WO2001055559A1 - Porous turbine blades and turbine equipped with blades of this type - Google Patents
Porous turbine blades and turbine equipped with blades of this type Download PDFInfo
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- WO2001055559A1 WO2001055559A1 PCT/EP2001/000239 EP0100239W WO0155559A1 WO 2001055559 A1 WO2001055559 A1 WO 2001055559A1 EP 0100239 W EP0100239 W EP 0100239W WO 0155559 A1 WO0155559 A1 WO 0155559A1
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- turbine
- blades
- blade
- microholes
- steam
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/32—Collecting of condensation water; Drainage ; Removing solid particles
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- 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
- F01D5/141—Shape, i.e. outer, aerodynamic form
- F01D5/145—Means for influencing boundary layers or secondary circulations
Definitions
- the invention relates to a turbine, in particular to a gas or steam turbine, with guide vanes arranged in a turbine housing and with rotor blades fastened to a turbine shaft.
- the working means for the gas turbine is obtained by burning a fuel, e.g. Petroleum or natural gas, produced by supplying compressed air, whereby the working fluid temperature is currently around 1200 ° C to 1400 ° C.
- a fuel e.g. Petroleum or natural gas
- steam turbines previously used can achieve a system efficiency of approx. 38% to 40% at a live steam temperature of approx. 540 ° C.
- a live steam temperature of approx. 540 ° C.
- its turbine shaft and in particular the blade roots of rotor blades can be cooled by means of cooling steam.
- the invention is based on the object of constructively developing a turbine, in particular a gas or steam turbine, in such a way that its efficiency is increased.
- This object is achieved according to the invention by the features of claim 1.
- at least some of the guide and / or rotor blades of the turbine are provided with a large number of microholes.
- the invention is based on the knowledge that the efficiency of both a gas turbine and a steam turbine is limited in particular by the fact that the flow of the working medium along the blade surface is not always ideally laminar. In particular in the boundary layer near the surface, vortices and thus a turbulent flow of the working medium form, which lead to a conversion of the kinetic energy of the working medium into heat. A not inconsiderable proportion of flow losses occurring in such a turbine can be attributed to this effect.
- the invention is based on the consideration that such eddies or turbulent flows on the blade surface can be avoided or at least reduced if a part of the working medium is suctioned off at the boundary layer near the surface and a laminar flow of the working medium is thereby practically forced on the blade surface , With this measure, the efficiency of the turbine can be increased by a few percentage points.
- both the guide blades provided with microholes and the rotor blades provided with microholes are hollow. Part of the working medium flowing past the blade surface is thus sucked away from the blade surface into the interior of the hollow blade.
- the guide vanes are expediently connected to an outer suction channel, preferably provided in or on the turbine housing, while the interior of the hollow rotor blades is connected to the interior of a hollow turbine shaft.
- the vacuum required for suction is advantageously generated by the fact that the microholes are connected to a turbine part, which has a relatively low working fluid pressure flowing around it. A pressure drop required for this is already present due to the expansion of the working fluid in the turbine between the turbine inlet and the turbine outlet and is therefore available for extraction.
- the microholes are designed as through-holes which enter the turbine blade on the surface side facing the working fluid flow and exit on the opposite rear side of the blade.
- the pressure drop between the front and rear of the turbine blade is used for the suction.
- the necessary suction of work fluid flowing along the respective turbine blade is preferably generated in that the microholes have a connection to a turbine part which is surrounded by work fluid of comparatively low pressure. An additional unit for suction can thus be saved. Exemplary embodiments of the invention are explained in more detail below with reference to a drawing. In it show:
- FIG. 1 shows a hollow turbine blade provided with microholes
- FIG. 2 schematically shows a turbine provided with a number of such turbine blades with an outer suction duct and with a hollow turbine shaft
- FIG. 3 shows a steam-cooled steam turbine with turbine blades provided with through-holes in a representation according to FIG.
- the turbine blade 1 shown in FIG. 1 with a blade leaf 2 curved like a banana and a blade root 3 like a hammer head is hollow.
- the interior 4 of the airfoil 2 and the interior 5 of the blade root 3 are connected to one another.
- the turbine blade 1 is provided in the region of the airfoil 2 with a large number of microholes 6 which enter the blade surface 7 and open into the interior 4.
- a portion ⁇ I M of the working medium or working medium M flowing along its blade surface 7 is sucked off via the microholes in the direction of arrow 8 into the interior 4 of the turbine blade 1 and flows out in the direction of arrow 9 via the interior 5 of the blade root 3 the turbine blade 1.
- a number of such turbine blades 1, which are provided with microholes 6, are used as guide blades 1 a and as blades 1 b.
- the guide vanes la are in a manner not shown on the respective blade root 3 in Turbine housing 11 anchored, while the blades lb are attached to a hollow turbine shaft 12.
- the inner spaces 4, 5 of the guide vanes 1 a are connected to a suction duct 13 provided in the outer region of the turbine housing 11.
- the inner spaces 4, 5 of the rotor blades 1b are connected to a cavity 14 of the turbine shaft 12, which cavity also serves as a suction channel.
- the portion m M of the working medium M flowing through the micro-holes 6 of the guide vanes la m through the discharge channel 13 is preferably fed back to the turbine 10 and introduced into its working space 15.
- the suction channel 13 is connected via a number of openings 16 to the working space 15 at a point at which the pressure pi of the working medium M is less than the pressure p 2 of the working medium M in the region of its entry via the microholes 6 in the corresponding guide vanes la.
- the extraction of the portion m M of the working medium M via the micro-holes 6 of the rotor blades 1b is carried out analogously, in that this portion m M of the working medium M is introduced through the corresponding guide blades 1b and through the turbine shaft 14 at a corresponding point m into the working space 15 of the turbine 10.
- the turbine shaft 14 also has corresponding openings 17 in the region of comparatively low medium pressure pi.
- FIG 3 shows a steam turbine 10 which is cooled by means of cow steam KD and which is fed fresh steam FD on the inlet side with a steam steam temperature T FD of, for example, 600 ° C. to 1000 ° C.
- T FD fresh steam temperature
- the hollow guide vanes la are supplied on the one hand via the turbine housing 11 and on the other hand via the hollow turbine shaft 14 the rotor blades 14b of the cow steam KD.
- the cooling steam KD flowing through the turbine blades la, lb enters the working space 15 of the turbine through corresponding openings in the turbine blades la, lb Steam turbine 10 ⁇ out and mixes there with the live steam FD relaxing along the rows of blades. This leaves the turbine 10 as exhaust steam AD.
- the steam-cooled turbine blades la, lb are followed in the flow direction 18 of the live steam FD along the turbine shaft 14 by further rows of blades with guide and rotor blades la and lb, which in turn are provided with microholes 6.
- the micro-holes are advantageously carried out at this expedient From guide die in the form of through holes 6 ⁇ , which pass through the turbine blades la lb.
- the passage of a portion ⁇ I of live steam FD through these through holes 6 ⁇ is due to the pressure difference between the steam pressure p 2 on the inflow side of the corresponding turbine blades la, lb and the pressure on the outflow or rear side of the corresponding turbine blade la, lb pi forced.
- the size of the micro-holes 6, 6 x is suitably in the u - region, wherein the inner diameter d of the micro holes is 6.6, for example 0.05 mm.
- the distance a between adjacent microholes 6, 6 is expediently less than 1 mm.
- the number of microholes 6, 6 provided on the respective blade surface 7 is in the order of 10 2 to 10 5, depending on the size of the respective airfoil 2.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
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- Fluid Mechanics (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Beschreibungdescription
PORÖSE TURBINENSCHAUFEL UND EINE MIT SOLCHEN SCHAUFELN AUSGERÜSTETE TURBINEPOROUS TURBINE BLADE AND A TURBINE EQUIPPED WITH SUCH BLADES
Die Erfindung bezieht sich auf eine Turbine, insbesondere auf eine Gas- oder Dampfturbine, mit in einem Turbinengehäuse angeordneten Leitschaufeln und mit an einer Turbinenwelle befestigten Laufschaufeln.The invention relates to a turbine, in particular to a gas or steam turbine, with guide vanes arranged in a turbine housing and with rotor blades fastened to a turbine shaft.
Mit in bisherigen Kraftwerksanlagen eingesetzten Gasturbinen kann derzeit ein Anlagenwirkungsgrad bis ca. 40% erreicht werden. Das Arbeitsmittel für die Gasturbine wird durch Verbrennen eines Brennstoffs, z.B. Erdöl oder Erdgas, unter Zufuhr verdichteter Luft erzeugt, wobei die Arbeitsmitteltempe- ratur derzeit bei etwa 1200°C bis 1400°C liegt.With gas turbines used in previous power plants, a plant efficiency of up to approx. 40% can currently be achieved. The working means for the gas turbine is obtained by burning a fuel, e.g. Petroleum or natural gas, produced by supplying compressed air, whereby the working fluid temperature is currently around 1200 ° C to 1400 ° C.
Demgegenüber kann mit bisher eingesetzten Dampfturbinen bei einer Frischdampftemperatur von ca. 540°C ein Anlagenwirkungsgrad von ca. 38% bis 40% erreicht werden. Wie aus der WO 97/25521 bekannt, können zur Erhöhung des Frischdampfzustandes mit einer angestrebten Frischdampftemperatur von 600 °C und einem angestrebten Frischdampfdruck von 270 bar und damit zur Steigerung des Wirkungsgrades einer Dampfturbine deren Turbinenwelle und insbesondere die Schaufelfüße von Laufschaufeln mittels Kühldampf gekühlt werden.In contrast, steam turbines previously used can achieve a system efficiency of approx. 38% to 40% at a live steam temperature of approx. 540 ° C. As is known from WO 97/25521, in order to increase the live steam state with a desired live steam temperature of 600 ° C. and a desired live steam pressure of 270 bar and thus to increase the efficiency of a steam turbine, its turbine shaft and in particular the blade roots of rotor blades can be cooled by means of cooling steam.
Mit einer kombinierten Gas- und Dampfturbinenanlage, bei der die im entspannten Arbeitsmittel aus der Gasturbine enthaltene Wärme zur Erzeugung von Dampf für die in einen Wasser- Dampf-Kreislauf geschaltete Dampfturbine genutzt wird, wird derzeit bei einer Frischdampftemperatur von ca. 540°C und einem Frischdampfdruck von z.B. 120bar ein Anlagenwirkungsgrad von etwa 55% bis 60% erreicht.With a combined gas and steam turbine system, in which the heat contained in the relaxed working fluid from the gas turbine is used to generate steam for the steam turbine connected to a water-steam cycle, a fresh steam temperature of approx. 540 ° C and a Live steam pressure of e.g. 120bar a system efficiency of around 55% to 60% is achieved.
Der Erfindung liegt die Aufgabe zugrunde, eine Turbine, insbesondere eine Gas- oder Dampfturbine, konstruktiv derart weiterzubilden, dass deren Wirkungsgrad erhöht ist. Diese Aufgabe wird erfindungsgemäß gelöst durch die Merkmale des Anspruchs 1. Dazu sind zumindest einige der Leit- und/- oder Laufschaufeln der Turbine mit einer Vielzahl von Mikro- löchern versehen.The invention is based on the object of constructively developing a turbine, in particular a gas or steam turbine, in such a way that its efficiency is increased. This object is achieved according to the invention by the features of claim 1. For this purpose, at least some of the guide and / or rotor blades of the turbine are provided with a large number of microholes.
Die Erfindung geht dabei von der Erkenntnis aus, dass der Wirkungsgrad sowohl einer Gasturbine als auch einer Dampfturbine insbesondere dadurch begrenzt wird, dass die Strömung des Arbeitsmediums entlang der Schaufeloberfläche nicht immer ideal laminar ist. Insbesondere in der oberflächennahen Grenzschicht bilden sich Wirbel und somit eine turbulente Strömung des Arbeitsmediums aus, die zu einer Umwandlung der kinetischen Energie des Arbeitsmediums in Wärme führen. Ein nicht unerheblicher Anteil an in einer derartigen Turbine auftretenden Strömungsverluste ist auf diesen Effekt zurückzuführen.The invention is based on the knowledge that the efficiency of both a gas turbine and a steam turbine is limited in particular by the fact that the flow of the working medium along the blade surface is not always ideally laminar. In particular in the boundary layer near the surface, vortices and thus a turbulent flow of the working medium form, which lead to a conversion of the kinetic energy of the working medium into heat. A not inconsiderable proportion of flow losses occurring in such a turbine can be attributed to this effect.
Die Erfindung liegt nun die Überlegung zugrunde, dass derar- tige Wirbel oder turbulente Strömungen an der Schaufeloberfläche dadurch vermieden oder zumindest verringert werden können, wenn an der oberflächennahen Grenzschicht ein Teil des Arbeitsmediums abgesaugt und dadurch an der Schaufeloberfläche eine laminare Strömung des Arbeitsmediums praktisch erzwungen wird. Durch diese Maßnahme kann der Wirkungsgrad der Turbine um einige Prozentpunkte erhöht werden.The invention is based on the consideration that such eddies or turbulent flows on the blade surface can be avoided or at least reduced if a part of the working medium is suctioned off at the boundary layer near the surface and a laminar flow of the working medium is thereby practically forced on the blade surface , With this measure, the efficiency of the turbine can be increased by a few percentage points.
In besonders vorteilhafter Ausgestaltung sind sowohl die mit Mikrolöchern versehenen Leitschaufeln als auch die mit Mikro- löchern versehenen Laufschaufeln hohl ausgeführt. Ein Teil des an der Schaufeloberfläche vorbeiströmenden Arbeitsmediums wird somit von der Schaufeloberfläche in den Innenraum der hohlen Schaufel abgesaugt. Die Leitschaufeln stehen dabei zweckmäßigerweise mit einem äußeren, vorzugsweise im oder am Turbinengehäuse vorgesehenen Absaugkanal in Verbindung, während der Innenraum der hohlen Laufschaufeln mit dem Innenraum einer hohl ausgeführten Turbinenwelle in Verbindung steht. Der zur Absaugung erforderliche Unterdruck wird vorteilhafterweise dadurch erzeugt, dass die Mikrolöcher mit einem Turbinenteil in Verbindung stehen, welches von Arbeitsmittel vergleichsweise niedrigen Arbeitsmitteldruck umströmt wird. Ein dazu erforderliches Druckgefälle ist aufgrund der in der Turbine stattfindenden Entspannung des Arbeitsmittels zwischen Turbineneintritt und Turbinenaustritt bereits vorhanden und somit zur Absaugung verfügbar.In a particularly advantageous embodiment, both the guide blades provided with microholes and the rotor blades provided with microholes are hollow. Part of the working medium flowing past the blade surface is thus sucked away from the blade surface into the interior of the hollow blade. The guide vanes are expediently connected to an outer suction channel, preferably provided in or on the turbine housing, while the interior of the hollow rotor blades is connected to the interior of a hollow turbine shaft. The vacuum required for suction is advantageously generated by the fact that the microholes are connected to a turbine part, which has a relatively low working fluid pressure flowing around it. A pressure drop required for this is already present due to the expansion of the working fluid in the turbine between the turbine inlet and the turbine outlet and is therefore available for extraction.
Insbesondere bei massiv, d.h. nicht hohl ausgeführten Turbinenschaufeln sind die Mikrolöcher als Durchgangslöcher ausgebildet, die auf der der Arbeitsmittelströmung zugewandten Oberflächenseite der Turbinenschaufel in diese eintreten und auf der gegenüberliegenden Schaufelrückseite austreten. Bei dieser Ausgestaltung der Turbinenschaufeln mit Mikrolöchern wird das Druckgefälle zwischen Vorder- und Rückseite der Turbinenschaufel für die Absaugung genutzt.Especially with massive, i.e. If the turbine blades are not hollow, the microholes are designed as through-holes which enter the turbine blade on the surface side facing the working fluid flow and exit on the opposite rear side of the blade. In this configuration of the turbine blades with microholes, the pressure drop between the front and rear of the turbine blade is used for the suction.
Die mit der Erfindung erzielten Vorteile bestehen insbesondere darin, dass durch eine Perforierung der Schaufeloberfläche von Leit- und/oder Laufschaufeln einer Turbine mit einer Vielzahl von Mikrolöchern durch Wirbelbildung im oberflächennahen Schaufelbereich Strömungsverluste besonders gering ge- halten werden. Dadurch verbleibt die kinetische Energie im Arbeitsmittel selbst oder in der sich bewegenden Schaufel. Dies wiederum führt zu einer Erhöhung des Wirkungsgrades um einige Prozentpunkte, so dass eine Turbine vergleichbarer Leistung gegenüber einer herkömmlichen Turbine kleiner gebaut werden kann.The advantages achieved by the invention consist in particular in that flow perforations in the blade area near the surface are kept particularly low by perforating the blade surface of guide and / or rotor blades of a turbine with a large number of microholes. As a result, the kinetic energy remains in the work equipment itself or in the moving blade. This in turn leads to an increase in efficiency by a few percentage points, so that a turbine of comparable performance can be built smaller than a conventional turbine.
Die erforderliche Absaugung von an- der jeweiligen Turbinenschaufel entlang strömendem Arbeitsmittel wird vorzugsweise dadurch erzeugt, dass die Mikrolöcher eine Verbindung zu ei- nem Turbinenteil aufweisen, das von Arbeitsmittel vergleichsweise niedrigen Drucks umströmt wird. Dadurch kann ein Zusatzaggregat zur Absaugung eingespart werden. Nachfolgend werden Ausführungsbeispiele der Erfindung anhand einer Zeichnung näher erläutert. Darin zeigen:The necessary suction of work fluid flowing along the respective turbine blade is preferably generated in that the microholes have a connection to a turbine part which is surrounded by work fluid of comparatively low pressure. An additional unit for suction can thus be saved. Exemplary embodiments of the invention are explained in more detail below with reference to a drawing. In it show:
FIG 1 eine mit Mikrolöchern versehene hohle Turbinenschaufel, FIG 2 schematisch eine mit einer Anzahl derartiger Turbi- nenschaufeln versehene Turbine mit einem äußeren Absaugkanal und mit einer hohlen Turbinenwelle, und FIG 3 in einer Darstellung gemäß FIG 2 eine dampfgekühlte Dampfturbine mit mit Durchgangslöchern versehenen Turbinenschaufeln .1 shows a hollow turbine blade provided with microholes, FIG. 2 schematically shows a turbine provided with a number of such turbine blades with an outer suction duct and with a hollow turbine shaft, and FIG. 3 shows a steam-cooled steam turbine with turbine blades provided with through-holes in a representation according to FIG.
Einander entsprechende Teile sind in allen Figuren mit den gleichen Bezugszeichen versehen.Corresponding parts are provided with the same reference symbols in all figures.
Die in FIG 1 dargestellte Turbinenschaufel 1 mit einem bananenartig gekrümmten Schaufelblatt 2 und einem hammerköpfartigen Schaufelfuß 3 ist hohl ausgeführt. Der Innenraum 4 des Schaufelblatts 2 und der Innenraum 5 des Schaufelfußes 3 stehen miteinander in Verbindung.The turbine blade 1 shown in FIG. 1 with a blade leaf 2 curved like a banana and a blade root 3 like a hammer head is hollow. The interior 4 of the airfoil 2 and the interior 5 of the blade root 3 are connected to one another.
Die Turbinenschaufel 1 ist im Bereich des Schaufelblattes 2 mit einer Vielzahl von Mikrolöchern 6 versehen, die an der Schaufeloberfläche 7 eintreten und in den Innenraum 4 münden. Über die Mikrolöcher wird beim Betrieb der Turbine ein Anteil ΠIM des an deren Schaufeloberfläche 7 entlangströmenden Arbeitsmittels oder Arbeitsmediums M in Richtung des Pfeils 8 in den Innenraum 4 der Turbinenschaufel 1 abgesaugt und strömt in Richtung des Pfeils 9 über den Innenraum 5 des Schaufelfußes 3 aus der Turbinenschaufel 1 ab.The turbine blade 1 is provided in the region of the airfoil 2 with a large number of microholes 6 which enter the blade surface 7 and open into the interior 4. During operation of the turbine, a portion ΠI M of the working medium or working medium M flowing along its blade surface 7 is sucked off via the microholes in the direction of arrow 8 into the interior 4 of the turbine blade 1 and flows out in the direction of arrow 9 via the interior 5 of the blade root 3 the turbine blade 1.
Bei der in FIG 2 dargestellten Turbine 10 sind eine Anzahl von derartigen, mit Mikrolöchern 6 versehenen Turbinenschau- fei 1 als Leitschaufeln la und als Laufschaufeln lb eingesetzt. Die Leitschaufeln la sind dabei in nicht näher dargestellter Art und Weise über den jeweiligen Schaufelfuß 3 im Turbinengehause 11 verankert, wahrend die Laufschaufeln lb an einer hohl ausgeführten Turbinenwelle 12 befestigt sind. Die Innenraume 4,5 der Leitschaufeln la stehen dabei mit einem im Außenbereich des Turbinengehause 11 vorgesehenen Absaugkanal 13 in Verbindung. Analog stehen die Innenraume 4,5 der Laufschaufeln lb mit einem ebenfalls als Absaugkanal dienenden Hohlraum 14 der Turbinenweile 12 in Verbindung.In the turbine 10 shown in FIG. 2, a number of such turbine blades 1, which are provided with microholes 6, are used as guide blades 1 a and as blades 1 b. The guide vanes la are in a manner not shown on the respective blade root 3 in Turbine housing 11 anchored, while the blades lb are attached to a hollow turbine shaft 12. The inner spaces 4, 5 of the guide vanes 1 a are connected to a suction duct 13 provided in the outer region of the turbine housing 11. Analogously, the inner spaces 4, 5 of the rotor blades 1b are connected to a cavity 14 of the turbine shaft 12, which cavity also serves as a suction channel.
Der über die Mikrolöcher 6 der Leitschaufeln la m den Abzug- kanal 13 strömende Anteil mM des Arbeitsmediums M wird vorzugsweise der Turbine 10 wieder zugeführt und dazu in deren Arbeitsraum 15 eingeleitet. Zu diesem Zweck steht der Absaugkanal 13 über eine Anzahl von Offnungen 16 mit dem Arbeitsraum 15 an einer Stelle in Verbindung, an der der Druck pi des Arbeitsmediums M kleiner ist als der Druck p2 des Arbeitsmittels M im Bereich dessen Eintritts über die Mikrolöcher 6 in die entsprechenden Leitschaufeln la.The portion m M of the working medium M flowing through the micro-holes 6 of the guide vanes la m through the discharge channel 13 is preferably fed back to the turbine 10 and introduced into its working space 15. For this purpose, the suction channel 13 is connected via a number of openings 16 to the working space 15 at a point at which the pressure pi of the working medium M is less than the pressure p 2 of the working medium M in the region of its entry via the microholes 6 in the corresponding guide vanes la.
Die Absaugung des Anteils mM des Arbeitsmittels M über die Mikrolöcher 6 der Laufschaufeln lb erfolgt analog, indem dieser Anteil mM des Arbeitsmediums M über die entsprechenden Leitschaufeln lb und durch die Turbinenwelle 14 an entsprechender Stelle m den Arbeitsraum 15 der Turbine 10 eingeleitet wird. Dazu weist die Turbinenwelle 14 ebenfalls entsprechende Offnungen 17 im Bereich vergleichsweise niedrigen Mediumsdrucks pi auf.The extraction of the portion m M of the working medium M via the micro-holes 6 of the rotor blades 1b is carried out analogously, in that this portion m M of the working medium M is introduced through the corresponding guide blades 1b and through the turbine shaft 14 at a corresponding point m into the working space 15 of the turbine 10. For this purpose, the turbine shaft 14 also has corresponding openings 17 in the region of comparatively low medium pressure pi.
FIG 3 zeigt eine mittels Kuhldampf KD gekühlte Dampfturbine 10 der emgangsseitig Frischdampf FD mit einer Fπschdampf- temperatur TFD von z.B. 600°C bis 1000°C zugeführt wird. Zur Kühlung der Leit- und Laufschaufeln la, lb zumindest der ersten Leit- bzw. Laufschaufelreihen wird einerseits über das Turbinengehause 11 den hohlen Leitschaufeln la und andererseits über die hohle Turbinenweile 14 den Laufschaufein lb der Kuhldampf KD zugeführt. Der die Turbinenschaufeln la, lb durchströmende Kuhldampf KD tritt über entsprechende Offnungen in den Turbinenschaufeln la, lb in den Arbeitsraum 15 der Dampfturbine 10 λ aus und vermischt sich dort mit dem sich entlang der Schaufelreihen entspannenden Frischdampf FD. Dieser verläßt die Turbine 10 als Abdampf AD.3 shows a steam turbine 10 which is cooled by means of cow steam KD and which is fed fresh steam FD on the inlet side with a steam steam temperature T FD of, for example, 600 ° C. to 1000 ° C. To cool the guide vanes and rotor blades la, lb of at least the first rows of guide vanes or rotor blades, the hollow guide vanes la are supplied on the one hand via the turbine housing 11 and on the other hand via the hollow turbine shaft 14 the rotor blades 14b of the cow steam KD. The cooling steam KD flowing through the turbine blades la, lb enters the working space 15 of the turbine through corresponding openings in the turbine blades la, lb Steam turbine 10 λ out and mixes there with the live steam FD relaxing along the rows of blades. This leaves the turbine 10 as exhaust steam AD.
An die dampfgekühlten Turbinenschaufeln la, lb schließen sich in Strömungsrichtung 18 des Frischdampfs FD entlang der Turbinenwelle 14 weitere Schaufelreihen mit Leit- und Laufschaufeln la bzw. lb an, die wiederum mit Mikrolöchern 6 versehen sind. Die Mikrolöcher sind bei dieser Aus führungsform zweck- mäßigerweise in Form von Durchgangslöchern 6λ ausgeführt, die die Turbinenschaufeln la, lb durchsetzen. Der Durchtritt eines Anteils ΠI des Frischdampfes FD durch diese Durchgangslöcher 6λ wird aufgrund der Druckdifferenz zwischen dem auf der Zuströmseite der entsprechenden Turbinenschaufeln la, lb herr- sehenden Dampfdruck p2 und dem auf der Abström- oder Rückseite der entsprechenden Turbinenschaufel la, lb herrschenden Druck pi erzwungen.The steam-cooled turbine blades la, lb are followed in the flow direction 18 of the live steam FD along the turbine shaft 14 by further rows of blades with guide and rotor blades la and lb, which in turn are provided with microholes 6. The micro-holes are advantageously carried out at this expedient From guide die in the form of through holes 6 λ, which pass through the turbine blades la lb. The passage of a portion ΠI of live steam FD through these through holes 6 λ is due to the pressure difference between the steam pressure p 2 on the inflow side of the corresponding turbine blades la, lb and the pressure on the outflow or rear side of the corresponding turbine blade la, lb pi forced.
Die Größe der Mikrolöcher 6, 6 x liegt zweckmäßigerweise im u - Bereich, wobei der Innendurchmesser d der Mikrolöcher 6,6 beispielsweise 0,05mm beträgt. Der Abstand a zwischen benachbarten Mikrolöchern 6, 6 ist zweckmäßigerweise kleiner als lmm. Die Anzahl der auf der jeweiligen Schaufeloberfläche 7 vorgesehenen Mikrolöcher 6,6 liegt je nach Größe des jewei- ligen Schaufelblattes 2 in der Größenordnung von 102 bis 105. The size of the micro-holes 6, 6 x is suitably in the u - region, wherein the inner diameter d of the micro holes is 6.6, for example 0.05 mm. The distance a between adjacent microholes 6, 6 is expediently less than 1 mm. The number of microholes 6, 6 provided on the respective blade surface 7 is in the order of 10 2 to 10 5, depending on the size of the respective airfoil 2.
Claims
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EP00101581 | 2000-01-27 | ||
| EP00101581.7 | 2000-01-27 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| WO2001055559A1 true WO2001055559A1 (en) | 2001-08-02 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| PCT/EP2001/000239 Ceased WO2001055559A1 (en) | 2000-01-27 | 2001-01-10 | Porous turbine blades and turbine equipped with blades of this type |
Country Status (1)
| Country | Link |
|---|---|
| WO (1) | WO2001055559A1 (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2900692A1 (en) * | 2006-05-05 | 2007-11-09 | Snecma Sa | COMPRESSOR BLADE COMPRISING A SUCTION DEVICE |
| US8336315B2 (en) | 2004-02-18 | 2012-12-25 | Siemens Aktiengesellschaft | Gas turbine with a compressor housing which is protected against cooling down and method for operating a gas turbine |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2597510A (en) * | 1947-04-15 | 1952-05-20 | Worthington Pump & Mach Corp | Blade element for rotary fluid machines |
| GB1085227A (en) * | 1963-07-26 | 1967-09-27 | Rolls Royce | Improvements in or relating to gas turbine engines |
| US3656863A (en) * | 1970-07-27 | 1972-04-18 | Curtiss Wright Corp | Transpiration cooled turbine rotor blade |
| GB1532815A (en) * | 1976-09-27 | 1978-11-22 | Rolls Royce | Rotor blades for ducted fans |
| JPS5688902A (en) * | 1979-12-19 | 1981-07-18 | Toshiba Corp | Turbine blade |
| US5480284A (en) * | 1993-12-20 | 1996-01-02 | General Electric Company | Self bleeding rotor blade |
| EP0726384A1 (en) * | 1995-02-13 | 1996-08-14 | Abb Research Ltd. | Stator blade for steam turbines |
| US5803410A (en) * | 1995-12-01 | 1998-09-08 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Skin friction reduction by micro-blowing technique |
-
2001
- 2001-01-10 WO PCT/EP2001/000239 patent/WO2001055559A1/en not_active Ceased
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2597510A (en) * | 1947-04-15 | 1952-05-20 | Worthington Pump & Mach Corp | Blade element for rotary fluid machines |
| GB1085227A (en) * | 1963-07-26 | 1967-09-27 | Rolls Royce | Improvements in or relating to gas turbine engines |
| US3656863A (en) * | 1970-07-27 | 1972-04-18 | Curtiss Wright Corp | Transpiration cooled turbine rotor blade |
| GB1532815A (en) * | 1976-09-27 | 1978-11-22 | Rolls Royce | Rotor blades for ducted fans |
| JPS5688902A (en) * | 1979-12-19 | 1981-07-18 | Toshiba Corp | Turbine blade |
| US5480284A (en) * | 1993-12-20 | 1996-01-02 | General Electric Company | Self bleeding rotor blade |
| EP0726384A1 (en) * | 1995-02-13 | 1996-08-14 | Abb Research Ltd. | Stator blade for steam turbines |
| US5803410A (en) * | 1995-12-01 | 1998-09-08 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Skin friction reduction by micro-blowing technique |
Non-Patent Citations (1)
| Title |
|---|
| PATENT ABSTRACTS OF JAPAN vol. 005, no. 162 (M - 092) 17 October 1981 (1981-10-17) * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8336315B2 (en) | 2004-02-18 | 2012-12-25 | Siemens Aktiengesellschaft | Gas turbine with a compressor housing which is protected against cooling down and method for operating a gas turbine |
| FR2900692A1 (en) * | 2006-05-05 | 2007-11-09 | Snecma Sa | COMPRESSOR BLADE COMPRISING A SUCTION DEVICE |
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