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EP2984295B1 - Seal ring segment for a stator of a turbine - Google Patents

Seal ring segment for a stator of a turbine Download PDF

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Publication number
EP2984295B1
EP2984295B1 EP14734785.0A EP14734785A EP2984295B1 EP 2984295 B1 EP2984295 B1 EP 2984295B1 EP 14734785 A EP14734785 A EP 14734785A EP 2984295 B1 EP2984295 B1 EP 2984295B1
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EP
European Patent Office
Prior art keywords
sealing ring
ring segment
turbine
stator
elastic element
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.)
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Application number
EP14734785.0A
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German (de)
French (fr)
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EP2984295A1 (en
Inventor
Thorsten Barz
Roland Häbel
Sebastian Stupariu-Cohan
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Siemens AG
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Siemens AG
Siemens Corp
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Priority to EP14734785.0A priority Critical patent/EP2984295B1/en
Publication of EP2984295A1 publication Critical patent/EP2984295A1/en
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Publication of EP2984295B1 publication Critical patent/EP2984295B1/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
    • 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
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • 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
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position

Definitions

  • the invention relates to a sealing ring segment for a stator of a turbine, which essentially has the shape of a cylinder jacket segment and has on its outer side a groove for fixing a plurality of guide vanes.
  • a turbine is a turbomachine that converts the internal energy (enthalpy) of a flowing fluid (liquid or gas) into rotational energy and ultimately into mechanical drive energy.
  • the fluid flow is removed by the vortex-free as possible laminar flow around the turbine blades a portion of its internal energy, which passes to the blades of the turbine.
  • the turbine shaft is rotated, the usable power is delivered to a coupled machine, such as a generator.
  • Blades and shaft are parts of the movable rotor or rotor of the turbine, which is arranged within a housing.
  • Blades mounted on the axle are mounted on the axle. Blades mounted in a plane each form a paddle wheel or impeller. The blades are slightly curved profiled, similar to an aircraft wing. Before each impeller is usually a stator. These vanes protrude from the housing into the flowing medium and cause it to spin. The swirl generated in the stator (kinetic energy) is used in the following impeller to set the shaft on which the impeller blades are mounted in rotation.
  • the stator and the impeller together are called stages. Often several such stages are connected in series. Since the stator is stationary, and the vanes are attached to the housing exterior, a seal must be made to the shaft of the impeller to minimize losses.
  • the guide vanes are held on the rotor side by cylinder jacket-shaped sealing rings. These usually consist of a plurality, usually ten segments. These are pushed onto an entanglement at the head of the vanes (tongue and groove connection) and thus seal off the hot gas duct in relation to the rotor. In order to prevent displacement in the circumferential direction, the sealing ring segments are individually fixed by bolts, each of which projects radially into one of the guide vanes.
  • a disadvantage of the known sealing ring segments is that when using sheet or large disc springs always a large-scale bias is applied to a plurality of vanes. This complicates the assembly of the vanes. In addition, the strength of the restoring force can not be individually adjusted or readjusted.
  • sealing ring segment for each fixable on the sealing ring segment vane each having at least one acting on the respective vane by means of a restoring force pressure pin which is formed as a cylindrical element which can be compressed in the axial direction.
  • the invention is based on the consideration that the life of the turbine increased and the repair cost for the turbine could be reduced if the wear could be reduced by the relative movement of individual vanes and sealing ring segment. For this, the relative movement would have to be limited. However, consideration must be given to the thermal expansion during operation, so that a fixed form-locking fixation is eliminated. Remedy creates a non-positive fixation by means of a pressure bolt, which ensures a force-locking fixation of the guide vane by its restoring force, while by the elasticity thermal expansion remains possible.
  • a pressure pin is a substantially cylindrical element which can be compressed in the axial direction, for example by an internal structure in the manner of a piston. In this case, the pressure pin z. B.
  • the pressure pin can be fixed by a corresponding opening in the sealing ring segment and aligned accordingly.
  • at least one pressure bolt acting on the respective guide blade by means of a restoring force is provided for each guide vane which can be fixed to the sealing ring segment.
  • the groove for fixing the guide vanes advantageously extends in the circumferential direction and / or the restoring force of the respective elastic element advantageously acts in the radial direction. This allows easy installation of the sealing ring segment, which can be easily pushed onto the entanglement of the guide vanes. Due to the radial orientation of the elastic element this can be biased from the inside after insertion of the sealing ring.
  • the respective elastic element in particular the pressure pin comprises a plate spring.
  • a diaphragm spring is understood to mean a conical annular shell which can be loaded in the axial direction and thus can be stressed in both stationary and oscillating (dynamic). The force is usually applied via the upper inner edge and the lower outer edge.
  • the diaphragm spring can be used as a single spring or as a spring column. In a column, either individual disc springs or spring assemblies consisting of several springs can be stacked alternately.
  • the diaphragm spring has in comparison with other types of springs a number of advantageous properties, it may, for. B. accommodate very large forces in a small installation space.
  • the diaphragm spring has a long service life under dynamic load, as z. B. occurs in a turbine.
  • Suitable materials include spring steels, also stainless and heat-resistant as well as copper (CuSn 8, CuBe 2) and nickel alloys (Nimonic, Inconel, Duratherm).
  • the respective elastic element in particular the pressure pin by means of a screw on the sealing ring segment fixed.
  • this results in a detachable connection, which thus allows a later replacement in the course of a revision, on the other hand allows a simple assembly.
  • the restoring force on the entanglement of the guide blade is precisely adjusted by the depth of the screwing.
  • an anti-rotation is provided, for example by a side einhakenden anti-rotation bolt.
  • the respective elastic element for the circumferential fixation of the sealing ring segment is arranged such that it fixes the respective guide vane in the circumferential direction in a form-fitting manner.
  • the guide vane has a corresponding recess into which the correspondingly executed elastic element is inserted.
  • a plurality of the vanes are arranged at their radially inwardly directed head by means of a spring in a groove of a described sealing ring segment.
  • a turbine advantageously comprises such a stator.
  • the turbine is designed as a gas turbine.
  • the thermal, mechanical and dynamic loads are particularly high, so that the described configuration of the sealing ring segment offers particular advantages in terms of minimizing wear.
  • a power plant advantageously comprises such a turbine.
  • the advantages achieved by the invention are, in particular, that by introducing a cup spring design for the defined fixed bias of the sealing ring and the vane, an avoidance of relative movements between the two parts is achieved. At the same time a thermal mobility is hereby ensured despite fixed bias. With the disc spring structures described a defined tension between blades and sealing ring segments can be applied, which minimizes or prevents the relative movement, in particular under dynamic loads between the components. The material wear can thus be reduced or avoided.
  • the FIG. 1 shows a turbine 100, here a gas turbine, in a longitudinal partial section.
  • the gas turbine 100 has inside a rotatably mounted around a rotation axis 102 (axial direction) rotor 103, which is also referred to as a turbine runner.
  • a rotation axis 102 axial direction
  • rotor 103 which is also referred to as a turbine runner.
  • an intake housing 104 a compressor 105
  • a combustion chamber 110 shown here as an annular combustion chamber 106, with a plurality of coaxially arranged burners 107, a turbine 108 and the exhaust housing 109th
  • the combustion chamber 106 communicates with an annular hot gas channel 111.
  • turbine stages 112 connected in series form the turbine 108.
  • Each turbine stage 112 is formed from two blade rings.
  • a guide blade ring 115 is followed by a ring 125 formed of rotor blades 120.
  • the guide vanes 130 are fastened to the stator 143, whereas the rotor blades 120 of a ring 125 are attached to the rotor 103 by means of a turbine disk 133.
  • the rotor blades 120 thus form components of the rotor or rotor 103.
  • Coupled to the rotor 103 is a generator or a working machine (not shown).
  • air 105 is sucked in and compressed by the compressor 105 through the intake housing 104.
  • the compressed air provided at the turbine-side end of the compressor 105 is supplied to the burners 107 where it is mixed with a fuel.
  • the mixture is then burned to form the hot and pressurized working fluid 113 in the combustor 110.
  • the working medium 113 flows along the hot gas channel 111 past the guide vanes 130 and the rotor blades 120.
  • the working medium 113 expands in a pulse-transmitting manner so that the rotor blades 120 drive the rotor 103 and drive the machine coupled to it.
  • the components exposed to the hot working medium 113 are subject to thermal loads during operation of the gas turbine 100.
  • the guide vanes 130 and rotor blades 120 of the first turbine stage 112, viewed in the direction of flow of the working medium 113, are subjected to the highest thermal load in addition to the heat shield stones lining the combustion chamber 106. In order to withstand the temperatures prevailing there, they are cooled by means of a coolant.
  • Each vane 130 has a vane root (not shown) facing the housing 138 of the turbine 108 and a vane head opposite the vane root.
  • the vane head faces the rotor 103 and is fixed in a sealing ring 140.
  • Each sealing ring 140 of a turbine stage encloses the shaft of the rotor 103. It is advantageously formed of ten similar sealing ring segments 144.
  • sealing pins 146 are provided in the sealing ring segments, which in FIG. 2 are shown in cross section.
  • the pressure pin 146 is fixed in a radially aligned through bore 148 with a thread 150 by screwing.
  • the pressure pin consists of a cylindrical portion 152 with a corresponding thread for screwing with the sealing ring segment, an adjoining piston 154 of smaller diameter, on which a in the axial direction of the pressure pin 146 movable capsule 156 sits, which surrounds the piston 154 at its tip , As a result, it is fixed in a form-fitting manner in the radial direction of the pressure bolt 146.
  • the piston 154 between section 152 and capsule 156 enclosing a total of eight mutually arranged disc springs 158 are positioned, which exert a restoring force at an axial compression of the pressure pin 146. Since the pressure pin 146 is screwed in the radial direction with respect to the axis of rotation of the gas turbine 102 in the sealing ring segment 144, it exerts a defined force on the entanglement the guide vane 130, so that relative movements are prevented, but thermal expansion remains possible. The return force can be adjusted via the screw-in depth.
  • FIG. 3 shows a longitudinal section through the sealing ring segment 144.
  • the sealing ring 144 has two both axially and radially spaced grooves 160 which extend in the circumferential direction and are open in the radial, each same direction.
  • the respective groove 160 is in this case encompassed by a section of the sealing ring segment 144 that is L-shaped in longitudinal section, whose first limb extends in the radial direction, and whose second limb extends in the axial direction of the turbine 100.
  • the pressure pin 146 is arranged in the region of the radially outer groove 160 such that the capsule 156 opens into an opening of the radially inner wall of the groove 160. Since the pressure pin 146 exerts a radial restoring force acting on the spring 162 in the groove 160, the spring 162 is thus pressed in the groove 160 against the radially aligned leg of the L-shaped portion of the sealing ring segment 144. The vane 130 is thus elastically fixed in the grooves 160.
  • the pressure pin 146 is secured against rotation by means of a bolt 164.
  • the bolt 164 is inserted through a axially extending bore which meets the bore 148 of the pressure bolt 146 and screwed. As a result, it exerts a lateral force on the thread of the pressure bolt 146 and fixes it non-positively.
  • FIG. 4 shows finally a partial section through the sealing ring 140 and the sealing ring segments 144.
  • the pressure pin 146 exert a restoring force on the guide vanes 130 as described.
  • One of the push pins 146 is additional designed as circumferential fixing bolt 166. It is longer than the remaining pressure pin 146 and protrudes into a depression 168 of a foot of a guide blade 130 which is molded onto it. As a result, the sealing ring segment 144 is fixed to the guide blade 130 in the circumferential direction.

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

Description

Die Erfindung betrifft ein Dichtringsegment für einen Stator einer Turbine, welches im Wesentlichen die Form eines Zylindermantelsegments aufweist und an seiner Außenseite eine Nut zur Fixierung einer Mehrzahl von Leitschaufeln aufweist.The invention relates to a sealing ring segment for a stator of a turbine, which essentially has the shape of a cylinder jacket segment and has on its outer side a groove for fixing a plurality of guide vanes.

Eine Turbine ist eine Strömungsmaschine, welche die innere Energie (Enthalpie) eines strömenden Fluids (Flüssigkeit oder Gas) in Rotationsenergie und letztlich in mechanische Antriebsenergie umwandelt. Dem Fluidstrom wird durch die möglichst wirbelfreie laminare Umströmung der Turbinenschaufeln ein Teil seiner inneren Energie entzogen, der auf die Laufschaufeln der Turbine übergeht. Über diese wird dann die Turbinenwelle in Drehung versetzt, die nutzbare Leistung wird an eine angekuppelte Arbeitsmaschine, wie beispielsweise an einen Generator, abgegeben. Laufschaufeln und Welle sind Teile des beweglichen Rotors oder Läufers der Turbine, der innerhalb eines Gehäuses angeordnet ist.A turbine is a turbomachine that converts the internal energy (enthalpy) of a flowing fluid (liquid or gas) into rotational energy and ultimately into mechanical drive energy. The fluid flow is removed by the vortex-free as possible laminar flow around the turbine blades a portion of its internal energy, which passes to the blades of the turbine. About this then the turbine shaft is rotated, the usable power is delivered to a coupled machine, such as a generator. Blades and shaft are parts of the movable rotor or rotor of the turbine, which is arranged within a housing.

In der Regel sind mehrere Schaufeln auf der Achse montiert. In einer Ebene montierte Laufschaufeln bilden jeweils ein Schaufelrad oder Laufrad. Die Schaufeln sind leicht gekrümmt profiliert, ähnlich einer Flugzeugtragfläche. Vor jedem Laufrad befindet sich üblicherweise ein Leitrad. Diese Leitschaufeln ragen vom Gehäuse in das strömende Medium hinein und versetzen es in einen Drall. Der im Leitrad erzeugte Drall (kinetische Energie) wird im darauffolgenden Laufrad genutzt, um die Welle, auf der die Laufradschaufeln montiert sind, in Rotation zu versetzen.As a rule, several blades are mounted on the axle. Blades mounted in a plane each form a paddle wheel or impeller. The blades are slightly curved profiled, similar to an aircraft wing. Before each impeller is usually a stator. These vanes protrude from the housing into the flowing medium and cause it to spin. The swirl generated in the stator (kinetic energy) is used in the following impeller to set the shaft on which the impeller blades are mounted in rotation.

Leitrad und Laufrad zusammen bezeichnet man als Stufe. Oft sind mehrere solcher Stufen hintereinandergeschaltet. Da das Leitrad stillsteht, und die Leitschaufeln am Gehäuseäußeren befestigt sind, muss zur Welle des Laufrads eine Abdichtung hergestellt werden, um Verluste so gering wie möglich zu halten. Hierzu sind die Leitschaufeln rotorseitig durch zylindermantelförmige Dichtringe gehalten. Diese bestehen üblicherweise aus einer Mehrzahl, üblicherweise zehn Segmenten. Diese werden auf eine Verhakung am Kopf der Leitschaufeln geschoben (Nut-Feder-Verbindung) und dichten so den Heißgaskanal gegenüber den Rotor ab. Um ein Verschieben in Umfangsrichtung zu verhindern, werden die Dichtringsegmente einzeln durch Bolzen, die jeweils radial in eine der Leitschaufeln ragen, fixiert.The stator and the impeller together are called stages. Often several such stages are connected in series. Since the stator is stationary, and the vanes are attached to the housing exterior, a seal must be made to the shaft of the impeller to minimize losses. For this purpose, the guide vanes are held on the rotor side by cylinder jacket-shaped sealing rings. These usually consist of a plurality, usually ten segments. These are pushed onto an entanglement at the head of the vanes (tongue and groove connection) and thus seal off the hot gas duct in relation to the rotor. In order to prevent displacement in the circumferential direction, the sealing ring segments are individually fixed by bolts, each of which projects radially into one of the guide vanes.

Aufgrund gegebener, für die im Betrieb übliche Wärmeausdehnung notwendiger Toleranzen zwischen Schaufeln und Dichtringen ist eine Relativbewegung möglich. Hierbei hat sich gezeigt, dass durch dynamische Anregungen erheblicher Verschleiß an den Dichtringsegmenten entstehen kann. Die Befunde reichen dabei von einfachem Verschleiß, welcher ein Austauschen während einer Revisionsmaßnahme notwendig macht, bis hin zu massivem Verschleiß, der zu einer Zwangsrevision mit Austausch des Dichtrings führen bzw. auch zu einem Turbinenschaden mit Schaufelschäden führen kann.Due to given, for the usual thermal expansion in operation necessary tolerances between blades and sealing rings, a relative movement is possible. It has been shown that dynamic wear can cause considerable wear on the sealing ring segments. The findings range from simple wear, which makes replacement during a revision measure necessary, to massive wear, which can lead to a forced revision with replacement of the sealing ring or even lead to a turbine damage with blade damage.

Hierbei ist es bekannt das Dichtringsegment mit auf die Leitschaufeln mittels einer Rückstellkraft wirkenden elastischen Elementen zu versehen. In der US 7,645,117 werden hierfür großflächig Tellerfedern angeordnet, in der US 2008/0019836 , der US 2011/0135479 und der EP 1 441 108 werden Blattfedern verwendet, die eine Krümmung oder Wellenform in azimutaler oder axialer Richtung aufweisen, so dass die entsprechende Vorspannung entsteht.It is known to provide the sealing ring segment with acting on the vanes by means of a restoring force elastic elements. In the US 7,645,117 For this purpose, large-area disc springs are arranged in the US 2008/0019836 , of the US 2011/0135479 and the EP 1 441 108 Leaf springs are used which have a curvature or waveform in the azimuthal or axial direction, so that the corresponding bias arises.

Nachteilig an den bekannten Dichtringsegmenten ist jedoch, dass bei der Verwendung von Blatt- oder großen Tellerfedern stets eine großflächige Vorspannung auf mehrere Leitschaufeln aufgebracht wird. Dies erschwert die Montage der Leitschaufeln. Zudem ist die Stärke der Rückstellkraft nicht individuell einstell- oder nachjustierbar.A disadvantage of the known sealing ring segments, however, is that when using sheet or large disc springs always a large-scale bias is applied to a plurality of vanes. This complicates the assembly of the vanes. In addition, the strength of the restoring force can not be individually adjusted or readjusted.

Es ist daher Aufgabe der Erfindung, ein Dichtringsegment der eingangs genannten Art anzugeben, welches eine höhere Lebensdauer und einen geringeren Reparaturaufwand für eine Turbine bei einfacher Montage und hoher Optimierbarkeit ermöglicht.It is therefore an object of the invention to provide a sealing ring segment of the type mentioned, which allows a longer life and lower repair costs for a turbine with a simple installation and high optimizability.

Diese Aufgabe wird erfindungsgemäß gelöst, indem das Dichtringsegment für jede an dem Dichtringsegment fixierbare Leitschaufel jeweils zumindest einen auf die jeweilige Leitschaufel mittels einer Rückstellkraft wirkenden Druckbolzen aufweist, der als zylinderförmiges Element ausgebildet ist, welches sich in axialer Richtung komprimieren lässt.This object is achieved by the sealing ring segment for each fixable on the sealing ring segment vane each having at least one acting on the respective vane by means of a restoring force pressure pin which is formed as a cylindrical element which can be compressed in the axial direction.

Die Erfindung geht dabei von der Überlegung aus, dass die Lebensdauer der Turbine erhöht und der Reparaturaufwand für die Turbine verringert werden könnte, wenn der Verschleiß durch die Relativbewegung einzelner Leitschaufeln und Dichtringsegment verringert werden könnte. Hierfür müsste die Relativbewegung beschränkt werden. Allerdings muss dabei auf die Wärmeausdehnung im Betrieb Rücksicht genommen werden, so dass eine feste formschlüssige Fixierung ausscheidet. Abhilfe schafft eine kraftschlüssige Fixierung mittels eines Druckbolzens, welcher durch seine Rückstellkraft eine kraftschlüssige Fixierung der Leitschaufel gewährleistet, während durch die Elastizität eine Wärmeausdehnung möglich bleibt. Ein Druckbolzen ist ein im Wesentlichen zylinderförmiges Element, welches sich in axialer Richtung komprimieren lässt, beispielsweise durch eine Innenstruktur in der Art eines Kolbens. Dabei ist der Druckbolzen z. B. durch entsprechende Federanordnung selbstrückstellend ausgestaltet. Der Druckbolzen lässt sich durch eine entsprechende Öffnung im Dichtringsegment fixieren und entsprechend ausrichten. Dabei ist für jede an dem Dichtringsegment fixierbare Leitschaufel jeweils zumindest ein auf die jeweilige Leitschaufel mittels einer Rückstellkraft wirkender Druckbolzen vorgesehen. Dadurch wird das Dichtringsegment besonders sicher fixiert, da eine kraftschlüssige Verbindung durch einen Druckbolzen mit jeder einzelnen Leitschaufel entsteht. Keine der Leitschaufeln kann daher eine Verschleiß erzeugende Relativbewegung ausführen.The invention is based on the consideration that the life of the turbine increased and the repair cost for the turbine could be reduced if the wear could be reduced by the relative movement of individual vanes and sealing ring segment. For this, the relative movement would have to be limited. However, consideration must be given to the thermal expansion during operation, so that a fixed form-locking fixation is eliminated. Remedy creates a non-positive fixation by means of a pressure bolt, which ensures a force-locking fixation of the guide vane by its restoring force, while by the elasticity thermal expansion remains possible. A pressure pin is a substantially cylindrical element which can be compressed in the axial direction, for example by an internal structure in the manner of a piston. In this case, the pressure pin z. B. configured by self-resetting by appropriate spring arrangement. The pressure pin can be fixed by a corresponding opening in the sealing ring segment and aligned accordingly. In this case, at least one pressure bolt acting on the respective guide blade by means of a restoring force is provided for each guide vane which can be fixed to the sealing ring segment. As a result, the sealing ring segment is fixed particularly securely, since a non-positive connection is formed by a pressure pin with each individual vane. Therefore, none of the vanes can perform a wear-producing relative movement.

In vorteilhafter Ausgestaltung des Dichtringsegments verläuft die Nut zur Fixierung der Leitschaufeln vorteilhafterweise in Umfangsrichtung und/oder die Rückstellkraft des jeweiligen elastischen Elements wirkt vorteilhafterweise in radialer Richtung. Dies ermöglicht eine einfache Montage des Dichtringsegments, das einfach auf die Verhakung der Leitschaufeln geschoben werden kann. Durch die radiale Ausrichtung des elastischen Elements kann dieses nach dem Einsetzen des Dichtrings von innen vorgespannt werden.In an advantageous embodiment of the sealing ring segment, the groove for fixing the guide vanes advantageously extends in the circumferential direction and / or the restoring force of the respective elastic element advantageously acts in the radial direction. This allows easy installation of the sealing ring segment, which can be easily pushed onto the entanglement of the guide vanes. Due to the radial orientation of the elastic element this can be biased from the inside after insertion of the sealing ring.

Vorteilhafterweise umfasst das jeweilige elastische Element, insbesondere der Druckbolzen eine Tellerfeder. Unter einer Tellerfeder versteht man eine kegelige Ringschale, die in Achsrichtung belastbar ist und so sowohl ruhend als auch schwingend (dynamische) beansprucht werden kann. Die Krafteinleitung erfolgt normalerweise über den oberen Innenrand und den unteren Außenrand. Die Tellerfeder kann dabei als Einzelfeder oder als Federsäule verwendet werden. In einer Säule können entweder einzelne Tellerfedern oder aus mehreren Federn bestehende Federpakete wechselsinnig geschichtet werden. Die Tellerfeder hat im Vergleich mit anderen Federarten eine Reihe von vorteilhaften Eigenschaften, so kann sie z. B. bei kleinem Einbauraum sehr große Kräfte aufnehmen. Ihre Federkennlinie kann je nach den Maßverhältnissen linear oder degressiv sein und durch geeignete Anordnung auch progressiv (steigend) gestaltet werden. Durch die fast beliebige Kombinationsmöglichkeit von Einzeltellerfedern kann die Kennlinie durch die Säulenlänge innerhalb weiter Grenzen variiert werden. Bei richtiger Dimensionierung hat die Tellerfeder eine hohe Lebensdauer bei dynamischer Belastung, wie sie z. B. in einer Turbine auftritt. Als Werkstoff kommen Federstähle, auch nichtrostende und warmfeste sowie Kupfer- (CuSn 8, CuBe 2) und Nickel-Legierungen (Nimonic, Inconel, Duratherm) in Frage.Advantageously, the respective elastic element, in particular the pressure pin comprises a plate spring. A diaphragm spring is understood to mean a conical annular shell which can be loaded in the axial direction and thus can be stressed in both stationary and oscillating (dynamic). The force is usually applied via the upper inner edge and the lower outer edge. The diaphragm spring can be used as a single spring or as a spring column. In a column, either individual disc springs or spring assemblies consisting of several springs can be stacked alternately. The diaphragm spring has in comparison with other types of springs a number of advantageous properties, it may, for. B. accommodate very large forces in a small installation space. Depending on the dimensional conditions, its spring characteristic can be linear or degressive and can also be designed progressively (rising) by suitable arrangement. Due to the almost any combination possibility of single-plate springs, the characteristic can be varied within wide limits by the column length. If properly dimensioned, the diaphragm spring has a long service life under dynamic load, as z. B. occurs in a turbine. Suitable materials include spring steels, also stainless and heat-resistant as well as copper (CuSn 8, CuBe 2) and nickel alloys (Nimonic, Inconel, Duratherm).

Weiterhin ist das jeweilige elastische Element, insbesondere der Druckbolzen mittels einer Verschraubung am Dichtringsegment fixiert. Hierdurch ergibt sich einerseits eine lösbare Verbindung, die somit einen späteren Austausch im Zuge einer Revision ermöglicht, andererseits eine einfache Montage erlaubt. Weiterhin wird durch die Tiefe des Einschraubens die Rückstellkraft auf die Verhakung der Leitschaufel präzise eingestellt. Um ein Lösen des Bolzens im Betrieb der Turbine zu verhindern, ist hierbei eine Verdrehsicherung vorgesehen, beispielsweise durch einen seitlich einhakenden Verdrehsicherungsbolzen.Furthermore, the respective elastic element, in particular the pressure pin by means of a screw on the sealing ring segment fixed. On the one hand, this results in a detachable connection, which thus allows a later replacement in the course of a revision, on the other hand allows a simple assembly. Furthermore, the restoring force on the entanglement of the guide blade is precisely adjusted by the depth of the screwing. In order to prevent loosening of the bolt during operation of the turbine, in this case an anti-rotation is provided, for example by a side einhakenden anti-rotation bolt.

In zusätzlicher vorteilhafter Ausgestaltung ist das jeweilige elastische Element für die Umfangsfixierung des Dichtringsegmentes derart angeordnet, dass es die jeweilige Leitschaufel in Umfangsrichtung formschlüssig fixiert. Hierfür weißt die Leitschaufel eine entsprechende Vertiefung auf, in die das entsprechend ausgeführte elastische Element eingeschoben wird. Dadurch übernimmt das elastische Element, insbesondere der Druckbolzen in der Art einer Doppelnutzung auch die Aufgabe des bislang verwendeten Umfangsfixierungsbolzens.In an additional advantageous embodiment, the respective elastic element for the circumferential fixation of the sealing ring segment is arranged such that it fixes the respective guide vane in the circumferential direction in a form-fitting manner. For this purpose, the guide vane has a corresponding recess into which the correspondingly executed elastic element is inserted. As a result, the elastic element, in particular the pressure pin in the manner of a double use, also takes over the task of the previously used circumferential fixing bolt.

In einem Stator für eine Turbine mit einer Anzahl von Leitschaufeln ist vorteilhafterweise eine Mehrzahl der Leitschaufeln an ihrem radial nach innen gerichteten Kopf mittels einer Feder in einer Nut eines beschriebenen Dichtringsegments angeordnet.In a stator for a turbine having a number of vanes, advantageously a plurality of the vanes are arranged at their radially inwardly directed head by means of a spring in a groove of a described sealing ring segment.

Eine Turbine umfasst vorteilhafterweise einen derartigen Stator.A turbine advantageously comprises such a stator.

Vorteilhafterweise ist die Turbine dabei als Gasturbine ausgelegt. Gerade in Gasturbinen sind die thermischen, mechanischen und dynamischen Belastungen besonders hoch, so dass die beschriebene Ausgestaltung des Dichtringsegments besondere Vorteile hinsichtlich der Minimierung des Verschleißes bietet.Advantageously, the turbine is designed as a gas turbine. Especially in gas turbines, the thermal, mechanical and dynamic loads are particularly high, so that the described configuration of the sealing ring segment offers particular advantages in terms of minimizing wear.

Eine Kraftwerksanlage umfasst vorteilhafterweise eine derartige Turbine.A power plant advantageously comprises such a turbine.

Die mit der Erfindung erzielten Vorteile bestehen insbesondere darin, dass durch die Einführung einer Tellerfederkonstruktion zur definierten festen Vorspannung von Dichtring und Leitschaufel eine Vermeidung von Relativbewegungen zwischen beiden Teilen erreicht wird. Gleichzeitig wird hiermit trotz fester Vorspannung eine Wärmebeweglichkeit sichergestellt. Mit den beschriebenen Tellerfederkonstruktionen kann eine definierte Verspannung zwischen Schaufeln und Dichtringsegmenten aufgebracht werden, die die Relativbewegung insbesondere bei dynamischen Belastungen zwischen den Bauteilen minimiert bzw. verhindert. Der Materialverschleiß kann somit reduziert bzw. vermieden werden.The advantages achieved by the invention are, in particular, that by introducing a cup spring design for the defined fixed bias of the sealing ring and the vane, an avoidance of relative movements between the two parts is achieved. At the same time a thermal mobility is hereby ensured despite fixed bias. With the disc spring structures described a defined tension between blades and sealing ring segments can be applied, which minimizes or prevents the relative movement, in particular under dynamic loads between the components. The material wear can thus be reduced or avoided.

Ein Ausführungsbeispiel der Erfindung wird anhand einer Zeichnung näher erläutert. Darin zeigen:

FIG 1
einen teilweisen Längsschnitt durch eine Gasturbine mit Ringbrennkammer,
FIG 2
einen Querschnitt durch einen Druckbolzen,
FIG 3
einen Querschnitt durch ein Dichtringsegment, und
FIG 4
einen Schnitt durch das Dichtringsegment.
An embodiment of the invention will be explained in more detail with reference to a drawing. Show:
FIG. 1
a partial longitudinal section through a gas turbine with annular combustion chamber,
FIG. 2
a cross section through a pressure pin,
FIG. 3
a cross section through a sealing ring segment, and
FIG. 4
a section through the sealing ring segment.

Gleiche Teile sind in allen Figuren mit denselben Bezugszeichen versehen.Identical parts are provided with the same reference numerals in all figures.

Die FIG 1 zeigt eine Turbine 100, hier eine Gasturbine, in einem Längsteilschnitt. Die Gasturbine 100 weist im Inneren einen um eine Rotationsachse 102 (Axialrichtung) drehgelagerten Rotor 103 auf, der auch als Turbinenläufer bezeichnet wird. Entlang des Rotors 103 folgen aufeinander ein Ansauggehäuse 104, ein Verdichter 105, eine Brennkammer 110, hier dargestellt als Ringbrennkammer 106, mit mehreren koaxial angeordneten Brennern 107, eine Turbine 108 und das Abgasgehäuse 109.The FIG. 1 shows a turbine 100, here a gas turbine, in a longitudinal partial section. The gas turbine 100 has inside a rotatably mounted around a rotation axis 102 (axial direction) rotor 103, which is also referred to as a turbine runner. Along the rotor 103 follow one another an intake housing 104, a compressor 105, a combustion chamber 110, shown here as an annular combustion chamber 106, with a plurality of coaxially arranged burners 107, a turbine 108 and the exhaust housing 109th

Die Brennkammer 106 kommuniziert mit einem ringförmigen Heißgaskanal 111. Dort bilden beispielsweise vier hintereinander geschaltete Turbinenstufen 112 die Turbine 108. Jede Turbinenstufe 112 wird aus zwei Schaufelringen gebildet. In Strömungsrichtung eines Arbeitsmediums 113 gesehen folgt im Heißgaskanal 111 einem Leitschaufelring 115 eine aus Laufschaufeln 120 gebildete Ring 125.The combustion chamber 106 communicates with an annular hot gas channel 111. There, for example, four turbine stages 112 connected in series form the turbine 108. Each turbine stage 112 is formed from two blade rings. As seen in the flow direction of a working medium 113, in the hot gas channel 111, a guide blade ring 115 is followed by a ring 125 formed of rotor blades 120.

Die Leitschaufeln 130 sind dabei am Stator 143 befestigt, wohingegen die Laufschaufeln 120 einer Ring 125 mittels einer Turbinenscheibe 133 am Rotor 103 angebracht sind. Die Laufschaufeln 120 bilden somit Bestandteile des Rotors oder Läufers 103. An dem Rotor 103 angekoppelt ist ein Generator oder eine Arbeitsmaschine (nicht dargestellt).The guide vanes 130 are fastened to the stator 143, whereas the rotor blades 120 of a ring 125 are attached to the rotor 103 by means of a turbine disk 133. The rotor blades 120 thus form components of the rotor or rotor 103. Coupled to the rotor 103 is a generator or a working machine (not shown).

Während des Betriebes der Gasturbine 100 wird vom Verdichter 105 durch das Ansauggehäuse 104 Luft 135 angesaugt und verdichtet. Die am turbinenseitigen Ende des Verdichters 105 bereitgestellte verdichtete Luft wird zu den Brennern 107 geführt und dort mit einem Brennstoff vermischt. Das Gemisch wird dann unter Bildung des heißen und unter Druck stehenden Arbeitsmediums 113 in der Brennkammer 110 verbrannt. Von dort aus strömt das Arbeitsmedium 113 entlang des Heißgaskanals 111 vorbei an den Leitschaufeln 130 und den Laufschaufeln 120. An den Laufschaufeln 120 entspannt sich das Arbeitsmedium 113 impulsübertragend, so dass die Laufschaufeln 120 den Rotor 103 antreiben und dieser die an ihn angekoppelte Arbeitsmaschine.During operation of the gas turbine 100, air 105 is sucked in and compressed by the compressor 105 through the intake housing 104. The compressed air provided at the turbine-side end of the compressor 105 is supplied to the burners 107 where it is mixed with a fuel. The mixture is then burned to form the hot and pressurized working fluid 113 in the combustor 110. From there, the working medium 113 flows along the hot gas channel 111 past the guide vanes 130 and the rotor blades 120. On the rotor blades 120, the working medium 113 expands in a pulse-transmitting manner so that the rotor blades 120 drive the rotor 103 and drive the machine coupled to it.

Die dem heißen Arbeitsmedium 113 ausgesetzten Bauteile unterliegen während des Betriebes der Gasturbine 100 thermischen Belastungen. Die Leitschaufeln 130 und Laufschaufeln 120 der in Strömungsrichtung des Arbeitsmediums 113 gesehen ersten Turbinenstufe 112 werden neben den die Brennkammer 106 auskleidenden Hitzeschildsteinen am meisten thermisch belastet. Um den dort herrschenden Temperaturen standzuhalten, werden diese mittels eines Kühlmittels gekühlt. Ebenso können die Schaufeln 120, 130 Beschichtungen gegen Korrosion (MCrAlX; M = Fe, Co, Ni, Seltene Erden) und Wärme (Wärmedämmschicht, beispielsweise ZrO2, Y2O4-ZrO2) aufweisen.The components exposed to the hot working medium 113 are subject to thermal loads during operation of the gas turbine 100. The guide vanes 130 and rotor blades 120 of the first turbine stage 112, viewed in the direction of flow of the working medium 113, are subjected to the highest thermal load in addition to the heat shield stones lining the combustion chamber 106. In order to withstand the temperatures prevailing there, they are cooled by means of a coolant. Likewise, the Blades 120, 130 have coatings against corrosion (MCrAlX, M = Fe, Co, Ni, rare earths) and heat (thermal barrier coating, eg ZrO2, Y2O4-ZrO2).

Jede Leitschaufel 130 weist einen dem Gehäuse 138 der Turbine 108 zugewandten Leitschaufelfuß (hier nicht dargestellt) und einen dem Leitschaufelfuß gegenüberliegenden Leitschaufelkopf auf. Der Leitschaufelkopf ist dem Rotor 103 zugewandt und in einem Dichtring 140 fixiert. Jeder Dichtring 140 einer Turbinenstufe umschließt dabei die Welle des Rotors 103. Er wird vorteilhafterweise aus zehn gleichartigen Dichtringsegmenten 144 gebildet.Each vane 130 has a vane root (not shown) facing the housing 138 of the turbine 108 and a vane head opposite the vane root. The vane head faces the rotor 103 and is fixed in a sealing ring 140. Each sealing ring 140 of a turbine stage encloses the shaft of the rotor 103. It is advantageously formed of ten similar sealing ring segments 144.

Aufgrund der gegebenen Toleranzen bei der Lagerung der Leitschaufeln 130 am Dichtring 140 kommt es zu Relativbewegungen der beiden Bauteile, die zu frühem Verschleiß und sogar Schäden an der Gasturbine 100 führen können.Due to the given tolerances in the storage of the guide vanes 130 on the sealing ring 140, there are relative movements of the two components, which can lead to premature wear and even damage to the gas turbine 100.

Daher sind in den Dichtringsegmenten 144 Druckbolzen 146 vorgesehen, die in FIG 2 im Querschnitt gezeigt sind. Der Druckbolzen 146 ist in einer in radialer Richtung ausgerichteten, durchgehenden Bohrung 148 mit einem Gewinde 150 durch Verschrauben fixiert. Der Druckbolzen besteht aus einem zylindrischen Abschnitt 152 mit einem entsprechenden Gewinde zur Verschraubung mit dem Dichtringsegment, einen sich daran anschließenden Kolben 154 mit geringerem Durchmesser, auf dem eine in axialer Richtung des Druckbolzens 146 bewegliche Kapsel 156 sitzt, die den Kolben 154 an dessen Spitze umschließt. Dadurch ist sie in radialer Richtung des Druckbolzens 146 formschlüssig fixiert.Therefore, 144 sealing pins 146 are provided in the sealing ring segments, which in FIG. 2 are shown in cross section. The pressure pin 146 is fixed in a radially aligned through bore 148 with a thread 150 by screwing. The pressure pin consists of a cylindrical portion 152 with a corresponding thread for screwing with the sealing ring segment, an adjoining piston 154 of smaller diameter, on which a in the axial direction of the pressure pin 146 movable capsule 156 sits, which surrounds the piston 154 at its tip , As a result, it is fixed in a form-fitting manner in the radial direction of the pressure bolt 146.

Den Kolben 154 zwischen Abschnitt 152 und Kapsel 156 umschließend sind insgesamt acht wechselseitig angeordnete Tellerfedern 158 positioniert, die bei einer axialen Stauchung des Druckbolzens 146 eine Rückstellkraft ausüben. Da der Druckbolzen 146 in radialer Richtung bezogen auf die Rotationsachse der Gasturbine 102 in das Dichtringsegment 144 eingeschraubt ist, übt es so eine definierte Kraft auf die Verhakung der Leitschaufel 130 aus, so dass Relativbewegungen unterbunden werden, eine Wärmeausdehnung aber möglich bleibt. Über die Einschraubtiefe lässt sich die Rückstellkraft einstellen.The piston 154 between section 152 and capsule 156 enclosing a total of eight mutually arranged disc springs 158 are positioned, which exert a restoring force at an axial compression of the pressure pin 146. Since the pressure pin 146 is screwed in the radial direction with respect to the axis of rotation of the gas turbine 102 in the sealing ring segment 144, it exerts a defined force on the entanglement the guide vane 130, so that relative movements are prevented, but thermal expansion remains possible. The return force can be adjusted via the screw-in depth.

FIG 3 zeigt einen Längsschnitt durch das Dichtringsegment 144. Der Dichtring 144 weist zwei sowohl axial als auch radial beabstandete Nuten 160 auf, die sich in Umfangsrichtung erstrecken und in radialer, jeweils gleicher Richtung geöffnet sind. Die jeweilige Nut 160 ist dabei von einem im Längsschnitt L-förmigen Abschnitt des Dichtringsegments 144 umfasst, dessen erster Schenkel sich in radialer Richtung, und dessen zweiter Schenkel sich in axialer Richtung der Turbine 100 erstreckt. Mit entsprechenden, sich in Umfangsrichtung erstreckenden Federn 162 des Kopfes der Leitschaufeln 130, die passgenau am Dichtringsegment 144 angeordnet sind, kann das Dichtringsegment 144 bei der Montage so auf den Leitschaufelkranz aufgeschoben werden. Der Druckbolzen 146 ist dabei im Bereich der radial äußeren Nut 160 derart angeordnet, dass die Kapsel 156 in einer Öffnung der radial inneren Wandung der Nut 160 mündet. Da der Druckbolzen 146 eine radiale Rückstellkraft ausübt, die auf die Feder 162 in der Nut 160 wirkt, wird die Feder 162 somit in der Nut 160 gegen den radial ausgerichteten Schenkel des L-förmigen Teils des Dichtringsegments 144 gepresst. Die Leitschaufel 130 wird somit elastisch in den Nuten 160 fixiert. FIG. 3 shows a longitudinal section through the sealing ring segment 144. The sealing ring 144 has two both axially and radially spaced grooves 160 which extend in the circumferential direction and are open in the radial, each same direction. The respective groove 160 is in this case encompassed by a section of the sealing ring segment 144 that is L-shaped in longitudinal section, whose first limb extends in the radial direction, and whose second limb extends in the axial direction of the turbine 100. With corresponding, circumferentially extending springs 162 of the head of the vanes 130, which are accurately fitted on the sealing ring segment 144, the sealing ring segment 144 can be pushed onto the guide vane ring during assembly. The pressure pin 146 is arranged in the region of the radially outer groove 160 such that the capsule 156 opens into an opening of the radially inner wall of the groove 160. Since the pressure pin 146 exerts a radial restoring force acting on the spring 162 in the groove 160, the spring 162 is thus pressed in the groove 160 against the radially aligned leg of the L-shaped portion of the sealing ring segment 144. The vane 130 is thus elastically fixed in the grooves 160.

Der Druckbolzen 146 ist gegen Verdrehen mittels eines Bolzens 164 gesichert. Der Bolzen 164 ist durch eine sich in axialer Richtung erstreckende Bohrung, die auf die Bohrung 148 des Druckbolzens 146 trifft eingeführt und verschraubt. Dadurch übt er eine seitliche Kraft auf das Gewinde des Druckbolzens 146 aus und fixiert diesen kraftschlüssig.The pressure pin 146 is secured against rotation by means of a bolt 164. The bolt 164 is inserted through a axially extending bore which meets the bore 148 of the pressure bolt 146 and screwed. As a result, it exerts a lateral force on the thread of the pressure bolt 146 and fixes it non-positively.

FIG 4 zeigt schließlich einen teilweisen Schnitt durch den Dichtring 140 und die Dichtringsegmente 144. Die Druckbolzen 146 üben wie beschrieben eine Rückstellkraft auf die Leitschaufeln 130 aus. Einer der Druckbolzen 146 ist zusätzlich als Umfangsfixierungsbolzen 166 ausgelegt. Er ist länger als die übrigen Druckbolzen 146 und ragt in eine ihm angeformte Vertiefung 168 eines Fußes einer Leitschaufel 130 hinein. Dadurch wird das Dichtringsegment 144 an der Leitschaufel 130 in Umfangsrichtung fixiert. FIG. 4 shows finally a partial section through the sealing ring 140 and the sealing ring segments 144. The pressure pin 146 exert a restoring force on the guide vanes 130 as described. One of the push pins 146 is additional designed as circumferential fixing bolt 166. It is longer than the remaining pressure pin 146 and protrudes into a depression 168 of a foot of a guide blade 130 which is molded onto it. As a result, the sealing ring segment 144 is fixed to the guide blade 130 in the circumferential direction.

Claims (9)

  1. Sealing ring segment (144) for a stator (143) of a turbine (100), said sealing ring segment (144) having substantially the shape of a cylinder casing segment and having on its outer side a groove (160) for fixing a plurality of guide vanes (130), characterized in that the sealing ring segment (144) has, for each guide vane (130) that is fixable to the sealing ring segment (144), in each case at least one pressure bolt (146) that acts on the respective guide vane (130) by means of a restoring force, said pressure bolt (146) being configured as a cylindrical element which can be compressed in the axial direction.
  2. Sealing ring segment (144) according to Claim 1,
    in which the groove (160) extends in the circumferential direction and/or the restoring force of the respective elastic element acts in the radial direction.
  3. Sealing ring segment (144) according to either of the preceding claims,
    in which the respective elastic element comprises a disk spring (158).
  4. Sealing ring segment (144) according to one of the preceding claims,
    in which the respective elastic element is fixed to the sealing ring segment (144) by means of a screw connection.
  5. Sealing ring segment (144) according to one of the preceding claims,
    in which the respective elastic element is arranged such that it fixes the respective guide vane (130) in a form-fitting manner in the circumferential direction.
  6. Stator (153) for a turbine (100) having a number of guide vanes (130), wherein a plurality of the guide vanes (130) are arranged at their radially inwardly directed root, by means of a spring (162), in a groove (160) in a sealing ring segment (144) according to one of Claims 1 to 5.
  7. Turbine (100) having a stator (153) according to Claim 6.
  8. Turbine (100) according to Claim 7, which is designed as a gas turbine.
  9. Power plant having a turbine (10) according to Claim 7 or 8.
EP14734785.0A 2013-06-28 2014-06-25 Seal ring segment for a stator of a turbine Active EP2984295B1 (en)

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PCT/EP2014/063432 WO2014207058A1 (en) 2013-06-28 2014-06-25 Sealing ring segment for a stator of a turbine
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CN107882599B (en) * 2017-11-01 2021-02-09 中国航发湖南动力机械研究所 Integral turbine outer ring connecting structure and turbine engine
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CN113294214B (en) * 2021-06-24 2022-07-22 上海万仞动力技术有限公司 Impulse turbine equipped with split joint partition plate

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US10215041B2 (en) 2019-02-26
JP2016523342A (en) 2016-08-08
WO2014207058A1 (en) 2014-12-31
SA515370314B1 (en) 2020-03-15
RU2016102766A3 (en) 2018-04-04
EP2984295A1 (en) 2016-02-17
RU2657390C2 (en) 2018-06-13
EP2818642A1 (en) 2014-12-31
CN105392966A (en) 2016-03-09
CN105392966B (en) 2018-03-20

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