EP2292934A2 - Axial compressor with a flow impulse generator - Google Patents
Axial compressor with a flow impulse generator Download PDFInfo
- Publication number
- EP2292934A2 EP2292934A2 EP10007218A EP10007218A EP2292934A2 EP 2292934 A2 EP2292934 A2 EP 2292934A2 EP 10007218 A EP10007218 A EP 10007218A EP 10007218 A EP10007218 A EP 10007218A EP 2292934 A2 EP2292934 A2 EP 2292934A2
- Authority
- EP
- European Patent Office
- Prior art keywords
- rotor
- flow
- wall
- axial compressor
- compressor according
- 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
- 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
Definitions
- the invention relates to an axial compressor which comprises within a compressor housing at least one rotor made of rotor blades connected to a drive shaft and a stator held on the housing inner wall and a flow pulse generator associated with the rotor gap present between the blade tips and the housing inner wall for stabilizing the rotor gap flow.
- compressed fluid is taken from the rear stages of the compressor and re-blown in the blade tip region of the front rotors in order to increase the flow pulse at the gap and thus actively influence the rotor gap flow and to stabilize the gap vortex.
- this mode of operation is disadvantageous in that the fluid in the compressor is more heated by the reintroduction of hot fluid from the rear of the compressor and thus the compressor efficiency drops.
- the compressor stability can also be influenced passively by formations formed in the compressor housing over the blade tips.
- a flow circulation caused by the injection conveys a certain amount of energy into the front region of the rotor tip, so that the momentum of the rotor inflow is increased and thus the rotor gap flow and finally the compressor operation are stabilized.
- this housing design is difficult to manufacture and can also be damaged when entering the rotor.
- the invention is therefore the object of developing an axial compressor of the type mentioned with respect to the flow pulse generator so that at a reduced manufacturing cost and without wear, a high local flow pulse for stabilizing the rotor gap flow and the compressor operation is achieved.
- the basic idea of the invention consists in the arrangement of a flow pulse generator on the inner wall of the compressor housing, consisting of upstream of the rotor in the flow direction extending and tapering pulse channels for accelerating the near-wall flow.
- the shape and dimension of the impulse channels directed towards the rotor gap is defined by circumferentially spaced-apart, gap-free fixed to the housing inner wall Separators determined.
- the thus formed flow pulse generator is easy to manufacture and ensures a favorable flow of the rotor gap and effective stabilization of the rotor gap flow.
- the operating range of the compressor is extended without adversely affecting the compressor efficiency.
- the pulse channels are each bounded by opposing side walls of the separating elements.
- the side walls have a fluidically favorable - straight and / or curved - course.
- the upstream inflow geometry of the separating elements is also designed to be favorable in terms of flow.
- the pulse channels have a rectangular cross-section.
- the inlet cross sections of the pulse channels are about twice as large as their outlet cross sections.
- the separating elements are covered to the housing interior through a thin top wall and so separated from the main flow to the rotors.
- the top wall may extend axially parallel in the flow direction or follow the course of the wall of the compressor housing.
- the pulse channels and separating elements have a height extending in the radial direction, which is at most twice as large as the width of the rotor gap.
- the length of the pulse channels and dividers in the axial direction is between 10 and 100% of the length of the tendon at the rotor blade tip.
- the pulse channels and separators terminate at a distance from the leading edge of the rotor blades whose size is between 10 and 100% of the length of the tendon at the rotor blade tip.
- two or more pulse channels are provided for each rotor blade passage located between two rotor blades.
- Fig. 1 shows an axial compressor used in a gas turbine engine having a plurality of assembled to a rotor drum and connected to a drive shaft 1 rotors 2 and arranged between the rotor blades 3, held on the compressor housing 4 stators 5.
- the front rotor 2 is assigned upstream and at a distance from the existing between the blade tips and the compressor housing 4 rotor gap 6 a fixed to the inner wall of the compressor housing 4 flow pulse generator 7.
- the flow pulse generator 7 is in a - compared to the main flow 8 -wandnahen Low flow rate region 9 is arranged at a distance A between the trailing edge 14 of the flow pulse generator 7 and the leading edge of the rotor blades 3.
- the distance A and the length L of the flow pulse generator 7 amount to about 10 to 100% of the chord length measured at the blade tip S of the rotor blades 3.
- the flow pulse generator 7 connects directly to the compressor housing 4, so that there is no air gap between them.
- the height H of the flow pulse generator corresponds at most twice the value of the width B of the rotor gap 6.
- the flow pulse generator 7 consists of a plurality of circumferentially spaced, tapered in the flow direction of the pulse channels 7a, which are provided by attached to the compressor housing 4, formed in accordance with the shape of the pulse channels 7a separating elements 7b.
- two flow pulse generators 7, ie two pulse channels 7a are provided for each rotor blade passage 10.
- three or four pulse channels 7a it is also possible for three or four pulse channels 7a to be assigned to a blade passage 10.
- the cross-sectional area of the pulse channels 7a is preferably rectangular and the inlet cross section should be about twice as large as the outlet cross section.
- the separating elements 7b and thus the pulse channels 7a are preferably shaped such that their course preferably follows the course of the compressor housing 4 follows.
- the front edge 13 of the separating elements 7b is designed to be favorable in terms of flow.
- the flow pulse generators 7 described above are easy to produce. There is no fear of wear or damage when the rotor blades 3 run in, and the compressor efficiency is not adversely affected by an increased fluid temperature.
- the flow pulse can be adapted specifically to the respective flow conditions, so that the operating range of the axial compressor is widened and the surge limit is increased.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
Die Erfindung betrifft einen Axialverdichter, der innerhalb eines Verdichtergehäuses mindestens einen Rotor aus mit einer Antriebswelle verbundenen Rotorschaufeln und einen an der Gehäuseinnenwand gehaltenen Stator sowie einen dem zwischen den Schaufelspitzen und der Gehäuseinnenwand vorhandenen Rotorspalt zugeordneten Strömungsimpulserzeuger zur Stabilisierung der Rotorspaltströmung umfasst.The invention relates to an axial compressor which comprises within a compressor housing at least one rotor made of rotor blades connected to a drive shaft and a stator held on the housing inner wall and a flow pulse generator associated with the rotor gap present between the blade tips and the housing inner wall for stabilizing the rotor gap flow.
Bei Axialverdichtern kann es bei hoher Belastung, zum Beispiel bei hoher Beschleunigung von mit einer Fluggasturbine angetriebenen Flugzeugen, zu Strömungsinstabilitäten im Bereich des zwischen den Spitzen der Rotorschaufeln und dem Verdichtergehäuse vorhandenen Rotorspaltes kommen, die den Betriebsbereich des Axialverdichters begrenzen. Durch einen am Rotorspalt erzeugten Strömungsimpuls kann der bei hoher Verdichterbelastung kritische Spaltwirbel stabilisiert und damit der Betriebsbereich des Verdichters vergrößert bzw. dessen Betriebsstabilität verbessert werden.In axial compressors under high load, for example high acceleration of aircraft driven by an aircraft gas turbine, flow instabilities can occur in the area of the rotor gap existing between the tips of the rotor blades and the compressor housing, which limit the operating range of the axial compressor. By means of a flow pulse generated at the rotor gap, the gap vortex which is critical at high compressor load can be stabilized and thus the operating range of the compressor can be increased or its operating stability can be improved.
Gemäß einer bekannten Maßnahme zur aktiven Beeinflussung der Verdichterstabilität wird verdichtetes Fluid aus den hinteren Stufen des Verdichters entnommen und im Schaufelspitzenbereich der vorderen Rotoren wieder eingeblasen, um den Strömungsimpuls am Spalt zu erhöhen und somit die Rotorspaltströmung aktiv zu beeinflussen und den Spaltwirbel zu stabilisieren. Diese Betriebsweise ist jedoch insofern nachteilig, als das Fluid im Verdichter durch die Wiedereinführung von heißem Fluid aus dem hinteren Teil der Verdichters stärker erhitzt wird und somit der Verdichterwirkungsgrad sinkt.According to a known measure for actively influencing the compressor stability, compressed fluid is taken from the rear stages of the compressor and re-blown in the blade tip region of the front rotors in order to increase the flow pulse at the gap and thus actively influence the rotor gap flow and to stabilize the gap vortex. However, this mode of operation is disadvantageous in that the fluid in the compressor is more heated by the reintroduction of hot fluid from the rear of the compressor and thus the compressor efficiency drops.
Die Verdichterstabilität kann auch durch im Verdichtergehäuse über den Schaufelspitzen ausgebildete Einformungen passiv beeinflusst werden. Eine durch die Einformung bewirkte Strömungszirkulation transportiert eine bestimmte Energiemenge in den vorderen Bereich der Rotorspitze, so dass der Impuls der Rotoranströmung erhöht und damit die Rotorspaltströmung und letztlich der Verdichterbetrieb stabilisiert werden. Abgesehen davon, dass auch bei diesem Verfahren eine bestimmte Fluidmenge rezirkuliert und eine höhere Erwärmung zur Folge hat, ist diese Gehäuseausbildung schwierig zu fertigen und kann zudem beim Einlaufen des Rotors beschädigt werden.The compressor stability can also be influenced passively by formations formed in the compressor housing over the blade tips. A flow circulation caused by the injection conveys a certain amount of energy into the front region of the rotor tip, so that the momentum of the rotor inflow is increased and thus the rotor gap flow and finally the compressor operation are stabilized. Apart from the fact that also in this method, a certain amount of fluid recirculates and has a higher heating result, this housing design is difficult to manufacture and can also be damaged when entering the rotor.
Der Erfindung liegt daher die Aufgabe zugrunde, einen Axialverdichter der eingangs erwähnten Art hinsichtlich des Strömungsimpulserzeugers so weiterzubilden, dass bei vermindertem Fertigungsaufwand und ohne Verschleiß ein hoher lokaler Strömungsimpuls zur Stabilisierung der Rotorspaltdurchströmung und des Verdichterbetriebs erzielt wird.The invention is therefore the object of developing an axial compressor of the type mentioned with respect to the flow pulse generator so that at a reduced manufacturing cost and without wear, a high local flow pulse for stabilizing the rotor gap flow and the compressor operation is achieved.
Erfindungsgemäß wird die Aufgabe mit einem gemäß den Merkmalen des Patentanspruchs 1 ausgebildeten Axialverdichter gelöst. Vorteilhafte Weiterbildungen und zweckmäßige Ausgestaltungen der Erfindung sind Gegenstand der Unteransprüche.According to the invention the object is achieved with a trained according to the features of claim 1 axial compressor. Advantageous developments and expedient embodiments of the invention are the subject of the dependent claims.
Der Grundgedanke der Erfindung besteht in der Anordnung eines Strömungsimpulserzeugers an der Innenwand des Verdichtergehäuses, bestehend aus sich stromauf vom Rotor in Strömungsrichtung erstreckenden und verjüngenden Impulskanälen zur Beschleunigung der wandnahen Strömung. Die Form und Abmessung der auf den Rotorspalt gerichteten Impulskanäle ist durch in Umfangsrichtung im Abstand aufeinander folgende, an der Gehäuseinnenwand spaltfrei befestigte Trennelemente bestimmt. Der so ausgebildete Strömungsimpulserzeuger ist einfach zu fertigen und gewährleistet eine günstige Anströmung des Rotorspaltes und eine effektive Stabilisierung der Rotorspaltdurchströmung. Der Betriebsbereich des Verdichters wird - ohne negative Beeinflussung des Verdichterwirkungsgrades - erweitert.The basic idea of the invention consists in the arrangement of a flow pulse generator on the inner wall of the compressor housing, consisting of upstream of the rotor in the flow direction extending and tapering pulse channels for accelerating the near-wall flow. The shape and dimension of the impulse channels directed towards the rotor gap is defined by circumferentially spaced-apart, gap-free fixed to the housing inner wall Separators determined. The thus formed flow pulse generator is easy to manufacture and ensures a favorable flow of the rotor gap and effective stabilization of the rotor gap flow. The operating range of the compressor is extended without adversely affecting the compressor efficiency.
In weiterer Ausbildung der Erfindung sind die Impulskanäle jeweils durch einander gegenüberliegende Seitenwände der Trennelemente begrenzt. Die Seitenwände haben einen strömungstechnisch günstigen - geraden und/oder gekrümmten - Verlauf. Die stromauf liegende Einströmgeometrie der Trennelemente ist ebenfalls strömungstechnisch günstig ausgebildet ist.In a further embodiment of the invention, the pulse channels are each bounded by opposing side walls of the separating elements. The side walls have a fluidically favorable - straight and / or curved - course. The upstream inflow geometry of the separating elements is also designed to be favorable in terms of flow.
In Ausgestaltung der Erfindung weisen die Impulskanäle einen rechteckigen Querschnitt auf. Die Eintrittsquerschnitte der Impulskanäle sind etwa doppelt so groß wie deren Austrittsquerschnitte.In an embodiment of the invention, the pulse channels have a rectangular cross-section. The inlet cross sections of the pulse channels are about twice as large as their outlet cross sections.
In vorteilhafter Weiterbildung der Erfindung sind die Trennelemente zum Gehäuseinneren hin durch eine dünne Deckwand abgedeckt und so von der Hauptströmung zu den Rotoren getrennt. Die Deckwand kann sich in Strömungsrichtung achsparallel erstrecken oder dem Verlauf der Wand des Verdichtergehäuses folgen.In an advantageous embodiment of the invention, the separating elements are covered to the housing interior through a thin top wall and so separated from the main flow to the rotors. The top wall may extend axially parallel in the flow direction or follow the course of the wall of the compressor housing.
In weiterer Ausgestaltung der Erfindung haben die Impulskanäle und Trennelemente eine sich in radialer Richtung erstreckende Höhe, die maximal zweimal so groß wie die Weite des Rotorspaltes ist. Die Länge der Impulskanäle und Trennelemente in axialer Richtung liegt zwischen 10 und 100% der Länge der Sehne an der Rotorschaufelspitze. Die Impulskanäle und Trennelemente enden in einem Abstand von der Vorderkante der Rotorschaufeln, dessen Größe zwischen 10 und 100% der Länge der Sehne an der Rotorschaufelspitze beträgt.In a further embodiment of the invention, the pulse channels and separating elements have a height extending in the radial direction, which is at most twice as large as the width of the rotor gap. The length of the pulse channels and dividers in the axial direction is between 10 and 100% of the length of the tendon at the rotor blade tip. The pulse channels and separators terminate at a distance from the leading edge of the rotor blades whose size is between 10 and 100% of the length of the tendon at the rotor blade tip.
In weiterer Ausbildung der Erfindung sind für jede zwischen zwei Rotorschaufeln liegende Rotorschaufelpassage zwei oder mehr Impulskanäle vorgesehen.In a further embodiment of the invention, two or more pulse channels are provided for each rotor blade passage located between two rotor blades.
Ein Ausführungsbeispiel der Erfindung wird anhand der Zeichnung näher erläutert. Es zeigen:
- Fig. 1
- einen Längsschnitt eines Axialverdichters für eine Fluggasturbine;
- Fig. 2
- eine schematische Darstellung eines am Verdich- tergehäuse vor dem Rotor angeordneten Strömungs- impulserzeugers,
- Fig. 3
- eine Draufsicht des Strömungsimpulserzeugers nach
Fig. 2 ; und - Fig. 4
- verschiedene Ausführungsvarianten von Strömungs- erzeugern in der Draufsicht.
- Fig. 1
- a longitudinal section of an axial compressor for an aircraft gas turbine;
- Fig. 2
- FIG. 2 is a schematic representation of a flow impulse generator arranged on the compressor housing in front of the rotor, FIG.
- Fig. 3
- a plan view of the flow pulse generator after
Fig. 2 ; and - Fig. 4
- various embodiments of flow generators in plan view.
Wie
Der Strömungsimpulserzeuger 7 besteht aus einer Mehrzahl von in Umfangsrichtung im Abstand ausgebildeten, sich in Strömungsrichtung verjüngenden Impulskanälen 7a, die durch am Verdichtergehäuse 4 angebrachte, entsprechend der Form der Impulskanäle 7a geformte Trennelemente 7b geschaffen werden. In der in
Die zuvor beschriebenen Strömungsimpulserzeuger 7 sind einfach herstellbar. Ein Verschleiß oder eine Beschädigung beim Einlaufen der Rotorschaufeln 3 ist nicht zu befürchten und der Verdichterwirkungsgrad wird nicht durch eine erhöhte Fluidtemperatur negativ beeinflusst. Zudem kann der Strömungsimpuls durch Form, Größe, Verlauf, Anzahl und Anordnung der Impulskanäle 7a gezielt an die jeweiligen Strömungsbedingungen angepasst werden, so dass der Betriebsbereich des Axialverdichters erweitert und die Pumpgrenze erhöht wird.The
- 11
- Antriebswelledrive shaft
- 22
- Rotorenrotors
- 33
- Rotorschaufelnrotor blades
- 44
- Verdichtergehäusecompressor housing
- 55
- Statorenstators
- 66
- Rotorspaltrotor gap
- 77
- StrömungsimpulserzeugerFlow pulse generator
- 7a7a
- Impulskanälepulse channels
- 7b7b
- Trennelementeseparators
- 88th
- Hauptströmungmainstream
- 99
- Bereich geringer Strömung^Low flow area ^
- 1010
- RotorschaufelpassageRotor blade passage
- 1111
- Seitenwand v. 7bSidewall v. 7b
- 1212
- Deckwand v. 7bCover wall v. 7b
- 1313
- Vorderkante v. 7bLeading edge v. 7b
- 1414
- Hinterkante v. 7bTrailing edge v. 7b
- AA
- Abstand zw. 3 und 7Distance between 3 and 7
- BB
- Weite von 6Width of 6
- HH
- Höhe von 7Height of 7
- LL
- Länge von 7Length of 7
- SS
- Sehnenlänge von 3Chord length of 3
Claims (10)
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102009033754A DE102009033754A1 (en) | 2009-07-17 | 2009-07-17 | Axial compressor with a flow pulse generator |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2292934A2 true EP2292934A2 (en) | 2011-03-09 |
EP2292934A3 EP2292934A3 (en) | 2014-03-19 |
Family
ID=42676814
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP10007218.0A Withdrawn EP2292934A3 (en) | 2009-07-17 | 2010-07-13 | Axial compressor with a flow impulse generator |
Country Status (3)
Country | Link |
---|---|
US (1) | US8591179B2 (en) |
EP (1) | EP2292934A3 (en) |
DE (1) | DE102009033754A1 (en) |
Families Citing this family (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2976634B1 (en) | 2011-06-14 | 2013-07-05 | Snecma | TURBOMACHINE ELEMENT |
CN102306074B (en) * | 2011-09-19 | 2013-05-29 | 深圳莱宝高科技股份有限公司 | Capacitive touch panel and manufacturing method thereof |
CN102279686B (en) * | 2011-09-19 | 2013-06-19 | 深圳莱宝高科技股份有限公司 | Capacitive touch panel and method for manufacturing same |
GB2556771A (en) * | 2015-08-13 | 2018-06-06 | Contech Eng Solutions Llc | Pipe joint for plastic pipes |
CN111611743B (en) * | 2020-05-15 | 2023-03-28 | 上海上电电力工程有限公司 | Axial-flow compressor characteristic line self-adaption method |
Family Cites Families (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3879939A (en) * | 1973-04-18 | 1975-04-29 | United Aircraft Corp | Combustion inlet diffuser employing boundary layer flow straightening vanes |
JPS5669404A (en) * | 1979-11-07 | 1981-06-10 | Hitachi Ltd | Turbine blade train |
DE3022206C2 (en) | 1980-06-13 | 1983-08-11 | M.A.N. Maschinenfabrik Augsburg-Nürnberg AG, 4200 Oberhausen | Axial compressor with shifted surge limit |
DE3308140C2 (en) * | 1983-03-08 | 1985-12-19 | MTU Motoren- und Turbinen-Union München GmbH, 8000 München | Multi-stage gas turbine |
SU1666807A1 (en) * | 1989-07-19 | 1991-07-30 | Харьковский авиационный институт им.Н.Е.Жуковского | Axial-flow compressor |
EP0978633A1 (en) * | 1998-08-07 | 2000-02-09 | Asea Brown Boveri AG | Turbomachine blade |
DE10205363A1 (en) * | 2002-02-08 | 2003-08-21 | Rolls Royce Deutschland | gas turbine |
US7575412B2 (en) * | 2002-02-28 | 2009-08-18 | Mtu Aero Engines Gmbh | Anti-stall casing treatment for turbo compressors |
DE102004030597A1 (en) * | 2004-06-24 | 2006-01-26 | Rolls-Royce Deutschland Ltd & Co Kg | Turbomachine with external wheel jet generation at the stator |
GB2417053B (en) * | 2004-08-11 | 2006-07-12 | Rolls Royce Plc | Turbine |
DE102006048933A1 (en) | 2006-10-17 | 2008-04-24 | Mtu Aero Engines Gmbh | Arrangement for influencing the flow |
US20100284795A1 (en) * | 2007-12-28 | 2010-11-11 | General Electric Company | Plasma Clearance Controlled Compressor |
-
2009
- 2009-07-17 DE DE102009033754A patent/DE102009033754A1/en not_active Withdrawn
-
2010
- 2010-07-13 EP EP10007218.0A patent/EP2292934A3/en not_active Withdrawn
- 2010-07-14 US US12/836,363 patent/US8591179B2/en not_active Expired - Fee Related
Non-Patent Citations (1)
Title |
---|
None |
Also Published As
Publication number | Publication date |
---|---|
EP2292934A3 (en) | 2014-03-19 |
DE102009033754A1 (en) | 2011-01-20 |
US20110014037A1 (en) | 2011-01-20 |
US8591179B2 (en) | 2013-11-26 |
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