD is the outer diameter ofstructure 220, and ID is the inner diameter ofstructure 220. In this illustrative example, the inner diameter ofstructure 220 is substantially the same as the outer diameter offluid line 224, L. - When solving for Q in equation (6), the temperature at the outer surface of
fluid line 224 is estimated. Given the above assumptions, the temperature at the outer surface offluid line 224 should be between about 0 degrees Fahrenheit, which is the temperature of the outer surface offluid line 224, and about negative 40 degrees Fahrenheit, which is the temperature offuel 218 infuel tank 216. - This estimated temperature is used to solve for Q in equation (6) as well as Q in equation (1), where d is the outer diameter of
structure 220, OD, and Ts is the temperature at the outer surface ofstructure 220 in equation (1). Further, the estimated temperature is adjusted until the calculated value for Q in equation (6) is substantially the same, within selected tolerances, as the calculated value for Q in equation (1), when d is the outer diameter ofstructure 220, OD, and Ts is the temperature at the outer surface ofstructure 220. - Given the different assumptions made in this example, the heat loss from the surface of
fluid line 224 to fuel 218 infuel tank 216 whenstructure 220 is used is about 23.7 British Thermal Units per hour-feet (BTU/hr-ft). In this manner, usingstructure 220 to provide insulation forfluid line 224 reduces the transfer of heat from the outer surface offluid line 224 intofuel 218 infuel tank 216 by about 81 percent. - Advantageous embodiments of the disclosure may be described in the context of aircraft manufacturing and
service method 1600 as shown inFIG. 16 andaircraft 1700 as shown inFIG. 17 . Turning first toFIG. 16 , an illustration of an aircraft manufacturing and service method is depicted in accordance with an advantageous embodiment. During pre-production, aircraft manufacturing andservice method 1600 may include specification and design 1602 ofaircraft 1700 inFIG. 17 andmaterial procurement 1604.Aircraft 1700 may be an example of one implementation ofaircraft 208 inFIG. 2 . - During production, component and
subassembly manufacturing 1606 andsystem integration 1608 ofaircraft 1700 inFIG. 17 takes place. Thereafter,aircraft 1700 inFIG. 17 may go through certification anddelivery 1610 in order to be placed inservice 1612. - While in
service 1612 by a customer,aircraft 1700 inFIG. 17 is scheduled for routine maintenance andservice 1614, which may include modification, reconfiguration, refurbishment, and other maintenance or service. In these illustrative examples,insulation system 200 fromFIG. 2 may be used to insulate a fluid line for a hydraulics system inaircraft 1700 during at least one of component andsubassembly manufacturing 1606,system integration 1608, and maintenance andservice 1614. - Each of the processes of aircraft manufacturing and
service method 1600 may be performed or carried out by a system integrator, a third party, and/or an operator. In these examples, the operator may be a customer. For the purposes of this description, a system integrator may include, without limitation, any number of aircraft manufacturers and major-system subcontractors; a third party may include, without limitation, any number of vendors, subcontractors, and suppliers; and an operator may be an airline, a leasing company, a military entity, a service organization, and so on. - With reference now to
FIG. 17 , an illustration of an aircraft is depicted in which an advantageous embodiment may be implemented. In this example,aircraft 1700 is produced by aircraft manufacturing andservice method 1600 inFIG. 16 and may includeairframe 1702 with plurality ofsystems 1704 and interior 1706. Examples ofsystems 1704 include one or more ofpropulsion system 1708,electrical system 1710,hydraulic system 1712, andenvironmental system 1714. Any number of other systems may be included. Although an aerospace example is shown, different advantageous embodiments may be applied to other industries, such as the automotive industry. - Apparatuses and methods embodied herein may be employed during at least one of the stages of aircraft manufacturing and
service method 1600 inFIG. 16 . - In one illustrative example, components or subassemblies produced in component and
subassembly manufacturing 1606 inFIG. 16 may be fabricated or manufactured in a manner similar to components or subassemblies produced whileaircraft 1700 is inservice 1612 inFIG. 16 . - As yet another example, one or more apparatus embodiments, method embodiments, or a combination thereof may be utilized during production stages, such as component and
subassembly manufacturing 1606 andsystem integration 1608 inFIG. 16 . One or more apparatus embodiments, method embodiments, or a combination thereof may be utilized whileaircraft 1700 is inservice 1612 and/or during maintenance andservice 1614 inFIG. 16 . The use of a number of the different advantageous embodiments may substantially expedite the assembly of and/or reduce the cost ofaircraft 1700. - Thus, the different advantageous embodiments provide a method and apparatus for insulating fluid lines. In one advantageous embodiment, an apparatus comprises a structure configured to be placed around a fluid line. The structure is configured to reduce the flow of fluid in a volume within the structure. This reduction of flow of fluid provides a substantially stagnant pool of fluid adjacent to the fluid line. This substantially stagnant pool of fluid insulates the fluid line.
- In this manner, the different advantageous embodiments provide a system for insulating fluid lines in a hydraulics system for an aircraft without adding undesired weight to the aircraft. Further, using fuel that is already present in a fuel tank of the aircraft to insulate these fluid lines provides the desired level of thermal insulation for the fluid lines without significantly increasing the weight and/or cost for providing this thermal insulation.
- The description of the different advantageous embodiments has been presented for purposes of illustration and description, and is not intended to be exhaustive or limited to the embodiments in the form disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art. Further, different advantageous embodiments may provide different advantages as compared to other advantageous embodiments. The embodiment or embodiments selected are chosen and described in order to best explain the principles of the embodiments, the practical application, and to enable others of ordinary skill in the art to understand the disclosure for various embodiments with various modifications as are suited to the particular use contemplated.
Claims (20)
1. An apparatus comprising:
a structure configured to be placed around a fluid line in a container that is configured to hold a fluid, wherein the structure is configured to reduce a flow of the fluid within a volume of the structure such that the fluid in the volume insulates the fluid line.
2. The apparatus of claim 1 , wherein the structure is configured to retain the fluid within the volume of the structure when the structure is at least partially immersed in the fluid in the container and wherein retained fluid within the volume of the structure flows out of the volume of the structure as a level of the fluid in the container lowers in a manner that results in less of the volume of the structure being filled with the fluid.
3. The apparatus of claim 1 further comprising:
a retaining system configured to hold the structure around the fluid line.
4. The apparatus of claim 3 , wherein the retaining system comprises:
a cover configured to hold the structure around the fluid line.
5. The apparatus of claim 3 , wherein the retaining system comprises:
a number of clamps configured to reduce movement of the structure along the fluid line.
6. The apparatus of claim 1 , wherein the flow of the fluid that is reduced is caused by a convective current through the fluid in the container.
7. The apparatus of claim 1 , wherein the structure comprises:
a porous material defining the volume, wherein the porous material is configured to reduce the flow of the fluid.
8. The apparatus of claim 7 , wherein the porous material takes a form of a foam.
9. The apparatus of claim 8 , wherein the foam has about 45 cells per inch and a porosity of about 93 percent.
10. The apparatus of claim 8 , wherein the foam has a thickness of about 0.2 inches.
11. The apparatus of claim 1 , wherein the structure comprises:
a tube configured to be placed around the fluid line.
12. The apparatus of claim 1 , wherein the fluid line is configured to carry a hydraulic fluid, the container is a fuel tank, and the fluid in the container is fuel.
13. The apparatus of claim 1 , wherein the structure is configured to maintain a desired temperature for the fluid line when the fluid in the container has a temperature of about minus 40 degrees Fahrenheit.
14. The apparatus of claim 1 further comprising:
the container; and
the fluid line.
15. The apparatus of claim 1 , wherein the fluid line and the container are located in a platform selected from one of a mobile platform, a stationary platform, a land-based structure, an aquatic-based structure, a space-based structure, an aircraft, an unmanned aerial vehicle, a helicopter, a submarine, a bus, a personnel carrier, a tank, a train, an automobile, a spacecraft, a space station, a satellite, a surface ship, a power plant, a dam, a manufacturing facility, a piece of equipment, and a building.
16. A fluid line insulation system for an aircraft comprising:
a structure configured to be placed around a fluid line in a fuel tank of the aircraft that is configured to hold fuel, wherein the structure is configured to reduce a flow of the fuel in a volume within the structure such that a transfer of heat between a fluid in the fluid line and the fuel in the fuel tank outside of the structure is reduced.
17. The fluid line insulation system of claim 16 , wherein the structure is a foam and further comprising:
a retaining system configured to hold the foam around the fluid line.
18. A method for insulating a fluid line, the method comprising:
positioning a structure around the fluid line, wherein the structure is configured to retain a fluid within a volume of the structure; and
reducing a flow of the fluid within the volume of the structure such that the fluid within the volume of the structure insulates the fluid line.
19. The method of claim 18 , wherein the structure and the fluid line are located in a fuel tank and wherein the structure is configured to contact the fluid line when positioned around the fluid line.
20. The method of claim 19 , wherein the fuel tank is in an aircraft.
Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/217,523 US20130048134A1 (en) | 2011-08-25 | 2011-08-25 | Stagnant Fuel Thermal Insulation System |
CN201210305469.7A CN102951295B (en) | 2011-08-25 | 2012-08-24 | Stagnant fuel thermal insulation system |
EP12181750.6A EP2562088B1 (en) | 2011-08-25 | 2012-08-24 | Stagnant fuel thermal insulation system |
JP2012185297A JP6093524B2 (en) | 2011-08-25 | 2012-08-24 | Thermal insulation system with stagnant fuel |
US14/194,914 US9677716B2 (en) | 2011-08-25 | 2014-03-03 | Stagnant fuel thermal insulation system |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
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US13/217,523 US20130048134A1 (en) | 2011-08-25 | 2011-08-25 | Stagnant Fuel Thermal Insulation System |
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Application Number | Title | Priority Date | Filing Date |
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US14/194,914 Division US9677716B2 (en) | 2011-08-25 | 2014-03-03 | Stagnant fuel thermal insulation system |
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US20130048134A1 true US20130048134A1 (en) | 2013-02-28 |
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US14/194,914 Active 2032-05-03 US9677716B2 (en) | 2011-08-25 | 2014-03-03 | Stagnant fuel thermal insulation system |
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US14/194,914 Active 2032-05-03 US9677716B2 (en) | 2011-08-25 | 2014-03-03 | Stagnant fuel thermal insulation system |
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Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US9677716B2 (en) | 2011-08-25 | 2017-06-13 | The Boeing Company | Stagnant fuel thermal insulation system |
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Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US9677716B2 (en) | 2011-08-25 | 2017-06-13 | The Boeing Company | Stagnant fuel thermal insulation system |
Also Published As
Publication number | Publication date |
---|---|
JP6093524B2 (en) | 2017-03-08 |
CN102951295A (en) | 2013-03-06 |
US20140174557A1 (en) | 2014-06-26 |
JP2013044433A (en) | 2013-03-04 |
EP2562088A2 (en) | 2013-02-27 |
EP2562088B1 (en) | 2016-10-12 |
CN102951295B (en) | 2017-03-01 |
EP2562088A3 (en) | 2013-08-14 |
US9677716B2 (en) | 2017-06-13 |
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