EP0851095B1 - Internal cooling blade of a turbo-machine - Google Patents
Internal cooling blade of a turbo-machine Download PDFInfo
- Publication number
- EP0851095B1 EP0851095B1 EP97810917A EP97810917A EP0851095B1 EP 0851095 B1 EP0851095 B1 EP 0851095B1 EP 97810917 A EP97810917 A EP 97810917A EP 97810917 A EP97810917 A EP 97810917A EP 0851095 B1 EP0851095 B1 EP 0851095B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- pins
- wall
- coolant
- turbomachine blade
- narrow gap
- 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
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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
- F28—HEAT EXCHANGE IN GENERAL
- F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
- F28F1/00—Tubular elements; Assemblies of tubular elements
- F28F1/10—Tubular elements and assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with projections, with recesses
- F28F1/12—Tubular elements and assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with projections, with recesses the means being only outside the tubular element
- F28F1/124—Tubular elements and assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with projections, with recesses the means being only outside the tubular element and being formed of pins
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F28—HEAT EXCHANGE IN GENERAL
- F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
- F28F3/00—Plate-like or laminated elements; Assemblies of plate-like or laminated elements
- F28F3/02—Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations
- F28F3/022—Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations the means being wires or pins
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- 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
Definitions
- the invention relates to an internally cooled turbomachine blade, with a Wall (W), which on the outside of a hot medium and on your A coolant flows around the inner wall, as well as with, in the inner wall introduced thermal bridges in the form of high-melting pins (S) with high thermal conductivity in the space exposed to the coolant (E) protrude.
- W Wall
- S high-melting pins
- Such internally cooled turbomachine blades are for example those of gas turbines with axial flow.
- Hollow, internally cooled turbine blades with liquid, steam or air as Coolants are well known.
- a particular problem is the cooling of the The trailing edge of such blades represents that in a closed circle of the coolant are flowed through.
- the walls forming the rear edge include one Narrow gap from which the heat is to be removed.
- the narrow gap in its Width should not be less than a minimum value.
- the wall thickness may be a certain one for reasons of strength Do not fall short.
- the invention has for its object an internally cooled Turbomachine blade to develop such that the known Overheating problems on the rear edge of the turbine blade reduced or completely should be avoided without losing the fluid mechanical properties to influence the rear edge sustainably.
- the narrow gap that the trailing edge encloses can be improved.
- an internally cooled turbomachine blade with a wall which is surrounded by a hot medium on its outside and a coolant on its inside wall, and with thermal bridges introduced in the inside wall in the form of high-melting pins with high thermal conductivity, which in the from Project coolant-loaded space, developed such that the coolant-charged space is a closed narrow gap, which is formed by the rear edge of the turbomachine blade from which the pins protrude into the narrow gap, and that the wall at the rear edge encloses the melting pins with a constant wall thickness.
- the advantages of the invention include the simplicity of the measure see. If the wall to be cooled is a cast one Turbine blade, so the pins can be shed together with the blade become. The measure also allows the efficiency of the training Blade trailing edge.
- the cast blade shown in FIG. 1 has three inner chambers a, b, and c, through which a coolant, for example steam, flows, perpendicular to the plane of the drawing.
- a coolant for example steam
- the inside of the wall W forming the blade contour - which is surrounded by hot gases on the outside on both sides - is surrounded by the coolant and gives off its heat to the coolant.
- the coolant circulates in a closed circuit, which means that coolant is not blown out into the flow channel either on the front edge, the suction side, the pressure side or in the region of the rear edge. This results in the problem with the trailing edge geometry, which is explained with reference to FIG. 2.
- the narrow gap E formed by the walls must have a minimum size in order to be able to absorb enough coolant to dissipate the heat generated.
- the inner edge rounding must therefore be designed with the diameter d.
- a minimum wall thickness T cannot be undershot.
- the dimension L a therefore generally corresponds to the wall thickness T. All this means that the outer edge rounding must be carried out with a relatively large diameter D a . So far, cooled trailing edges are known.
- the invention seeks to remedy this. 3 are for better Heat dissipation in the wall around which the coolant flows Form of pins S arranged. These pins are attached so that they are in the from Coolant-loaded space, i.e. protrude into the narrow gap E.
- the thermal bridges are high-melting material. Because such internally cooled blades usually are cast, it is advisable to arrange the pins in the casting cores beforehand and integrally potting them with the shovel. This has the advantage that in this Area on the usual spacers in the form of quartz or aluminide struts can be dispensed with.
- pins are high Thermal conductivity to choose.
- This is a suitable material synthetic diamond.
- a synthetic diamond made of C-14 isotopes has shown thermal conductivity.
- the pins S are cylindrical. It goes without saying that too other geometries with larger exchange areas are possible, for example, pins that have a polygonal shape in cross section or are serrated are.
Description
Die Erfindung betrifft eine innengekühlte Turbomaschinenschaufel, mit einer Wandung (W), welche an ihrer Aussenseite von einem heissen Medium und an ihrer Innenwand von einem Kühlmittel umströmt ist, sowie mit, in der Innenwandung eingebrachten thermischen Brücken in Form von hochschmelzenden Stiften (S) mit hoher Wärmeleitfähigkeit, welche in den vom Kühlmittel beaufschlagten Raum (E) hineinragen.The invention relates to an internally cooled turbomachine blade, with a Wall (W), which on the outside of a hot medium and on your A coolant flows around the inner wall, as well as with, in the inner wall introduced thermal bridges in the form of high-melting pins (S) with high thermal conductivity in the space exposed to the coolant (E) protrude.
Derartige innengekühlte Turbomaschinenschaufel sind beispielsweise jene von axialdurchströmten Gasturbinen.Such internally cooled turbomachine blades are for example those of gas turbines with axial flow.
Hohle, innengekühlte Turbinenschaufeln mit Flüssigkeit, Dampf oder Luft als Kühlmittel sind hinlänglich bekannt. Ein Problem stellt insbesondere die Kühlung der Hinterkante von solchen Schaufeln dar, die im gechlossenen Kreis vom Kühlmittel durchströmt sind. Die die Hinterkante bildenden Wandungen umfassen einen Engspalt, aus dem die Wärme abzuführen ist. Hierzu darf der Engspalt in seiner Breite einen minimalen Wert nicht unterschreiten. Um eine Überhitzung der Hinterkante zu vermeiden, darf auch keine grossen Materialansamlungen vorhanden sein. Darüber hinaus darf die Wandstärke aus Festigkeitsgründen ein bestimmtes Mass nicht unterschreiten. Diese Vorgaben führen dazu, dass innengekühlte Schaufeln mit grossen Rundungsradien an der Hinterkante versehen sind, was sich ungünstig auf den Schaufelwirkungsgrad auswirkt.Hollow, internally cooled turbine blades with liquid, steam or air as Coolants are well known. A particular problem is the cooling of the The trailing edge of such blades represents that in a closed circle of the coolant are flowed through. The walls forming the rear edge include one Narrow gap from which the heat is to be removed. For this, the narrow gap in its Width should not be less than a minimum value. To overheat the To avoid trailing edges, there must also be no large accumulations of material his. In addition, the wall thickness may be a certain one for reasons of strength Do not fall short. These requirements result in internally cooled Buckets with large radii of curvature at the rear edge are what is adversely affects the blade efficiency.
In der DE 32 11 139 C1 ist eine Axialturbinenschaufel, insbesondere eine Axialturbinenlaufschaufel für Gasturbinentriebwerke beschrieben, bei der zu Zwecken einer verbesserten Kühlung der Nasenkante der Turbinenschaufel Stifte oder Drähte aus hoch-wärmeleitfähigen Material in die Nasenkantenzone integriert sind und dabei teilweise von der Kühlluft umspült werden. Sie dienen einem verbesserten Wärmeabfluß aus dem Material aus dem Axialturbinenschaufeln gefertigt sind. Zwar helfen diese Maßnahmen grundsätzlich einer verbesserten Kühlung, doch vermag die in der vorbeschriebenen Druckschrift beschriebene Lehre nicht das Problem an der Hinterkante zu lösen. Auch sind der Druckschrift keine Hinweise zu entnehmen derartige Stifte im Bereich der Hinterkante einer Turbinenschaufel einzusetzen.DE 32 11 139 C1 describes an axial turbine blade, in particular one Axial turbine blade for gas turbine engines described in the case of For improved cooling of the nose edge of the turbine blade pins or wires made of highly thermally conductive material integrated into the nose edge zone are and are partially washed around by the cooling air. They serve you improved heat dissipation from the material from the axial turbine blades are made. In principle, these measures help an improved one Cooling, but can do the teaching described in the above publication does not solve the problem at the rear edge. Also the publication is none Instructions for removing such pins in the area of the rear edge of a Use turbine blade.
Aus der US 5,348,446 geht eine Turbinenschaufel aus einem mehrschicht-Metallverbund hervor, um den Wärmeübergang durch die Turbinenschaufelwand zu verbessern. Die mit der Turbinenhinterkante verbundenen Probleme werden in dieser Druckschrift nicht genannt.No. 5,348,446 describes a turbine blade made of a multilayer metal composite to heat transfer through the turbine blade wall improve. The problems associated with the trailing edge of the turbine are in this Documentation not mentioned.
Aus der US 5,566,752 geht ein wärmeübertragendes Element hervor, das im Wesentlichen aus einem Hitze gut leitendem Material, wie bspw. Diamant-Material besteht.From US 5,566,752 a heat transfer element emerges, which in Essentially made of a material that is a good conductor of heat, such as diamond material consists.
Die Erfindung liegt die Aufgabe zugrunde, eine innengekühlte Turbomaschinenschaufel derart weiterzubilden, dass die bekannten Überhitzungsprobleme an der Hinterkante der Turbinenschaufel reduziert oder ganz vermieden werden sollen, ohne dabei die strömungsmechanischen Eigenschaften der Hinterkante nachhaltig zu beeinflussen. Insbesondere soll die Wärmeableitung aus dem Engspalt, den die Hinterkante einschließt verbessert werden.The invention has for its object an internally cooled Turbomachine blade to develop such that the known Overheating problems on the rear edge of the turbine blade reduced or completely should be avoided without losing the fluid mechanical properties to influence the rear edge sustainably. In particular, should the heat dissipation the narrow gap that the trailing edge encloses can be improved.
Erfindungsgemäss wird eine innengekühlte
Turbomaschinenschaufel, mit einer Wandung, welche an ihrer Aussenseite von
einem heissen Medium und an ihrer Innenwand von einem Kühlmittel umströmt ist,
sowie mit, in der Innenwandung eingebrachten thermischen Brücken in Form von
hochschmelzenden Stiften mit hoher Wärmeleitfähigkeit, welche in den vom
Kühlmittel beaufschlagten Raum hineinragen, derart weitergebildet, dass der vom
Kühlmittel beaufschlagte Raum ein geschlossener Engspalt ist, der von der
Hinterkante der Turbomaschinenschaufel gebildet ist, von der aus die Stifte in den
Engspalt hineinragen, und
dass die Wandung an der Hinterkante mit gleichbleibender Wandstärke die
hochschmelzenden Stifte umschließt.According to the invention, an internally cooled turbomachine blade, with a wall which is surrounded by a hot medium on its outside and a coolant on its inside wall, and with thermal bridges introduced in the inside wall in the form of high-melting pins with high thermal conductivity, which in the from Project coolant-loaded space, developed such that the coolant-charged space is a closed narrow gap, which is formed by the rear edge of the turbomachine blade from which the pins protrude into the narrow gap, and
that the wall at the rear edge encloses the melting pins with a constant wall thickness.
Die Vorteile der Erfindung sind unter anderem in der Einfachheit der Massnahme zu sehen. Handelt es sich bei der zu kühlenden Wand um eine gegossene Turbinenschaufel, so können die Stifte zusammen mit der Schaufel vergossen werden. Die Massnahme erlaubt zudem eine wirkungsgradgünstige Ausbildung der Schaufelhinterkante.The advantages of the invention include the simplicity of the measure see. If the wall to be cooled is a cast one Turbine blade, so the pins can be shed together with the blade become. The measure also allows the efficiency of the training Blade trailing edge.
In der Zeichnung ist ein Ausführungsbeispiel der Erfindung anhand einer innengekühlten Gasturbinenschaufel dargestellt. Es zeigen:
- Fig. 1
- eine Schaufel im Querschnitt;
- Fig. 2
- das Detail z aus Fig. 1 mit einer zum Stand der Technik zählenden Hinterkante,
- Fig. 3
- das Detail z aus Fig. 1 mit einer erfindungsgemässen Hinterkante,
- Fig. 4
- einen Längsschnitt durch den Hinterkantenbereich einer Schaufel.
- Fig. 1
- a blade in cross section;
- Fig. 2
- the detail z from FIG. 1 with a trailing edge which is part of the prior art,
- Fig. 3
- the detail z from FIG. 1 with a trailing edge according to the invention,
- Fig. 4
- a longitudinal section through the rear edge area of a blade.
Es sind nur die für das Verständnis der Erfindung wesentlichen Elemente gezeigt. Die Strömungsrichtung der beteiligten Medien ist mit Pfeilen bezeichnet.Only the elements essential for understanding the invention are shown. The direction of flow of the media involved is indicated by arrows.
Die in Fig. 1 dargestellte, gegossene Schaufel weist drei Innenkammern a, b, und c
auf, die von einem Kühlmittel, beispielsweise Dampf, senkrecht zur
Zeichnungsebene durchströmt sind. Dabei werden die Innenseiten der die
Schaufelkontur bildenden Wand W - die aussen beidseitig von heissen Gasen
umströmt ist - vom Kühlmittel umströmt und geben ihre Wärme an das Kühlmittel ab.
Es versteht sich, dass zumindest in den zwei vorderen Kammern a, b zahlreiche
nicht gezeigte Hilfsmittel wie Leitrippen, Strömungskanäle, Einsätze für Prallkühlung
und dergleichen zur Verbesserung der Wandkühlung vorgesehen sein können. Im
Beispielsfall zirkuliert das Kühlmittel im geschlossenen Kreis, worunter verstanden
wird, dass weder an der Vorderkante, der Saugseite, der Druckseite noch im Bereich
der Hinterkante ein Ausblasen von Kühlmittel in den Strömungskanal erfolgt.
Hieraus ergibt sich die Problematik mit der Hinterkantengeometrie, welche anhand
der Fig. 2 erläutert ist.The cast blade shown in FIG. 1 has three inner chambers a, b, and c, through which a coolant, for example steam, flows, perpendicular to the plane of the drawing. The inside of the wall W forming the blade contour - which is surrounded by hot gases on the outside on both sides - is surrounded by the coolant and gives off its heat to the coolant. It goes without saying that at least in the two front chambers a, b numerous aids, not shown, such as guide ribs, flow channels, inserts for impingement cooling and the like can be provided to improve the wall cooling. In the example, the coolant circulates in a closed circuit, which means that coolant is not blown out into the flow channel either on the front edge, the suction side, the pressure side or in the region of the rear edge.
This results in the problem with the trailing edge geometry, which is explained with reference to FIG. 2.
Der von den Wänden gebildete Engspalt E muss eine minimale Grösse haben, um genügend Kühlmittel zur Abfuhr der anfallenden Wärme aufnehmen zu können. Die innere Kantenabrundung ist deshalb mit dem Durchmesser d auszubilden. Aus Festigkeitsgründen kann eine minimale Wandstärke T nicht unterschritten werden. Um eine Überhitzung der Hinterkante zu vermeiden, darf es dort zu keiner grossen Materialansammlung kommen. Das Mass La entspricht demnach in der Regel der Wandstärke T. All dies führt dazu, dass die äussere Kantenabrundung mit einem relativ grossen Durchmesser Da auszuführen ist. Soweit sind gekühlte Hinterkanten bekannt.The narrow gap E formed by the walls must have a minimum size in order to be able to absorb enough coolant to dissipate the heat generated. The inner edge rounding must therefore be designed with the diameter d. For reasons of strength, a minimum wall thickness T cannot be undershot. In order to avoid overheating the rear edge, there must be no large accumulation of material there. The dimension L a therefore generally corresponds to the wall thickness T. All this means that the outer edge rounding must be carried out with a relatively large diameter D a . So far, cooled trailing edges are known.
Hier will die Erfindung Abhilfe schaffen. Gemäss Fig. 3 werden zur besseren Wärmeabfuhr in der vom Kühlmittel umströmten Wandung thermische Brücken in Form von Stiften S angeordnet. Diese Stifte sind so angebracht, dass sie in den vom Kühlmittel beaufschlagten Raum, d.h. in den Engspalt E hineinragen.The invention seeks to remedy this. 3 are for better Heat dissipation in the wall around which the coolant flows Form of pins S arranged. These pins are attached so that they are in the from Coolant-loaded space, i.e. protrude into the narrow gap E.
Aus Herstellungsgründen handelt es sich bei den thermischen Brücken um hochschmelzendes Material. Da solche innengekühlten Schaufeln in der Regel gegossen sind, bietet es sich an, die Stifte vorab in den Giesskernen anzuordnen und sie mit der Schaufel integral zu vergiessen. Dies hat den Vorteil, dass in diesem Bereich auf die üblichen Distanzstücke in Form von Quarz oder Aluminidstreben verzichtet werden kann.For manufacturing reasons, the thermal bridges are high-melting material. Because such internally cooled blades usually are cast, it is advisable to arrange the pins in the casting cores beforehand and integrally potting them with the shovel. This has the advantage that in this Area on the usual spacers in the form of quartz or aluminide struts can be dispensed with.
Aus der Fig. 3 ist ersichtlich, dass - bei gleichbleibender Wandstärke T und gleichbleibender innerer Kantenabrundung d - auf diese Weise eine grössere Materialansammlung mit dem Mass Ln, an der Hinterkante ermöglicht wird. Dies erlaubt wiederum die Ausbildung einer wesentlich schärferen Hinterkante, was sich durch den kleineren Durchmesser D, der Kantenabrundung auszeichnet.From Fig. 3 it can be seen that - with constant wall thickness T and constant inner edge rounding d - in this way a larger material accumulation with the dimension L n is made possible at the rear edge. This in turn allows the formation of a much sharper trailing edge, which is characterized by the smaller diameter D, the rounded edges.
Um die gewünschte Wärmeabfuhr zu gewährleisten, sind Stifte mit hoher Wärmeleitfähigkeit zu wählen. Hierzu bietet sich als geeignetes Material synthetischer Diamant an. Als ganz besonders vorteilhaft hinsichtlich Wärmeleitfähigkeit hat sich ein synthetischer Diamant aus C-14 Isotopen gezeigt.To ensure the desired heat dissipation, pins are high Thermal conductivity to choose. This is a suitable material synthetic diamond. As very particularly advantageous in terms of A synthetic diamond made of C-14 isotopes has shown thermal conductivity.
Im Beispielsfall sind die Stifte S zylindrisch ausgeführt. Es versteht sich, dass auch andere Geometrien, die grössere Austauschflächen aufweisen, möglich sind, beispielsweise Stifte, die im Querschnitt eine Vieleckform aufweisen oder gezahnt sind. In the example, the pins S are cylindrical. It goes without saying that too other geometries with larger exchange areas are possible, for example, pins that have a polygonal shape in cross section or are serrated are.
Bei gegebenen Bedingungen, d.h. Geometrie und Wandstärke der Hinterkante; Geometrie des vom Kühlmittel zu durchströmenden Engspaltes E; Wärmebelastung der Schaufelhinterkante; Art, Temperatur und Strömungsgeschwindigkeit des Kühlmittels, sind die Wärmeleitfähigkeit des gewählten Stiftmaterials sowie die in den durchströmten Engspalt hineinragenden Austauschflächen massgebend für die Anzahl der zu verwendenden Stifte über der Schaufelhöhe.Given conditions, i.e. Geometry and wall thickness of the rear edge; Geometry of the narrow gap E to be flowed through by the coolant; heat stress the trailing edge of the blade; Type, temperature and flow rate of the Coolant, are the thermal conductivity of the selected pin material as well as in the through the narrow gap protruding exchange areas decisive for the Number of pens to be used above the bucket height.
Gemäss Fig. 4 ist in einem Längsschnitt durch die hintere Kammer c eine solche gestaffelte regelmässige Anordnung von Stiften in der Radialen über der Schaufelhöhe, d.h. die Länge der Hinterkante der Turbinenschaufel, gezeigt. Je nach Wärmebelastung über der Schaufelhöhe kann selbstverständlich auch eine ungleiche Teilung zur Anwendung gelangen oder bei gleicher Teilung können Stifte mit unterschiedlichen Wärmetauschflächen vorgesehen werden. 4 is a longitudinal section through the rear chamber c staggered regular arrangement of pins in the radial over the Bucket height, i.e. the length of the trailing edge of the turbine blade. Depending on Thermal stress above the bucket height can of course also be an uneven one Pitch can be used or pens with the same pitch different heat exchange surfaces can be provided.
- a,b,cABC
- Innenkammern der SchaufelInner chambers of the shovel
- WW
- zu kühlende Wandwall to be cooled
- Ee
- Engspaltnarrow gap
- LL
- Länge der MaterialansammlungLength of material accumulation
- TT
- WandstärkeWall thickness
- dd
- innere Kantenabrundunginner edge rounding
- DD
- äussere Kantenabrundungouter edge rounding
- SS
- Kühlstiftcooling pin
Claims (4)
- Internally cooled turbomachine blade, having a wall (W) around which a hot medium flows on its outer side and a coolant flows on its inner wall, and having thermal bridges which are introduced in the inner wall and are in the form of refractory pins (S) of high thermal conductivity, which pins project into the space (E) upon which the coolant acts, characterized in that the space (E) upon which the coolant acts is a closed narrow gap (E) which is formed by the trailing edge of the turbomachine blade, from which the pins (S) project into the narrow gap, and in that the wall (W) surrounds the refractory pins (S) at the trailing edge with a constant wall thickness (T).
- Internally cooled turbomachine blade according to Claim 1, characterized in that the pins (S) are made of synthetic diamond of C-14 isotopes.
- Internally cooled turbomachine blade according to Claim 1, characterized in that the pins (S) are cast together with the wall (W).
- Internally cooled turbomachine blade according to Claim 1, characterized in that the narrow gap (E) extends at least approximately over the entire height of the turbomachine blade, and in that a plurality of pins are arranged distributed over the height.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE19654115 | 1996-12-23 | ||
| DE19654115A DE19654115A1 (en) | 1996-12-23 | 1996-12-23 | Device for cooling a wall on both sides |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| EP0851095A1 EP0851095A1 (en) | 1998-07-01 |
| EP0851095B1 true EP0851095B1 (en) | 2002-09-25 |
Family
ID=7816083
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP97810917A Expired - Lifetime EP0851095B1 (en) | 1996-12-23 | 1997-11-27 | Internal cooling blade of a turbo-machine |
Country Status (4)
| Country | Link |
|---|---|
| EP (1) | EP0851095B1 (en) |
| JP (1) | JPH10196304A (en) |
| CN (1) | CN1186151A (en) |
| DE (2) | DE19654115A1 (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE59910200D1 (en) | 1999-04-21 | 2004-09-16 | Alstom Technology Ltd Baden | Coolable component |
| DE19926817A1 (en) * | 1999-06-12 | 2000-12-14 | Abb Research Ltd | Turbine component, especially blade, has elements with very good heat conducting qualities integrated into blade so that they partially or completely intersperse blade in direction of greatest temperature gradients |
| GB0008897D0 (en) | 2000-04-12 | 2000-05-31 | Cheiros Technology Ltd | Improvements relating to heat transfer |
| US11333022B2 (en) * | 2019-08-06 | 2022-05-17 | General Electric Company | Airfoil with thermally conductive pins |
Family Cites Families (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE559676C (en) * | 1931-08-20 | 1932-09-22 | E H Hans Holzwarth Dr Ing | Method for cooling blades, in particular for internal combustion turbines |
| GB2087065B (en) * | 1980-11-08 | 1984-11-07 | Rolls Royce | Wall structure for a combustion chamber |
| DE3211139C1 (en) * | 1982-03-26 | 1983-08-11 | MTU Motoren- und Turbinen-Union München GmbH, 8000 München | Axial turbine blades, in particular axial turbine blades for gas turbine engines |
| GB8607526D0 (en) * | 1986-03-26 | 1986-04-30 | Artus R G C | Cooled component assembly |
| US5810552A (en) * | 1992-02-18 | 1998-09-22 | Allison Engine Company, Inc. | Single-cast, high-temperature, thin wall structures having a high thermal conductivity member connecting the walls and methods of making the same |
| US5348446A (en) * | 1993-04-28 | 1994-09-20 | General Electric Company | Bimetallic turbine airfoil |
| FR2714254B1 (en) * | 1993-12-20 | 1996-03-08 | Aerospatiale | Heat transfer element, usable in particular in electronics as a printed circuit or component support and its manufacturing process. |
| US5566752A (en) * | 1994-10-20 | 1996-10-22 | Lockheed Fort Worth Company | High heat density transfer device |
| US5536143A (en) * | 1995-03-31 | 1996-07-16 | General Electric Co. | Closed circuit steam cooled bucket |
-
1996
- 1996-12-23 DE DE19654115A patent/DE19654115A1/en not_active Ceased
-
1997
- 1997-11-27 DE DE59708321T patent/DE59708321D1/en not_active Expired - Fee Related
- 1997-11-27 EP EP97810917A patent/EP0851095B1/en not_active Expired - Lifetime
- 1997-12-22 JP JP9353641A patent/JPH10196304A/en active Pending
- 1997-12-22 CN CN97125588A patent/CN1186151A/en active Pending
Also Published As
| Publication number | Publication date |
|---|---|
| EP0851095A1 (en) | 1998-07-01 |
| CN1186151A (en) | 1998-07-01 |
| DE19654115A1 (en) | 1998-06-25 |
| JPH10196304A (en) | 1998-07-28 |
| DE59708321D1 (en) | 2002-10-31 |
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