EP1283326B1 - Kühlung einer Turbinenschaufel - Google Patents
Kühlung einer Turbinenschaufel Download PDFInfo
- Publication number
- EP1283326B1 EP1283326B1 EP01119263A EP01119263A EP1283326B1 EP 1283326 B1 EP1283326 B1 EP 1283326B1 EP 01119263 A EP01119263 A EP 01119263A EP 01119263 A EP01119263 A EP 01119263A EP 1283326 B1 EP1283326 B1 EP 1283326B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- blade
- vane
- cooling medium
- cooling
- turbine blade
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
Links
- 238000001816 cooling Methods 0.000 title claims description 74
- 239000002826 coolant Substances 0.000 claims description 93
- 230000007423 decrease Effects 0.000 claims description 8
- 230000008901 benefit Effects 0.000 description 5
- 238000002485 combustion reaction Methods 0.000 description 5
- 230000000694 effects Effects 0.000 description 5
- 230000001965 increasing effect Effects 0.000 description 5
- 238000010276 construction Methods 0.000 description 4
- 238000013461 design Methods 0.000 description 4
- 239000000446 fuel Substances 0.000 description 4
- 239000002184 metal Substances 0.000 description 3
- 238000005266 casting Methods 0.000 description 2
- 230000002708 enhancing effect Effects 0.000 description 2
- 238000002156 mixing Methods 0.000 description 2
- 238000012546 transfer Methods 0.000 description 2
- 230000007704 transition Effects 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 230000003116 impacting effect Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012805 post-processing Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000008646 thermal stress Effects 0.000 description 1
- 238000012549 training Methods 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/187—Convection cooling
- 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
- F05D2260/205—Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes
Definitions
- the invention relates to a turbine blade with a extending along a blade axis, mainly in its longitudinal direction by a cooling medium can be flowed through Airfoil.
- Gas turbines are used in many areas to drive generators or used by work machines. It is the Energy content of a fuel for generating a rotational movement used a turbine shaft.
- the fuel will burned in a combustion chamber, being used by an air compressor compressed air is supplied. That in the combustion chamber produced by the combustion of the fuel, under high Pressure and high temperature working medium is doing via a turbine downstream of the combustion unit led, where it relaxes work.
- For guiding the flow medium in the turbine unit are also usually between adjacent blade rows with the turbine housing connected Leitschaufelschschsch arranged.
- the turbine blades, in particular the guide vanes usually have for suitable guidance of the working medium along a blade axis extended on, on the end for attachment of the turbine blade at the respective Carrier body a transverse to the blade axis horrrekkende Platform can be formed.
- the components and components exposed to this high exposed to thermal loads are usually one Cooling of the affected components, in particular of Runners and / or vanes of the turbine unit, provided.
- the turbine blades are therefore usually designed coolable, in particular, an effective and reliable Cooling seen in the direction of flow of the working medium first rows of blades should be ensured.
- For cooling usually has the respective turbine blade one integrated into the airfoil or the blade profile Cooling medium channel, from which a cooling medium targeted in particular the thermally loaded zones of the turbine blade can be supplied.
- cooling air As a cooling medium usually cooling air is used. This usually becomes the respective turbine blade in the way of an open cooling over an integrated one Cooling medium channel supplied. After exiting the turbine blade the cooling air is in the process with that in the turbine unit mixed working medium.
- the design performance However, such a cooled gas turbine is limited, especially because of the limited mechanical Resilience of individual components of the gas turbine one further increase in performance usually only can be reached by an increased fuel supply. These in turn requires a comparatively increased need for Cooling medium for cooling the turbine blades, in turn Losses in the available compressor mass flow means. These Losses can only be tolerated to a limited extent become. Moreover, it can also be used in gas turbines with regard to a required safety will be necessary, a mixing from flowing out of the turbine blade cooling medium and prevent the turbine unit flowing through the working medium.
- the invention is therefore based on the object, a turbine blade of the type mentioned above for which Relatively simple means a reliable and effective closed cooling, especially using of cooling air as the cooling medium is enabled.
- the invention is based on the consideration that a effective cooling for a turbine blade in particular with a flat action on the wall to be cooled of the blade with cooling medium can be achieved. It was recognized that such a surface admission of a targeted Supply of the cooling medium to the wall and a Guide the cooling medium along this required. This is achievable by a separate inflow and outflow channel is provided for cooling medium. Starting from this Division of the cooling medium channel is the admission the wall of the airfoil to be cooled in the way that the cooling medium in the course of his crossing of the Flowed in the outflow channel in a transverse direction becomes.
- the guidance of the cooling medium mainly in the longitudinal direction of the blade allows compliance particularly short and thus loss-reduced flow paths for the Coolant flow.
- This main flow direction is changed only in the area in a transverse direction in which a such change of targeted and effective cooling is used. Inevitable flow losses are thus at a low level held.
- the inflow channel can be selected, especially thermally highly loaded areas of the turbine blade assigned Make outlet openings for cooling medium to transfer into have the discharge channel.
- the inflow passage in about evenly distributed over its length to be cooled Inner wall of the airfoil facing outlet openings for the cooling medium. This way is special simply a flat cooling of the blade can be achieved.
- the cooling can be done by means of a so-called impingement cooling take place, one having the outlet openings Wall of the inflow channel serves as an impact cooling wall, with the on she encounters impinging cooling medium in intensive contact and then via the outlet openings for passage into the Outflow channel can be derived.
- the passage of the cooling medium to the inner wall to be cooled of the airfoil takes place in the transverse direction purposeful and enhancing the cooling effect by the or - with several internal walls to be cooled - each to be cooled Inner wall of the airfoil each with the cooling medium conductive, provided transversely to the blade axis ribs is. These ribs also have an additional cooling rib effect result and thus further improve the cooling.
- the inflow channel takes the free cross-section the inflow channel in the blade in the longitudinal direction preferably from.
- the fact is taken into account, that in the course of the inflow channel an increasing part of Cooling medium has already left the inflow and in the Outflow channel has passed.
- the turbine blade particularly advantageous if the free cross-section of the inflow channel in the airfoil in its Linear decreases linearly.
- the inflow channel For example, very simple from flat metal plates be formed.
- free Volume flow of cooling medium through the turbine blade through takes the free cross section of the discharge channel in the blade in the longitudinal direction corresponding to the decrease of free cross section of the inflow channel to.
- the cooling medium leaves the inflow is the free cross-section the Anströmkanals reduced and at the same time in corresponding dimension of the free cross section of the outflow channel increased for outflowing cooling medium. This can be done in the Course of the outflow additionally in these trespassing Cooling medium without hindrance be removed quickly.
- a very simple construction of inflow and / or outflow channel for example, from flat plates results when the inflow and / or the outflow channel parallel to the longitudinal direction of the airfoil and perpendicular to the to be cooled Inner wall of the airfoil according to an advantageous Training has a triangular cross-section.
- the first and the second inflow channel open preferably in a common outflow channel for Cooling medium.
- the outflow channel for example, low in a central region of the airfoil.
- the inflow channel is at its one entrance surface for cooling medium remote from the end and / or the discharge channel facing away from its one exit surface for cooling medium Start closed, creating a simple construction and a trouble-free supply and discharge of the cooling medium to the and is enabled by the turbine blade.
- An advantage is a turbine blade, in which at the Airfoil at thedemediumabströmseite a transversely formed to the blade axis platform is formed when the platform one connected to the inflow, with Has cooling medium acted upon cooling chamber. To this Way is the inflow, the cooling medium to be cooled Inner wall of the airfoil feeds, the design of the Turbine blade considerably simpler at the same time as a feed channel used by cooling medium to the cooling chamber of the platform.
- each cooling chamber advantageously poured into the respective platform and outwards completed by a cover plate.
- the cooling chamber be produced directly during the casting of the turbine blade, so that a post-processing of the casting is not required is.
- For reliable completion of the respective cooling chamber To the outside is only the attachment of the respective Cover plate required.
- a particularly reliable cooling of the respective structural parts with cooling medium can be reached by means of an impingement cooling.
- the or each cooling chamber is advantageous in one Floor area arranged at a distance from the chamber floor Impact cooling plate provided.
- the impingement cooling plate is in the essentially formed as a perforated plate, wherein on the Impact cooling plate impacting cooling medium with this in particular intensive contact occurs and then on the perforation can be derived.
- a reliable cooling medium discharge is in a further advantageous embodiment a more limited by the chamber bottom and the baffle plate Outflow space of the cooling chamber connected to the outflow channel. Accordingly, for a reliable supply of cooling medium to the cooling chamber according to another advantageous embodiment through the cover plate and the baffle cooling plate limited inflow space of the cooling chamber connected to the inflow channel.
- the turbine blade is preferably as a guide vane for a gas turbine, in particular for a stationary gas turbine, educated.
- the advantages achieved by the invention are in particular in that by providing an inflow and an outflow channel in the turbine blade, the cooling medium when crossing from the inflow into the outflow channel in a transverse direction is guided along the inside of the airfoil, whereby allows a two-dimensional loading of the airfoil is and results in a particularly effective cooling.
- the Turbine blade is doing with relatively little effort producible, in particular, it is important that Inlet and outlet channel as simple inserts in the airfoil can be mounted, can be formed.
- inclusion of concepts a closed cooling with air as the cooling medium allows.
- the turbine blade 1 according to FIG. 1 has an airfoil 2, which extends along a blade axis 4.
- the Airfoil 2 is for the appropriate influence of a in a dedicated turbine unit flowing working medium arched and / or curved.
- the turbine blade 1 is used as a guide vane for one here not shown gas turbine and in the manner of a closed Cooling as coolable with cooling air as the cooling medium Turbine blade formed.
- the blade 2 mainly in its longitudinal direction L of cooling medium K. permeable, wherein the cooling medium K from ademediumanströmseite AS forth in the blade 2 and enters ademediumabströmseite BS from this again emerges.
- a inflow channel 6 in the cooling medium K of thedemediumanströmseite AS ago can come forth, and a discharge channel 8 for cooling medium K out.
- the inflow channel 6 is on the one hand by a flat, closed wall 10, the diagonal in the airfoil 2, and on the other hand a flat, outlet openings 12 for cooling medium K having Wall 14 limited; the closed wall 10 and the outlet openings 12 having wall 14 can of sheet metal plates be formed.
- the outlet openings 12, the in distributed approximately uniformly over the length 1 of the inflow channel 6 are, having wall 14 is parallel to a to be cooled Inner wall 16 of the airfoil 2 arranged so that between this inner wall 16 and the aforementioned wall 14th the inflow channel 6, an overflow channel 18 is formed.
- In the overflow 18 is from the inflow duct 6 in the Outflow channel 8 passing cooling medium K in a transverse direction Q of the airfoil 2 on the inner wall to be cooled 16 of the airfoil 2 along.
- At this inner wall 16 are in the transverse direction Q of the airfoil 2 extending Ridges 20 are arranged, which are the flow direction of the override cooling medium K and also in addition serve as cooling fins for the airfoil 2.
- the outflow channel 8 is limited on the one hand from the plane, closed wall 10, diagonally in the blade 2 extends and the inflow channel 6 of the Outflow channel 8 separates, and on the other hand by an inner wall 22 of the airfoil 2, which is the inner wall to be cooled 16 opposite.
- the arrangement is chosen such that the free cross section 40 of the inflow channel 6 in the blade 2 in the longitudinal direction thereof L decreases linearly. At the same time increases with the measure this decrease in the free cross section 52 of the outflow channel. 8 in the blade 2 in the longitudinal direction L to. Furthermore Both the inflow 6 and the outflow channel 8 are parallel to the longitudinal direction L of the airfoil 2 and perpendicular to the inner wall 16 to be cooled a triangular cross-section on.
- the overflow of the cooling medium K from the inflow channel 6 in the discharge channel 8 illustrates Figure 2
- the a cross section along line II - II through the turbine blade 1 represents FIG.
- the outlet openings 12 having wall 14 and the opposite of this, closed wall 10 has the inflow channel. 6 two connecting the latter walls 10, 14, further Walls 24, 26, so that the inflow duct 6 except one Entry surface and the outlet openings 12 are closed is.
- the other walls 24, 26 each of a sheet metal plate are formed.
- inflowing cooling medium K leaves this channel on the Outlet openings 12 and then encounters the inner wall 16 of the airfoil 2.
- This results in an impact cooling effect which is further enhanced by the fact that the cooling medium K - additionally guided by ribs 20 - on the inner wall 16 of the airfoil 2 in the transverse direction Q is guided along and thereby by overflow channels 18, 28, 30 enters the discharge channel 8; while the cooling medium flows K around at least part of the inflow channel 6 around and passes then into the discharge channel 8, through which it turns in Flows longitudinally of the airfoil 2.
- Due to the the inner wall 16 of the airfoil 2 arranged ribs 20 results in a cooling effect enhancing cooling fin effect.
- FIG. 3 Another turbine blade 1 with an airfoil 2 shows in a partially cut, perspective view Figure 3.
- the airfoil 2 here has a first and a second Anströmkanal 6, 32 for cooling medium K, wherein the inflow channels 6, 32 relative to the blade axis 4 symmetrical to each other are arranged and the airfoil 2 in his Pull longitudinal direction L through a length 1.
- Cooling medium K occurs at thedemediumanströmseite AS of the airfoil. 2 in the inflow channels 6, 32, flows through the airfoil 2 in its longitudinal direction L in both inflow channels 6, 32nd and leaves it via outlet openings 12, which are shown in FIG. 3 for the sake of clarity, only in the first inflow channel 6 are shown.
- the cooling medium K flows in one perpendicular to the longitudinal direction L of the airfoil 2 extending Transverse Q each on an inner wall to be cooled 16, 36 of the airfoil 2 along.
- These inner walls 16, 36 are the outlet openings 12 of the inflow channels 6, 32 arranged opposite and with - in Figure 3 of For clarity, only on the first to be cooled inner wall 16 - ribs 20 for guiding the cooling medium K provided.
- the flow along the to be cooled inner walls 16, 36 takes place during a transition of the cooling medium K from the inflow channels 6, 32 in a common outflow channel 8 for cooling medium K, the center between the Anströmkanälen 6, 32 is arranged. Via the outflow channel 8 becomes the cooling medium K in the longitudinal direction L of the airfoil 2 whosedemediumabströmseite BS supplied.
- Point to theRiemediumanströmseite AS of the airfoil the inflow channels 6, 32 each have an entry surface 34, 38 forming free cross section of equal size.
- This free cross-section of the inflow channels 6, 32 increases in the airfoil 2 in the longitudinal direction L from linear, so that at half length 1/2 of the free cross section 40, 42 also respectively is halved when the inflow channels 6, 32 at their the Inlet surface 34, 38 for cooling medium K opposite end 44, 46 have no free cross-section. That means at the same time that the inflow channels at each of this end 44, 46th are closed.
- the discharge channel 8 is at its one of a formed free cross section exit surface 48 for cooling medium K facing away beginning 50 closed and has no there free cross section on.
- the free cross section of the outflow channel 8 in the blade 2 takes in the longitudinal direction L corresponding to the decrease of the free cross section of the Anströmkanäle 6, 32 to. Therefore, the free cross section 52 the outflow channel 8 at half the length 1/2 of the airfoil 2 an area which is the sum of the free cross sections 40, 42 of the inflow channels 6, 32 corresponds at this point. In order to is a free outflow of the cooling medium K ensured.
- FIG. 1 Another turbine blade 1, in particular a vane for a gas turbine, with a two re a blade axis 4 symmetrically arranged inflow channels 6, 32 for cooling medium K having blade 2 shows Figure 4 in a longitudinal section.
- ademediumanströmseite AS a transverse to the Blade axis 4 extending first platform 62 integrally formed, which forms a head plate.
- ademediumabströmseite BS is a transverse to the blade axis 4 extending, a foot plate forming second platform 64 is formed.
- cooling medium K enters thedemediumanströmseite AS in the first Platform 62 and in one of a cover 66 shielded central, with the inflow channels 6, 32 connected Area of the airfoil 2 a.
- a cooling chamber 68 of the first Platform 62 is connected to the outflow channel 8, so that already used for cooling the first platform 62 Coolant K through the discharge channel 8 immediately can be led out of the blade 2.
- the the inflow channels 6, 32 supplied cooling medium K leaves These inflow channels 6, 32 either through outlet openings 12, 70 in to be cooled inner walls 16, 36 of the airfoil 2 facing walls 14, 72 or through at the respective Entry surface for cooling medium K opposite ends of the Anströmkanäle 6, 32 provided transitions 74, 76 to a Cooling chamber 78 of the second platform 64.
- the cooling medium K the passes through the outlet openings 12, 70, is in a transverse direction Q at the to be cooled, ribs 20, 80 having Inner walls 16, 36 of the airfoil 2 along out, then enters the discharge channel 8 and leaves over this the blade 2 at thedemediumabströmseite BS.
- the cooling chambers 68, 78 of the platforms 62, 64 are in this cast in and outwards in each case via a cover plate 82, 84 completed.
- the cooling chambers 68, 78 each in its bottom region with a distance to the chamber bottom 86, 88 arranged impingement cooling plate 90, 92 provided.
- a discharge space 94 present through the chamber floor 86 and the Impact cooling plate 90 is limited and connected to the discharge channel 8 is.
- the cooling chamber 78 of the second Platform 64 on a Anströmraum 96 through the cover plate 84 and the impingement cooling plate 92 is limited and to the Anströmkanäle 6, 32 is connected. This way you can the Anströmraum 96 are fed by the inflow channels 6, 32, through walls 10, 98 separated from the discharge channel 8 are.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
- Figur 1
- eine Turbinenschaufel in einem Teil-Längsschnitt,
- Figur 2
- einen Querschnitt durch die Turbinenschaufel nach Figur 1,
- Figur 3
- eine andere Turbinenschaufel in teilgeschnittener perspektivischer Ansicht und
- Figur 4
- eine weitere Turbinenschaufel in einem Längsschnitt.
Claims (15)
- Turbinenschaufel (1) mit einem sich entlang einer Schaufelachse (4) erstreckenden, hauptsächlich in seiner Längsrichtung (L) von einem Kühlmedium (K) durchströmbaren Schaufelblatt (2), wobei im Schaufelblatt (2) im wesentlichen über seine gesamte Länge (1) ein Anström- (6) und ein Abströmkanal (8) für Kühlmedium (K) geführt sind und der Anström- (6) und der Abströmkanal (8) kühlmediumseitig derart miteinander verbunden sind, daß von dem Anström- (6) in den Abströmkanal (8) übertretendes Kühlmedium (K) in einer Querrichtung (Q) an einer zu kühlenden Innenwandung (16) des Schaufelblattes (2) entlang geführt ist,
wobei der Anströmkanal (6) in etwa gleichmäßig über seine Länge verteilt der zu kühlenden Innenwandung (16) des Schaufelblattes (2) zugewandte Austrittsöffnungen (12) für das Kühlmedium (K) aufweist,
dadurch gekennzeichnet, dass
dass durch mehrere, in Querrichtung (Q) verteilte Austrittsöffnungen (12) eine flächigen Beaufschlagung der Innenwandung (16) mit Kühlmedium erzielbar und
die oder jede zu kühlenden Innenwandung (16) des Schaufelblattes (2) jeweils mit das Kühlmedium (K) leitenden, quer zur Schaufelachse (4) angeordneten Rippen (20, 80) versehen ist. - Turbinenschaufel nach Anspruch 1, bei der der freie Querschnitt (40) des Anströmkanals (6) im Schaufelblatt (2) in dessen Längsrichtung (L) abnimmt.
- Turbinenschaufel nach Anspruch 2, bei der der freie Querschnitt (40) des Anströmkanals (6) im Schaufelblatt (2) in dessen Längsrichtung (L) linear abnimmt.
- Turbinenschaufel nach Anspruch 2 oder 3, bei der der freie Querschnitt (52) des Abströmkanals (8) im Schaufelblatt (2) in dessen Längsrichtung (L) entsprechend der Abnahme des freien Querschnitts (40) des Anströmkanals (6) zunimmt.
- Turbinenschaufel nach einem der vorhergehenden Ansprüche, bei der der Anströmkanal (6) und/oder der Abströmkanal (8) parallel zur Längsrichtung (L) des Schaufelblattes (2) und senkrecht zu der zu kühlenden Innenwandung (16) des Schaufelblattes (2) einen dreieckigen Querschnitt aufweist.
- Turbinenschaufel nach einem der vorhergehenden Ansprüche, bei der bezogen auf die Schaufelachse (4) symmetrisch zu dem ersten Anströmkanal (6) ein zweiter Anströmkanal (32) für Kühlmedium (K) zur Kühlung einer weiteren Innenwandung (36) des Schaufelblattes (2) angeordnet ist.
- Turbinenschaufel nach Anspruch 6, bei der der erste und der zweite Anströmkanal (6, 32) in einen gemeinsamen Abströmkanal (8) für Kühlmedium (K) münden.
- Turbinenschaufel nach einem der vorhergehenden Ansprüche, bei der der Anströmkanal (6, 32) an seinem einer Eintrittsfläche (34, 38) für Kühlmedium (K) abgewandten Ende (44, 46) und/oder der Abströmkanal (8) an seinem einer Austrittsfläche (48) für Kühlmedium (K) abgewandten Anfang (50) verschlossen ist.
- Turbinenschaufel nach einem der vorhergehenden Ansprüche, bei der an das Schaufelblatt (2) an dessen Kühlmediumabströmseite (BS) eine sich quer zur Schaufelachse (4) erstreckende Plattform (64) angeformt ist, die eine an den Anströmkanal (6, 32) angeschlossene, mit Kühlmedium (K) beaufschlagbare Kühlkammer (78) aufweist.
- Turbinenschaufel nach einem der vorhergehenden Ansprüche, bei der an das Schaufelblatt (2) an dessen Kühlmediumanströmseite (AS) eine sich quer zur Schaufelachse (4) erstreckende Plattform (62) angeformt ist, die eine an den Abströmkanal (8) angeschlossene, mit Kühlmedium (K) beaufschlagbare Kühlkammer (68) aufweist.
- Turbinenschaufel nach Anspruch 9 oder 10, bei der die oder jede Kühlkammer (68, 78) in die jeweilige Plattform (62, 64) eingegossen und nach außen über ein Abdeckblech (82, 84) abgeschlossen ist.
- Turbinenschaufel nach einem der Ansprüche 9 bis 11, bei der die oder jede Kühlkammer (68, 78) in einem Bodenbereich mit einem beabstandet zum Kammerboden (86, 88) angeordneten Prallkühlblech (90, 92) versehen ist.
- Turbinenschaufel nach Anspruch 12, bei der ein durch den Kammerboden (86) und das Prallkühlblech (90) begrenzter Abströmraum (94) der Kühlkammer (68) an den Abströmkanal (8) angeschlossen ist.
- Turbinenschaufel nach Anspruch 12, bei der ein durch das Abdeckblech (84) und das Prallkühlblech (92) begrenzter Anströmraum (96) der Kühlkammer (78) an den Anströmkanal (6, 32) angeschlossen ist.
- Turbinenschaufel nach einem der vorhergehenden Ansprüche, die als Leitschaufel für eine Gasturbine ausgebildet ist.
Priority Applications (6)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
ES01119263T ES2254296T3 (es) | 2001-08-09 | 2001-08-09 | Enfriamiento de un alabe de turbina. |
EP01119263A EP1283326B1 (de) | 2001-08-09 | 2001-08-09 | Kühlung einer Turbinenschaufel |
DE50108466T DE50108466D1 (de) | 2001-08-09 | 2001-08-09 | Kühlung einer Turbinenschaufel |
JP2002226904A JP4249959B2 (ja) | 2001-08-09 | 2002-08-05 | タービン翼 |
CNB02128539XA CN1318733C (zh) | 2001-08-09 | 2002-08-09 | 燃气轮机叶片/导向叶片 |
US10/214,760 US6905301B2 (en) | 2001-08-09 | 2002-08-09 | Turbine blade/vane |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP01119263A EP1283326B1 (de) | 2001-08-09 | 2001-08-09 | Kühlung einer Turbinenschaufel |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1283326A1 EP1283326A1 (de) | 2003-02-12 |
EP1283326B1 true EP1283326B1 (de) | 2005-12-21 |
Family
ID=8178287
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP01119263A Expired - Lifetime EP1283326B1 (de) | 2001-08-09 | 2001-08-09 | Kühlung einer Turbinenschaufel |
Country Status (6)
Country | Link |
---|---|
US (1) | US6905301B2 (de) |
EP (1) | EP1283326B1 (de) |
JP (1) | JP4249959B2 (de) |
CN (1) | CN1318733C (de) |
DE (1) | DE50108466D1 (de) |
ES (1) | ES2254296T3 (de) |
Families Citing this family (24)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7121796B2 (en) * | 2004-04-30 | 2006-10-17 | General Electric Company | Nozzle-cooling insert assembly with cast-in rib sections |
ES2312890T3 (es) * | 2004-07-26 | 2009-03-01 | Siemens Aktiengesellschaft | Elemento enfriado de una turbomaquina y procedimiento de moldeo de este elemento enfriado. |
FR2893080B1 (fr) * | 2005-11-07 | 2012-12-28 | Snecma | Agencement de refroidissement d'une aube d'une turbine, aube de turbine le comportant, turbine et moteur d'aeronef en etant equipes |
CN1318735C (zh) * | 2005-12-26 | 2007-05-30 | 北京航空航天大学 | 一种适用于燃气涡轮发动机的脉动冲击冷却叶片 |
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-
2001
- 2001-08-09 DE DE50108466T patent/DE50108466D1/de not_active Expired - Lifetime
- 2001-08-09 ES ES01119263T patent/ES2254296T3/es not_active Expired - Lifetime
- 2001-08-09 EP EP01119263A patent/EP1283326B1/de not_active Expired - Lifetime
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2002
- 2002-08-05 JP JP2002226904A patent/JP4249959B2/ja not_active Expired - Fee Related
- 2002-08-09 US US10/214,760 patent/US6905301B2/en not_active Expired - Lifetime
- 2002-08-09 CN CNB02128539XA patent/CN1318733C/zh not_active Expired - Fee Related
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JP4249959B2 (ja) | 2009-04-08 |
US6905301B2 (en) | 2005-06-14 |
DE50108466D1 (de) | 2006-01-26 |
JP2003056305A (ja) | 2003-02-26 |
ES2254296T3 (es) | 2006-06-16 |
US20030035726A1 (en) | 2003-02-20 |
CN1318733C (zh) | 2007-05-30 |
CN1405431A (zh) | 2003-03-26 |
EP1283326A1 (de) | 2003-02-12 |
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