EP0278434B1 - Rotorblatt - Google Patents

Rotorblatt Download PDF

Info

Publication number
EP0278434B1
EP0278434B1 EP88101712A EP88101712A EP0278434B1 EP 0278434 B1 EP0278434 B1 EP 0278434B1 EP 88101712 A EP88101712 A EP 88101712A EP 88101712 A EP88101712 A EP 88101712A EP 0278434 B1 EP0278434 B1 EP 0278434B1
Authority
EP
European Patent Office
Prior art keywords
blade
tip
axis
injection holes
degrees
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 - Lifetime
Application number
EP88101712A
Other languages
English (en)
French (fr)
Other versions
EP0278434A2 (de
EP0278434A3 (en
Inventor
Wolfgang P. Weinhold
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Individual
Original Assignee
Individual
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 Individual filed Critical Individual
Publication of EP0278434A2 publication Critical patent/EP0278434A2/de
Publication of EP0278434A3 publication Critical patent/EP0278434A3/en
Application granted granted Critical
Publication of EP0278434B1 publication Critical patent/EP0278434B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/10—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using sealing fluid, e.g. steam
    • 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
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • 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
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • F04D29/684—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps by fluid injection

Definitions

  • the present invention relates generally to blades used for example in turbomachinery and particularly to an improved turbine rotor blade.
  • a gap between the rotor and the casing exists in all turbomachinery such as gas turbine engines, compressors, radial compressors or pumps. Furthermore the minimum size of this gap is dictated by different rates of thermal expansion and radial growth of the blades and the casing during different operational conditions. It is well established that greater operating efficiency and power output of a turbomachinery may be achieved by any means reducing the tip leakage flow, controlling the boundary layer, and increasing inlet operation temperatures.
  • the tip leakage flow is the largest single source of energy loss in a turbomachine.
  • the interaction of leakage flow, blade, and annulus wall boundary layers and radial transport of mass, momentum and energy results in a highly complex flow field near the tip region of a turbomachine.
  • a further idea to reduce the tip leakage flow is the so called active clearance control. Thereby, the clearance or gap between the tip of the rotor blade and the casing of a turbine engine is maintained at a minimum by cooling or heating the casing of the turbo engine.
  • a cooling fluid flows through openings arranged in the tip surface of the blade and is directed against the tip side wall surfaces in a plane perpendicular to the side walls.
  • a rotor blade which has a cap disposed over the tip of the blade and formed of a plurality of chordwisely extending wafers stacked in the spanwise direction.
  • the outmost wafer is fabricated of an abrasive material.
  • at least two of said wafers have a plurality of laterally extending cooling passages for the flow of cooling air from spanwise cavity to the pressure side of the blade. Additional passages extend in the essentially spanwise direction across the cap and may be canted to increase the amount of convective cooling capacity.
  • An object of the invention is an improved configuration for a blade, especially a rotor blade in a turbine engine, by which the energy loss in the turbo engine is significantly reduced.
  • a further object of the invention is to reduce the tip leakage flow and to influence the complex flow field, thereby to reduce the corner separation zones and the energy losses produced by the complex flow field along the rotor blade.
  • Yet another object of the present invention is to cool the surfaces of the rotor blade, and its root.
  • the blade comprises canted elongated injection holes on the blade tip surface, the angles between the axes of said holes and the radial axis of the blade having a component in the direction of the local chordline of the tip surface between 15 and 75 degrees.
  • the injection holes are generally arranged in the tip surface essentially over the whole length thereof between the leading and the trailing edge of the blade.
  • chordline is approximately parallel to the main flow direction of the working gas along the rotor blade.
  • the main flow is thereby diverted in such a manner that no tip leakage flow occurs.
  • Similar injection holes may be provided in the sidewalls of the blade near the tip and the root regions and in the root portion of the blade. The fluid passing through these holes supports the reduction of the tip leakage flow and/or smooth the flow of the working fluid and make it more uniform.
  • tip leakage flow and the boundery layer on a blade as well as the corner separation zones may be controlled by this specific injection or suction arrangement located at the tip plane and at airfoil sections close to the tip and root plane, respectively, and at the root plane close to the airfoil section.
  • the nature of this tip leakage and boundary control structure is based on an air-curtain effect interwoven with an entrainment effect which reduces the tip leakage flow as well or controls the boundary layer in such a fashion that the efficiency of the stage increases and the flow field behind the blade is more uniform.
  • Such arrangements may also provide cooling in addition to decreasing tip leakage flow and boundary layer control.
  • Fig. 1 and 2 depict a blade 10 comprising a root portion 12 and a hollow airfoil portion 14.
  • the airfoil portion 14 of the blade 10 is contoured to define a concave side 16, a convex side 17, and has a blade tip 18.
  • the root portion 12 of the blade 10 secures the blade in a rotor disc (not shown) attached rigidly thereto and includes an inlet port 13 leading to various elongate injection holes 30, 40A, 40B, 50A, 50B, 60A and 60B.
  • the main flow direction of a working fluid is designated as MF.
  • the blade 10 has a generally flat surface 19 at the blade tip 18 structured to prevent tip leakage flow driven from the pressure 16 to the suction side 17 of blade 10, crossing the blade tip 18.
  • a radially extending collar may be provided along the border lines of the tip surface 19 to increase the flow resistance between pressure and suction side.
  • the blade tip 18 of the rotor blade 10 comprises a plurality of elongate injection holes 30, arranged in a pattern, for example as shown in a row along a chordline C of the tip surface 19, running from the leading to the trailing edge of the blade.
  • the injection holes 30 should be arranged over the whole peripheral length of the rotor blade 10.
  • the fluid support for the injection running through hollow airfoil portion 14 enters at inlet port 13.
  • the axes A of the elongated injection holes 30 are inclined with respect to the radial axis X of the blade under angles alpha less than 90 degrees. In this embodiment the angle is 45 degrees. Preferred values of this angle are between 15 and 75 degrees.
  • the detail of the injection holes 30 is shown in Fig. 3 and 4.
  • the local direction of the chordline is designated as Y in the diagram of figure 4, the direction perpendicular thereto and perpendicular to the radial axis X as Z.
  • the axis A of an injection hole preferably lies in the plane X-Y, so that the fluid F flows upwards with a component F Y in the local direction of the chordline leading to the trailing edge of the rotor blade.
  • the injection holes 30 thus provide means for controlling the boundary layer of blade 10 at the blade tip 18 and thus means for depressing the tip leakage flow crossing the blade tip 18, and the vortices close to blade tip 18.
  • the blade 10 further comprises a plurality of injection holes 40A on the concave side 16 close to blade tip 18 and a plurality of injection holes 40B close to blade tip 18 on the convex side 17.
  • the axes of the injection holes 40A on the pressure side and the holes 40B on the suction side form an angle less than 90 degrees between the radial extended tip plane and the perpendicular on the outer wall respectively. They have a component in the direction of the local main flow MF.
  • the fluid passing through the injection holes 40A and 40B is directed upwards towards the trailing edge of the blade.
  • the fluid for the injection coming from hollow airfoil portion 14 enters at inlet port 13.
  • injection holes 40A and 40B and 50A and 50B and 60A and 60B are shown in Fig. 5.
  • holes 40A, 40B, 50A and 50B do not appear to extend to the hollow portion of the blade 18 because of the angle which they make with the plane of the drawings. These holes do, however, communicate with the hollow plenum.
  • the injection holes 40A and 40B thus provide means for controlling the boundary layer and vortices close to the tip on the concave side 16 and the convex side 17, respectively. Moreover, the effect of reducing the tip leakage flow is supported.
  • the axes of these holes form angles of less than 90 degrees with both the normal to the local plane of the rotor and with the radial axis of the rotor.
  • the axes of those holes are not normal to the local plane of rotor.
  • blade 10 includes a plurality of injection holes 50A and 50B close to the root plane 44 on the concave side 16 and the convex side 17, respectively.
  • the axes of the injection holes 50A and 50B are directed towards the blade root 44 and form angles less than 90 degrees with the local plane of the concave side 16 and the convex side 17, respectively. These axes are, however, not normal to the local surface plane.
  • the axes of the elongate holes also form an angle of less than 90 degrees with the radial axis of the rotor.
  • the fluid for the injection comes from the hollow airfoil portion 14 and enters the hollow plenum at said inlet port 13.
  • the horizontal detail of the injection holes 50A and 50B is shown in Fig. 7.
  • the injection holes 50A and 50B thus provide means for controlling the boundary layer and vortices close to the root plane on the concave side 16 and the convex side 17, respectively.
  • Blade 10 also comprises a plurality of elongate injection holes 60A and 60B close to the concave side 16 an the convex side 17 on the root plane 44.
  • the elongate injection holes 60A and 60B are directed towards the side walls 16, 17 of the blade under angles less than 90 degree with the local perpendicular of the root plane 44.
  • the fluid for the injection enters at inlet port 13.
  • the detail of the injection holes 60A and 60B is shown in Fig. 5.
  • the injection holes 60A and 60B thus provide means for controlling the boundary layer and vortices close to the root plane 44 on the concave side 16 and the convex side 17, respectively.
  • Figure 9a shows the qualitative behavior of the main flow MF along a test standard blade 10 in the tip region.
  • a fluid -short arrows F- is injected in the main flow between the pressure and suction side and directed upwards towards the trailing edge of the blade, with a component in the chordline C.
  • the mainflow MF is diverted in the direction of the fluid flow F. No tip leakage flow occurs. Furthermore, the main flow is smoothed so that the secondary effects in the flow field, such as vortices and distortions in the boundary layer region, are significantly reduced.
  • the volume of fluid injection through the holes into the gap region has a value between 0,05 % and 0,4 % of the working fluid volume, dependent on the configuration of the blade and the casing. Best results for a blade as shown in figures 1 and 2 may be achieved for values between 0,15 % and 0,25 %.
  • a conventional standard rotor blade having no injection holes arranged and directed as in fig. 9a produces a significant leakage flow LF between the pressure side P and the suction side S of the main flow MF interwoven with secondary effects. It is to be pointed out that the occurrence of leakage flow LF cannot be suppressed even if a fluid is blown into the gap region radially or in a plane perpendicular to the local chordline as known in the state of the art for cooling purpose.
  • the invention may be used for example to reduce the leakage flow between a stator with adjustable guide vanes and a rotating shaft and to improve the secondary effects of the main flow as explained above.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (13)

  1. Blatt (10), insbesondere Rotorblatt, das in einem Gehäuse mit einem Spalt zwischen Rotor und Gehäuse rotiert, mit folgenden Merkmalen:
    einer Wurzel (12),
    Schaufeln (14) mit Wänden, die mit ihrer Kontur konkave bzw. konvexe Seiten zur Zusammenwirkung mit einer Hauptströmung (MF) eines Fluides definieren,
    einen Wurzel und Schaufeln (12, 14) miteinander verbindenen Hohlraum, durch den eine Fluidströmung fließt, und
    eine Blattspitze (18), die an ihrer Oberfläche (19) mehrere längliche Einblaskanäle (30) aufweist, deren Öffnungen an der Oberfläche (19) der Blattspitze (18) im wesentlichen über deren gesamte Sehnenlange (C) von der vorderen zur hinteren Kante der Blattspitzenoberfläche (19) verteilt sind,
    dadurch gekennzeichnet, daß der Winkel (α) zwischen der Achse (A) eines jeden Einblaskanals (30) und der radialen Achse (X) des Blattes (10) eine Komponente (Fy, Fty, F4) in Richtung der lokalen Sehne (C, Y) der Blattoberfläche (19) zwischen 15 und 75 Grad beträgt, wodurch ein Effekt eines Luftvorhanges vermischt mit einem Mitreißeffekt erzeugt wird, wodurch die Leckquerströmung an der Blattspitze reduziert wird.
  2. Blatt nach Anspruch 1, wobei der Winkel (α) zwischen der Achse (A) jedes Einblaskanals (30) und der radialen Achse (X) des Blattes (10) 45 Grad beträgt.
  3. Blatt (10) nach Anspruch 1 oder 2, wobei die Einblasöffnungen der Kanäle (30) in einer allgemein flachen Oberfläche (19) der Blattspitze (18) angeordnet sind.
  4. Blatt (10) nach einem der vorhergehenden Ansprüche, mit mehreren länglichen Einblaskanälen (40A, 40B) in den konkaven und konvexen Seite (16, 17) in der Nähe der Blattspitze (18), wobei die Achse eines jeden Kanals (40A, 40B) einen Winkel kleiner als 90 Grad mit dem örtlichen Lot auf die Außenwand und ebenso einen Winkel kleiner als 90 Grad mit einer radialen Achse des Blattes (10) bildet.
  5. Blatt nach Anspruch 4, wobei die Achse eines jeden Einblaskanales (40A, 40B) aufwärts gegen den Spitzenbereich (18) des Blattes (10) und gegen das hintere Ende des Blattes (10) gerichtet ist.
  6. Blatt (10) nach einem der vorhergehenden Ansprüche, mit mehreren länglichen Einblaskanälen (50A, 50B) in den konkaven und konvexen Seiten (16, 17) in der Nähe des Wurzelbereiches (44) des Blattes (10), wobei die Achsen der Kanäle (50A, 50B) gegen den Wurzelbereich (12, 44) gerichtet sind.
  7. Blatt (10) nach Anspruch 6, wobei die Achse eines jeden Einblaskanales (50A, 50B) einen Winkel kleiner als 90 Grad mit dem örtlichen Lot auf die entsprechende Außenwand (16, 17) des Blattes und ebenso einen Winkel kleiner als 90 Grad mit der radialen Achse (X) des Blattes (10) bildet.
  8. Blatt (10) nach Anspruch 6 oder 7, wobei die Achse eines jeden Einblaskanals (50A, 50B) eine Komponente in Richtung auf das hintere Ende des Blattes (10) aufweist.
  9. Blatt (10) nach einem der vorhergehenden Ansprüche, mit mehreren länglichen Einblaskanälen (60A, 60B) im Wurzelbereich (12, 54) in der Nähe der konkaven und konvexen Seiten (16, 17) des Blattes (10), wobei die Achse eines jeden Kanals (60A, 60B) gegen die Blattoberfläche (16, 17) gerichtet ist.
  10. Blatt (10) nach Anspruch 9, wobei die Achse eines jeden Einblaskanals einen Winkel kleiner als 90 Grad mit der örtlichen Ebene (44) des Wurzelbereiches (12) bildet.
  11. Blatt (10) nach Anspruch 10, wobei die Achsen der Einblaskanäle (60A, 60B) eine Komponente in Richtung auf das hintere Ende des Blattes (10) aufweisen.
  12. Blatt (10) nach einem der Ansprüche 1 bis 3, wobei die Fluidvolumenrate, die durch die Einblaskanäle (30) in der Blattspitzenoberfläche strömt, 0,05 % bis 0,4 % der Volumenrate der Hauptströmung beträgt.
  13. Blatt (10) nach Anspruch 12, wobei die Fluidvolumenrate, die durch die Einblaskanäle (30) strömt, 0,15 % bis 0,25% der Volumenrate der Hauptströmung beträgt.
EP88101712A 1987-02-06 1988-02-05 Rotorblatt Expired - Lifetime EP0278434B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US1178887A 1987-02-06 1987-02-06
US11788 1987-02-06

Publications (3)

Publication Number Publication Date
EP0278434A2 EP0278434A2 (de) 1988-08-17
EP0278434A3 EP0278434A3 (en) 1990-01-31
EP0278434B1 true EP0278434B1 (de) 1994-07-20

Family

ID=21751969

Family Applications (1)

Application Number Title Priority Date Filing Date
EP88101712A Expired - Lifetime EP0278434B1 (de) 1987-02-06 1988-02-05 Rotorblatt

Country Status (2)

Country Link
EP (1) EP0278434B1 (de)
DE (1) DE3850681T2 (de)

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2315818B (en) * 1988-07-29 1998-06-24 United Technologies Corp Clearence control for the turbine of a gas turbine engine
NO306741B1 (no) * 1988-08-24 1999-12-13 United Technologies Corp Aksialturbin for en gassturbinmotor
US5667359A (en) * 1988-08-24 1997-09-16 United Technologies Corp. Clearance control for the turbine of a gas turbine engine
US5382135A (en) * 1992-11-24 1995-01-17 United Technologies Corporation Rotor blade with cooled integral platform
DE10305351A1 (de) * 2003-02-10 2004-08-19 Rolls-Royce Deutschland Ltd & Co Kg Verdichterschaufel mit Vertiefung auf radialer Außenfläche
US6830432B1 (en) * 2003-06-24 2004-12-14 Siemens Westinghouse Power Corporation Cooling of combustion turbine airfoil fillets
DE10355241A1 (de) 2003-11-26 2005-06-30 Rolls-Royce Deutschland Ltd & Co Kg Strömungsarbeitsmaschine mit Fluidzufuhr
US20070122280A1 (en) * 2005-11-30 2007-05-31 General Electric Company Method and apparatus for reducing axial compressor blade tip flow
CN110863864B (zh) * 2019-12-11 2022-05-10 沈阳航空航天大学 一种内部带有横向蜿蜒交替缩扩短通道的涡轮叶片

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1024754B (de) * 1956-02-11 1958-02-20 Maschf Augsburg Nuernberg Ag Gekuehlte Laufschaufel fuer heiss betriebene Turbinen oder Verdichter
US4020538A (en) * 1973-04-27 1977-05-03 General Electric Company Turbomachinery blade tip cap configuration
US4214355A (en) * 1977-12-21 1980-07-29 General Electric Company Method for repairing a turbomachinery blade tip
US4390320A (en) * 1980-05-01 1983-06-28 General Electric Company Tip cap for a rotor blade and method of replacement
GB2077363A (en) * 1980-06-05 1981-12-16 United Technologies Corp Wafer tip cap for rotor blades

Also Published As

Publication number Publication date
EP0278434A2 (de) 1988-08-17
DE3850681D1 (de) 1994-08-25
DE3850681T2 (de) 1995-03-09
EP0278434A3 (en) 1990-01-31

Similar Documents

Publication Publication Date Title
US4863348A (en) Blade, especially a rotor blade
US4604031A (en) Hollow fluid cooled turbine blades
US3527543A (en) Cooling of structural members particularly for gas turbine engines
US3726604A (en) Cooled jet flap vane
EP1445424B1 (de) Hohlschaufel mit eingebautem Kreislauf zur Schaufelspitzenkühlung
US5370499A (en) Film cooling of turbine airfoil wall using mesh cooling hole arrangement
EP0330601B1 (de) Kühlung einer Gasturbinenschaufel
US6174135B1 (en) Turbine blade trailing edge cooling openings and slots
US5927946A (en) Turbine blade having recuperative trailing edge tip cooling
JPS6349522Y2 (de)
JP4801513B2 (ja) ターボ機械の可動な翼のための冷却回路
US4515526A (en) Coolable airfoil for a rotary machine
US7118329B2 (en) Tip sealing for a turbine rotor blade
US6234754B1 (en) Coolable airfoil structure
EP0929734B1 (de) Turbinenleitschaufelkühlung
EP0670954B1 (de) Verstärkte hinterkante für gusskern einer turbinenschaufel
JP4152184B2 (ja) 下降段を有するタービンのプラットフォーム
US6568909B2 (en) Methods and apparatus for improving engine operation
US5238364A (en) Shroud ring for an axial flow turbine
JPH10274001A (ja) ガスタービンエンジン内の翼の冷却通路の乱流促進構造
US5090866A (en) High temperature leading edge vane insert
US10677066B2 (en) Turbine blade with airfoil tip vortex control
JPH0353442B2 (de)
JP2000161003A (ja) 直列インピンジメント冷却エ―ロフォイル
EP0838575B1 (de) Verfahren zur Kühlung von Leitschaufeln

Legal Events

Date Code Title Description
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

Kind code of ref document: A2

Designated state(s): CH DE FR GB IT LI SE

PUAL Search report despatched

Free format text: ORIGINAL CODE: 0009013

AK Designated contracting states

Kind code of ref document: A3

Designated state(s): CH DE FR GB IT LI SE

17P Request for examination filed

Effective date: 19900726

17Q First examination report despatched

Effective date: 19910529

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): CH DE FR GB IT LI SE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LI

Effective date: 19940720

Ref country code: CH

Effective date: 19940720

REF Corresponds to:

Ref document number: 3850681

Country of ref document: DE

Date of ref document: 19940825

ITF It: translation for a ep patent filed

Owner name: ING. ANTON AUSSERER

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

ET Fr: translation filed
EAL Se: european patent in force in sweden

Ref document number: 88101712.3

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 19950619

Year of fee payment: 9

26N No opposition filed
PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 19960205

Year of fee payment: 9

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: SE

Payment date: 19960228

Year of fee payment: 9

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 19960403

Year of fee payment: 9

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Effective date: 19970205

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SE

Effective date: 19970206

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 19970205

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Effective date: 19971030

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Effective date: 19971101

EUG Se: european patent has lapsed

Ref document number: 88101712.3

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES;WARNING: LAPSES OF ITALIAN PATENTS WITH EFFECTIVE DATE BEFORE 2007 MAY HAVE OCCURRED AT ANY TIME BEFORE 2007. THE CORRECT EFFECTIVE DATE MAY BE DIFFERENT FROM THE ONE RECORDED.

Effective date: 20050205

REG Reference to a national code

Ref country code: SK

Ref legal event code: SPCT

Owner name: MERUS LABS LUXCO SARL, LU

Free format text: PRODUCT NAME: HYDROBROMID (S)-2-{1-[2-(2,3-DIHYDROBENZOFURAN-5-YL)ETYL]-3--PYROLIDINYL}-2,2-DIFENYLACETAMIDU; REGISTRATION NO/DATE: EU/1/04/294/001-012 20041022; FORMER OWNER: NOVARTIS INTERNATIONAL PHARMACEUTICAL LTD.

Spc suppl protection certif: 26 5002-2005

Filing date: 20050401

Expiry date: 20150317