EP2788586B1 - Blade ring for an axial turbo engine and method for adjusting the absorption characteristics of the blade ring - Google Patents

Blade ring for an axial turbo engine and method for adjusting the absorption characteristics of the blade ring Download PDF

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Publication number
EP2788586B1
EP2788586B1 EP12786929.5A EP12786929A EP2788586B1 EP 2788586 B1 EP2788586 B1 EP 2788586B1 EP 12786929 A EP12786929 A EP 12786929A EP 2788586 B1 EP2788586 B1 EP 2788586B1
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EP
European Patent Office
Prior art keywords
blade
ring
blade ring
flow rate
adjustment
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.)
Not-in-force
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EP12786929.5A
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German (de)
French (fr)
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EP2788586A1 (en
Inventor
Armin De Lazzer
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Siemens AG
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Siemens AG
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Publication of EP2788586A1 publication Critical patent/EP2788586A1/en
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Publication of EP2788586B1 publication Critical patent/EP2788586B1/en
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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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/141—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of shiftable members or valves obturating part of the flow path
    • 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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/167—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes of vanes moving in translation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2220/00—Application
    • F05B2220/30—Application in turbines
    • F05B2220/301—Application in turbines in steam turbines
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/31—Application in turbines in steam turbines

Definitions

  • the invention relates to a blade ring for an axial turbomachine, an axial turbomachine with the blade ring and a method for adjusting the absorption capacity of the blade ring.
  • the maximum process steam mass flow which can be conveyed by the steam turbine is one of the decisive variables in the design of the steam turbine and is referred to as the steam capacity of the steam turbine.
  • the vane rings of the steam turbine have a plurality of vanes, which are arranged distributed uniformly over the circumference, wherein between the vanes blade channels are formed. Radially, the blade channels are limited on the hub side of a hub contour and the housing side of a housing contour.
  • the absorption capacity of the steam turbine is decisively influenced by the absorption capacity of the first guide vane ring, which is essentially determined by the entirety of all effective cross sections of the vane passages of the first guide vane ring.
  • the invention has for its object to provide a blade ring for an axial turbomachine, the axial turbomachine with the blade ring and a method for adjusting the absorption capacity of the blade ring, wherein the above-mentioned problems are overcome and in particular the absorption capacity of the axial turbomachine is corrected in a corrective manner.
  • the US 5,683,225 includes the features of the preamble of claim 1.
  • the blade ring according to the invention for an axial turbomachine has a radially inwardly facing outer surface arranged on an outer ring and a radially outwardly facing inner surface arranged on an inner ring which delimits an annular flow channel tapering in the main flow direction of the axial turbomachine and arranged concentrically and parallel to one another are, and at least one Justierschaufel, which is arranged in the flow channel by means of a guide device to a surface line of one of the surfaces displaceable parallel and lockable on at least one of the rings in a predetermined position.
  • a generatrix is characterized in that it is arranged on one of the two surfaces and is directed to the imaginary tip of the respective surface.
  • the diameter of the flow channel decreases in the direction of the taper of the inner surface and the outer surface.
  • the at least one adjusting blade displaced in the direction of tapering by means of the guide device its distance decreases in the circumferential direction to the blades arranged adjacent in the blade ring, whereby the obstruction of the flow channel for the fluid flowing through the flow channel increases and decreases the absorption capacity of the blade ring accordingly.
  • the ability to swallow can be increased by displacing the at least one adjusting blade by means of the guide device counter to the direction of tapering.
  • the ability to swallow the blade ring is advantageously easily changed under the operation of the guide device.
  • the inner ring is formed as a disc.
  • the outer surface and the inner surface are preferably conical surfaces.
  • the outer surface and the inner surface alternatively have along the respective surface line in each cross section perpendicular to the axis of the flow channel segmentally equal radii of curvature, so that remain constant when moving the Justierschaufel the extensions of the radial gaps between the Justierschaufel and the surfaces.
  • each of the cross sections of the outer surface and the inner surface is preferably formed perpendicular to the axis of the flow channel in each case by a polygon or by a plurality of immediately adjacent arranged circle segments.
  • the blade ring is preferably a diagonal stage of the axial turbomachine.
  • the diagonal stage advantageously has the flow channel, which is bounded by the two conical surfaces.
  • the blade ring is a vane ring with fixed, non-rotating vanes and a fixed, non-rotating inner surface and outer surface.
  • the blade ring has a plurality of blades, wherein the blades are alternately the Justingschaufeln and fixedly attached to the outer surface and / or on the inner surface blades.
  • Each of the fixed blades is preferably integrally formed with the inner ring and the outer ring or integrally with a segment of the inner ring and a segment of the outer ring. This advantageously results in a high rigidity of the blade ring.
  • the fact that every second blade is firmly attached, results in the manufacture of the blade ring advantageously good accessibility of the blade ring for a production tool.
  • the guide device has a sliding groove in the inner ring and / or in the outer ring as well as on the radially outer side and / or on the radially inner side of the Justierschaufel a pin, wherein the pin engages in the sliding groove.
  • the guide device preferably has, in at least one of the sliding grooves downstream of the main flow direction of the axial turbomachine, a stop with which the adjusting blade can be fixed in the predetermined position. In this case, the adjusting blade is pressed during operation of the axial turbomachine by the fluid flowing in the flow channel against the fluid stop, whereby the determination of the adjusting blade is accomplished.
  • the position of the adjusting blade in the flow channel can be defined for example by introducing a spacer to the stop.
  • the spacer can for example be fixedly mounted by grub screws and / or by welding points on the outer ring and / or on the inner ring.
  • the guide means is arranged such that the at least one adjusting blade is exchangeable with another adjusting blade.
  • the at least one adjusting blade can be exchanged for the other adjusting blade with other aerodynamic properties.
  • An adaptation of the swallowing ability can also be carried out by a suitable exchange, for example by the other adjusting blade having a profile with a shorter or longer chord length.
  • the axial turbomachine according to the invention has the blade ring according to the invention.
  • the absorption capacity of the axial turbomachine is preferably determined by the ability to swallow the blade ring.
  • the method according to the invention for adjusting the buoyancy of the blade ring comprises the following steps: predetermining a desired value of the buoyancy of the blade ring; Determining the actual value of the buoyancy of the blade ring; Comparing the desired value of the buoyancy of the blade ring with the actual value of the buoyancy of the blade ring; Moving the at least one adjusting blade by means of the guide device parallel to the generatrix such that the desired value of the swallowing ability becomes equal to the actual value of the swallowing ability; Locking the adjusting blade with the guide device. If the ability to swallow the axial turbomachine is defined by the ability to swallow the blade ring, the ability to swallow the axial turbomachine can be changed by moving the at least one adjusting blade.
  • FIG. 1 shows a longitudinal section through an axial turbomachine with a preferred embodiment of the blade ring according to the invention.
  • an axial turbomachine 1 comprises a housing 22, a shaft 21 and a plurality of blade rings 11 to 13.
  • a fluid 25 is flowable within the housing 22 with a main flow direction 17.
  • a first vane ring 11, a blade ring 12 and a second vane ring 13 are shown, which are arranged in this order in the main flow direction 17 of the fluid 25.
  • the first vane ring 11 has an outer cone ring 24 fastened to the housing 22 with a conical outer surface 2 facing radially inwards, and an inner conical ring 23 with a conical inner surface 3 facing radially outward within the outer conical ring 24.
  • the cone outer surface 2 and the inner cone surface 3 are arranged concentrically with each other, have a same cone angle 18, are arranged parallel to each other in each axial section and define an annular flow channel 4.
  • the inner cone ring 23 and the outer cone ring 24 are truncated cones. However, it is also conceivable that the inner cone ring 23 includes its conical tip.
  • the cone axes 26 of the cone outer surface 2 and the inner cone surface 3 coincide with the shaft axis 27.
  • the conical surfaces 2, 3 are oriented so that the outer diameter 28 (shown in the figure is half the outer diameter 28) of the flow channel 4 in the main flow direction 17 decreases.
  • the inner cone ring 23 and the outer cone ring 24 are modified such that the cone inner surface 3 and the cone outer surface 2 along the respective surface line 6 and along the width of Justierschaufel 7 in each cross-section perpendicular to the shaft 21 have the same curvature radii, so that when moving the Justierschaufel 7, the extensions of the radial gaps between the Justierschaufel 7 and the conical surfaces 2, 3 remain constant. It is conceivable, for example, that the radii of curvature are infinitely large, so that each of the cross sections of the conical surfaces 2, 3 forms a polygon perpendicular to the shaft 21, wherein a blade is arranged on each of the segments of the polygon. Downstream of the main flow direction 17, the length of each of the path segments of the polygon becomes shorter.
  • each of the cross sections is formed perpendicular to the shaft 21 of a plurality of circle segments.
  • the radii of curvature of the circular segments can be both larger and smaller than the radii of the flow channel 4. Downstream of the main flow direction 17, the extent of each of the circle segments becomes shorter, whereas the radius of curvature remains constant in each case.
  • a Justierschaufel 7 is arranged, which is arranged with its radial outer side 9 on the cone outer surface 2 and with its radially inner side 10 on the inner surface of the cone 3.
  • the Justierschaufel 7 has on its inner radial side 9 and its radial outer side 10 each have a pin 15, wherein the pins 15 each engage in a sliding groove 14 in the inner cone ring 23 and the outer taper ring 24.
  • the slide grooves 14 are arranged parallel to each other and each extend along a surface line 6 of the conical surfaces 2, 3, so that the Justierschaufel 7 is parallel to the generatrices 6 slidably.
  • the adjusting blade 7 When the adjusting blade 7 is displaced in the main flow direction 17, the distance in the circumferential direction of the adjusting blade 7 is reduced to the blades arranged adjacent to it in the first guide blade ring 11, whereby the obstruction for the fluid 25 in the first guide blade ring 11 increases. Increased obstruction reduces the ability of the first vane ring 11 to absorb moisture. Conversely, the ability to swallow can be increased by displacing the adjusting vane 7 upstream of the main flow direction 17.
  • the maximum possible displacement 8 of the adjusting blade 7 is limited by the length of the flow channel 4 in the main flow direction 17 and the length of the Gleitnuten 14. To change the ability to swallow, it is also conceivable that the adjusting blade 7 is replaced by another adjusting blade, which has a shorter or longer chord length.
  • the sliding groove 14 in the tapered inner surface 3 is limited in the main flow direction 17 by a stop 29, i. it is not guided to the downstream end 5 of the flow channel 4, so that during operation of the axial turbomachine 1, the Justierschaufel 7 is pressed by the flow of the fluid 25 to the stop 29. It is also possible to limit the sliding groove 14 in the conical outer surface 2 in the main flow direction 17 of a stop or to limit both Gleitnuten 14 of a stop. Upstream of the main flow direction 17, the sliding grooves 14 are not limited, so that the adjusting blade 7 is removable from the flow channel 4 and exchangeable with another adjusting blade.
  • spacers 16 are provided for detecting the position of the Justierschaufel 7 in the Gleitnuten.
  • the spacers 16 are arranged both on the downstream side of the pins 15, as well as on the upstream side of the pins 15. It is in principle possible to provide no spacers 16 on the upstream side, because the Justierschaufel 7 is pressed in operation against the downstream spacers 16 or against the end of the sliding groove 14. The minimum possible absorption capacity for the adjusting blade 7 is achieved if none of the spacers 16 are provided on the downstream side.
  • All the blades in the first blade ring 11 are designed as adjusting blades 7 and thus designed to be displaceable.
  • the blades could alternately as the adjusting blades 7 are formed and designed to be fixed to the conical surfaces 2, 3.
  • the inner cone ring 23, the outer cone ring 24 and the fixed blades are made of one piece.
  • a fixed blade together with one segment of the inner cone ring 23 and the outer cone ring 24 is made of one piece and thus the first vane ring 11 is composed of a plurality of segments.
  • the Justierschaufeln 7 are also provided for a blade ring.
  • the inner cone ring 23 are fixedly connected to the shaft 21 and the Justierschaufel 7 with its radially inner side 10 slidably disposed on the inner cone ring 23.
  • the inner cone ring 23 and the Justierschaufel 7 are thus rotating components of the axial turbomachine 1.
  • a gap could be provided between the radial outer side 9 of the movable blade 7 and the cone outer surface 2, a gap could be provided.
  • the Justierschaufel 7 could also be with its outer radial side 9 with the outer cone ring 24 in engagement. In the latter case, the outer cone ring 24 would also be a rotating component.
  • the adjustment of the absorption capacity of the first vane ring 11 is to be carried out as follows: predetermining a desired value of the ability to swallow the blade ring 11; Determining the actual value of the swallowability of the blade ring 11; Comparing the target value of the ability to swallow of the blade ring 11 with the actual value of the ability to swallow the blade ring 11; Moving the at least one adjusting blade 7 by means of the guide device parallel to the generating line 6 such that the desired value of the swallowing ability becomes equal to the actual value of the swallowing ability; Detecting the Justierschaufel 7 with the guide device.

Description

Die Erfindung betrifft einen Schaufelkranz für eine Axialturbomaschine, eine Axialturbomaschine mit dem Schaufelkranz und ein Verfahren zum Justieren der Schluckfähigkeit des Schaufelkranzes.The invention relates to a blade ring for an axial turbomachine, an axial turbomachine with the blade ring and a method for adjusting the absorption capacity of the blade ring.

Um einen wirtschaftlichen Betrieb einer Dampfturbine zu erzielen, ist es von Bedeutung, dass ein maximal möglicher Prozessdampfmassenstrom eines Dampferzeugers, beispielsweise eines Kraftwerks, in der Dampfturbine entspannt werden kann. Der maximal durch die Dampfturbine förderbare Prozessdampfmassenstrom ist eine der maßgeblichen Größen bei der Auslegung der Dampfturbine und wird als die Schluckfähigkeit der Dampfturbine bezeichnet. Die Leitschaufelkränze der Dampfturbine weisen eine Vielzahl an Leitschaufeln auf, die gleichmäßig über den Umfang verteilt angeordnet sind, wobei zwischen den Leitschaufeln Schaufelkanäle ausgebildet sind. Radial sind die Schaufelkanäle nabenseitig begrenzt von einer Nabenkontur und gehäuseseitig von einer Gehäusekontur. Die Schluckfähigkeit der Dampfturbine wird durch die Schluckfähigkeit des ersten Leitschaufelkranzes maßgeblich beeinflusst, die im Wesentlichen durch die Gesamtheit aller effektiven Querschnitte der Schaufelkanäle des ersten Leitschaufelkranzes bestimmt ist.In order to achieve economical operation of a steam turbine, it is important that a maximum possible process steam mass flow of a steam generator, for example a power plant, in the steam turbine can be expanded. The maximum process steam mass flow which can be conveyed by the steam turbine is one of the decisive variables in the design of the steam turbine and is referred to as the steam capacity of the steam turbine. The vane rings of the steam turbine have a plurality of vanes, which are arranged distributed uniformly over the circumference, wherein between the vanes blade channels are formed. Radially, the blade channels are limited on the hub side of a hub contour and the housing side of a housing contour. The absorption capacity of the steam turbine is decisively influenced by the absorption capacity of the first guide vane ring, which is essentially determined by the entirety of all effective cross sections of the vane passages of the first guide vane ring.

Die Schluckfähigkeit von neu hergestellten Dampfturbinen unterliegt aufgrund von Fertigungstoleranzen und Montagetoleranzen von Bauteilen der Dampfturbine gewissen Ungenauigkeiten. Ferner verändert sich die Schluckfähigkeit aufgrund von Alterung der Bauteile. Daher ist es oftmals vonnöten, die Schluckfähigkeit der Dampfturbine zu korrigieren, um die Dampfturbine wieder im Nennzustand betreiben zu können. Dazu werden im Betrieb befindliche Leitschaufeln durch neue Leitschaufeln mit einer hinsichtlich der Schluckfähigkeit der Dampfturbine verbesserten Profilierung ausgetauscht. In der Regel werden alle Leitschaufeln eines betroffenen Schaufelkranzes ausgetauscht, was jedoch sehr aufwändig und kostenintensiv ist. Alternativ dazu kann die Hinterkante von den Leitschaufeln verkürzt werden. Damit ist jedoch die Schluckfähigkeit des Leitschaufelkranzes lediglich erhöhbar und das Verkürzen führt häufig zu schlechteren aerodynamischen Eigenschaften sowie zu einer geringeren mechanischen Festigkeit der Leitschaufeln.The absorption capacity of newly manufactured steam turbines is subject to certain inaccuracies due to manufacturing tolerances and assembly tolerances of components of the steam turbine. Furthermore, the ability to swallow changes due to aging of the components. Therefore, it is often necessary to correct the absorption capacity of the steam turbine in order to operate the steam turbine in the nominal state again. For this purpose, operating vanes are replaced by new vanes exchanged with a respect to the ability to swallow the steam turbine improved profiling. In general, all the vanes of an affected blade ring are replaced, which is very complex and costly. Alternatively, the trailing edge of the vanes may be shortened. Thus, however, the ability to absorb the vane ring is only increased and shortening often leads to poorer aerodynamic properties and to a lower mechanical strength of the vanes.

Der Erfindung liegt die Aufgabe zugrunde, einen Schaufelkranz für eine Axialturbomaschine, die Axialturbomaschine mit dem Schaufelkranz und ein Verfahren zum Justieren der Schluckfähigkeit des Schaufelkranzes zu schaffen, wobei die oben genannten Probleme überwunden sind und insbesondere die Schluckfähigkeit der Axialturbomaschine auf korrigierende Weise veränderbar ist.The invention has for its object to provide a blade ring for an axial turbomachine, the axial turbomachine with the blade ring and a method for adjusting the absorption capacity of the blade ring, wherein the above-mentioned problems are overcome and in particular the absorption capacity of the axial turbomachine is corrected in a corrective manner.

Die US 5,683,225 beinhaltet die Merkmale der Präambel von Anspruch 1.The US 5,683,225 includes the features of the preamble of claim 1.

Der erfindungsgemäße Schaufelkranz für eine Axialturbomaschine weist eine an einem Außenring angeordnete, radial nach innen gewandte Außenfläche und eine an einem Innenring angeordnete, radial nach außen gewandte Innenfläche, welche einen ringförmigen und sich in der Hauptströmungsrichtung der Axialturbomaschine verjüngenden Strömungskanal begrenzen und konzentrisch sowie parallel zueinander angeordnet sind, sowie mindestens eine Justierschaufel auf, die im Strömungskanal mittels einer Führungseinrichtung zu einer Mantellinie einer der Flächen parallel verschiebbar angeordnet und an mindestens einem der Ringe in einer vorherbestimmten Position feststellbar ist.The blade ring according to the invention for an axial turbomachine has a radially inwardly facing outer surface arranged on an outer ring and a radially outwardly facing inner surface arranged on an inner ring which delimits an annular flow channel tapering in the main flow direction of the axial turbomachine and arranged concentrically and parallel to one another are, and at least one Justierschaufel, which is arranged in the flow channel by means of a guide device to a surface line of one of the surfaces displaceable parallel and lockable on at least one of the rings in a predetermined position.

Eine Mantellinie zeichnet sich dadurch aus, dass sie auf einer der beiden Flächen angeordnet ist und zu der gedachten Spitze der jeweiligen Fläche gerichtet ist.A generatrix is characterized in that it is arranged on one of the two surfaces and is directed to the imaginary tip of the respective surface.

Der Durchmesser des Strömungskanals nimmt in Richtung der Verjüngung der Innenfläche und der Außenfläche ab. Wird die mindestens eine Justierschaufel mit Hilfe der Führungseinrichtung in Verjüngungsrichtung hin verschoben, so nimmt ihr Abstand in Umfangsrichtung zu den im Schaufelkranz benachbart angeordneten Schaufeln ab, wodurch die Versperrung des Strömungskanals für das durch den Strömungskanal strömende Fluid zunimmt und die Schluckfähigkeit des Schaufelkranzes dementsprechend abnimmt. Analog kann die Schluckfähigkeit erhöht werden, indem die mindestens eine Justierschaufel mit Hilfe der Führungseinrichtung entgegen der Verjüngungsrichtung verschoben wird. Somit ist die Schluckfähigkeit des Schaufelkranzes vorteilhaft unter der Betätigung der Führungseinrichtung einfach veränderbar. Dies kann beispielsweise vonnöten sein, wenn sich die Schluckfähigkeit des Schaufelkranzes aufgrund von Alterung von Komponenten der Axialturbomaschine verändert oder wenn die Schluckfähigkeit an sich ändernde Rahmenbedingungen, wie beispielsweise ein geänderter Prozessdampfmassenstrom, angepasst werden soll. Weiterhin kann eine Korrektur der Schluckfähigkeit zur Kompensation von Fertigungstoleranzen oder Montagetoleranzen einer neu hergestellten Axialturbomaschine durchgeführt werden. Es ist denkbar, dass der Innenring als eine Scheibe ausgebildet ist.The diameter of the flow channel decreases in the direction of the taper of the inner surface and the outer surface. Will the at least one adjusting blade displaced in the direction of tapering by means of the guide device, its distance decreases in the circumferential direction to the blades arranged adjacent in the blade ring, whereby the obstruction of the flow channel for the fluid flowing through the flow channel increases and decreases the absorption capacity of the blade ring accordingly. Analogously, the ability to swallow can be increased by displacing the at least one adjusting blade by means of the guide device counter to the direction of tapering. Thus, the ability to swallow the blade ring is advantageously easily changed under the operation of the guide device. This may be necessary, for example, if the buoyancy of the blade ring changes due to aging of components of the axial turbomachine or if the absorption capacity is to be adapted to changing boundary conditions, such as, for example, a modified process steam mass flow. Furthermore, a correction of the ability to swallow to compensate for manufacturing tolerances or assembly tolerances of a newly manufactured axial turbomachine can be performed. It is conceivable that the inner ring is formed as a disc.

Die Außenfläche und die Innenfläche sind bevorzugt Kegelflächen. Die Außenfläche und die Innenfläche haben alternativ bevorzugt entlang der jeweiligen Mantellinie in jedem Querschnitt senkrecht zur Achse des Strömungskanals segmentweise gleiche Krümmungsradien, so dass beim Verschieben der Justierschaufel die Erstreckungen der Radialspalte zwischen der Justierschaufel und den Flächen konstant bleiben. Dabei ist jeder der Querschnitte der Außenfläche und der Innenfläche bevorzugt senkrecht zur Achse des Strömungskanals jeweils von einem Polygon oder von einer Mehrzahl an unmittelbar benachbart angeordneten Kreissegmenten gebildet.The outer surface and the inner surface are preferably conical surfaces. The outer surface and the inner surface alternatively have along the respective surface line in each cross section perpendicular to the axis of the flow channel segmentally equal radii of curvature, so that remain constant when moving the Justierschaufel the extensions of the radial gaps between the Justierschaufel and the surfaces. In this case, each of the cross sections of the outer surface and the inner surface is preferably formed perpendicular to the axis of the flow channel in each case by a polygon or by a plurality of immediately adjacent arranged circle segments.

Der Schaufelkranz ist bevorzugt eine Diagonalstufe der Axialturbomaschine. Die Diagonalstufe weist vorteilhaft den Strömungskanal auf, der von den beiden Kegelflächen begrenzt ist. Bevorzugtermaßen ist der Schaufelkranz ein Leitschaufelkranz mit fest stehenden, nicht rotierenden Leitschaufeln sowie einer fest stehenden, nicht rotierenden Innenfläche und Außenfläche.The blade ring is preferably a diagonal stage of the axial turbomachine. The diagonal stage advantageously has the flow channel, which is bounded by the two conical surfaces. Preferably, the blade ring is a vane ring with fixed, non-rotating vanes and a fixed, non-rotating inner surface and outer surface.

In einer bevorzugten Ausführungsform weist der Schaufelkranz eine Mehrzahl an Schaufeln auf, wobei die Schaufeln alternierend die Justierschaufeln sowie fest an der Außenfläche und/oder an der Innenfläche angebrachte Schaufeln sind. Jede der fest angebrachten Schaufeln ist bevorzugt einstückig zusammen mit dem Innenring und dem Außenring oder einstückig zusammen mit einem Segment des Innenrings und einem Segment des Außenrings hergestellt. Somit ergibt sich vorteilhaft eine hohe Steifigkeit des Schaufelkranzes. Dadurch, dass jede zweite Schaufel fest angebracht ist, ergibt sich bei der Fertigung des Schaufelkranzes vorteilhaft eine gute Zugänglichkeit des Schaufelkranzes für ein Fertigungswerkzeug.In a preferred embodiment, the blade ring has a plurality of blades, wherein the blades are alternately the Justingschaufeln and fixedly attached to the outer surface and / or on the inner surface blades. Each of the fixed blades is preferably integrally formed with the inner ring and the outer ring or integrally with a segment of the inner ring and a segment of the outer ring. This advantageously results in a high rigidity of the blade ring. The fact that every second blade is firmly attached, results in the manufacture of the blade ring advantageously good accessibility of the blade ring for a production tool.

Es ist bevorzugt, dass die Führungseinrichtung eine Gleitnut in dem Innenring und/oder in dem Außenring sowie an der Radialaußenseite und/oder an der Radialinnenseite der Justierschaufel einen Zapfen aufweist, wobei der Zapfen in die Gleitnut eingreift. Die Führungseinrichtung weist bevorzugt in mindestens einer der Gleitnuten stromab der Hauptströmungsrichtung der Axialturbomaschine einen Anschlag auf, mit dem die Justierschaufel in der vorherbestimmten Position feststellbar ist. Dabei wird die Justierschaufel im Betrieb der Axialturbomaschine durch das in dem Strömungskanal strömende Fluid gegen den Anschlag gedrückt, wodurch die Feststellung der Justierschaufel bewerkstelligt wird. Die Position der Justierschaufel im Strömungskanal kann beispielsweise durch Einbringen eines Abstandsstücks an den Anschlag definiert werden. Das Abstandsstück kann beispielsweise durch Madenschrauben und/oder durch Schweißpunkte an dem Außenring und/oder an dem Innenring fest angebracht werden.It is preferred that the guide device has a sliding groove in the inner ring and / or in the outer ring as well as on the radially outer side and / or on the radially inner side of the Justierschaufel a pin, wherein the pin engages in the sliding groove. The guide device preferably has, in at least one of the sliding grooves downstream of the main flow direction of the axial turbomachine, a stop with which the adjusting blade can be fixed in the predetermined position. In this case, the adjusting blade is pressed during operation of the axial turbomachine by the fluid flowing in the flow channel against the fluid stop, whereby the determination of the adjusting blade is accomplished. The position of the adjusting blade in the flow channel can be defined for example by introducing a spacer to the stop. The spacer can for example be fixedly mounted by grub screws and / or by welding points on the outer ring and / or on the inner ring.

Bevorzugtermaßen ist die Führungseinrichtung derart eingerichtet, dass die mindestens eine Justierschaufel gegen eine andere Justierschaufel austauschbar ist. Somit kann die mindestens eine Justierschaufel gegen die andere Justierschaufel mit anderen aerodynamischen Eigenschaften getauscht werden. Auch eine Anpassung der Schluckfähigkeit kann durch einen geeigneten Tausch durchgeführt werden, indem beispielsweise die andere Justierschaufel ein Profil mit einer kürzeren oder längeren Sehnenlänge hat.Preferably, the guide means is arranged such that the at least one adjusting blade is exchangeable with another adjusting blade. Thus, the at least one adjusting blade can be exchanged for the other adjusting blade with other aerodynamic properties. An adaptation of the swallowing ability can also be carried out by a suitable exchange, for example by the other adjusting blade having a profile with a shorter or longer chord length.

Die erfindungsgemäße Axialturbomaschine weist den erfindungsgemäßen Schaufelkranz auf. Die Schluckfähigkeit der Axialturbomaschine ist bevorzugt durch die Schluckfähigkeit des Schaufelkranzes bestimmt.The axial turbomachine according to the invention has the blade ring according to the invention. The absorption capacity of the axial turbomachine is preferably determined by the ability to swallow the blade ring.

Das erfindungsgemäße Verfahren zum Justieren der Schluckfähigkeit des Schaufelkranzes weist folgende Schritte auf: Vorherbestimmen eines Soll-Werts der Schluckfähigkeit des Schaufelkranzes; Ermitteln des Ist-Werts der Schluckfähigkeit des Schaufelkranzes; Vergleichen des Soll-Werts der Schluckfähigkeit des Schaufelkranzes mit dem Ist-Wert der Schluckfähigkeit des Schaufelkranzes; Verschieben der mindestens einen Justierschaufel mittels der Führungseinrichtung parallel zu der Mantellinie derart, dass der Soll-Wert der Schluckfähigkeit gleich wird mit dem Ist-Wert der Schluckfähigkeit; Feststellen der Justierschaufel mit der Führungseinrichtung. Wenn die Schluckfähigkeit der Axialturbomaschine durch die Schluckfähigkeit des Schaufelkranzes definiert ist, kann durch das Verschieben der mindestens einen Justierschaufel die Schluckfähigkeit der Axialturbomaschine verändert werden.The method according to the invention for adjusting the buoyancy of the blade ring comprises the following steps: predetermining a desired value of the buoyancy of the blade ring; Determining the actual value of the buoyancy of the blade ring; Comparing the desired value of the buoyancy of the blade ring with the actual value of the buoyancy of the blade ring; Moving the at least one adjusting blade by means of the guide device parallel to the generatrix such that the desired value of the swallowing ability becomes equal to the actual value of the swallowing ability; Locking the adjusting blade with the guide device. If the ability to swallow the axial turbomachine is defined by the ability to swallow the blade ring, the ability to swallow the axial turbomachine can be changed by moving the at least one adjusting blade.

Im Folgenden wird anhand der beigefügten schematischen Zeichnung die Erfindung näher erläutert. Die Figur zeigt einen Längsschnitt durch eine Axialturbomaschine mit einer bevorzugten Ausführungsform des erfindungsgemäßen Schaufelkranzes.In the following, the invention is explained in more detail with reference to the accompanying schematic drawing. The figure shows a longitudinal section through an axial turbomachine with a preferred embodiment of the blade ring according to the invention.

Wie es aus der Figur ersichtlich ist, weist eine Axialturbomaschine 1 ein Gehäuse 22, eine Welle 21 sowie eine Mehrzahl an Schaufelkränzen 11 bis 13 auf. Ein Fluid 25 ist innerhalb des Gehäuses 22 mit einer Hauptströmungsrichtung 17 strömbar.As can be seen from the figure, an axial turbomachine 1 comprises a housing 22, a shaft 21 and a plurality of blade rings 11 to 13. A fluid 25 is flowable within the housing 22 with a main flow direction 17.

In der Figur sind ein erster Leitschaufelkranz 11, ein Laufschaufelkranz 12 und ein zweiter Leitschaufelkranz 13 dargestellt, die in dieser Reihenfolge in der Hauptströmungsrichtung 17 des Fluids 25 angeordnet sind.In the figure, a first vane ring 11, a blade ring 12 and a second vane ring 13 are shown, which are arranged in this order in the main flow direction 17 of the fluid 25.

Der erste Leitschaufelkranz 11 weist einen an dem Gehäuse 22 befestigten Außenkegelring 24 mit einer radial nach innen gewandten Kegelaußenfläche 2 und innerhalb des Außenkegelrings 24 einen Innenkegelring 23 mit einer radial nach außen gewandten Kegelinnenfläche 3 auf. Die Kegelaußenfläche 2 und die Kegelinnenfläche 3 sind zueinander konzentrisch angeordnet, haben einen gleichen Kegelwinkel 18, sind in jedem Axialabschnitt parallel zueinander angeordnet und begrenzen einen ringförmigen Strömungskanal 4. Wie es aus der Figur ersichtlich ist, sind der Innenkegelring 23 und der Außenkegelring 24 Kegelstümpfe. Es ist jedoch auch denkbar, dass der Innenkegelring 23 seine Kegelspitze mit umfasst.The first vane ring 11 has an outer cone ring 24 fastened to the housing 22 with a conical outer surface 2 facing radially inwards, and an inner conical ring 23 with a conical inner surface 3 facing radially outward within the outer conical ring 24. The cone outer surface 2 and the inner cone surface 3 are arranged concentrically with each other, have a same cone angle 18, are arranged parallel to each other in each axial section and define an annular flow channel 4. As can be seen from the figure, the inner cone ring 23 and the outer cone ring 24 are truncated cones. However, it is also conceivable that the inner cone ring 23 includes its conical tip.

Die Kegelachsen 26 der Kegelaußenfläche 2 und der Kegelinnenfläche 3 fallen mit der Wellenachse 27 zusammen. Die Kegelflächen 2, 3 sind so orientiert, dass der Außendurchmesser 28 (in der Figur ist der halbe Außendurchmesser 28 gezeigt) des Strömungskanals 4 in der Hauptströmungsrichtung 17 abnimmt.The cone axes 26 of the cone outer surface 2 and the inner cone surface 3 coincide with the shaft axis 27. The conical surfaces 2, 3 are oriented so that the outer diameter 28 (shown in the figure is half the outer diameter 28) of the flow channel 4 in the main flow direction 17 decreases.

Alternativ sind der Innenkegelring 23 und der Außenkegelring 24 derart modifiziert, dass die Kegelinnenfläche 3 und die Kegelaußenfläche 2 entlang der jeweiligen Mantellinie 6 und entlang der Breite der Justierschaufel 7 in jedem Querschnitt senkrecht zur Welle 21 segmentweise gleiche Krümmungsradien haben, so dass beim Verschieben der Justierschaufel 7 die Erstreckungen der Radialspalte zwischen der Justierschaufel 7 und den Kegelflächen 2, 3 konstant bleiben. Denkbar ist beispielsweise, dass die Krümmungsradien unendlich groß sind, so dass jeder der Querschnitte der Kegelflächen 2, 3 senkrecht zur Welle 21 jeweils ein Polygon bildet, wobei an jeder der Streckensegmente des Polygons jeweils eine Schaufel angeordnet ist. Stromab der Hauptströmungsrichtung 17 wird die Länge jeder der Streckensegmente des Polygons kürzer.Alternatively, the inner cone ring 23 and the outer cone ring 24 are modified such that the cone inner surface 3 and the cone outer surface 2 along the respective surface line 6 and along the width of Justierschaufel 7 in each cross-section perpendicular to the shaft 21 have the same curvature radii, so that when moving the Justierschaufel 7, the extensions of the radial gaps between the Justierschaufel 7 and the conical surfaces 2, 3 remain constant. It is conceivable, for example, that the radii of curvature are infinitely large, so that each of the cross sections of the conical surfaces 2, 3 forms a polygon perpendicular to the shaft 21, wherein a blade is arranged on each of the segments of the polygon. Downstream of the main flow direction 17, the length of each of the path segments of the polygon becomes shorter.

Ebenso ist denkbar, dass jeder der Querschnitte senkrecht zur Welle 21 aus einer Mehrzahl von Kreissegmenten gebildet ist. Die Krümmungsradien der Kreissegmente können dabei sowohl größer als auch kleiner als die Radien des Strömungskanals 4 sein. Stromab der Hauptströmungsrichtung 17 wird die Erstreckung jeder der Kreissegmente kürzer, wohingegen der Krümmungsradius jeweils konstant bleibt.It is also conceivable that each of the cross sections is formed perpendicular to the shaft 21 of a plurality of circle segments. The radii of curvature of the circular segments can be both larger and smaller than the radii of the flow channel 4. Downstream of the main flow direction 17, the extent of each of the circle segments becomes shorter, whereas the radius of curvature remains constant in each case.

Denkbar sind nicht nur Strecken oder Kreissegmente für die Querschnitte der Kegelflächen 2, 3 sondern auch andere Formen, dessen Querschnitte sich entlang der Mantellinie 6 nicht ändern. Ebenso ist das Vorsehen von unterschiedlichen Formen für die Kegelaußenfläche 2 und die Kegelinnenfläche 3 denkbar, beispielsweise ein Polygon für die Kegelaußenfläche 2 und Kreissegmente für die Kegelinnenfläche 3.Not only distances or circular segments for the cross sections of the conical surfaces 2, 3 but also other shapes whose cross sections do not change along the surface line 6 are conceivable. Likewise, the provision of different shapes for the cone outer surface 2 and the inner cone surface 3 is conceivable, for example a polygon for the cone outer surface 2 and circle segments for the inner surface of the cone 3.

Innerhalb des Strömungskanals 4 ist eine Justierschaufel 7 angeordnet, die mit ihrer Radialaußenseite 9 an der Kegelaußenfläche 2 und mit ihrer Radialinnenseite 10 an der Kegelinnenfläche 3 angeordnet ist. Die Justierschaufel 7 weist an ihrer Radialinnenseite 9 und ihrer Radialaußenseite 10 jeweils einen Zapfen 15 auf, wobei die Zapfen 15 jeweils in eine Gleitnut 14 im Innenkegelring 23 und im Außenkegelring 24 eingreifen. Die Gleitnuten 14 sind zueinander parallel angeordnet und verlaufen jeweils entlang einer Mantellinie 6 der Kegelflächen 2, 3, so dass die Justierschaufel 7 parallel zu den Mantellinien 6 verschiebbar ist. Wird die Justierschaufel 7 in der Hauptströmungsrichtung 17 verschoben, so verringert sich der Abstand in Umfangsrichtung der Justierschaufel 7 zu den ihr im ersten Leitschaufelkranz 11 benachbart angeordneten Schaufeln, wodurch die Versperrung für das Fluid 25 in dem ersten Leitschaufelkranz 11 zunimmt. Durch die zunehmende Versperrung verringert sich die Schluckfähigkeit des ersten Leitschaufelkranzes 11. Umgekehrt kann die Schluckfähigkeit vergrößert werden, indem die Justierschaufel 7 stromauf der Hauptströmungsrichtung 17 verschoben wird. Der maximal mögliche Verschiebeweg 8 der Justierschaufel 7 ist durch die Länge des Strömungskanals 4 in der Hauptströmungsrichtung 17 und die Länge der Gleitnuten 14 begrenzt. Zur Veränderung der Schluckfähigkeit ist es ebenso denkbar, dass die Justierschaufel 7 durch eine andere Justierschaufel ersetzt wird, die eine kürzere oder längere Sehnenlänge hat.Within the flow channel 4 a Justierschaufel 7 is arranged, which is arranged with its radial outer side 9 on the cone outer surface 2 and with its radially inner side 10 on the inner surface of the cone 3. The Justierschaufel 7 has on its inner radial side 9 and its radial outer side 10 each have a pin 15, wherein the pins 15 each engage in a sliding groove 14 in the inner cone ring 23 and the outer taper ring 24. The slide grooves 14 are arranged parallel to each other and each extend along a surface line 6 of the conical surfaces 2, 3, so that the Justierschaufel 7 is parallel to the generatrices 6 slidably. When the adjusting blade 7 is displaced in the main flow direction 17, the distance in the circumferential direction of the adjusting blade 7 is reduced to the blades arranged adjacent to it in the first guide blade ring 11, whereby the obstruction for the fluid 25 in the first guide blade ring 11 increases. Increased obstruction reduces the ability of the first vane ring 11 to absorb moisture. Conversely, the ability to swallow can be increased by displacing the adjusting vane 7 upstream of the main flow direction 17. The maximum possible displacement 8 of the adjusting blade 7 is limited by the length of the flow channel 4 in the main flow direction 17 and the length of the Gleitnuten 14. To change the ability to swallow, it is also conceivable that the adjusting blade 7 is replaced by another adjusting blade, which has a shorter or longer chord length.

Für die Gleitnuten 14 und die Zapfen 15 sind verschiedene Formen denkbar, wie z.B. eine T-Form oder eine schwalbenschwanzartige Form. Die Gleitnut 14 in der Kegelinnenfläche 3 ist in der Hauptströmungsrichtung 17 von einem Anschlag 29 begrenzt, d.h. sie ist nicht bis zu dem stromab liegenden Ende 5 des Strömungskanals 4 geführt, so dass im Betrieb der Axialturbomaschine 1 die Justierschaufel 7 durch die Strömung des Fluids 25 an den Anschlag 29 gedrückt wird. Es ist ebenso möglich, die Gleitnut 14 in der Kegelaußenfläche 2 in der Hauptströmungsrichtung 17 von einem Anschlag zu begrenzen oder beide Gleitnuten 14 von einem Anschlag zu begrenzen. Stromauf der Hauptströmungsrichtung 17 sind die Gleitnuten 14 nicht begrenzt, so dass die Justierschaufel 7 aus dem Strömungskanal 4 herausnehmbar und gegen eine andere Justierschaufel tauschbar ist.For the slide grooves 14 and the pins 15, various shapes are conceivable, e.g. a T-shape or dovetail-like shape. The sliding groove 14 in the tapered inner surface 3 is limited in the main flow direction 17 by a stop 29, i. it is not guided to the downstream end 5 of the flow channel 4, so that during operation of the axial turbomachine 1, the Justierschaufel 7 is pressed by the flow of the fluid 25 to the stop 29. It is also possible to limit the sliding groove 14 in the conical outer surface 2 in the main flow direction 17 of a stop or to limit both Gleitnuten 14 of a stop. Upstream of the main flow direction 17, the sliding grooves 14 are not limited, so that the adjusting blade 7 is removable from the flow channel 4 and exchangeable with another adjusting blade.

Wie es aus der Figur ersichtlicht ist, sind zum Feststellen der Position der Justierschaufel 7 in den Gleitnuten 14 Abstandsstücke 16 vorgesehen. Die Abstandsstücke 16 sind sowohl auf der stromab liegenden Seite der Zapfen 15, als auch auf der stromauf liegenden Seite der Zapfen 15 angeordnet. Es ist prinzipiell möglich, keine Abstandsstücke 16 auf der stromauf liegenden Seite vorzusehen, weil die Justierschaufel 7 im Betrieb gegen die stromab liegenden Abstandsstücke 16 oder gegen das Ende der Gleitnut 14 gedrückt wird. Die für die Justierschaufel 7 minimal mögliche Schluckfähigkeit wird erreicht, wenn keine der Abstandsstücke 16 auf der stromab liegenden Seite vorgesehen werden.As can be seen from the figure, 14 spacers 16 are provided for detecting the position of the Justierschaufel 7 in the Gleitnuten. The spacers 16 are arranged both on the downstream side of the pins 15, as well as on the upstream side of the pins 15. It is in principle possible to provide no spacers 16 on the upstream side, because the Justierschaufel 7 is pressed in operation against the downstream spacers 16 or against the end of the sliding groove 14. The minimum possible absorption capacity for the adjusting blade 7 is achieved if none of the spacers 16 are provided on the downstream side.

Es sind alle Schaufeln in dem ersten Laufschaufelkranz 11 als die Justierschaufeln 7 ausgebildet und damit verschiebbar ausgeführt. Alternativ könnten die Schaufeln abwechselnd als die Justierschaufeln 7 ausgebildet und fest an den Kegelflächen 2, 3 angebracht ausgeführt sein. Dabei ist denkbar, dass der Innenkegelring 23, der Außenkegelring 24 und die fest angebrachten Schaufeln aus einem Stück gefertigt sind. Ebenso ist denkbar, dass jeweils eine fest angebrachte Schaufel zusammen mit jeweils einem Segment des Innenkegelrings 23 und des Außenkegelrings 24 aus einem Stück gefertigt ist und somit der erste Leitschaufelkranz 11 aus einer Vielzahl von Segmenten zusammengesetzt ist.All the blades in the first blade ring 11 are designed as adjusting blades 7 and thus designed to be displaceable. Alternatively, the blades could alternately as the adjusting blades 7 are formed and designed to be fixed to the conical surfaces 2, 3. It is conceivable that the inner cone ring 23, the outer cone ring 24 and the fixed blades are made of one piece. It is also conceivable that in each case a fixed blade together with one segment of the inner cone ring 23 and the outer cone ring 24 is made of one piece and thus the first vane ring 11 is composed of a plurality of segments.

Es ist denkbar, dass die Justierschaufeln 7 für ebenfalls einen Laufschaufelkranz vorgesehen sind. Dabei sind der Innenkegelring 23 fest mit der Welle 21 verbunden und die Justierschaufel 7 mit ihrer Radialinnenseite 10 verschiebbar an dem Innenkegelring 23 angeordnet. Der Innenkegelring 23 und die Justierschaufel 7 sind somit rotierende Komponenten der Axialturbomaschine 1. Zwischen der Radialaußenseite 9 der verschiebbaren Schaufel 7 und der Kegelaußenfläche 2 könnte ein Spalt vorgesehen sein. Die Justierschaufel 7 könnte ebenfalls mit ihrer Radialaußenseite 9 mit dem Außenkegelring 24 in Eingriff stehen. In letzterem Fall wäre der Außenkegelring 24 ebenfalls eine rotierende Komponente.It is conceivable that the Justierschaufeln 7 are also provided for a blade ring. In this case, the inner cone ring 23 are fixedly connected to the shaft 21 and the Justierschaufel 7 with its radially inner side 10 slidably disposed on the inner cone ring 23. The inner cone ring 23 and the Justierschaufel 7 are thus rotating components of the axial turbomachine 1. Between the radial outer side 9 of the movable blade 7 and the cone outer surface 2, a gap could be provided. The Justierschaufel 7 could also be with its outer radial side 9 with the outer cone ring 24 in engagement. In the latter case, the outer cone ring 24 would also be a rotating component.

Das Justieren der Schluckfähigkeit des ersten Leitschaufelkranzes 11 ist wie folgt durchzuführen: Vorherbestimmen eines Soll-Werts der Schluckfähigkeit des Schaufelkranzes 11; Ermitteln des Ist-Werts der Schluckfähigkeit des Schaufelkranzes 11; Vergleichen des Soll-Werts der Schluckfähigkeit des Schaufelkranzes 11 mit dem Ist-Wert der Schluckfähigkeit des Schaufelkranzes 11; Verschieben der mindestens einen Justierschaufel 7 mittels der Führungseinrichtung parallel zu der Mantellinie 6 derart, dass der Soll-Wert der Schluckfähigkeit gleich wird mit dem Ist-Wert der Schluckfähigkeit; Feststellen der Justierschaufel 7 mit der Führungseinrichtung.The adjustment of the absorption capacity of the first vane ring 11 is to be carried out as follows: predetermining a desired value of the ability to swallow the blade ring 11; Determining the actual value of the swallowability of the blade ring 11; Comparing the target value of the ability to swallow of the blade ring 11 with the actual value of the ability to swallow the blade ring 11; Moving the at least one adjusting blade 7 by means of the guide device parallel to the generating line 6 such that the desired value of the swallowing ability becomes equal to the actual value of the swallowing ability; Detecting the Justierschaufel 7 with the guide device.

Obwohl die Erfindung im Detail durch die bevorzugten Ausführungsbeispiele näher illustriert und beschrieben wurde, so ist die Erfindung nicht durch die offenbarten Beispiele eingeschränkt und andere Variationen können vom Fachmann hieraus abgeleitet werden, ohne den Schutzumfang der Erfindung zu verlassen.Although the invention has been further illustrated and described in detail by the preferred embodiments, the invention is not limited by the disclosed examples and other variations can be derived therefrom by those skilled in the art without departing from the scope of the invention.

Claims (13)

  1. Blade ring for an axial turbomachine (1),
    having an outer face (2) which is arranged on an outer ring (24) and is oriented radially inward, and an inner face (3) which is arranged on an inner ring (23) and is oriented radially outward, which faces are arranged concentrically and parallel with one another and delimit an annular flow duct (4) which tapers in the main flow direction (17) of the axial turbomachine (1), characterized by at least one adjustment blade (7) which is arranged such that it can be displaced, in the flow duct (4), parallel to a side line (6) of one of the faces (2, 3) by means of a guiding device (14, 15), and which can be secured in a predetermined position on at least one of the rings (23, 24).
  2. Blade ring according to Claim 1,
    wherein the outer face (2) and the inner face (3) are conical faces.
  3. Blade ring according to Claim 1,
    wherein the outer face (2) and the inner face (3) have, in segments along the respective side line (6), identical radii of curvature in every cross section perpendicular to the axis of the flow duct (4) such that, when the adjustment blade (7) is displaced, the radial gaps between the adjustment blade (7) and the faces (2, 3) remain constant.
  4. Blade ring according to Claim 3,
    wherein each of the cross sections of the outer face (2) and of the inner face (3) is in each case formed, perpendicular to the axis of the flow duct (4), from a polygon or from a plurality of circle segments which are arranged immediately adjacent to one another.
  5. Blade ring according to one of Claims 1 to 4,
    wherein the blade ring (11) is a diagonal stage of the axial turbomachine (1).
  6. Blade ring according to one of Claims 1 to 5,
    wherein the blade ring (11) has a plurality of blades, wherein the blades are, in alternation, the adjustment blades (7) and blades which are securely attached to the outer face (2) and/or to the inner face (3).
  7. Blade ring according to Claim 6,
    wherein each of the securely attached blades is made in one piece together with the inner ring (23) and the outer ring (24) or in one piece together with a segment of the inner ring (23) and a segment of the outer ring (24).
  8. Blade ring according to one of Claims 1 to 7,
    wherein the guiding device has a sliding groove (14) in the inner ring (23) and/or in the outer ring (24), and a peg (15) on the radial outer side (9) and/or on the radial inner side (10) of the adjustment blade (7), wherein the peg (15) engages in the sliding groove (14).
  9. Blade ring according to Claim 8,
    wherein the guiding device has, in at least one of the sliding grooves (14) downstream in the main flow direction (17) of the axial turbomachine (1), an endstop (29) by means of which the adjustment blade (7) can be secured in the predetermined position.
  10. Blade ring according to one of Claims 1 to 9,
    wherein the guiding device (14, 15) is set up such that the at least one adjustment blade (7) can be exchanged for another adjustment blade.
  11. Axial turbomachine having a blade ring (11) according to one of Claims 1 to 10.
  12. Axial turbomachine according to Claim 11,
    wherein the maximum flow rate of the axial turbomachine (1) is defined by the maximum flow rate of the blade ring (11).
  13. Method for adjusting the maximum flow rate of a blade ring (11) according to one of Claims 1 to 10,
    having the steps of:
    - predetermining a setpoint value for the maximum flow rate of the blade ring (11);
    - determining the actual value of the maximum flow rate of the blade ring (11);
    - comparing the actual value of the maximum flow rate of the blade ring (11) with the setpoint value for the maximum flow rate of the blade ring (11);
    - displacing the at least one adjustment blade (7) by means of the guiding device (14, 15) parallel to the side line (6) such that the setpoint value for the maximum flow rate is the same as the actual value of the maximum flow rate;
    - securing the adjustment blade (7) with the guiding device (14, 15).
EP12786929.5A 2012-02-02 2012-11-07 Blade ring for an axial turbo engine and method for adjusting the absorption characteristics of the blade ring Not-in-force EP2788586B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP12786929.5A EP2788586B1 (en) 2012-02-02 2012-11-07 Blade ring for an axial turbo engine and method for adjusting the absorption characteristics of the blade ring

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP12153630.4A EP2623717A1 (en) 2012-02-02 2012-02-02 Blade ring for an axial turbo engine and method for adjusting the absorption characteristics of the blade ring
PCT/EP2012/071992 WO2013113415A1 (en) 2012-02-02 2012-11-07 Blade ring for an axial turbomachine, and a method for adjusting the maximum flow rate of said blade ring
EP12786929.5A EP2788586B1 (en) 2012-02-02 2012-11-07 Blade ring for an axial turbo engine and method for adjusting the absorption characteristics of the blade ring

Publications (2)

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EP2788586A1 EP2788586A1 (en) 2014-10-15
EP2788586B1 true EP2788586B1 (en) 2016-01-20

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EP12153630.4A Withdrawn EP2623717A1 (en) 2012-02-02 2012-02-02 Blade ring for an axial turbo engine and method for adjusting the absorption characteristics of the blade ring
EP12786929.5A Not-in-force EP2788586B1 (en) 2012-02-02 2012-11-07 Blade ring for an axial turbo engine and method for adjusting the absorption characteristics of the blade ring

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EP12153630.4A Withdrawn EP2623717A1 (en) 2012-02-02 2012-02-02 Blade ring for an axial turbo engine and method for adjusting the absorption characteristics of the blade ring

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US (1) US20150030431A1 (en)
EP (2) EP2623717A1 (en)
JP (1) JP5855768B2 (en)
CN (1) CN104105844B (en)
WO (1) WO2013113415A1 (en)

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IT201700061762A1 (en) * 2017-06-06 2018-12-06 Ansaldo Energia Spa STATIC GROUP FOR A STAGE OF RADIAL-AXIAL EXPANSION OF STEAM TURBINE

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Also Published As

Publication number Publication date
JP2015506439A (en) 2015-03-02
CN104105844A (en) 2014-10-15
CN104105844B (en) 2016-03-16
EP2623717A1 (en) 2013-08-07
JP5855768B2 (en) 2016-02-09
WO2013113415A1 (en) 2013-08-08
EP2788586A1 (en) 2014-10-15
US20150030431A1 (en) 2015-01-29

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