EP0891471B1 - Thrust-compensating process and device for turbomachines - Google Patents
Thrust-compensating process and device for turbomachines Download PDFInfo
- Publication number
- EP0891471B1 EP0891471B1 EP97918065A EP97918065A EP0891471B1 EP 0891471 B1 EP0891471 B1 EP 0891471B1 EP 97918065 A EP97918065 A EP 97918065A EP 97918065 A EP97918065 A EP 97918065A EP 0891471 B1 EP0891471 B1 EP 0891471B1
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- EP
- European Patent Office
- Prior art keywords
- pressure
- inner casing
- turbomachine
- thrust compensation
- axial
- 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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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/26—Double casings; Measures against temperature strain in casings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/26—Double casings; Measures against temperature strain in casings
- F01D25/265—Vertically split casings; Clamping arrangements therefor
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D3/00—Machines or engines with axial-thrust balancing effected by working-fluid
- F01D3/04—Machines or engines with axial-thrust balancing effected by working-fluid axial thrust being compensated by thrust-balancing dummy piston or the like
Definitions
- the present invention relates to a method and a Device in a turbomachine with an outer and a Inner housing or guide vane carrier for thrust compensation.
- the field of application of the invention is included Turbomachines in pot design, the pressure of a axial fluid flowing through the turbomachine in the longitudinal direction of the shaft at least on the inner housing caused.
- DE 22 18 500 is a multi-shell housing a steam turbine for high steam pressures and temperatures described.
- live steam comes at high pressure into the inner case. After an expansion of about 20% of the The entire gradient of the turbine part is the steam through drilling led into the outer housing and so presses in the area further expansion course the inner housing in the area of the joints.
- guide vane carrier is chosen. in this connection the full live steam pressure is in the space between inside and Outer housing and thus presses the two support halves together.
- the term further includes the term "Inner housing" is always the constructive solution with a guide vane carrier.
- DE 22 18 500 discloses a multi-shell Steam turbine housing for high steam pressures and temperatures.
- An inner shell is made using a support ring clamped against the outer housing and thus axially fixed.
- the US 3,754,833 in turn or its priority document, the DE 20 54 465 describes a device for radial-centric heat-moving storage and centering of shaft seal housings on the outer casing of turbomachinery.
- the turbine shown there has a pot housing an axis-normal parting line.
- a carrying the guide vanes Inner housing is in the pot housing on a Lagerund Centering point used. This centering point will formed by a Uhde board cutter closure.
- Bypass channels in the inner housing are used for axial thrust compensation.
- the object of the present invention is therefore to create of a method for thrust compensation in a turbomachine and a corresponding design of the same.
- the invention is intended to produce axial forces in the longitudinal direction balance the wave.
- the invention provides that at least a first surface of the Exterior of part of the inner housing for axial thrust compensation divided into two sections for axial thrust compensation is applied, each with different pressure a distinction between the two pressures caused by at least one means, in particular a seal becomes.
- the exterior of a part of the inner housing is preferred pressurized to compensate for axial thrust, which is at least as large as the outlet pressure of the Is fluid, and preferably about as large as the inlet pressure.
- the Pressure for axial thrust compensation of the axial force of the outlet pressure towards the inner housing Because of the overlay both pressures result in a reduced resulting Pressure that also causes less thrust.
- This axial thrust compensation is particularly on the inner housing the turbomachine feasible. This ensures that the previous high construction costs for fixing the inner housing can be reduced. The occurring on the fixing elements Surface pressures are therefore lower and therefore lead also to smaller deformations.
- the invention is the pressure on the outside Part of the inner case according to the operating conditions such as full or partial load. By suitable The pressure is then controlled on the inner housing occurring axial thrust adjustable.
- the suitable means preferably a seal.
- the axial thrust compensation of the inner housing is therefore not can only be influenced by the pressure, but also by the Pressure available effective area to form a Axial force.
- This acting surface becomes the first surface now divided into two areas by the mean.
- the active surface comprises at least one Part of the outer face of the inner case.
- the machine has the possibility of finding a suitable one Dimension of the outer part of the inner housing for Axial thrust compensation to make this thrust so small to keep as possible.
- the axial thrust is also a part of a turbine Variation of the areas, determined by means of the diameter one or two I-ring seals, also adjustable.
- the seal itself is thus pressurized and particularly burdened. Because of the seal it is on both Partial pressure acting between the inside and External housing attachable.
- Figure 1 shows an embodiment of an inventive Turbo machine 1, a high-pressure turbine 1 in pot design, which has an inner housing 2 and an outer housing 3.
- the fluid 4 flowing through the turbomachine 1 also joins the inlet pressure P1 and leaves the high-pressure turbine 1 again with the outlet pressure P2.
- the pressure difference between the inlet and outlet pressure leads to an axial thrust not only on the inner housing 2 but also on the shaft 5.
- the inner housing 2 has one on its outside Surface A1, which acts on the inlet pressure P1 becomes.
- a pressure on the surface A1 is preferably at least this large as the outlet pressure P2 of the fluid 4 from the turbomachine 1.
- the pressure on the area A1 can also as large as the inlet pressure of the fluid and / or a pressure be inside the inner housing 2.
- the Area A1 part of the end face of the inner housing 2.
- the Axial thrust arising on this surface A1 overlaps the of the surface A2 'created axial force on the inner housing 2, whereby axial thrust compensation takes place on this.
- the fixation 6 of the inner housing 2 relative to the outer housing 3 is lower surface pressures due to this axial thrust compensation subjected.
- This allows a variety of construction options to initiate an axial thrust in the outer housing 3, for. B. can in the previous state of Support rings used in technology are eliminated.
- the overall structure Such a turbomachine according to the invention can be thus simplify due to the improved axial thrust compensation.
- the axial pressure transmitting Area A1 of the outer part of the inner casing 2 by means arranged around the shaft 5 7 limited.
- This means 7 advantageously a seal, limits the attacking pressure P1 to the axial pressure transmitting one Area A1, so that by using means 7 a precisely defined axial thrust compensation can take place.
- the use of such a means 7 Possibility to add another area A3 to the outer part of the To apply another pressure P3 to the inner housing 2.
- the pressure P3 in connection with the area A3 then generates also a contribution to axial thrust compensation.
- the areas A1 and A3 together therefore form a for the purposes of the invention first surface of the outer part of the inner housing 2.
- the Areas A1 and A3 individually are the partial areas.
- the pressure P3 which is advantageous compared to the pressure P1 lower, serves as a barrier pressure. Pressure and flow losses over the or the seals as a means 7 can can be reduced by means of this advantageous pressure rating. This makes the seal, especially an I-ring seal not only pressurized, but also with the Can withstand pressure. By using several means 7 can For a better pressure rating also other, separate from each other Surfaces for axial thrust compensation are created, like this by the dotted line 7 with the area A3 ' and the pressure P3 'is indicated. Because of the building geometry the turbomachine 1 is advantageously the seal 7 between the inner part of the outer housing 3 and the outer Part of the inner housing 2 attached, in particular so that it direct contact with the inner housing 2 and the outer housing 3 Has.
- the invention provides that an axial thrust compensation not only on the inner housing 2 but also on the Wave 5 takes place.
- the turbomachine is designed so that an axial pressure transmitting surface A2 '' with the outlet pressure P2 is applied. So, because of the Pressure difference between the inlet pressure P1 and the outlet pressure P2 above the blades, axial thrust occurring at the Wave 5 are at least partially compensated.
- Figure 2 shows the arrangement in a schematic representation a high pressure part HD, a medium pressure part MD and of a low pressure part ND of a turbine on a shaft.
- This illustration shows that the forces from the pressure P1 on surface A1 and from print P3 on surface A3 act in the negative X direction. The force from the pressure P2 however, these forces have a positive effect on the area A2 '' X direction opposite.
- the invention is therefore not only one Part turbine, but rather on a strand of turbo machines connected in series for axial thrust compensation applicable.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Basic Packing Technique (AREA)
Abstract
Description
Die vorliegende Erfindung betrifft ein Verfahren und eine Vorrichtung bei einer Turbomaschine mit einem Außen- und einem Innengehäuse bzw. Leitschaufelträger zum Schubausgleich. Insbesondere liegt das Anwendungsgebiet der Erfindung bei Turbokraftmaschinen in Topfbauweise, wobei der Druck eines durch die Turbomaschine durchströmenden Fluides eine Axialkraft in Längsrichtung der Welle mindestens auf das Innengehäuse verursacht.The present invention relates to a method and a Device in a turbomachine with an outer and a Inner housing or guide vane carrier for thrust compensation. In particular, the field of application of the invention is included Turbomachines in pot design, the pressure of a axial fluid flowing through the turbomachine in the longitudinal direction of the shaft at least on the inner housing caused.
Es ist bekannt, daß bei Turbomaschinen mit einem hohen Innendruck das Gehäuse in ein Innen- und ein Außengehäuse aufgeteilt wird. In der DE 22 18 500 ist ein mehrschaliges Gehäuse einer Dampfturbine für hohe Dampfdrücke und Dampftemperaturen beschrieben. Bei der vorliegenden Konstruktion der Hochdruckturbine in Topfbauart tritt der Frischdampf mit hohem Druck in das Innegehäuse ein. Nach einer Expansion von ca. 20% des gesamten Gefälles der Teilturbine wird der Dampf durch Bohrungen in das Außengehäuse geführt und preßt so im Bereich des weiteren Expansionsverlaufes das Innengehäuse im Bereich der Teilfugen zusammen. Bei unterkritischen Dampfzuständen wird die Konstruktion mit Leitschaufelträger gewählt. Hierbei steht der volle Frischdampfdruck im Raum zwischen Innen- und Außengehäuse an und preßt so die beiden Trägerhälften zusammen. Im weiteren Verlauf der Beschreibung umfaßt der Begriff "Innengehäuse" auch immer die konstruktive Lösung mit Leitschaufelträger. Die an verschiedenen Flächen angreifenden Drücke sorgen nun in ihrer Überlagerung weiterhin für einen resultierenden Schub auf die Bauteile, der durch entsprechende Vorrichtungen am Innengehäuse und/oder Außengehäuse und/oder an der Welle aufgefangen werden muß. Dazu ist es weiterhin bekannt, daß der Zwischenraum zwischen dem Innenund dem Außengehäuse gegen die Austrittsseite des durch die Turbomaschine durchströmenden Fluides abgedichtet ist, so daß vom Innengehäuse der Differenzdruck zwischen Ein- und Austritt aufzunehmen ist, während das Außengehäuse abströmseitig dem Austrittsdruck und einströmseitig dem Druck zwischen Außen- und Innengehäuse gegenüber dem Atmosphärendruck standhalten muß. Die in den verschiedenen Räumen einer Turbomaschine anliegenden Drücke sorgen für hohe Axialkräfte, die über entsprechende Vorrichtungen, wie z. B. Bajonettringe, Gewinderinge, Uhde-Brettschneider-Verschlüsse oder Verschraubungen auf das Außengehäuse oder andere geeignete Vorrichtungen übertragen werden müssen. Diese Kräfte verursachen neben möglichen großen Verformungen auch hohe Flächenpressungen an entsprechenden Abstützungen.It is known that in turbomachinery with a high internal pressure the housing is divided into an inner and an outer housing becomes. DE 22 18 500 is a multi-shell housing a steam turbine for high steam pressures and temperatures described. In the present construction of the high pressure turbine In the pot design, live steam comes at high pressure into the inner case. After an expansion of about 20% of the The entire gradient of the turbine part is the steam through drilling led into the outer housing and so presses in the area further expansion course the inner housing in the area of the joints. With subcritical steam conditions the construction with guide vane carrier is chosen. in this connection the full live steam pressure is in the space between inside and Outer housing and thus presses the two support halves together. The term further includes the term "Inner housing" is always the constructive solution with a guide vane carrier. Those attacking different areas Pressures now continue to provide one in their overlay resulting thrust on the components by appropriate Devices on the inner housing and / or outer housing and / or must be caught on the shaft. It is for that further known that the space between the interior and the outer housing against the outlet side of the through the Turbomachine flowing fluid is sealed so that the differential pressure between the inlet and outlet from the inner housing is to be recorded, while the outer housing on the downstream side the outlet pressure and on the inflow side the pressure between external and withstand the inner casing against atmospheric pressure got to. The one in the different rooms of a turbo machine applied pressures ensure high axial forces via appropriate devices, such as. B. bayonet rings, Threaded rings, Uhde board cutter closures or screw connections on the outer casing or other suitable devices must be transferred. These forces cause alongside possible large deformations also high surface pressures appropriate supports.
Die DE 22 18 500 beispielsweise offenbart ein mehrschaliges Gehäuse einer Dampfturbine für hohe Dampfdrücke und Dampftemperaturen. Eine Innenschale wird mittels eines Stützringes gegen das Außengehäuse verspannt und somit axial fixiert. Die US 3,754,833 wiederum bzw. ihre Prioritätsschrift, die DE 20 54 465, beschreibt eine Einrichtung zur radial-zentrisch wärmebeweglichen Lagerung und Zentrierung von Wellendichtungsgehäusen an äußeren Gehäuseschalen von Turbomaschinen. Die dort dargestellte Turbine weist ein Topfgehäuse mit einer achsnormalen Teilfuge auf. Ein die Leitschaufeln tragendes Innengehäuse wird in dem Topfgehäuse an einer Lagerund Zentrierstelle eingesetzt. Diese Zentrierstelle wird durch einen Uhde-Brettschneider-Verschluß ausgebildet. Im Bereich der Wellendurchführungen durch das Topfgehäuse befinden sich Wellendichtungsgehäuse, auf denen Dichtungsdeckel aufgesetzt sind. Bypasskanäle im Innengehäuse dienen zum Axialschubausgleich.DE 22 18 500, for example, discloses a multi-shell Steam turbine housing for high steam pressures and temperatures. An inner shell is made using a support ring clamped against the outer housing and thus axially fixed. The US 3,754,833 in turn or its priority document, the DE 20 54 465 describes a device for radial-centric heat-moving storage and centering of shaft seal housings on the outer casing of turbomachinery. The turbine shown there has a pot housing an axis-normal parting line. A carrying the guide vanes Inner housing is in the pot housing on a Lagerund Centering point used. This centering point will formed by a Uhde board cutter closure. In the area the shaft bushings are through the pot housing shaft seal housing on which sealing cover is placed are. Bypass channels in the inner housing are used for axial thrust compensation.
Der Bauaufwand bei Turbomaschinen zum Auffangen der Axialkräfte ist, wie oben ausgeführt, insgesamt sehr hoch. Da der Wirkungsgrad einer Turbomaschine durch Strömungsverluste nun stark beeinflußt wird, müssen die Schubkräfte weiterhin so aufgefangen werden, daß bei entsprechenden Wärmedehnungen der Welle und des Innen- und Außengehäuses sich nur möglichst kleine Radialspalte an den Schaufelenden ergeben.The construction effort for turbo machines to absorb the axial forces is, as stated above, very high overall. Since the Efficiency of a turbo machine through flow losses now is strongly influenced, the thrust must continue so be caught that with appropriate thermal expansion of the Shaft and the inner and outer housing only possible result in small radial gaps at the blade ends.
Aufgabe der vorliegenden Erfindung ist daher die Schaffung eines Verfahrens zum Schubausgleich bei einer Turbomaschine sowie eine entsprechende Ausgestaltung derselben. Insbesondere soll die Erfindung auftretende Axialkräfte in Längsrichtung der Welle ausgleichen.The object of the present invention is therefore to create of a method for thrust compensation in a turbomachine and a corresponding design of the same. In particular the invention is intended to produce axial forces in the longitudinal direction balance the wave.
Diese Aufgabe wird durch ein Verfahren mit den Merkmalen des Anspruches 1 und durch eine Turbomaschine mit den Merkmalen des Anspruches 6 gelöst. Vorteilhafte Ausgestaltungen und Weiterbildungen sind in den jeweils abhängigen Ansprüchen beschrieben.This task is accomplished by a process with the characteristics of Claim 1 and by a turbomachine with the features of claim 6 solved. Advantageous configurations and Further developments are described in the respective dependent claims.
Die Erfindung sieht vor,daß mindestens eine erste Fläche des Äußeren eines Teiles des Innengehäuses zu einem Axialschubausgleich in zwei Teilflächen zum Axialschubausgleich unterteilt wird, die jeweils mit unterschiedlichem Druck beaufschlagt werden, wobei eine Abgrenzung zwischen beiden Drücken durch mindestens ein Mittel, insbesondere eine Dichtung, verursacht wird. Bevorzugt wird das Äußere eines Teiles des Innengehäuses mit einem Druck zum Axialschubausgleich beaufschlagt, der mindestens so groß wie der Austrittsdruck des Fluides ist, und vorzugsweise ungefähr so groß wie der Eintrittsdruck.The invention provides that at least a first surface of the Exterior of part of the inner housing for axial thrust compensation divided into two sections for axial thrust compensation is applied, each with different pressure a distinction between the two pressures caused by at least one means, in particular a seal becomes. The exterior of a part of the inner housing is preferred pressurized to compensate for axial thrust, which is at least as large as the outlet pressure of the Is fluid, and preferably about as large as the inlet pressure.
In einer vorteilhaften Ausführung der Erfindung wirkt der Druck zum Axialschubausgleich der Axialkraft des Austrittsdruckes am Innengehäuse entgegen. Aufgrund der Überlagerung beider Drücke ergibt sich ein verringerter resultierender Druck, der damit auch nur einen geringeren Schub verursacht. Dieser Axialschubausgleich ist insbesondere am Innengehäuse der Turbomaschine durchführbar. Dadurch wird erreicht, daß der bisherige hohe Bauaufwand zur Fixierung des Innengehäuses verringert werden kann. Die an den Fixierelementen auftretenden Flächenpressungen sind daher geringer und führen deswegen auch zu geringeren Verformungen. In einer vorteilhaften Weiterentwicklung der Erfindung wird der Druck auf den äußeren Teil des Innengehäuses entsprechend den Betriebsbedingungen wie beispielsweise Voll- oder Teillast eingestellt. Durch geeignete Steuerung des Druckes ist dann der am Innengehäuse auftretende Axialschub einstellbar.In an advantageous embodiment of the invention, the Pressure for axial thrust compensation of the axial force of the outlet pressure towards the inner housing. Because of the overlay both pressures result in a reduced resulting Pressure that also causes less thrust. This axial thrust compensation is particularly on the inner housing the turbomachine feasible. This ensures that the previous high construction costs for fixing the inner housing can be reduced. The occurring on the fixing elements Surface pressures are therefore lower and therefore lead also to smaller deformations. In an advantageous further development the invention is the pressure on the outside Part of the inner case according to the operating conditions such as full or partial load. By suitable The pressure is then controlled on the inner housing occurring axial thrust adjustable.
Neben der Beaufschlagung eines äußeren Teiles des Innengehäuses mit einem Druck zum Axialschubausgleich wird weiterhin eine Begrenzung der Abmessung dieses äußeren Teiles durch das geeignete Mittel, vorzugsweise eine Dichtung, vorgenommen. Der Axialschubausgleich des Innengehäuses ist dadurch nicht nur über den Druck beeinflußbar, sondern auch über die dem Druck zur Verfügung stehende wirkende Fläche zur Bildung einer Axialkraft. Diese wirkende Fläche als erste Fläche wird nun durch das Mittel in die zwei Teilflächen unterteilt. Vorzugsweise umfaßt die wirkende Fläche dabei mindestens einen Teil der äußeren Stirnfläche des Innengehäuses. Je nach Auslegung der Maschine besteht damit die Möglichkeit, eine geeignete Abmessung des äußeren Teiles des Innengehäuses zum Axialschubausgleich vorzunehmen, um diesen Schub so gering wie möglich zu halten. Entsprechend den jeweiligen Dampfparametern einer Teilturbine ist der Axialschub ebenfalls durch Variation der Flächen, festgelegt mittels des Durchmessers eines oder zweier I-Ringdichtungen, ebenfalls einstellbar. Die Dichtung selbst wird somit mit Druck beaufschlagt und insbesondere belastet. Aufgrund der Dichtung ist der auf beiden Teilflächen jeweils wirkende Druck auch zwischen Innenund Außengehäuse aufbringbar.In addition to the application of an outer part of the inner housing with a pressure for axial thrust compensation will continue a limitation of the dimension of this outer part by the suitable means, preferably a seal. The axial thrust compensation of the inner housing is therefore not can only be influenced by the pressure, but also by the Pressure available effective area to form a Axial force. This acting surface becomes the first surface now divided into two areas by the mean. Preferably the active surface comprises at least one Part of the outer face of the inner case. Depending on the design the machine has the possibility of finding a suitable one Dimension of the outer part of the inner housing for Axial thrust compensation to make this thrust so small to keep as possible. According to the respective steam parameters the axial thrust is also a part of a turbine Variation of the areas, determined by means of the diameter one or two I-ring seals, also adjustable. The seal itself is thus pressurized and particularly burdened. Because of the seal it is on both Partial pressure acting between the inside and External housing attachable.
Weitere Vorteile und Eigenschaften der Erfindung werden anhand der folgenden Zeichnungen erläutert. Vorteilhafte Ausgestaltungen der Erfindung sind durch Kombinationen der offenbarten Merkmale möglich. Es zeigen:
- Figur 1
- eine erfindungsgemäße stationäre Hochdruckturbine in Topfbauweise und
Figur 2- eine schematische Anordnung eines Turbinenstranges.
- Figure 1
- a stationary high-pressure turbine according to the invention in pot design and
- Figure 2
- a schematic arrangement of a turbine train.
Figur 1 zeigt als Ausführungsbeispiel einer erfindungsgemäßen
Turbomaschine 1 eine Hochdruckturbine 1 in Topfbauweise, welche
ein Innengehäuse 2 und ein Außengehäuse 3 aufweist. Das
durch die Turbomaschine 1 durchströmende Fluid 4 tritt mit
dem Eintrittsdruck P1 ein und verläßt die Hochdruckturbine 1
wieder mit dem Austrittsdruck P2. Die Druckdifferenz zwischen
dem Ein- und dem Austrittsdruck führt zu einem Axialschub
nicht nur an dem Innengehäuse 2 sondern auch an der Welle 5.
Je nach Art der Leit- und Laufschaufeln findet dort ein unterschiedlicher
Druckabbau des hindurchströmenden Fluides 4
statt, der sich auf die Welle 5 und das Innengehäuse 2 auswirkt.
Das Innengehäuse 2 weist an seiner Außenseite eine
Fläche A1 auf, die mit dem Eintrittsdruck P1 beaufschlagt
wird. Ein Druck auf die Fläche A1 ist bevorzugt mindestens so
groß wie der Austrittsdruck P2 des Fluides 4 aus der Turbomaschine
1. Insbesondere kann der Druck auf der Fläche A1 auch
so groß wie der Eintrittsdruck des Fluides und/oder ein Druck
im Inneren des Innengehäuses 2 sein. Vorzugsweise umfaßt die
Fläche A1 einen Teil der Stirnfläche des Innengehäuses 2. Der
auf dieser Fläche A1 entstehende Axialschub überlagert die an
der Fläche A2' entstandene Axialkraft am Innengehäuse 2, wodurch
ein Axialschubausgleich an diesem stattfindet. Die Fixierung
6 des Innengehäuses 2 gegenüber dem Außengehäuse 3
ist aufgrund dieses Axialschubausgleiches geringeren Flächenpressungen
unterworfen. Dieses erlaubt vielfältige Konstruktionsmöglichkeiten
zur Einleitung einer Axialschubkraft in
das Außengehäuse 3, z. B. können die im früheren Stand der
Technik verwendeten Stützringe entfallen. Der Gesamtaufbau
einer derartigen erfindungsgemäßen Turbomaschine läßt sich
somit aufgrund des verbesserten Axialschubausgleiches vereinfachen.Figure 1 shows an embodiment of an inventive
Turbo machine 1, a high-pressure turbine 1 in pot design, which
has an
In der in der Figur 1 dargestellten Erfindung wird die axialdruckübertragende
Fläche A1 des äußeren Teiles des Innengehäuses
2 durch ein, um die Welle 5 herum angeordnetes Mittel
7 begrenzt. Dieses Mittel 7, vorteilhafterweise eine Dichtung,
begrenzt den angreifenden Druck P1 auf die axialdruckübertragende
Fläche A1, so daß durch Verwendung des Mittels 7
ein genau definierter Axialschubausgleich stattfinden kann.
Weiterhin bietet der Einsatz eines derartigen Mittels 7 die
Möglichkeit, eine weitere Fläche A3 an dem äußeren Teil des
Innengehäuses 2 mit einem weiteren Druck P3 zu beaufschlagen.
Der Druck P3 in Verbindung mit der Fläche A3 erzeugt dann
ebenfalls einen Beitrag zum Axialschubausgleich. Die Flächen
A1 und A3 zusammen bilden daher im Sinne der Erfindung eine
erste Fläche des äußeren Teiles des Innengehäuses 2 aus. Die
Flächen A1 und A3 einzeln sind dann die Teilflächen.In the invention shown in Figure 1, the axial pressure transmitting
Area A1 of the outer part of the
Der Druck P3, der gegenüber dem Druck P1 vorteilhafterweise
niedriger ist, dient als Sperrdruck. Druck- und Strömungsverluste
über der oder den Dichtungen als Mittel 7 können
mittels dieser vorteilhaften Druckstufung verringert werden.
Dadurch ist die Dichtung, insbesondere eine I-Ringdichtung
nicht nur mit Druck beaufschlagbar, sondern auch mit dem
Druck belastbar. Durch Verwendung mehrerer Mittel 7 können
für eine günstige Druckstufung auch weitere, voneinander getrennte
Flächen zum Axialschubausgleich geschaffen werden,
wie dieses durch das gestrichelte Mittel 7 mit der Fläche A3'
und dem Druck P3' angedeutet ist. Aufgrund der Baugeometrie
der Turbomaschine 1 wird die Dichtung 7 vorteilhafterweise
zwischen dem inneren Teil des Außengehäuses 3 und dem äußeren
Teil des Innengehäuses 2 angebracht, insbesondere so, daß sie
direkten Kontakt zu dem Innengehäuse 2 und dem Außengehäuse 3
hat. Als Dichtung 7 bietet sich eine I-Ringdichtung an, deren
Durchmesser D von der, die gewünschte Axialkraft übertragenden
Fläche A1 bzw. A3 abhängt. Eine vorteilhafte Ausgestaltung
der Erfindung sieht vor, daß ein Axialschubausgleich
nicht nur an dem Innengehäuse 2 sondern ebenfalls an der
Welle 5 stattfindet. Dazu ist die Turbomaschine so gestaltet,
daß eine axialdruckübertragende Fläche A2'' mit dem Austrittsdruck
P2 beaufschlagt wird. So kann der, aufgrund der
Druckdifferenz des Eintrittsdruckes P1 und des Austrittsdrukkes
P2 über den Schaufeln, auftretende Axialschub an der
Welle 5 zumindest teilweise ausgeglichen werden.The pressure P3, which is advantageous compared to the pressure P1
lower, serves as a barrier pressure. Pressure and flow losses
over the or the seals as a means 7 can
can be reduced by means of this advantageous pressure rating.
This makes the seal, especially an I-ring seal
not only pressurized, but also with the
Can withstand pressure. By using several means 7 can
For a better pressure rating also other, separate from each other
Surfaces for axial thrust compensation are created,
like this by the dotted line 7 with the area A3 '
and the pressure P3 'is indicated. Because of the building geometry
the turbomachine 1 is advantageously the seal 7
between the inner part of the
Figur 2 zeigt in einer schematischen Darstellung die Anordnung eines Hochdruckteils HD, eines Mitteldruckteiles MD und eines Niederdruckteiles ND einer Turbine auf einer Welle. Diese Darstellung verdeutlicht, daß die Kräfte aus dem Druck P1 auf die Fläche A1 und aus dem Druck P3 auf die Fläche A3 in negativer X-Richtung wirken. Die Kraft aus dem Druck P2 auf die Fläche A2'' wirkt dagegen diesen Kräften in positiver X-Richtung entgegen. Die Erfindung ist somit nicht nur an einer Teilturbine, sondern vielmehr auch an einem Strang von hintereinander geschalteten Turbomaschinen zum Axialschubausgleich anwendbar.Figure 2 shows the arrangement in a schematic representation a high pressure part HD, a medium pressure part MD and of a low pressure part ND of a turbine on a shaft. This illustration shows that the forces from the pressure P1 on surface A1 and from print P3 on surface A3 act in the negative X direction. The force from the pressure P2 however, these forces have a positive effect on the area A2 '' X direction opposite. The invention is therefore not only one Part turbine, but rather on a strand of turbo machines connected in series for axial thrust compensation applicable.
Claims (12)
- Method for axial thrust compensation on a turbomachine (1) with an outer casing (3) and an inner casing (2) or blade carrier, in particular a turbo engine of pot-type construction, the pressure of a fluid (4) flowing through the turbomachine causing an axial force in the longitudinal direction of the shaft (5), at least on the inner casing (2), and an exterior of part of the inner casing (2) being subjected to a pressure for axial thrust compensation, characterized in that at least one first area (A1+A3) of the exterior of the part of the inner casing (2) being divided for axial thrust compensation into two partial areas (A1, A3) for axial thrust compensation, each of which is subjected to a different pressure (P1, P3), separation between the two pressures (P1, P3) being brought about by at least one means (7), in particular a seal.
- Method according to Claim 1, characterized in that the means (7) itself, in particular an I-ring seal, is subjected to pressure (P1, P3), in particular subjected to pressure loading.
- Method according to Claim 1 or 2, characterized in that the respective pressure (P1, P3) acting on the two partial areas (A1, A3) are applied between the inner casing (2) and the outer casing (3).
- Method according to one of the preceding claims, characterized in that the pressure (P1, P3) on the partial area (A1, A3) of the exterior of the part of the inner casing (2) is set in accordance with a respective operating condition of the turbomachine.
- Method according to one of the preceding claims, characterized in that the pressure (P1, P3) is applied to an end face of the inner casing (2).
- Turbomachine (1) with an outer casing (3) and an inner casing (2) or blade carrier, in particular a turbo engine of pot-type construction, the outlet pressure (P2) of a fluid (4) flowing through the turbomachine (1) causing an axial force in the longitudinal direction of the shaft (5), at least on the inner casing (2), characterized in that a means (7) divides two partial areas (A1, A3) of a first area (A1+A3), which transmit axial pressure, on an exterior of part of the inner casing (2), each of which areas contributes to axial thrust compensation (5).
- Turbomachine according to Claim 6, characterized in that the two partial areas (A1, A3) which transmit axial pressure can each be subjected to a different pressure (P1, P3).
- Turbomachine according to Claim 7, characterized in that the means (7) can be subjected to pressure (P1, P3), in particular two different pressures simultaneously.
- Turbomachine according to Claim 7 or 8, characterized in that the means (7) is arranged between the inner casing (2) and the outer casing (3), in particular in such a way that it has direct contact with the inner casing (2) and the outer casing (3).
- Turbomachine according to one of Claims 6 to 9, characterized in that the means (7) is a seal, preferably an I-ring seal, which is, in particular, arranged around the shaft (5).
- Turbomachine according to one Claims 6 to 10, characterized in that the pressure-transmitting partial area (A1, A3) for thrust compensation at least partially comprises an end face of the inner casing.
- Turbomachine according to one of Claims 6 to 11, characterized in that the pressure-transmitting partial area (A1, A3) for thrust compensation can be subjected to the inlet pressure (P1) or to a pressure from the interior of the inner casing (2).
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE19614335 | 1996-04-11 | ||
| DE19614335 | 1996-04-11 | ||
| PCT/DE1997/000674 WO1997038209A1 (en) | 1996-04-11 | 1997-04-02 | Thrust-compensating process and device for turbomachines |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| EP0891471A1 EP0891471A1 (en) | 1999-01-20 |
| EP0891471B1 true EP0891471B1 (en) | 2002-06-26 |
Family
ID=7791006
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP97918065A Expired - Lifetime EP0891471B1 (en) | 1996-04-11 | 1997-04-02 | Thrust-compensating process and device for turbomachines |
Country Status (11)
| Country | Link |
|---|---|
| US (1) | US6213710B1 (en) |
| EP (1) | EP0891471B1 (en) |
| JP (1) | JP2000508040A (en) |
| KR (1) | KR20000005303A (en) |
| CN (1) | CN1081724C (en) |
| AT (1) | ATE219816T1 (en) |
| CZ (1) | CZ326498A3 (en) |
| DE (1) | DE59707599D1 (en) |
| PL (1) | PL183594B1 (en) |
| RU (1) | RU2175721C2 (en) |
| WO (1) | WO1997038209A1 (en) |
Families Citing this family (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE59807765D1 (en) * | 1997-11-03 | 2003-05-08 | Siemens Ag | TURBINE HOUSING AND METHOD FOR THE PRODUCTION THEREOF |
| JP3986873B2 (en) * | 2001-05-08 | 2007-10-03 | 花王株式会社 | Liquid detergent composition |
| ES2267655T3 (en) | 2001-11-22 | 2007-03-16 | Siemens Aktiengesellschaft | METHOD OF MANUFACTURE OF STEAM TURBINES. |
| JP2006016976A (en) * | 2004-06-30 | 2006-01-19 | Toshiba Corp | Turbine nozzle support device and steam turbine |
| US8256575B2 (en) * | 2007-08-22 | 2012-09-04 | General Electric Company | Methods and systems for sealing rotating machines |
| CN101952557A (en) * | 2008-03-31 | 2011-01-19 | 三菱重工业株式会社 | Rotary mechanism |
| DE102008022966B4 (en) * | 2008-05-09 | 2014-12-24 | Siemens Aktiengesellschaft | rotary engine |
| EP2192266A1 (en) * | 2008-11-26 | 2010-06-02 | Siemens Aktiengesellschaft | Rotor device for a steam turbine and steam turbine |
| JP2010174795A (en) * | 2009-01-30 | 2010-08-12 | Mitsubishi Heavy Ind Ltd | Turbine |
| CH701914A1 (en) * | 2009-09-30 | 2011-03-31 | Alstom Technology Ltd | Steam turbine i.e. high pressure steam turbine, has piston seal arranged between rotor and stator, and release groove arranged at rotor, arranged in region of thrust balance piston and running in circumferential direction of rotor |
| EP2333253A1 (en) * | 2009-12-08 | 2011-06-15 | Siemens Aktiengesellschaft | Internal casing for a turbo-machine |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE281253C (en) * | ||||
| FR1094273A (en) * | 1953-08-31 | 1955-05-16 | Siemens Ag | Double jacket turbine operating at high exhaust pressure |
| DE1152703B (en) * | 1959-12-14 | 1963-08-14 | Licentia Gmbh | Multi-stage impulse turbine |
| JPS5227282B2 (en) | 1970-11-05 | 1977-07-19 | ||
| DE2218500B2 (en) * | 1972-04-17 | 1974-01-31 | Kraftwerk Union AG, 4330 Mülheim | MULTI-SHELLED HOUSING OF A STEAM TURBINE FOR HIGH STEAM PRESSURE AND STEAM TEMPERATURES |
| JPS59213907A (en) * | 1983-05-19 | 1984-12-03 | Fuji Electric Co Ltd | Barrel-type turbine |
-
1997
- 1997-04-02 RU RU98120399/06A patent/RU2175721C2/en not_active IP Right Cessation
- 1997-04-02 AT AT97918065T patent/ATE219816T1/en not_active IP Right Cessation
- 1997-04-02 KR KR1019980708015A patent/KR20000005303A/en active IP Right Grant
- 1997-04-02 PL PL97329236A patent/PL183594B1/en not_active IP Right Cessation
- 1997-04-02 CZ CZ983264A patent/CZ326498A3/en unknown
- 1997-04-02 EP EP97918065A patent/EP0891471B1/en not_active Expired - Lifetime
- 1997-04-02 WO PCT/DE1997/000674 patent/WO1997038209A1/en active IP Right Grant
- 1997-04-02 DE DE59707599T patent/DE59707599D1/en not_active Expired - Lifetime
- 1997-04-02 CN CN97193662A patent/CN1081724C/en not_active Expired - Lifetime
- 1997-04-02 JP JP9535741A patent/JP2000508040A/en active Pending
-
1998
- 1998-10-13 US US09/170,183 patent/US6213710B1/en not_active Expired - Lifetime
Also Published As
| Publication number | Publication date |
|---|---|
| JP2000508040A (en) | 2000-06-27 |
| DE59707599D1 (en) | 2002-08-01 |
| CN1081724C (en) | 2002-03-27 |
| EP0891471A1 (en) | 1999-01-20 |
| KR20000005303A (en) | 2000-01-25 |
| PL329236A1 (en) | 1999-03-15 |
| US6213710B1 (en) | 2001-04-10 |
| RU2175721C2 (en) | 2001-11-10 |
| PL183594B1 (en) | 2002-06-28 |
| CN1215449A (en) | 1999-04-28 |
| CZ326498A3 (en) | 1999-02-17 |
| ATE219816T1 (en) | 2002-07-15 |
| WO1997038209A1 (en) | 1997-10-16 |
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