EP1046784A1 - Kühlbares Bauteil - Google Patents
Kühlbares Bauteil Download PDFInfo
- Publication number
- EP1046784A1 EP1046784A1 EP99810329A EP99810329A EP1046784A1 EP 1046784 A1 EP1046784 A1 EP 1046784A1 EP 99810329 A EP99810329 A EP 99810329A EP 99810329 A EP99810329 A EP 99810329A EP 1046784 A1 EP1046784 A1 EP 1046784A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- pins
- component
- blow
- gas side
- medium
- 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
- 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
- F05D2260/208—Heat transfer, e.g. cooling using heat pipes
-
- 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
- F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
-
- 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
- F05D2300/00—Materials; Properties thereof
- F05D2300/10—Metals, alloys or intermetallic compounds
- F05D2300/13—Refractory metals, i.e. Ti, V, Cr, Zr, Nb, Mo, Hf, Ta, W
- F05D2300/131—Molybdenum
-
- 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
- F05D2300/00—Materials; Properties thereof
- F05D2300/10—Metals, alloys or intermetallic compounds
- F05D2300/14—Noble metals, i.e. Ag, Au, platinum group metals
- F05D2300/141—Silver
-
- 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
- F05D2300/00—Materials; Properties thereof
- F05D2300/20—Oxide or non-oxide ceramics
- F05D2300/22—Non-oxide ceramics
- F05D2300/224—Carbon, e.g. graphite
Definitions
- the present invention relates to a coolable component according to the Preamble of claim 1.
- cooling in which one Coolant flows over a surface of a component, and this heat deprives while another surface with a heat input is applied.
- a particular disadvantage of convection cooling is that that the entire heat to be dissipated through the component wall must be transported. The area exposed to the heat input is at a much higher temperature than the cooled surface. In addition become significant temperature gradients over component walls and thus Thermal stresses caused.
- the film cooling known from US 3,527,543 was therefore used for a long time preferred where a coolant - preferably air coming from the compressor is removed, or steam - through the component wall from one Cold gas side flows to the hot gas side to which hot gas is applied.
- the coolant absorbs heat from the material while it is flows through the blow-out openings.
- a film lays down relatively cool medium over the hot gas side of the component, and protects it from direct contact with the hot medium. You misplace yourself with modern gas turbines completely on film cooling, the Coolant consumption, however, by mass.
- a coolable component consisting of a Base material, which component is in operation on a hot gas side with a first flowing medium and on a cold gas side with a second flowing medium is in contact, the temperature of the first medium is higher than that of the second medium, such that the component of the the first medium is heated and cooled by the second medium, and wherein the base material of the component encloses pins, which pins from the Cold gas side protrude into the flow of the second medium, and which pins are made of a material whose thermal conductivity is greater is that of the base material used to manufacture the component, such that the pins operate as heat sinks in the base material heat transfer should improve from the pins to the cooling medium become.
- the component Has blow-out openings, through which at least part during operation said second medium flows from the cold gas side to the hot gas side, in such a way that the blow-out openings also act as heat sinks, and that along at least one line on the cold gas side each at least one pin and at least one opening are arranged.
- the blow-out openings also act as heat sinks, and that along at least one line on the cold gas side each at least one pin and at least one opening are arranged.
- the essence of the invention is, on the one hand, the heat instead of through the Coolant flowing through blow-out openings through thermal to lead highly conductive pins out of the material, so that the Limit coolant consumption.
- the limitation of Coolant consumption has a very positive effect on the Efficiency when compressor air is used for cooling purposes.
- the pins are expediently running along the cold gas side Alignments arranged, analogous to the arrangement of the blow-out openings in the Film cooling.
- the fluid mechanical constraints prevent in a closed cooling system within a component a good one, for example, when cooling a trailing edge of a blade convective heat transfer from the pins to the coolant, but what a The condition for the function of the cooling device is.
- blow-out openings and heat conducting pins can be according to different criteria, and in individual cases will of course be one detailed calculation of the temperature distributions in the Require machine component.
- For a minimized coolant consumption will probably be the alternating one Arrangement of two pins and one blow-out opening prove suitable, the opening is expediently arranged centrally between two pins.
- the alternating arrangement of one pin and one opening each prefer to be.
- the thermal conductivity of the Material from which the pins are made as high as possible, and at least have three times the value of the base material.
- the melting point too the material must of course be sufficiently high.
- Materials that are suitable for the production of the thermal pins for example Tungsten, silver, or especially diamond.
- the pens have to be one have the best possible heat transfer to the base material, which is what realizes that they are cast in the components.
- the pens are so deep in that Base material introduced, as it corresponds to 30% to 80% of the material thickness. On the one hand, this ensures a large heat exchange surface, on the other hand the formation of thermal bridges is avoided.
- the Thermal pins of course by a certain axial dimension in the Protect the coolant.
- the invention unfolds Cooling configuration their specific advantages, especially when used in hollow components, inside of which the flow of a cooling medium is provided, in particular where component walls are pointed Collide angles.
- This configuration can be found in particular the trailing edges of gas turbine blades.
- the cooling configuration according to the invention is also used for the cooling of Advantageously to use blade platforms.
- the pens help Dissipate heat from the very solidly built platforms without the To allow cooling air consumption to rise above the masses.
- the Cooling configuration according to the invention advantageously also with impingement cooling be combined
- a first preferred embodiment of the invention is in two views in the Figures 1 and 2 shown.
- the hollow cast turbine blade is in the Operation flows around from a hot gas flow 8, which has a heat input causes the hot gas side 11 into the material of the blade.
- the temperature of the hot gas exceeds that of a material temperature allowed given the mechanical load considerably.
- the function of such a turbine blade can therefore only be achieved by one sufficient cooling can be guaranteed.
- the Blade cooled from its cold gas side 12 by the coolant 9. in the Different internals can be present, such as Baffle cooling plates, or webs for guiding the coolant on the cold gas side.
- Rows of blow-out openings 21 are on the surface of the blade lines running normal to the direction of flow of the hot gas to recognize. Coolant that flows through these openings takes on the one hand heat from the material; on the other hand, the cooler goes down Blow-out flow with appropriate arrangement and design of the Blow-out openings 21 as an insulating layer on the hot gas side 11 of the Blade, and partially isolates it from the hot gas flow 8.
- Shape and size of the blow-out openings 21, as well as their distance from each other, are not essential to the invention, and the chosen representation should not be understood in a restrictive sense.
- the top view of the blade shown in FIG. 2 shows one particularly well Material accumulation 141 in the area of the rear edge 14, and the interior 121 which narrows sharply near the rear edges Material accumulation is very likely to overheat.
- the shovel very thin in this area.
- the surface on the hot gas side 11 is in Trailing edge area much larger than the surface on the cold gas side 12.
- such material accumulation is potentially developing large local temperature differences extremely strong Thermal stress cracks at risk. Because of the special geometric Boundary conditions in the rear edge area must literally remove the heat from the Material accumulation can be transported out.
- a row of blow-out openings 22 along the trailing edge through this flowing coolant 7 takes heat from the Material accumulation 141 and transports it to the outside.
- the blow-out openings 22 are heat sinks. Not too much for the temperature differences along the rear edge to allow it to grow and to avoid local overheating A certain maximum distance between the heat sinks exceed. As a rule of thumb for a design criterion, it is stated that the Distance between two blow-out openings 22 eight hydraulic diameters should not exceed a blow-out opening. This initially results in a large number of blow-out openings and thus in a large one Blow-out mass flow at the trailing edge of the blade.
- a pin 23 made of a material with a high Thermal conductivity - this should be at least three times as high as that Thermal conductivity of the blade material - in the material accumulation 141 introduced, which serves as an additional heat sink.
- Thermally conductive pin two to twenty pin diameter in the blade interior and has the best possible contact with the blade material.
- the latter can be achieved by using the pins when casting the bucket be poured in. They must have a certain length in the Bucket material can be embedded without penetrating it, however, since it otherwise a harmful thermal bridge between the hot gas side 11 and the cold gas side 12 of the blade. It will turn out to be cheap prove if the pins are embedded at a depth in the blade material, which corresponds to between 30% and 80% of the total material thickness, whereby the cheapest measure in individual cases through a numerical simulation of the Heat flows will have to be determined.
- the pins are arranged so that their longitudinal axes are more or less parallel to the exhaust openings run. Furthermore, it is favorable if a along the trailing edge of the blade Number of heat conducting pins and blow-out openings approximately in one flight are arranged. This proves to be particularly advantageous with regard to to ensure a good flow of coolant around the pins, which is a necessary condition for the function of the heat conducting pins as heat sinks represents.
- the trailing edge blow-out openings induce 22 forced convection in the narrow cooling gap, and the heat-conducting pins are arranged by the Blow-out streams 7 flow around and cooled. It shows the close Interdependence of the rear edge blow-out and the heat conducting pins.
- FIG. 3 A further preferred embodiment is shown in FIG. 3 two blow-out openings, two heat conducting pins. This will the coolant consumption compared to the geometry shown in FIG. 1 reduced again.
- flow control devices 25 are also in Blade interior introduced that the blow-out air flow 7 on the Guide thermal pins. Such measures can of course also be used for one Fig. 1 corresponding configuration may be useful.
- the pipe of the coolant to the rear edge can also by appropriate turbulators in the main cooling duct respectively.
- the invention is advantageous at least when used on trailing blade edges make sure that the distance between two heat sinks is not greater is selected as eight hydraulic diameters of a rear edge blow-out opening.
- the preferred one Cross-sectional area of the pins called between one and ten Cross-sectional areas of a blow-out opening.
- the shape of the heat conducting pins can be varied within wide limits. So is for example, a round cross-section is not mandatory. Is appropriate however, in all circumstances, it extends along a longitudinal axis to choose significantly larger than the extension in the other directions.
- the shape of the thermal pins is primarily due to the manufacturing method be determined, and a cylindrical pin is cut off by a Wire particularly easy to obtain. However, through the targeted Design, for example, of the part of the protruding into the coolant The flow around the pin as well as the heat exchange surface to be changed. Two examples of possible geometries are in FIGS. 4 and 5 shown.
- the design shown in Fig. 4 holds the conical shape Flow cross section between the pin 23 and the cooling side Component walls 12 largely constant.
- Consoles 231 enlarge the Heat exchange surface between the base material 141 and the Thermally conductive pin 23, and improve the fixation of the pin in the base material.
- the corrugated design from FIG. 5 also increases the Heat exchange surface, both on the material and
- FIG. 6 carries a Blade platform 3 a blade 1.
- the entire configuration is from a hot gas flow 8 flows against.
- the airfoil is on itself known cooled any way, cooling and coolant supply of the Airfoil are not considered in the figure.
- In the hollow Blade platform flows in coolant 9, and strikes an impact cooling insert 31.
- the coolant flows through openings in the impact cooling insert 32.
- Coolant jets 91 hit the cold gas side 12 of the at high speed Platform where an intensive convection heat exchange takes place.
- the coolant is subsequently discharged through blowout openings 22.
- blow-out stream 7 along the line VII - VII well recognizable, essentially in an escape along the Platform leading edge heat-conducting pins 23 and blow-out openings 22 arranged alternately so that the blow-out stream 7 is only the Thermal conductors around and finally flows through the blow-out openings.
- this top view is for the sake of clarity part of the Openings of the impact cooling insert are not shown.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
- Fig. 1 eine erste bevorzugte Ausführungsform der Erfindung zur Kühlung der Hinterkante einer Gasturbinenschaufel
- Fig. 2 eine Draufsicht auf die in Fig. 1 dargestellte Gasturbinenschaufel
- Fig. 3 eine weitere bevorzugte Ausführungsform der Erfindung zur Kühlung der Hinterkante einer Gasturbinenschaufel
- Fig. 4 und 5 Beispiele für mögliche Varianten der Gestaltung der Wärmeleitstifte
- Fig. 6 ein weiteres Beispiel für die Anwendung der Erfindung bei der Kühlung einer Plattformkante, und Fig. 7 einen Schnitt entlang der in Fig. 6 eingezeichneten Linie VII - VII.
- 1
- Schaufelblatt
- 3
- Schaufelplattform
- 7
- Ausblaseströmung
- 8
- Heissgasströmung
- 9
- Kühlmittelströmung
- 11
- Heissgasseite
- 12
- Kaltgasseite
- 14
- Hinterkante
- 21
- Ausblaseöffnungen
- 22
- Ausblaseöffnungen
- 23
- Wärmeleitstift
- 25
- Strömungsleiteinrichtung
- 31
- Prallkühlblech
- 32
- Prallkühlöffnung
- 91
- Jet
- 121
- Schaufelinnenraum
- 141
- Hinterkanten-Basismaterial
- 231
- Konsole
Claims (13)
- Kühlbares Bauteil, bestehend aus einem Basismaterial, welches Bauteil im Betrieb auf einer Heissgasseite (11) mit einem ersten strömenden Medium (8) und auf einer Kaltgasseite (12) mit einem zweiten strömenden Medium (9) in Kontakt ist, wobei die Temperatur des ersten Mediums höher ist als die des zweiten Mediums, dergestalt, dass das Bauteil von dem ersten Medium erwärmt und von dem zweiten Medium gekühlt wird, und wobei das Basismaterial des Bauteils Stifte (23) umschliesst, welche Stifte aus der Kaltgasseite (12) heraus in die Strömung des zweiten Mediums hineinragen, und welche Stifte aus einem Material bestehen, dessen Wärmeleitfähigkeit grösser ist als diejenige des zur Herstellung des Bauteils verwendeten Basismaterials, dergestalt, dass die Stifte im Betrieb als Wärmesenken in dem Basismaterial wirken, dadurch gekennzeichnet, dass das Bauteil Ausblaseöffnungen (22) aufweist, durch welche im Betrieb mindestens ein Teil (7) besagten zweiten Mediums von der Kaltgasseite zur Heissgasseite strömt, dergestalt, dass die Ausblaseöffnungen ebenfalls als Wärmesenken wirken, und dass entlang mindestens einer Linie auf der Kaltgasseite jeweils mindestens ein Stift und mindestens eine Öffnung abwechselnd angeordnet sind.
- Kühlbares Bauteil nach Anspruch 1, dadurch gekennzeichnet, dass wenigstens eine Anzahl von abwechselnd angeordneten Stiften und Öffnungen in einer Flucht angeordnet sind.
- Kühlbares Bauteil nach Anspruch 1, dadurch gekennzeichnet, dass die Stifte aus einem Material bestehen, dessen Wärmeleitfähigkeit wenigstens den dreifachen Wert der Wärmeleitfähigkeit des Basismaterials aufweist.
- Kühlbares Bauteil nach Anspruch 1, dadurch gekennzeichnet, dass der Abstand zwischen zwei Wärmesenken (22, 23) kleiner als das achtfache des hydraulischen Durchmessers einer Ausblaseöffnung (22) ist.
- Kühlbares Bauteil nach Anspruch 1, dadurch gekennzeichnet, dass Öffnungen (22) und Stifte (23) annähernd identische Abstände voneinander haben.
- Kühlbares Bauteil nach Anspruch 1, dadurch gekennzeichnet, dass die Stifte zwischen 30% und 80% einer lokalen Materialstärke, in der Längsrichtung der Stifte gemessen, in des Basismaterial des Bauteils hineinragen.
- Kühlbares Bauteil nach Anspruch 1, dadurch gekennzeichnet, dass die Stifte wenigstens doppelt so weit in das zweite Medium hineinragen, wie es dem Mass entspricht, das sich aus der Wurzel der Querschnittsfläche des Stiftes an der Durchdringung mit der Kaltgasseite ergibt.
- Kühlbares Bauteil nach Anspruch 1, dadurch gekennzeichnet, dass auf der Kaltgasseite Mittel (25) angeordnet sind, die das Medium (7), das durch die Ausblaseöffnungen (22) strömt, über die Stifte (23) leitet.
- Kühlbares Bauteil nach Anspruch 1, dadurch gekennzeichnet, dass die Stifte parallel zu den Ausblaseöffnungen verlaufen.
- Kühlbares Bauteil nach Anspruch 1, dadurch gekennzeichnet, dass die Stifte in dem Bauteil eingegossen sind.
- Kühlbares Bauteil nach Anspruch 1, dadurch gekennzeichnet, dass das Bauteil ein Hohlkörper ist, wobei die Heissgasseite aussen und die Kaltgasseite innen liegt.
- Kühlbares Bauteil nach Anspruch 11, dadurch gekennzeichnet, dass das Bauteil eine Gasturbinenschaufel ist, und die Stifte (23) und Ausblaseöffnungen (22) entlang wenigstens einer Linie auf der Kaltgasseite (12) einer zur Gasturbinenschaufel gehörenden Schaufelplattform (3) angeordnet sind.
- Kühlbares Bauteil nach Anspruch 11, dadurch gekennzeichnet, dass das Bauteil eine Gasturbinenschaufel ist, dass die Ausblaseöffnungen (22) und Stifte (23) entlang einer zur Schaufel gehörenden Hinterkante (14) angeordnet sind, und dass die Stifte ins Innere (121) der Gasturbinenschaufel hineinragen.
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP04101493A EP1445423B1 (de) | 1999-04-21 | 1999-04-21 | Kühlbare Turbomaschinenschaufel |
EP99810329A EP1046784B1 (de) | 1999-04-21 | 1999-04-21 | Kühlbares Bauteil |
DE59910200T DE59910200D1 (de) | 1999-04-21 | 1999-04-21 | Kühlbares Bauteil |
US09/551,534 US6305904B1 (en) | 1999-04-21 | 2000-04-18 | Coolable component |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP99810329A EP1046784B1 (de) | 1999-04-21 | 1999-04-21 | Kühlbares Bauteil |
Related Child Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP04101493A Division EP1445423B1 (de) | 1999-04-21 | 1999-04-21 | Kühlbare Turbomaschinenschaufel |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1046784A1 true EP1046784A1 (de) | 2000-10-25 |
EP1046784B1 EP1046784B1 (de) | 2004-08-11 |
Family
ID=8242780
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP99810329A Expired - Lifetime EP1046784B1 (de) | 1999-04-21 | 1999-04-21 | Kühlbares Bauteil |
EP04101493A Expired - Lifetime EP1445423B1 (de) | 1999-04-21 | 1999-04-21 | Kühlbare Turbomaschinenschaufel |
Family Applications After (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP04101493A Expired - Lifetime EP1445423B1 (de) | 1999-04-21 | 1999-04-21 | Kühlbare Turbomaschinenschaufel |
Country Status (3)
Country | Link |
---|---|
US (1) | US6305904B1 (de) |
EP (2) | EP1046784B1 (de) |
DE (1) | DE59910200D1 (de) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2505789A1 (de) * | 2011-03-30 | 2012-10-03 | Techspace Aero S.A. | Gasflussabscheider mit Enteisungsvorrichtung über Wärmebrücke |
Families Citing this family (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1847684A1 (de) * | 2006-04-21 | 2007-10-24 | Siemens Aktiengesellschaft | Turbinenschaufel |
EP2426317A1 (de) * | 2010-09-03 | 2012-03-07 | Siemens Aktiengesellschaft | Turbinenschaufel für eine Gasturbine |
US10871075B2 (en) | 2015-10-27 | 2020-12-22 | Pratt & Whitney Canada Corp. | Cooling passages in a turbine component |
US10533749B2 (en) * | 2015-10-27 | 2020-01-14 | Pratt & Whitney Cananda Corp. | Effusion cooling holes |
US11333022B2 (en) * | 2019-08-06 | 2022-05-17 | General Electric Company | Airfoil with thermally conductive pins |
Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB624939A (en) * | 1946-07-12 | 1949-06-20 | Bbc Brown Boveri & Cie | Gas turbine combustion chamber |
US3527543A (en) | 1965-08-26 | 1970-09-08 | Gen Electric | Cooling of structural members particularly for gas turbine engines |
GB2117455A (en) * | 1982-03-26 | 1983-10-12 | Mtu Muenchen Gmbh | Axial flow turbine blade |
DE4430302A1 (de) | 1994-08-26 | 1996-02-29 | Abb Management Ag | Prallgekühltes Wandteil |
EP0750957A1 (de) * | 1995-06-07 | 1997-01-02 | Allison Engine Company, Inc. | Einstückig gegossene, hochtemperaturbeständige, dünnwandige Strukturen, deren Wände mit einem eingegossenen Verbindungselement höherer Wärmeleitfähigkeit verbunden sind |
DE19654115A1 (de) | 1996-12-23 | 1998-06-25 | Asea Brown Boveri | Vorrichtung zum Kühlen einer beidseitig umströmten Wand |
-
1999
- 1999-04-21 EP EP99810329A patent/EP1046784B1/de not_active Expired - Lifetime
- 1999-04-21 DE DE59910200T patent/DE59910200D1/de not_active Expired - Lifetime
- 1999-04-21 EP EP04101493A patent/EP1445423B1/de not_active Expired - Lifetime
-
2000
- 2000-04-18 US US09/551,534 patent/US6305904B1/en not_active Expired - Fee Related
Patent Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB624939A (en) * | 1946-07-12 | 1949-06-20 | Bbc Brown Boveri & Cie | Gas turbine combustion chamber |
US3527543A (en) | 1965-08-26 | 1970-09-08 | Gen Electric | Cooling of structural members particularly for gas turbine engines |
GB2117455A (en) * | 1982-03-26 | 1983-10-12 | Mtu Muenchen Gmbh | Axial flow turbine blade |
DE4430302A1 (de) | 1994-08-26 | 1996-02-29 | Abb Management Ag | Prallgekühltes Wandteil |
EP0750957A1 (de) * | 1995-06-07 | 1997-01-02 | Allison Engine Company, Inc. | Einstückig gegossene, hochtemperaturbeständige, dünnwandige Strukturen, deren Wände mit einem eingegossenen Verbindungselement höherer Wärmeleitfähigkeit verbunden sind |
DE19654115A1 (de) | 1996-12-23 | 1998-06-25 | Asea Brown Boveri | Vorrichtung zum Kühlen einer beidseitig umströmten Wand |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2505789A1 (de) * | 2011-03-30 | 2012-10-03 | Techspace Aero S.A. | Gasflussabscheider mit Enteisungsvorrichtung über Wärmebrücke |
US8899917B2 (en) | 2011-03-30 | 2014-12-02 | Techspace Aero S.A. | Gas flow separator with a thermal bridge de-icer |
RU2591068C2 (ru) * | 2011-03-30 | 2016-07-10 | Текспейс Аеро С.А. | Разделитель потока газа с устройством для предотвращения обледенения, содержащим тепловой мост |
Also Published As
Publication number | Publication date |
---|---|
EP1445423B1 (de) | 2006-08-02 |
US6305904B1 (en) | 2001-10-23 |
EP1445423A2 (de) | 2004-08-11 |
EP1046784B1 (de) | 2004-08-11 |
DE59910200D1 (de) | 2004-09-16 |
EP1445423A3 (de) | 2004-08-25 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP2087206B1 (de) | Turbinenschaufel | |
DE60031185T2 (de) | Methode zur Kühlung einer Wand einer Strömungsmaschinenschaufel | |
EP1309773B1 (de) | Anordnung von turbinenleitschaufeln | |
DE3248162C2 (de) | Kühlbare Schaufel | |
DE60213328T2 (de) | Gekühlte hohle Schaufelspitzenabdeckung einer Turbinenschaufel | |
DE60305385T2 (de) | Luftfilmgekühlter Mikrokreislauf und Bauteil und Herstellungsverfahren für ein solches Bauteil | |
DE3211139C1 (de) | Axialturbinenschaufel,insbesondere Axialturbinenlaufschaufel fuer Gasturbinentriebwerke | |
DE102011000878B4 (de) | Turbinenschaufel mit abgeschirmtem Kühlmittelzuführungskanal | |
EP1270873A2 (de) | Gasturbinenschaufel | |
EP0964981B1 (de) | Turbinenschaufel sowie deren verwendung in einer gasturbinenanlage | |
DE102006004437A1 (de) | Plattform einer Laufschaufel einer Gasturbine, Verfahren zur Herstellung einer Laufschaufel, Dichtungsplatte und Gasturbine | |
EP1267040A2 (de) | Gasturbinenschaufelblatt | |
EP1113145A1 (de) | Schaufel für Gasturbinen mit Drosselquerschnitt an Hinterkante | |
EP2087207B1 (de) | Turbinenschaufel | |
EP1188500A1 (de) | Vorrichtung und Verfahren zur Herstellung einer Schaufel für eine Turbine sowie entsprechend hergestellte Schaufel | |
EP1668236B1 (de) | Brennkammer mit kühleinrichtung und verfahren zur herstellung der brennkammer | |
EP3456923B1 (de) | Schaufel einer strömungsmaschine mit kühlkanal und darin angeordnetem verdrängungskörper sowie verfahren zur herstellung | |
EP2126286A1 (de) | Turbinenschaufel | |
EP1046784B1 (de) | Kühlbares Bauteil | |
EP0892150B1 (de) | Kühlsystem für den Hinterkantenbereich einer hohlen Gasturbinenschaufel | |
EP0954680B1 (de) | Turbinenschaufel sowie verwendung in einer gasturbinenanlage | |
EP3473808B1 (de) | Schaufelblatt für eine innengekühlte turbinenlaufschaufel sowie verfahren zur herstellung einer solchen | |
EP3263838A1 (de) | Turbinenschaufel mit innerem kühlkanal | |
EP0973998B1 (de) | Verfahren zur kühlung einer turbinenschaufel | |
EP3762586A1 (de) | Bauteilwand eines heissgasbauteils |
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: A1 Designated state(s): DE GB |
|
AX | Request for extension of the european patent |
Free format text: AL;LT;LV;MK;RO;SI |
|
17P | Request for examination filed |
Effective date: 20010407 |
|
RAP1 | Party data changed (applicant data changed or rights of an application transferred) |
Owner name: ALSTOM (SCHWEIZ) AG |
|
AKX | Designation fees paid |
Free format text: DE GB |
|
RAP1 | Party data changed (applicant data changed or rights of an application transferred) |
Owner name: ALSTOM (SWITZERLAND) LTD |
|
17Q | First examination report despatched |
Effective date: 20030722 |
|
GRAP | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOSNIGR1 |
|
RAP1 | Party data changed (applicant data changed or rights of an application transferred) |
Owner name: ALSTOM TECHNOLOGY LTD |
|
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 GB |
|
REG | Reference to a national code |
Ref country code: GB Ref legal event code: FG4D Free format text: NOT ENGLISH |
|
REF | Corresponds to: |
Ref document number: 59910200 Country of ref document: DE Date of ref document: 20040916 Kind code of ref document: P |
|
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: 20050512 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: DE Payment date: 20110429 Year of fee payment: 13 Ref country code: GB Payment date: 20110328 Year of fee payment: 13 |
|
GBPC | Gb: european patent ceased through non-payment of renewal fee |
Effective date: 20120421 |
|
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: 20120421 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R119 Ref document number: 59910200 Country of ref document: DE Effective date: 20121101 |
|
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: 20121101 |