EP2275690A2 - Axial compressor - Google Patents
Axial compressor Download PDFInfo
- Publication number
- EP2275690A2 EP2275690A2 EP10007329A EP10007329A EP2275690A2 EP 2275690 A2 EP2275690 A2 EP 2275690A2 EP 10007329 A EP10007329 A EP 10007329A EP 10007329 A EP10007329 A EP 10007329A EP 2275690 A2 EP2275690 A2 EP 2275690A2
- Authority
- EP
- European Patent Office
- Prior art keywords
- rotor
- blade
- rotor hub
- compressor
- height
- 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.)
- Withdrawn
Links
Images
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
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
- F04D29/324—Blades
-
- 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
-
- 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
- F04D29/684—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps by fluid injection
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
- F05D2240/304—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the trailing edge of a rotor blade
Definitions
- the invention relates to an axial compressor which comprises at least one rotor arranged in a housing with compressor blades extending from a rotor hub and a stator, in particular for an aircraft gas turbine.
- the essential components of an axial compressor provided for increasing the pressure of the supplied air are the rotor which is rotatably driven in a housing and the guide means (stator) which is mounted on the housing inner wall and consists of individual guide vanes.
- the rotor consists of compressor blades arranged at the circumference of a drive shaft or hub.
- multi-stage compressors used in gas turbine engines comprise two or more connected to a drum and connected to a drive shaft rotor disks on the outer circumference of the compressor blades are either detachable and thus easily replaceable attached or - in the case of a blisk designed as a rotor - are integrally formed.
- the compressor blades emanate directly from the outer peripheral surface of the rotor disk in a blisk
- the compressor blades mounted axially or circumferentially on the rotor disk each have an integral blade root (platform, shroud) which is held on the rotor disk via a guide piece integrally formed on its underside is.
- the transitional area between the compressor blades and the rotor hub that is, the compressor blade and the peripheral surface of the rotor disk with integrally molded blades and the blade root with interchangeable blades mounted on the rotor disk, however, experience secondary flow phenomena, for example, corner separations, channel vortices, or cross channel flows. which lead to flow separations on the blade surface and the rotor hub (blade root, rotor disk), in particular in rotors with high hub load such as the fan or the low-pressure compressor of a gas turbine engine, and result in locally high pressure losses. This reduces the compressor efficiency and consequently increases fuel consumption.
- the invention is therefore based on the object of specifying a particular for aircraft gas turbines axial compressor with improved aerodynamic performance.
- an axial compressor which comprises at least one arranged in a housing rotor with rotor hub starting compressor blades and a stator and the compressor blades a blade tip, a leading and trailing edge and a measured at the rotor hub chord length and measured at the blade center height between the rotor hub and Having blade tip
- the core of the invention in the formation of an emanating from the trailing edge of the compressor blades and immediately adjacent to the rotor hub slot-shaped recess through which in the transition region between the rotor hub and compressor blades usually occurring secondary flows can be significantly reduced, and therefore caused by secondary flow phenomena losses can be reduced and thus the compressor efficiency is increased.
- the rotor hub may be formed by the blade root of separately manufactured on the periphery of a rotor disk compressor blades or - in integrally connected to the rotor disk compressor blades - also directly through the rotor hub.
- the slot-shaped recess has a maximum height of two percent of the blade height, which may be constant or different in the longitudinal direction of the recess, for example starting from the trailing edge may be gradually reduced.
- the recess has a minimum length of ten percent of the chord length and a maximum length of 50 percent of the chord length.
- the in Fig. 1 shown axial compressor which acts here as a low-pressure compressor in an aircraft gas turbine, comprises five rotors 2 connected to a rotor drum 1.
- the rotor drum 1 is arranged in a housing 3 and connected to a drive shaft 4.
- the Rotors 2 each consist of a rotor disk 5, which forms, as it were, a rotor hub 6 connected to the drive shaft 4, from the outer peripheral surface of which the compressor blades 7 originate.
- the compressor blades 7 as detachably mounted on the rotor disk 5, exchangeable individual blades with a the outer peripheral surface of the rotor hub 6 and rotor disk 5 forming blade root 8 (inner shroud, inner platform) executed.
- stator 9 Between the compressor blades 7 of the adjacent rotors 2 are each a stator 9, consisting of stator 3 attached to the housing 10 is arranged.
- the compressor blades 7 can also be formed integrally on the rotor disks 5 (rotor hub 6) in the design of the rotors 2 as a blisk, so that in this case the compressor blades 7 emanate directly from the peripheral surface of the rotor disk 5 or rotor hub 6.
- Fig. 2 schematically shows a directly from a hub 6, that is, the peripheral surface of the rotor disk 5 outgoing compressor blade 7, a blade tip 11, a leading edge 12 and a trailing edge 13 and a chord length C on the rotor hub 6 and a height H between the rotor hub 6 and blade tip eleventh at half the chord length C has.
- a directly adjacent to the rotor hub 6 (rotor disk 5, blade root 8) section is formed from the rear edge 13 outgoing slot-shaped recess 14 in the compressor blade 7, whose height S does not exceed two percent of the blade height H and whose length L at least 10% of Chord length C and at most 50% of the chord length C is.
- the height S of the recess 14 along the chord length C may be constant or variable.
- the height S of the recess 14, which here has a length L of 10% of the chord length C gradually decreases towards the middle of the blade.
- the formation of channel vortices, transverse flows and corner separations in the transition region between the rotor hub 6 - here the blade root 8 or the rotor disk 5 - becomes clear reduces and thus improves the secondary flow behavior and the flow to the subsequent stator 9, so that - especially in rotors with high hub load as the fan of a gas turbine engine - the rotor losses are reduced and increases the compressor efficiency and ultimately the fuel consumption can be reduced.
Landscapes
- 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 mindestens einen in einem Gehäuse angeordneten Rotor mit von einer Rotornabe ausgehenden Verdichterschaufeln und einen Stator umfasst, insbesondere für eine Fluggasturbine.The invention relates to an axial compressor which comprises at least one rotor arranged in a housing with compressor blades extending from a rotor hub and a stator, in particular for an aircraft gas turbine.
Die wesentliche Bestandteile eines zur Erhöhung des Druckes der zugeführten Luft vorgesehenen Axialverdichters sind der in einem Gehäuse drehbar angetriebene Rotor und die an der Gehäuseinnenwand angebrachte, aus einzelnen Leitschaufeln bestehende Leiteinrichtung (Stator). Der Rotor besteht aus am Umfang einer Antriebswelle oder Nabe im Abstand angeordneten Verdichterschaufeln. Bei Gasturbinentriebwerken eingesetzte mehrstufige Verdichter umfassen zwei oder mehrere zu einer Trommel verbundene und an eine Antriebswelle angeschlossene Rotorscheiben, an deren Außenumfang die Verdichterschaufeln entweder lösbar und damit leicht austauschbar befestigt sind oder -im Falle eines als Blisk ausgeführten Rotors - einstückig angeformt sind. Während die Verdichterschaufeln bei einer Blisk unmittelbar von der Außenumfangsfläche der Rotorscheibe ausgehen, weisen die axial oder in Umfangsrichtung zur Rotorscheibe montierten Verdichterschaufeln jeweils einen integral mit dieser verbundenen Schaufelfuß (Plattform, Deckband) auf, der über ein an dessen Unterseite angeformtes Führungsstück an der Rotorscheibe gehalten ist.The essential components of an axial compressor provided for increasing the pressure of the supplied air are the rotor which is rotatably driven in a housing and the guide means (stator) which is mounted on the housing inner wall and consists of individual guide vanes. The rotor consists of compressor blades arranged at the circumference of a drive shaft or hub. In multi-stage compressors used in gas turbine engines comprise two or more connected to a drum and connected to a drive shaft rotor disks on the outer circumference of the compressor blades are either detachable and thus easily replaceable attached or - in the case of a blisk designed as a rotor - are integrally formed. While the compressor blades emanate directly from the outer peripheral surface of the rotor disk in a blisk, the compressor blades mounted axially or circumferentially on the rotor disk each have an integral blade root (platform, shroud) which is held on the rotor disk via a guide piece integrally formed on its underside is.
Bei einem Gasturbinentriebwerk wird zwischen dem Fan sowie Niederdruck-, Mitteldruck- und Hochdruckverdichtern unterschieden, an die hinsichtlich der aerodynamischen Leistungsfähigkeit hohe Anforderungen gestellt werden. In dem Übergangsbereich zwischen den Verdichterschaufeln und der Rotornabe, das heißt, der Verdichterschaufel und der Umfangsfläche der Rotorscheibe bei integral angeformten Schaufeln bzw. der Verdichterschaufel und dem Schaufelfuß bei an der Rotorscheibe montierten austauschbaren Schaufeln, treten jedoch Sekundärströmungsphänomene, zum Beispiel Eckenablösungen, Kanalwirbel oder Querkanalströmungen, auf, die - insbesondere bei Rotoren mit hoher Nabenbelastung wie dem Fan oder dem Niederdruckverdichter eines Gasturbinentriebwerks - zu Strömungsablösungen an der Schaufeloberfläche und der Rotornabe (Schaufelfuß, Rotorscheibe) führen und lokal hohe Druckverluste zur Folge haben. Dadurch wird der Verdichterwirkungsgrad reduziert und folglich der Treibstoffverbrauch erhöht.In a gas turbine engine, a distinction is made between the fan as well as low-pressure, medium-pressure and high-pressure compressors, to which high demands are made in terms of aerodynamic performance. In However, the transitional area between the compressor blades and the rotor hub, that is, the compressor blade and the peripheral surface of the rotor disk with integrally molded blades and the blade root with interchangeable blades mounted on the rotor disk, however, experience secondary flow phenomena, for example, corner separations, channel vortices, or cross channel flows. which lead to flow separations on the blade surface and the rotor hub (blade root, rotor disk), in particular in rotors with high hub load such as the fan or the low-pressure compressor of a gas turbine engine, and result in locally high pressure losses. This reduces the compressor efficiency and consequently increases fuel consumption.
Der Erfindung liegt daher die Aufgabe zugrunde, einen insbesondere für Fluggasturbinen vorgesehen Axialverdichter mit verbesserter aerodynamischer Leistungsfähigkeit anzugeben.The invention is therefore based on the object of specifying a particular for aircraft gas turbines axial compressor with improved aerodynamic performance.
Erfindungsgemäß wird die Aufgabe mit einem gemäß den Merkmalen des Patenanspruchs 1 ausgebildeten Axialverdichter gelöst. Vorteilhafte Weiterbildungen 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 of the invention are the subject of the dependent claims.
Ausgehend von einem Axialverdichter, der mindestens einen in einem Gehäuse angeordneten Rotor mit von einer Rotornabe ausgehenden Verdichterschaufeln und einen Stator umfasst und dessen Verdichterschaufeln eine Schaufelspitze, eine Vorder- und Hinterkante und eine an der Rotornabe gemessene Sehnenlänge sowie eine in Schaufelmitte gemessene Höhe zwischen Rotornabe und Schaufelspitze aufweisen, besteht der Kern der Erfindung in der Ausbildung einer von der Hinterkante der Verdichterschaufeln ausgehenden und unmittelbar an die Rotornabe angrenzenden schlitzförmigen Ausnehmung, durch die im Übergangsbereich zwischen Rotornabe und Verdichterschaufeln üblicherweise auftretende Sekundärströmungen deutlich reduziert und mithin durch Sekundärströmungsphänomene bedingte Verluste verringert werden können und somit der Verdichterwirkungsgrad erhöht wird.Starting from an axial compressor, which comprises at least one arranged in a housing rotor with rotor hub starting compressor blades and a stator and the compressor blades a blade tip, a leading and trailing edge and a measured at the rotor hub chord length and measured at the blade center height between the rotor hub and Having blade tip, the core of the invention in the formation of an emanating from the trailing edge of the compressor blades and immediately adjacent to the rotor hub slot-shaped recess through which in the transition region between the rotor hub and compressor blades usually occurring secondary flows can be significantly reduced, and therefore caused by secondary flow phenomena losses can be reduced and thus the compressor efficiency is increased.
Die Rotornabe kann durch den Schaufelfuß von am Umfang einer Rotorscheibe montierten separat gefertigten Verdichterschaufeln oder - bei integral mit der Rotorscheibe verbundenen Verdichterschaufeln - auch unmittelbar durch die Rotornabe gebildet sein.The rotor hub may be formed by the blade root of separately manufactured on the periphery of a rotor disk compressor blades or - in integrally connected to the rotor disk compressor blades - also directly through the rotor hub.
In weiterer Ausbildung der Erfindung weist die schlitzförmige Ausnehmung eine maximale Höhe von zwei Prozent der Schaufelhöhe auf, die in Längsrichtung der Ausnehmung konstant oder unterschiedlich sein, beispielsweise ausgehend von der Hinterkante allmählich geringer werden kann.In a further embodiment of the invention, the slot-shaped recess has a maximum height of two percent of the blade height, which may be constant or different in the longitudinal direction of the recess, for example starting from the trailing edge may be gradually reduced.
In weiterer Ausbildung der Erfindung hat die Ausnehmung eine minimale Länge von zehn Prozent der Sehnenlänge und eine maximale Länge von 50 Prozent der Sehnenlänge.In a further embodiment of the invention, the recess has a minimum length of ten percent of the chord length and a maximum length of 50 percent of the chord length.
Ein Ausführungsbeispiel der Erfindung wird anhand der Zeichnung näher erläutert. Es zeigen:
- Fig. 1
- einen Längsschnitt eines Niederdruckverdichters für eine Fluggasturbine; und
- Fig. 2
- eine schematische Darstellung einer an einer Ro- tornabe angebrachten Verdichterschaufel.
- Fig. 1
- a longitudinal section of a low-pressure compressor for an aircraft gas turbine; and
- Fig. 2
- a schematic representation of an attached to a rotor hub compressor blade.
Der in
Aufgrund der in dem an die Rotornabe 6 (Schaufelfuß bzw. Rotorscheibe) angrenzenden Abschnitt in die Verdichterschaufel 7 eingeformten schlitzartigen Ausnehmung 14 wird die Ausbildung von Kanalwirbeln, Querströmungen und Eckenablösungen im Übergangsbereich zwischen der Rotornabe 6 - hier dem Schaufelfuß 8 oder der Rotorscheibe 5 - deutlich reduziert und somit das Sekundärströmungsverhalten und die Anströmung auf den nachfolgenden Stator 9 verbessert, so dass - insbesondere bei Rotoren mit hoher Nabenbelastung wie dem Fan eines Gasturbinentriebwerks - die Rotorverluste gesenkt werden und der Verdichterwirkungsgrad erhöht und letztlich der Treibstoffverbrauch reduziert werden kann.Due to the slit-
- 11
- Rotortrommelrotor drum
- 22
- Rotorrotor
- 33
- Gehäusecasing
- 44
- Antriebswelledrive shaft
- 55
- Rotorscheibe (Rotornabe)Rotor disc (rotor hub)
- 66
- Rotornaberotor hub
- 77
- Verdichterschaufelcompressor blade
- 88th
- Schaufelfuß (Rotornabe)Blade root (rotor hub)
- 99
- Statorstator
- 1010
- Statorschaufelstator
- 1111
- Schaufelspitzeblade tip
- 1212
- Vorderkanteleading edge
- 1313
- Hinterkantetrailing edge
- 1414
- schlitzförmige Ausnehmungslot-shaped recess
- CC
- Sehnenlängechord length
- HH
- Höhe der SchaufelHeight of the shovel
- SS
- Höhe der schlitzförmigen AusnehmungHeight of the slot-shaped recess
Claims (8)
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102009033756A DE102009033756A1 (en) | 2009-07-17 | 2009-07-17 | Axial compressor, in particular for an aircraft gas turbine |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2275690A2 true EP2275690A2 (en) | 2011-01-19 |
EP2275690A3 EP2275690A3 (en) | 2017-04-26 |
Family
ID=42358034
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP10007329.5A Withdrawn EP2275690A3 (en) | 2009-07-17 | 2010-07-15 | Axial compressor |
Country Status (3)
Country | Link |
---|---|
US (1) | US20110027091A1 (en) |
EP (1) | EP2275690A3 (en) |
DE (1) | DE102009033756A1 (en) |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US9359905B2 (en) | 2012-02-27 | 2016-06-07 | Solar Turbines Incorporated | Turbine engine rotor blade groove |
EP3058176B1 (en) | 2013-10-02 | 2020-08-26 | United Technologies Corporation | Gas turbine engine with compressor disk deflectors |
GB201505400D0 (en) * | 2015-03-30 | 2015-05-13 | Rolls Royce Plc | Multi coordinate reference system for positioning bladed drum |
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US1982969A (en) * | 1933-02-17 | 1934-12-04 | Edward A Stalker | Aircraft |
US2399828A (en) * | 1941-10-29 | 1946-05-07 | Roche Jean Alfred | Propeller |
FR1002324A (en) * | 1946-09-09 | 1952-03-05 | S. A. | Improvements made to bladed turbo-machines, especially axial compressors |
US2622688A (en) * | 1949-12-06 | 1952-12-23 | United Aircraft Corp | Spinner construction with boundary layer control |
US2637403A (en) * | 1949-12-06 | 1953-05-05 | United Aircraft Corp | Propeller spinner construction with boundary layer control |
US2599598A (en) * | 1950-01-13 | 1952-06-10 | Wirkkala Propeller Sales Inc | Propeller |
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US2745501A (en) * | 1952-03-13 | 1956-05-15 | Gen Motors Corp | Propeller spinner assembly |
US3403893A (en) * | 1967-12-05 | 1968-10-01 | Gen Electric | Axial flow compressor blades |
US3572960A (en) * | 1969-01-02 | 1971-03-30 | Gen Electric | Reduction of sound in gas turbine engines |
DE2034890A1 (en) * | 1969-07-21 | 1971-02-04 | Rolls Royce Ltd Derby, Derbyshire (Großbritannien) | Blade for axial flow machines |
JPS5115210A (en) * | 1974-07-02 | 1976-02-06 | Rotoron Inc | Zatsuongenshono fuan |
DE3304296A1 (en) * | 1982-03-15 | 1983-09-15 | Süddeutsche Kühlerfabrik Julius Fr. Behr GmbH & Co KG, 7000 Stuttgart | Axial fan impeller, especially for a cooling fan for water-cooled internal combustion engines |
DE3716717A1 (en) * | 1986-05-19 | 1987-11-26 | Usui Kokusai Sangyo Kk | BLADES FOR HIGH-SPEED PROPELLER FANS |
US5112191A (en) * | 1989-04-11 | 1992-05-12 | General Electric Company | Rotating cowling |
US5352123A (en) * | 1992-06-08 | 1994-10-04 | Quickturn Systems, Incorporated | Switching midplane and interconnection system for interconnecting large numbers of signals |
JPH0946782A (en) * | 1995-08-01 | 1997-02-14 | Fujitsu Ltd | Transfer method for setting information and monitoring information in communication equipment |
US6062817A (en) * | 1998-11-06 | 2000-05-16 | General Electric Company | Apparatus and methods for cooling slot step elimination |
US6272136B1 (en) * | 1998-11-16 | 2001-08-07 | Sun Microsystems, Incorporated | Pseudo-interface between control and switching modules of a data packet switching and load balancing system |
EP1316017A2 (en) * | 2000-08-07 | 2003-06-04 | Inrange Technologies Corporation | Method and apparatus for imparting fault tolerance in a director switch |
US7068609B2 (en) * | 2000-08-09 | 2006-06-27 | Broadcom Corporation | Method and apparatus for performing wire speed auto-negotiation |
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GB2371706B (en) * | 2001-01-30 | 2003-04-23 | 3Com Corp | Link aggregation control for network devices |
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CA2488151C (en) * | 2002-06-05 | 2009-04-28 | Aloys Wobben | Rotor blade for a wind power plant |
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JP4541013B2 (en) * | 2004-03-29 | 2010-09-08 | 富士通株式会社 | Network equipment with Ethernet interface |
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US8780899B2 (en) * | 2006-01-23 | 2014-07-15 | Allied Telesis Holdings K.K. | Method and system for improving traffic distribution across a communication network |
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-
2009
- 2009-07-17 DE DE102009033756A patent/DE102009033756A1/en not_active Withdrawn
-
2010
- 2010-07-14 US US12/836,373 patent/US20110027091A1/en not_active Abandoned
- 2010-07-15 EP EP10007329.5A patent/EP2275690A3/en not_active Withdrawn
Non-Patent Citations (1)
Title |
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None |
Also Published As
Publication number | Publication date |
---|---|
DE102009033756A1 (en) | 2011-01-20 |
EP2275690A3 (en) | 2017-04-26 |
US20110027091A1 (en) | 2011-02-03 |
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