EP2532898A1 - Axial turbo compressor - Google Patents
Axial turbo compressor Download PDFInfo
- Publication number
- EP2532898A1 EP2532898A1 EP11169109A EP11169109A EP2532898A1 EP 2532898 A1 EP2532898 A1 EP 2532898A1 EP 11169109 A EP11169109 A EP 11169109A EP 11169109 A EP11169109 A EP 11169109A EP 2532898 A1 EP2532898 A1 EP 2532898A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- channel
- wall
- compressor
- removal
- 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
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
- F04D27/02—Surge control
- F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
- F04D27/0215—Arrangements therefor, e.g. bleed or by-pass valves
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
- F04D27/02—Surge control
- F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
- F04D27/023—Details or means for fluid extraction
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
- F04D29/526—Details of the casing section radially opposing blade tips
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
- F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
- F04D29/682—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps by fluid extraction
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
- F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
- F04D29/685—Inducing localised fluid recirculation in the stator-rotor interface
Definitions
- the invention relates to a Axialturbover emphasizer with an about a rotational axis concentrically arranged annular compressor passage, which is bounded radially outwardly by a channel wall and rotatably mounted in the ringable to a ring rotatable blades about the rotation axis, wherein the free-ending tips of the blades each with gap formation of Channel wall opposite and the channel wall in the axial portion of the tips at least partially a wall structuring (also known as casing treatment) and wherein a removal opening of a removal channel for tapping of a medium flowing in the compressor channel medium is provided in the channel wall.
- a wall structuring also known as casing treatment
- the above-described arrangement is for example from the GB 2 158 879 A known.
- the casing treatment is provided on the casing-side channel wall above an upstream blade row and the bleed-off point is located at a downstream row of blades.
- a valve is provided in the removal channel in order to tap different quantities of compressor air as a function of the operating state. Both measures allow a degree of regulation of the operation of the compressor for high pressure conditions, without causing unwanted compressor phenomena such as pumps or detachment phenomena (surge).
- the disadvantage is that the aforementioned embodiment has proven to be inadequate for a partial load operation of a gas turbine.
- the object of the invention is therefore to provide an axial turbocompressor, in which the operating range is further improved by a more efficient avoidance of undesired compressor phenomena.
- Another object of the invention is to provide a gas turbine with a Axialturbover participatr invention, which avoids inadmissible emissions especially at part load operation.
- the invention is provided to settle the removal opening in the wall structuring. It is thus not only the simultaneous application of a casing treatment and the tapping of compressor air within a Axialturboverêtrs proposed, but the combination also takes place locally, namely in the range of a single blade row of Axialturbover confusers. Damming the compressed air and thus an aerodynamically unfavorable high pressure ratio in the subsequent compressor stages can thus be avoided, which largely avoids the emergence of unwanted compressor phenomena. Due to the combination according to the invention, the surge limit of the relevant compressor stage can be adjusted in a particularly simple and operating state-dependent manner.
- the adjustable in size or shape Casing Treatment not only the setting of the wall structuring, but also serves as an actuator for connecting or disconnecting the removal of compressor air. This also allows a particularly space-saving design.
- the aforementioned embodiment can be implemented in a particularly simple design if the wall structuring can be changed in size and / or shape by means of a movable insert and the removal opening is located in a side wall of the insert receiving the insert.
- the insert may be formed as a plug, which can be moved along the recess. Depending on the position of the plug, either the recess is completely closed (for the first operating state), the recess is only partially closed with the removal openings still closed (for the second operating state) or the recess and the removal opening are open (for the third operating state). In this respect, alone by the displacement of the plug along its receiving recess between the three aforementioned operating conditions are switched back and forth in a simple and reliable manner.
- the removal channel may be connected on the flow output side with a blow-off air system and / or cooling air system.
- FIG. 1 shows a stationary gas turbine 10 in a longitudinal partial section.
- the gas turbine 10 has inside a rotatably mounted about an axis of rotation 12 rotor 14, which is also referred to as a turbine runner.
- rotor 14 successively follow an intake housing 16, a Axialturbover Noticer 18, a toroidal annular combustion chamber 20 with a plurality of rotationally symmetrical mutually arranged burners 22, a turbine unit 24 and an exhaust housing 26.
- the gas turbine can also be equipped with silo or with tube combustion chambers.
- the Axialturbover Noticer 18 includes a ring-shaped compressor duct 25 with successively cascaded compressor stages of blade and vane rings.
- the rotor blades 14 arranged on the blades 27 are with their free-ending blade tips 29 an outer channel wall 42 of the compressor passage 25 opposite.
- the compressor passage 25 opens via a compressor outlet diffuser 36 in a plenum 38.
- the annular combustion chamber 20 is provided with its combustion chamber 28, which communicates with an annular hot gas duct 30 of the turbine unit 24.
- four turbine stages 32 connected in series are arranged in the turbine unit 24.
- a generator or a working machine (each not shown) is coupled.
- the axial turbocharger 18 draws in ambient air 34 through the intake housing 16 as a medium to be compressed and compresses it.
- the compressed air is guided through the compressor outlet diffuser 36 into the plenum 38, from where it flows into the burner 22.
- Fuel also passes into the combustion space 28 via the burners 22.
- the fuel is burned to a hot gas M with the addition of the compressed air.
- the hot gas M then flows into the hot gas duct 30, where it relaxes to perform work on the turbine blades of the turbine unit 24.
- the energy released during this process is absorbed by the rotor 14 and on the one hand used to drive the Axialturboverêtrs 18 and on the other hand to drive a working machine or electric generator.
- At least one wall structuring is provided in the channel wall 42.
- This wall structuring is in FIG. 1 for the sake of clarity not shown.
- This wall structuring is furthermore known as a so-called "casing treatment” and is designed, for example, as grooves running continuously in the circumferential direction or distributed over the circumference and extending in the axial direction.
- the wall structuring is usually provided in an axial section of the compressor duct 25, in which the free-ending tips of rotor blades 27 lie opposite one another with gap formation of the duct wall 42.
- FIGS. 2 and 3 show now in detail in cross section a section through the channel wall 42 of the compressor duct 25 in the region of a wall structure 44.
- the wall structuring 44 comprises according to this first embodiment a plurality of radially extending through the channel wall 42 recesses 46. In each recess 46 sits a radially displaceable, in Cross-section T-shaped insert 48. In the recess 46 open two channels laterally. These channels are designed as removal channels 50. Its opening 52 is located in the wall structure 44, ie in the side wall 54 of the recess 46. When pushed inward insert 48, the recess 46 and at the same time the removal openings 52 are completely closed (not shown).
- the recess 46 is partially opened to activate the aerodynamically effective Wand Wegberichtbericht 44 by the insert 48 from its recess 46, the relevant closure position was moved to the outside.
- the first opening 52 of the removal channel 50 is exposed, so that at the same time the compressor duct 25 via the recess 46 compressor air removed, ie can be tapped.
- the in FIG. 3 shown position of the insert 48 are both removal openings 52 of the removal channels 50 exposed.
- the wall structure 44 is variable in size and / or shape and thereby the removal opening 52 at least partially exposed.
- FIG. 4 shows a second embodiment of the device according to the invention in a perspective view.
- the second embodiment in the direction of the compressor channel 25 facing surface of the channel wall 42 are now provided in the circumferential direction endlessly extending grooves 60 along which the tips of the blades, not shown, rotate.
- a side wall 61 of the grooves 60 open several, uniformly distributed along the circumference removal channels 62, only a few of which are shown schematically.
- the valve system for opening and / or closing the removal of compressor air is nevertheless not formed by movable inserts, but designed as a downstream system.
- the extraction channels 62 can of course also be distributed unevenly.
- the wall structure 44 is formed as extending in the axial direction, evenly distributed over the circumference of the channel wall 42 grooves 64 which are located in a circumferentially rotatable insert 45, which arranged in a channel wall 42, corresponding to the insert 45 recess 47 is settled.
- the removal openings 52 of the removal channels 50 are arranged between the grooves 64 webs 49 of the insert 45.
- FIGS. 6 and 7 show the FIGS. 6 and 7 in each case partial perspective representation.
- FIG. 6 shows a channel wall 42 having a groove 66 which is endless in the circumferential direction, in which a radially displaceable insert 68 for opening and closing the wall structuring 44 and the removal opening 52 arranged in the groove side wall 70 is located.
- the removal opening 52 is closed by the insert 68.
- the removal opening 52 is open.
- the present invention proposes an axial turbocompressor 18 or a gas turbine 10 with an annular compressor channel 25 arranged concentrically around a rotation axis 12, which is bounded radially on the outside by a channel wall 42 and in the ringable rotor blades 29 which can be combined to form a ring around the axis of rotation 12 are arranged rotatably mounted.
- the free-ending tips 29 of the blades 29 are each with gap formation of the channel wall 42 opposite, wherein in the channel wall 42 itself in the axial portion of the tips 29 at least partially a wall structuring 44 is provided.
- a removal opening 52 of a removal channel 50 for tapping and removal of air flowing in the compressor passage 25 is provided, which is located according to the invention in the wall structure 44.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
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- Sustainable Development (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
Die Erfindung betrifft einen Axialturboverdichter mit einem um eine Rotationsachse konzentrisch angeordneten ringförmigen Verdichterkanal, welcher radial außen von einer Kanalwand begrenzt ist und in dem zu einem Kranz zusammenfassbare Laufschaufeln um die Rotationsachse drehbar gelagert angeordnet sind, wobei die frei endenden Spitzen der Laufschaufeln jeweils unter Spaltbildung der Kanalwand gegenüberliegen und die Kanalwand im axialen Abschnitt der Spitzen zumindest teilweise eine Wandstrukturierung (auch als Casing Treatment bekannt) aufweist und wobei eine Entnahmeöffnung eines Entnahmekanals zum Abzapfen von einem im Verdichterkanal strömenden Medium in der Kanalwand vorgesehen ist.The invention relates to a Axialturboverdichter with an about a rotational axis concentrically arranged annular compressor passage, which is bounded radially outwardly by a channel wall and rotatably mounted in the ringable to a ring rotatable blades about the rotation axis, wherein the free-ending tips of the blades each with gap formation of Channel wall opposite and the channel wall in the axial portion of the tips at least partially a wall structuring (also known as casing treatment) and wherein a removal opening of a removal channel for tapping of a medium flowing in the compressor channel medium is provided in the channel wall.
Die voranbeschriebene Anordnung ist beispielsweise aus der
Aufgabe der Erfindung ist daher die Bereitstellung eines Axialturboverdichters, bei dem der Betriebsbereich weiter verbessert wird durch ein effizienteres Vermeiden von ungewünschten Verdichter-Phänomenen.The object of the invention is therefore to provide an axial turbocompressor, in which the operating range is further improved by a more efficient avoidance of undesired compressor phenomena.
Weitere Aufgabe der Erfindung ist die Bereitstellung einer Gasturbine mit einem erfindungsgemäßen Axialturboverdichter, welche insbesondere bei Teillastbetrieb unzulässig hohe Emissionen vermeidet.Another object of the invention is to provide a gas turbine with a Axialturboverdichter invention, which avoids inadmissible emissions especially at part load operation.
Die der Erfindung zugrundeliegende Aufgabe wird mit einem Axialturboverdichter gemäß den Merkmalen des Anspruchs 1 gelöst. Vorteilhafte Weiterbildungen und Ausgestaltungen sind in den jeweils abhängigen Ansprüchen angegeben.The problem underlying the invention is achieved with an axial turbocompressor according to the features of claim 1. Advantageous developments and refinements are specified in the respective dependent claims.
Erfindungsgemäß ist vorgesehen, die Entnahmeöffnung in der Wandstrukturierung anzusiedeln. Es wird somit nicht nur die gleichzeitige Anwendung eines Casing Treatments und dem Abzapfen von Verdichterluft innerhalb eines Axialturboverdichters vorgeschlagen, sondern die Kombination erfolgt auch örtlich, nämlich im Bereich einer einzigen Laufschaufelreihe des Axialturboverdichters. Ein Aufstauen der verdichteten Luft und ein damit aerodynamisch ungünstig hohes Druckverhältnis in den nachfolgenden Verdichterstufen kann somit vermieden werden, was das Entstehen der ungewünschten Verdichterphänomene weitgehend vermeidet. Durch die erfindungsgemäße Kombination kann die Pumpgrenze der betreffenden Verdichterstufe besonders einfach und betriebzustandabhängig angepasst werden. Dies ermöglicht bei der Verwendung des Axialturboverdichters in einer stationären Gasturbine einen besonders tiefen Teillastbetrieb, ohne das Emissionsgrenzen dabei überschritten werden. Bei der Verwendung in einer Gasturbine kann nämlich durch das Abzapfen von Verdichterluft eine für die Teillast entsprechende geringe Luftmenge in die Brennkammer geführt werden, wodurch die CO-Emissionen minimiert werden. Es wird also dem Verdichter gezielt Luft entzogen, so dass keine ungewollten strömungsmechanischen Effekte auftreten, wie sie bei konventionellen Abblaseklappen vorkommen können. Zudem unterstützt das im Casing Treatment vorgesehene Abgreifen von Luft auch die Wirkung der Wandstrukturierung selber, so dass das Casing Treatment raumsparender ausgebildet sein kann als ein Casing Treatment ohne darin angesiedelte Entnahmeöffnungen.According to the invention, it is provided to settle the removal opening in the wall structuring. It is thus not only the simultaneous application of a casing treatment and the tapping of compressor air within a Axialturboverdichters proposed, but the combination also takes place locally, namely in the range of a single blade row of Axialturboverdichters. Damming the compressed air and thus an aerodynamically unfavorable high pressure ratio in the subsequent compressor stages can thus be avoided, which largely avoids the emergence of unwanted compressor phenomena. Due to the combination according to the invention, the surge limit of the relevant compressor stage can be adjusted in a particularly simple and operating state-dependent manner. This allows when using the Axialturboverdichters in a stationary gas turbine, a particularly deep part-load operation, without the emission limits are exceeded. Namely, when used in a gas turbine, by tapping compressor air, a small amount of air corresponding to the partial load can be fed into the combustion chamber, thereby minimizing CO emissions. It is the compressor targeted air withdrawn, so that no unwanted fluid mechanical effects occur, as they may occur in conventional Abblaseklappen. In addition, the tapping of air provided in the casing treatment also supports the effect of the wall structuring itself, so that the casing treatment can be made more space-saving Can be used as a Casing Treatment without removal openings.
Gemäß einer ersten vorteilhaften Weiterbildung ist die Wandstrukturierung in ihrer Größe und/oder Form veränderbar und dadurch die Entnahmeöffnung zumindest teilweise freilegbar. Diese Ausgestaltung ermöglicht in einfacher Konstruktion insgesamt drei Betriebszustände des Axialturboverdichters:
- 1. der Axialturboverdichter wird ohne Casing Treatment und ohne Entnahme von Verdichterluft betrieben, vorzugsweise bei Volllast,
- 2. der Axialturboverdichter wird nur mit Casing Treatment betrieben, aber weiterhin ohne das Abzapfen von Verdichterluft, vorzugsweise bei hoher Teillast, und
- 3. der Axialturboverdichter wird mit Casing Treatment betrieben bei gleichzeitigem Abzapfen von Verdichterluft, vorzugsweise bei niedriger Teillast.
- 1. the axial turbocompressor is operated without casing treatment and without the removal of compressor air, preferably at full load,
- 2. The Axialturboverdichter is operated only with Casing Treatment, but still without the tapping of compressor air, preferably at high part load, and
- 3. The Axialturboverdichter is operated with casing treatment with simultaneous tapping of compressor air, preferably at low partial load.
Demzufolge dient das in seiner Größe oder Form einstellbare Casing Treatment nicht allein der Einstellung der Wandstrukturierung, sondern gleichzeitig auch als Stellorgan zum Zu- oder Abschalten der Entnahme von Verdichterluft. Auch dies ermöglicht eine besonders raumsparende Konstruktion.Accordingly, the adjustable in size or shape Casing Treatment not only the setting of the wall structuring, but also serves as an actuator for connecting or disconnecting the removal of compressor air. This also allows a particularly space-saving design.
Die vorgenannte Ausgestaltung lässt sich besonders einfach konstruktiv umsetzen, wenn die Wandstrukturierung mittels eines beweglichen Einsatzes in ihrer Größe und/oder Form veränderbar ist und die Entnahmeöffnung in einer Seitenwand der den Einsatz aufnehmenden Ausnehmung angesiedelt ist. Der Einsatz kann als Stopfen ausgebildet sein, welcher entlang der Ausnehmung verschoben werden kann. Je nach Position des Stopfens ist entweder die Ausnehmung vollständig verschlossen (für den ersten Betriebszustand), die Ausnehmung nur teilweise verschlossen mit weiterhin verschlossenen Entnahmeöffnungen (für den zweiten Betriebszustand) oder die Ausnehmung sowie die Entnahmeöffnung sind geöffnet (für den dritten Betriebszustand). Insofern kann allein durch die Verschiebung des Stopfens entlang seiner ihn aufnehmenden Ausnehmung zwischen den drei vorgenannten Betriebszuständen in einfacher und zuverlässiger Weise hin und her geschaltet werden.The aforementioned embodiment can be implemented in a particularly simple design if the wall structuring can be changed in size and / or shape by means of a movable insert and the removal opening is located in a side wall of the insert receiving the insert. The insert may be formed as a plug, which can be moved along the recess. Depending on the position of the plug, either the recess is completely closed (for the first operating state), the recess is only partially closed with the removal openings still closed (for the second operating state) or the recess and the removal opening are open (for the third operating state). In this respect, alone by the displacement of the plug along its receiving recess between the three aforementioned operating conditions are switched back and forth in a simple and reliable manner.
Zweckmäßigerweise kann der Entnahmekanal strömungsausgangsseitig mit einem Abblaseluftsystem und/oder Kühlluftsystem verbunden sein.Appropriately, the removal channel may be connected on the flow output side with a blow-off air system and / or cooling air system.
Ebenso zweckmäßig ist es, mehrere Entnahmeöffnungen je Laufschaufelkranz anzuordnen. In diesem Fall lässt sich über den Umfang des Axialturboverdichters gesehen das im Verdichterkanal strömende Medium - zumeist Luft - gleichmäßig diesem entnehmen. Besonders vorteilhaft weist eine Gasturbine einen erfindungsgemäßen Axialturboverdichter der voran beschriebenen Bauweise auf, wodurch sich die Gasturbine besonders emissionsarm bei niedriger Teillast betreiben lässt.It is equally expedient to arrange a plurality of removal openings per blade ring. In this case can be seen over the circumference of the Axialturboverdichters seen the medium flowing in the compressor passage - usually air - uniformly remove this. Particularly advantageously, a gas turbine on an axial turbocompressor according to the invention of the construction described above, whereby the gas turbine can be operated with low emissions particularly low emissions at low partial load.
Weitere Vorteile, Merkmale und Eigenschaften der Erfindung werden anhand von bevorzugten Ausführungsbeispielen in der Zeichnung näher erläutert. Zweckmäßige Ausgestaltungen ergeben sich durch vorteilhafte Kombinationen von Merkmalen der dargestellten erfindungsgemäßen Vorrichtungen. Es zeigen:
- Figur 1
- eine stationäre Gasturbine mit einem Axialturboverdichter in einem Längsteilschnitt,
- Figur 2, 3
- jeweils einen Ausschnitt durch den Querschnitt des Gehäuses des Axialturboverdichters mit einer ersten Ausgestaltung eines Casing Treatments,
- Figur 4
- in perspektivischer Ansicht einen Ausschnitt des Gehäuses des Axialturboverdichters mit einem Casing Treatment gemäß einer zweiten Ausgestaltung,
- Figur 5
- eine dritte Ausgestaltung der erfindungsgemäßen Vorrichtung in perspektivischer Darstellung und
- Figur 6, 7
- eine vierte Ausgestaltung der erfindungsgemäßen Kombination von Casing Treatment und Entnahmeöffnung.
- FIG. 1
- a stationary gas turbine with a Axialturboverdichter in a longitudinal partial section,
- FIG. 2, 3
- each a section through the cross section of the housing of the Axialturboverdichters with a first embodiment of a casing treatment,
- FIG. 4
- 3 is a perspective view of a section of the housing of the axial turbo-compressor with a casing treatment according to a second embodiment,
- FIG. 5
- a third embodiment of the device according to the invention in a perspective view and
- FIG. 6, 7
- a fourth embodiment of the combination of casing treatment and removal opening according to the invention.
Der Axialturboverdichter 18 umfasst einen ringförmig ausgebildeten Verdichterkanal 25 mit darin kaskadisch aufeinanderfolgenden Verdichterstufen aus Laufschaufel- und Leitschaufelkränzen. Die am Rotor 14 angeordneten Laufschaufeln 27 liegen mit ihren frei endenden Schaufelblattspitzen 29 einer äußeren Kanalwand 42 des Verdichterkanals 25 gegenüber. Der Verdichterkanal 25 mündet über einen Verdichterausgangsdiffusor 36 in einem Plenum 38. Darin ist die Ringbrennkammer 20 mit ihrem Verbrennungsraum 28 vorgesehen, der mit einem ringförmigen Heißgaskanal 30 der Turbineneinheit 24 kommuniziert. Gemäß dem gezeigten Ausführungsbeispiels sind in der Turbineneinheit 24 vier hintereinander geschaltete Turbinenstufen 32 angeordnet. Am Rotor 14 ist ein Generator oder eine Arbeitsmaschine (jeweils nicht dargestellt) angekoppelt.The
Im Betrieb der Gasturbine 10 saugt der Axialturboverdichter 18 durch das Ansauggehäuse 16 als zu verdichtendes Medium Umgebungsluft 34 an und verdichtet diese. Die verdichtete Luft wird durch den Verdichterausgangsdiffusor 36 in das Plenum 38 geführt, von wo aus es in die Brenner 22 einströmt. Über die Brenner 22 gelangt auch Brennstoff in den Verbrennungsraum 28. Dort wird der Brennstoff unter Zugabe der verdichteten Luft zu einem Heißgas M verbrannt. Das Heißgas M strömt anschließend in den Heißgaskanal 30, wo es sich arbeitsleistend an den Turbinenschaufeln der Turbineneinheit 24 entspannt. Die währenddessen freigesetzte Energie wird vom Rotor 14 aufgenommen und einerseits zum Antrieb des Axialturboverdichters 18 und andererseits zum Antrieb einer Arbeitsmaschine oder elektrischen Generators genutzt.During operation of the
Beim Betrieb der Gasturbine 10 und somit beim Betrieb des Axialturboverdichters 18 können jedoch Zustände und aerodynamische Phänomene auftreten, die den Betrieb teilweise begrenzen. Um das Auftreten dieser Zustände und Phänomene zu vermeiden, ist in der Kanalwand 42 zumindest eine Wandstrukturierung vorgesehen. Diese Wandstrukturierung ist in
Die
In einer gemäß
Nach einer dritten Ausgestaltung, welche in
Eine vierte Ausgestaltung eines einstellbaren Casing Treatments mit darin angeordneten Entnahmeöffnungen 52 zeigen die
Insgesamt wird mit der vorliegenden Erfindung ein Axialturboverdichter 18 bzw. eine Gasturbine 10 vorgeschlagen, mit einem um eine Rotationsachse 12 konzentrisch angeordneten ringförmigen Verdichterkanal 25, welcher radial außen von einer Kanalwand 42 begrenzt ist und in dem zu einem Kranz zusammenfassbare Laufschaufeln 29 um die Rotationsachse 12 drehbar gelagert angeordnet sind. Dabei liegen die frei endenden Spitzen 29 der Laufschaufeln 29 jeweils unter Spaltbildung der Kanalwand 42 gegenüber, wobei in der Kanalwand 42 selber im axialen Abschnitt der Spitzen 29 zumindest teilweise eine Wandstrukturierung 44 vorgesehen ist. Um das Betriebsverhalten des Axialturboverdichters 18 weiter zu verbessern, ist eine Entnahmeöffnung 52 eines Entnahmekanals 50 zum Abzapfen und Abführen von im Verdichterkanal 25 strömender Luft vorgesehen, die erfindungsgemäß in der Wandstrukturierung 44 angesiedelt ist.Overall, the present invention proposes an
Claims (6)
mit einem um eine Rotationsachse (12) konzentrisch angeordneten ringförmigen Verdichterkanal (25), welcher radial außen von einer Kanalwand (42) begrenzt ist und in dem zu einem Kranz zusammenfassbare Laufschaufeln (27) um die Rotationsachse (12) drehbar gelagert angeordnet sind, wobei die frei endenden Spitzen (29) der Laufschaufeln (27) jeweils unter Spaltbildung der Kanalwand (42) gegenüber liegen und die Kanalwand (42) im axialen Abschnitt der Spitzen (29) zumindest teilweise eine Wandstrukturierung (44) aufweist und
wobei eine Entnahmeöffnung (52) eines Entnahmekanals (50) zum Abzapfen von im Verdichterkanal (42) strömenden Medium in der Kanalwand (42) vorgesehen ist,
dadurch gekennzeichnet, dass
die Entnahmeöffnung (52) in der Wandstrukturierung (44) angesiedelt ist.Axial Turbo Compressor (18),
with an annular compressor channel (25) arranged concentrically around a rotation axis (12), which is bounded radially on the outside by a channel wall (42) and in which blades (27) which can be combined to form a ring are arranged so as to be rotatable about the axis of rotation (12) the freely ending tips (29) of the rotor blades (27) lie opposite one another with gap formation of the channel wall (42) and the channel wall (42) at least partially has a wall structuring (44) in the axial section of the tips (29) and
wherein a removal opening (52) of a removal channel (50) for tapping media flowing in the compressor channel (42) is provided in the channel wall (42),
characterized in that
the removal opening (52) is located in the wall structure (44).
bei dem die Wandstrukturierung (44) in ihrer Größe und/oder Form veränderbar und dadurch die Entnahmeöffnung (52) zumindest teilweise freilegbar ist.Axial turbo compressor (18) according to claim 1,
in which the wall structuring (44) is variable in size and / or shape and thereby the removal opening (52) is at least partially exposed.
bei dem die Wandstrukturierung (44) mittels eines beweglichen Einsatzes (45, 48, 68) in ihrer Größe und/oder Form veränderbar ist und die Entnahmeöffnung (52) in einer Seitenwand (54, 70) der den Einsatz (45, 48, 68) aufnehmenden Ausnehmung (46, 47, 70) angesiedelt ist.Axial turbo compressor (18) according to claim 2,
in which the wall structuring (44) is variable in size and / or shape by means of a movable insert (45, 48, 68) and the removal opening (52) in a side wall (54, 70) of the insert (45, 48, 68 ) receiving recess (46, 47, 70) is settled.
bei dem der Entnahmekanal (50) strömungsausgangseitig mit einem Abblaseluftsystem und/oder Kühlluftsystem verbunden ist.An axial turbocompressor (18) according to claim 1, 2 or 3,
in which the removal channel (50) is connected on the flow output side to a blow-off air system and / or cooling air system.
bei dem mehrere Entnahmeöffnungen (52) je Laufschaufelkranz vorgesehen sind.Axial turbo compressor (18) according to one of the preceding claims,
in which a plurality of removal openings (52) are provided per blade ring.
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP11169109A EP2532898A1 (en) | 2011-06-08 | 2011-06-08 | Axial turbo compressor |
US13/488,540 US20120315131A1 (en) | 2011-06-08 | 2012-06-05 | Axial turbocompressor |
JP2012129623A JP2012255440A (en) | 2011-06-08 | 2012-06-07 | Axial turbo compressor |
CN2012101871763A CN102817865A (en) | 2011-06-08 | 2012-06-07 | Axial turbo compressor |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP11169109A EP2532898A1 (en) | 2011-06-08 | 2011-06-08 | Axial turbo compressor |
Publications (1)
Publication Number | Publication Date |
---|---|
EP2532898A1 true EP2532898A1 (en) | 2012-12-12 |
Family
ID=44872640
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP11169109A Withdrawn EP2532898A1 (en) | 2011-06-08 | 2011-06-08 | Axial turbo compressor |
Country Status (4)
Country | Link |
---|---|
US (1) | US20120315131A1 (en) |
EP (1) | EP2532898A1 (en) |
JP (1) | JP2012255440A (en) |
CN (1) | CN102817865A (en) |
Families Citing this family (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP3023592A1 (en) * | 2014-11-20 | 2016-05-25 | Siemens Aktiengesellschaft | Diffuser of a thermal energy machine and thermal energy machine |
CN108119406B (en) * | 2018-01-11 | 2020-11-27 | 南京航空航天大学 | Axial compressor circumferential large-interval small-through-hole casing |
US11092030B2 (en) | 2019-04-18 | 2021-08-17 | Raytheon Technologies Corporation | Adaptive case for a gas turbine engine |
US12018621B1 (en) | 2023-08-16 | 2024-06-25 | Rolls-Royce North American Technologies Inc. | Adjustable depth tip treatment with rotatable ring with pockets for a fan of a gas turbine engine |
US11965528B1 (en) | 2023-08-16 | 2024-04-23 | Rolls-Royce North American Technologies Inc. | Adjustable air flow plenum with circumferential movable closure for a fan of a gas turbine engine |
US11970985B1 (en) | 2023-08-16 | 2024-04-30 | Rolls-Royce North American Technologies Inc. | Adjustable air flow plenum with pivoting vanes for a fan of a gas turbine engine |
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EP1413771A1 (en) * | 2002-10-22 | 2004-04-28 | Snecma Moteurs | Casing, compressor, turbine and gas turbine engine having such casing |
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GB2172053B (en) * | 1985-03-05 | 1988-10-05 | Rolls Royce | Gas turbine engine valve control system |
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DE69204861T2 (en) * | 1991-01-30 | 1996-05-23 | United Technologies Corp | Fan housing with recirculation channels. |
RU2034175C1 (en) * | 1993-03-11 | 1995-04-30 | Центральный институт авиационного моторостроения им.П.И.Баранова | Turbo-compressor |
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GB2356588B (en) * | 1999-11-25 | 2003-11-12 | Rolls Royce Plc | Processing tip treatment bars in a gas turbine engine |
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JP3872966B2 (en) * | 2001-06-29 | 2007-01-24 | 株式会社日立プラントテクノロジー | Axial fluid machine |
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-
2011
- 2011-06-08 EP EP11169109A patent/EP2532898A1/en not_active Withdrawn
-
2012
- 2012-06-05 US US13/488,540 patent/US20120315131A1/en not_active Abandoned
- 2012-06-07 CN CN2012101871763A patent/CN102817865A/en active Pending
- 2012-06-07 JP JP2012129623A patent/JP2012255440A/en active Pending
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US3365172A (en) * | 1966-11-02 | 1968-01-23 | Gen Electric | Air cooled shroud seal |
JPS59168296A (en) * | 1983-03-16 | 1984-09-21 | Hitachi Ltd | Surging preventive device of multistage axial-flow compressor |
GB2158879A (en) | 1984-05-19 | 1985-11-20 | Rolls Royce | Preventing surge in an axial flow compressor |
EP1013937A2 (en) * | 1998-12-23 | 2000-06-28 | United Technologies Corporation | Rotor tip bleed in gas turbine engines |
EP1413771A1 (en) * | 2002-10-22 | 2004-04-28 | Snecma Moteurs | Casing, compressor, turbine and gas turbine engine having such casing |
Also Published As
Publication number | Publication date |
---|---|
CN102817865A (en) | 2012-12-12 |
JP2012255440A (en) | 2012-12-27 |
US20120315131A1 (en) | 2012-12-13 |
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