EP0068002B1 - Etage de turbine - Google Patents
Etage de turbine Download PDFInfo
- Publication number
- EP0068002B1 EP0068002B1 EP82900113A EP82900113A EP0068002B1 EP 0068002 B1 EP0068002 B1 EP 0068002B1 EP 82900113 A EP82900113 A EP 82900113A EP 82900113 A EP82900113 A EP 82900113A EP 0068002 B1 EP0068002 B1 EP 0068002B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- grid
- stationary
- ceiling plate
- floor plate
- stationary grid
- 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.)
- Expired
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
- F01D5/145—Means for influencing boundary layers or secondary circulations
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
- F01D1/18—Non-positive-displacement machines or engines, e.g. steam turbines without stationary working-fluid guiding means
- F01D1/20—Non-positive-displacement machines or engines, e.g. steam turbines without stationary working-fluid guiding means traversed by the working-fluid substantially axially
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
- F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
- F01D5/143—Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2200/00—Mathematical features
- F05D2200/20—Special functions
- F05D2200/26—Special functions trigonometric
- F05D2200/261—Sine
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2200/00—Mathematical features
- F05D2200/20—Special functions
- F05D2200/26—Special functions trigonometric
- F05D2200/262—Cosine
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2200/00—Mathematical features
- F05D2200/20—Special functions
- F05D2200/26—Special functions trigonometric
- F05D2200/264—Cotangent
-
- 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
- Y10S415/00—Rotary kinetic fluid motors or pumps
- Y10S415/914—Device to control boundary layer
Definitions
- the present invention relates to a turbine stage comprising a circular fixed grid followed by a circular mobile grid, each grid comprising vanes mounted between a floor and a ceiling.
- This series of blades thus defines a series of channels traversed by a fluid, each channel being limited by two consecutive blades and by the floor and the ceiling.
- This slippage generates a whirlwind of trigonometric direction at the ceiling of the channel and of opposite direction on the floor for an observer placed downstream of the grid of blades of figure 1.
- the invention relates to a turbine stage comprising a circular fixed grid followed by a circular mobile grid, each grid comprising vanes mounted between a floor and a ceiling of revolution around the axis of the turbine, the pitch of the blades of the fixed grid being L s at the ceiling and L B at the floor and the outlet angle of the jet of fluid from the fixed grid with the plane of this grid being ⁇ 1S in line with the ceiling and ⁇ 1B in line with the floor, in which the distance to the axis of the ceiling decreases from the entry of the fixed grid towards the exit of the fixed grid where it has the value r s , then goes increasing from the entry of the movable grid where it has the value r s until the mobile gate exits.
- Such a turbine stage is known from British Patent No. 596,784.
- the curvature of the floor and the ceiling is calculated so that the pressure is constant in the intergrid space (at the outlet of the fixed grid) from bottom to top of this space, it that is, the radial static pressure gradient is zero.
- the meridian curvature of the ceiling in line with the intergrid plane is substantially equal to
- the invention also relates to a turbine stage comprising a circular fixed grid followed by a circular mobile grid comprising blades mounted between a floor and a ceiling of revolution around the axis of the turbine, the pitch of the blades of the fixed grid being L s at the ceiling and L B at the floor and the exit angle of the jet of fluid from the fixed grid with the plane of this grid being a 1S at the level of the ceiling and ⁇ 1B at the level of the floor in which the distance to l the floor axis varies continuously from the entry of the fixed grid towards the exit of said fixed grid where it reaches an extremum r B , then varies in the opposite direction in a continuous manner from the entry of the grid mobile where it has the value r B until the mobile grid exits.
- This turbine stage is also known from British Patent No. 596,784.
- the meridian curvature of the floor of the fixed grid in line with the intergrid plane is substantially equal to the difference the extremum r e being a minimum when the difference is negative and a maximum when the difference is positive.
- the radial gradient of intergrid static pressure is not zero, as in the British patent, but is equal to the tangential gradient of static intergrid pressure, which has the effect of confining the disturbed zone to the floor in a relatively small flow passage section.
- the two measurements can be combined on the ceiling and on the floor so as to confine the disturbed area on the ceiling and that on the floor in a relatively small flow passage section.
- the meridian curvature of the ceiling of the fixed grid to the right of the intergrid plane is substantially equal to thus the equality between the radial and tangential static pressure gradients at the outlet of the fixed grid in the vicinity of the ceiling is maintained.
- the meridian curvature of the fixed grid floor in front of the intergrid plane is substantially equal to the absolute value of the difference the extremum r e then being a minimum when the difference is negative and a maximum when the difference is positive, thus the equality between the gradients of radial and tangential static pressure in the vicinity of the floor at the outlet of the fixed grid is maintained.
- the turbine stage comprises the 2 combined variants, which makes it possible, on the one hand, to reduce the intensity of the vortices on the ceiling and on the floor and, on the other hand, to confine in a narrow area.
- the distance to the axis of the ceiling varies according to a curve having a maximum at the entry of the fixed grid and at the exit of the movable grid and a minimum in the intergrid plane.
- FIG. 1 there are shown two blades A and B which are part of a fixed grid and whose foot is fixed on a floor 1 and the head on a ceiling 2.
- the floor and the ceiling are usually cylindrical or frustoconical surfaces .
- the lower surface of dawn B, the upper surface of dawn A, floor 1 and ceiling 2 define a channel 3.
- FIG. 2 it is indicated at the outlet of a fixed grid in the vicinity of the upper surface of the dawn A the static pressure p s in the vicinity of the ceiling and the static pressure p B in the vicinity of the floor of the grid fixed blades.
- the pressure p s is greater than the pressure p B so that in the vicinity of the ceiling, the secondary vortex is amplified while it is damped in the vicinity of the floor.
- Static pressure constantly decreases from ceiling to floor.
- the evolution of the static radial pressure intergrille in a conventional turbine is represented in FIG. 3 by the curve in solid diagrammed line which starts from r B radius of the floor in the plane intergrille up to r s radius of the ceiling in the same plane and the dotted curve shows schematically the desired evolution.
- the meridian of the ceiling and / or vein floor of the fixed grid must have a curved shape.
- FIG. 5 there is shown a cylindrical section of the top of the blades A and B of a fixed grid.
- the angle ⁇ 1S designates the injection angle of the jet (in the following mobile grid) with the grid front in line with the ceiling, V 1 the absolute speed intergrids, V u the tangential component of the absolute speed intergrids and V m the projection of the absolute speed intergrille in the meridian plane.
- L s represents the pitch of the blades on the ceiling
- the angle ⁇ 1S is very easily calculated from the relation on sin ( ⁇ S being the width of the neck between the blades A and B in the vicinity of the ceiling).
- FIG. 6 there is shown a cylindrical section of the foot of the blades A and B of a fixed grid.
- the angle ⁇ 1B designates the injection angle of the jet (in the following movable grid) with the grid front.
- the pitch of vanes A and B on the floor is L B
- the width of the neck is ⁇ B
- the angle ⁇ 1B is very easily calculated from the relation
- the radial gradient of intergrid static pressure is determined by the following formula: with V m absolute speed intergrille in the meridian plane, p the meridian curvature of the fluid threads. p, r, p, Vu have the same meaning as in equation (1).
- R is negative in equation (2) when the meridian approaches the axis and R is positive when the meridian moves away from the axis.
- a 1 being the angle of injection of the jet with this grid front at level r and L is the spacing between 2 consecutive blades at the same level.
- AP is the pressure drop in the fixed grid. But according to Bernouilli's law By matching the values of and we find with the sign (+) for the floor and the sign (-) for the ceiling. Given that and
- FIG. 7 is shown in section a turbine stage according to the invention in which the effect of the secondary losses in the vicinity of the ceiling has been minimized.
- the fluid steam for example, goes along the arrow from right to left.
- the stage comprises a fixed grid 4 followed by a mobile grid 5.
- the fixed grid comprises vanes 6 mounted between a floor 1 and a ceiling 2.
- the movable grid 5 comprises vanes 7 mounted between a floor 11 and a ceiling 12.
- the ceiling 2 of the grid 4 is a surface of revolution around the axis of the turbine, the meridian of which is a half-arc of a sinusoid which approaches the axis, from the inlet to the outlet.
- the ceiling 12 of the grid 5 is substantially symmetrical with the ceiling 2 with respect to the intergrid plane which is perpendicular to the axis of the turbine.
- the floor is that of a conventional turbine.
- Figures 8 and 9 is shown in section a turbine stage according to the invention in which the effect of secondary losses in the vicinity of the floor has been minimized.
- the reference numbers are those of the references of FIG. 7 in which 100 has been added.
- the floor 101 of the fixed grid 104 is a surface of revolution around the axis of the turbine including the meridian is a half-arc of a sinusoid which approaches the axis, from the entry to the exit.
- the floor 111 of the movable grid 105 is substantially symmetrical with the floor 101 with respect to the intergrid plane.
- the curvature of the floor in the intergrid plane is In figure 9 the difference between is positive so that the meridian of the floor 101 'is for the fixed grid 104 a half-arc of sinusoid which moves away from the axis, from the entry towards the exit of the grid.
- the meridian of the floor 111 'of the movable grid 105 is the symmetrical of the meridian of the floor 101' with respect to the intergrid plane.
- FIG. 10 shows a turbine stage according to the invention with a ceiling similar to that of the stage in FIG. 7 and a floor similar to that in FIG. 8.
- the reference numbers have been increased by 200 by compared to those in figure 7.
- FIG. 11 a turbine stage according to the invention is shown with a ceiling like that of the turbine stage of FIG. 7 and a floor like that of FIG. 9.
- the numbers of references have been increased by 100 compared to those in Figure 9.
- Figures 12 and 13 are variants of Figures 10 and 11 in which the meridians of the floor 311 respectively 311 'and the ceiling 312 of the movable grid 305 are straight lines.
- FIG. 14 shows a section of a fixed grid with a surface of revolution about the axis comprising means for reducing the secondary losses in each channel limited by the upper surface 401 of a blade A and the lower surface 402 of a dawn B. These means are described for example in Belgian patent n ° 677 969.
- the floor and / or the ceiling were dug in the vicinity of the upper surface of dawn A, which causes a local decrease in the depression in line with the floor and / or ceiling.
- material 404 was brought to the floor and / or the ceiling in the vicinity of the lower surface of the vane B, which causes a local reduction in the overpressure in line with the floor and / or the ceiling.
- the internal shape of the fixed grid also has a periodicity radians, N D being the number of vanes of the directrix.
- N D being the number of vanes of the directrix.
- the tangential static pressure gradient in the vicinity of the ceiling is reduced by a factor X and / or the tangential static pressure gradient in the vicinity of the floor at the outlet of the fixed grid by a factor of X '.
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
- Crystals, And After-Treatments Of Crystals (AREA)
- Separation By Low-Temperature Treatments (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
AT82900113T ATE12291T1 (de) | 1981-01-05 | 1981-12-30 | Turbinenstufe. |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR8100039 | 1981-01-05 | ||
FR8100039 | 1981-03-17 |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0068002A1 EP0068002A1 (fr) | 1983-01-05 |
EP0068002B1 true EP0068002B1 (fr) | 1985-03-20 |
Family
ID=9253860
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP82900113A Expired EP0068002B1 (fr) | 1981-01-05 | 1981-12-30 | Etage de turbine |
Country Status (8)
Country | Link |
---|---|
US (2) | US4778338A (ja) |
EP (1) | EP0068002B1 (ja) |
JP (1) | JPH023003B2 (ja) |
AT (1) | ATE12291T1 (ja) |
DE (1) | DE3169495D1 (ja) |
IT (1) | IT1154402B (ja) |
WO (1) | WO1982002418A1 (ja) |
ZA (1) | ZA8234B (ja) |
Families Citing this family (24)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
ZA8234B (en) * | 1981-01-05 | 1982-11-24 | Alsthom Atlantique | A turbine stage |
US5447413A (en) * | 1992-03-31 | 1995-09-05 | Dresser-Rand Company | Stator endwall for an elastic-fluid turbine |
ES2163678T3 (es) * | 1996-03-28 | 2002-02-01 | Mtu Aero Engines Gmbh | Hoja de paleta para turbinas. |
JPH10184304A (ja) * | 1996-12-27 | 1998-07-14 | Toshiba Corp | 軸流タービンのタービンノズルおよびタービン動翼 |
EP0943784A1 (de) * | 1998-03-19 | 1999-09-22 | Asea Brown Boveri AG | Konturierter Kanal einer axialen Strömungsmaschine |
DE10233033A1 (de) * | 2002-07-20 | 2004-01-29 | Rolls-Royce Deutschland Ltd & Co Kg | Strömungs-Arbeits-Maschine mit überhöhtem Rotor-Stator-Kontraktionsverhältnis |
ITTO20030894A1 (it) * | 2003-11-11 | 2005-05-12 | Ansaldo Energia Spa | Perfezionamenti in statori di turbine assiali. |
US7217096B2 (en) * | 2004-12-13 | 2007-05-15 | General Electric Company | Fillet energized turbine stage |
US7134842B2 (en) * | 2004-12-24 | 2006-11-14 | General Electric Company | Scalloped surface turbine stage |
US7249933B2 (en) * | 2005-01-10 | 2007-07-31 | General Electric Company | Funnel fillet turbine stage |
US7220100B2 (en) * | 2005-04-14 | 2007-05-22 | General Electric Company | Crescentic ramp turbine stage |
US7465155B2 (en) * | 2006-02-27 | 2008-12-16 | Honeywell International Inc. | Non-axisymmetric end wall contouring for a turbomachine blade row |
WO2007113149A1 (de) * | 2006-03-31 | 2007-10-11 | Alstom Technology Ltd | Leitschaufel für eine strömungsmaschine, insbesondere für eine dampfturbine |
GB0704426D0 (en) * | 2007-03-08 | 2007-04-18 | Rolls Royce Plc | Aerofoil members for a turbomachine |
DE102007020025A1 (de) * | 2007-04-27 | 2008-10-30 | Honda Motor Co., Ltd. | Form eines Gaskanals in einer Axialströmungs-Gasturbinenmaschine |
US8647067B2 (en) * | 2008-12-09 | 2014-02-11 | General Electric Company | Banked platform turbine blade |
US20100303604A1 (en) * | 2009-05-27 | 2010-12-02 | Dresser-Rand Company | System and method to reduce acoustic signature using profiled stage design |
US8312729B2 (en) * | 2009-09-21 | 2012-11-20 | Honeywell International Inc. | Flow discouraging systems and gas turbine engines |
CN102235241A (zh) * | 2011-06-28 | 2011-11-09 | 北京动力机械研究所 | 入口带大扩张通道的低压涡轮结构 |
US8864452B2 (en) * | 2011-07-12 | 2014-10-21 | Siemens Energy, Inc. | Flow directing member for gas turbine engine |
US9267386B2 (en) | 2012-06-29 | 2016-02-23 | United Technologies Corporation | Fairing assembly |
EP2885506B8 (en) | 2012-08-17 | 2021-03-31 | Raytheon Technologies Corporation | Contoured flowpath surface |
DE102014225689A1 (de) | 2014-12-12 | 2016-07-14 | MTU Aero Engines AG | Strömungsmaschine mit Ringraumerweiterung und Schaufel |
JP6684593B2 (ja) * | 2016-01-07 | 2020-04-22 | 三菱重工業株式会社 | 軸流タービン |
Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR398600A (fr) * | 1909-01-18 | 1909-06-08 | Arnold Kienast | Perfectionnements aux turbines |
Family Cites Families (20)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2735612A (en) * | 1956-02-21 | hausmann | ||
CA613424A (en) * | 1961-01-31 | H. Pavlecka Vladimir | Method and apparatus of compressing fluid | |
DE579989C (de) * | 1933-07-04 | Karl Roeder Dr Ing | Kopfringlose Beschaufelung fuer axialbeaufschlagte Dampf- oder Gasturbinen | |
US1632907A (en) * | 1924-03-03 | 1927-06-21 | Losel Franz | High-pressure steam turbine and method of utilizing high-pressure steam therein |
FR677969A (fr) * | 1929-07-06 | 1930-03-17 | Monture de sac | |
DE560687C (de) * | 1930-08-28 | 1932-10-06 | Escher Wyss Maschf Ag | Schaufelung fuer Dampf- und Gasturbinen |
GB564336A (en) * | 1942-06-29 | 1944-09-22 | Escher Wyss Maschf Ag | Multistage axial flow compressor |
US2392673A (en) * | 1943-08-27 | 1946-01-08 | Gen Electric | Elastic fluid turbine |
FR996967A (fr) * | 1949-09-06 | 1951-12-31 | Rateau Soc | Perfectionnement aux aubages de turbomachines |
US2859910A (en) * | 1954-03-29 | 1958-11-11 | Edward A Stalker | Stators for axial flow compressors |
US2991929A (en) * | 1955-05-12 | 1961-07-11 | Stalker Corp | Supersonic compressors |
US2846137A (en) * | 1955-06-03 | 1958-08-05 | Gen Electric | Construction for axial-flow turbomachinery |
US2981066A (en) * | 1956-04-12 | 1961-04-25 | Elmer G Johnson | Turbo machine |
FR1442526A (fr) * | 1965-05-07 | 1966-06-17 | Rateau Soc | Perfectionnements aux canaux courbes parcourus par un gaz ou une vapeur |
US3804335A (en) * | 1973-05-21 | 1974-04-16 | J Sohre | Vaneless supersonic nozzle |
FR2438157A1 (fr) * | 1978-10-05 | 1980-04-30 | Alsthom Atlantique | Grille d'aubes pour turbine ou compresseur |
FR2471501A1 (fr) * | 1979-12-17 | 1981-06-19 | Inst Francais Du Petrole | Dispositif de pompage de fluides diphasiques |
US4371311A (en) * | 1980-04-28 | 1983-02-01 | United Technologies Corporation | Compression section for an axial flow rotary machine |
US4460309A (en) * | 1980-04-28 | 1984-07-17 | United Technologies Corporation | Compression section for an axial flow rotary machine |
ZA8234B (en) * | 1981-01-05 | 1982-11-24 | Alsthom Atlantique | A turbine stage |
-
1981
- 1981-01-05 ZA ZA8234A patent/ZA8234B/xx unknown
- 1981-12-30 JP JP57500218A patent/JPH023003B2/ja not_active Expired - Lifetime
- 1981-12-30 US US06/414,253 patent/US4778338A/en not_active Expired - Fee Related
- 1981-12-30 EP EP82900113A patent/EP0068002B1/fr not_active Expired
- 1981-12-30 DE DE8282900113T patent/DE3169495D1/de not_active Expired
- 1981-12-30 AT AT82900113T patent/ATE12291T1/de active
- 1981-12-30 WO PCT/FR1981/000172 patent/WO1982002418A1/en active IP Right Grant
-
1982
- 1982-01-04 IT IT67002/82A patent/IT1154402B/it active
-
1988
- 1988-07-01 US US07/214,992 patent/US4832567A/en not_active Expired - Fee Related
Patent Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR398600A (fr) * | 1909-01-18 | 1909-06-08 | Arnold Kienast | Perfectionnements aux turbines |
Also Published As
Publication number | Publication date |
---|---|
JPS57502074A (ja) | 1982-11-18 |
JPH023003B2 (ja) | 1990-01-22 |
DE3169495D1 (en) | 1985-04-25 |
US4832567A (en) | 1989-05-23 |
EP0068002A1 (fr) | 1983-01-05 |
ATE12291T1 (de) | 1985-04-15 |
IT1154402B (it) | 1987-01-21 |
US4778338A (en) | 1988-10-18 |
WO1982002418A1 (en) | 1982-07-22 |
IT8267002A0 (it) | 1982-01-04 |
ZA8234B (en) | 1982-11-24 |
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Legal Events
Date | Code | Title | Description |
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PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
|
AK | Designated contracting states |
Designated state(s): AT BE CH DE FR GB LI LU NL SE |
|
17P | Request for examination filed |
Effective date: 19821228 |
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GRAA | (expected) grant |
Free format text: ORIGINAL CODE: 0009210 |
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AK | Designated contracting states |
Designated state(s): AT BE CH DE FR GB LI LU NL SE |
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