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WO2005019604A1 - Flow guide device contained in the diffuser of turbomachinery and flow diversion method - Google Patents

Flow guide device contained in the diffuser of turbomachinery and flow diversion method Download PDF

Info

Publication number
WO2005019604A1
WO2005019604A1 PCT/EP2004/007252 EP2004007252W WO2005019604A1 WO 2005019604 A1 WO2005019604 A1 WO 2005019604A1 EP 2004007252 W EP2004007252 W EP 2004007252W WO 2005019604 A1 WO2005019604 A1 WO 2005019604A1
Authority
WO
WIPO (PCT)
Prior art keywords
outflow
guide
deflection surface
rotor
guide device
Prior art date
Application number
PCT/EP2004/007252
Other languages
German (de)
French (fr)
Inventor
Andreas Kayser
Original Assignee
Siemens Aktiengesellschaft
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Siemens Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Priority to EP04740600A priority Critical patent/EP1651842A1/en
Publication of WO2005019604A1 publication Critical patent/WO2005019604A1/en

Links

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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • 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
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • F01D25/162—Bearing supports
    • 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
    • F01D25/30—Exhaust heads, chambers, or the like
    • 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
    • F05D2250/00—Geometry
    • F05D2250/40—Movement of components
    • F05D2250/41—Movement of components with one degree of freedom
    • F05D2250/411—Movement of components with one degree of freedom in rotation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/70—Adjusting of angle of incidence or attack of rotating blades
    • F05D2260/74—Adjusting of angle of incidence or attack of rotating blades by turning around an axis perpendicular the rotor centre line

Definitions

  • the invention relates to an outflow guide device in a diffuser of a turbomachine with a guide blade, which has a leading edge and a trailing edge, between which a deflection surface is provided and which deflects a flow medium from an incident direction, and a method for changing an outflow guide device.
  • a gas turbine as an example of a turbomachine
  • intake air is compressed and heated in the compressor part and then strongly heated and accelerated in a combustion chamber with the addition of a fuel.
  • a multi-stage turbine connects to the combustion chamber in terms of flow.
  • the flow medium which is a mixture of the burned fuel and the compressed air, flows through the multi-stage turbine.
  • the movement of the flow medium creates an angular momentum on the rotor and thus ultimately leads to a rotation of the rotor.
  • the rotational energy is then converted into electrical energy using a generator.
  • the flow medium flows in a diffuser past a bearing star, which has several guide blades.
  • the bearing star serves on the one hand for deflecting the flow medium and on the other hand as a holder for the rotatably mounted rotor.
  • the bearing star and in particular the guide blades are usually made rigid and of the same material.
  • Such a bearing star arrangement is described in document DE 39 42 203.
  • the bearing star arrangement there relates to a turbine engine.
  • the object of the present invention is to provide an outflow guiding device with which flow losses in a diffuser can be reduced.
  • Another object is to provide a method for changing an outflow guide device in a diffuser to reduce the flow losses.
  • the object directed to the outflow guiding device is achieved by an outflow guiding device
  • Turbomachine with a guide blade which has a leading edge and a trailing edge between which a deflecting surface is provided which deflects a flow medium from an incident direction
  • the outflow guiding device being mountable in a diffuser
  • the outflow guiding device comprising a rotor-side end and a stator-side end and the rotor-side End is designed to support a rotor
  • the guide blade being adjustable with respect to the course of its deflection surface relative to the direction of incidence.
  • the object directed towards the method is achieved by a method for changing an outflow guide device of a turbomachine with a guide blade, which has a leading edge and a trailing edge between which a deflection surface is provided which deflects a flow medium from an incident direction, the outflow guide device in a diffuser is installed, a rotor-side end and a stator-side end being provided for the outflow guiding device and the rotor-side end supporting the rotor, a course of the deflection surface of the guide blade being adjustable relative to the incident sighting.
  • the advantage can be seen, inter alia, in the fact that a flow of a flow medium through the outflow guiding device can be changed in a targeted manner, and thereby an inflow of the Lagersterns is improved.
  • Another advantage is that the outflow guiding device can be adjusted during the intended operation.
  • Another advantage is that an exhaust gas swirl is reduced and, furthermore, the flow is improved for each load state of the turbine or operating state of the turbine.
  • the guide blade is preferably designed in such a way that the deflection surface can be rotated.
  • the guide sheet is rotatably mounted about an axis of rotation.
  • the axis of rotation is essentially perpendicular to the direction of incidence. This changes the overall aerodynamics of the blade.
  • the outer shape of the deflection surface is preferably designed to be adjustable.
  • the guide sheet comprises a front part located in the leading edge and a rear part located in the trailing edge.
  • the rear part located in the trailing edge is rotatably supported about an axis of rotation.
  • the axis of rotation is essentially parallel to the trailing edge.
  • the front part which is usually very solid, can be rigidly installed in the diffuser.
  • the rear part which is rotatably supported, improves the inflow through the outflow guide device due to the changeable aerodynamics.
  • the rear part is preferably designed in such a way that the rear part is moved in a flow direction that runs directly from the leading edge to the trailing edge.
  • the length in the flow direction of a respective guide sheet can hereby be changed individually.
  • the guide sheet can be shortened or lengthened in the direction of flow.
  • Figure 1 is a perspective view of a prior art power stage of a gas turbine
  • FIG. 2 shows a perspective illustration of a guide sheet of an outflow guide device belonging to the prior art
  • Figure 3 is a cross-sectional view of a guide sheet in a first embodiment
  • Figure 4 is a cross-sectional view of a guide sheet in a second embodiment
  • Figure 5 is a cross-sectional view of a guide sheet in a third embodiment.
  • FIG. 1 shows a perspective illustration of a gas turbine 1 belonging to the prior art.
  • An end turbine stage 3 which comprises a plurality of moving blades 4, is attached to a rotatably mounted rotor 2.
  • An outer housing is arranged around the rotor 2 and has a lower part 5a and an upper part 5b.
  • the rotor 2 is rotatably mounted about an axis of rotation 6.
  • a flow medium flows parallel to the axis of rotation 6 in the direction of the turbine stage 3.
  • the flow medium flows into the diffuser 7.
  • the flow medium flows through an incident direction through a so-called bearing star, which is also referred to as a discharge guide device 8.
  • the outflow guide device 8 comprises six guide blades 9. In alternative embodiments, fewer or more than six guide blades 9 are possible.
  • the flow medium flows out at a varying outflow angle after turbine stage 3.
  • the outflow angle depends on a load attached to the rotor 2.
  • the outflow guiding device 8 comprises a rotor-side end 10 and a stator-side end 11.
  • the rotor-side end 10 is designed such that the rotor 2 is rotatably mounted therein.
  • Figure 2 is a perspective view of a
  • a flow medium flows to the guide blade 9 in an incident direction 12.
  • the incident direction 12 depends on the outflow angle.
  • the flow medium is true 'first to a leading edge 13, flows around a respective environmental guide surface 15 and then flows from a trailing edge 14 from the gas turbine 1 out.
  • the guide sheet 9 is designed such that the guide sheet 9 can be adjusted with respect to the course of its deflecting surface 15 relative to the direction of incidence 12.
  • This configuration of the guide blade 9 minimizes losses which are caused by non-optimal flow against the guide blade 9 as a result of the load-dependent varying outflow angle.
  • the deflection surface (15) can be rotatable.
  • the outer shape of the deflection surface (15) can be adjustable.
  • a first embodiment is shown in FIG. 3.
  • a cross section of the guide leaf 9 can be seen in FIG. The viewing direction is essentially perpendicular to the direction of incidence 12 in the direction of the axis of rotation 6.
  • the guide blade 9 is in this case rotatably mounted about an axis of rotation 16.
  • This axis of rotation 16 is essentially perpendicular to the direction of incidence 12.
  • the axis of rotation 16 lies essentially in the center of the guide blade 9.
  • the axis of rotation 6 can also be attached closer to the leading edge 13 or the trailing edge 14.
  • the guide sheet 9 is rotated about the axis of rotation 16.
  • the guide sheet 9 is rotated about the axis of rotation 16 either clockwise 17 or counterclockwise 18.
  • a flow medium that impinges on the guide blade 9 in the direction of incidence 12 can thereby be deflected.
  • the guide sheet 9 comprises a front part 20 comprising the leading edge 13 and a rear part 19 comprising the trailing edge 14.
  • the front part 20 is of rigid construction.
  • the front part 20 can also be rotatably supported about a further axis of rotation.
  • the rear part 19 is designed such that it is rotatably mounted about an axis of rotation 21.
  • the axis of rotation 21 is attached in a front region 22 of the rear part 19.
  • a rear region 23 can thereby be moved either clockwise 17 or counterclockwise 18.
  • a third embodiment of the guide sheet 9 can be seen in FIG.
  • the rear part 19 is moved in the flow direction either to the direction of incidence (represented by arrow 24) or counter to the direction of incidence (represented by arrow 25).
  • the front part 20 of the guide sheet 9 can be rotatably mounted about an additional axis of rotation in an alternative embodiment.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Turbines (AREA)

Abstract

The invention relates to a flow guide device contained in the diffuser (7) of turbomachinery. Said device comprises at least one guide blade (9) with a leading edge (13) and a trailing edge (14), a deflection surface (15) being provided between said edges. The deflection surface diverts a flow medium from its direction of arrival (12) and the course of the deflection surface (15) of the guide blade or blades can be adjusted in relation to the direction of arrival (12).

Description

Beschreibungdescription
ABSTROMLEITEINRICHTUNG IM DIFFUSOR EINER STRÖMUNG SMASCHINE UND VERFAHREN ZUR STRÖMUNGSABLENKUNGDISCHARGE DEVICE IN THE DIFFUSER OF A FLOW MACHINE AND METHOD FOR DEFLECTING THE FLOW
Die Erfindung betrifft eine Abströmleiteinrichtung in einem Diffusor einer Strömungsmaschine mit einem Leitblatt, das eine Anströmkante und eine Abströmkante aufweist, zwischen denen eine Umlenkfläche vorgesehen ist und die ein Strδmungs- medium aus einer Einfallsrichtung umlenkt sowie ein Verfahren zur Änderung einer Abströmleiteinrichtung.The invention relates to an outflow guide device in a diffuser of a turbomachine with a guide blade, which has a leading edge and a trailing edge, between which a deflection surface is provided and which deflects a flow medium from an incident direction, and a method for changing an outflow guide device.
In einer Gasturbine als Beispiel einer Strömungsmaschine wird im Verdichterteil Ansaugluft komprimiert und erwärmt und anschließend in einer Brennkammer unter Beimischung eines Brennstoffes stark erhitzt und beschleunigt. Eine mehrstufige Turbine schließt strömungstechnisch an die Brennkammer an. Durch die mehrstufige Turbine strömt das Strömungsmedium, das ein Gemisch aus dem verbrannten Brennstoff und der komprimierten Luf ist . Die Bewegung des Strδmungsmediums erzeugt einen Drehimpüls auf den Rotor und führt somit schließlich zu einer Rotation des Rotors. Die Rotationsenergie wird anschließend mittels eines Generators in elektrische Energie umgewandelt .In a gas turbine as an example of a turbomachine, intake air is compressed and heated in the compressor part and then strongly heated and accelerated in a combustion chamber with the addition of a fuel. A multi-stage turbine connects to the combustion chamber in terms of flow. The flow medium, which is a mixture of the burned fuel and the compressed air, flows through the multi-stage turbine. The movement of the flow medium creates an angular momentum on the rotor and thus ultimately leads to a rotation of the rotor. The rotational energy is then converted into electrical energy using a generator.
Nach der letzten Stufe der mehrstufigen Turbine strömt das Strömungsmedium in einem Diffusor an einem Lagerstern, der mehrere Leitblätter aufweist, vorbei. Der Lagerstern dient einerseits zur Umlenkung des Strömungsmediums und andererseits als Halterung für den drehbar gelagerten Rotor. Übli- cherweise werden der Lagerstern und insbesondere die Leit- blätter starr und materialeinheitlich ausgeführt.After the last stage of the multi-stage turbine, the flow medium flows in a diffuser past a bearing star, which has several guide blades. The bearing star serves on the one hand for deflecting the flow medium and on the other hand as a holder for the rotatably mounted rotor. The bearing star and in particular the guide blades are usually made rigid and of the same material.
In dem Dokument DE 39 42 203 ist eine solche Lagersternanordnung beschrieben. Die dortige Lagersternanordnung bezieht sich auf ein Turbinentriebwerk. Aufgabe der vorliegenden Erfindung ist es, eine Abströmleiteinrichtung anzugeben, mit der Strömungsverluste in einem Diffusor verringert werden können.Such a bearing star arrangement is described in document DE 39 42 203. The bearing star arrangement there relates to a turbine engine. The object of the present invention is to provide an outflow guiding device with which flow losses in a diffuser can be reduced.
Eine weitere Aufgabe ist es, ein Verfahren zur Änderung einer Abströmleiteinrichtung in einem Diffusor zur Verringerung der Strömungsverluste anzugeben .Another object is to provide a method for changing an outflow guide device in a diffuser to reduce the flow losses.
Die auf die Abstrδmleiteinrichtung gerichtete Aufgabe wird gelöst durch eine Abströmleiteinrichtung einerThe object directed to the outflow guiding device is achieved by an outflow guiding device
Strömungsmaschine mit einem Leitblatt, das eine Anströmkante und eine Abströmkante aufweist zwischen denen eine Umlenkfläche vorgesehen ist, die ein Strömungsmedium aus einer Einfallsrichtung umlenkt, wobei die Abströmleiteinrichtung in einem Diffusor einbaubar ist, wobei die Abströmleiteinrichtung ein rotorseitiges Ende und ein statorseitiges Ende umfasst und das rotorseitige Ende zum Lagern eines Rotors ausgebildet ist, wobei das Leitblatt hinsichtlich eines Verlaufs seiner Umlenkfläche relativ zur Einfallsrichtung einstellbar ist.Turbomachine with a guide blade, which has a leading edge and a trailing edge between which a deflecting surface is provided which deflects a flow medium from an incident direction, the outflow guiding device being mountable in a diffuser, the outflow guiding device comprising a rotor-side end and a stator-side end and the rotor-side End is designed to support a rotor, the guide blade being adjustable with respect to the course of its deflection surface relative to the direction of incidence.
Die auf das Verfahren hin gerichtete Aufgabe wird gelöst durch ein Verfahren zur Änderung einer Abströmleiteinrichtung einer Strömungsmaschine mit einem Leitblatt, das eine Anströmkante und eine Abströmkante aufweist zwischen denen eine Umlenkfläche vorgesehen ist, die ein Strömungsmedium aus einer Einfallsrichtung umlenkt, wobei die Abströmleiteinrichtung in einem Diffusor eingebaut wird, wobei für die Abströmleiteinrichtung ein rotorseitiges Ende und ein statorseitiges Ende vorgesehen wird und das rotorseitige Ende den Rotor lagert, wobei ein Verlauf der Umlenkfläche des Leitblattes relativ zur EinfallSichtung einstellbar ist.The object directed towards the method is achieved by a method for changing an outflow guide device of a turbomachine with a guide blade, which has a leading edge and a trailing edge between which a deflection surface is provided which deflects a flow medium from an incident direction, the outflow guide device in a diffuser is installed, a rotor-side end and a stator-side end being provided for the outflow guiding device and the rotor-side end supporting the rotor, a course of the deflection surface of the guide blade being adjustable relative to the incident sighting.
Der Vorteil ist unter anderem darin zu sehen, dass eine Strömung eines Strδmungsmediums durch die Abströmleiteinrichtung gezielt verändert werden kann und dadurch eine Anströmung des Lagersterns verbessert wird. Ein weiterer Vorteil ist, dass die Abströmleiteinrichtung während des bestimmungsgemäßen Betriebes eingestellt werden kann.The advantage can be seen, inter alia, in the fact that a flow of a flow medium through the outflow guiding device can be changed in a targeted manner, and thereby an inflow of the Lagersterns is improved. Another advantage is that the outflow guiding device can be adjusted during the intended operation.
Ein weiterer Vorteil ist, dass ein Abgasdrall vermindert wird und des weiteren wird für jeden Lastzustand der Turbine bzw. Betriebszustand der Turbine die Strömung verbessert.Another advantage is that an exhaust gas swirl is reduced and, furthermore, the flow is improved for each load state of the turbine or operating state of the turbine.
Vorzugsweise wird das Leitblatt derart ausgebildet, dass die Umlenkfläche drehbar ist. Insbesondere wird das Leitblatt um eine Drehachse drehbar gelagert . Die Drehachse verläuft hierbei im wesentlichen senkrecht zur Einfallsrichtung. Dadurch wird die Leitblattaerodynamik insgesamt verändert .The guide blade is preferably designed in such a way that the deflection surface can be rotated. In particular, the guide sheet is rotatably mounted about an axis of rotation. The axis of rotation is essentially perpendicular to the direction of incidence. This changes the overall aerodynamics of the blade.
Vorzugsweise ist die äußere Form der Umlenkfläche einstellbar ausgebildet. Insbesondere umfasst das Leitblatt ein in der Anströmkante befindliches Vorderteil und ein in der Abströmkante befindliches Heckteil. Das in der Abströmkante befindliche Heckteil ist um eine Drehachse drehbar gelagert. Die Drehachse ist hierbei im wesentlichen parallel zur Abströmkante ausgebildet.The outer shape of the deflection surface is preferably designed to be adjustable. In particular, the guide sheet comprises a front part located in the leading edge and a rear part located in the trailing edge. The rear part located in the trailing edge is rotatably supported about an axis of rotation. The axis of rotation is essentially parallel to the trailing edge.
Dadurch kann das Vorderteil, das in der Regel sehr massiv ausgeführt ist, starr in den Diffusor eingebaut werden. Das Heckteil, das drehbar gelagert wird, verbessert durch die veränderbare Aerodynamik die Anströmung durch die Abströmleiteinrichtung .As a result, the front part, which is usually very solid, can be rigidly installed in the diffuser. The rear part, which is rotatably supported, improves the inflow through the outflow guide device due to the changeable aerodynamics.
Vorzugsweise wird das Heckteil bei einer weiteren Ausfüh- rungsform der Erfindung derart ausgebildet, dass das Heckteil in einer Strömungsrichtung, die von der Anströmkante direkt zur Abströmkante verläuft, bewegt wird. Die Länge in Strömungsrichtung eines jeweiligen Leitblattes kann hierdurch individuell geändert werden. Je nach Anforderung kann das Leit- blatt in Strömungsrichtung verkürzt oder verlängert werden. Anhand der nachfolgenden Beschreibung werden Ausführungsbei- spiele der Erfindung unter Bezugnahme auf die Zeichnungen noch näher erläutert .In a further embodiment of the invention, the rear part is preferably designed in such a way that the rear part is moved in a flow direction that runs directly from the leading edge to the trailing edge. The length in the flow direction of a respective guide sheet can hereby be changed individually. Depending on the requirements, the guide sheet can be shortened or lengthened in the direction of flow. Based on the following description, exemplary embodiments of the invention are explained in more detail with reference to the drawings.
Dabei zeigen:Show:
Figur 1 eine perspektivische Darstellung einer zum Stand der Technik gehörenden Endstufe einer Gasturbine;Figure 1 is a perspective view of a prior art power stage of a gas turbine;
Figur 2 eine perspektivische Darstellung eines zum Stand der Technik gehörenden Leitblattes einer Abströmleiteinrichtung;FIG. 2 shows a perspective illustration of a guide sheet of an outflow guide device belonging to the prior art;
Figur 3 eine Querschnittsansicht eines Leitblattes in einer ersten Ausführungsform;Figure 3 is a cross-sectional view of a guide sheet in a first embodiment;
Figur 4 eine Querschnittsansicht eines Leitblattes in einer zweiten Ausführungsform;Figure 4 is a cross-sectional view of a guide sheet in a second embodiment;
Figur 5 eine Querschnittsansicht eines Leitblattes in einer dritten Ausführungsform.Figure 5 is a cross-sectional view of a guide sheet in a third embodiment.
In Figur 1 ist eine perspektivische Darstellung einer zum Stand der Technik gehörenden Gasturbine 1 zu sehen. An einem drehbar gelagerten Rotor 2 ist unter anderem eine End-Turbi- nenstufe 3, die mehrere Laufschaufeln 4 umfasst, angebracht. Um den Rotor 2 herum ist ein Außengehäuse angeordnet, das ein Unterteil 5a und ein Oberteil 5b aufweist. Der Rotor 2 ist um eine Rotationsachse 6 drehbar gelagert. Ein Strömungsmedium strömt im Betrieb parallel zur Rotationsachse 6 in Richtung der Turbinenstufe 3. Nach der Turbinenstufe 3 strömt das Strömungsmedium in den Diffusor 7. Nach dem Diffusor 7 strömt das Strömungsmedium unter einer Einfallsrichtung durch einen sogenannten Lagerstern, der auch als Abströmleiteinrichtung 8 bezeichnet wird. Die Abströmleiteinrichtung 8 umfasst sechs Leitblätter 9. In alternativen Ausführungsformen sind weniger oder mehr als sechs Leitblätter 9 möglich.FIG. 1 shows a perspective illustration of a gas turbine 1 belonging to the prior art. An end turbine stage 3, which comprises a plurality of moving blades 4, is attached to a rotatably mounted rotor 2. An outer housing is arranged around the rotor 2 and has a lower part 5a and an upper part 5b. The rotor 2 is rotatably mounted about an axis of rotation 6. During operation, a flow medium flows parallel to the axis of rotation 6 in the direction of the turbine stage 3. After the turbine stage 3, the flow medium flows into the diffuser 7. After the diffuser 7, the flow medium flows through an incident direction through a so-called bearing star, which is also referred to as a discharge guide device 8. The outflow guide device 8 comprises six guide blades 9. In alternative embodiments, fewer or more than six guide blades 9 are possible.
Das Strδmungsmedium strömt unter einem variierenden Abströmwinkel nach der Turbinenstufe 3 aus . Der Abströmwinkel hängt von einer an dem Rotor 2 anhängenden Last ab.The flow medium flows out at a varying outflow angle after turbine stage 3. The outflow angle depends on a load attached to the rotor 2.
Die Abströmleiteinrichtung 8 umfasst ein rotorseitiges Ende 10 und ein statorseitiges Ende 11. Das rotorseitige Ende 10 ist derart ausgebildet, dass der Rotor 2 darin drehbar gelagert wird.The outflow guiding device 8 comprises a rotor-side end 10 and a stator-side end 11. The rotor-side end 10 is designed such that the rotor 2 is rotatably mounted therein.
In der Figur 2 ist eine perspektivische Darstellung einesIn Figure 2 is a perspective view of a
Leitblattes 9 zu sehen. In einer Einfallsrichtung 12 strömt ein Strömungsmedium zum Leitblatt 9. Die Einfallsrichtung 12 hängt von dem Abströmwinkel ab. Das Strömungsmedium trifft' zunächst auf eine Anströmkante 13, umströmt jeweils eine Um- lenkfläche 15 und strömt anschließend von einer Abströmkante 14 aus der Gasturbine 1 heraus .Guide 9 can be seen. A flow medium flows to the guide blade 9 in an incident direction 12. The incident direction 12 depends on the outflow angle. The flow medium is true 'first to a leading edge 13, flows around a respective environmental guide surface 15 and then flows from a trailing edge 14 from the gas turbine 1 out.
Erfindungsgemäß wird das Leitblatt 9 derart ausgebildet, dass das Leitblatt 9 hinsichtlich eines Verlaufs seiner Umlenkflä- ehe 15 relativ zur Einfallsrichtung 12 einstellbar ist.According to the invention, the guide sheet 9 is designed such that the guide sheet 9 can be adjusted with respect to the course of its deflecting surface 15 relative to the direction of incidence 12.
Durch diese Ausbildung des Leitblattes 9 werden Verluste, die durch nichtoptimale Anströmung des Leitblattes 9 infolge des lastabhängigen variierenden Abströmwinkels hervorgerufen wird, minimiert.This configuration of the guide blade 9 minimizes losses which are caused by non-optimal flow against the guide blade 9 as a result of the load-dependent varying outflow angle.
In einer Ausführungsform kann die Umlenkfläche (15) drehbar sein. In einer alternativen Ausführungsform kann die äußere Form der Umlenkfläche (15) einstellbar sein. Eine erste Ausführungsform ist in Figur 3 dargestellt . In Figur 3 ist ein Querschnitt des Leitblattes 9 zu sehen. Die Blickrichtung ist hierbei im wesentlichen senkrecht zur Einfallsrichtung 12 in Richtung der Rotationsachse 6. Das Leitblatt 9 ist hierbei um eine Drehachse 16 drehbar gelagert. Diese Drehachse 16 ist im wesentlichen senkrecht zur Einfallsrichtung 12. Die Drehachse 16 liegt in diesem Ausführungsbeispiel im Wesentlichen in der Mitte des Leitblattes 9. Der Drehachsel6 kann aber auch in einer alternativen Ausfüh- rungsform näher zur Anströmkante 13 oder zur Abstrδmkante 14 angebracht werden. Während des Betriebes wird das Leitblatt 9 um die Drehachse 16 gedreht. Das Leitblatt 9 wird hierbei um die Drehachse 16 entweder im Uhrzeigersinn 17 oder entgegen dem Uhrzeigersinn 18 gedreht. Ein Strömungsmedium, das in Einfallsrichtung 12 auf das Leitblatt 9 auftrifft, kann hierdurch umgelenkt werden.In one embodiment, the deflection surface (15) can be rotatable. In an alternative embodiment, the outer shape of the deflection surface (15) can be adjustable. A first embodiment is shown in FIG. 3. A cross section of the guide leaf 9 can be seen in FIG. The viewing direction is essentially perpendicular to the direction of incidence 12 in the direction of the axis of rotation 6. The guide blade 9 is in this case rotatably mounted about an axis of rotation 16. This axis of rotation 16 is essentially perpendicular to the direction of incidence 12. In this exemplary embodiment, the axis of rotation 16 lies essentially in the center of the guide blade 9. However, in an alternative embodiment, the axis of rotation 6 can also be attached closer to the leading edge 13 or the trailing edge 14. During operation, the guide sheet 9 is rotated about the axis of rotation 16. The guide sheet 9 is rotated about the axis of rotation 16 either clockwise 17 or counterclockwise 18. A flow medium that impinges on the guide blade 9 in the direction of incidence 12 can thereby be deflected.
In Figur 4 ist eine zweite Ausführungsform des Leitblattes 9 zu sehen. Das Leitblatt 9 umfasst in dieser Ausführungsform ein die Anströmkante 13 umfassendes Vorderteil 20 und ein die Abströmkante 14 umfassendes Heckteil 19. Das Vorderteil 20 ist starr ausgeführt. In einer alternativen Ausführungsform kann das Vorderteil 20 auch um eine weitere Drehachse drehbar gelagert werden. Das Heckteil 19 ist derart ausgebildet, dass es um eine Drehachse 21 drehbar gelagert ist. Die Drehachse 21 ist hierbei in einem vorderen Bereich 22 des Heckteils 19 angebracht. Ein hinterer Bereich 23 ist dadurch entweder dem Uhrzeigersinn 17 oder entgegen Uhrzeigersinn 18 bewegbar.A second embodiment of the guide sheet 9 can be seen in FIG. In this embodiment, the guide sheet 9 comprises a front part 20 comprising the leading edge 13 and a rear part 19 comprising the trailing edge 14. The front part 20 is of rigid construction. In an alternative embodiment, the front part 20 can also be rotatably supported about a further axis of rotation. The rear part 19 is designed such that it is rotatably mounted about an axis of rotation 21. The axis of rotation 21 is attached in a front region 22 of the rear part 19. A rear region 23 can thereby be moved either clockwise 17 or counterclockwise 18.
In der Figur 5 ist eine dritte Ausführungsform des Leitblattes 9 zu sehen. Hierbei wird das Heckteil 19 in Strömungs- richtung entweder zur Einfallsrichtung (dargestellt durch den Pfeil 24) oder entgegen die Einfallsrichtung (durch den Pfeil 25 dargestellt) bewegt. Das Vorderteil 20 des Leitblattes 9 kann in einer alternativen Ausführungsform um eine weitere Drehachse drehbar gelagert werden. A third embodiment of the guide sheet 9 can be seen in FIG. Here, the rear part 19 is moved in the flow direction either to the direction of incidence (represented by arrow 24) or counter to the direction of incidence (represented by arrow 25). The front part 20 of the guide sheet 9 can be rotatably mounted about an additional axis of rotation in an alternative embodiment.

Claims

Patentansprüche claims
1. Abströmleiteinrichtung einer Strömungsmaschine mit einem Leitblatt (9) , das eine Anstrδmkante (13) und eine Abströmkante (14) aufweist, zwischen denen eine Umlenkfläche (15) vorgesehen ist, die ein Strömungsmedium aus einer Einfallsrichtung (26) umlenkt, wobei die Abströmleiteinrichtung in einem Diffusor (7) eihbaubar ist, wobei die Abströmleiteinrichtung ein rotorseitiges Ende (10) und ein statorseitiges Ende (11) umfasst und das rotorseitige Ende (10) zum Lagern eines Rotors (2) ausgebildet ist, d a d u r c h g e k e n n z e i c h n e t, dass das Leitblatt (9) hinsichtlich eines Verlaufs seiner Umlenkfläche (15) relativ zur Einfallsrichtung (12) einstellbar ist.1. Abströmleiteinrichtung a turbomachine with a guide blade (9) having a leading edge (13) and a trailing edge (14), between which a deflection surface (15) is provided, which deflects a flow medium from an incident direction (26), the discharge guide can be built in a diffuser (7), the outflow guiding device comprising a rotor-side end (10) and a stator-side end (11) and the rotor-side end (10) being designed for mounting a rotor (2), characterized in that the guide blade (9 ) is adjustable with respect to a course of its deflection surface (15) relative to the direction of incidence (12).
2. Abströmleiteinrichtung nach Anspruch 1, , d a d u r c h g e k e n n z e i c h n e t, dass die Umlenkfläche (15) drehbar ausgebildet ist.2. Abströmleiteinrichtung according to claim 1,, d a d u r c h g e k e n e z e i c h n e t that the deflection surface (15) is rotatable.
3. Abströmleiteinrichtung nach Anspruch 1 oder 2, , d a d u r c h g e k e n n z e i c h n e t, dass die äußere Form der Umlenkfläche (15) einstellbar ist.3. Abströmleiteinrichtung according to claim 1 or 2, d a d u r c h g e k e n n z e i c h n e t that the outer shape of the deflection surface (15) is adjustable.
4. Abströmleiteinrichtung nach einem der Ansprüche 1 bis 3 , d a d u r c h g e k e n n z e i c h n e t, dass das Leitblatt (9) um eine Drehachse (16) drehbar ist, wobei die Drehachse (16) im Wesentlichen senkrecht zur Ein- fallsrichtung (12) verläuft. 4. Abströmleiteinrichtung according to any one of claims 1 to 3, d a d u r c h g e k e n n z e i c h n e t that the guide blade (9) is rotatable about an axis of rotation (16), the axis of rotation (16) is substantially perpendicular to the direction of incidence (12).
Abströmleiteinrichtung nach einem der Ansprüche 1 bis 4, d a d u r c h g e k e n n z e i c h n e t, dass das Leitblatt (9) ein die Anströmkante (13) umfassendes Vorderteil (20) aufweist und ein die Abströmkante (14) umfassendes Heckteil (19) aufweist, wobei das Heckteil (19) um eine Drehachse (21) , die parallel zur Abströmkante (14) liegt, drehbar ist. Outflow guide device according to one of Claims 1 to 4, characterized in that the guide blade (9) has a front part (20) comprising the leading edge (13) and a rear part (19) comprising the outflow edge (14), the rear part (19) around an axis of rotation (21) which is parallel to the trailing edge (14) is rotatable.
6. Abströmleiteinrichtung nach einem der Ansprüche 1 bis 5, d a d u r c h g e k e n n z e i c h n e t, dass das Heckteil (19) in einer Strömungsrichtung, die von der Anströmkante (13) direkt zur Abströmkante (14) verläuft, bewegbar ist.6. Abströmleiteinrichtung according to any one of claims 1 to 5, d a d u r c h g e k e n n z e i c h n e t that the rear part (19) in a flow direction that runs from the leading edge (13) directly to the trailing edge (14) is movable.
7. Dampfturbine mit einer Abströmleiteinrichtung nach einem der Ansprüche 1 bis 6.7. Steam turbine with an outflow guide device according to one of claims 1 to 6.
8. Gasturbine mit einer Abströmleiteinrichtung nach einem der Ansprüche 1 bis 6.8. Gas turbine with an outflow guide device according to one of claims 1 to 6.
9. Turboverdichter mit einer Abströmleiteinrichtung nach einem der Ansprüche 1 bis 6.9. Turbo compressor with an outflow guide device according to one of claims 1 to 6.
10. Verfahren zur Änderung einer Abströmleiteinrichtung einer Strömungsmaschine mit einem Leitblatt (9) , das eine Anströmkante (13) und eine Abströmkante (14) aufweist zwischen denen eine Umlenkfläche (15) vorgesehen ist, die ein Strömungsmedium aus einer Einfallsrichtung (12) umlenkt, wobei die Abströmleiteinrichtung in einem Diffusor (7) eingebaut wird, wobei für die Abströmleiteinrichtung ein rotorseitiges Ende (10) und ein statorseitiges Ende (11) vorgesehen wird und das rotorseitige Ende (10) den Rotor (2) lagert, wobei ein Verlauf der Umlenkfläche (15) des Leitblattes (9) relativ zur Einfallsrichtung (12) eingestellt wird.10. A method for changing an outflow guide device of a turbomachine with a guide blade (9) which has a leading edge (13) and a trailing edge (14) between which a deflection surface (15) is provided which deflects a flow medium from an incident direction (12), wherein the outflow guide device is installed in a diffuser (7), a rotor-side end (10) and a stator-side end (11) being provided for the outflow guide device, and the end (10) on the rotor side supports the rotor (2), a course of the deflection surface (15) of the guide blade (9) being set relative to the direction of incidence (12).
11. Verfahren nach Anspruch 10, d a d u r c h g e k e n n z e i c h n e t, dass die Umlenkfläche verdreht wird.11. The method according to claim 10, d a d u r c h g e k e n n z e i c h n e t that the deflection surface is rotated.
12. Verfahren nach Anspruch 10 oder 11, d a d u r c h g e k e n n z e i c h n e t, dass eine äußere Form der Umlenkfläche (15) eingestellt wird.12. The method of claim 10 or 11, d a d u r c h g e k e n n z e i c h n e t that an outer shape of the deflection surface (15) is set.
13. Verfahren nach einem der Ansprüche 10 bis 12, d a d u r c h g e k e n n z e i c h n e t, dass das Leitblatt (9) um eine Drehachse (16) , die senkrecht zur Einfallsrichtung (12) verläuft, verdreht wird.13. The method according to any one of claims 10 to 12, so that the guide blade (9) is rotated about an axis of rotation (16) which is perpendicular to the direction of incidence (12).
14. Verfahren nach Anspruch 10, d a d u r c h g e k e n n z e i c h n e t, dass die Abstrδmkante (14) um eine Drehachse (21) parallel ver- dreht wird, die im Wesentlichen parallel zur Anström- (13) - oder Abströmkante (14) ist.14. The method as claimed in claim 10, so that the outflow edge (14) is rotated parallel about an axis of rotation (21) which is essentially parallel to the inflow (13) or outflow edge (14).
15. Verfahren nach Anspruch 10, d a d u r c h g e k e n n z e i c h n e t, dass die Abströmkante (14) in einer Strömungsrichtung, die von der Anstrδmkante (13) direkt zur Abströmkante (14) verläuft, bewegt wird. 15. The method according to claim 10, so that the trailing edge (14) is moved in a flow direction that runs from the leading edge (13) directly to the trailing edge (14).
PCT/EP2004/007252 2003-08-08 2004-07-02 Flow guide device contained in the diffuser of turbomachinery and flow diversion method WO2005019604A1 (en)

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EP04740600A EP1651842A1 (en) 2003-08-08 2004-07-02 Flow guide device contained in the diffuser of turbomachinery and flow diversion method

Applications Claiming Priority (2)

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EP03018164A EP1505263A1 (en) 2003-08-08 2003-08-08 Guiding device in a diffuser flow passage of a turbomachine and method of operation
EP03018164.8 2003-08-08

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Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7632064B2 (en) 2006-09-01 2009-12-15 United Technologies Corporation Variable geometry guide vane for a gas turbine engine
US9032721B2 (en) * 2011-12-14 2015-05-19 Siemens Energy, Inc. Gas turbine engine exhaust diffuser including circumferential vane
EP2644838A1 (en) * 2012-03-27 2013-10-02 Alstom Technology Ltd Exhaust gas housing of a gas turbine
US9422864B2 (en) * 2012-12-20 2016-08-23 General Electric Company Staggered double row, slotted airfoil design for gas turbine exhaust frame
DE102020209792A1 (en) 2020-08-04 2022-02-10 MTU Aero Engines AG vane

Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH247831A (en) * 1942-11-26 1947-03-31 Jendrassik Georg Turbine for hot work equipment.
US2934895A (en) * 1958-09-15 1960-05-03 Curtiss Wright Corp Dual cycle engine distributor construction
US2945672A (en) * 1956-10-05 1960-07-19 Marquardt Corp Gas turbine unit
US3285567A (en) * 1963-11-29 1966-11-15 Bristol Siddeley Engines Ltd Axial flow turbines and compressors
US3563669A (en) * 1969-07-10 1971-02-16 Gen Motors Corp Variable area nozzle
US4292802A (en) * 1978-12-27 1981-10-06 General Electric Company Method and apparatus for increasing compressor inlet pressure
FR2526485A1 (en) * 1982-05-07 1983-11-10 Snecma Inlet for turbomachine - has movable front section to vary pitch angle of blades on support sleeve
EP0094296A1 (en) * 1982-05-04 1983-11-16 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Device for regulating the pressure drop across at least one flux of a multiflux turbine
US4972671A (en) * 1988-05-11 1990-11-27 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Turbo-engine air intake grill
US4989406A (en) * 1988-12-29 1991-02-05 General Electric Company Turbine engine assembly with aft mounted outlet guide vanes
US5259187A (en) * 1993-02-05 1993-11-09 General Electric Company Method of operating an aircraft bypass turbofan engine having variable fan outlet guide vanes

Patent Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH247831A (en) * 1942-11-26 1947-03-31 Jendrassik Georg Turbine for hot work equipment.
US2945672A (en) * 1956-10-05 1960-07-19 Marquardt Corp Gas turbine unit
US2934895A (en) * 1958-09-15 1960-05-03 Curtiss Wright Corp Dual cycle engine distributor construction
US3285567A (en) * 1963-11-29 1966-11-15 Bristol Siddeley Engines Ltd Axial flow turbines and compressors
US3563669A (en) * 1969-07-10 1971-02-16 Gen Motors Corp Variable area nozzle
US4292802A (en) * 1978-12-27 1981-10-06 General Electric Company Method and apparatus for increasing compressor inlet pressure
EP0094296A1 (en) * 1982-05-04 1983-11-16 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Device for regulating the pressure drop across at least one flux of a multiflux turbine
FR2526485A1 (en) * 1982-05-07 1983-11-10 Snecma Inlet for turbomachine - has movable front section to vary pitch angle of blades on support sleeve
US4972671A (en) * 1988-05-11 1990-11-27 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Turbo-engine air intake grill
US4989406A (en) * 1988-12-29 1991-02-05 General Electric Company Turbine engine assembly with aft mounted outlet guide vanes
US5259187A (en) * 1993-02-05 1993-11-09 General Electric Company Method of operating an aircraft bypass turbofan engine having variable fan outlet guide vanes

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