GB2287988A - Thermal protection jacket panel and method of making the panel - Google Patents
Thermal protection jacket panel and method of making the panel Download PDFInfo
- Publication number
- GB2287988A GB2287988A GB9504318A GB9504318A GB2287988A GB 2287988 A GB2287988 A GB 2287988A GB 9504318 A GB9504318 A GB 9504318A GB 9504318 A GB9504318 A GB 9504318A GB 2287988 A GB2287988 A GB 2287988A
- Authority
- GB
- United Kingdom
- Prior art keywords
- sheet
- rollers
- roller
- axis
- panel
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000004519 manufacturing process Methods 0.000 title claims description 16
- 238000000034 method Methods 0.000 claims description 10
- 238000005096 rolling process Methods 0.000 claims description 10
- 239000011295 pitch Substances 0.000 claims description 6
- 239000002184 metal Substances 0.000 claims description 2
- 230000035882 stress Effects 0.000 description 4
- 239000000463 material Substances 0.000 description 2
- 238000005452 bending Methods 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 239000006260 foam Substances 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 230000008646 thermal stress Effects 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/78—Other construction of jet pipes
- F02K1/82—Jet pipe walls, e.g. liners
- F02K1/822—Heat insulating structures or liners, cooling arrangements, e.g. post combustion liners; Infrared radiation suppressors
-
- 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
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Shaping Of Tube Ends By Bending Or Straightening (AREA)
- Pressure Welding/Diffusion-Bonding (AREA)
Abstract
A thermal protection jacket panel 9 having improved mechanical resistance to stress is constituted by a corrugated sheet 9 provided with transverse humps 10 of which the crests 11 follow wavy lines across the panel so as to effectively corrugate the panel not only longitudinally but also transversely. The panel is curved so as to be useable in a liner assembly for a turbojet afterburner. The panel may be made by using a dimensionally stable profiled roller 14S and imparting to it a reciprocating linear movement along its axis of rotation 12 as the sheet 9 is being rolled thereby. A reaction roller (14I) or a deformable plate may be applied to the other face of the sheet 9. <IMAGE>
Description
THERMAL PROTECTION JACKET PANEL AND
METHOD OF MAKING THE PANEL
The invention relates to panels for use in forming a thermal protection jacket in an afterburner duct of an aircraft turbo-engine, such as a turbojet engine, and also relates to the manufacture of such panels.
Turbojet engines, particularly those used on military aircraft, are often equipped with afterburners, which involves the provision of fuel dispensing devices, an exhaust nozzle and an afterburner duct.
As shown in Figure 1, the exhaust nozzle 1 is situated downstream of the exit from the combustion chamber 2, and as the exhaust gases are maintained at a very high temperature which would tend to damage the outer wall 4 of the exhaust nozzle the nozzle is fitted with a thermal protection jacket 3. An airflow is also provided in an afterburner duct 5 defined between the thermal protection jacket 3 and the outer wall 4 of the nozzle 1.
In use the thermal protection jacket 3 is subjected to a high number of mechanical and thermal stresses. In order to withstand these stresses composite materials are used to manufacture the panels which are assembled to form the thermal protection jacket 3. The panels 6 are in fact assembled to form cylindrical stages which are then themselves assembled together so that the joint lines between the panels are offset from stage to stage.
As shown in Figure 2 thermal protection jackets generally as described above and currently in use have a corrugated structure along their longitudinal axis 7. In other words, the panels of the thermal protection jacket each comprise a part cylindrical section having folds 8 disposed side by side in the direction of the longitudinal axis 7 of the thermal protection jacket.
These folds 8 form corrugations which enable the thermal protection jacket to offer a greater resistance to mechanical stresses and thus prevent implosion of the jacket.
However, in the longitudinal plane, if the upstream end of the jacket is fixed and a substantial stress is applied to the downstream end, the deflection obtained in the plane of application of this stress is almost identical to that induced in a cylindrical thermal protection jacket which is not corrugated.
With the aim of overcoming this drawback, according to the invention there is provided a thermal protection jacket panel for an aircraft turbo-engine, comprising a metal sheet which is arcuately curved about an axis parallel to the longitudinal axis of the sheet and which is corrugated along the longitudinal axis so as to form a succession of humps each extending across the whole width of the sheet following a wavy line which shifts longitudinally alternately from one side to the other of a transverse line substantially perpendicular to the longitudinal axis.
The invention further provides a method of making such a thermal protection jacket panel by rolling, wherein a dimensionally stable roller having a surface profile which corresponds to the desired corrugation profile to be produced is applied to one face of a sheet, the roller is driven to rotate about its axis, which is substantially parallel to the longitudinal axis of the jacket panel sheet, and relative linear movement between the roller and the sheet is created in a direction parallel to the axis of the roller as the roller and the sheet move relatively in a direction substantially perpendicular to the axis.
In a first embodiment of the method, two dimensionally stable rollers are applied simultaneously to the opposite faces of the sheet, the surface profile of one of the rollers being axially offset relative to the other by half the pitch of the profile, and the axes of the two rollers being mutually parallel and spaced from each other by a distance such that the gap between the surfaces of the rollers is equal to the thickness of the sheet.
Preferably the surface profiles of the rollers include several pitches of corrugations.
In a second embodiment of the method a deformable second roller is applied to the other face of the sheet opposite the first roller, the axes of rotation of the two rollers being parallel.
In a third embodiment of the method the roller is applied to the face of the sheet while the opposite face of the sheet is in contact with a deformable flat plate which is fixed to the frame of the machine tool being used and the dimensions of which are at least equal to those of the sheet.
In the first two embodiments of the method, the sheet may be fixed to the table of the machine tool in order to be driven parallelly relative to the two rollers.
Alternatively, the sheet may be fixed and the rollers moved linearly parallel to their axes of rotation.
In the manufacturing method in accordance with the invention it is possible to curve each sheet about an axis parallel to the longitudinal axis of the sheet either after rolling the sheet to form the corrugations or during the rolling to form the corrugations.
Various embodiments of the invention will now be described, by way of example only, with reference to the accompanying diagrammatic drawings in which:
Figure 1 is a axial cross-section of a turbojet engine in which a thermal protection jacket is provided in the afterburner duct of the exhaust nozzle;
Figure 2 is a perspective view of a thermal protection jacket panel of known construction;
Figure 3 is a perspective view of one embodiment of a thermal protection jacket panel in accordance with the invention;
Figure 4 is a perspective view of a portion of the thermal protection jacket panel of Figure 3, prior to the curving of the panel, together with a pair of rollers which may be used in a first embodiment of the method of making the panel in accordance with the invention;
Figure 5 is a side view of a pair of rollers as used in a second embodiment of the method of making a panel in accordance with the invention; and,
Figure 6 is a side view of part of the apparatus used in a third embodiment of the method of making a panel in accordance with the invention.
One embodiment of a thermal protection jacket panel 6 in accordance with the invention is shown in Figure 3 and includes a succession of humps 10 which together form a corrugated or undulating surface in the direction of the longitudinal axis 7 of the panel. Each of these humps 10 follows a wavy line transversely across the panel 6 such that the crests 11 of the humps together make successive alternating changes of direction along the longitudinal axis 7 as the humps are traced across the panel. When a number of the panels are assembled to form a complete thermal protection jacket, the humps 10 are continuous around the whole of the circumference of the thermal protection jacket and are regularly spaced along its length. As a result of the wavy lines followed by the crests of the humps, in any transverse plane yog the jacket will exhibit a variation in height around the circumference (i.e. a variation in the distance of the jacket from its axis 7). It will thus be understood that the mechanical stability of the thermal protection jacket, and of the individual panels, will be improved not only on bending but also in torsion.
It will be noted that the shape of the wavy line followed by each of the humps 10 may or may not be sinusoidal, the principle being that there should be a variation of the position of the hump in the direction of the longitudinal axis 7 as the hump progresses across the panel.
Figure 4 shows part of such a panel before it is curved about the longitudinal axis, illustrating the humps 10 and in particular the wavy course of their crests 11.
Figure 4 also shows two dimensionally stable rollers 14S and 14I for use in manufacturing the panel. There can also be seen in this figure a fixed vertical member 15 representing the machine tool carrying these two rollers 14S and 14I. Their respective axes of rotation 12 and 13 are parallel and horizontal, and their respective surfaces 16, 26 are of a shape corresponding to the corrugation profile to be given to a sheet 9 in forming the panel 6. The upper roller 14S is made to bear upon the upper surface of the sheet 9, while the lower roller 14I bears upon the lower surface of the sheet 9.
The surface profiles of the rollers 14S and 14I are mutually offset along their respective axes 12 and 13 so that a trough 17 on the first roller 14S is disposed opposite a crest 29 on the second roller 14I and vice versa. In other words, the shape of the surface 16 of one roller is the inverse of the shape of the surface 26 of the other roller.
A gap is provided between the surfaces 16, 26 of the two rollers 14S and 14I, and preferably the size of this gap is equal to the initial thickness of the sheet 9 which is to form the thermal protection jacket panel.
It will be easily understood that if one of the rollers, for example the roller 14S, is driven in rotation around its axis 12, as shown by the arrow 18, the sheet 9 will tend to move along the axis Oy from the moment it is introduced between the two rollers 14S and 14I. Only one of these rollers needs to be driven in rotation for the assembly to be able to operate, although both of the rollers may be driven.
It will be seen that if the assembly composed of the fixed member 15 and the rollers 14 is made to perform a linear reciprocation along the axis Ox shown in Figure 4, it will be possible to form, during the movement of the sheet 9 relative to this assembly along the axis Oy, a wavy hump 10 across the sheet. In other words, it is possible to create, along the axis Ox, variation in the position of each of the humps 10, thus defining curves for the crests 11 which wind alternately to the left and to the right of median lines parallel to the axis Oy.
It will be noted that in Figure 4 one of the rollers has been showm with a trough 17 and two crests 19. This represents one and a half pitches of the profile.
Obviously, rollers having lengths equal to several pitches may be used to increase the rate of production.
Referring now to Figure 5, an alternative method of manufacture is illustrated in which a dimensionally stable roller 14 similar to the roller 14S of the previous embodiment is arranged to be driven in rotation around its axis 12 in the direction of arrow 18. In this embodiment, however, the second roller 20, which is rotatably mounted about an axis 13 parallel to the axis 12, is made of a flexible deformable material, such as a foam. In this case, the second roller 20 is deformed only when the sheet 9 is passing between the rollers and is being deformed under the action of the first dimensionally stable roller 14.
Figure 6 illustrates another possible method which uses an upper dimensionally stable roller 14 rotatably mounted about its axis 12 and arranged to bear on the upper surface 9S of the sheet 9. In this case the lower surface 91 bears on a flat plate 20 which is fixed on a table 21 of the rolling machine, for example a numerically controlled machining unit. The plate 20 is preferably deformable, being made for example of a foamed material, and must have dimensions at least equal to those of the sheet 9 which is to be shaped.
Generally, in most of these cases, the sheet 9 is fixed in translation, that is to say it is fixed to the frame of the machine tool on which it is to be rolled, and the roller 14 (Figure 6) or the two rollers 14S and 14I (Figures 4 and 5) are movable linearly along their axes 12 and 13. In this way the relative alternating lateral movement between the rollers 14, 141, 14S, 20 and the sheet 9 is effected to produce the wavy lines of the crests 11 of the humps 10 which are formed as the sheet is rolled.
In the embodiment shown in Figure 4, it is possible that the sheet 9 may be moved in the direction of the axis Ox, while the rollers 14S and 14I remain fixed in this direction.
In all these cases, the corrugated sheet which is produced is subsequently curved to obtain the desired arcuate curve about the axis 7 as shown in Figure 3.
It is possible, however, for the corrugations to be formed as the sheet is being curved arcuately about the axis 7. In this case it is possible either to use two dimensionally stable rollers, or one deformable roller together with a dimensionally stable roller as previously described.
If the reciprocating movement of the roller(s) is sinusoidal, the lines of the crests 11 obtained will also be sinusoidal.
Thermal protection jackets constructed form panels made in accordance with the invention have an increased rigidity in the longitudinal plane compared to thermal protection jackets made from panels which do not have the double corrugation. The corrugated structure reduces deformation in the downstream zone of the jacket.
Furthermore, the structure prevents the formation of hot points, and the infrared signature of the thermal protection jacket is more discrete.
Claims (10)
1. A thermal protection jacket panel for an aircraft turbo-engine, comprising a metal sheet which is arcuately curved about an axis parallel to the longitudinal axis of the sheet and which is corrugated along the longitudinal axis so as to form a succession of humps each extending across the whole width of the sheet following a wavy line which shifts longitudinally alternately from one side to the other of a transverse line substantially perpendicular to the longitudinal axis.
2. A method of making a panel according to claim 1 by rolling, comprising applying simultaneously to the opposite faces of a sheet two dimensionally stable rollers having surface profiles corresponding to the longitudinal corrugation profile to be imparted to the sheet, the surface profile of one of the rollers being axially offset relative to the other by half the pitch of the profile, and the axes of the two rollers being mutually parallel and spaced from each other by a distance such that the gap between the surfaces of the rollers is equal to the thickness of the sheet;
driving at least one of the rollers to rotate about its axis; and,
causing relative linear movement between the rollers and the sheet in a direction parallel to the axes of the rollers as the sheet passes between the rollers in a direction substantially perpendicular to the axes.
3. A method according to claim 2, in which the surface profile of the rollers include several pitches of corrugations.
4. A method of making a panel according to claim 1 by rolling, comprising:
applying to one face of a sheet a dimensionally stable first roller having a surface profile which corresponds to the longitudinal corrugation profile to be imparted to the sheet;
applying a deformable second roller to the other face of the sheet opposite the first roller;
driving the first roller to rotate about its axis; and,
causing relative linear movement between the rollers and the sheet in a direction parallel to the axes of the rollers as the sheet passes between the rollers in a direction substantially perpendicular to the axes.
5. A method of making a panel according to claim 1 by rolling, comprising:
applying to one face of a sheet a dimensionally stable roller having a surface profile which corresponds to the longitudinal corrugation profile to be imparted to the sheet;
applying simultaneously to the other face of the sheet a deformable flat plate which is fixed to the table of the rolling machine being used and the dimensions of which are at least equal to those of the sheet;
driving the roller to rotate about its axis; and,
causing relative linear movement between the roller and the sheet in a direction parallel to the axis of the roller as the sheet passes between the roller and the deformable plate in a direction substantially perpendicular to the axis.
6. A method according to any one of claims 2 to 4, in which the rollers are moved linearly relative to the sheet.
7. A method according to any one of claims 2 to 6, in which the sheet is curved about an axis parallel to the longitudinal axis of the sheet after the sheet has been corrugated by the rolling.
8. A method according to any one of claims 2 to 6, in which the sheet is curved about an axis parallel to its longitudinal axis during the rolling of the sheet to form the corrugations.
9. A panel according to claim 1, substantially as described with reference to Figure 3 of the accompanying drawings.
10. A method of making a panel according to claim 1, substantially as described with reference to any one of
Figures 4 to 6 of the accompanying drawings.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR9402442A FR2716933B1 (en) | 1994-03-03 | 1994-03-03 | Thermal protection jacket element for a turbomachine and its manufacturing processes. |
Publications (3)
| Publication Number | Publication Date |
|---|---|
| GB9504318D0 GB9504318D0 (en) | 1995-04-19 |
| GB2287988A true GB2287988A (en) | 1995-10-04 |
| GB2287988B GB2287988B (en) | 1997-09-17 |
Family
ID=9460630
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB9504318A Expired - Fee Related GB2287988B (en) | 1994-03-03 | 1995-03-03 | Method of making a panel for a thermal protection jacket |
Country Status (2)
| Country | Link |
|---|---|
| FR (1) | FR2716933B1 (en) |
| GB (1) | GB2287988B (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1441180A1 (en) * | 2003-01-27 | 2004-07-28 | Siemens Aktiengesellschaft | Heatshield, combustion chamber and gas turbine |
| EP1353127A3 (en) * | 2002-04-10 | 2005-01-12 | General Electric Company | Annular one-piece corrugated liner for combustor of a gas turbine engine |
| EP1924058A2 (en) | 2004-09-20 | 2008-05-21 | QUALCOMM Incorporated | Electronic device with three movable layers |
| GB2457333A (en) * | 2008-02-08 | 2009-08-12 | Nichias Corp | Rolled sheet with orthogonal sinusoidal profiles |
| EP3514363A1 (en) * | 2018-01-19 | 2019-07-24 | Rolls-Royce plc | Aircraft nozzle |
| RU2729560C2 (en) * | 2018-06-14 | 2020-08-07 | Публичное акционерное общество "ОДК-Уфимское моторостроительное производственное объединение" (ПАО "ОДК-УМПО") | Jet turbine flat nozzle |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB836088A (en) * | 1957-03-18 | 1960-06-01 | Gen Motors Corp | Improvements in turbojet engine afterburners |
| GB1354159A (en) * | 1970-12-02 | 1974-06-05 | Gewiss L V | Manufacture of corrugated structures |
| US3918285A (en) * | 1967-06-21 | 1975-11-11 | Tuyaux Metalliques Flexibles S | Method and apparatus for forming flexible corrugated members |
| EP0486133A1 (en) * | 1990-11-15 | 1992-05-20 | General Electric Company | Film cooled combustor liner for gas turbine |
| WO1993005901A1 (en) * | 1991-09-20 | 1993-04-01 | Jan Gunnar Sergenius | Material in the form of a strip, plate, foil, sheet, board or the like, which is provided with a stiffening corrugation or embossing |
Family Cites Families (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB204422A (en) * | 1922-07-05 | 1923-10-04 | Marcus Albert Popham | Improved means of fixing the heads of polo sticks to cane shafts |
| GB624285A (en) * | 1946-07-01 | 1949-06-01 | Westinghouse Electric Int Co | Improvements in or relating to combustion apparatus |
| US2477583A (en) * | 1946-07-25 | 1949-08-02 | Westinghouse Electric Corp | Combustion chamber construction |
| GB745533A (en) * | 1953-01-27 | 1956-02-29 | Frank Morris Gilbert | Improvements in or relating to machines for the corrugation of metal sheets |
| US2794319A (en) * | 1953-03-02 | 1957-06-04 | Westinghouse Electric Corp | Afterburner shell construction |
| CA1005365A (en) * | 1973-05-10 | 1977-02-15 | Charles D. Mclain | Patterned tubing and a method of fabricating same from metallic strip |
| DE2453876B2 (en) * | 1974-11-13 | 1976-09-09 | Siegwart, Emil, 6603 Sulzbach | DEVICE FOR MANUFACTURING WINDING TUBES |
| US4018072A (en) * | 1975-10-22 | 1977-04-19 | Pacific Roller Die Co., Inc. | End recorrugator |
| DE3035234C2 (en) * | 1980-09-18 | 1982-07-08 | August Wilhelm 5901 Wilnsdorf Schäfer | Device for manufacturing a corrugated tube compensator from a circular cylindrical sheet metal tube section |
| US4823583A (en) * | 1987-06-11 | 1989-04-25 | W. R. Grace & Co.-Conn. | Particulate trap |
-
1994
- 1994-03-03 FR FR9402442A patent/FR2716933B1/en not_active Expired - Fee Related
-
1995
- 1995-03-03 GB GB9504318A patent/GB2287988B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB836088A (en) * | 1957-03-18 | 1960-06-01 | Gen Motors Corp | Improvements in turbojet engine afterburners |
| US3918285A (en) * | 1967-06-21 | 1975-11-11 | Tuyaux Metalliques Flexibles S | Method and apparatus for forming flexible corrugated members |
| GB1354159A (en) * | 1970-12-02 | 1974-06-05 | Gewiss L V | Manufacture of corrugated structures |
| EP0486133A1 (en) * | 1990-11-15 | 1992-05-20 | General Electric Company | Film cooled combustor liner for gas turbine |
| WO1993005901A1 (en) * | 1991-09-20 | 1993-04-01 | Jan Gunnar Sergenius | Material in the form of a strip, plate, foil, sheet, board or the like, which is provided with a stiffening corrugation or embossing |
Non-Patent Citations (1)
| Title |
|---|
| ROLLS-ROYCE PLC"THE JET ENGINE"1986,RR TECH.PUB. P.63FIG.6-6 * |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1353127A3 (en) * | 2002-04-10 | 2005-01-12 | General Electric Company | Annular one-piece corrugated liner for combustor of a gas turbine engine |
| EP1441180A1 (en) * | 2003-01-27 | 2004-07-28 | Siemens Aktiengesellschaft | Heatshield, combustion chamber and gas turbine |
| WO2004068035A2 (en) * | 2003-01-27 | 2004-08-12 | Siemens Aktiengesellschaft | Heat shield element, combustion chamber and gas turbine |
| WO2004068035A3 (en) * | 2003-01-27 | 2004-09-23 | Siemens Ag | Heat shield element, combustion chamber and gas turbine |
| EP1924058A2 (en) | 2004-09-20 | 2008-05-21 | QUALCOMM Incorporated | Electronic device with three movable layers |
| GB2457333A (en) * | 2008-02-08 | 2009-08-12 | Nichias Corp | Rolled sheet with orthogonal sinusoidal profiles |
| GB2457333B (en) * | 2008-02-08 | 2012-07-18 | Nichias Corp | Metallic molded sheet and heat shielding cover |
| US9149851B2 (en) | 2008-02-08 | 2015-10-06 | Nichias Corporation | Metallic molded sheet and heat shielding cover |
| EP3514363A1 (en) * | 2018-01-19 | 2019-07-24 | Rolls-Royce plc | Aircraft nozzle |
| US20190226423A1 (en) * | 2018-01-19 | 2019-07-25 | Rolls-Royce Plc | Aircraft nozzle |
| RU2729560C2 (en) * | 2018-06-14 | 2020-08-07 | Публичное акционерное общество "ОДК-Уфимское моторостроительное производственное объединение" (ПАО "ОДК-УМПО") | Jet turbine flat nozzle |
Also Published As
| Publication number | Publication date |
|---|---|
| FR2716933A1 (en) | 1995-09-08 |
| GB9504318D0 (en) | 1995-04-19 |
| GB2287988B (en) | 1997-09-17 |
| FR2716933B1 (en) | 1996-04-05 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PCNP | Patent ceased through non-payment of renewal fee |
Effective date: 20050303 |