WO2000071956A1 - Soufflerie et echangeur de chaleur associe - Google Patents

Soufflerie et echangeur de chaleur associe Download PDF

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Publication number
WO2000071956A1
WO2000071956A1 PCT/US2000/013640 US0013640W WO0071956A1 WO 2000071956 A1 WO2000071956 A1 WO 2000071956A1 US 0013640 W US0013640 W US 0013640W WO 0071956 A1 WO0071956 A1 WO 0071956A1
Authority
WO
WIPO (PCT)
Prior art keywords
heat exchanger
section
coolant
flow
edge
Prior art date
Application number
PCT/US2000/013640
Other languages
English (en)
Inventor
Thomas G. Moll
Carl E. Jauch
C. Lynn Marksberry
Original Assignee
Aero Systems Engineering, Inc.
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Aero Systems Engineering, Inc. filed Critical Aero Systems Engineering, Inc.
Priority to AU50264/00A priority Critical patent/AU5026400A/en
Publication of WO2000071956A1 publication Critical patent/WO2000071956A1/fr

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F28—HEAT EXCHANGE IN GENERAL
    • F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
    • F28F3/00—Plate-like or laminated elements; Assemblies of plate-like or laminated elements
    • F28F3/02—Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations
    • F28F3/025—Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations the means being corrugated, plate-like elements
    • 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
    • F28D1/00—Heat-exchange apparatus having stationary conduit assemblies for one heat-exchange medium only, the media being in contact with different sides of the conduit wall, in which the other heat-exchange medium is a large body of fluid, e.g. domestic or motor car radiators
    • F28D1/02—Heat-exchange apparatus having stationary conduit assemblies for one heat-exchange medium only, the media being in contact with different sides of the conduit wall, in which the other heat-exchange medium is a large body of fluid, e.g. domestic or motor car radiators with heat-exchange conduits immersed in the body of fluid
    • F28D1/03—Heat-exchange apparatus having stationary conduit assemblies for one heat-exchange medium only, the media being in contact with different sides of the conduit wall, in which the other heat-exchange medium is a large body of fluid, e.g. domestic or motor car radiators with heat-exchange conduits immersed in the body of fluid with plate-like or laminated conduits
    • F28D1/0366—Heat-exchange apparatus having stationary conduit assemblies for one heat-exchange medium only, the media being in contact with different sides of the conduit wall, in which the other heat-exchange medium is a large body of fluid, e.g. domestic or motor car radiators with heat-exchange conduits immersed in the body of fluid with plate-like or laminated conduits the conduits being formed by spaced plates with inserted elements
    • F28D1/0383—Heat-exchange apparatus having stationary conduit assemblies for one heat-exchange medium only, the media being in contact with different sides of the conduit wall, in which the other heat-exchange medium is a large body of fluid, e.g. domestic or motor car radiators with heat-exchange conduits immersed in the body of fluid with plate-like or laminated conduits the conduits being formed by spaced plates with inserted elements with U-flow or serpentine-flow inside the conduits
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
    • G01M9/02—Wind tunnels
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
    • G01M9/02—Wind tunnels
    • G01M9/04—Details

Definitions

  • the present invention relates generally to wind tunnels. More particularly, the present invention relates to closed circuit wind tunnels and the use of a plate-fin heat exchanger in such wind tunnels.
  • Wind tunnels help researchers simulate the forces acting on an object moving through air. To obtain useful results, the conditions in the wind tunnel should closely match the conditions the object will encounter in actual service.
  • Flow generation means in the form of a fan generally drives the air flow in a wind tunnel to create the tunnel flowstream. Unfortunately, much of the energy supplied by the
  • a "fin-tube" type of heat exchanger presents a very large resistance to the flowstream.
  • the resistance increases the power needed to drive the wind tunnel, which in turn increases the temperature of the flow even more.
  • many wind tunnels increase the size of the heat exchanger in the cross- flowstream direction. This in turn requires the expansion of the wind tunnel duct cross- section to house the larger heat exchanger.
  • the transition from a smaller duct upstream of the heat exchanger to the larger duct required to house the heat exchanger often requires the use of a wide angle diffuser which significantly increases the risk of flow separation, turbulence, and angularity problems.
  • the flow around the cross-stream tubes in a "fin-tube" heat exchanger produces unsteady turbulent flow characteristics which in turn causes dynamic forces on the tube. These forces may induce tube vibration due to the low natural frequency of the slender, long span coolant tube which in turn may lead to undesirable noise and high stress or fatigue which often results in tube failure or leaks.
  • the cross-stream tubes also cause
  • the present invention relates to a wind tunnel with an improved heat exchanger structure that overcomes the problems and limitations of the prior art. Specifically, the wind tunnel and heat exchanger combination of the present
  • invention provides for a more compact and efficient heat exchanger capability, reduces turbulence in the flowstream and minimizes the flowstream blockage or resistance resulting from the heat exchanger.
  • the present invention includes a wind l miel with a "plate-fin" heat exchanger comprised of a plurality of heat transfer fins separated by a plurality of
  • the heat exchanger fins and parting sheets create a plurality of passageways or channels for passage of the air flowstream and the cooling fluid.
  • Plate-fin heat exchangers have particular application to wind tunnels and offer significant advantages in flow quality over wind tunnel designs of the prior art.
  • plate-fin heat exchangers eliminate the turbulence generated by flow unsteadiness and separation around the tubes. This improves the flowstream through the test section and allows for better and more accurate measurements. Lower turbulence levels also enhance the acoustic characteristics of the tunnel, which can be very critical for certain types of testing.
  • a second advantage of the plate-fin heat exchanger over the prior art is its flow
  • the plate-fin modules are made of many small cell, long length flow passages. These passages are similar to the honeycomb flow straighteners typically installed in wind tunnels.
  • a third advantage in flow quality of plate-fin heat exchangers is that their high efficiency allows designers to reduce the size of, or even eliminate the need for, a wide angle diffuser which is often required when using "fin-tube" heat exchangers. Besides the advantages in flow quality, plate-fin heat exchangers also offer significant economic advantages.
  • Another object of the present invention is to provide a wind tunnel with a heat
  • a further object of the present invention is to provide a wind tunnel with a heat
  • a still further object of the present invention is to provide a closed circuit wind tunnel with a plate-fin type heat exchanger.
  • Figure 1 is an isometric view of the wind tunnel in accordance with the present invention.
  • Figure 2 is an isometric view of the heat exchanger assembly for use in the wind tunnel of the present invention.
  • Figure 3 is an elevational view of the air inlet side of the heat exchanger assembly
  • FIG 4 is an elevational end view of the heat exchanger assembly of Figure 2, with portions shown in broken lines.
  • FIG. 5 is an enlarged fragmentary view showing the water box detail for one of the heat exchanger modules of the heat exchanger assembly of Figure 4.
  • Figure 6 is an isometric view, with portions shown in broken lines, of a heat exchanger module for use in the wind tunnel of the present invention.
  • Figure 7 is an enlarged fragmentary view, with portions broken away, showing the cooling fluid manifold at the manifold end of the module.
  • Figure 8 is an enlarged fragmentary view showing a portion of a heat exchanger unit at the end of the module opposite the manifold end.
  • Figure 9 is a sectional view as viewed through one of the cooling fluid passages and showing the flow paths of coolant through the module.
  • Figure 10 is a sectional view as viewed through one of the air flow passages and showing the flow path of air through the module.
  • Figure 11 is an isometric, fragmentary view of the coolant manifold end of a heat exchanger unit in accordance with the present invention.
  • Figure 11 A is a further isometric fragmentary view of a heat exchanger unit.
  • Figure 12 is an enlarged, fragmentary elevational view showing the corrugated fin construction for an air flow element in the heat exchanger unit.
  • Figure 13 is an isometric view of the manifold end of an alternate embodiment of a heat exchanger unit in accordance with the present invention.
  • Figure 14 is an isometric view of the end of a heat exchanger unit opposite the coolant manifold end.
  • Figure 15 is a fragmentary isometric view of an alternate heat exchanger unit.
  • Figure 16 is a fragmentary isometric view of a still further alternate heat exchanger
  • FIG. 1 showing an isometric view of the wind tunnel in accordance with the present invention in combination with the improved heat exchanger.
  • the wind tunnel 10 includes a flow generator means which is commonly in the form of a fan 12, a heat exchanger or heat exchanger assembly 14, a plurality of turning vanes 13 and 17, one or more flow conditioning elements 15, a nozzle 16 and a test section 18.
  • the fan 12 is driven by a motor drive 20 to create a high velocity air flowstream 21 in the flow duct 19.
  • the actual air velocity which is generated varies greatly depending on the intended use for the wind tunnel; however, typical values range from as low as 100 mph or lower to several times the speed of sound.
  • the preferred embodiment uses a fan to accelerate the air because of its ability to move large volumes of air.
  • those skilled in the art will realize that various alternate flow generating
  • the motor drive 20 powers the flow generator 12. Unfortunately, much of the energy supplied by the motor drive 20 and the fan 12 is converted into heat. This can be used as well.
  • the embodiment solves this problem by directing the air flowstream 21 through the flow duct 19 and into the heat exchanger 14.
  • the temperature of the air leaving the heat exchanger 14 will vary depending upon the intended application of the wind tunnel and the velocity airflow involved; however, a typical temperature for air exiting the heat exchanger 14 is in the range of 80 - 160°F and most preferably less than 120°F.
  • the air flowstream 21 travels through the turning ⁇ .MI . 13, which changes the flow direction of the flowstream 180°, and to the flow conditioning elements 15.
  • the flow conditioning elements straighten the flowstream 21 to further reduce any turbulence.
  • the preferred embodiment contemplates use of a honeycomb-style flow straightener.
  • the flow conditioning elements could be any number of flow conditioning elements.
  • the flowstream 21 Upon leaving the flow conditioning elements 15, the flowstream 21 is further accelerated by the nozzle 16 before entering the test section 18. During use, the flowstream 21 passes over a test object (not shown) in the test section 18 before being returned by the flow duct 24 and through the turning vane 17 to the flow generator 12.
  • a test object not shown
  • the heat exchanger 14 of the present invention can be placed anywhere in the wind tunnel flow stream between the fan 12 and the test section 18. Further, because of the flow conditioning properties of the exchanger 14 of the present invention, it can be used, in certain circumstances, to replace the flow straightener element 15.
  • the wind tunnel is a closed circuit wind tunnel in which the air is continuously circulated through the system along the air flowstream 21. It is understood, however, that many of the concepts and features of the present invention are equally applicable to wind tunnels which are not of the closed circuit type.
  • the heat exchanger assembly 14 is mounted on supports 26 and includes a lower heat exchanger section 23 comprised of a plurality of heat exchanger modules 25 positioned in side-by-side relationship and an upper heat exchanger section 27 also comprised of a plurality of heat exchanger modules 25 positioned in side-by-side relationship.
  • the lower heat exchanger section 23 is supported on the frame 26 and the upper heat exchanger section 27 is supported on top of
  • the lower and upper heat exchanger sections 23 and 27 can be connected with each other by any desired means.
  • the mating ends of the modules 25 in the lower and upper sections 23 and 27 may be provided with flanges and bolted together with bolts 33 as shown in Figures 3 and 4. This design allows operators to easily remove any individual module for maintenance or replacement. It also provides flexibility in heat exchanger design.
  • the heat exchanger assembly 14 is provided with lower and upper coolant supply conduits 30 and 34, respectively. These supply conduits 30 and 34 are connected with the main cooling fluid supply pipe 28.
  • a coolant inlet conduit 31 extends from the supply conduit 30 to each of the modules 25 in the lower heat exchanger section 23 to provide coolant to such modules.
  • a coolant inlet conduit 32 extends from the supply conduit 34 into the modules 25 in the upper heat exchanger section 27 to provide coolant to such modules.
  • the first heat exchanger assembly 14 is also provided with lower and upper coolant return conduits 39 and 40 and associated conduits 36 and 38 to facilitate flow of coolant from the modules in the lower and upper sections 23 and 27 to the main coolant return pipe 29.
  • the conduits 36 extends between the modules in the lower section 23 and the conduit 39, while the conduits 38 extend between the modules in the upper section 27 and the conduit 40.
  • the modules 25 can be stacked as shown, with the modules in the lower and upper sections 23 and 27 being inverted relative to one another and the supply conduits being located entirely on the exterior of assembly 14.
  • the cooling fluid is water, which is typically provided with corrosion inhibitors, biocide and/or antifreeze chemicals.
  • corrosion inhibitors biocide and/or antifreeze chemicals.
  • cooling fluids could be utilized as well including liquids other than water or gases such as air.
  • each heat exchanger module 25 includes a front or air flow inlet side 41, a back or air exit side 42 and a pair of sides 44,44 separating the front and back sides 41 and 42.
  • Each module 25 also includes a coolant manifold end 45 and an end 46 opposite the manifold end. As best shown in Figures 6, 7 and 9, the manifold end
  • each module 25 is provided with a coolant inlet manifold chamber 49 and a coolant outlet manifold chamber 50 for facilitating the flow of coolant fluid to and from the heat exchanger units as described in greater detail below.
  • each module includes an outer wall 43, a separation wall 51 and a generally vertical partition wall 48.
  • the inlet manifold chamber 49 is defined by a portion of the walls 43
  • the outlet or return manifold chamber 50 is defined by the other portions of the walls 43 and 51 and the other side of the partition wall
  • Each of the heat exchanger modules 25 is comprised of a plurality of heat exchanger units 52 which are positioned in side-by-side relationship to one another in a direction perpendicular to the direction of air flow and which are shown best in Figures 7,
  • each of the heat exchanger units 52 includes a pair of coolant flow members or sections 54 and 55 on its sides and one or more air flow members or sections 56 sandwiched between the coolant flow members 54 and 55.
  • each of the air flow members 56 includes a plurality of fins 58 aligned with the direction of air flow and defining flow passages 57 to direct the flow of air through the passages 57 from the inlet side of the member 56 to its outlet side.
  • These fins 58 may be conventional corrugated heat exchanger fins such as that best shown in Figure 12. As shown, the fins 58 extend back and forth between a pair of parting sheets
  • the parting sheets 59 define and separate each air flow member 56.
  • four air flow members 56 are shown as being sandwiched between each pair of coolant flow members 54 and 55; however, any number of air flow members can be utilized depending upon the particular use for the wind tunnel. In some applications only one or two air flow members 56 are sandwiched between the coolant flow members.
  • each of the heat exchanger units 52 includes a wall 51
  • the wall 51 is formed by the top fin 58 extending between the parting sheets 59.
  • the separation wall 51 extends only over the air flow members 56 to prevent coolant fluid in the manifold chambers 49 and 50 from entering the air flow members 56.
  • Each of the coolant flow members 54 and 55 is defined by a pair of parting sheets
  • each heat exchanger unit 52 includes a plurality of generally verticJiy extending fins 62 extending from the manifold end of each heat exchanger unit 52 toward the end opposite the manifold end. These vertically extending fins 62 define a plurality of coolant fluid inlet and return passages as illustrated best in Figure 9.
  • 54 and 55 also includes a central wall or fin 64 extending from the partition wall 48 to the fluid passage transition point 65 to define and separate the coolant inlet and return
  • the end of the coolant flow members 54 and 55 opposite the manifold end includes a plurality of generally horizontal fins or fin sections 66. These horizontal fins 66 are connected with the generally vertical fins 62 on each side of the divider fin 64 to define coolant flow passages from the chamber 49 to the chamber 50. Specifically, flow of cooling fluid passes from the chamber 49 through the flow passages defined by the fins 62 on the left-hand side of the divider fin 64 as shown in Figure 9, horizontally between the fins 66 and then upwardly between the fins 62 on the right-hand side of the divider fin 64 shown in Figure 9 to the outlet chamber 50.
  • the fins 62 and 66 in the cooling members 54 and 55 define a coolant passageway and are of a corrugated
  • each module 25 can be comprised of any number of heat exchanger units 52 desired. Further, the entire collection of heat exchanger units 52 in each module 25, including the parting sheets 59, 60 and 61, the fins 58, 62 and 66 and the elements of each
  • heat exchanger unit 52 are brazed into a monolithic unit. This provides the plate-fin heat exchanger of the present invention capable of resisting extremely high tunnel flows and coolant pressures. Under operating conditions, the parting sheets 59, 60 and 61 function as primary heat transfer surfaces and also function to prevent the mixing of the air flow with
  • the heat transfer fins 58, 62 and 66 function to maintain the structural rigidity of each heat exchanger unit and also serve as secondary heat transfer surfaces.
  • the heat transfer and flow defining fins 58, 62 and 66 in the preferred embodiment are made from aluminum because of its high heat transfer properties, good brazing characteristics and relatively low cost. Those skilled in the art, however, will understand that a wide variety of materials such as stainless steel, copper, nickel, carbon steel, alloy steel or titanium can be substituted.
  • Figure 13 discloses an alternate embodiment illustrating a modified heat exchanger unit 52 designed to reduce tunnel flow resistance.
  • the coolant flow members 54 and 55 of each heat exchanger unit 52 are provided with leading edge headers 69 with a rounded profile and a trailing edge header 70 with a tapered profile.
  • the rounded profile header 69 at the leading edge which faces the air flow reduces drag and turbulence in the air flow.
  • the tapered edge header 70 at the trailing edge of the unit 52 reduces drag and turbulence caused by eddies on the downstream side of the unit 52.
  • Figure 14 shows the end of the heat exchanger unit 52 opposite the manifold end. As shown, both the air flow and coolant flow passages are closed at that end. Flanges 73
  • FIGS 15 and 16 show alternate embodiments of the heat exchanger unit, and in
  • a secondary liquid flow passage is formed in the coolant portion of the heat exchanger unit. Flow of liquid through this secondary flow passage can be independently controlled and can be at a temperature different than that of the primary flow passages for the purpose of controlling the transfer of heat or coolant to the leading edge header of the coolant section.
  • the header 75 at the leading edge of the coolant flow section is provided with an interior flow passage 76 through which a secondary coolant 83 can flow.
  • this secondary coolant 83 can be provided at an elevated temperature to prevent the water droplets from freezing on the leading edge of the
  • This secondary flow passage includes a plurality of adjacent flow channels 80 separated by a plurality of flow guides or partitions 81.
  • a secondary coolant 84 which is provided at a temperature greater than that of the primary coolant can be directed through the secondary coolant passage to prevent
  • secondary flow channels would also need to be provided in the trailing headers to provide flow to the lead edge headers.
  • the coolant fluid then passes from the manifold chamber 49 through the coolant passages defined by the fins 62 to the left of the divider fin 64, across the end of the heat exchanger unit 52 through the passages defined by the fins 66 and back through the flow passages between the fins 62 to the right of the divider fin 64 to the manifold chamber 50.
  • the coolant fluid is then returned through the conduits 36, 38, 39 and 40 to the main coolant fluid return 29. From here, the heated coolant is cooled by external means such as a cooling tower and recirculated back through the heat exchanger

Abstract

L'invention porte sur un échangeur de chaleur (14) à ailettes en plaques pour soufflerie (10).
PCT/US2000/013640 1999-05-21 2000-05-18 Soufflerie et echangeur de chaleur associe WO2000071956A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AU50264/00A AU5026400A (en) 1999-05-21 2000-05-18 Wind tunnel and heat exchanger therefor

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US13520299P 1999-05-21 1999-05-21
US60/135,202 1999-05-21

Publications (1)

Publication Number Publication Date
WO2000071956A1 true WO2000071956A1 (fr) 2000-11-30

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PCT/US2000/013640 WO2000071956A1 (fr) 1999-05-21 2000-05-18 Soufflerie et echangeur de chaleur associe

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AU (1) AU5026400A (fr)
WO (1) WO2000071956A1 (fr)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102012307A (zh) * 2010-11-18 2011-04-13 中国人民解放军国防科学技术大学 超声速边界层风洞
CN102621907A (zh) * 2012-03-31 2012-08-01 中国科学院安徽光学精密机械研究所 一种恒温风洞控制系统
CN104019956A (zh) * 2014-06-11 2014-09-03 中国环境科学研究院 环形回路的环境模拟标定风洞
CN105203345A (zh) * 2015-10-20 2015-12-30 长春轨道客车股份有限公司 用于列车空调风量测试的通用型辅助风道装置
CN105628331A (zh) * 2015-12-28 2016-06-01 中国航天空气动力技术研究院 大型常规高超声速风洞的节能环保布局
CN115218696A (zh) * 2022-08-31 2022-10-21 中国空气动力研究与发展中心高速空气动力研究所 一种在风洞中用于冷却空气的板翅式换热器

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4841538A (en) * 1986-03-05 1989-06-20 Kabushiki Kaisha Toshiba CO2 gas laser device
US5417280A (en) * 1992-08-27 1995-05-23 Mitsubishi Jukogyo Kabushiki Kaisha Stacked heat exchanger and method of manufacturing the same

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4841538A (en) * 1986-03-05 1989-06-20 Kabushiki Kaisha Toshiba CO2 gas laser device
US5417280A (en) * 1992-08-27 1995-05-23 Mitsubishi Jukogyo Kabushiki Kaisha Stacked heat exchanger and method of manufacturing the same

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102012307A (zh) * 2010-11-18 2011-04-13 中国人民解放军国防科学技术大学 超声速边界层风洞
CN102621907A (zh) * 2012-03-31 2012-08-01 中国科学院安徽光学精密机械研究所 一种恒温风洞控制系统
CN104019956A (zh) * 2014-06-11 2014-09-03 中国环境科学研究院 环形回路的环境模拟标定风洞
CN105203345A (zh) * 2015-10-20 2015-12-30 长春轨道客车股份有限公司 用于列车空调风量测试的通用型辅助风道装置
CN105628331A (zh) * 2015-12-28 2016-06-01 中国航天空气动力技术研究院 大型常规高超声速风洞的节能环保布局
CN115218696A (zh) * 2022-08-31 2022-10-21 中国空气动力研究与发展中心高速空气动力研究所 一种在风洞中用于冷却空气的板翅式换热器

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