US3894579A - Heat exchanger devices for fluid flows - Google Patents

Heat exchanger devices for fluid flows Download PDF

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Publication number
US3894579A
US3894579A US224580A US22458072A US3894579A US 3894579 A US3894579 A US 3894579A US 224580 A US224580 A US 224580A US 22458072 A US22458072 A US 22458072A US 3894579 A US3894579 A US 3894579A
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United States
Prior art keywords
block
passages
exchanger
heat exchanger
gas
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US224580A
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English (en)
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Maurice G Brille
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Societe Anonime de Vehicules Industriels et dEquipements SA SAVIEM
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Societe Anonime de Vehicules Industriels et dEquipements SA SAVIEM
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Priority claimed from FR7104206A external-priority patent/FR2126940A1/fr
Priority claimed from FR7203350A external-priority patent/FR2170815A2/fr
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/08—Heating air supply before combustion, e.g. by exhaust gases
    • F02C7/10—Heating air supply before combustion, e.g. by exhaust gases by means of regenerative heat-exchangers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/08—Heating air supply before combustion, e.g. by exhaust gases
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/08—Heating air supply before combustion, e.g. by exhaust gases
    • F02C7/10—Heating air supply before combustion, e.g. by exhaust gases by means of regenerative heat-exchangers
    • F02C7/105—Heating air supply before combustion, e.g. by exhaust gases by means of regenerative heat-exchangers of the rotary type
    • 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
    • F28D19/00—Regenerative heat-exchange apparatus in which the intermediate heat-transfer medium or body is moved successively into contact with each heat-exchange medium
    • F28D19/04—Regenerative heat-exchange apparatus in which the intermediate heat-transfer medium or body is moved successively into contact with each heat-exchange medium using rigid bodies, e.g. mounted on a movable carrier
    • 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
    • F28D19/00—Regenerative heat-exchange apparatus in which the intermediate heat-transfer medium or body is moved successively into contact with each heat-exchange medium
    • F28D19/04—Regenerative heat-exchange apparatus in which the intermediate heat-transfer medium or body is moved successively into contact with each heat-exchange medium using rigid bodies, e.g. mounted on a movable carrier
    • F28D19/041—Regenerative heat-exchange apparatus in which the intermediate heat-transfer medium or body is moved successively into contact with each heat-exchange medium using rigid bodies, e.g. mounted on a movable carrier with axial flow through the intermediate heat-transfer medium
    • 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
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S165/00—Heat exchange
    • Y10S165/009—Heat exchange having a solid heat storage mass for absorbing heat from one fluid and releasing it to another, i.e. regenerator
    • Y10S165/013—Movable heat storage mass with enclosure
    • Y10S165/014—Reciprocated linearly

Definitions

  • ABSTRACT Apparatus for producing the transfer of heat from one gaseous flow to another by the alternating and successive passage of the flows through successive sections of an exchanger block having a relatively large specific area comprising a device for dividing the gaseous flows into a plurality of streams flowing in separate passages, the exchanger block of cylindrical configuration being disposed across the passages so as to discontinue same and receive the flows therethrough; a mechanism for imparting an axial reciprocating motion to the exchanger block together with a movement of rotation about its axis; the passages having equal widths and being flat and disposed in parallel relation ship, with seals similar to piston-rings disposed between the passages and the block, the sections of the exchanger block consisting of porous elements permitting the fluid flow in the transverse direction but not in the axial direction.
  • This apparatus is particularly adequate for gas turbine equipping land vehicles, notably in that the heat exchange
  • the present invention relates in general to means for producing a transfer of heat between gaseous fluid streams, and more particularly to a heat exchanger to be interposed between gaseous fluids, notably supercharging compressed air and exhaust gas of engines, such as gas turbine regenerators-exchangers.
  • regenerator-exchanger designates in general heat transfer devices comprising a block of metallic or ceramic permeable material, against which the hot gases and the compressed air are caused to impinge or flow by turns, in order to cool said gases and heat or re-heat said compressed air.
  • Heat exchangers of this character consist as a rule of disks rotating at a relatively low speed.
  • any communication between the burnt gases on the one hand and the compressed air on the other hand, i.e., between the conduits in which these gaseous fluids are conveyed must be carefully avoided, since said compressed air circulates under a pressure of the order of 4 to 5 bars (58 to 73 psi) and even a small loss of compressed air by leakage would reduce considerably the turbine efficiency. Therefore, a reliable fluid-tight joint must be provided along the two lines defining the boundaries between the exhaust gas conduit and the compressed air conduit, which are in actual contact with said rotary disk.
  • the gaseous fluids are distributed in the form of a sequence of flat parallel jets or streams of substantially equal width in which the hot and cold jets alternate.
  • This jet assembly is discontinued by a cylindrical space extending therethrough and receiving in proper fitting relationship a heat exchanger also of cylindrical configuration to which an axial reciprocating motion is imparted with an amplitude equal to the width of one of said jets, the gaseou-s flows passing through said cylindrical exchanger along planes perpendicular to its axis, between a stacking of cellular plates constituting a porous pattern fluidproof in the axial direction, and according to the present invention a movement of rotation combined with said axial reciprocating motion is imparted to said movable exchanger body.
  • the gas and air streams are each divided into a plurality of flat layers disposed alternately, i.e., with one gas layer alternating with an air layer.
  • the cylindrical movable block of the heat exchanger is reciprocated along a rectilinear path by using suitable means, so that the section thereof which lies across the gaseous jet is shifted to a position in which it lies across the air jet, and vice versa.
  • this block of permeable material is so constructed that the fluids can flow only in the radial direction, not in the axial direction, therethrough.
  • This block may consist of metal and more particularly of metal circular plates stacked to prevent any axial communication and separated from one another by projections, corrugations or peaks imparting a high permeability in any radial direction while creating a turbulence particularly favorable to heat exchanges.
  • the reciprocating motion may be imparted to the cylindrical block either through a crank and connecting-rod mechanism or through a gaseous pressure (for example the pressure of the compressed air) exerted by turns to each end of the block, the air consumption in this case being extremely low in comparison with the turbine output.
  • a gaseous pressure for example the pressure of the compressed air
  • the fluid tightness between the walls of the jets and the exchanger is obtained very simply by using circular packings of the piston-ring type, as commonly used in internal combustion engines. These rings are fitted into the wall of the fluid passage and their width is sufficient to cover simultaneously a plurality of cellular plate thicknesses of the exchanger cylinder, so as to constitute therewith a labyrinth-type seal.
  • the fluid-tightness or seal is of the valve or autoclave type.
  • these rings may be 5 to 6 mm in width, the cell width being of the order of 0.5 mm, with a reciprocation frequency of less than 10 per minute.
  • the rings may consist of two concentric layers of materials having different coefficients of thermal expansion, the material having the higher coefficient being disposed inside the other.
  • the movement of rotation of the exchanger cylinder about its axis is added to its reciprocating motion.
  • This rotational movement promotes the temperature compensation and therefore the stress in the exchanger cylinder, thus improving the homogeneousness of the exchange action.
  • the peripheral linear velocity of rotation is selected to be higher than the linear velocity of the movement of translation.
  • the cellular pattern is not a purely directional one. it may consist of a plurality of circular projections having their axes parallel to the exchanger axis and interconnecting the walls of a pair of adjacent plates of the cellular pattern.
  • This rotation is particularly advantageous in that it tends to equalize the block temperature and avoid distortions.
  • the movement of rotation may be produced independently of the movement of translation, the former being advantageously faster than the latter.
  • the movements of rotation and translation of the exchanger block are produced simulta' neously from the action of at least one of the fluids flowing therethrough.
  • the exchanger block By controlling the rotational and translational movements of the cylinder by means of a fluid under pressure the exchanger block can be constructed as a fully self-contained unit as far as the sustained movement thereof is concerned, without resorting to cumbersome and expensive additional mechanisms, a particularly advantageous feature in the case of gas turbine driven land vehicles.
  • the cylindrical exchanger block is mounted for rotation about its axis and the axial planes of the gaseous flow passages are off-set on a same side in relation to said axis.
  • the passages may be designed with a lateral wall directed tangentially to the exchanger block, the other wall lying approximately in the diametral plane of said block.
  • This other wall may lead directly to the exchanger or, according to a modification adapted to improve the output, it may be outflared so as to be connected tangentially thereto.
  • the outlet passages are designed symmetrically to the corresponding inlet passages, in relation to an axial plane of the exchanger block.
  • This arrangement is also characterized by a considerable flexibility in the orientation of the fluid jets or passages, this constituting a valuable feature in the case of an adaptation to existing vehicles.
  • a reversing valve responsive to an electrical time-lag device may be used, of a type currently used in the field of pneumatic control systems, but a valve incorporating pneumatic retarding means, usually more cumbersome but operating without any external source of power, may also be used.
  • the pressure of the fluids circulating through the exchanger is utilized for advantageously and adjustably obtaining the combined alternate movements of translation and rotational movements of the exchanger block.
  • This arrangement is particularly advantageous in the specific case of gas turbine driven land vehicles due to its simplicity and moderate weight and over-all dimensions, and also to its flexibility of mounting and orientation, notably in the case of trucks.
  • Another essential advantageous feature characterizing this invention is that it facilitates considerably the general design of a gas turbine in the case of a vehicle.
  • the disks are disposed coercively on the sides of the turbine, so that the transverse over-all dimensions, in. the plane of the turbine shaft become relatively large and are difficult to house between the two longitudinal beams of the chassis.
  • the fluid passages are constructed with shapes less satisfactory from the point of view of pressure losses.
  • the exchangers according to this invention these can be disposed above the turbine axis and behind the turbine unit, so that the transverse overall dimensions across the longitudinal members of the vehicle remain within reasonable limits.
  • the exchangers of this invention it is also possible to use particularly direct exhaust pipes, without any pressure loss except for the flow through said blocks.
  • the heat exchangers according to this invention are also advantageous in that the exchanger cylinders can be removed and replaced very easily for checking and cleaning purposes, by pulling them from one end, like the cartridges of filter units, thus minimizing maintenance costs.
  • FIG. 1 is a front elevational view of a disk exchanger of a known type
  • FIG. 2 is a sectional view of the same disk, taken along a diametral plane
  • FIG. 3 is an axial section of a heat exchanger according to this invention.
  • FIG. 4 is a cross sectional view of the exchanger of FIG. 3;
  • FIG. 5 is a section similar to FIG. 3 in the ,case of a gaseous pressure motion control system (utilizing for example compressed air);
  • a gaseous pressure motion control system utilizing for example compressed air
  • FIG. 6 is a plan view of a sealing ring
  • FIG. 7 is an elevational view of the ring of FIG. 6;
  • FIG. 8 is a sectional view of a typical ring fitted in position
  • FIG. 9 is a sectional view of a composite ring consisting of a bimetallic structure
  • FIGS. 10 and 11 corresponding to FIGS. 3 and 5 respectively illustrate a device for rotatably driving the exchanger cylinder
  • FIG. 12 is a modified form of embodiment of the structure shown in FIG. 4, wherein the gaseous flows have different directions;
  • FIG. 13 is a perspective view of a block die for illustrating diagrammatically the multidirectional exchange and turbulence relief elements
  • FIG. 14 is a diagrammatic axial section showing a general view of a turbine for equipping a vehicle
  • FIG. 15 is a corresponding plane view of an advantageous arrangement for a similar assembly
  • FIG. 16 illustrates a plan view from above, in the direction of the axis of the heat exchanger, showing diagrammatically an exchanger block and the means for connecting the fluid passages thereto;
  • FIG. 17 is a modified form of embodiment of said fluid passages
  • FIG. 18 is a diagrammatic axial view of a vehicle turbine assembly, similar to the view of FIG. 14;
  • FIGS. 18A and 188 show, more specifically, apparatus which may be used in the apparatus of FIG. 18, and
  • FIG. 19 is a plan view from above taken along the lines XIXXIX of FIG. 18.
  • FIGS. 1 and 2 illustrating a known type of heat exchanger, wherein the disks revolve slowly and intersect simultaneously the cold and hot flows, the two radii separating the two passages and along which it is desired to provide a sealed or fluidtight joint, are clearly shown together with the special rollers for rotatably driving said disks through peripheral teeth, and the particularly elaborate and contorted configuration of the passages or duct means.
  • FIG. 3 shows in elevation an exchanger constructed according to the principle of this invention, which comprises a compressed air inlet 1, an exhaust gas inlet 2, the division of the inlet duct 1 into a plurality of branch sections 3, the number of these branch sections being if desired greater than two, and also the division of inlet duct 2 into a plurality of branch sections 4 interposed between said sections 3.
  • the cylindrical exchanger block 5 extends at right angles through all these branch sections which on the other hand have all the same width corresponding to the block stroke.
  • the joint between the block and the duct sections is sealed by means of rings 6 illustrated more in detail in FIGS. 6, 7, 8 and 9. These sealing rings are substantially like ordinary piston rings, with a cut gap at mid-height as shown at 7.
  • this ring may consist of a bimetallic assembly with the material or strip having the higher coefficient of expansion disposed inside. These two strips may have a constant thickness, or, as illustrated in FIG. 9, a variable thickness to take due account of the higher temperature on the burnt gas side 13 than on the compressed air side 14. In this case the interface of these two strips is oblique, as shown at 12.
  • the materials and dimensions of the bimetallic strip it is possible to adjust very accurately the opening thereof. A slight rounding of the edges of the friction face of these rings will facilitate the engagement and frictional contact with the edges of the exchanger sections during the operation.
  • the block comprises a series of circular stamped or pressed plates or like elements 21 stacked and clamped on a central rod 15 by means ofend flanges l6 and nuts 17.
  • the extensions of this rod 15 are guided in sliding elements and at the upper end the rod is driven through a connecting-rod l9 and a crank 20.
  • the circular plates 21 may consist of disks formed with projections 22 or peaks 23 (FIG. 13) so that ducts 3 and 4 are not coer cively directed through the block in mutual parallel relationship as illustrated in FIG. 4, and may form be tween each other an angle as shown in FIG. 12. Since the block is reciprocated in the axial direction through a distance equal to the width of ducts 3 and 4, the heat stored in the materials is transferred into the next lower or upper cold duct.
  • the movements of block 5 may be obtained by means of compressed air pressure.
  • FIG. 5 the same block as described in the foregoing is illustrated but without any extension of the central rod and without any guide means, the compressed air being supplied for example through ducts 24 either to the upper portion or to the lower portion by a valve 25 automatically controlled by pneumatic time-lag means 55.
  • the used air escapes through nozzle means 26.
  • the movement thus obtained is relatively rapid and the block remains a certain time in each end position, the movement being damped out however by a proper control of the air exhaust across the nozzle means 26. In this case the block is retained only by its sealing rings, without any additional stress.
  • the present invention is directed more particularly to a rotary block of the type illustrated diagrammatically in FIGS. I0 and 11.
  • the rod 15 may have a ring shaped extension 27 solid with a gear 28 driven in turn from a pinion 29.
  • the translation is still obtained either through the bead 30 and the connecting-rod and crank mechanism 19, 20, or through compressed air supplied via ducts 24.
  • the rotation of the aforesaid block comprising the stamped or pressed metal plates 23 is favorable not only to the temperature balance but also to turbulence about the peaks and therefore to the heat exchange effect.
  • the term peak is used herein to denote any type of round shaped projection producing the same resistance to the gaseous fluid flow in all directions.
  • the block rotation is combined with its translation for producing a tacking" movement propitious to the reduction in the coefficient of friction on the block and therefore to the reduction in the mechanical losses and to a longer useful life of the apparatus, even in the case of a ceramic block.
  • no details have been proposed herein for a possible constitution of a ceramic block, the ideal solution consisting in reproducing as closely as possible what is obtained with the metal elements 23.
  • the plates formed with the aforesaid peaks or like projections may also be made of ceramic. It is also possible to construct a unitary or one-piece ceramic block, provided of course that no axial communication or circulation takes place.
  • the arrangement may be fitted in a turbine as illustrated in FIGS. 14 and 15 illustrating a typical example of a possible application of these heat exchangers.
  • the supercharger 31 is driven from the first turbine wheel 32. Within the gaseous flow in said duct the second turbine wheel 33 drives the reduction gearing 34 and the output shaft 35. Between the first and second wheels 32, 33 a swivelling distributor 36 is provided.
  • the air compressed by supercharger 31 is divided into two streams by the symmetric manifolds or header 37.
  • Each manifold or header 37 terminates in front of the vertical cylindrical exchanger 38 and is divided of course as shown in FIGS. 5 and 11. They open into a general manifold or header 39 supplying air to the combustion chamber 40.
  • the primary air necessary for the combustion penetrates at 41 and the secondary air at 42, the stream of burnt or exhaust gas being guided through the manifold 43 directing the hot gases under pressure towards the turbine 32.
  • the gases expanding at the outlet of turbine 33 are directed to the rear through duct means 44 also extending through the heat exchangers 38 after having been divided into a plurality of channels as illustrated in FIGS. 3, 5 and 11, but without changing their direction, except downstream of the turbine at which a single elbow 45 directs them back to the chimney 46.
  • the means for controlling the movements of exchangers 38 are not shown but the means contemplated in FIGS. 3, 5, l0 and 11 may be used to this end. It may be noted that the exchangers 38 are disposed completely beneath the axis 47 of the turbine unit, i.e.,
  • the two exchangers must be synchronized and off-set by a half-stroke in order to improve the regularity of the air temperature.
  • the movements of rotation and translation of the exchanger block are obtained simultaneously through the action of at least one of the pressure fluids flowing therethrough.
  • one of the lateral walls of the gaseous flow inlet passage is tangent to the external cylinder of the exchanger block, the other wall being directed in a substantially diametral plane of the exchanger block, and on the other hand the gaseous flow discharge passages are symmetrical to the inlet passages in relation to a diametral plane of the exchanger.
  • the exchanger block 5 is rotatably driven about its axis 50 due to the pressure gas introduced through the passages 3 and 4 and flowing through the sections of block 5. These passages are shifted in relation to the axis 50 so that the dynamic effect of the fluids is preponderant over one half of block 5 and generates a torque producing its rotation.
  • the exchange is advantageously located in positions where elbows are necessary in the general system so that this driving effect can be obtained without resorting to additional means.
  • FIG. 17 illustrates a modified form of embodiment of this arrangement, wherein the passage is connected through a rounded wall 51 externally tangent to the block 5, thus reducing pressure losses and increasing the passage output.
  • FIG. 18 illustrates an arrangement contemplated in the case of a vehicle and similar to that illustrated in FIGS. 14 and 15. It will be seen that in this modified arrangement a supercharger 31 driven from the first turbine wheel 32 supplies compressed air to headers 37 having a divided end portion upstream of the cylindrical exchanger 38, the air emerging therefrom being directed by the general header 39 into the combustion chamber 40 through ports 41 and 42. The combustion gases are directed by header 43, 44 to exchanger 38 from which they flow to the chimney 46. As shown in this figure the axis 50 of the heat exchanger is disposed across or transversely to the direction of flow of the fluid passages in order to reduce pressure losses by reducing the length of these passages and obtaining a flow path as direct as possible.
  • FIG. 19 illustrates in section the contour of passages 37 and 44 in which the gaseous flows impart a torque to the exchanger block 5.
  • the block axis 50 is off-set in relation to the axial planes of these passages, and the resulting asymmetry of the gaseous flow determines the rotation of said block.
  • the torque is provided by both hotgas and cold-gas streams.
  • the drive may be derived from one fraction only of the gases flowing through the exchanger, the other fraction flowing through the exchanger section without producing any torque or even in counter-current relationship.
  • This flow of one fraction of the gases in countercurrent relationship which acts as a dynamic brake retarding the rotation of the exchanger block is also advantageous in that it increases the velocity of flow of these gases along its walls and therefore the rate of heat exchange.
  • the rotatable drive is caused by only one fraction of the gas throughout, it is less sensitive to variations in this throughput.
  • the reciprocating movement of translation of the exchanger block is also caused by the gas pressure and controlled through the reversing valve 25 (FIG. 18) supplied with gas under pressure through a branch line 52 connected to one of the fluid passages upstream of the exchanger.
  • This gas is distributed by turns to each one of the end faces of the cylindrical exchanger block via ducts 53 and 54, the pipe associated with the opposite, non-pressurized face being vented at the same time to the atmosphere.
  • time-lag device 55 The time-lag actuation of reversing valve 25, preset as a function of the desired heat exchange time of the block sections is obtained through a time-lag device 55.
  • a time-lag device 55 may consist of an electric timing mechanism controlling an electromagnet connected to valve 25. If a pneumatic time-lag device is used the latter is supplied with pressure fluid through a pipe line 56 connected to manifold 52.
  • a coil 55' of an electromagnet may be energized by the closure of a circuit through an electric timing mechanism 55''.
  • FIG. 18B a preferred embodiment, wherein use is made of the pressure involved by the gases released from the turbine, thus avoiding energy expenses.
  • the device comprises a piston 61 located within device 55, for controlling valve intended to enable the gases coming from duct 52 to flow towards duct 53 and 54.
  • Duct 52 is connected to duct 56 which cooperates with valve 57 itself connected by means of a rod system to valve 58, so as to feed in turn a gas flow through ducts 59 and 60 at each respective face of piston 61.
  • Piston 61 is integral with cross-head 62 itself provided with a fork member 63 intended to insure that valve 57, and thus valve 25, is reversed in both directions.
  • Time-lag device 55 comprises at each end thereof calibrated openings 64 having a flow area smaller than that of ducts 59 and 60.
  • Gas overpressure within device 55 causes piston 61 to move towards the opposite extremity, until fork 63 pushes the lever of valve 57 out of its point of unstable equilibrium, i.e., in the opposite position, thus actuating valve 25 so as to invert the gas flow within duct 53 and 59 towards ducts 54 and 60, wherein the aforesaid process is repeated, due to the pressure increase on the relative face of piston 61.
  • a device for producing a heat exchange between gaseous flows in which the heat transfers take place between a hot flow and a cold flow by causing said flows to be directed by turns and successively through sections of a heat exchanger block comprising:
  • a cylindrical exchanger block provided within said cylindrical space and being both axially reciprocating and rotatable therein, the amplitude of reciprocation corresponding to the width of one of said passages, said block including stacked pressed plates forming a porous cellular structure in the transverse direction but being fluid-tight in the axial direction of said block so as to provide fluidtightness between said gaseous flow passages and said enchange block, said gaseous flows passing through said block in planes perpendicular to the block axis;
  • Heat exchanger device according to claim 1 wherein said means for axially reciprocating comprises means for alternately supplying one of said gases to an upper and lower portion of said exchanger block.
  • Heat exchanger device according to claim 2 wherein said means for alternately supplying comprises:
  • an automatically controlled valve for directing a supply of the gas to either said first or second duct.
  • Heat exchanger device according to claim 1 wherein the alternate passages have axial planes that are off-set on a same side in relation to the axis of rotatiori of said block and said rotating means comprises at least one fraction of said gaseous flow directed across said exchanger block.
  • Heat exchanger device wherein one of the lateral walls of the off-set alternate passages is tangent to said exchanger block, the other lateral wall being directed in a substantially diametral plane of said block.
  • Heat exchanger device wherein said lateral walls of said passages lying substantially in a diametral plane of said block are connected thereto through a rounded portion directed tangentially to the outer cylindrical surface of said exchanger block.
  • Heat exchanger device wherein said passages for receiving the gas to be cooled are disposed symmetrically to the passages for receiving the gas to be heated in relation to a diametral plane of said exchanger block.
  • a reversing valve means for alternately supplying the flow of gas to the respective end faces
  • time lag means for actuating said reversing valve.
  • Heat exchanger device according to claim 9 wherein said time lag means comprises an electromagnetic control device connected to said reversing valve means and an electric timing mechanism associated with said electromagnetic control device.
  • Heat exchanger device according to claim 9 wherein said time lag means comprises a pneumatic timing device responsive to one of the gases flowing through said exchanger block.
  • Heat exchanger device according to claim 9 wherein said reversing valve means simultaneously supplies gas to one end face of said exchanger block and vents gas from the other end face to the atmosphere.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US224580A 1971-02-09 1972-02-08 Heat exchanger devices for fluid flows Expired - Lifetime US3894579A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR7104206A FR2126940A1 (en) 1971-02-09 1971-02-09 Gas turbine exhaust cooler - with cylindrical block permeable only radially and oscillating axially
FR7203350A FR2170815A2 (en) 1972-02-01 1972-02-01 Regenerative heat exchanger - partic for gas turbine driven vehicles

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US3894579A true US3894579A (en) 1975-07-15

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US224580A Expired - Lifetime US3894579A (en) 1971-02-09 1972-02-08 Heat exchanger devices for fluid flows

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US (1) US3894579A (en:Method)
JP (1) JPS506653B1 (en:Method)
DE (1) DE2206109C3 (en:Method)
GB (1) GB1382876A (en:Method)
IT (1) IT947434B (en:Method)
SU (1) SU553944A3 (en:Method)

Cited By (8)

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US20030178499A1 (en) * 2002-01-21 2003-09-25 Webasto Thermosysteme International Gmbh Vehicle heating appliance with a valve in the fuel supply
US20060054301A1 (en) * 2004-02-19 2006-03-16 Mcray Richard F Variable area mass or area and mass species transfer device and method
US20090101302A1 (en) * 2007-10-17 2009-04-23 Tupper Myron D Dynamic heat exchanger
US20110185985A1 (en) * 2010-02-03 2011-08-04 Farshid Ahmady Fluid heating apparatus
US20130105105A1 (en) * 2011-10-31 2013-05-02 Harlod L. O'Brien Bimetallic seal for air heaters
US20180274389A1 (en) * 2017-03-23 2018-09-27 MTU Aero Engines AG Turbomachine having a mounting element
US20190049114A1 (en) * 2017-08-10 2019-02-14 General Electric Company Volute combustor for gas turbine engine
EP3770542A1 (en) * 2019-07-24 2021-01-27 Inline Heat Recovery Inc. Heat recovery unit

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JPH0239145U (en:Method) * 1988-09-09 1990-03-15

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US3665806A (en) * 1968-09-30 1972-05-30 Lucas Industries Ltd Fluid operated servomechanism

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US2210916A (en) * 1938-04-05 1940-08-13 Sperry Gyroscope Co Inc Automatic pilot for dirigible craft
US2769912A (en) * 1954-04-12 1956-11-06 Phillips Petroleum Co Shut-off valve
US3665806A (en) * 1968-09-30 1972-05-30 Lucas Industries Ltd Fluid operated servomechanism

Cited By (12)

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Publication number Priority date Publication date Assignee Title
US20030178499A1 (en) * 2002-01-21 2003-09-25 Webasto Thermosysteme International Gmbh Vehicle heating appliance with a valve in the fuel supply
US6983890B2 (en) * 2002-01-21 2006-01-10 Webasto Thermosysteme International Gmbh Vehicle heating appliance with a valve in the fuel supply
US20060054301A1 (en) * 2004-02-19 2006-03-16 Mcray Richard F Variable area mass or area and mass species transfer device and method
US20090101302A1 (en) * 2007-10-17 2009-04-23 Tupper Myron D Dynamic heat exchanger
US20110185985A1 (en) * 2010-02-03 2011-08-04 Farshid Ahmady Fluid heating apparatus
US9353967B2 (en) * 2010-02-03 2016-05-31 Farshid Ahmady Fluid heating apparatus
US20130105105A1 (en) * 2011-10-31 2013-05-02 Harlod L. O'Brien Bimetallic seal for air heaters
US20180274389A1 (en) * 2017-03-23 2018-09-27 MTU Aero Engines AG Turbomachine having a mounting element
US20190049114A1 (en) * 2017-08-10 2019-02-14 General Electric Company Volute combustor for gas turbine engine
US10502424B2 (en) * 2017-08-10 2019-12-10 General Electric Company Volute combustor for gas turbine engine
EP3770542A1 (en) * 2019-07-24 2021-01-27 Inline Heat Recovery Inc. Heat recovery unit
US11441775B2 (en) 2019-07-24 2022-09-13 Inline Heat Recovery Inc. Heat recovery unit

Also Published As

Publication number Publication date
DE2206109B2 (de) 1975-02-13
DE2206109C3 (de) 1975-09-25
SU553944A3 (ru) 1977-04-05
DE2206109A1 (de) 1972-08-17
JPS506653B1 (en:Method) 1975-03-17
IT947434B (it) 1973-05-21
GB1382876A (en) 1975-02-05

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