EP1266127A1 - Cooling system for a turbine blade - Google Patents

Cooling system for a turbine blade

Info

Publication number
EP1266127A1
EP1266127A1 EP01919384A EP01919384A EP1266127A1 EP 1266127 A1 EP1266127 A1 EP 1266127A1 EP 01919384 A EP01919384 A EP 01919384A EP 01919384 A EP01919384 A EP 01919384A EP 1266127 A1 EP1266127 A1 EP 1266127A1
Authority
EP
European Patent Office
Prior art keywords
insert
blade
horizontal ribs
wall
cooling fluid
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
EP01919384A
Other languages
German (de)
French (fr)
Other versions
EP1266127B1 (en
Inventor
Peter Tiemann
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.)
Siemens AG
Original Assignee
Siemens AG
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 Siemens AG filed Critical Siemens AG
Priority to EP01919384A priority Critical patent/EP1266127B1/en
Publication of EP1266127A1 publication Critical patent/EP1266127A1/en
Application granted granted Critical
Publication of EP1266127B1 publication Critical patent/EP1266127B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

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
    • F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
    • F01D5/189—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall the insert having a tubular cross-section, e.g. airfoil shape
    • 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
    • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2212—Improvement of heat transfer by creating turbulence
    • 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
    • F05D2260/22141—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs

Definitions

  • the invention relates to a blade, in particular a turbine blade, with at least one channel which is delimited by walls, wherein an insert which can be acted upon by a cooling fluid is inserted into at least one channel.
  • Chambers are formed between the insert and the walls of the blade, which run in the direction of a longitudinal axis of the blade.
  • the cooling fluid enters the chamber from the insert and impacts the walls of the blade. It then flows along the walls and exits through specially designed chambers on the outside of the walls and from there the surroundings.
  • the effect of convection cooling when the cooling fluid flows along the walls is only slight, since the flow length is very limited. Mixing of the cooling fluid also occurs in the chambers along the longitudinal axis of the blade, so that targeted cooling is not possible.
  • Blades with partially hollow walls through which a cooling fluid flows. Due to the reduction in the wall thickness in the area of the hollow chambers, a high cooling efficiency is achieved. However, blades with such hollow walls require a complicated casting process with high reject rates and are therefore very expensive.
  • the object of the present invention is therefore to provide a blade which, with simple manufacture, achieves an improvement in the cooling effect.
  • this object is achieved in a shovel of the type mentioned in the introduction in that at least one of the walls is provided with a number of horizontal ribs which are arranged between the insert and the wall, and in that the insert is provided with openings through which the
  • Cooling fluid from the insert can enter between the horizontal ribs.
  • the horizontal ribs guide the coolant along the wall of the blade and prevent the coolant from flowing
  • the insert touches the horizontal ribs.
  • the insert is clipped and aligned in the desired position.
  • the horizontal ribs, the insert and the wall form the chambers through which the cooling fluid flows.
  • the chambers reliably prevent the cooling fluid from flowing in the direction of the longitudinal axis of the blade.
  • the cooling effect along the longitudinal axis of the blade can be varied in a targeted manner by applying the cooling fluid to the chambers differently.
  • the openings of the insert are at a first end of the chambers and exit openings for the cooling fluid m the wall are arranged at a second end of the chambers.
  • the cooling fluid therefore flows along the entire length of the chamber along the wall to be cooled, so that the convection cooling is further improved.
  • the horizontal ribs can be arranged essentially perpendicular to the longitudinal axis of the blade.
  • an angular position can be provided. With a vertical arrangement with respect to the longitudinal axis, the length of the horizontal ribs and thus the chambers is minimized. The angular position enables the length of the chambers to be increased and thus further improved convection cooling.
  • the insert is advantageously closed at one end.
  • the cooling fluid is only supplied from the other end of the insert.
  • the cooling fluid is prevented from escaping through the end facing away from the supply side, so that the cooling efficiency is increased.
  • cooling fluid can be supplied from both ends.
  • the turbulators serve to stiffen the wall and merge into one another and m the horizontal ribs. This results in a significant increase in rigidity without additional material. With the same strength of the blade, the wall thickness can be reduced again. At the same time, good heat exchange between the walls and the cooling fluid is achieved. This results in high cow efficiency and high overall efficiency.
  • the stiffening of the wall does not only occur in the area of a single turbulator. Rather, a large-area stiffening is provided by connecting the turbulators to one another.
  • the turbulators are advantageously straight. The use of straight turbulators enables high rigidity with simple manufacture.
  • the turbulators are arranged such that, together with the horizontal ribs, they form mutually adjacent recesses in the form of polygons, in particular triangles or rhombuses.
  • the inside of the wall is provided with a honeycomb structure.
  • the individual polygons or honeycombs each form a closed, highly resilient cross-section and support each other. A substantial increase in rigidity can be achieved.
  • the wall thickness of the wall is reduced at least in the area between the turbulators. This reduction in wall thickness is made possible by the fact that the turbulators stiffen the wall. By reducing the wall thickness, the cow's efficiency is increased again.
  • the turbulators can advantageously be used as metal feed channels when casting the blade. The honeycomb structure is therefore easy to manufacture.
  • the blade according to the invention can be designed as a guide blade or as a rotor blade of a rotary machine.
  • FIG. 1 shows a longitudinal section through a rotary machine
  • FIG. 2 shows a perspective, broken-away representation of a blade
  • 3 shows a plan view of the inside of a wall of the blade
  • FIG. 8 shows a view similar to FIG. 7 in the second embodiment.
  • FIG. 1 shows a longitudinal section through a rotary machine in the form of a turbine 10 with a housing 11 and a rotor 12.
  • the housing 11 is provided with guide vanes 13 and the rotor 12 with rotor blades 14.
  • the turbine 10 is flowed through according to arrow 15 by a fluid which flows along the guide vanes 13 and rotor blades 14 and rotates the rotor 12 m around an axis 16.
  • the temperature of the fluid is relatively high in many application cases, particularly in the area of the first row of blades (shown on the left in FIG. 1). A cooling of the guide vanes 13 and blades 14 is therefore provided.
  • Flow of the cooling fluid is indicated schematically by the arrows 17, 18.
  • FIG. 2 schematically shows a broken view of a guide vane 13.
  • the guide vane 13 has curved outer walls 19, 20.
  • the interior lying between the outer walls 19, 20 is divided into a total of three channels 22 via two partition walls 21 m.
  • An insert 25 is inserted into each of the channels 22.
  • the embedding of the middle channel 22 is not shown for better illustration.
  • the two outer walls 19, 20 are provided with a number of horizontal ribs 24 in each of the channels 22.
  • the horizontal ribs 24 run along the walls 19, 20 and extend as far as the partition walls 21.
  • Turbulators 23 are arranged between the horizontal ribs 24.
  • the inserts 25 touch the horizontal ribs 24.
  • the cooling fluid in particular cooling air, is supplied to an interior 26 of the inserts 25.
  • the inserts 25 are provided with a number of openings 27 through which the cooling fluid exits the space between the outer walls 19, 20 and the insert 25.
  • the cooling fluid then flows along the outer walls 19, 20 to outlet openings 28 in the walls 19, 20. This flow is indicated schematically by the arrow 30.
  • the openings 27 of the inserts 25 are arranged at a distance from the opening 28 of the outer walls 19, 20. In the exemplary embodiment shown, the opening openings 28 form essentially straight rows 29.
  • the cooling fluid emerging from the inserts 25 first impacts the outer walls 19, 20 and leads there to one
  • the front edge of the guide vane 13 shown on the left in FIG. 2 is additionally provided with direct impact cooling.
  • the insert 25 has further openings 36 for this impingement cooling, which are arranged directly behind the front edge of the guide vane 13.
  • the cooling medium exits directly through these openings 36 and provides targeted cooling of the front edge of the guide vane 13.
  • the associated insert 25 is also provided with a further opening 37 in the region of the rear edge of the guide vane 13. Through this opening 37, cooling fluid emerges directly in a narrow gap 38 between the outer walls 19, 20 and causes film cooling there.
  • FIGS. 3 to 5 show further details of the inside of the outer wall 19.
  • the horizontal ribs 24 run essentially at right angles to a longitudinal axis 31 of the guide vane 13. They are arranged parallel to one another. Between the horizontal ribs 24 straight turbulators 23 are arranged, which merge into one another and the ho ⁇ zonal ⁇ ppen 24.
  • the front edge 33 of the horizontal ribs 24 merges into the partition 21 in the middle channel 22 m. In the channel 22 on the left in FIG. 2, the front edge 33 is arranged at some distance from the foremost outflow openings 28.
  • the cooling fluid enters this chamber 32 through the openings 27 of the insert 25 m. It then flows according to arrow 30 to the opening 28.
  • the openings 27 are arranged at one end of the chamber 32 and the opening 28 at the other end. This maximizes the distance that the cooling fluid traverses as it flows along the outer wall 19. This results in maximum convection cooling.
  • the effect of convection cooling is further enhanced by the turbulators 23, since these improve the heat exchange between the outer wall 19 and the cooling fluid.
  • the chambers 32 can be supplied with the cooling fluid in different ways. This is achieved by varying the number and / or the size of the openings 27 in the insert 25. In this way, individual chambers 32 can be specifically cooled more or less than others. The cooling can thus be specifically adjusted along the longitudinal axis 31 of the guide vane 13 and adapted to the prevailing boundary conditions.
  • the turbulators 23 also serve to stiffen the outer wall 19.
  • the straight turbulators 23 are arranged in such a way that they form polygons. In FIG. 3, game triangles and shown in Figure 6 as examples diamonds.
  • the stiffening achieved by the turbulators 23 enables a reduction in the wall thickness d of the outer wall 19 in the region between the turbulators 23. Because of this reduction in the wall thickness d, the cooling efficiency increases further.
  • Figure 6 shows a plan view of the inside of the outer wall 19 m of the second embodiment.
  • the turbulators 24 are opposite to the longitudinal axis 31
  • turbulators 23 are provided, four of which are combined to form a rhombus. The reduction in the wall thickness is indicated schematically in these diamonds with visible edges.
  • the second outer wall 20 is also provided with corresponding turbulators 23 and horizontal ribs 24.
  • the horizontal ribs 24 and turbulators 23 can alternatively or additionally also be provided for a moving blade 14.
  • FIGS. 7 and 8 show two configurations of an insert 25. In the configuration according to FIG.
  • Cooling fluid is supplied from both ends 34, 35 of the insert and exits through openings 27.
  • Such an insert 25 can be used, for example, in the first row of blades.
  • an insert 25 according to FIG. 8 can be provided, which is closed at the end 34.
  • the cooling fluid is then only supplied via the end 35.
  • This insert 25 is used in the further rows of blades, in which only one end of the guide vane 13 or the rotor blade 14 can be acted upon by the cooling fluid via the housing 11 or the rotor 12. Due to the horizontal ribs 24 provided according to the invention, there is a directed flow of the cooling fluid along the outer walls 19, 20. The cooling effect is therefore significantly improved. At the same time, simple manufacture is possible since there is no need for blades with hollow walls.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

The invention relates to a blade (13; 14) for a turbine (10), comprising at least one channel (22) which is delimited by walls (19, 20, 21). An insert (25) which can be subjected to the action of a liquid coolant is inserted into at least one channel (22). According to the invention, at least one of the walls (19; 20) is provided with a number of horizontal ribs (24) which are located between the insert (25) and the wall (19; 20). Said insert (25) is provided with openings (27) through which the liquid coolant passes out of the insert (25) and between the horizontal ribs (24). The liquid coolant is therefore conducted along the wall (19, 20) and guided by the horizontal ribs (24) in order to provide improved convection cooling.

Description

Beschreibungdescription
KUH SYSTEM FÜR EINE TURBINENSCHAUFELCOW SYSTEM FOR A TURBINE SHOVEL
Die Erfindung betrifft eine Schaufel, insbesondere eine Tur- binenschaufel, mit mindestens einem Kanal, der von Wanden begrenzt ist, wobei m mindestens einen Kanal ein mit einem Kuhlfluid beaufschlagbarer Einsatz eingefugt ist.The invention relates to a blade, in particular a turbine blade, with at least one channel which is delimited by walls, wherein an insert which can be acted upon by a cooling fluid is inserted into at least one channel.
Eine derartige Schaufel ist aus der US 5,419,039 bekannt.Such a blade is known from US 5,419,039.
Zwischen dem Einsatz und den Wanden der Schaufel werden Kammern gebildet, die m Richtung einer Langsachse der Schaufel verlaufen. Das Kuhlfluid tritt aus dem Einsatz m diese Kammern ein und prallt auf die Wände der Schaufel. Anschließend strömt es an den Wände entlang und tritt durch Austnttsoff- nungen m speziell geformte Kammern an der Außenseite der Wände und von dort m die Umgebung aus. Bei der bekannten Schaufel ist die Wirkung der Konvektionskuhlung beim Strömen des Kuhlfluids entlang den Wanden nur gering, da die Stro- mungslange stark begrenzt ist. Weiter tritt eine Vermischung des Kuhlfluids m den Kammern entlang der Langsachse der Schaufel auf, so daß keine gezielte Kühlung möglich ist.Chambers are formed between the insert and the walls of the blade, which run in the direction of a longitudinal axis of the blade. The cooling fluid enters the chamber from the insert and impacts the walls of the blade. It then flows along the walls and exits through specially designed chambers on the outside of the walls and from there the surroundings. In the known blade, the effect of convection cooling when the cooling fluid flows along the walls is only slight, since the flow length is very limited. Mixing of the cooling fluid also occurs in the chambers along the longitudinal axis of the blade, so that targeted cooling is not possible.
Eine andere Schaufel ist aus der auf dieselbe Anmeldenn zu- ruckgehenden WO98/25009 bekannt. Diese Druckschrift beschreibt eine Schaufel mit bereichsweise hohl ausgebildeten Wanden, die von einem Kuhlfluid durchströmt werden. Aufgrund der Verringerung der Wandstarke im Bereich der Hohlkammern wird eine hohe Kuhlefflzienz erreicht. Allerdings erfordern Schaufeln mit derartigen Hohlwanden einen komplizierten Gußvorgang mit hohen Ausschußraten und sind daher sehr teuer.Another blade is known from WO98 / 25009, which is based on the same applications. This document describes a blade with partially hollow walls through which a cooling fluid flows. Due to the reduction in the wall thickness in the area of the hollow chambers, a high cooling efficiency is achieved. However, blades with such hollow walls require a complicated casting process with high reject rates and are therefore very expensive.
Aufgabe der vorliegenden Erfindung ist es daher, eine Schaufel bereitzustellen, die bei einfacher Herstellung eine Ver- besserung der Kuhlwirkung erreicht. Erfindungsgemaß wird diese Aufgabe bei einer Schaufel der eingangs genannten Art dadurch gelost, daß wenigstens eine der Wände mit einer Anzahl von Horizontalrippen versehen ist, die zwischen dem Einsatz und der Wand angeordnet sind, und daß der Einsatz mit Offnungen versehen ist, durch die dasThe object of the present invention is therefore to provide a blade which, with simple manufacture, achieves an improvement in the cooling effect. According to the invention, this object is achieved in a shovel of the type mentioned in the introduction in that at least one of the walls is provided with a number of horizontal ribs which are arranged between the insert and the wall, and in that the insert is provided with openings through which the
Kuhlfluid aus dem Einsatz zwischen die Horizontalrippen eintreten kann.Cooling fluid from the insert can enter between the horizontal ribs.
Die Horizontalrippen leiten das Kuhlmittel entlang der Wand der Schaufel und verhindern ein Strömen des Kuhlmittels mThe horizontal ribs guide the coolant along the wall of the blade and prevent the coolant from flowing
Richtung der Langsachse der Schaufel. Es wird somit eine gute Konvektionskuhlung der Wand erreicht. Weiter versteifen die Horizontalrippen die Schaufel, so daß die Wandstarke verringert werden kann. Die Verringerung der Wandstarke fuhrt zu einer erhöhten Kuhleffizienz . Die Herstellung der Schaufel kann mit bekannten Verfahren ohne komplexen Querschnitt erfolgen. Hohlwande sind nicht erforderlich. Die Ausschußquote wird daher wesentlich gesenkt.Direction of the longitudinal axis of the blade. Good convection cooling of the wall is thus achieved. Furthermore, the horizontal ribs stiffen the blade, so that the wall thickness can be reduced. The reduction in wall thickness leads to increased cow efficiency. The blade can be produced using known methods without a complex cross section. Cavity walls are not necessary. The reject rate is therefore significantly reduced.
Vorteilhafte Ausgestaltungen und Weiterbildungen der Erfindung gehen aus den abhangigen Ansprüchen hervor.Advantageous refinements and developments of the invention emerge from the dependent claims.
In vorteilhafter Ausgestaltung berührt der Einsatz die Horizontalrippen. Der Einsatz wird abgestutzt und m der ge- wünschten Position ausgerichtet.In an advantageous embodiment, the insert touches the horizontal ribs. The insert is clipped and aligned in the desired position.
Nach einer vorteilhaften Weiterbildung bilden die Horizontalrippen, der Einsatz und die Wand von dem Kuhlfluid durchströmte Kammern. Durch die Kammern wird ein Strömen des Kuhlfluids m Richtung der Langsachse der Schaufel zuverlässig verhindert. Weiter kann die Kuhlwirkung entlang der Langsachse der Schaufel durch eine unterschiedliche Beaufschlagung der Kammern mit dem Kuhlfluid gezielt variiert werden.According to an advantageous development, the horizontal ribs, the insert and the wall form the chambers through which the cooling fluid flows. The chambers reliably prevent the cooling fluid from flowing in the direction of the longitudinal axis of the blade. Furthermore, the cooling effect along the longitudinal axis of the blade can be varied in a targeted manner by applying the cooling fluid to the chambers differently.
In vorteilhafter Ausgestaltung sind die Offnungen des Einsatzes an einem ersten Ende der Kammern und Austnttsoffnungen für das Kuhlfluid m der Wand an einem zweiten Ende der Kammern angeordnet sind. Das Kuhlfluid strömt daher entlang der ganze Lange der Kammer an der zu kühlenden Wand entlang, so daß die Konvektionskuhlung weiter verbessert wird.In an advantageous embodiment, the openings of the insert are at a first end of the chambers and exit openings for the cooling fluid m the wall are arranged at a second end of the chambers. The cooling fluid therefore flows along the entire length of the chamber along the wall to be cooled, so that the convection cooling is further improved.
Die Horizontalrippen können im wesentlichen senkrecht zu der Langsachse der Schaufel angeordnet sein. Alternativ kann eine Winkelstellung vorgesehen werden. Bei einer senkrechten Anordnung bezuglich der Langsachse wird die Lange der Horizon- talrippen und damit der Kammern minimiert. Die Winkelstellung ermöglicht eine Vergrößerung der Lange der Kammern und damit eine nochmals verbesserte Konvektionskuhlung.The horizontal ribs can be arranged essentially perpendicular to the longitudinal axis of the blade. Alternatively, an angular position can be provided. With a vertical arrangement with respect to the longitudinal axis, the length of the horizontal ribs and thus the chambers is minimized. The angular position enables the length of the chambers to be increased and thus further improved convection cooling.
Vorteilhaft ist der Einsatz an einem Ende verschlossen. Das Kuhlfluid wird m diesem Fall nur von dem anderen Ende des Einsatzes her zugeführt. Ein Austreten des Kuhlfluids durch das von der Zufuhrseite abgewandte Ende wird verhindert, so daß die Kuhleffizienz gesteigert wird. Alternativ kann von beiden Enden her Kuhlfluid zugeführt werden.The insert is advantageously closed at one end. In this case, the cooling fluid is only supplied from the other end of the insert. The cooling fluid is prevented from escaping through the end facing away from the supply side, so that the cooling efficiency is increased. Alternatively, cooling fluid can be supplied from both ends.
Gemäß einer vorteilhaften Ausgestaltung dienen die Turbulato- ren zur Versteifung der Wand und gehen ineinander und m die Horizontalrippen über. Hierdurch wird eine wesentliche Erhöhung der Steifigkeit ohne zusatzliches Material erreicht. Bei gleicher Festigkeit der Schaufel kann die Wandstarke nochmals verringert werden. Gleichzeitig wird ein guter Wärmeaustausch zwischen den Wanden und dem Kuhlfluid erreicht. Es ergeben sich somit eine hohe Kuhleffizienz und ein hoher Gesamtwirkungsgrad.According to an advantageous embodiment, the turbulators serve to stiffen the wall and merge into one another and m the horizontal ribs. This results in a significant increase in rigidity without additional material. With the same strength of the blade, the wall thickness can be reduced again. At the same time, good heat exchange between the walls and the cooling fluid is achieved. This results in high cow efficiency and high overall efficiency.
Die Versteifung der Wand stellt sich nicht nur im Bereich eines einzelnen Turbulators ein. Es wird vielmehr durch die Verbindung der Turbulatoren miteinander eine großflächige Versteifung bereitgestellt. Vorteilhaft sind die Turbulatoren gerade ausgebildet. Die Verwendung gerader Turbulatoren ermöglicht eine hohe Steifig- keit bei einfacher Fertigung.The stiffening of the wall does not only occur in the area of a single turbulator. Rather, a large-area stiffening is provided by connecting the turbulators to one another. The turbulators are advantageously straight. The use of straight turbulators enables high rigidity with simple manufacture.
Nach einer vorteilhaften Ausgestaltung sind die Turbulatoren derart angeordnet, daß sie zusammen mit den Horizontalrippen nebenemanderliegende Ausnehmungen m Form von Vielecken bilden, insbesondere Dreiecke oder Rauten. Die Innenseite der Wand wird mit einer Wabenstruktur versehen. Die einzelnen Vielecke oder Waben bilden jeweils einen geschlossenen, hoch belastbaren Querschnitt und stutzen sich gegenseitig ab. Es laßt sich eine wesentliche Erhöhung der Steifigkeit erzielen.According to an advantageous embodiment, the turbulators are arranged such that, together with the horizontal ribs, they form mutually adjacent recesses in the form of polygons, in particular triangles or rhombuses. The inside of the wall is provided with a honeycomb structure. The individual polygons or honeycombs each form a closed, highly resilient cross-section and support each other. A substantial increase in rigidity can be achieved.
In vorteilhafter Weiterbildung ist die Wandstarke der Wand zumindest im Bereich zwischen den Turbulatoren verringert. Diese Verringerung der Wandstarke wird dadurch ermöglicht, daß die Turbulatoren eine Versteifung der Wand bewirken. Durch die Verringerung der Wandstarke wird die Kuhleffizienz nochmals erhöht. Die Turbulatoren können hierbei vorteilhaft beim Gießen der Schaufel als Metallemspeisungskanale verwendet werden. Die Wabenstruktur ist daher gut herstellbar.In an advantageous development, the wall thickness of the wall is reduced at least in the area between the turbulators. This reduction in wall thickness is made possible by the fact that the turbulators stiffen the wall. By reducing the wall thickness, the cow's efficiency is increased again. The turbulators can advantageously be used as metal feed channels when casting the blade. The honeycomb structure is therefore easy to manufacture.
Die erfmdungsgemaße Schaufel kann als Leitschaufel oder als Laufschaufel einer Rotationsmaschine ausgebildet werden.The blade according to the invention can be designed as a guide blade or as a rotor blade of a rotary machine.
Nachstehend wird die Erfindung an Hand von Ausfuhrungsbeispielen naher beschrieben, die schematisch m der Zeichnung dargestellt sind. Für gleiche oder funktionsidentische Bauteile werden durchgehend dieselben Bezugszeichen verwendet. Dabei zeigt:The invention is described in more detail below with reference to exemplary embodiments, which are shown schematically in the drawing. The same reference symbols are used throughout for identical or functionally identical components. It shows:
FIG 1 einen Längsschnitt durch eine Rotationsmaschine;1 shows a longitudinal section through a rotary machine;
FIG 2 eine perspektivische, aufgebrochene Darstellung einer Schaufel; FIG 3 eine Draufsicht auf die Innenseite einer Wand der Schaufel;2 shows a perspective, broken-away representation of a blade; 3 shows a plan view of the inside of a wall of the blade;
FIG 4 einen Schnitt längs der Linie IV-IV m Figur 3; FIG 5 einen Schnitt längs der Linie V-V m Figur 3; FIG 6 eine Ansicht ähnlich Figur 3 in zweiter Ausgestaltung; FIG 7 eine schematische Darstellung eines Einsatzes in erster Ausgestaltung; und4 shows a section along the line IV-IV m Figure 3; 5 shows a section along the line VV m Figure 3; 6 shows a view similar to FIG. 3 in a second embodiment; 7 shows a schematic illustration of an insert in a first embodiment; and
FIG 8 eine Ansicht ahnlich Figur 7 m zweiter Ausgestaltung .8 shows a view similar to FIG. 7 in the second embodiment.
Figur 1 zeigt eine Längsschnitt durch eine Rotationsmaschine in Form einer Turbine 10 mit einem Gehäuse 11 und einem Rotor 12. Das Gehäuse 11 ist mit Leitschaufeln 13 und der Rotor 12 mit Laufschaufeln 14 versehen. Im Betrieb wird die Turbine 10 gemäß Pfeilπchtung 15 von einem Fluid durcnstromt, das an den Leitschaufein 13 und Laufschaufeln 14 entlangstromt und den Rotor 12 m Drehung um eine Achse 16 versetzt.FIG. 1 shows a longitudinal section through a rotary machine in the form of a turbine 10 with a housing 11 and a rotor 12. The housing 11 is provided with guide vanes 13 and the rotor 12 with rotor blades 14. In operation, the turbine 10 is flowed through according to arrow 15 by a fluid which flows along the guide vanes 13 and rotor blades 14 and rotates the rotor 12 m around an axis 16.
Die Temperatur des Fluids ist m vielen Anwendungsfallen, insbesondere im Bereich der ersten Schaufelreihe (m Figur 1 links dargestellt) , relativ hoch. Es ist daher eine K hlung der Leitschaufeln 13 und Laufschaufeln 14 vorgesehen. DasThe temperature of the fluid is relatively high in many application cases, particularly in the area of the first row of blades (shown on the left in FIG. 1). A cooling of the guide vanes 13 and blades 14 is therefore provided. The
Strömen des Kuhlfluids ist schematisch mit den Pfeilen 17, 18 angedeutet .Flow of the cooling fluid is indicated schematically by the arrows 17, 18.
Figur 2 zeigt schematisch eine aufgebrochene Darstellung ei- ner Leitschaufel 13. Die Leitschaufel 13 weist gebogene Außenwände 19, 20 auf. Der zwischen den Außenwanden 19, 20 liegende Innenraum wird über zwei Trennwände 21 m insgesamt drei Kanäle 22 unterteilt. In jeden der Kanäle 22 ist ein Einsatz 25 eingesetzt. Zur besseren Darstellung ist der Em- satz des mittleren Kanals 22 nicht gezeichnet.FIG. 2 schematically shows a broken view of a guide vane 13. The guide vane 13 has curved outer walls 19, 20. The interior lying between the outer walls 19, 20 is divided into a total of three channels 22 via two partition walls 21 m. An insert 25 is inserted into each of the channels 22. The embedding of the middle channel 22 is not shown for better illustration.
Die beiden Außenwände 19, 20 sind m jedem der Kanäle 22 mit einer Anzahl von Horizontalrippen 24 versehen. Die Horizontalrippen 24 verlaufen entlang den Wanden 19, 20 und erstre- cken sich bis zu den Trennwanden 21. Zwischen den Horizonal- rippen 24 sind Turbulatoren 23 angeordnet. Die Einsätze 25 berühren die Horizontalrippen 24. Das Kuhlfluid, insbesondere Kuhlluft, wird einem Innenraum 26 der Einsätze 25 zugeführt. Die Einsätze 25 sind mit einer Anzahl von Offn ngen 27 versehen, durch die das Kuhlfluid m den Zwischenraum zwischen den Außenwanden 19, 20 und dem Em- satz 25 austritt. Anschließend strömt das Kuhlfluid entlang den Außenwanden 19, 20 bis zu Austnttsoffnungen 28 in den Wanden 19, 20. Dieses Strömen ist schematisch mit dem Pfeil 30 angezeigt. Die Offnungen 27 der Einsätze 25 sind hierbei beabstandet zu den Austnttsoffnungen 28 der Außenwände 19, 20 angeordnet. Die Austnttsoffnungen 28 bilden im dargestellten Ausfuhrungsbeispiel im wesentlichen gerade Reihen 29.The two outer walls 19, 20 are provided with a number of horizontal ribs 24 in each of the channels 22. The horizontal ribs 24 run along the walls 19, 20 and extend as far as the partition walls 21. Turbulators 23 are arranged between the horizontal ribs 24. The inserts 25 touch the horizontal ribs 24. The cooling fluid, in particular cooling air, is supplied to an interior 26 of the inserts 25. The inserts 25 are provided with a number of openings 27 through which the cooling fluid exits the space between the outer walls 19, 20 and the insert 25. The cooling fluid then flows along the outer walls 19, 20 to outlet openings 28 in the walls 19, 20. This flow is indicated schematically by the arrow 30. The openings 27 of the inserts 25 are arranged at a distance from the opening 28 of the outer walls 19, 20. In the exemplary embodiment shown, the opening openings 28 form essentially straight rows 29.
Das aus den Einsatzen 25 austretende Kuhlfluid prallt zu- nächst auf die Außenwände 19, 20 und fuhrt dort zu einerThe cooling fluid emerging from the inserts 25 first impacts the outer walls 19, 20 and leads there to one
Prallkuhlung . Anschließend strömt es entlang der Außenwände 19, 20 bis zu den Austnttsoffnungen 28, so daß eine Konvektionskuhlung erreicht wird. Nach dem Austreten aus den Austnttsoffnungen 28 bildet sich ein Film des Kuhlfluids an der Außenseite der Außenwände 19, 20, so daß ebenfalls eine Film- kuhlung zur Verfugung gestellt wird. Es ergibt sich eine wesentlich verbesserte Kühlung.Impact cooling. It then flows along the outer walls 19, 20 to the outlet openings 28, so that convection cooling is achieved. After exiting the outlet openings 28, a film of the cooling fluid forms on the outside of the outer walls 19, 20, so that film cooling is also made available. This results in a significantly improved cooling.
Die m Figur 2 links dargestellte Vorderkante der Leitschau- fei 13 ist zusätzlich mit einer direkten Prallkuhlung versehen. Der Einsatz 25 weist für diese Prallkuhlung weitere Offnungen 36 auf, die unmittelbar hinter der Vorderkante der Leitschaufel 13 angeordnet sind. Das Kuhlmedium tritt ber diese Offnungen 36 direkt aus und stellt eine gezielte Kuh- lung der Vorderkante der Leitschaufel 13 bereit.The front edge of the guide vane 13 shown on the left in FIG. 2 is additionally provided with direct impact cooling. The insert 25 has further openings 36 for this impingement cooling, which are arranged directly behind the front edge of the guide vane 13. The cooling medium exits directly through these openings 36 and provides targeted cooling of the front edge of the guide vane 13.
Auch im Bereich der Hinterkante der Leitschaufel 13 ist der zugehörige Einsatz 25 mit einer weiteren Öffnung 37 versehen. Durch diese Öffnung 37 tritt Kuhlfluid direkt m einen schma- len Spalt 38 zwischen den Außenwanden 19, 20 aus und bewirkt dort eine Filmkuhlung. Die Figuren 3 bis 5 zeigen nähere Einzelheiten der Innenseite der Außenwand 19. Die Horizontalrippen 24 verlaufen im wesentlichen rechtwinklig zu einer Langsachse 31 der Leitschaufel 13. Sie sind parallel zueinander angeordnet. Zwischen den Horizontalrippen 24 sind gerade Turbulatoren 23 angeordnet, die ineinander und m die Hoπzonalπppen 24 übergehen.The associated insert 25 is also provided with a further opening 37 in the region of the rear edge of the guide vane 13. Through this opening 37, cooling fluid emerges directly in a narrow gap 38 between the outer walls 19, 20 and causes film cooling there. FIGS. 3 to 5 show further details of the inside of the outer wall 19. The horizontal ribs 24 run essentially at right angles to a longitudinal axis 31 of the guide vane 13. They are arranged parallel to one another. Between the horizontal ribs 24 straight turbulators 23 are arranged, which merge into one another and the hoπzonalπppen 24.
Die Vorderkante 33 der Horizontalrippen 24 geht bei dem mittleren Kanal 22 m die Trennwand 21 über. Bei dem m Figur 2 linken Kanal 22 ist die Vorderkante 33 mit einigem Abstand zu den vordersten Ausströmöffnungen 28 angeordnet.The front edge 33 of the horizontal ribs 24 merges into the partition 21 in the middle channel 22 m. In the channel 22 on the left in FIG. 2, the front edge 33 is arranged at some distance from the foremost outflow openings 28.
Jeweils zwei Horizontalrippen 24 begrenzen zusammen mit der Außenwand 19 und dem Einsatz 25 eine Kammer 32. Das Kuhlfluid tritt durch die Offnungen 27 des Einsatzes 25 m diese Kammer 32 ein. Anschließend strömt es gemäß Pfeilπchtung 30 zu den Austnttsoffnungen 28. Die Offnungen 27 sind hierbei an dem einen Ende der Kammer 32 und die Austnttsoffnungen 28 an dem anderen Ende angeordnet. Hierdurch wird die Strecke, die das Kuhlfluid beim Strömen entlang der Außenwand 19 überstreicht, maximiert. Es ergibt sich somit eine maximale Konvektionskuhlung. Der Effekt der Konvektionskuhlung wird durch die Turbulatoren 23 noch verstärkt, da diese den Wärmeaustausch zwischen der Außenwand 19 und dem Kuhlfluid verbessern.Two horizontal ribs 24, together with the outer wall 19 and the insert 25, delimit a chamber 32. The cooling fluid enters this chamber 32 through the openings 27 of the insert 25 m. It then flows according to arrow 30 to the opening 28. The openings 27 are arranged at one end of the chamber 32 and the opening 28 at the other end. This maximizes the distance that the cooling fluid traverses as it flows along the outer wall 19. This results in maximum convection cooling. The effect of convection cooling is further enhanced by the turbulators 23, since these improve the heat exchange between the outer wall 19 and the cooling fluid.
Die Kammern 32 können unterschiedlich mit dem Kuhlfluid beaufschlagt werden. Dies wird über eine Variation der Anzahl und/oder der Große der Offnungen 27 des Einsatzes 25 erreicht Auf diese Weise können einzelne Kammern 32 gezielt starker oder schwacher als andere gekühlt werden. Die Kühlung kann somit entlang der Langsachse 31 der Leitschaufel 13 gezielt eingestellt und an die herrschenden Randbedingungen angepaßt werden.The chambers 32 can be supplied with the cooling fluid in different ways. This is achieved by varying the number and / or the size of the openings 27 in the insert 25. In this way, individual chambers 32 can be specifically cooled more or less than others. The cooling can thus be specifically adjusted along the longitudinal axis 31 of the guide vane 13 and adapted to the prevailing boundary conditions.
Die Turbulatoren 23 dienen weiter zur Versteifung der Außenwand 19. Die geraden Turbulatoren 23 sind hierbei derart angeordnet, daß sie Vielecke bilden. In Figur 3 sind als Bei- spiel Dreiecke und in Figur 6 als Beispiele Rauten dargestellt. Die durch die Turbulatoren 23 erzielte Versteifung ermöglicht eine Verringerung der Wandstarke d der Außenwand 19 im Bereich zwischen den Turbulatoren 23. Aufgrund dieser Verringerung der Wandstarke d steigt die Kuhleffizienz weiter an.The turbulators 23 also serve to stiffen the outer wall 19. The straight turbulators 23 are arranged in such a way that they form polygons. In FIG. 3, game triangles and shown in Figure 6 as examples diamonds. The stiffening achieved by the turbulators 23 enables a reduction in the wall thickness d of the outer wall 19 in the region between the turbulators 23. Because of this reduction in the wall thickness d, the cooling efficiency increases further.
Figur 6 zeigt eine Draufsicht auf die Innenseite der Außenwand 19 m zweiter Ausgestaltung. Bei dieser Ausgestaltung sind die Turbulatoren 24 gegenüber der Langsachse 31 derFigure 6 shows a plan view of the inside of the outer wall 19 m of the second embodiment. In this embodiment, the turbulators 24 are opposite to the longitudinal axis 31
Leitschaufel 13 geneigt. Auf Grund dieser Neigung vergrößert sich die Lange der Kammern 32 und damit die Wirkung der Konvektionskuhlung. Auch bei dieser Ausgestaltung sind gerade Turbulatoren 23 vorgesehen, von denen jeweils vier zu einer Raute zusammengefaßt sind. Die Verringerung der Wandstarke ist schematisch m diesen Rauten mit Sichtkanten angedeutet.Guide vane 13 inclined. Due to this inclination, the length of the chambers 32 increases and thus the effect of the convection cooling. In this embodiment, too, turbulators 23 are provided, four of which are combined to form a rhombus. The reduction in the wall thickness is indicated schematically in these diamonds with visible edges.
Selbstverständlich ist auch die zweite Außenwand 20 mit entsprechenden Turbulatoren 23 und Horizontalrippen 24 versehen. Die Horizontalrippen 24 und Turbulatoren 23 können alternativ oder zusätzlich auch bei einer Laufschaufel 14 vorgesehen werden.Of course, the second outer wall 20 is also provided with corresponding turbulators 23 and horizontal ribs 24. The horizontal ribs 24 and turbulators 23 can alternatively or additionally also be provided for a moving blade 14.
Die Figuren 7 und 8 zeigen zwei Ausgestaltungen eines Einsat- zes 25. Bei der Ausgestaltung gemäß Figur 7 wird dasFIGS. 7 and 8 show two configurations of an insert 25. In the configuration according to FIG
Kuhlfluid von beiden Enden 34, 35 des Einsatzes zugeführt und tritt durch die Offnungen 27 aus. Ein derartiger Einsatz 25 kann beispielsweise m der ersten Schaufelreihe verwendet werden.Cooling fluid is supplied from both ends 34, 35 of the insert and exits through openings 27. Such an insert 25 can be used, for example, in the first row of blades.
Alternativ kann ein Einsatz 25 gemäß Figur 8 vorgesehen werden, der an dem Ende 34 verschlossen ist. Das Kuhlfluid wird dann nur über das Ende 35 zugeführt. Dieser Einsatz 25 wird m den weiteren Schaufelreihen verwendet, m denen jeweils nur ein Ende der Leitschaufel 13 oder der Laufschaufel 14 über das Gehäuse 11 beziehungsweise den Rotor 12 mit dem Kuhlfluid beaufschlagt werden kann. Aufgrund der erfindungsgemaß vorgesehenen Horizontalrippen 24 ergibt sich eine gerichtete Strömung des Kuhlfluids entlang der Außenwände 19, 20. Die Kuhlwirkung wird daher wesentlich verbessert. Gleichzeitig ist eine einfache Herstellung möglich, da auf Schaufeln mit Hohlwanden verzichtet werden kann. Alternatively, an insert 25 according to FIG. 8 can be provided, which is closed at the end 34. The cooling fluid is then only supplied via the end 35. This insert 25 is used in the further rows of blades, in which only one end of the guide vane 13 or the rotor blade 14 can be acted upon by the cooling fluid via the housing 11 or the rotor 12. Due to the horizontal ribs 24 provided according to the invention, there is a directed flow of the cooling fluid along the outer walls 19, 20. The cooling effect is therefore significantly improved. At the same time, simple manufacture is possible since there is no need for blades with hollow walls.

Claims

Patentansprüche claims
1. Schaufel, insbesondere Turbinenschaufel (13; 14), mit mindestens einem Kanal (22), der von Wanden (19, 20, 21) be- grenzt ist, wobei m mindestens einen Kanal (22) ein mit einem Kuhlfluid beaufschlagbarer Einsatz (25) eingefugt ist, dadurch gekennzeichnet, daß wenigstens eine der Wände (19; 20) mit einer Anzahl von Horizontalrippen (24) versehen ist, die zwischen dem Einsatz (25) und der Wand (19; 20) angeordnet sind, und daß der Einsatz (25) mit Offnungen (27) versehen ist, durch die das Kuhlfluid aus dem Einsatz (25) zwischen die Horizontalrippen (24) eintreten kann.1. Blade, in particular turbine blade (13; 14), with at least one channel (22) which is delimited by walls (19, 20, 21), wherein at least one channel (22) is an insert which can be acted upon with a cooling fluid ( 25) is inserted, characterized in that at least one of the walls (19; 20) is provided with a number of horizontal ribs (24) which are arranged between the insert (25) and the wall (19; 20), and in that the Insert (25) is provided with openings (27) through which the cooling fluid from the insert (25) can enter between the horizontal ribs (24).
2. Schaufel nach Anspruch 1, dadurch ge ennzeichnet, daß der Einsatz (25) die Horizontalrippen (24) ber hrt.2. Bucket according to claim 1, characterized in that the insert (25) touches the horizontal ribs (24).
3. Schaufel nach Anspruch 2, dadurch gekennzeichnet, daß die Horizontalrippen (24), der Einsatz (25) und die Wand (19; 20) von dem Kuhlfluid durchströmte Kammern (32) bilden.3. Blade according to claim 2, characterized in that the horizontal ribs (24), the insert (25) and the wall (19; 20) of the cooling fluid flow through chambers (32).
4. Schaufel nach Anspruch 3, dadurch gekennzeichnet, daß die Offnungen (27) des Einsatzes (25) an einem ersten Ende der Kammern (32) und Austnttsoffnungen (28) für das Kuhlfluid in der Wand (19; 20) an einem zweiten Ende der Kammern (32) angeordnet sind.4. A blade according to claim 3, characterized in that the openings (27) of the insert (25) at a first end of the chambers (32) and outlet openings (28) for the cooling fluid in the wall (19; 20) at a second end the chambers (32) are arranged.
5. Schaufel nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, daß die Horizontalrippen (24) im wesentlichen senkrecht zu einer Langsachse (25) der Schaufel (13; 14) angeordnet sind.5. Blade according to one of claims 1 to 4, characterized in that the horizontal ribs (24) are arranged substantially perpendicular to a longitudinal axis (25) of the blade (13; 14).
6. Schaufel nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, daß der Einsatz (25) an einem Ende (34) verschlossen ist. 6. Bucket according to one of claims 1 to 5, characterized in that the insert (25) is closed at one end (34).
7. Schaufel nach einem der Ansprüche 1 bis 6, dadurch gekennzeichnet, daß zwischen den Horizontalrippen (24) Turbulatoren (23) zur Verbesserung des Wärmeaustausches zwischen der Wand (19; 20) und dem Kuhlfluid vor- gesehen sind.7. Blade according to one of claims 1 to 6, characterized in that between the horizontal ribs (24) turbulators (23) to improve the heat exchange between the wall (19; 20) and the cooling fluid are provided.
8. Schaufel nach Anspruch 7, dadurch gekennzeichnet, daß die Turbolatoren (23) zur Versteifung der Wand (19; 20) dienen und ineinander und m die Horizontalrippen (24) übergehen.8. A blade according to claim 7, characterized in that the turbolators (23) serve to stiffen the wall (19; 20) and merge into one another and the horizontal ribs (24).
9. Schaufel nach Anspruch 7 oder 8, dadurch gekennzeichnet, daß die Turbulatoren (23 ) im wesentlichen gerade ausgebildet sind.9. A blade according to claim 7 or 8, characterized in that the turbulators (23) are substantially straight.
10. Schaufel nach Anspruch 8 oder 9, dadurch gekennzeichnet, daß Turbulatoren (23) derart angeordnet sind, daß sie zusammen mit den Horizontalrippen (24) nebenemanderliegende Ausnehmungen Form von Viel- ecken, insbesondere Dreiecken oder Rauten, bilden.10. A blade according to claim 8 or 9, characterized in that turbulators (23) are arranged such that they form, together with the horizontal ribs (24) adjacent recesses in the form of polygons, in particular triangles or diamonds.
11. Schaufel nach Anspruch 9 oder 10, dadurch gekennzeichnet, daß die Wandstarke (d) der Wand (19; 20) zumindest im Bereich zwischen den Turbulatoren (23) verringert ist.11. Blade according to claim 9 or 10, characterized in that the wall thickness (d) of the wall (19; 20) is reduced at least in the region between the turbulators (23).
12. Schaufel nach einem der Ansprüche 1 bis 11, dadurch gekennzeichnet, daß die Schaufel als Leitschaufel (13) oder als Laufschaufel (14) einer Rotationsma- sch e (10) ausgebildet ist. 12. A blade according to one of claims 1 to 11, characterized in that the blade is designed as a guide blade (13) or as a moving blade (14) of a rotary mesh (10).
EP01919384A 2000-03-22 2001-03-12 Cooling system for a turbine blade Expired - Lifetime EP1266127B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP01919384A EP1266127B1 (en) 2000-03-22 2001-03-12 Cooling system for a turbine blade

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
EP00106245A EP1136651A1 (en) 2000-03-22 2000-03-22 Cooling system for an airfoil
EP00106245 2000-03-22
PCT/EP2001/002755 WO2001071163A1 (en) 2000-03-22 2001-03-12 Cooling system for a turbine blade
EP01919384A EP1266127B1 (en) 2000-03-22 2001-03-12 Cooling system for a turbine blade

Publications (2)

Publication Number Publication Date
EP1266127A1 true EP1266127A1 (en) 2002-12-18
EP1266127B1 EP1266127B1 (en) 2005-01-12

Family

ID=8168201

Family Applications (2)

Application Number Title Priority Date Filing Date
EP00106245A Withdrawn EP1136651A1 (en) 2000-03-22 2000-03-22 Cooling system for an airfoil
EP01919384A Expired - Lifetime EP1266127B1 (en) 2000-03-22 2001-03-12 Cooling system for a turbine blade

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP00106245A Withdrawn EP1136651A1 (en) 2000-03-22 2000-03-22 Cooling system for an airfoil

Country Status (6)

Country Link
US (1) US6769875B2 (en)
EP (2) EP1136651A1 (en)
JP (1) JP4637437B2 (en)
CN (1) CN1293285C (en)
DE (1) DE50105062D1 (en)
WO (1) WO2001071163A1 (en)

Families Citing this family (59)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6902372B2 (en) * 2003-09-04 2005-06-07 Siemens Westinghouse Power Corporation Cooling system for a turbine blade
JP4191578B2 (en) * 2003-11-21 2008-12-03 三菱重工業株式会社 Turbine cooling blade of gas turbine engine
US6929451B2 (en) 2003-12-19 2005-08-16 United Technologies Corporation Cooled rotor blade with vibration damping device
US7125225B2 (en) 2004-02-04 2006-10-24 United Technologies Corporation Cooled rotor blade with vibration damping device
US7217095B2 (en) * 2004-11-09 2007-05-15 United Technologies Corporation Heat transferring cooling features for an airfoil
US7513745B2 (en) 2006-03-24 2009-04-07 United Technologies Corporation Advanced turbulator arrangements for microcircuits
US20070258814A1 (en) * 2006-05-02 2007-11-08 Siemens Power Generation, Inc. Turbine airfoil with integral chordal support ribs
US7544044B1 (en) * 2006-08-11 2009-06-09 Florida Turbine Technologies, Inc. Turbine airfoil with pedestal and turbulators cooling
US7497655B1 (en) 2006-08-21 2009-03-03 Florida Turbine Technologies, Inc. Turbine airfoil with near-wall impingement and vortex cooling
JP4957131B2 (en) * 2006-09-06 2012-06-20 株式会社Ｉｈｉ Cooling structure
US7857588B2 (en) * 2007-07-06 2010-12-28 United Technologies Corporation Reinforced airfoils
US8257035B2 (en) * 2007-12-05 2012-09-04 Siemens Energy, Inc. Turbine vane for a gas turbine engine
US8348612B2 (en) * 2008-01-10 2013-01-08 General Electric Company Turbine blade tip shroud
US7946817B2 (en) * 2008-01-10 2011-05-24 General Electric Company Turbine blade tip shroud
US8393867B2 (en) 2008-03-31 2013-03-12 United Technologies Corporation Chambered airfoil cooling
CN101981381A (en) 2008-03-31 2011-02-23 川崎重工业株式会社 Cooling structure for gas turbine combustor
US8342797B2 (en) * 2009-08-31 2013-01-01 Rolls-Royce North American Technologies Inc. Cooled gas turbine engine airflow member
US9347324B2 (en) 2010-09-20 2016-05-24 Siemens Aktiengesellschaft Turbine airfoil vane with an impingement insert having a plurality of impingement nozzles
US8777569B1 (en) * 2011-03-16 2014-07-15 Florida Turbine Technologies, Inc. Turbine vane with impingement cooling insert
US20120304654A1 (en) * 2011-06-06 2012-12-06 Melton Patrick Benedict Combustion liner having turbulators
CN102425459B (en) * 2011-11-21 2014-12-10 西安交通大学 Heavy-type combustion engine high-temperature turbine double-medium cooling blade
US20140328669A1 (en) * 2011-11-25 2014-11-06 Siemens Aktiengesellschaft Airfoil with cooling passages
RU2634986C2 (en) * 2012-03-22 2017-11-08 Ансалдо Энерджиа Свитзерлэнд Аг Cooled wall
US9719372B2 (en) 2012-05-01 2017-08-01 General Electric Company Gas turbomachine including a counter-flow cooling system and method
EP2893145B1 (en) * 2012-08-20 2019-05-01 Ansaldo Energia IP UK Limited Internally cooled airfoil for a rotary machine
US9759072B2 (en) 2012-08-30 2017-09-12 United Technologies Corporation Gas turbine engine airfoil cooling circuit arrangement
EP2754856A1 (en) 2013-01-09 2014-07-16 Siemens Aktiengesellschaft Blade for a turbomachine
CN103967531A (en) * 2013-02-01 2014-08-06 西门子公司 Film-cooled turbine blade for fluid machinery
CN103277145A (en) * 2013-06-09 2013-09-04 哈尔滨工业大学 Cooling blade of gas turbine
JP6245740B2 (en) * 2013-11-20 2017-12-13 三菱日立パワーシステムズ株式会社 Gas turbine blade
US10494939B2 (en) 2014-02-13 2019-12-03 United Technologies Corporation Air shredder insert
KR101501444B1 (en) * 2014-04-30 2015-03-12 연세대학교 산학협력단 Gas Turbine Blade Having an Internal Cooling Passage Structure for Improving Cooling Performance
CN106471212A (en) * 2014-06-17 2017-03-01 西门子能源公司 There is leading edge impinging cooling system and the turbine airfoil cooling system of nearly wall impact system
GB201417476D0 (en) * 2014-10-03 2014-11-19 Rolls Royce Plc Internal cooling of engine components
EP3048262A1 (en) * 2015-01-20 2016-07-27 Alstom Technology Ltd Wall for a hot gas channel in a gas turbine
US9850763B2 (en) * 2015-07-29 2017-12-26 General Electric Company Article, airfoil component and method for forming article
US10577947B2 (en) * 2015-12-07 2020-03-03 United Technologies Corporation Baffle insert for a gas turbine engine component
US10422233B2 (en) * 2015-12-07 2019-09-24 United Technologies Corporation Baffle insert for a gas turbine engine component and component with baffle insert
US10337334B2 (en) 2015-12-07 2019-07-02 United Technologies Corporation Gas turbine engine component with a baffle insert
US10280841B2 (en) 2015-12-07 2019-05-07 United Technologies Corporation Baffle insert for a gas turbine engine component and method of cooling
PL232314B1 (en) 2016-05-06 2019-06-28 Gen Electric Fluid-flow machine equipped with the clearance adjustment system
US10309246B2 (en) 2016-06-07 2019-06-04 General Electric Company Passive clearance control system for gas turbomachine
US10392944B2 (en) 2016-07-12 2019-08-27 General Electric Company Turbomachine component having impingement heat transfer feature, related turbomachine and storage medium
US10605093B2 (en) 2016-07-12 2020-03-31 General Electric Company Heat transfer device and related turbine airfoil
EP3472437B1 (en) 2016-07-28 2020-04-15 Siemens Aktiengesellschaft Turbine airfoil with independent cooling circuit for mid-body temperature control
US10465526B2 (en) 2016-11-15 2019-11-05 Rolls-Royce Corporation Dual-wall airfoil with leading edge cooling slot
US10648341B2 (en) 2016-11-15 2020-05-12 Rolls-Royce Corporation Airfoil leading edge impingement cooling
US10767487B2 (en) * 2016-11-17 2020-09-08 Raytheon Technologies Corporation Airfoil with panel having flow guide
US10844724B2 (en) * 2017-06-26 2020-11-24 General Electric Company Additively manufactured hollow body component with interior curved supports
US10450873B2 (en) * 2017-07-31 2019-10-22 Rolls-Royce Corporation Airfoil edge cooling channels
EP3460190A1 (en) * 2017-09-21 2019-03-27 Siemens Aktiengesellschaft Heat transfer enhancement structures on in-line ribs of an aerofoil cavity of a gas turbine
US10787913B2 (en) 2018-11-01 2020-09-29 United Technologies Corporation Airfoil cooling circuit
US10934857B2 (en) 2018-12-05 2021-03-02 Raytheon Technologies Corporation Shell and spar airfoil
US10822963B2 (en) 2018-12-05 2020-11-03 Raytheon Technologies Corporation Axial flow cooling scheme with castable structural rib for a gas turbine engine
US20200182068A1 (en) * 2018-12-05 2020-06-11 United Technologies Corporation Axial flow cooling scheme with structural rib for a gas turbine engine
US11396819B2 (en) * 2019-04-18 2022-07-26 Raytheon Technologies Corporation Components for gas turbine engines
US11371360B2 (en) * 2019-06-05 2022-06-28 Raytheon Technologies Corporation Components for gas turbine engines
DE102020106135B4 (en) * 2020-03-06 2023-08-17 Doosan Enerbility Co., Ltd. FLOW MACHINE COMPONENT FOR A GAS TURBINE, FLOW MACHINE ASSEMBLY AND GAS TURBINE WITH THE SAME
CN114109515B (en) * 2021-11-12 2024-01-30 中国航发沈阳发动机研究所 Turbine blade suction side cooling structure

Family Cites Families (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US429677A (en) 1890-06-10 Whip-socket and rein-holder
US3574481A (en) * 1968-05-09 1971-04-13 James A Pyne Jr Variable area cooled airfoil construction for gas turbines
BE755567A (en) * 1969-12-01 1971-02-15 Gen Electric FIXED VANE STRUCTURE, FOR GAS TURBINE ENGINE AND ASSOCIATED TEMPERATURE ADJUSTMENT ARRANGEMENT
US4118146A (en) * 1976-08-11 1978-10-03 United Technologies Corporation Coolable wall
US4296779A (en) * 1979-10-09 1981-10-27 Smick Ronald H Turbulator with ganged strips
JPS60182304A (en) * 1984-02-29 1985-09-17 Toshiba Corp Cooled blade of gas turbine
US5232343A (en) * 1984-05-24 1993-08-03 General Electric Company Turbine blade
JPS61187501A (en) * 1985-02-15 1986-08-21 Hitachi Ltd Cooling construction of fluid
US5405242A (en) 1990-07-09 1995-04-11 United Technologies Corporation Cooled vane
JPH04259603A (en) * 1991-02-14 1992-09-16 Toshiba Corp Turbine stator blade
JPH05214957A (en) * 1991-11-04 1993-08-24 General Electric Co <Ge> Cooling wing to be made to collide with joining foil insert
US5695321A (en) * 1991-12-17 1997-12-09 General Electric Company Turbine blade having variable configuration turbulators
US5468125A (en) * 1994-12-20 1995-11-21 Alliedsignal Inc. Turbine blade with improved heat transfer surface
DE19634238A1 (en) * 1996-08-23 1998-02-26 Asea Brown Boveri Coolable shovel
WO1998025009A1 (en) 1996-12-02 1998-06-11 Siemens Aktiengesellschaft Turbine blade and its use in a gas turbine system
EP0905353B1 (en) * 1997-09-30 2003-01-15 ALSTOM (Switzerland) Ltd Impingement arrangement for a convective cooling or heating process
SE512384C2 (en) * 1998-05-25 2000-03-06 Abb Ab Component for a gas turbine

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO0171163A1 *

Also Published As

Publication number Publication date
EP1136651A1 (en) 2001-09-26
CN1418284A (en) 2003-05-14
WO2001071163A1 (en) 2001-09-27
CN1293285C (en) 2007-01-03
US6769875B2 (en) 2004-08-03
US20030049127A1 (en) 2003-03-13
DE50105062D1 (en) 2005-02-17
JP2003528246A (en) 2003-09-24
JP4637437B2 (en) 2011-02-23
EP1266127B1 (en) 2005-01-12

Similar Documents

Publication Publication Date Title
EP1266127B1 (en) Cooling system for a turbine blade
DE10001109B4 (en) Cooled shovel for a gas turbine
EP1113145B1 (en) Blade for gas turbines with metering section at the trailing edge
EP1267039B1 (en) Cooling configuration for an airfoil trailing edge
DE4441507C3 (en) Cooled turbine blade
DE602005000449T2 (en) Cooling with microchannels for a turbine blade
DE3789514T2 (en) Cooled gas turbine blade.
DE69823236T2 (en) DEVICE FOR COOLING GAS TURBINE SHOVELS AND METHOD FOR THE PRODUCTION THEREOF
DE2718661C2 (en) Guide vane grille for a gas turbine with an axial flow
DE2930949C2 (en)
DE2241192C3 (en) Hollow gas turbine blade
DE19612840A1 (en) Device and method for cooling a wall surrounded by hot gas on one side
DE1601561C3 (en) Cooled airfoil blade for an axial flow machine
EP1223308A2 (en) Cooling of a turbo machine component
CH628397A5 (en) AIR COOLED TURBINE BLADE.
DE2042947A1 (en) Blade arrangement with cooling device
DE2343673A1 (en) PIN-RIB COOLING SYSTEM
DE2202857B1 (en) Cooled blades for gas turbines
DE3508976C2 (en) Cooled turbine guide vane
DE2241194A1 (en) FLOW MACHINE SHOVEL WITH A WING-SHAPED CROSS-SECTIONAL PROFILE AND WITH A NUMBER OF COOLING DUCTS RUNNING IN THE LENGTH DIRECTION OF THE SHOVEL
EP1668236B1 (en) Combustion chamber comprising a cooling unit and method for producing said combustion chamber
EP2087207B1 (en) Turbine blade
EP1292760B1 (en) Configuration of a coolable turbine blade
EP1192333B1 (en) Component that can be subjected to hot gas, especially a turbine blade
DE2127454A1 (en) Gas turbine

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20020809

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE CH CY DE DK ES FI FR GB GR IE IT LI LU MC NL PT SE TR

RBV Designated contracting states (corrected)

Designated state(s): AT BE CH CY DE FR GB IT LI

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

RBV Designated contracting states (corrected)

Designated state(s): DE FR GB IT

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 FR GB IT

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20050112

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: 50105062

Country of ref document: DE

Date of ref document: 20050217

Kind code of ref document: P

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: GERMAN

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)

Effective date: 20050316

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: 20051013

EN Fr: translation not filed
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: 20111001

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20150513

Year of fee payment: 15

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20160310

Year of fee payment: 16

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: IT

Payment date: 20160329

Year of fee payment: 16

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 50105062

Country of ref document: DE

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20170312

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170312

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170312

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: 20161001