EP0954680B1 - Turbinenschaufel sowie verwendung in einer gasturbinenanlage - Google Patents
Turbinenschaufel sowie verwendung in einer gasturbinenanlage Download PDFInfo
- Publication number
- EP0954680B1 EP0954680B1 EP97949947A EP97949947A EP0954680B1 EP 0954680 B1 EP0954680 B1 EP 0954680B1 EP 97949947 A EP97949947 A EP 97949947A EP 97949947 A EP97949947 A EP 97949947A EP 0954680 B1 EP0954680 B1 EP 0954680B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- wall
- cooling
- turbine blade
- region
- outlet
- 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
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
- F01D5/18—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
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/187—Convection cooling
-
- 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
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/221—Improvement of heat transfer
- F05D2260/2212—Improvement of heat transfer by creating turbulence
Definitions
- the invention relates to a turbine blade with one of a hot gas flow around wall structure, at least in some areas an outer wall around which the hot gas can flow, one Inner wall and one arranged between the inner wall and outer wall Has cooling area for the flow of a cooling fluid.
- the invention further relates to the use of a such a turbine blade in a gas turbine plant.
- a gas turbine vane with a guide from Cooling gas for cooling them is described in US Pat. No. 5,419,039.
- the guide vane is designed as a casting or composed of two castings. She points inside a supply of cooling air from the compressor to the assigned Gas turbine plant on. In their the hot gas flow exposed to the gas turbine, enclosing the air supply Wall structure are cast-in cool bags that are open on one side intended.
- the cooler bags are on the outside of the wall structure both in the flow direction of the hot gas and perpendicular to the direction of flow of the hot gas along the Main direction of expansion of the guide vane arranged. In each Cooling bag flows from the cooling air supply over a plurality of holes in the wall structure cooling air into the cooler bag on.
- Cooling bag can be a base or unspecified can use several unspecified sockets for improvement the heat conduction can be provided.
- DE 22 41 192 B2 includes a hollow gas turbine blade described an operation.
- This insert serves as a partition in the cavity enclosed by the turbine blade.
- the Insert consists of two parts by spacers are spaced from each other.
- the cavity of the turbine blade is by a longitudinally extending web in an inlet chamber for cooling air and into an outlet chamber divided for cooling air.
- the two parts of the insert are in the entry chamber made impermeable to cooling air, so that the two parts form a channel, which is only in the inflow area the turbine blade toward the inlet chamber is open.
- Cooling air therefore flows from the inflow area the turbine blade through the through the two parts of the Insert formed channel in the direction of the trailing edge the turbine blade.
- the two parts of the insert each have a plurality from openings, through the cooling air into the outlet chamber can leak. Both at the inflow area as well There are openings for at the trailing edge of the turbine blade the exit of cooling air is provided. Through the openings in the inflow area is cooled by film as cooling air escapes reached on the outer surface of the blade wall.
- Japanese Patent Application Laid-Open 3-130503A is a process for cooling high temperature loaded components of a gas turbine, in particular a gas turbine blade, described using water.
- the Gas turbine blade is designed as a hollow blade and has a partition on the inside. This partition is via cooling fins with the outer wall of the turbine blade connected. In the interior enclosed by the partition feeds are provided through which under pressure standing water can be blasted into the gap can. The water atomized in this way collides with the partition and thereby cools them. Over the cooling fins by cooling the partition also the outer wall of the Shovel chilled. Both in the outer wall and in the There are a large number of small holes in the partition.
- the object of the invention is to provide a turbine blade with a specify coolable wall structure. There is another task in using such a turbine blade specify.
- a turbine blade with a Task directed by hot gas flow around wall structure solved by such a turbine blade that has an inflow area, an outflow area and in between, opposite each other has a pressure side and a suction side and at least in some areas the hot gas can flow around it Outer wall, an inner wall and one between the inner wall and Outside wall arranged cooling area for flow with a Has cooling fluid and the cooling area one of the inner wall assigned inlet and one assigned to the outer wall Has outlet for cooling fluid, wherein in the cooling area of flow around the cooling fluid in a main flow direction Heat transfer elements are arranged one behind the other are thermally connected to the outer wall.
- the cooling area is preferably designed as a cooling chamber, which is enclosed by the outer wall and the inner wall.
- the Forming an enclosed cooling chamber increases flexibility in the manufacture of inlet and outlet and gives the Possibility of retrofitting the inlet and the outlet of cooling fluid, especially cooling air, according to the requirements to change the turbine blade.
- the outlet is preferably through one or more holes manufactured. These holes or funnel-shaped openings are preferably opposite the main flow direction inclined, in particular by an angle of less than 45 °, preferably 20 ° to 30 °.
- the inclination is preferably chosen so that against a flow of the turbine blade hot gas flowing around an acute angle of, for example also 45 ° is formed. By such a point Angle is the formation of a cooling film on the surface the outer wall favors.
- the direction of the holes or funnel-shaped openings can also be from one level perpendicular to the main axis of the turbine blade by the same Point out the angle.
- the outer wall can be made with a smaller one Wall thickness should be formed, which makes them special can be effectively cooled via the heat transfer elements.
- the cross section of the cooling area between the inner wall and the outer wall is preferred to form a high speed of the cooling fluid low trained, and is particularly in the area the wall thickness of the outer wall. Through a small flow Cross section of the cooling area and a so formed high speed of the cooling fluid become very high Heat transfer numbers reached. It also trains cooling air exiting the cooling area on the outer wall cooling film on the surface exposed to the hot gas Outer wall (film cooling).
- a plurality of heat transfer elements are preferably along a line arranged in a row, the line opposite the main flow direction, preferably at an angle of 90 °.
- the main direction of flow is preferred essentially perpendicular to a main axis of the turbine blade, along which the turbine blade is directed is. With a turbine blade that is used as a guide blade the main flow direction corresponds to the Flow direction of a flowing around the turbine blade Hot gas or is the opposite.
- the heat transfer elements are preferred along the line equally spaced.
- the heat transfer elements are preferably column-like or platform-like and extend from the outer wall to the inner wall. she can also be firmly connected to the inner wall.
- the cross section of the heat transfer elements is in each case the heat transfer and adaptable to fluidic requirements, for example circular, polygonal or in the manner of a Flow profile trained.
- the heat transfer elements directly in the main flow direction consecutive rows are preferred offset from each other, especially by half the distance two heat transfer elements arranged along the line. This primarily ensures that the between two heat transfer elements adjacent along the line sub-flows of the cooling fluid flowing essentially completely with one downstream in the main flow direction Heat transfer element for exchanging thermal energy comes into contact.
- the outlet can also function as a funnel-shaped, towards Outer surface of the outer wall expanding opening is formed his.
- the subsequent introduction of such a funnel-shaped Opening is, for example, by eroding or working out feasible using laser beams.
- the funnel-shaped Opening has a cross section, which for example be circular, rectangular or some other simple geometric Can have shape and possibly also over changes the diameter of the outer wall. Through a funnel shape widening opening is a particularly good film cooling accessible from the outer wall.
- the inlet is preferably directed along an axis, which is inclined towards the outer wall, especially on the Outer wall is vertical. Incoming through the inlet Cooling fluid therefore strikes the outer wall, causing a additional impingement cooling of the outer wall at least in the area of the inlet is reached.
- the outlet of a cooling area is preferably between the inlet for cooling air and the inflow area the turbine blade arranged. This ensures a so-called counterflow cooling, in which the cooling fluid inside the cooling area against the flow direction of the the hot gas flow flowing around the turbine blade is. This leads in particular to one used as a guide vane Turbine blade for improved film cooling.
- the cooling area with counterflow is preferably on the Suction side in the vicinity of the outflow area arranged so that the associated outlet for cooling fluid with respect to the Hot gas flow upstream of the lowest area Pressure level of the flowing along the suction side Hot gas lies. This is particularly advantageous aerodynamically, the flow of hot gas in the outflow area is largely unaffected by escaping cooling fluid.
- a cooling area between an outer wall and an inner wall is arranged as a whole by casting in one Work step can be produced.
- the turbine blade also contain two or more cast parts, using suitable methods (joining processes) according to Pouring be firmly connected.
- the inlet is made by casting.
- the turbine blade preferably has a variety of cooling areas both along their major axis as well as in a plane perpendicular to the main axis.
- a stationary guide vane Gas turbine can be on the suction side as well as on the Pressure side three times three cooling chambers and depending on what can be achieved Heat transfer also more or less cooling chambers exhibit.
- a geometrically complex blade preferably has less on the suction side and pressure side Cooling chambers as a comparable guide vane.
- the task aimed at using the turbine blade is solved in that the turbine blade as a moving blade or guide vane in a gas turbine plant, in particular in the gas turbine, in the temperatures of clearly over 1000 ° C of the hot gas flowing around the turbine blade occur is used.
- Turbine blade 1 a guide blade of a gas turbine, is shown.
- This has a wall structure 2 with an inflow area 8, an outflow area 9 and a pressure side 10 and a suction side 11, which are arranged opposite each other are.
- In the wall structure 2 are both on the suction side 11 as well as three on the pressure side 10 each as cooling chambers 20 formed hollow cooling areas 5, 5a are provided.
- This Cooling areas 5, 5a are in the wall structure 2 between one Outer wall 3 and an inner wall 4 arranged.
- the outer wall 3 is in operation of the gas turbine, not shown, of a hot gas 18 (see Figure 2).
- the turbine blade 1 is designed as a hollow blade, so that one of the inner wall 4 enclosed cooling air supply 21 is formed is.
- the cooling areas 5, 5a have a length that is clear larger, for example 10 times larger than their cross section is.
- the outer wall 3 has a significantly smaller wall thickness than the inner wall 4, for example the wall thickness is the outer wall 3 1.0 mm and the wall thickness of the inner wall 4 1.5 mm.
- the cross section of the cooling areas 5, 5a lies in the area the wall thickness of the outer wall 3 and is, for example in about 1.0 mm.
- Over the length of each cooling area 5, 5a are a plurality, preferably over five, heat transfer elements 7 arranged. From the cooling air supply 21 leads into each cooling area 5, 5a, a respective inlet 15 into, which is preferably as a bore or a plurality formed from holes or cast and the required Cooling capacity is adjusted.
- the inlet 15 is along directed an axis 22 which is substantially perpendicular stands on the outer wall 3. This will create an additional one Impact cooling of the outer wall 3 is achieved in the area of the inlet 15.
- a respective outlet leads from each cooling area 5, 5a 16 to the outer surface of the wall structure 2.
- the outlet 16 is also preferably through a bore 17 or more Bores 17, depending on the cooling capacity requirement; executed.
- the outlet 16 can also e.g. by eroding or Machining with a laser beam and be funnel-shaped expand towards the flow of hot gas 18.
- the Bores 17 are opposite to the flow direction of the Turbine blade 1 hot gas 18 flowing past under a acute angle inclined, which is particularly favorable Form cooling air film on the outer surface of wall structure 2 can.
- the outlet is in particular on the suction side 11 16 arranged closer to the inflow area 8 than that of the same Cooling chamber 20 assigned inlet 15. This will Cooling air 6 in counterflow to the flow of hot gas 18 in the Cooling chamber 20 out.
- FIG. 2 and FIG. 3 show an enlarged representation of the wall structure 2 in the area of a cooling chamber 20.
- the cooling chamber 20 is flowed through by cooling fluid 6, in particular cooling air, along a main flow direction 12.
- the main flow direction 12 is essentially perpendicular to the main axis 19 of the turbine blade 1.
- the bores 17 of the outlet 16 can be directed out of a plane perpendicular to the main axis 19.
- the heat transfer elements 7 are designed as columns with a circular cross section and a diameter d 1 . They are thermally connected to both the inner wall 4 and the outer wall 3.
- Several heat transfer elements 7 are each arranged along a line 14, which is perpendicular to the main flow direction 12.
- a plurality of rows 13a, 13b are provided along the main flow direction 12.
- the distance d 2 between two adjacent rows 13a, 13b is approximately the same or slightly less than the distance d 3 between adjacent heat transfer elements 7 of a row 13a, 13b.
- the diameter d 1 of a heat transfer element 7 is, for example, 1.0 mm
- the distance d 2 between two rows 13a, 13b is approximately between 1.5 mm and 1.75 mm
- the distance d 3 between two heat transfer elements 7 is approximately 1.75 mm
- the diameter d 1 and the distances d 2 , d 3 can vary from line 14 to line 14, according to the desired heat transfer.
- the heat transfer elements 7 of immediately adjacent rows 13a, 13b are offset from one another along the respective line 14 by approximately half the distance d 3 .
- the alternating arrangement of the heat transfer elements 7 thus increases the contact time for heat transfer between the cooling air 6 and the heat transfer element 7 connected to the outer wall 3, so that particularly high heat transfer and thus cooling of the outer wall 3 takes place.
- the effectiveness of the cooling is further enhanced by the fact that the outer wall 3 is designed with a small wall thickness.
- the supporting inner wall 4, which is not directly exposed to the hot gas 18, is also cooled.
- the invention is characterized by a turbine blade a wall structure in which the cooling function essentially on an outer wall and the supporting function essentially is divided on an inner wall.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
- FIG 1
- eine Leitschaufel einer Gasturbine in einem Querschnitt,
- FIG 2
- eine vergrößerte Darstellung der Wandstruktur gemäß Figur 1 und
- FIG 3
- einen Schnitt durch die Wandstruktur gemäß Figur 2.
Claims (12)
- Turbinenschaufel (1) mit einer von einem Heißgas (18) umströmbaren Wandstruktur (2), die einen Anströmbereich (8), einen Abströmbereich (9) und dazwischenliegend sich gegenüberliegend eine Druckseite (10) sowie eine Saugseite (11) aufweist und zumindest bereichsweise eine von dem Heißgas (18) umströmbare Außenwand (3), eine Innenwand (4) und einen zwischen Innenwand (4) und Außenwand (3) angeordneten Kühlbereich (5) zur Durchströmung mit einem Kühlfluid (6) aufweist, und jeder Kühlbereich (5) einen die Innenwand (4) durchdringenden Einlaß (15) und einen die Außenwand (3) durchdringenden Auslaß (16) für Kühlfluid (6) aufweist,
dadurch gekennzeichnet,daß
in dem Kühlbereich (5) von dem Kühlfluid (6) in einer Hauptströmungsrichtung (12) umströmbare Wärmeübertragungselemente (7) hintereinander angeordnet sind, die wärmetechnisch mit der Außenwand (3) verbunden sind und der Kühlbereich (5) als eine von Außenwand (3) und Innenwand (4) umschlossene Kühlkammer (20) ausgebildet ist. - Turbinenschaufel (1) nach Anspruch 1,
dadurch gekennzeichnet, daß der Auslaß (16) durch eine Bohrung (17) oder mehrere Bohrungen (17) hergestellt ist. - Turbinenschaufel (1) nach Anspruch 1 oder 2,
dadurch gekennzeichnet, daß mehrere Wärmeubertragungselemente (7) in einer Reihe (13) entlang einer Linie (14) angeordent sind, wobei die Linie (14) gegenüber der Hauptströmungsrichtung (12), vorzugsweise um einen Winkel von 90°, geneigt ist. - Turbinenschaufel (1) nach Anspruch 3,
dadurch gekennzeichnet, daß mehrere Reihen (13) zueinander parallel angeordnet sind, und die Wärmeübertragungselemente (7) unmittelbar benachbarter Reihen (13a, 13b) entlang der Linie (14) zueinander versetzt sind. - Turbinenschaufel (1) nach einem der vorhergehenden Anspruche, dadurch gekennzeichnet, daß die Innenwand (4), insbesondere dicker, z.B. um den Faktor 1,5, als die Außenwand ist.
- Turbinenschaufel (1) nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß der Auslaß (16) einen Querschnitt aufweist, welcher sich von der Kühlkammer (20) zu der von dem Heißgas (18) umströmbaren Oberfläche der Außenwand (3) hin erweitert.
- Turbinenschaufel (1) nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß der Einlaß (15) entlang einer Achse (22) gerichtet ist, die gegenüber der Außenwand (3) geneigt ist, insbesondere um einen Winkel von etwa 90°.
- Turbinenschaufel (1) nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß zumindest bei einem Kühlbereich (5a) der Auslaß (16) zwischen dem Einlaß (15) und dem Anströmbereich (8) angeordnet ist.
- Turbinenschaufel (1) nach Anspruch 8,
dadurch gekennzeichnet, daß der Kühlbereich (5a) an der Saugseite (11) in der Umgebung des Abströmbereichs (9) so angeordent ist, daß der Auslaß (16) zwischen einem Bereich mit dem niedrigsten Druckniveau bei Umströmung mit Heißgas (18) und dem Anströmbereich (8) liegt. - Turbinenschaufel (1) nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß Außenwand (3), Innenwand (4) und Wärmeübertragungselemente (7) durch Gießen in einem Arbeitsschritt hergestellt sind.
- Turbinenschaufel (1) nach einem der vorhergehenden Ansprüche, welche eine Laufschaufel oder eine Leitschaufel für eine Gasturbine ist.
- Verwendung einer Turbinenschaufel (1) nach Anspruch 9 in einer Gasturbinenanlage.
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE19649924 | 1996-12-02 | ||
DE19649924 | 1996-12-02 | ||
PCT/DE1997/002702 WO1998025009A1 (de) | 1996-12-02 | 1997-11-18 | Turbinenschaufel sowie verwendung in einer gasturbinenanlage |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0954680A1 EP0954680A1 (de) | 1999-11-10 |
EP0954680B1 true EP0954680B1 (de) | 2002-02-06 |
Family
ID=7813384
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP97949947A Expired - Lifetime EP0954680B1 (de) | 1996-12-02 | 1997-11-18 | Turbinenschaufel sowie verwendung in einer gasturbinenanlage |
Country Status (4)
Country | Link |
---|---|
EP (1) | EP0954680B1 (de) |
JP (1) | JP4027430B2 (de) |
DE (1) | DE59706345D1 (de) |
WO (1) | WO1998025009A1 (de) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP3564484A1 (de) | 2018-05-04 | 2019-11-06 | Siemens Aktiengesellschaft | Bauteilwand eines heissgasbauteils |
Families Citing this family (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6126397A (en) * | 1998-12-22 | 2000-10-03 | United Technologies Corporation | Trailing edge cooling apparatus for a gas turbine airfoil |
US6254334B1 (en) * | 1999-10-05 | 2001-07-03 | United Technologies Corporation | Method and apparatus for cooling a wall within a gas turbine engine |
EP1136651A1 (de) | 2000-03-22 | 2001-09-26 | Siemens Aktiengesellschaft | Kühlsystem für eine Turbinenschaufel |
EP1188902A1 (de) | 2000-09-14 | 2002-03-20 | Siemens Aktiengesellschaft | Bauteil mit einer prallgekühlten Wand |
JP4586265B2 (ja) * | 2000-12-07 | 2010-11-24 | 株式会社Ihi | タービン翼のトランスピレーション冷却伝熱促進構造 |
US6511293B2 (en) | 2001-05-29 | 2003-01-28 | Siemens Westinghouse Power Corporation | Closed loop steam cooled airfoil |
US6896487B2 (en) * | 2003-08-08 | 2005-05-24 | United Technologies Corporation | Microcircuit airfoil mainbody |
US7364405B2 (en) * | 2005-11-23 | 2008-04-29 | United Technologies Corporation | Microcircuit cooling for vanes |
EP1930544A1 (de) * | 2006-10-30 | 2008-06-11 | Siemens Aktiengesellschaft | Turbinenschaufel |
US9638057B2 (en) | 2013-03-14 | 2017-05-02 | Rolls-Royce North American Technologies, Inc. | Augmented cooling system |
US10683762B2 (en) | 2016-07-12 | 2020-06-16 | Rolls-Royce North American Technologies Inc. | Gas engine component with cooling passages in wall |
CN109139128A (zh) * | 2018-10-22 | 2019-01-04 | 中国船舶重工集团公司第七0三研究所 | 一种船用燃气轮机高压涡轮导叶冷却结构 |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE3003347A1 (de) * | 1979-12-20 | 1981-06-25 | BBC AG Brown, Boveri & Cie., Baden, Aargau | Gekuehlte wand |
US5405242A (en) | 1990-07-09 | 1995-04-11 | United Technologies Corporation | Cooled vane |
US5690472A (en) * | 1992-02-03 | 1997-11-25 | General Electric Company | Internal cooling of turbine airfoil wall using mesh cooling hole arrangement |
US5328331A (en) * | 1993-06-28 | 1994-07-12 | General Electric Company | Turbine airfoil with double shell outer wall |
US5702232A (en) * | 1994-12-13 | 1997-12-30 | United Technologies Corporation | Cooled airfoils for a gas turbine engine |
-
1997
- 1997-11-18 EP EP97949947A patent/EP0954680B1/de not_active Expired - Lifetime
- 1997-11-18 WO PCT/DE1997/002702 patent/WO1998025009A1/de active IP Right Grant
- 1997-11-18 JP JP52504598A patent/JP4027430B2/ja not_active Expired - Fee Related
- 1997-11-18 DE DE59706345T patent/DE59706345D1/de not_active Expired - Lifetime
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP3564484A1 (de) | 2018-05-04 | 2019-11-06 | Siemens Aktiengesellschaft | Bauteilwand eines heissgasbauteils |
US11220915B2 (en) | 2018-05-04 | 2022-01-11 | Siemens Energy Global GmbH & Co. KG | Component wall of a hot gas component |
Also Published As
Publication number | Publication date |
---|---|
EP0954680A1 (de) | 1999-11-10 |
JP2001505275A (ja) | 2001-04-17 |
JP4027430B2 (ja) | 2007-12-26 |
DE59706345D1 (de) | 2002-03-21 |
WO1998025009A1 (de) | 1998-06-11 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP0964981B1 (de) | Turbinenschaufel sowie deren verwendung in einer gasturbinenanlage | |
DE602005000449T2 (de) | Kühlung mit Mikrokanälen für eine Turbinenschaufel | |
EP0954680B1 (de) | Turbinenschaufel sowie verwendung in einer gasturbinenanlage | |
DE60202212T2 (de) | Kühlbares segment für turbomaschinen und turbinen mit brennkammer | |
DE60015233T2 (de) | Turbinenschaufel mit interner Kühlung | |
DE10001109B4 (de) | Gekühlte Schaufel für eine Gasturbine | |
DE3248161C2 (de) | ||
DE3248162C2 (de) | Kühlbare Schaufel | |
DE102005044183A1 (de) | Vorrichtung und Verfahren zur Kühlung von Turbinenschaufelplattformen | |
DE4441507A1 (de) | Turbinenkühlschaufel | |
DE3248163A1 (de) | Kuehlbare schaufel | |
EP1283326B1 (de) | Kühlung einer Turbinenschaufel | |
EP0892149B1 (de) | Kühlsystem für den Vorderkantenbereich einer hohlen Gasturbinenschaufel | |
DE2657405A1 (de) | Oberflaechenkuehlvorrichtung, insbesondere fuer gasturbinentriebwerke | |
EP1247602B1 (de) | Verfahren zur Herstellung einer Turbinenschaufel | |
DE60030030T2 (de) | Kühlkreislauf für dampf- und luftgekühlte Turbinenleitschaufeln | |
DE19814680A1 (de) | Gekühlte Gasturbinen-Laufschaufel | |
WO2005068783A1 (de) | Gekühlte schaufel für eine gasturbine | |
EP1409926B1 (de) | Prallkühlvorrichtung | |
EP0972910A1 (de) | Berührungsloses Abdichten von Spalten in Gasturbinen | |
EP1668236B1 (de) | Brennkammer mit kühleinrichtung und verfahren zur herstellung der brennkammer | |
DE102016112282A1 (de) | Kühlstruktur für eine stationäre Schaufel | |
EP0973998B1 (de) | Verfahren zur kühlung einer turbinenschaufel | |
DE69925447T2 (de) | Kühlbare Schaufelblätter | |
DE2643049A1 (de) | Schaufel mit gekuehlter plattform fuer eine stroemungsmaschine |
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 |
|
17P | Request for examination filed |
Effective date: 19990520 |
|
AK | Designated contracting states |
Kind code of ref document: A1 Designated state(s): CH DE FR GB IT LI |
|
GRAG | Despatch of communication of intention to grant |
Free format text: ORIGINAL CODE: EPIDOS AGRA |
|
GRAG | Despatch of communication of intention to grant |
Free format text: ORIGINAL CODE: EPIDOS AGRA |
|
GRAH | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOS IGRA |
|
17Q | First examination report despatched |
Effective date: 20010710 |
|
GRAH | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOS IGRA |
|
GRAA | (expected) grant |
Free format text: ORIGINAL CODE: 0009210 |
|
REG | Reference to a national code |
Ref country code: GB Ref legal event code: IF02 |
|
AK | Designated contracting states |
Kind code of ref document: B1 Designated state(s): CH DE FR GB IT LI |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: EP |
|
REF | Corresponds to: |
Ref document number: 59706345 Country of ref document: DE Date of ref document: 20020321 |
|
GBT | Gb: translation of ep patent filed (gb section 77(6)(a)/1977) |
Effective date: 20020411 |
|
ET | Fr: translation filed | ||
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: LI Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20021130 Ref country code: CH Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20021130 |
|
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 |
|
26N | No opposition filed |
Effective date: 20021107 |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: PL |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: PLFP Year of fee payment: 19 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: GB Payment date: 20151109 Year of fee payment: 19 Ref country code: IT Payment date: 20151126 Year of fee payment: 19 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: FR Payment date: 20151110 Year of fee payment: 19 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: DE Payment date: 20170120 Year of fee payment: 20 |
|
GBPC | Gb: european patent ceased through non-payment of renewal fee |
Effective date: 20161118 |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: ST Effective date: 20170731 |
|
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 Effective date: 20161118 Ref country code: FR Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20161130 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R071 Ref document number: 59706345 Country of ref document: DE |
|
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: 20161118 |