EP1081336A2 - Gebauter Leitkranz für eine Gasturbine - Google Patents
Gebauter Leitkranz für eine Gasturbine Download PDFInfo
- Publication number
- EP1081336A2 EP1081336A2 EP00115821A EP00115821A EP1081336A2 EP 1081336 A2 EP1081336 A2 EP 1081336A2 EP 00115821 A EP00115821 A EP 00115821A EP 00115821 A EP00115821 A EP 00115821A EP 1081336 A2 EP1081336 A2 EP 1081336A2
- Authority
- EP
- European Patent Office
- Prior art keywords
- airfoil
- guide ring
- platform
- shroud
- circumference
- 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
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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
- F01D9/044—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators permanently, e.g. by welding, brazing, casting or the like
Definitions
- the invention relates to a built guide ring for a gas turbine, in particular a Aircraft engine, comprising at least one shroud with a peripheral surface and at least one airfoil with a surface, the shroud at least has an opening for fastening the airfoil, the peripheral surface of the shroud faces the airfoil, and the airfoil at least an end section at least in sections over its surface protruding platform having a transition curvature, which in the Breakthrough is used.
- Built wreaths are integral components that generally have an annular outer shroud, comprise several airfoils and, if necessary, an annular inner shroud.
- Such guide rings can also be constructed and segmented e.g. used in aircraft engine compressors.
- the cover band extends in the generally around the longitudinal axis of the gas turbine.
- the blades are in the arranged essentially in the radial direction.
- the airfoil has at least one End section with a constant profile or a constant cross-sectional area on which is inserted into an opening formed in the shroud during assembly and by e.g. Soldering or welding is attached.
- the airfoil can also at an opposite, second end section a constant profile or one have a constant cross-section and in a second shroud, i.e. one - Outside and inside shroud.
- the disadvantage here is that the profile of the Blade does not have to be constant over the entire channel height, but in Is limited in terms of its profile geometry for assembly reasons. The For example, the airfoil may no sharp bend or significant thickening in his have between the end portions.
- DE-AS 12 00 070 is a manufacturing process for a guide vane ring known in which the blades in their grooves formed in an annular body with their Blade base are used, the blade having a curvature in the blade root merges and the ring body finally into several segments is separated.
- EP 0 704 602 A2 discloses turbine blades arranged on a carrier which the airfoil surface in a radius in the peripheral surface of the carrier transforms.
- EP 0 199 073 A1 describes a manufacturing method for a guide vane known, which is fixed by soldering to a stator, the guide vane made an oversized profile rod is produced, and this for Enlargement of the soldering area on at least one end in the cold state a foot-like Thickened up and a soldering surface is formed in the area.
- the profile rod can be slanted on one side become.
- the object of the present invention is to provide a built guide ring to create the type described above, which saves axial length, itself can be manufactured as simply as possible and with no or only minor restrictions in With regard to the profile geometry of the airfoil, e.g. due to assembly reasons.
- the solution to the problem is characterized in that the Platform in the area of an entry and / or exit edge of the airfoil less than protrudes over the surface of the airfoil in the middle region of the airfoil and so axial space is saved.
- the platform With its circumference, the platform can be connected to a circumference of the airfoil that is radial lies in an area lying opposite the tip of the airfoil, so the distance between the two aforementioned sizes except in the range the leading and / or trailing edge is essentially constant.
- the transition curvature can be from a central area of the airfoil in the direction be formed increasingly narrow on the leading and / or trailing edge.
- the blade in the area of the leading and / or trailing edge cannot have any the surface of which has the protruding platform.
- the advantage of such a built guide ring is that the additional provided platform of connecting the airfoil and shroud without Restriction with regard to the profile geometry of the airfoil is possible.
- the platform provided with a transition curve in the With regard to aerodynamics and strength advantages with it.
- the breakthroughs in the shroud have larger radii in the area of the leading and trailing edge are easier to manufacture.
- the transition curvature hugs for optimal design in terms of aerodynamics and strength to the surface of the airfoil and the peripheral surface adjacent to the platform in the assembled state of the deck band.
- the airfoil can be in the area of the leading and / or trailing edge have no platform protruding over its circumference, so that the axial Overall length of the guide ring is further reduced. Since the platform also with your This occurs in the circumference in the leading and / or trailing edge on both sides Problem of too narrow and difficult to manufacture edges in the openings of the Shrouds not on.
- the surface of the airfoil can be in the area of the inlet and / or Trailing edge in the assembled state on the peripheral surface of the shroud adjoin, in the other area along the circumference of the airfoil, e.g. in the middle area on the suction and pressure side, one over the circumference of the airfoil protruding platform with a transition curvature.
- the transition curvature can alternatively be from a central area of the airfoil, e.g. on the suction and pressure side, in the direction of the leading and / or trailing edge be increasingly narrow, so that due to the narrower curvature axial overall length is saved in the area of the entry and / or exit edge.
- the transition curvature can be circular at least in sections be and have a radius, this in the central region of the airfoil be larger than in the other areas along the circumference of the airfoil can. If the airfoil has a circumference along the entire circumference protruding platform, the radius is in the area of the leading and / or trailing edge smallest to reduce the axial length.
- the radius can be along the circumference of the airfoil constant and its center be changed so that the transition curvature along the entire circumference to the surface of the airfoil hugs and at the leading and / or trailing edge a tangent jump to the peripheral surface of the cover tape is present.
- Manufacturing with a constant radius is cheap.
- the tangent jump at the leading and / or trailing edge the until it can gradually increase there, the axial length of the guide ring is reduced.
- FIG. 1 shows a section of a guide ring known from the prior art with an outer shroud 1 and an airfoil 2, which has an end section 3 having.
- the outer shroud 1 there are several, generally equidistantly arranged Breakthroughs 4 formed.
- an airfoil 2 inserted with its end section 3 and there by e.g. Soldering or Welding attached.
- the end sections 3 the blades 2 have a two-dimensional or constant profile.
- the blades 2 do not necessarily have a constant profile over the entire Must have channel height, is subject to their profile geometry for installation reasons significant restrictions.
- the blades 2 must not bend or have significant thickening. It is also problematic, which is proportionate Form narrowly profiled openings 4 in the shroud 1.
- FIG. 2 shows a plan view of an embodiment of the built guide ring, in which an airfoil 2 in cross section and one on the free end of the Blade 2 adjoining platform 5 is shown.
- it corresponds the profile or the shape of the opening 4 in the shroud 1 the profile or scope 6 of the platform 5 and is larger than the circumference 7 of the airfoil 2.
- the surface 8 of the airfoil 2 goes into the platform with a transition curve 9 6 over, which is designed so that they are both in the assembled state Surface 8 of the airfoil 2 and the inner peripheral surface 10 of the Cover band 1 hugs.
- the transition curvature 9 is designed as a radius that in the central region 11 of the Blade 2 larger than in the area of the leading edge and trailing edge 12, 13 and until then e.g. can gradually decrease.
- the transition curve 9 have a constant radius along the circumference, wherein in In this case, its center point changes towards the leading and trailing edge 12, 13, that the peripheral curvature 9 also there on the surface 8 of the airfoil 2 hugs and, as shown in Fig. 7, to the inner peripheral surface 10 of the shroud 1 has a tolerable tangent jump. This alternative has manufacturing advantages.
- Fig. 3 shows a sectional view of the shroud 1 and the airfoil 2, at which is the radius of the transition curve 9 in the central region 11 of the airfoil 2 is shown.
- the blade 2 is with the platform 5 in an opening 4 in the Cover tape 1 used, the profile or the shape of the opening 4 the profile or corresponds to the extent 6 of the platform 5.
- the platform 5 stands with its scope 6 in this area 11 clearly above the surface 8 of the airfoil 2.
- the blade 4 is a section in the area of the inlet and outlet edges 12, 13 of the airfoil 2 shown.
- the blade 2 is with its platform 5 in the cover band 1 trained breakthrough 4 used and attached.
- the platform 5 points as a transition curvature 9 has a radius that is significantly smaller than that in the central region 11, shown in FIG. 3, so that the platform 5 with its circumference 6 protrudes significantly less over the surface 8 of the airfoil 2.
- the radius or the transition curve 9 nestles on the one hand on the surface 8 of the Blade 2 and on the other hand to the inwardly facing peripheral surface 10 of the cover tape 1.
- By significantly reducing the transition radius 9 in Area of the leading and trailing edge 12, 13 is the axial length of the built Leitkranzes effectively reduced.
- the openings 4 in the Produce shroud 1 more efficiently due to the lack of pointed edges or the like. since the circumference 6 of the platform 5 is larger than that of the airfoil 2.
- the reduction in axial length in the embodiment 4 also advantageous in terms of production technology with a transition curvature 9 with a constant radius along the circumference if its center is as described above, changes towards the leading and / or trailing edge 12, 13 and there a tangent jump T is permitted at the transition to the shroud 1.
- the tangent jump T can with a constant radius to the leading and / or trailing edge 12, 13 gradually increase.
- Fig. 5 shows a further embodiment of the built guide ring, in which a cut airfoil 2 and a platform 5 are shown in plan view.
- the platform 5 stands with its circumference 6 in the central region 11 of the airfoil 2 or on the pressure and suction side over the surface 8 of the airfoil 2 before and here has a transition curvature 9.
- the platform 5 ends immediately adjacent to the leading edge 12 and the trailing edge 13 and stands in these two Areas not over the profile or the circumference 7 of the airfoil 2 before.
- the transition curvature ending on both sides of the entry and / or exit edge 12, 13 9 is designed so that it extends to the surface in the circumferential direction 8 hugs or there directly at the leading and trailing edge 12, 13 expires. In this way, the axial dimensions of the built guide ring can be reduce effectively without narrow openings 4 with sharp edges in the cover tapes 1 must be manufactured.
- FIG. 6 shows the embodiment of FIG. 5 in a sectional view, in which the Cover band 1, the airfoil 2 and the platform 5 directly in the area of the inlet and Trailing edge 12, 13 is shown.
- the airfoil has 2 at the transition to the platform 5 no transition curve 9, whereby the axial length is effectively reduced.
- Platform 5 is in this area with its circumference 6 essentially not over the surface 8 of the airfoil 2 or its scope 7 before.
- FIG. 7 shows the exemplary embodiment from FIG. 5 in a section shown in FIG. 5 adjacent to the leading and trailing edges 12, 13 of the airfoil 2.
- the transition curvature 9 has the same radius as in the central region 11 of the airfoil 2 on.
- the representation of the transition curvature 9 in the central region 11 corresponds in this exemplary embodiment, that of the exemplary embodiment according to FIG. 2 and is shown in FIG. 3.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
- Fig. 1
- eine Schnittansicht durch ein Schaufelblatt und ein Deckband aus dem Stand der Technik,
- Fig. 2
- eine Draufsicht auf ein geschnittenes Schaufelblatt samt Plattform gemäß einem Ausführungsbeispiel des erfindungsgemäßen gebauten Leitkranzes,
- Fig. 3
- eine Schnittansicht des Ausführungsbeispiels aus Fig. 2,
- Fig. 4
- eine weitere Schnittansicht des Ausführungsbeispiels aus Fig. 2,
- Fig. 5
- eine Draufsicht auf ein geschnittenes Schaufelblatt samt Plattform gemäß einem anderen Ausführungsbeispiel des erfindungsgemäßen gebauten Leitkranzes,
- Fig. 6
- eine Schnittansicht des Ausführungsbeispiels gemäß Fig. 5 und
- Fig. 7
- eine weitere Schnittansicht des Ausführungsbeispiels gemäß Fig. 5.
Claims (9)
- Gebauter Leitkranz für eine Gasturbine, insbesondere ein Flugtriebwerk, umfassend ein Deckband (1) mit einer Umfangsfläche (10) und wenigstens ein Schaufelblatt (2) mit einer Oberfläche (8), wobei das Deckband (1) wenigstens einen Durchbruch (4) zur Befestigung des Schaufelblatts (2) aufweist, und wobei das Schaufelblatt (2) an wenigstens einem Endabschnitt (3) eine zumindest abschnittsweise über dessen Oberfläche (8) vorstehende, eine Übergangskrümmung (9) aufweisende Plattform (5) aufweist, die in den Durchbruch (4) eingesetzt ist, dadurch gekennzeichnet, dass die Plattform (5) im Bereich einer Ein- und /oder Austrittskante (1 2,13) des Schaufelblatts (2) weniger als im Mittenbereich (11) des Schaufelblatts (2) über die Oberfläche (8) des Schaufelblatts (2) vorsteht.
- Gebauter Leitkranz nach Anspruch 1, dadurch gekennzeichnet, dass die Plattform (5) mit Ihrem Umfang (6) an einen Umfang (7) des Schaufelblatts (2) angepaßt ist.
- Gebauter Leitkranz nach Anspruch 1 oder 2, dadurch gekennzeichnet, dass die Plattform (5) im Mittenbereich (11) auf einer Saug- und/oder einer Druckseite des Schaufelblatts (2) über die Oberfläche (8) des Schaufelblatts (2) vorsteht.
- Gebauter Leitkranz nach einem oder mehreren der vorhergehenden Ansprüche, dadurch gekennzeichnet, die Übergangskrümmung (9) von einem Mittenbereich (11) des Schaufelblatts (2) in Richtung auf eine Ein- und/oder eine Austrittskante (12,13) zunehmend enger ausgebildet ist oder das Schaufelblatt (2) im Bereich der ein- und/oder Austrittskante (12,13) keine über dessen Oberfläche (8) vorstehende Plattform (5) aufweist.
- Gebauter Leitkranz nach einem oder mehreren der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass sich die übergangskrümmung (9) an die Oberfläche (8) des Schaufelblattes (2) und einer angrenzenden Umfangsfläche (10) des Deckbands (1) anschmiegt.
- Gebauter Leitkranz nach einem oder mehreren der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass die Oberfläche (8) des Schaufelblatts (2) im Bereich der Ein- und/oder Austrittskante (12,13) an die Umfangsfläche (10) des Deckbands (1) angrenzt.
- Gebauter Leitkranz nach einem oder mehreren der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass die Übergangskrümmung (9) wenigstens abschnittsweise als Radius ausgeführt ist.
- Gebauter Leitkranz nach Anspruch 7, dadurch gekennzeichnet, dass der Radius in einem Mittenbereich (11) des Schaufelblatts (2) größer als in den anderen Bereichen entlang des Umfangs (7) des Schaufelblatts (2) ist.
- Gebauter Leitkranz nach Anspruch 8, dadurch gekennzeichnet, dass der Radius entlang des Umfangs (7) des Schaufelblatts (2) konstant ist und sein Mittelpunkt so verändert ist, daß sich die Übergangskrümmung (9) entlang des gesamten Umfangs (7) an die Oberfläche (8) des Schaufelblatts (2) anschmiegt und an der Ein- und/oder Austrittskante (12, 13) ein Tangentensprung (T) zur Umfangsfläche (10) des Deckbands (1) vorliegt.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE19941133 | 1999-08-30 | ||
DE19941133A DE19941133C1 (de) | 1999-08-30 | 1999-08-30 | Gebauter Leitkranz für eine Gasturbine, insbesondere ein Flugtriebwerk |
Publications (3)
Publication Number | Publication Date |
---|---|
EP1081336A2 true EP1081336A2 (de) | 2001-03-07 |
EP1081336A3 EP1081336A3 (de) | 2003-10-01 |
EP1081336B1 EP1081336B1 (de) | 2005-02-02 |
Family
ID=7920103
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP00115821A Expired - Lifetime EP1081336B1 (de) | 1999-08-30 | 2000-07-22 | Gebauter Leitkranz für eine Gasturbine |
Country Status (3)
Country | Link |
---|---|
US (1) | US6543998B1 (de) |
EP (1) | EP1081336B1 (de) |
DE (2) | DE19941133C1 (de) |
Families Citing this family (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2899270A1 (fr) * | 2006-03-30 | 2007-10-05 | Snecma Sa | Aube de redresseur a amenagement de forme localise, secteur de redresseurs, etage de compression, compresseur et turbomachine comportant une telle aube |
FR2899269A1 (fr) * | 2006-03-30 | 2007-10-05 | Snecma Sa | Aube de redresseur optimisee, secteur de redresseurs, etage de compression, compresseur et turbomachine comportant une telle aube |
US7748956B2 (en) * | 2006-12-19 | 2010-07-06 | United Technologies Corporation | Non-stablug stator apparatus and assembly method |
US8740557B2 (en) * | 2009-10-01 | 2014-06-03 | Pratt & Whitney Canada Corp. | Fabricated static vane ring |
US8920117B2 (en) * | 2011-10-07 | 2014-12-30 | Pratt & Whitney Canada Corp. | Fabricated gas turbine duct |
US9840929B2 (en) * | 2013-05-28 | 2017-12-12 | Pratt & Whitney Canada Corp. | Gas turbine engine vane assembly and method of mounting same |
US9869190B2 (en) | 2014-05-30 | 2018-01-16 | General Electric Company | Variable-pitch rotor with remote counterweights |
US20160017731A1 (en) * | 2014-07-17 | 2016-01-21 | Rolls-Royce Corporation | Vane assembly |
US10072510B2 (en) | 2014-11-21 | 2018-09-11 | General Electric Company | Variable pitch fan for gas turbine engine and method of assembling the same |
US9988918B2 (en) | 2015-05-01 | 2018-06-05 | General Electric Company | Compressor system and airfoil assembly |
US10100653B2 (en) | 2015-10-08 | 2018-10-16 | General Electric Company | Variable pitch fan blade retention system |
US11674435B2 (en) | 2021-06-29 | 2023-06-13 | General Electric Company | Levered counterweight feathering system |
US11795964B2 (en) | 2021-07-16 | 2023-10-24 | General Electric Company | Levered counterweight feathering system |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE1200070B (de) | 1961-11-21 | 1965-09-02 | Siemens Ag | Verfahren zum Herstellen von Leitschaufel-kranzsegmenten fuer Gasturbinen |
EP0199073A1 (de) | 1985-04-19 | 1986-10-29 | Man Gutehoffnungshütte Gmbh | Verfahren zur Herstellung einer Leitschaufel für ein Turbinen- oder Verdichter-Leitrad und nach dem Verfahren hergestellte Leitschaufel |
EP0704602A2 (de) | 1994-08-30 | 1996-04-03 | Gec Alsthom Limited | Turbinenschaufel |
Family Cites Families (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2681788A (en) * | 1951-05-23 | 1954-06-22 | Solar Aircraft Co | Gas turbine vane structure |
FR1095927A (fr) * | 1953-02-02 | 1955-06-07 | Bristol Aeroplane Co Ltd | Perfectionnements apportés au montage des aubes à profil d'aile dans les compresseurs et autres applications |
FR1389254A (fr) * | 1963-04-08 | 1965-02-12 | Rolls Royce | Compresseur pour moteur à turbine à gaz |
US4260327A (en) * | 1979-07-25 | 1981-04-07 | General Electric Company | Guide vane assembly for reverse flow cooled dynamoelectric machine |
US5474419A (en) * | 1992-12-30 | 1995-12-12 | Reluzco; George | Flowpath assembly for a turbine diaphragm and methods of manufacture |
US5765993A (en) * | 1996-09-27 | 1998-06-16 | Chromalloy Gas Turbine Corporation | Replacement vane assembly for fan exit guide |
-
1999
- 1999-08-30 DE DE19941133A patent/DE19941133C1/de not_active Expired - Fee Related
-
2000
- 2000-07-22 EP EP00115821A patent/EP1081336B1/de not_active Expired - Lifetime
- 2000-07-22 DE DE50009400T patent/DE50009400D1/de not_active Expired - Fee Related
- 2000-08-25 US US09/645,483 patent/US6543998B1/en not_active Expired - Fee Related
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE1200070B (de) | 1961-11-21 | 1965-09-02 | Siemens Ag | Verfahren zum Herstellen von Leitschaufel-kranzsegmenten fuer Gasturbinen |
EP0199073A1 (de) | 1985-04-19 | 1986-10-29 | Man Gutehoffnungshütte Gmbh | Verfahren zur Herstellung einer Leitschaufel für ein Turbinen- oder Verdichter-Leitrad und nach dem Verfahren hergestellte Leitschaufel |
EP0704602A2 (de) | 1994-08-30 | 1996-04-03 | Gec Alsthom Limited | Turbinenschaufel |
Also Published As
Publication number | Publication date |
---|---|
EP1081336A3 (de) | 2003-10-01 |
US6543998B1 (en) | 2003-04-08 |
DE50009400D1 (de) | 2005-03-10 |
DE19941133C1 (de) | 2000-12-28 |
EP1081336B1 (de) | 2005-02-02 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
DE19941134C1 (de) | Schaufelkranz für eine Gasturbine | |
DE60037170T2 (de) | Leitschaufel | |
DE602004006323T2 (de) | Verfahren zur Herstellung einer Turbine mit Turbinenschaufeln unterschiedlicher Resonanzfrequenzen samt einer solchen Turbine | |
EP1898054B1 (de) | Gasturbine | |
EP2505783B1 (de) | Rotor einer Axialverdichterstufe einer Turbomaschine | |
DE19941133C1 (de) | Gebauter Leitkranz für eine Gasturbine, insbesondere ein Flugtriebwerk | |
DE60203214T2 (de) | Turbinenschaufel mit Labyrinthschneidendichtung | |
EP2478186B1 (de) | Rotor einer Turbomaschine | |
DE102007002326A1 (de) | Turbinenschaufel- und Leitkranzkonstruktion | |
DE3148985C2 (de) | Rotorbaugruppe | |
DE102015224283A1 (de) | Leitschaufelcluster für eine Strömungsmaschine | |
WO2008092427A1 (de) | Gasturbine mit einem nachleitkranz und mit einem mischer | |
EP3121373A1 (de) | Gekühltes turbinenlaufrad, insbesondere für ein flugtriebwerk | |
EP3056677B1 (de) | Schaufel und Strömungsmaschine | |
EP3428402B1 (de) | Leitschaufelsegment mit gekrümmter entlastungsfuge | |
EP2410131A2 (de) | Rotor einer Turbomaschine | |
EP2394028B1 (de) | Abdichtvorrichtung an dem Schaufelschaft einer Rotorstufe einer axialen Strömungsmaschine und ihre Verwendung | |
EP2927503B1 (de) | Gasturbinenverdichter, Flugtriebwerk und Auslegungsverfahren | |
DE102018206601A1 (de) | Schaufel, Schaufelsegment und Baugruppe für eine Turbomaschine und Turbomaschine | |
EP2607626A1 (de) | Turbomaschine und Turbomaschinenstufe | |
EP1163426B1 (de) | Turbomaschinenschaufel | |
EP3885535B1 (de) | Dichtring für einen rotor und rotor mit einem solchen | |
EP1355041A2 (de) | Turbinenschaufel | |
EP2650475B1 (de) | Schaufel für eine Strömungsmaschine, Schaufelanordnung sowie Strömungsmaschine | |
EP3492701A1 (de) | Turbomaschinen-strömungskanal |
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): AT BE CH CY DE DK ES FI FR GB GR IE IT LI LU MC NL PT SE |
|
AX | Request for extension of the european patent |
Free format text: AL;LT;LV;MK;RO;SI |
|
RAP1 | Party data changed (applicant data changed or rights of an application transferred) |
Owner name: MTU AERO ENGINES GMBH |
|
PUAL | Search report despatched |
Free format text: ORIGINAL CODE: 0009013 |
|
AK | Designated contracting states |
Kind code of ref document: A3 Designated state(s): AT BE CH CY DE DK ES FI FR GB GR IE IT LI LU MC NL PT SE |
|
AX | Request for extension of the european patent |
Extension state: AL LT LV MK RO SI |
|
17P | Request for examination filed |
Effective date: 20031008 |
|
17Q | First examination report despatched |
Effective date: 20040212 |
|
AKX | Designation fees paid |
Designated state(s): DE ES FR GB IT |
|
GRAP | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOSNIGR1 |
|
GRAS | Grant fee paid |
Free format text: ORIGINAL CODE: EPIDOSNIGR3 |
|
GRAA | (expected) grant |
Free format text: ORIGINAL CODE: 0009210 |
|
AK | Designated contracting states |
Kind code of ref document: B1 Designated state(s): DE ES FR GB IT |
|
REG | Reference to a national code |
Ref country code: GB Ref legal event code: FG4D Free format text: NOT ENGLISH |
|
REG | Reference to a national code |
Ref country code: IE Ref legal event code: FG4D Free format text: GERMAN |
|
REF | Corresponds to: |
Ref document number: 50009400 Country of ref document: DE Date of ref document: 20050310 Kind code of ref document: P |
|
GBT | Gb: translation of ep patent filed (gb section 77(6)(a)/1977) |
Effective date: 20050318 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: ES Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20050513 |
|
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 |
|
ET | Fr: translation filed | ||
26N | No opposition filed |
Effective date: 20051103 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: FR Payment date: 20090716 Year of fee payment: 10 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: DE Payment date: 20090722 Year of fee payment: 10 Ref country code: GB Payment date: 20090720 Year of fee payment: 10 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: IT Payment date: 20090725 Year of fee payment: 10 |
|
GBPC | Gb: european patent ceased through non-payment of renewal fee |
Effective date: 20100722 |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: ST Effective date: 20110331 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: DE Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20110201 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R119 Ref document number: 50009400 Country of ref document: DE Effective date: 20110201 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: FR Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20100802 Ref country code: IT Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20100722 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: GB Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20100722 |