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EP0851095A1 - Cooling device for a wall - Google Patents

Cooling device for a wall Download PDF

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Publication number
EP0851095A1
EP0851095A1 EP97810917A EP97810917A EP0851095A1 EP 0851095 A1 EP0851095 A1 EP 0851095A1 EP 97810917 A EP97810917 A EP 97810917A EP 97810917 A EP97810917 A EP 97810917A EP 0851095 A1 EP0851095 A1 EP 0851095A1
Authority
EP
European Patent Office
Prior art keywords
wall
coolant
pins
narrow gap
cooled
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
Application number
EP97810917A
Other languages
German (de)
French (fr)
Other versions
EP0851095B1 (en
Inventor
Kenneth Hall
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Switzerland GmbH
Original Assignee
ABB Asea Brown Boveri Ltd
Asea Brown Boveri AB
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by ABB Asea Brown Boveri Ltd, Asea Brown Boveri AB filed Critical ABB Asea Brown Boveri Ltd
Publication of EP0851095A1 publication Critical patent/EP0851095A1/en
Application granted granted Critical
Publication of EP0851095B1 publication Critical patent/EP0851095B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • 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 a device for cooling a Wall, which is on the outside of a hot medium and a coolant flows around its inner wall.
  • Such walls to be cooled are, for example, the internally cooled ones Turbomachinery blades, especially those from axial flow gas turbines.
  • Hollow, internally cooled turbine blades with liquid, steam or air as a coolant are well known.
  • a problem provides in particular the cooling of the rear edge of such blades, which are in a closed circle from the coolant are flowed through.
  • the walls forming the rear edge include a narrow gap from which the heat is to be removed.
  • the narrow gap may have a minimal width Do not fall below the value.
  • To overheat the rear edge avoiding large amounts of material to be available.
  • the wall thickness is allowed For reasons of strength, do not fall below a certain level.
  • the invention has for its object on a cooled Wall to create a device that dissipates heat especially improved from a narrow gap.
  • the advantages of the invention include simplicity to see the measure. Is it the one to be cooled? Wall around a cast turbine blade, so the Pins are shed together with the shovel. The measure also allows an efficient training of Blade trailing edge.
  • the cast blade shown in Fig. 1 has three Inner chambers a, b, and c, which are surrounded by a coolant, for example steam, flows perpendicular to the plane of the drawing are. In doing so, the inside of the blade contour forming wall W - the outside on both sides of hot Gases flows around - flows around the coolant and give their Heat to the coolant. It is understood that at least numerous, not shown, in the two front chambers a, b Aids such as guide ribs, flow channels, inserts for Impingement cooling and the like to improve wall cooling can be provided.
  • the coolant circulates in a closed circle, which means that neither on the front edge, the suction side, the pressure side nor blowing out coolant in the area of the rear edge the flow channel takes place.
  • the gap E formed by the walls must have a minimum size in order to be able to absorb sufficient 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 of 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 used for better heat dissipation in the coolant flowed around the wall thermal bridges in the form of pins S arranged. These pins are attached so that they fit into the space exposed to the coolant, i.e. in the narrow gap E protrude into it.
  • Pins are used to ensure the desired heat dissipation to choose with high thermal conductivity.
  • This offers itself synthetic diamond as a suitable material.
  • a synthetic diamond from C-14 isotopes has been shown.
  • the pins S are cylindrical. It it goes without saying that other geometries, the larger exchange areas have, are possible, for example pens, which have a polygonal shape or toothed in cross section are.

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  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Thermal Sciences (AREA)
  • Geometry (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

A gas turbine blade (W) cooling device has an external flow of hot medium, and an internal coolant flow and involves thermal bridging. This is formed by pegs (S) of material melting at a high temperature, and having higher thermal conductivity than the wall. These project internally into the coolant flow. Preferably the pegs are made of synthetic diamond, made using the C-14 isotope. They are cast into the wall. The space cooled is the closed narrow gap (E) at the rear edge of an internally-cooled gas turbine. The gap and line of pegs, extend over the length of the blade.

Description

Technisches GebietTechnical field

Die Erfindung betrifft eine Vorrichtung zum Kühlen einer Wand, welche an ihrer Ausssenseite von einem heissen Medium und an ihrer Innenwand von einem Kühlmittel umströmt ist.The invention relates to a device for cooling a Wall, which is on the outside of a hot medium and a coolant flows around its inner wall.

Derartige zu kühlende Wände sind beispielsweise die innengekühlten Schaufeln von Turbomaschinen, besonders jene von axialdurchströmten Gasturbinen.Such walls to be cooled are, for example, the internally cooled ones Turbomachinery blades, especially those from axial flow gas turbines.

Stand der TechnikState of the art

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. Darüberhinaus darf die Wandstärke aus Festigkeitsgründen ein bestimmtes Mass nicht ünterschreiten. 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 a coolant are well known. A problem provides in particular the cooling of the rear edge of such blades, which are in a closed circle from the coolant are flowed through. The walls forming the rear edge include a narrow gap from which the heat is to be removed. For this purpose, the narrow gap may have a minimal width Do not fall below the value. To overheat the rear edge avoiding large amounts of material to be available. In addition, the wall thickness is allowed For reasons of strength, do not fall below a certain level. These requirements result in internally cooled blades large rounding radii at the rear edge are what adversely affects blade efficiency.

Darstellung der ErfindungPresentation of the invention

Die Erfindung liegt die Aufgabe zugrunde, an einer gekühlten Wand eine Vorrichtung zu schaffen, die die Wärmeableitung insbesondere aus einem Engspalt verbessert.The invention has for its object on a cooled Wall to create a device that dissipates heat especially improved from a narrow gap.

Erfindungsgemäss wird dies dadurch erreicht, dass in der vom Kühlmittel umströmten Wandung thermische Brücken in Form von hochschmelzenden Stiften mit hoher Wärmeleitfähigkeit angeordnet sind, welche in den vom Kühlmittel beaufschlagten Raum hineinragen.According to the invention this is achieved in that in the Coolant flowing around thermal bridges in the form of wall high-melting pins arranged with high thermal conductivity are in the space exposed to the coolant protrude into it.

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 simplicity to see the measure. Is it the one to be cooled? Wall around a cast turbine blade, so the Pins are shed together with the shovel. The measure also allows an efficient training of Blade trailing edge.

Kurze Beschreibung der ZeichnungBrief description of the drawing

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.
Es sind nur die für das Verständnis der Erfindung wesentlichen Elemente gezeigt. Die Strömungsrichtung der beteiligten Medien ist mit Pfeilen bezeichnet.In the drawing, an embodiment of the invention is shown using an internally cooled gas turbine blade. Show it:
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.
Only the elements essential for understanding the invention are shown. The direction of flow of the media involved is indicated by arrows.

Weg zur Ausführung der ErfindungWay of carrying out the invention

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.The cast blade shown in Fig. 1 has three Inner chambers a, b, and c, which are surrounded by a coolant, for example steam, flows perpendicular to the plane of the drawing are. In doing so, the inside of the blade contour forming wall W - the outside on both sides of hot Gases flows around - flows around the coolant and give their Heat to the coolant. It is understood that at least numerous, not shown, in the two front chambers a, b Aids such as guide ribs, flow channels, inserts for Impingement cooling and the like to improve wall cooling can be provided. In the example, the coolant circulates in a closed circle, which means that neither on the front edge, the suction side, the pressure side nor blowing out coolant in the area of the rear edge the flow channel takes place.

Hieraus ergibt sich die Problematik mit der Hinterkantengeometrie, welche anhand der Fig. 2 erläutert ist. Der von den Wänden gebildete Enspalt 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. This results in the problem with the trailing edge geometry, which is explained with reference to FIG. 2. The gap E formed by the walls must have a minimum size in order to be able to absorb sufficient 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 of 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 used for better heat dissipation in the coolant flowed around the wall thermal bridges in the form of pins S arranged. These pins are attached so that they fit into the space exposed to the coolant, i.e. in the narrow gap E protrude into it.

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, it is thermal Bridges around high-melting material. Because such internally cooled Blades are usually cast, it lends itself arrange the pins in advance in the casting cores and use them to shed the shovel integrally. This has the advantage that in this area to form the usual spacers 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 Dn der Kantenabrundung auszeichnet.From Fig. 3 it can be seen that - with constant wall thickness T and constant inner edge rounding d - a larger material accumulation with the dimension L n at the rear edge is made possible in this way. This in turn allows the formation of a much sharper trailing edge, which is characterized by the smaller diameter D n of 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.Pins are used to ensure the desired heat dissipation to choose with high thermal conductivity. This offers itself synthetic diamond as a suitable material. As a whole has particularly advantageous in terms of thermal conductivity a synthetic diamond from C-14 isotopes has been shown.

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 it goes without saying that other geometries, the larger exchange areas have, are possible, for example pens, which have a polygonal shape or toothed in cross section 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 Trailing edge; Geometry of the coolant to flow through Narrow gap E; Thermal load on the trailing edge of the blade; Kind, Temperature and flow rate of the coolant - are the thermal conductivity of the selected pin material as well as the exchange areas protruding into the narrow gap decisive for the number of used Pins 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 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 such a staggered regular arrangement of Pins shown in the radial above the blade height. Each after heat stress above the bucket height can of course an unequal division can also be used or with the same pitch, pens with different Heat exchange surfaces are provided.

Es versteht sich, dass die Erfindung nicht auf das gezeigte und beschriebene Beispiel beschränkt ist. In Abweichung zur gezeigten Hinterkantenkühlung könnten selbstvertändlich auch andere Schaufelpartien auf die neue Art gekühlt werden und zwar überall dort, wo sich Probleme mit grossen Materialansammlungen stellen, von denen Wärme abzuführen ist, z.B. im Bereich der Schaufelfüsse oder der Schaufelspitzen. Im übrigen ist die Erfindung keineswegs auf Schaufeln oder Engspalte beschränkt, sondern kann bei allen umströmten und zu kühlenden Elementen angewendet werden,It is understood that the invention is not limited to that shown and described example is limited. In deviation from trailing edge cooling shown could of course also other blade sections are cooled in the new way and wherever there are problems with large material accumulations places from which heat is to be removed, e.g. in the Area of the blade roots or the blade tips. Furthermore the invention is by no means on blades or narrow gaps limited, but can with all flow and to be cooled Elements are applied

BezugszeichenlisteReference list

a,b,cABC
Innenkammern derSchaufelInner chambers of the blade
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
äusseere Kantenabrundungouter edge rounding
SS
KühlstiftCooling pin

Claims (6)

Vorrichtung zum Kühlen einer Wand (W), welche an ihrer Ausssenseite von einem heissen Medium und an ihrer Innenwand von einem Kühlmittel umströmt ist, dadurch gekennzeichnet, dass in der vom Kühlmittel umströmten Wandung thermische Brücken in Form von hochschmelzenden Stiften (S) mit hoher Wärmeleitfähigkeit angeordnet sind, welche in den vom Kühlmittel beaufschlagten Raum (E) hineinragen.Device for cooling a wall (W), which on its Outside of a hot medium and on hers A coolant flows around the inner wall, characterized in that in the coolant flowed around the wall thermal bridges in the form of high-melting Pins (S) with high thermal conductivity are arranged, which in the acted upon by the coolant Protrude into room (E). Vorrichtung nach Anspruch 1, dadurch gekennzeichnet, dass die Stifte (S) aus synthetischem Diamant aus C-14 Isotopen bestehen.Device according to claim 1, characterized in that the pins (S) made of synthetic diamond from C-14 Isotopes exist. Vorrichtung nach Anspruch 1, dadurch gekennzeichnet, dass die Stifte (S) mit der Wand (W) zusammen vergossen sind.Device according to claim 1, characterized in that the pins (S) shed together with the wall (W) are. Vorrichtung nach Anspruch 1, dadurch gekennzeichnet, dass der vom Kühlmittel beaufschlagte Raum ein geschlossener Engspalt (E) ist, der zumindest teilweise von der zu kühlenden Wand (W) selbst gebildet ist.Device according to claim 1, characterized in that the space exposed to the coolant is a closed one Narrow gap (E) is at least partially from the wall (W) to be cooled itself is formed. Vorrichtung nach Anspruch 4, dadurch gekennzeichnet, dass der Engspalt (E) von der Hinterkante einer innengekühlten Turbomaschinenschaufel gebildet ist.Device according to claim 4, characterized in that the narrow gap (E) from the trailing edge of an internally cooled Turbomachine blade is formed. Vorrichtung nach Anspruch 5, dadurch gekennzeichnet, dass der Engspalt (E) sich zumindest annähernd über die ganze Höhe der Turbomaschinenschaufel erstreckt und dass eine Mehrzahl von Stiften über der Höhe verteilt angeordnet ist.Device according to claim 5, characterized in that the narrow gap (E) is at least approximately over the entire height of the turbomachine blade extends and that a plurality of pins are arranged distributed over the height is.
EP97810917A 1996-12-23 1997-11-27 Internal cooling blade of a turbo-machine Expired - Lifetime EP0851095B1 (en)

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 true EP0851095A1 (en) 1998-07-01
EP0851095B1 EP0851095B1 (en) 2002-09-25

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EP97810917A Expired - Lifetime EP0851095B1 (en) 1996-12-23 1997-11-27 Internal cooling blade of a turbo-machine

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Country Link
EP (1) EP0851095B1 (en)
JP (1) JPH10196304A (en)
CN (1) CN1186151A (en)
DE (2) DE19654115A1 (en)

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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

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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
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EP0750957A1 (en) * 1995-06-07 1997-01-02 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

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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
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
EP0239322A2 (en) * 1986-03-26 1987-09-30 Raymonde Gene Clifford Artus Cooled component assembly
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Also Published As

Publication number Publication date
EP0851095B1 (en) 2002-09-25
DE19654115A1 (en) 1998-06-25
CN1186151A (en) 1998-07-01
DE59708321D1 (en) 2002-10-31
JPH10196304A (en) 1998-07-28

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