EP1113145A1 - Schaufel für Gasturbinen mit Drosselquerschnitt an Hinterkante - Google Patents
Schaufel für Gasturbinen mit Drosselquerschnitt an Hinterkante Download PDFInfo
- Publication number
- EP1113145A1 EP1113145A1 EP00811043A EP00811043A EP1113145A1 EP 1113145 A1 EP1113145 A1 EP 1113145A1 EP 00811043 A EP00811043 A EP 00811043A EP 00811043 A EP00811043 A EP 00811043A EP 1113145 A1 EP1113145 A1 EP 1113145A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- guide element
- ribs
- rear edge
- walls
- cooling
- 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
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
- B22D11/00—Continuous casting of metals, i.e. casting in indefinite lengths
- B22D11/04—Continuous casting of metals, i.e. casting in indefinite lengths into open-ended moulds
- B22D11/0405—Rotating moulds
-
- 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
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/12—Fluid guiding means, e.g. vanes
- F05D2240/122—Fluid guiding means, e.g. vanes related to the trailing edge of a stator vane
-
- 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
- F05D2240/00—Components
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
- F05D2240/304—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the trailing edge of a rotor blade
Definitions
- the present invention relates to the field of gas turbine engines Guide elements such as guide or turbine blades. It affects one of a hot Air flow around the guide element for a gas turbine, which at least in a rear edge area, in which the air flow breaks off from the guide element at least two substantially parallel, and with ribs together there are walls connected to form inner cooling channels, and which is cooled on the inside with cooling medium flowing through the cooling channels, the cooling medium at the rear edge substantially parallel to the walls between them emerges from the guide element.
- a gas turbine comprises a multitude of elements, which consist of hot working air be flown to. Because the working air has a temperature that for many the materials from which such flow-around components are built, in particular leads to severe signs of wear after a long period of operation it is necessary to cool many of these components.
- the cooling can be used as internal cooling be designed in which the elements are designed as hollow profiles or simple be provided with internal cooling channels through which a cooling air flow is passed becomes.
- film cooling it is also possible to use what is known as film cooling to provide, in which the elements are acted upon by an outside cooling air film become.
- Modern gas turbine blades usually use a combination of the above methods, i.e. an internal convective cooling system is used, which critical points also has openings for film blowing.
- an internal convective cooling system is used, which critical points also has openings for film blowing.
- the amount of cooling air used must be minimized. This means, that even for large components only a small cooling air mass flow Available. To the low cooling mass flows at the same time required to realize and control efficient internal heat transfer the flow cross-sections reduced accordingly. Throttle cross sections introduced become.
- the throttling of the cooling mass flow takes place in the area of the cast blade trailing edge, near the Cooling air outlet takes place.
- the end of the ribs is the pressure and suction side Connect the wall, set back in the axial direction, i.e. the ribs end already inside the shovel and do not reach the rear edge.
- Figure 1 shows a section through a guide vane according to the prior art, such as it is often used in gas turbines. It is an axial to Main axis of the turbine and cut perpendicular to the plane of the airfoil through a guide vane, as is typically immediately after the combustion chamber and in front of the first row of the gas turbine for optimal flow against the blades be used.
- the blade is designed as a hollow profile, which bounded on the suction side by a wall 10 and on the pressure side by a further wall 11 becomes. In the inflow area, the blade is widened, walls 10 and 11 are in a curve connected to each other, and is located between the walls 10 and 11 there is a central, radially extending insert 12 around which the cooling channel leads around.
- the guide vane 30 is only one of the two axially Direction, broken ribs interconnected walls 10 and 11 limited, cooling channels run in between. Often the central one Insert 12 completely or partially enclosed by approximately axially extending ribs. These ribs converge at the rear end of the insert (16 in Fig. 1) and from there connect the suction and pressure side bucket walls. Between The ribs form approximately axial channels in which the cooling air is guided becomes.
- the fin bank can be interrupted by one in the radial To produce plenum 18.
- the following ribbed bench 17 can be arranged "in line" or offset to the previous ribbed.
- the pressure and suction walls are very short ribs or so-called pin rows connected together.
- State of the art is well, leave these internals (ribs, pins, etc.) inside the blade ends.
- This avoids the need for the core required for casting production has a large jump in the cross-sectional area exactly at the rear edge.
- This strong discontinuity in the cross-sectional shape of the core leads to the manufacture to a high number of core breaks.
- the above procedure has the considerable Disadvantage that the outlet cross section of the cooling air and thus the cooling air mass flow can only be controlled insufficiently.
- the walls also mostly have film cooling holes 13-15, through which Cooling air can flow to the outside.
- the invention is therefore based on the object of a hot air flow flow around the guide element of a gas turbine, which at least in a rear Edge area, at which the air flow breaks off from the guide element, at least two arranged substantially parallel, and with ribs inside each other Cooling channels forming connecting walls, and which with cooling medium flowing through the cooling channels is cooled on the inside, the Coolant at the trailing edge substantially parallel to the walls between this emerges from the guide element.
- a first preferred embodiment of the invention is characterized in that that the throughput of cooling medium through the guide element essentially through the dimensioning of the between the ribs, here so-called throttle ribs Outlet openings is determined.
- the better one due to the arrangement Accessibility and reworkability is particularly advantageous if the Throttling of the cooling air through the throttling ribs on the rear edge is effected, and the throttling from the outside easily by drilling or the like. can be set or measured.
- Another embodiment of the invention is characterized in that the Thickness of the guide element at the rear edge in the range from 0.5 to 5 mm, in particular is preferably in the range of 1.0 to 2.5 mm, and that the slot thickness of the Cooling air ducts between the walls at the outlet in the range of 0.3 to 2 mm, is in particular in the range from 0.8 to 1.5 mm.
- the guiding element is designed as a guide blade arranged in front of a turbine rotor and if air is used as the cooling medium, the ones according to the invention prove Arrangement and these dimensions as particularly advantageous.
- the invention further comprises a method for producing one of one hot air flow around the guide element of a gas turbine, which at least in a rear edge area, in which the air flow breaks off from the guide element at least two substantially parallel, and with ribs together there are walls connected to form inner cooling channels, and which is cooled on the inside with cooling medium flowing through the cooling channels, the cooling medium at the rear edge substantially parallel to the Walls between them emerges from the guide element, which is characterized by that the guiding element is manufactured in a casting process that the rear edge area with the guide element or its walls in Flow direction extending supernatant is poured, and that after the Pour the supernatant so that at least part of the ribs arranged as a throttling ribs with the rear edge essentially flush are.
- the casting core is shaped so that the rib geometry over the rear edge of the blade is modeled in the cast core. Only after one The rib geometry is about 0.5 to 5, preferably 1 to 3 core thicknesses hidden.
- This method makes it easy to manufacture one according to the invention Guiding element only possible. With a normal casting process, namely the effective throttle cross-section is not simply placed directly on the trailing edge become. The sudden increase in cross-section at the outlet in the casting core leads to manufacturing to a sharp increase in core breaks. This can be done while leaving a protrusion during the casting process can be avoided.
- a preferred embodiment of the method is characterized in that no ribs are arranged between the walls in the area of the overhang, and that the throughput of cooling medium through the finished guide element essentially by the dimensioning of the arranged between the throttle ribs Outlet openings is determined. If in the area of the protrusion on any ribs can be dispensed with in the casting process, in particular in the preferred Press casting processes ("investment casting") are largely avoided. It shows furthermore that especially if the length of the supernatant is in the range from 0.5 to 3 times as large, particularly preferably of the same size, as slot thickness of the cooling air duct between the walls, such core breaks can be avoided can do without excessive post-processing after manufacture would.
- Figure 2 a shows a section through a guide vane directly to the rear edge bordering ribs 24 between the walls 10 and 11. It is about a figure 2 corresponding axially to the main axis of the turbine and perpendicular to Blade plane running section through a guide blade.
- the shovel is again formed as a hollow profile, which is on the suction side of a wall 10, and is delimited on the pressure side by a further wall 11.
- Figure 2c) shows a section along the line X-X in Figure 2a), i.e. essentially parallel to the leaf plane. Immediately adjacent to the insert 12 first ribs 16.
- the single ones Ribs of the rows 16 and 17 advantageously have a so-called division ratio, the ratio of the radial width e normal to the plane of the sheet radial spacing f, in the range of 0.25 to 0.75.
- Another radial plenum 19 follows, followed by so-called pins 20, i.e. as simple webs formed rows of ribs which are as uniform as possible Allow distribution of the cooling air flow at the rear edge 21.
- the division ratio (Diameter g to radial spacing h) of the pins 20 lies in the Range from 0.25 to 0.7.
- Such a blade is usually produced using the casting process, as a rule an investment casting process.
- This casting process can but when making the effective throttle cross section not just straight to the Trailing edge.
- the sudden cross-sectional expansion at the outlet in the cast core leads to a sharp increase in core breaks during manufacture. However, this can be avoided if a protrusion is left in the casting process become.
- the cooling geometry shown in the core is based on the actual one Component limit extended.
- Figure 2b) shows the edge area of an element extended in this way beyond the rear edge by the length b. in the In the region of the protrusion, there are advantageously no more ribs.
- the transition from the throttle geometry does not then coincide with the core holder, rather, it first occurs within the extended component Transition from the throttle geometry to a continuous radial channel instead, which can then be used as a core holder without the risk of core breakage can.
- This transition can be optimal in various ways depending on the procedure to be designed to hold the core, i.e. it is not imperative that the two Walls as shown in Figure 2b) simply extended evenly to the rear e.g. also a gradual protruding expansion or rejuvenation resp. Thickening of the walls in the area of the overhang is conceivable.
- the protruding geometry is after the casting to the target length of the rear edge post-processed, i.e. removed so that the throttling points coincide with the rear edge. This can e.g. together with those that are usually necessary after the fact Post-processing such as erosion and laser drilling of the film cooling holes 13-15 happen.
- the rear edge usually has a thickness d im Range from 0.5 to 5 mm, preferably in the range from 1.0 to 2.5 mm.
- the slit thickness c of the cooling air duct is usually in the range from 0.3 to 2.0 mm, preferably in Range from 0.8 to 1.5 mm.
- the protrusion b above the rear edge 0.5 to 5 times, preferably 1 to 3 times, the length a of Throttle ribs 24 amount, it is particularly advantageous if the projection b is the same as the length a of the throttle ribs.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
- Da der Querschnitt klein ist, wirken sich selbst kleine Toleranzen bei der Herstellung (Guss) auf den Kühlluftmassendurchsatz der Schaufel aus.
- Da die Drosselstelle im Inneren des Leitelements liegt, lässt sich der wirksame Drosselquerschnitt nur schwer messen und kontrollieren.
- Da die Drosselkante im Inneren des Leitelements liegt, kann der wirksame Drosselquerschnitt nachträglich nur schwer modifiziert werden.
- Die beiden meist recht dünnen Wände sind äusserst anfällig auf Beschädigungen, welche von Fremdkörpern im Heissgas verursacht werden, und welche u.U. sogar zu einer Veränderung der Drosselquerschnitte führen können.
- Durch die stufenweise Expansion der Kühlluft (1) am Ende der Rippen und (2) an der Schaufelhinterkante lässt sich der Kühlluftmassenstrom nur schwer kontrollieren und justieren.
- Fig. 1
- zeigt einen Querschnitt durch eine Leitschaufel mit interner Kühlung für eine Gasturbine nach dem Stand der Technik; und
- Fig. 2
- a) zeigt einen Querschnitt durch eine Leitschaufel mit unmittelbar an der Hinterkante der Schaufel angeordneten Drosselrippen, b) eine Detailansicht des Hinterkantenbereichs des Schnittes nach a), und c) einen Schnitt entlang der Linie X-X in Figur 2a), d.h. im wesentlichen parallel zur Ebene der Schaufel durch den internen Kühlkanal.
- Der effektive Drosselquerschnitt kann leicht bei der Austrittskante gemessen werden.
- Es entsteht nur eine Drosselstelle genau na der Hinterkante anstatt zweier Drosselstellen am Ende der Rippen und der Hinterkante.
- Gegebenenfalls beim Gussverfahren entstandene Ungenauigkeiten der Drosselregion können leicht nachbearbeitet werden, da die Drosselstellen von aussen zugänglich sind.
- Der Drosselquerschnitt kann bei Bedarf leicht verändert werden.
- Die Anordnung der Rippen ganz am Ende der Schaufel führt zu einer erhöhten Stabilität der Abrisskante, so können Fremdkörper im Arbeitsluftstrom die Hinterkante weniger beschädigen und die Kühlung der Komponente kann durch derartige Deformationen weniger beeinträchtigt werden.
- 10
- saugseitige Wand
- 11
- druckseitige Wand
- 12
- Einsatz bzw. Kern
- 13
- saugseitige Filmbohrungen
- 14
- Filmbohrungen an Vorderkante
- 15
- druckseitige Filmbohrungen
- 16
- am Einsatz anschliessende Rippen
- 17
- Zwischenrippen
- 18
- vorderes radiales Plenum
- 19
- hinteres radiales Plenum
- 20
- Pins
- 21
- Hinterkante des Blattes
- 22
- Austrittsöffnung an der Hinterkante
- 23
- Arbeitsluftstrom
- 24
- Drosselrippen an Hinterkante
- 25
- Kühlluftaustrittsöffnungen an Hinterkante
- 26
- axiale Kanäle zwischen Rippen 17
- 27
- axiale Kanäle zwischen Kippen 16
- 28
- eintrittsseitiger Kühlluftstrom
- 29
- austrittsseitiger Kühlluftstrom
- 30
- Leitschaufel
- a
- Länge der Drosselrippen
- b
- Länge des Überstandes nach Guss
- c
- Schlitzdicke des Kühlluftkanals beim Austritt
- d
- Dicke der Leitschaufel an der Hinterkante
- e
- Breite der Drosselrippen
- f
- Rippenteilung der Drosselrippen
- g
- Breite der Pins 20
- h
- Teilung der Pins 20
Claims (11)
- Von einem heissen Luftstrom (23) umströmtes Leitelement (30) einer Gasturbine, welches wenigstens in einem hinteren Kantenbereich (21), bei dem der Luftstrom (23) vom Leitelement (30) abreisst, aus wenigstens zwei im wesentlichen parallel angeordneten, und mit Rippen (16,17,20) miteinander in innere Kühlkanäle (18,19,25,26,27) ausbildender Weise verbundenen Wänden (10,11) besteht, und welches mit durch die Kühlkanäle (18,19,25,26,27) strömendem Kühlmedium (28,29) innenseitig gekühlt wird, wobei das Kühlmedium an der hinteren Kante (21) im wesentlichen parallel zu den Wänden (10,11) zwischen diesen aus dem Leitelement (30) austritt,
dadurch gekennzeichnet, dass
wenigstens ein Teil der Rippen (24) mit der hinteren Kante (21) im we sentlichen bündig abschliessend angeordnet sind. - Leitelement (30) nach Anspruch 1, dadurch gekennzeichnet, dass der Durchsatz an Kühlmedium (28,29) durch das Leitelement (30) im wesentlichen durch die Dimensionierung der zwischen den Drosselrippen (24) angeordneten Austrittsöffnungen (25) bestimmt ist.
- Leitelement (30) nach Anspruch 2, dadurch gekennzeichnet, dass die Drosselrippen (24) parallel zur Hinterkante (21) eine Breite (e) aufweisen und um jeweils eine Rippenteilung (f) beabstandet angeordnet
sind, und dass das Verhältnis von Breite (e) zu Rippenteilung (f) im Bereich von 0.25 bis 0.75 liegt. - Leitelement (30) nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass die Dicke (d) des Leitelements (30) an der Hinterkante (21) im Bereich von 0.5 bis 5 mm, insbesondere bevorzugt im Bereich von 1.0 bis 2.5 mm liegt, und dass die Schlitzdicke (c) der Kühlluftkanäle (25) zwischen den Wänden (10,11) beim Austritt (21) im Bereich von 0.3 bis 2 mm, insbesondere im Bereich von 0.8 bis 1.5 mm beträgt.
- Leitelement (30) nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, dass es als vor einem Turbinenrotor angeordnete Leitschaufel (30) ausgebildet ist und dass als Kühlmedium Luft verwendet wird.
- Leitschaufel (30) nach Anspruch 5, dadurch gekennzeichnet, dass die Leitschaufel in ihrem Anströmbereich verbreitert ausgebildet ist und im Anströmbereich die Kühlluft um einen inneren, zentralen, radial verlaufenden Einsatz (12) in saugseitigen und druckseitigen Kühlkanälen strömt, und dass die Kühlluft zwischen am Einsatz (12) anschliessenden Rippen (16), dann zwischen Zwischenrippen (17), dann zwischen Pins (20) zwischen den Wänden (10,11) hindurchströmt bevor sie durch Austrittsöffnungen (25) an der Hinterkante aus der Leitschaufel (30) austritt.
- Verfahren zur Herstellung eines von einem heissen Luftstrom (23) umströmten Leitelements (30) einer Gasturbine, welches wenigstens in einem hinteren Kantenbereich (21), bei dem der Luftstrom (23) vom Leitelement (30) abreisst, aus wenigstens zwei im wesentlichen parallel angeordneten, und mit Rippen (16,17,20) miteinander in innere Kühlkanäle (18,19,25,26,27) ausbildender Weise verbundenen Wänden (10,11) besteht, und welches mit durch die Kühlkanäle (18,19,25,26,27) strömendem Kühlmedium (28,29) innenseitig gekühlt wird, wobei das Kühlemedium an der hinteren Kante (21) im wesentlichen parallel zu den Wänden (10,11) zwischen diesen aus dem Leitelement (30) austritt,
dadurch gekennzeichnet, dass
das Leitelement (30) in einem Giessverfahren hergestellt wird, dass dabei der hintere Kantenbereich (21) mit einem das Leitelement (30) respektive dessen Wände (10,11) in Strömungsrichtung verlängernden Überstand gegossen wird, und dass nach dem Giessen der Überstand derart abgetragen wird, dass wenigstens ein Teil der Rippen als Drosselrippen (24) mit der hinteren Kante (21) im wesentlichen bündig abschliessend angeordnet sind. - Verfahren nach Anspruch 7, dadurch gekennzeichnet, dass der Durchsatz an Kühlmedium (28,29) durch das fertige Leitelement (30) im wesentlichen durch die Dimensionierung der zwischen den Drosselrippen (24) angeordneten Austrittsöffnungen (25) bestimmt ist.
- Verfahren nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass es sich beim Gussverfahren um ein Pressgussverfahren handelt, dass der Überstand eine Länge (b) hinter der Hinterkante (21) aufweist, dass die Wände (10,11) beim Austritt (21) um eine Schlitzdicke (c) der Kühlluftkanäle (25) beabstandet sind, und dass insbesondere die Länge (b) des Überstandes im Bereich von 0.5 bis 5 Mal so gross, insbesondere bevorzugt 1 bis 3 Mal so gross, ist wie Schlitzdicke (c).
- Verfahren nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass die Drosselrippen (24) parallel zur Hinterkante (21) eine Breite (e) aufweisen und um jeweils eine Rippenteilung (f) beabstandet angeordnet sind, dass das Verhältnis von Breite (e) zu Rippenteilung (f) im Bereich von 0.25 bis 0.75 liegt, dass die Dicke (d) des Leitelements (30) an der Hinterkante (21) im Bereich von 0.5 bis 5 mm, insbesondere bevorzugt im Bereich von 1.0 bis 2.5 mm liegt, und dass die Schlitzdicke (c) der Kühlluftkanäle (25) zwischen den Wänden (10,11) beim Austritt (21) im Bereich von 0.3 bis 2 mm, insbesondere im Bereich von 0.8 bis 1.5 mm beträgt.
- Verfahren nach einem der vorangehenden Ansprüche, dadurch gekennzeichnet, dass es sich beim Leitelement um eine vor einem Turbinenrotor angeordnete Leitschaufel (30) handelt, und dass als Kühlmedium Luft verwendet wird.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE19963349 | 1999-12-27 | ||
DE19963349A DE19963349A1 (de) | 1999-12-27 | 1999-12-27 | Schaufel für Gasturbinen mit Drosselquerschnitt an Hinterkante |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1113145A1 true EP1113145A1 (de) | 2001-07-04 |
EP1113145B1 EP1113145B1 (de) | 2006-04-05 |
Family
ID=7934726
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP00811043A Expired - Lifetime EP1113145B1 (de) | 1999-12-27 | 2000-11-07 | Schaufel für Gasturbinen mit Drosselquerschnitt an Hinterkante |
Country Status (3)
Country | Link |
---|---|
US (1) | US6481966B2 (de) |
EP (1) | EP1113145B1 (de) |
DE (2) | DE19963349A1 (de) |
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WO2009109462A1 (de) * | 2008-03-07 | 2009-09-11 | Alstom Technology Ltd | Schaufel für eine gasturbine |
EP1715139A3 (de) * | 2005-04-22 | 2010-04-07 | United Technologies Corporation | Kühlung der Abströmkante einer Turbinenschaufel |
WO2010086419A1 (de) | 2009-01-30 | 2010-08-05 | Alstom Technology Ltd. | Gekühlte schaufel für eine gasturbine |
EP2584145A1 (de) * | 2011-10-20 | 2013-04-24 | Siemens Aktiengesellschaft | Gekühlte Turbinenleitschaufel oder gekühltes Turbinenleitblatt für eine Turbomaschine |
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EP1715139A3 (de) * | 2005-04-22 | 2010-04-07 | United Technologies Corporation | Kühlung der Abströmkante einer Turbinenschaufel |
EP2538029A1 (de) * | 2005-04-22 | 2012-12-26 | United Technologies Corporation | Kühlung der Abströmkante einer Turbinenschaufel |
WO2009109462A1 (de) * | 2008-03-07 | 2009-09-11 | Alstom Technology Ltd | Schaufel für eine gasturbine |
US8182225B2 (en) | 2008-03-07 | 2012-05-22 | Alstomtechnology Ltd | Blade for a gas turbine |
WO2010086419A1 (de) | 2009-01-30 | 2010-08-05 | Alstom Technology Ltd. | Gekühlte schaufel für eine gasturbine |
US8721281B2 (en) | 2009-01-30 | 2014-05-13 | Alstom Technology Ltd. | Cooled blade for a gas turbine |
EP2565382A3 (de) * | 2011-08-30 | 2015-04-22 | General Electric Company | Schaufelprofil mit Anordnung von Kühlstiften |
EP2584145A1 (de) * | 2011-10-20 | 2013-04-24 | Siemens Aktiengesellschaft | Gekühlte Turbinenleitschaufel oder gekühltes Turbinenleitblatt für eine Turbomaschine |
WO2013056975A1 (en) * | 2011-10-20 | 2013-04-25 | Siemens Aktiengesellschaft | A cooled turbine guide vane or blade for a turbomachine |
US9896942B2 (en) | 2011-10-20 | 2018-02-20 | Siemens Aktiengesellschaft | Cooled turbine guide vane or blade for a turbomachine |
Also Published As
Publication number | Publication date |
---|---|
DE19963349A1 (de) | 2001-06-28 |
DE50012523D1 (de) | 2006-05-18 |
US20010012484A1 (en) | 2001-08-09 |
US6481966B2 (en) | 2002-11-19 |
EP1113145B1 (de) | 2006-04-05 |
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