WO2004013557A1 - Echangeur thermique et son utilisation - Google Patents

Echangeur thermique et son utilisation Download PDF

Info

Publication number
WO2004013557A1
WO2004013557A1 PCT/GB2003/003380 GB0303380W WO2004013557A1 WO 2004013557 A1 WO2004013557 A1 WO 2004013557A1 GB 0303380 W GB0303380 W GB 0303380W WO 2004013557 A1 WO2004013557 A1 WO 2004013557A1
Authority
WO
WIPO (PCT)
Prior art keywords
channel members
heat exchanger
row
fluid
exchanger according
Prior art date
Application number
PCT/GB2003/003380
Other languages
English (en)
Inventor
Tanzi Besant
John Coplin
Albert Demargne
Original Assignee
Hiflux Limited
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 Hiflux Limited filed Critical Hiflux Limited
Priority to AU2003252972A priority Critical patent/AU2003252972A1/en
Priority to GB0501813A priority patent/GB2408319B/en
Publication of WO2004013557A1 publication Critical patent/WO2004013557A1/fr

Links

Classifications

    • 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
    • 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
    • F28D7/00—Heat-exchange apparatus having stationary tubular conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
    • F28D7/16—Heat-exchange apparatus having stationary tubular conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall the conduits being arranged in parallel spaced relation
    • F28D7/1684—Heat-exchange apparatus having stationary tubular conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall the conduits being arranged in parallel spaced relation the conduits having a non-circular cross-section
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F28—HEAT EXCHANGE IN GENERAL
    • F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
    • F28F1/00—Tubular elements; Assemblies of tubular elements
    • F28F1/02—Tubular elements of cross-section which is non-circular
    • F28F1/04—Tubular elements of cross-section which is non-circular polygonal, e.g. rectangular
    • F28F1/045—Tubular elements of cross-section which is non-circular polygonal, e.g. rectangular with assemblies of stacked elements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F28—HEAT EXCHANGE IN GENERAL
    • F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
    • F28F1/00—Tubular elements; Assemblies of tubular elements
    • F28F1/10—Tubular elements and assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with projections, with recesses
    • F28F1/12—Tubular elements and assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with projections, with recesses the means being only outside the tubular element
    • F28F1/14—Tubular elements and assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with projections, with recesses the means being only outside the tubular element and extending longitudinally
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F28—HEAT EXCHANGE IN GENERAL
    • F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
    • F28F13/00—Arrangements for modifying heat-transfer, e.g. increasing, decreasing
    • F28F13/06—Arrangements for modifying heat-transfer, e.g. increasing, decreasing by affecting the pattern of flow of the heat-exchange media
    • 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
    • F28D21/00—Heat-exchange apparatus not covered by any of the groups F28D1/00 - F28D20/00
    • F28D21/0001—Recuperative heat exchangers
    • F28D21/0003—Recuperative heat exchangers the heat being recuperated from exhaust gases

Definitions

  • This present invention relates to a heat exchanger and its use in various industrial applications. Various such applications are set-out in more detail hereinbelow but use in a gas turbine arrangement constitutes one preferred class of embodiments.
  • Gas turbines are often used in distributed electrical power generation and also in transport applications. There are problems in providing appropriate heat exchangers (recuperators) in this and other applications, which operate sufficiently well and also are of appropriate size, cost and performance.
  • tube and fin heat exchangers comprise a structure in which one fluid runs back and forth along lengths of tubes of substantially circular internal cross section spaced apart from each other by an approximately uniform distance.
  • US-A-4 602 674 describes a two-circuit heat exchanger with a helical arrangement of non-circular tubes. However, fluid is not directed through gaps between tubes.
  • the present invention provides a matrix of rows of spaced apart hollow tubular channel members wherein the channel members in one row are staggered relative to those in an adjacent row, the spacings between members in one row directing fluid flowing around the outside of the channel members onto respective channel members in the adjacent row whereupon the flow is split.
  • the matrix has one or more features endowing aerodynamic advantage and/or enhanced thermal efficiency and/or manufacturing advantage.
  • a non-exhaustive list of those features comprises spacing between the rows (at least at one point) being less than the maximum spacing between at least two adjacent members in a row, at least two channel members having an external protrusion for guiding fluid into the spacings between adjacent members in the (next) adjacent row, individual channel members comprising a plurality of tubular elements, and one or more subsidiary directing passages being situated through the channel members.
  • Other features which may be taken alone or in combination with each other and/or in combination with one or more of the features recited in the preceding sentence, in order to define any aspect of the present invention will be described further hereinbelow.
  • a heat exchanger comprising a plurality of elongate channel members arranged substantially parallel to and spaced apart from each other in their longitudinal extent to define therebetween, a first flow path for a first fluid, said channel members each comprising an interior defining a second flow path for a second fluid, the channel members being arranged in rows and columns such that the channel members in a first row are staggered relative to the channel members in a second rows adjacent to said first row, whereby the spacing between adjacent members in the first row forms directing passages in the first flow path for causing impingement of first fluid on respective channel members in the second row;
  • each directing passage having an entry region and an exit region
  • the first flow path being split after each impingement from a respective directing passage such that the spacing between the first and second rows defines respective first and second communicating passages;
  • each communicating passage being less than the minimum cross-sectional area of the respective directing passage.
  • a heat exchanger wherein the space between the tubular channel members is connected to a source of a first fluid so that said first fluid can pass through that space and the interior of the channel members is connected to a source of a second fluid so that said second fluid can pass through the interior of those channel members.
  • the first fluid is hotter than the second fluid when exiting their respective sources.
  • respective means are provided for forcing the first fluid from its source through the space between the channel members and for forcing the second fluid from its source through the interior of the channel members.
  • the sources of first and second fluids may comprise respective first and second manifolds.
  • the matrix or assembly of tubular channel members is conveniently contained within a casing or jacket.
  • a heat exchanger according to any aspect of the invention may optionally contain one or more additional tubular members which are in a different configuration to that defined for tubular channel members in the broadest expression of that aspect of the invention, eg at the top, bottom and/or side of the overall tubular matrix.
  • a heat exchanger according to the present invention preferably comprises at least 3, eg. 10 or more channel members. There is no upper limit to the number of channel members but depending on application, this could go up to 100's or 1,000's, eg. 10,000.
  • the directing and communicating passages are elongate in one dimension. Where there is reference to the cross-sectional area of such a passage at any given point and at that point, the passage has an axis of symmetry in the general direction of flow of the first fluid, the cross-sectional area refers to the cross section orthogonal to that axis. Where the passage is asymmetric at that point, then the cross sectional area refers to the cross section orthogonal to the major direction of flow at that point.
  • the concept utilised by the present invention is based on a multi-stage apparatus that relies on flow impingement that is usually counter-flow from stage to stage but mutually normal with regard to the directions of flow of the two fluids, to achieve high levels of heat transfer over a moderate amount of heat transfer surface area.
  • the use of impingement allows an arrangement of heat transfer surfaces that no longer requires equal areas on the hot and cold sides, or close intimacy. This enables the use of thicker, high-temperature materials manufactured in such a way as to deliver the robustness and reliability that is lacking in current recuperators. In that form, the heat exchanger is then capable of sustained high temperature operation.
  • impingement of the flows can be performed at velocities that are comparatively higher than those encountered in conventional heat exchangers. This is enhanced by the use of aerodynamics to shape the passages and ensure that only a very small amount of pressure loss is generated in the entire impingement and flow process.
  • the first fluid is preferably hotter than the second fluid, although a reverse situation is not excluded.
  • the first fluid flows through the matrix of channel members, in a directional perpendicular to the rows, and around the outside of the channel members.
  • the second fluid flows through the interiors of the channel members.
  • the direction of flow of the first fluid is in a direction at right angles to the direction of flow of the second fluid.
  • the direction of flow of the second fluid in one row is opposite to that in the adjacent row or rows.
  • the channel members may be substantially straight and/or substantially curved.
  • the overall structure of the heat exchanger may either be a block of square or rectangular cross section, or else cylindrical.
  • the dimension along the length of the channels will be termed the height, or z axis.
  • the dimension through the cross section of the channel members in the direction of flow of the first fluid, perpendicular to the rows of channel members will be termed the length, or y axis.
  • the dimension through the cross section of the channel members perpendicular to the direction of flow of the first fluid and parallel to the rows of channel members will be termed the width, or x axis.
  • the concepts of length, width and height will be applied to the individual channel members as well as to the total heat exchanger matrix.
  • a "row" will have a substantially circular profile rather than be substantially straight.
  • each of the channel members in any one stage, most preferably over all stages, has a substantially identical cross-sectional shape but preferably the cross- sectional shape of a least two of the channel members in the length (y) direction has an axis of symmetry.
  • the channel members are preferably in the form of an elongate element and most preferably, are made from castable high temperature alloys, for example of the type commonly used for fabrication of turbine blades. Alternatively, high temperature ceramics may be used. Depending on the material in question the method of manufacture may be casting, superplastic forming with diffusion bonding, sheet metal fabrication or extrusion, the latter being more suitable for intended use at intermediate or low temperatures.
  • channel member is generally or substantially rectangular (but as described below, external surface protrusions can be advantageous) and for reasons such aerodynamic flow control and physical strength, this rectangular shape preferably has rounded corners.
  • the communicating passages may be curved so that the walls of the channel members are convex on the upstream side relative to the first fluid flow direction and concave on the downstream side.
  • the channel members can be regarded as a arranged in a matrix comprising rows and columns, wherein the channel members in one row are staggered width- wise in relation to the channel members in an adjacent row or both adjacent rows, such as are bricks in a wall.
  • the gaps between adjacent channel members in one row face a position approximately centre in the or each respective channel member in adjacent row or both adjacent rows, in other arrangements the gaps may be situated so as to be laterally offset from this approximately centre position.
  • the profile of the first flow path is preferably chosen to ensure fast (accelerated) flow in the impinging jet of first fluid as it meets a channel member in an adjacent row. This is preferably achieved by one or more restrictions in the flow path, particularly such restriction (s) situated in the passage interconnecting the gaps between adjacent channel members in a given row with the equivalent gaps in an adjacent row, in which passage the impinging jet is formed, and/or situated in the region of corners or turns on the first flow path. As well as increasing the velocity of flow in the impinging jet, such restrictions can be used to minimize separations and wakes, resulting in reduced resistance to flow and improved heat transfer.
  • first transition regions are defined between the exit regions of each respective directing passage in the first row and the respective communicating channels and the channel members in the first row have an external profile such that they are curved in convex fashion in the first transition regions.
  • second transition regions are defined between the respective communicating passages and respective directing passages are defined between adjacent channel members in a third row adjacent to the second row and the channel members in the second row have an external profile such that they are curved in convex fashion in the second transition regions. It is especially preferred that the communicating passages widen after the first transition regions and then taper to narrow until a point just before the second transition regions.
  • the communicating passages may be generally straight relative to the cross section of the channel members. However, they may be curved along at least part of their extent relative to the cross section at the channel members.
  • the channel members may even be of aerofoil shape (longest axis in cross section arranged in the length, y, direction).
  • a preferred arrangement with generally straight communicating passages is where at least two of the channel members are generally rectangular in cross section. Most preferably, these the rectangular cross-sections have rounded corners.
  • the gap between adjacent members in one row is positioned to direct first fluid onto a position generally mid-way along the width of a channel member in an adjacent row. Then it is preferred that the cross section of at least two of the channel members has a respective axis of symmetry in the length (y) direction.
  • the gap between adjacent members in one row is positioned to direct first fluid onto a position staggered with respect to the middle point along the width of a channel member in an adjacent row.
  • an external surface of at least two of the channel members in one row has a protrusion for diverting first fluid into the directing passage between channel members in an adjacent row.
  • At least one, preferably substantially all of the channel members have a protrusion for directing first fluid into the gap between adjacent channel member(s) in an adjacent row.
  • At least two of the channel members are provided with means for increasing their external surface area, for example external fins, surface dimples or other protrusions. These are advantageously located on an external surface facing an adjacent row which is downstream of the direction of flow of the first fluid. Thus, they will be on the same side (external surface) of the channel member as the aforementioned protrusion (when such exists).
  • at least two of the channel members are preferably provided with internal support members such as ties, webs, ribs or posts.
  • a channel member may also comprise a plurality of elements of substantially circular or other cross section connected side-by-side in the width (x) direction. The elements may differ in diameter from each other to determine the appropriate communicating channel profile.
  • Another variant provides segmentation of at least one, preferably substantially all of the channel members to define one or more secondary directing passages. These generally will have a maximum cross section less than that of the (primary) directing passages. These secondary passages may be straight or at least partially curved but will generally run parallel to the (primary) directing passages. In this way, there is enhanced transfer of downward momentum to enhance heat transfer.
  • At least two of the channel members are substantially straight in their elongate extent.
  • at least two of the channel members are curved over at least part of their elongated extent.
  • the rows of channel members are substantially straight. In one cylindrical configurations, the rows of channel members are arranged in concentric circles.
  • the internal space in the channel members constitutes a flow path for the second fluid.
  • a respective manifold can be arranged at each end of the matrix to interconnect the interior flow paths of the individual channel members.
  • any means for transferring second fluid from one row to the next may be employed and it is even possible for the channel members from row to row to be fabricated as a continuous tubular structure.
  • a heat exchanger comprising a plurality of elongate channel members arranged substantially parallel to and spaced apart from each other in their longitudinal extent to define therebetween, a first flow path for a first fluid, said channel members each comprising an interior defining a second flow path for a second fluid, the channel members being arranged in rows and columns such that the channel members in a first row are staggered relative to the channel members in a second rows adjacent to said first row, whereby the spacing between adjacent members in the first row forms directing passages in the first flow path for causing impingement of first fluid on respective channel members in the second row;
  • each directing passage having an entry region and an exit region
  • the first flow path being split after each impingement from a respective directing passage such that the spacing between the first and second rows defines respective first and second communicating passages;
  • a third aspect of the present invention provides a heat exchanger comprising a plurality of elongate channel members arranged substantially parallel to and spaced apart from each other in their longitudinal extent to define therebetween, a first flow path for a first fluid, said channel members each comprising an interior defining a second flow path for a second fluid, the channel members being arranged in rows and columns such that the channel members in a first row are staggered relative to the channel members in a second rows adjacent to said first row, whereby the spacing between adjacent members in the first row forms directing passages in the first flow path for causing impingement of first fluid on respective channel members in the second row;
  • each directing passage having an entry region and an exit region
  • the first flow path being split after each impingement from a respective directing passage such that the spacing between the first and second rows defines respective first and second communicating passages;
  • the channel members comprising a plurality of tubular elements connected side-by-side in their elongate extent.
  • a fourth aspect of the present invention provides a heat exchanger comprising a plurality of elongate channel members arranged substantially parallel to and spaced apart from each other in their longitudinal extent to define therebetween, a first flow path for a first fluid, said channel members each comprising an interior defining a second flow path for a second fluid, the channel members being arranged in rows and columns such that the channel members in a first row are staggered relative to the channel members in a second rows adjacent to said first row, whereby the spacing between adjacent members in the first row forms directing passages in the first flow path for causing impingement of first fluid on respective channel members in the second row;
  • each directing passage having an entry region and an exit region
  • the first flow path being split after each impingement from a respective directing passage such that the spacing between the first and second rows defines respective first and second communicating passages;
  • At least one of the channel members being provided with one or more secondary directing passages.
  • the heat exchanger of any aspect of the present invention is especially suited for use with a power producing apparatus.
  • the power producing apparatus may comprise a gas turbine.
  • an especially preferred embodiment of the present invention is a recuperator for a gas turbine.
  • a recuperator uses hot turbine exhaust gas to preheat compressor delivery air prior to entry into the combustor, thus reducing the amount of fuel required to achieve the high turbine entry temperatures needed for efficiency.
  • Figure 1 of the accompanying drawings shows a recuperated gas turbine which is used to drive a generator for production of electricity.
  • a compressor 1 , a turbine 3 and a generator 5 are arranged on a common shaft 7.
  • the turbine 3 drives the compressor 1 and generator 5.
  • the compressor 1 comprises cold intake air which is passed through a recuperator 9 and then, to a combustor 11 , the output of which drives the turbine 3. This defines a cold path 13 through the recuperator.
  • the exhaust is of the turbine 3 is directed through the hot path 17 of the recuperator to heat compressed air in the cold path 13 and then exits through final exhaust 19.
  • revolution of the shaft 7 also turns the generator 5 to produce electricity.
  • recuperators The performance of recuperators is quantified primarily in terms of heat exchange effectiveness and the associated pressure loss.
  • the effectiveness of a recuperator is a measure of the percentage of heat extracted from the hot exhaust gas and transferred into the cool air from the compressor. A good recuperator should have an effectiveness of over 75%. Pressure loss in the recuperator must be kept low, as it tends to reduce the expansion ratio through the turbine, which in turn is detrimental to the power output. Pressure losses should be below 10%, ideally below 5%.
  • recuperator greatly enhances the efficiency of the type of small gas turbines that are used for distributed power generation.
  • current unrecuperated microturbines operate at efficiencies of under 20% compared to around 30% or more for the recuperated cycle. Waste heat in the exhaust from the recuperator can be used to provider domestic heating. (Combined Heat and Power) which effectively further improves the efficiency for the end user.
  • Combined Heat and Power Combined Heat and Power
  • the heat exchanger may be applied to a turbo-charger or a supercharger of a reciprocating engine power producer.
  • the heat exchanger may be used to cool air, and desirably after compression of the air in the turbocharger or super-charger, before the air enters the reciprocating power producer.
  • the invention provides a boiler with a heat transfer mechanism in the form of a heat exchanger apparatus according to the present invention.
  • heat exchanger apparatus is used to preheat gas, prior to expansion of the gas in a gas expander.
  • High pressure gas is sometimes used to drive a turbine driven electrical power generator. Preheating the gas prior to expansion increases the power output and may prevent the formation of ice particles in the turbine expander.
  • the present invention may also be claimed in terms of a heat exchanger according to the present invention connected to a supply of the respective first and second fluids, either of which may be liquid or gas and either may be hotter than the other.
  • first and second fluids either of which may be liquid or gas and either may be hotter than the other.
  • first fluid is a hot gas
  • second fluid is a cold gas.
  • Figure 1 shows a schematic diagram of use of a recuperator with a conventional gas turbine
  • Figure 2 shows in perspective view, a recuperator element of a heat exchange recording to the present invention
  • Figure 3 shows a cross-section through a heat exchanger (recuperator) of the present invention, comprising a matrix of bricks of the kind shown in Fig 2;
  • Figure 4 shows a schematic diagram in cross-section of a typical impinging 2D jet.
  • Figure 5 shows a detailed cross-section through the recuperator shown in Fig 3, illustrating the contours of the hot flow path passages (internal cold passages not shown);
  • Figure 6 shows a rear perspective view of a single brick of the kind shown in Fig 2., with the manifold in place for interconnection of individual bricks to complete the fluid cold path;
  • Figure 7 shows a curved non-rectangular variant of the channel member formation shown in Figure 3;
  • Figure 8 shows a variant of the channel member formation shown in Figure 3, in which the channel members are split
  • Figure 9 shows a variant of the channel member formation shown in Figure 7, in which the channel members are split
  • Figure 10 shows an axial section through a turbine-generator combination, utilising a multi-segmented variant of the recuperator of the embodiment of Figures 2- 6;
  • Figure 11 shows a radial section along XI-XI of Figure 10
  • Figure 12 shows in plan view, an alternative multi-segment recuperator arrangement to that shown in Figures 10 and 11;
  • Figure 13 shows a first cylindrical equivalent of the channel member formation as shown in Figure 3, with axial height, circumferential width and radial length;
  • Figure 14 shows a second cylindrical equivalent of the channel member formation shown in Figure 3 with circumferential height, axial width and radial length;
  • Figure 15 shows a third cylindrical equivalent of the channel member formation shown in Figure 3 with circumferential width, axial length and radial height;
  • Figure 16 shows a side elevation of the arrangement shown in Figure 12;
  • Figure 17 shows another form of channel member made up of a series of tubular elements.
  • Figure 18 shows a variant at the channel member arrangement shown in Figure 3 but formed with secondary directing passages.
  • a recuperator according to one embodiment of the present invention is made up of rows of elongated, flat and hollow channel members 27 of approximately rectangular cross section. As explained in more detail hereinbelow, these channel members are assembled in close proximity to each other, thus forming passages through which hot gas is passed.
  • a perspective view of one of these basic rectangular elements (channel members 27) is shown in Figure 2.
  • Each channel member comprises a first wall 29 and a second wall 31 , substantially parallel to the first wall 29.
  • the first and second walls 29, 31 are spaced apart by a hollow passage 35, therebetween.
  • the first wall 29 and the second wall 31 are joined by respective third (side) wall 37 and fourth side wall 39, substantially parallel to the third side wall 37.
  • the hollow channel is also situated between these third and fourth side walls.
  • the height dimension (z) is denoted by arrow 41 and is parallel to the third and fourth side walls 37, 39.
  • the length dimension (y) is denoted by arrow 43, which is also parallel to third and fourth side walls 37, 39 but orthogonal to the height dimension denoted by arrow 41.
  • the direction of arrow 43 (y dimension) is in the direction from the first wall 29 to the second wall 31 and denotes the direction of flow of the first fluid.
  • wall 31 is downstream of wall 29 in the direction of flow of the first fluid.
  • the direction of flow of the second fluid is in the direction of arrow 41 (z).
  • the first fluid which flows around the outside of the channel member 27 is hot turbine gas.
  • the second fluid is cold air from the compressor.
  • first and second walls 29, 31 have plurality of web members 47, 49 etc. extending therebetween within the passage 35, extending laterally in the height (z) dimension parallel to arrow 41.
  • a plurality of fins 53, 55 etc. are arranged on the external surface 51 of second wall 31 and these extend parallel to the width (x) dimension 45.
  • the fins can be pitched fairly close together, which may also be beneficial from a structural point of view.
  • the combination of additional area and increased heat transfer coefficient using fin leads to a significant improvement in overall performance, which translates into a substantial reduction in the number of stages.
  • Figure 3 represents a cross-section through the recuperator along a plane normal to length of the basic elements.
  • the contours shown in Figure 3 are extruded in the out-of-page direction.
  • FIG. 3 denotes the channel member shown in Figure 2.
  • this drawing shows a plurality of such channel members denoted 65, 67, 69 etc. Not all of these channel members bear a reference numeral, for reasons of clarity.
  • the matrix may comprise, for example, from 4 to 20 channel members.
  • the channel members 27, 65, 67, 69 etc. are arranged in staggered fashion like bricks in a wall.
  • the web members such as 47, 49 etc. are only shown for the channel members in the middle of the drawing. However, it can be taken that all channel members are substantially identical.
  • each channel member 27 etc. is spaced apart from the adjacent channel members. The spaces therebetween define the flow path 75 for the hot gas which is the first fluid.
  • the direction of flow of the hot gas is generally that denoted by the length dimension arrow 43.
  • the hot gas (first fluid) impinges on the septum faces 71 etc. of these channel members and flows around each side 37, 39.
  • the cold air (second fluid) flows internally up or down each channel 35 etc. (alternatively from row to row) of these channel members, so that heat is transferred in a classical convective manner.
  • the downstream (with regard to the hot gas) surface 31 etc. has formed at its midpoint, a protrusion 57 etc.
  • the gaps between adjacent channel members 27 etc. in each row or stage 73 etc. form a jet path (directing passage) 77 etc. so that the hot gas directed through each such jet 77 strikes a point approximately mid-way along the first wall 29 etc., i.e. the septum 71 etc.
  • the flow is then split into respective left 79 and right 81 communicating channels to pass along the septum surface 71 before entering the top of the respective jets 83, 85 between adjacent channel members in the next row or stage.
  • each respective corner 87, 89, 91 , 93 etc. of each channel member is rounded on both its internal surface and external surface to improve aerodynamic properties and hence throughput and efficiency of heat transfer. This is further aided by provision of respective protrusions 57 etc. on the downstream side (relative to direction of the flow of the first fluid) on the relevant external surface 31 etc. of each channel member, as described above with reference to Figure 2.
  • Figure 4 shows a typical configuration for such a confined jet or directing passage 77 etc.
  • the face on which the flow impinges is the septum 71.
  • the dimensions of the channel members and passages therebetween are sized relative to the nozzle width, D.
  • D the nozzle width
  • the lateral width of the channel, X/D is typically greater than 10, while the flow-wise length of the brick, Z D, is about 3.
  • the passage height, H/D is generally between 0.5 and 1.
  • the height of the bricks is about 60 times the nozzle width D.
  • the recuperator is made up of 24 channel members per stage (row), with anywhere between 10 and 30 stages.
  • the heat transfer performance of the device is largely conditioned by the ability of the hot side to deliver the heat to the channel members, in this case via the impingement process.
  • the extent to which the impingement can deliver a significant rate of heat transfer depends on the mass flow passed through the machine and on the number and dimensions of the nozzles.
  • a typical metal thickness is of the order of one or two millimetres, resulting in a moderate metal temperature gradient of about 0.15K.
  • these values are given by way of example only and should not be construed as limiting in any way.
  • the pick-up heat at the cold-side solid surfaces is achieved through classical convection, with flow velocities that are sufficiently large to generate heat transfer coefficients (for example) of about 200 W/(m 2 K) or more.
  • This combined with the relatively large amount of "exposed" heat transfer area means that the cold side is more than able to absorb the heat transferred from the hot side. It should be noted that the pressure loss generated on the cold side is still expected to be acceptable because of the higher density of the flow dropping the volume flow rate.
  • a directing passage 95 between adjacent channel members 97, 99 in a row of channel members directs a jet of hot (first) fluid 101 towards a septum 103 constituted by an upper surface of another channel member 105 directly below it.
  • the hot (first) fluid then splits to flow along respective communicating passages 107, 109. That part of the fluid flowing along communicating passage 109 will now be described by way of example. However, it can be understood that the following description of the path applies to each split flow after impingement upon the septum of the channel member below.
  • a transition region 111 which has a convex curve as viewed from the outside of the channel member, i.e. viewed from within the first fluid flow path.
  • the communicating passage 109 a first narrow cross section at region 113.
  • the communicating passage 109 then immediately starts to widen at a region 115 to reach its maximum cross sectional area at a region 117, approximately one quarter of the way along the communicating passage 109 from the directing passage 95.
  • the communicating passage 109 then tapers in cross sectional area along its length up to a second narrow cross section at point 119, just before the corner 89 of the channel member where the septum 103 terminates and is contiguous with a turn to define the next directing passage 77.
  • the variation in cross sectional area of the directing passage 109 is formed by variations in the lower surface 121 of the upper channel member which forms one side of the above- mentioned directing passage 109.
  • the septum (upper surface) 103 of the lower channel member is substantially flat.
  • the narrowed region 119 at the distal end of tapered region 121 has a cross sectional area somewhat less than the maximum cross sectional area 117 of the channel 109, but slightly narrower than the cross sectional area of initial constricted region 113, after the convex turn 111.
  • the fluid then enters another pair of communicating passages 123, 124, which are constricted, then widen, then taper in the same fashion as the communicating passage 109, before the fluid meets the next directing passage 83 etc.
  • the communicating passage 123 runs back parallel to the first mentioned communicating passage 109.
  • the cold side air flows along the length of each channel member and is turned and prepared for the next stage by a manifold that fits at either end of the matrix of channel members.
  • the manifold is illustrated in Figure 6.
  • the exit of the manifold matches that of either the previous or subsequent stage (row of channel members) thus sealing cold side air from the hot passages.
  • the external shapes of the manifold form the top and bottom endwalls of the hot passages.
  • the internal channel 35 of a channel member such as channel member 27 shown in Figure 2 communicates with a corresponding internal passage of a channel member in an adjacent row, via a manifold 125 arranged at one end 127 thereof.
  • a corresponding manifold 129 is arranged at the other end 131 of the channel member 27 to communicate with the internal passage of a channel member in an adjacent channel member on the other side from the first mentioned adjacent channel member connected by the first mentioned manifold 125.
  • the aerodynamics of the recuperator embodiment depicted in Figures 2- 6 is determined by the need to minimise the pressure loss and to provide flow conditions that enable enough heat to be transferred. On the hot side, this is achieved mainly through selective contraction and diffusion of the flow passage. This is done both to enhance the heat transfer performance and to mitigate the effects of wakes and flow recirculations.
  • the septum surface is left flat and contouring of the passage prior to turn and mixing is achieved by shaping the rearward surface of the channel members of the upstream rows (see Figures 3 and 5).
  • a bulbous corner is used to help the flow turn around the impingement, also helped by the direction of the impingement pressure gradient.
  • This is followed by a reasonably strong diffusion starting (for example) with X/D of about 1 , which is made sustainable partly by the presence of the blockage generated by the fin passages.
  • the passage height starts a gentle contraction that is maintained until the end of septum turn is initiated.
  • the purpose of this contraction is to maintain a slight increase in wall shear stress that is favourable to heat transfer.
  • the finned passages are terminated well before the turn.
  • the exemplary embodiment shown in the Figures 2-6 is based on channel members of substantially rectangular cross section with rounded corners and an elongate protrusion running the length of the middle of one major face thereof.
  • the spacing in a row or rows may be positioned such that the directing passages are offset and do not face the centre of the septum of the channel member(s) in the adjacent row, along the width (x) direction.
  • matrices of channel members of respectively different cross sections are also possible.
  • each directing passage directs the jet to impinge upon the center of the septum of the next channel member.
  • the major external surfaces of these channel members are curved.
  • each directing channel defined between respective channel members in each row, denoted as 171 , 173, 175 etc. directs the jet of hot gas (first fluid) onto a septum surface of convex curvature.
  • the channel members have respective curved profiles as depicted by numerals 185, 187 etc., which join in the middle to define a protrusion such as 189 (equivalent to protrusion 57 in the first embodiment) to direct the fluid into the next directing passages.
  • the curvature of facing concave 185, 187 surfaces and convex 193, 195 septum surfaces have substantially the same curvature.
  • each directing passage 173, 175 etc. have a greater cross sectional area than that of the communicating passages 181 , 191.
  • the communicating passages may be profiled as described for passages 109, 123 and the first embodiment, except that their overall shape and that of the septum surfaces, is curved rather than straight.
  • cross sectional profiles of the channel members of the embodiments described in Figures 2-7 are continuous, i.e. the external walls thereof, are uninterrupted.
  • multi-part channel members with discontinuous external surfaces are also possible.
  • aerodynamic flow determining features such as the protrusion 57 shown in relation to Figures 2-6, can be formed as solid separate pieces, adjacent the part of the channel member which carries the second fluid, or they may be separate but also, themselves convey fluid.
  • each channel member in cross section is subdivided along the width (x) direction denoted by arrow 201.
  • These channel members 203, 205, 207 are arranged in rows 209, 211 etc. and define directing passages between channel members in adjacent rows, such as 213, 215 etc.
  • communicating passages 217, 219 are defined between adjacent rows.
  • each channel member has a protrusion such as 221 facing the next directing passage 215 etc.
  • a division 223, 225, 227, in the width (201, x) direction means that each channel member 203, 205 etc. has an upper portion 229, 231 etc. which is substantially rectangular in cross section with rounded corners, the upper surface of which 233, 235 etc. forms a respective septum surface for having a jet of hot fluid impinging thereon.
  • the lower (other side) surface 237, 239 faces an upper surface 241 , 245 etc. of a lower portion 247, 249 of the respective channel members 203, 205 etc. These facing upper surfaces 241 , 245 of the lower portion, are substantially flat.
  • FIG. 9 shows another matrix which is an adaptation of the embodiment depicted in Figure 7, in the same way as that of Figure 9 is adapted from the embodiment of Figures 2-6.
  • the protrusion such as 259 which faces the next directing passage, is formed as a separate portion 261 etc. formed below an upper portion 263 etc., with a substantially semicircular gap such as 265 between the two portions 261 , 263.
  • the directing passages are shown as the gap 267 etc. between adjacent channel members in each row and the communicating passages 269, 271 etc. are generally profiled like the communicating passages 189, 191 in the embodiment of Figure 7.
  • FIG. 10 there is shown a gas turbine 275 connected by a shaft 277 to an electrical generator 279.
  • Reference numeral 280 denotes insulation and numeral 282 denotes a fan cooled air gap around the shaft.
  • the exhaust 281 between the turbine and the generator housing 283 is lead radially from the axis of symmetry (along shaft 277) to six recuperator modules 285, 287, 289, 291, 293, 295.
  • each recuperator such as shown by numeral 295 for recuperator module 285 to the outside such as shown by numeral 297 for module 285 and then into a collector chamber 299 leading to a chimney 301.
  • This enables a recuperator of optimal dimensions to be segmented so as to fit efficiently around the turbine generator assembly.
  • in the radial direction corresponds to the length (y) dimension.
  • the height or z direction is also in the plane of the paper but is perpendicular to the length (y) and the width (x) is parallel to the axis of the shaft 277, into the plane of the paper.
  • FIG. 12 there is shown an alternative arrangement of recuperator in conjunction with a gas turbine.
  • a shaft 303 is connected at its left hand end to a gas turbine (not shown) and its right hand end, to a generator 305.
  • four pairs of heat exchanger modules respectively denoted 307, 309, 311 , 313 are arranged around the shaft 303 but oriented so that the height (z) is into the plane of the paper, the length (y) dimension is parallel to the axis of the shaft 303 and the width (x) is disposed radially with respect to the axis of the shaft 303.
  • Arrows 310 denote hot air flow whilst insulation is denoted by reference numeral 312.
  • the turbine exhaust is led into the space 315 between the respective pairs of recuperator modules (307, 309) and (311, 313), respectively.
  • the hot gas after heat exchange, then passes to the chimney 317 from its associated collector arranged around the recuperator modules, via the outside surfaces 319, 321 and 323, 325, i.e. the reverse sides of the modules to the sides receiving the exhaust input (315) in the space between the respective modules.
  • Figure 13 shows an arrangement whereby the channel members 327, 331 , 333 etc. in cross section are in the form of circumferential segments (i.e. curved) with their width (x) running circumferentially (or parallel to the circumference) and height (z) into the plane of the paper.
  • the "rows" of channel members are curved segments at or parallel to the circumference.
  • the length (y) direction is therefore radial (r in cylindrical co-ordinate system).
  • the gaps 335 etc. between adjacent channel members form the directing passages for the impinging sets, facing the respective concave curved septum surfaces 337 etc of the respective channel members in the next "row” outwardly (flow of first fluid being from the centre, radially outwards).
  • the elongate dimension i.e. height (z) runs circumferentially with the length (y) corresponding to the direction of flow of the first fluid, running radially from centre to edge (r in cylindrical co-ordinates) and the width (x) being axial (into the plane of the paper, equivalent to z in a cylindrical coordinate system).
  • Figure 14 shows a plurality of channel members 339, 341 , 343 etc with their height (z) dimension running circumferentially, i.e. they are curved in their elongate extent.
  • the width is axial and the length is a radial (e).
  • the septum 44 surfaces 345 etc. are curved in concave fashion around the circumference.
  • the directing passages 347 etc. are radial so that in the radial length direction, first fluid (hot gas) blows radially from inside to outside. Since the ends 349 etc. of the channel members 339 etc.
  • the manifolds (not shown) for directing second (cold gas) fluid from one stage to the next are situated in gaps 349 etc. running the length of the stacks of channel members.
  • the height (z) is radial so that in their elongate extent, the channel members 351, 353, 357 etc. taper in cross-sectional area, i.e. they widen from each end 359 etc. closest to the cylindrical axis of symmetry to the other end 361 etc. at the periphery.
  • the flow (y) direction is into the plane of the paper along the axial length of the device.
  • the ends 359, 361 , etc. are curved in the width (x) dimension, following the cylindrical curvature.
  • Figure 17 shows a cross-section to an alternative form of channel member 391.
  • This comprises five thin section tubes 393, 395, 397 etc. which are positioned side by side in their elongate extent and held together by welds along their elongate points of respective mutual contact 399, 401 etc.
  • a skin 403 made of sheet metal or metal foil is wrapped around the tubes 393 etc. and secured together by a weld line (not shown) along the longitudinal direction.
  • the space 405 between the skin and the tubes is filled with a metal honeycomb mesh structure 407 to aid thermal conductivity between the tubes 393 etc. and skin 403.
  • the upper surface 409 of the skin 403 forms the septum surface.
  • the lower surface 411 of the skin 403 is shaped in the form of an elongate ridge 413 running the longitudinal extent of the channel member 391, directly underneath the middle tube 397. This ridge 413 functions as the protrusion 57 in the embodiment of Figure 2.
  • This form of construction allows the channel members to be fabricated from thinner materials by relatively simple methods.
  • Figure 18 shows a recuperator arrangement which is analogous to that shown in Figure 3, wherein individual channel members 415, 417, 419 etc. are spaced apart by primary directing passages 421 etc.
  • the channel members are hollow as in other embodiments but for clarity are shown in this figure by solid stippling.
  • These channel members 415 etc. are segmented so as to be divided by secondary directing channels 423, 425, 427, 429 etc. substantially parallel to the primary directing passages 421 etc.
  • the secondary directing passages are smaller in cross section than the primary directing passages. In this way, the downward momentum is better transferred to fluid in the communicating passages 431 etc. to improve heat transfer to the upper septum surfaces 433 etc.
  • the longitudinal "spine" on the lower surface 435 of each channel member 415 etc. is in the form of a protrusion 437, as with the embodiment shown in Figure 3.

Landscapes

  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Thermal Sciences (AREA)
  • Geometry (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)

Abstract

L'invention concerne un échangeur thermique comprenant une pluralité d'éléments (27) à canal allongé sensiblement parallèles et espacés les uns des autres dans leur sens longitudinal, de façon à définir entre eux un premier chemin d'écoulement pour un premier fluide. Lesdits éléments à canal (27) comprennent chacun une partie intérieure définissant un second chemin d'écoulement pour un second fluide. Ils sont disposés en rangées et en colonnes, de sorte que lesdits éléments de la première rangée sont placés en quinconce par rapport aux éléments (27) de la seconde rangée adjacente à la première rangée. L'espace entre les éléments adjacents dans la première rangée forme des passages d'orientation dans le premier chemin d'écoulement, de façon à entraîner une action du premier fluide sur les éléments à canal correspondants dans la seconde rangée.
PCT/GB2003/003380 2002-08-01 2003-08-01 Echangeur thermique et son utilisation WO2004013557A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
AU2003252972A AU2003252972A1 (en) 2002-08-01 2003-08-01 Heat exchanger and use thereof
GB0501813A GB2408319B (en) 2002-08-01 2003-08-01 Heat exchanger and use thereof

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GBGB0217916.6A GB0217916D0 (en) 2002-08-01 2002-08-01 Heat exchanger and use thereof
GB0217916.6 2002-08-01

Publications (1)

Publication Number Publication Date
WO2004013557A1 true WO2004013557A1 (fr) 2004-02-12

Family

ID=9941583

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/GB2003/003380 WO2004013557A1 (fr) 2002-08-01 2003-08-01 Echangeur thermique et son utilisation

Country Status (3)

Country Link
AU (1) AU2003252972A1 (fr)
GB (2) GB0217916D0 (fr)
WO (1) WO2004013557A1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2012112889A2 (fr) * 2011-02-18 2012-08-23 Ethier Jason Dispositifs d'écoulement de fluide ayant une géométrie verticalement simple et procédés de fabrication de ces derniers
JP2014526669A (ja) * 2011-09-15 2014-10-06 ギルバート，パトリック 熱交換器等のための配管アセンブリ
EP3242105A1 (fr) * 2016-05-06 2017-11-08 United Technologies Corporation Échangeur de chaleur à gradient de température de chaleur
US10030580B2 (en) 2014-04-11 2018-07-24 Dynamo Micropower Corporation Micro gas turbine systems and uses thereof
EP3183524A4 (fr) * 2014-08-22 2018-08-29 Mohawk Innovative Technology Inc. Échangeur thermique à faible perte de charge à haute efficacité

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR658208A (fr) * 1927-12-09 1929-06-01 Cie De Fives Lille Pour Const Perfectionnements aux échangeurs thermiques
US1979859A (en) * 1932-08-29 1934-11-06 Brown Roger Stuart Tube for boilers, heat exchangers, and the like
GB468980A (en) * 1936-03-16 1937-07-16 Harold Livsey Improvements in or connected with tubular feed water heaters and like heat exchangers
GB576094A (en) * 1942-08-12 1946-03-19 Bristol Aeroplane Co Ltd Improvements in or relating to heat-exchangers
GB739050A (en) * 1951-11-28 1955-10-26 Andre Huet Improvements in or relating to heat exchangers
US4602674A (en) 1982-02-08 1986-07-29 Ab Elge-Verken Two-circuit heat exchanger
GB2271418A (en) * 1992-10-09 1994-04-13 Mtu Muenchen Gmbh Alternate rows of drop-shaped heat exchange tubes arranged to face in opposite directions
FR2784313A1 (fr) * 1998-10-07 2000-04-14 Paul Brunon Dispositif pour creer un effet tourbillonnaire dans un ecoulement fluidique
WO2002097354A1 (fr) * 2001-05-25 2002-12-05 Anglia Polytechnic University Echangeur thermique

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR658208A (fr) * 1927-12-09 1929-06-01 Cie De Fives Lille Pour Const Perfectionnements aux échangeurs thermiques
US1979859A (en) * 1932-08-29 1934-11-06 Brown Roger Stuart Tube for boilers, heat exchangers, and the like
GB468980A (en) * 1936-03-16 1937-07-16 Harold Livsey Improvements in or connected with tubular feed water heaters and like heat exchangers
GB576094A (en) * 1942-08-12 1946-03-19 Bristol Aeroplane Co Ltd Improvements in or relating to heat-exchangers
GB739050A (en) * 1951-11-28 1955-10-26 Andre Huet Improvements in or relating to heat exchangers
US4602674A (en) 1982-02-08 1986-07-29 Ab Elge-Verken Two-circuit heat exchanger
GB2271418A (en) * 1992-10-09 1994-04-13 Mtu Muenchen Gmbh Alternate rows of drop-shaped heat exchange tubes arranged to face in opposite directions
FR2784313A1 (fr) * 1998-10-07 2000-04-14 Paul Brunon Dispositif pour creer un effet tourbillonnaire dans un ecoulement fluidique
WO2002097354A1 (fr) * 2001-05-25 2002-12-05 Anglia Polytechnic University Echangeur thermique

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2012112889A2 (fr) * 2011-02-18 2012-08-23 Ethier Jason Dispositifs d'écoulement de fluide ayant une géométrie verticalement simple et procédés de fabrication de ces derniers
WO2012112889A3 (fr) * 2011-02-18 2013-11-28 Ethier Jason Dispositifs d'écoulement de fluide ayant une géométrie verticalement simple et procédés de fabrication de ces derniers
US9217370B2 (en) 2011-02-18 2015-12-22 Dynamo Micropower Corporation Fluid flow devices with vertically simple geometry and methods of making the same
JP2014526669A (ja) * 2011-09-15 2014-10-06 ギルバート，パトリック 熱交換器等のための配管アセンブリ
US10030580B2 (en) 2014-04-11 2018-07-24 Dynamo Micropower Corporation Micro gas turbine systems and uses thereof
US10907543B2 (en) 2014-04-11 2021-02-02 Dynamo Micropower Corporation Micro gas turbine systems and uses thereof
EP3183524A4 (fr) * 2014-08-22 2018-08-29 Mohawk Innovative Technology Inc. Échangeur thermique à faible perte de charge à haute efficacité
US10094284B2 (en) 2014-08-22 2018-10-09 Mohawk Innovative Technology, Inc. High effectiveness low pressure drop heat exchanger
EP3242105A1 (fr) * 2016-05-06 2017-11-08 United Technologies Corporation Échangeur de chaleur à gradient de température de chaleur
US10260422B2 (en) 2016-05-06 2019-04-16 United Technologies Corporation Heat temperature gradient heat exchanger

Also Published As

Publication number Publication date
AU2003252972A1 (en) 2004-02-23
GB2408319A (en) 2005-05-25
GB2408319B (en) 2006-03-01
GB0501813D0 (en) 2005-03-09
GB0217916D0 (en) 2002-09-11

Similar Documents

Publication Publication Date Title
AU2004278549B2 (en) Heat exchanger and use thereof
EP1834153B1 (fr) Echangeur de chaleur
JP4726911B2 (ja) 熱交換器
EP0887612B1 (fr) Structure de transfert de chaleur
US11248850B2 (en) Heat exchanger with interspersed arrangement of cross-flow structures
JP2002534627A (ja) ガスタービンエンジン用のレキュペレータ
US7347671B2 (en) Turbine blade turbulator cooling design
JP4019218B2 (ja) ロケットエンジン部材並びにロケットエンジン部材の製造方法
US11639828B2 (en) Heat exchanger
JP7440712B2 (ja) ガスタービンエンジン用のシュラウド
WO2004013557A1 (fr) Echangeur thermique et son utilisation
US20020073688A1 (en) Annular recuperator
KR101795039B1 (ko) 핀 및 튜브 열교환기
GB2451113A (en) Corrugations of a heat exchanger matrix having first and second different amplitudes
US11879691B2 (en) Counter-flow heat exchanger
CN216620751U (zh) 列管换热器结构
RU2755759C1 (ru) Рекуперативный теплообменник и способ его работы
JPH04358726A (ja) 車両用ガスタービン

Legal Events

Date Code Title Description
AK Designated states

Kind code of ref document: A1

Designated state(s): AE AG AL AM AT AU AZ BA BB BG BR BY BZ CA CH CN CO CR CU CZ DE DK DM DZ EC EE ES FI GB GD GE GH GM HR HU ID IL IN IS JP KE KG KP KR KZ LC LK LR LS LT LU LV MA MD MG MK MN MW MX MZ NI NO NZ OM PG PH PL PT RO RU SC SD SE SG SK SL SY TJ TM TN TR TT TZ UA UG US UZ VC VN YU ZA ZM ZW

AL Designated countries for regional patents

Kind code of ref document: A1

Designated state(s): GH GM KE LS MW MZ SD SL SZ TZ UG ZM ZW AM AZ BY KG KZ MD RU TJ TM AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IT LU MC NL PT RO SE SI SK TR BF BJ CF CG CI CM GA GN GQ GW ML MR NE SN TD TG

121 Ep: the epo has been informed by wipo that ep was designated in this application
ENP Entry into the national phase

Ref document number: 0501813

Country of ref document: GB

Kind code of ref document: A

Free format text: PCT FILING DATE = 20030801

122 Ep: pct application non-entry in european phase
NENP Non-entry into the national phase

Ref country code: JP

WWW Wipo information: withdrawn in national office

Country of ref document: JP