EP2653658A1 - Guide blade assembly for an axial flow machine and method for laying the guide blade assembly - Google Patents
Guide blade assembly for an axial flow machine and method for laying the guide blade assembly Download PDFInfo
- Publication number
- EP2653658A1 EP2653658A1 EP12164299.5A EP12164299A EP2653658A1 EP 2653658 A1 EP2653658 A1 EP 2653658A1 EP 12164299 A EP12164299 A EP 12164299A EP 2653658 A1 EP2653658 A1 EP 2653658A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- axial flow
- flow machine
- vane
- blades
- guide
- 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- Withdrawn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
- 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
- F01D25/04—Antivibration arrangements
-
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
- F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
-
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/10—Anti- vibration means
-
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/16—Form or construction for counteracting blade vibration
-
- 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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
-
- 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
- F05D2230/00—Manufacture
-
- 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
- F05D2260/96—Preventing, counteracting or reducing vibration or noise
- F05D2260/961—Preventing, counteracting or reducing vibration or noise by mistuning rotor blades or stator vanes with irregular interblade spacing, airfoil shape
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49316—Impeller making
- Y10T29/4932—Turbomachine making
Definitions
- the invention relates to a vane ring for an axial flow machine, the axial flow machine and a method for laying out the vane ring.
- the steam turbine has a plurality of stages, each stage having a stator vane having a plurality of vanes and a rotor having a plurality of blades.
- the blades are mounted on the shaft of the steam turbine and rotate during operation of the steam turbine, the vanes are mounted on the housing of the steam turbine and are fixed.
- the blades can be excited to vibrate during operation of the steam turbine.
- the oscillation is characterized in that a vibration node is arranged at the blade roots of the blades. The stress caused by the vibration is high, in particular at the blade roots, so that material fatigue can occur at the blade roots, which necessitates a cost-intensive replacement of the guide blades.
- a flow channel is formed through which the steam flows during operation of the steam turbine.
- the velocity distribution of the flow downstream of the vane ring has local velocity minima in the region of the trailing edges of the guide vanes, which are referred to as trailing dents.
- the follower dents can excite the blades disposed downstream of the vane ring to vibrate.
- the invention has the object of providing a stage for an axial turbomachine, the axial turbomachine with the stage and to provide a method of laying out the step, wherein the above problems are overcome and the blades of the stage have a long life.
- Each vane is composed of the profile sections, each profile section being assigned a threading point and all profile sections having their threading points "threaded" onto a threading line. According to the invention, there is a displacement of the at least one profile section, so that the threading point of the at least one profile section no longer lies on the original threading line.
- the pitch angle is the angle between two connecting lines that extend from a common point on the axis of the axial flow machine and are perpendicular to the axis and terminate at corresponding points on the surfaces of the two adjacent vanes.
- the two corresponding points are two points that are the same radial distance from the axis of the Axialströmungsmaschine have and in each case at the same points of the guide vanes, that is, for example, a point either on the pressure side, on the suction side, on the leading edge or on the trailing edge of the respective vane, are arranged.
- the pitch angle is the nominal pitch angle 2 * II / n, with the circle number ⁇ and n of the number of vanes arranged in the vane ring.
- the blades may be exposed to two different vibrational excitation mechanisms, namely, flutter and forced-response.
- Fluttering is a self-excited vibration in which energy is transferred from the flow to the vibrations of the blades.
- the flutter is excited by small blade vibrations, which may be self-energizing, so that the blade vibrates more with each successive oscillation period. This can lead to a demolition of the blades.
- By varying the pitch angle, with two adjacent channels another flow deflection angle results, whereby the inflow from the blade ring to the blade ring is irregular over the circumference of the axial flow machine. As a result, the load on the blades changes during one revolution, whereby the flutter is advantageously reduced.
- the forced oscillation results from periodic excitation of the blades.
- a channel is respectively arranged, through which a fluid of the axial flow machine can be flowed.
- the trailing shafts assigned to the two channels have a different shape and circumferential position as a result of the changing pitch angle.
- the downstream blades submerge in the trailing shafts, whereby the blades undergo a transient flow, which leads to a vibration excitation of Can guide blades. Due to the fact that the trailing shafts are inhomogenized over the circumference, the oscillation excitation takes place unperiodically, as a result of which the forced vibrations of the rotor blades are likewise advantageously weak.
- the displacement of the at least one profile section is preferably carried out on a displacement path, which amounts to a maximum of 10% of the extent of the channel between the two guide vanes in the circumferential direction for each of the two adjacently arranged guide vanes.
- the profile cuts are preferably shifted in such a way that the guide blade is inclined against a guide blade arranged adjacent to it. In this case, the pitch angle varies linearly over the blade height.
- the profile sections are preferably displaced in such a way that at least one of two adjacently arranged guide vanes is curved.
- the pitch angle varies non-linearly over the blade height.
- the guide vanes, in which profile sections are shifted, are preferably arranged distributed symmetrically about the axis of the axial flow machine. Thus, the downstream flow from the vane ring is symmetrical.
- the blades are preferably designed such that none of the natural frequencies of the blades match the rotational frequency of the axial flow machine or a multiple of the rotational frequency up to and including eight times the rotational frequency.
- the coupling can lead to an increase in an energy input from the flow into the vibrations.
- the profile sections on a cylindrical surface or a conical surface whose axes coincide with the axis of the axial flow machine are preferably located on an S 1 flow area or in a tangential plane of the axial flow machine.
- the S 1 flow area extends in the circumferential direction and in the axial direction of the axial flow machine and describes a surface that follows an idealized flow.
- the method preferably has the step of: adapting the at least one profile section to the aerodynamic boundary conditions changed after shifting.
- the stage according to the invention is designed with the method according to the invention.
- the axial flow machine according to the invention comprises the step, in particular as the last, downstream stage of the axial flow machine.
- the blades in the last stage of the axial flow machine are the blades with the longest radial extensions in the axial flow machine and are thus particularly susceptible to vibration excitation. An unperiodic vibration excitation of the blades is thus advantageous, especially in the last stage.
- an axial flow machine 1 has a vane ring 2 and a housing 7.
- the vane ring 2 has a plurality of guide vanes 3, 4, wherein each of the guide vanes 3, 4 has a blade root 5, a blade tip 6, a pressure side 9 and a suction side 10.
- Each of the vanes 3, 4 is with its blade tip 6 on the housing and with her Blade foot 5 fixedly attached to a hub ring 8.
- a channel 14 is formed, in which a working fluid is flowable. Is shown in FIGS. 1 to 3 in each case the trailing edge of the guide vanes 3, 4.
- FIG. 3 For example, a pitch angle 13 of the axial flow machine 1 is shown.
- a surface point 15 is respectively shown on the trailing edges of the guide vanes 3, 4.
- the two surface points 15 have the same distance from the axis 11 of the axial flow machine 1
- FIG. 3 two connecting lines 16 are shown, each starting from the two surface points 15, perpendicular to the axis 11 of the axial flow machine 1 and each end at the same point on the axis 11 of the axial flow machine 1.
- the two connecting lines 16 include the pitch angle 13.
- FIGS. 1 to 3 the vane ring 2 is shown prior to a displacement of at least one profile section and after moving the at least one profile section. Shown are in the FIGS. 1 to 3 Guide vanes 3 before moving (solid lines) and vanes 4 after moving (dashed lines).
- the vanes 3 are characterized in that they have the same pitch angle 13 for each vane 3 and for each surface point 15, namely the nominal pitch angle 12.
- the nominal pitch angle 12 is 2 * ⁇ / n, where n is the number of vanes 3 in FIG the vane ring 2 and ⁇ is the circle number.
- the profile sections are shifted in such a way that the guide vanes 4 are inclined in comparison to the guide vanes 3.
- the guide vane ring 2 after shifting each have the same pairs of adjacently arranged guide vanes 4.
- the pairs are characterized in that the blade root 5 of the one vane 4 of the pair in a circumferential direction of the vane ring 2 and the blade tip 6 is displaced in the other circumferential direction, which is directed counter to a circumferential direction.
- the other vane 4 of the pair is inclined against the one vane 4 of the pair, ie the vane root 5 of the other vane 4 of the pair is displaced in the other circumferential direction and the vane tip 6 of the other vane 4 is displaced in the one circumferential direction.
- the vane ring 2 off FIG. 2 also has pairs of vanes 4.
- the vanes 4 of the pairs are curved such that the vanes 4 have a belly.
- a guide vane 4 of the pair has a belly in one circumferential direction and the other vane 4 of the pair has a belly in the other circumferential direction.
- the guide vanes 4 have a plurality of bellies, which are arranged either on the same side of the guide vanes 3 in the circumferential direction or on both sides of the guide vanes 4 in the circumferential direction.
- the pitch angle 13 varies non-linearly across the blade height.
- the vane ring 2 completely formed from the pairs and also here it is conceivable that between two pairs one or a plurality of Guide vanes 3 is arranged. It is also conceivable that alternately a curved running vane 4 and a stator blade 3 are arranged.
- every other of the vanes 3, 4 in the vane ring 2 is inclined relative to the respective vanes 3.
- the thus inclined guide vanes 4 are alternately shifted with their blade roots 5 in the one circumferential direction respectively in the other circumferential direction and with their blade tips 6 alternately in the other circumferential direction respectively in the one circumferential direction.
- the deviations of the guide vanes 4 relative to the guide vanes 3 a maximum of 10% of the available extent of the channels 14 in the circumferential direction.
- the deviations are obtained by displacing profile sections of the guide vanes 3 in the circumferential direction.
- the profile sections of the guide vanes 3 can lie on a cylinder surface or conical surface symmetrical about the axis 11, in a tangential plane of the axial flow machine 1 or on an S 1 flow surface.
- FIG. 4 a longitudinal section through the axial flow machine 1 with a main flow direction 21 and with the stage 22 according to the invention is shown.
- the step 22 includes the vane ring 2 and a blade ring 20 disposed downstream of the vane ring 2. Shown are each a vane 18 and a blade 19. Also shown is a hub 17 which rotates about the axis 11 during operation of the axial flow machine 1. The vane 18 is attached to the housing 7, the blade 19 to the hub 17.
- a flow with an inhomogeneous velocity distribution is formed downstream of the vane ring 2.
- the load of the blades 19 changes during one revolution, whereby a flutter of the blades 19 is advantageously reduced.
- the method for laying out a step 22 for an axial flow machine 1 comprising a vane ring 2 and a rotor blade 20 arranged downstream of the vane ring 2 is preferably carried out as follows:
Abstract
Description
Die Erfindung betrifft einen Leitschaufelkranz für eine Axialströmungsmaschine, die Axialströmungsmaschine und ein Verfahren zum Auslegen des Leitschaufelkranzes.The invention relates to a vane ring for an axial flow machine, the axial flow machine and a method for laying out the vane ring.
In einer Dampfturbine wird zur Erzeugung von Rotationsenergie Wasserdampf entspannt. Die Dampfturbine weist eine Mehrzahl von Stufen auf, wobei jede Stufe einen Leitschaufelkranz mit einer Mehrzahl an Leitschaufeln und einen Laufschaufelkranz mit einer Mehrzahl an Laufschaufeln aufweist. Die Laufschaufeln sind an der Welle der Dampfturbine angebracht und rotieren im Betrieb der Dampfturbine, die Leitschaufeln sind an dem Gehäuse der Dampfturbine angebracht und stehen fest. Die Schaufeln können im Betrieb der Dampfturbine zu einer Schwingung angeregt werden. Die Schwingung zeichnet sich dadurch aus, dass an den Schaufelfüßen der Schaufeln ein Schwingungsknoten angeordnet ist. Die Spannungsbelastung durch die Schwingung ist insbesondere an den Schaufelfüßen hoch, so dass es an den Schaufelfüßen zu einer Materialermüdung kommen kann, welche einen kostenintensiven Tausch der Leitschaufeln erforderlich macht.Steam is released in a steam turbine to generate rotational energy. The steam turbine has a plurality of stages, each stage having a stator vane having a plurality of vanes and a rotor having a plurality of blades. The blades are mounted on the shaft of the steam turbine and rotate during operation of the steam turbine, the vanes are mounted on the housing of the steam turbine and are fixed. The blades can be excited to vibrate during operation of the steam turbine. The oscillation is characterized in that a vibration node is arranged at the blade roots of the blades. The stress caused by the vibration is high, in particular at the blade roots, so that material fatigue can occur at the blade roots, which necessitates a cost-intensive replacement of the guide blades.
Zwischen jeweils zwei benachbart angeordneten Leitschaufeln ist ein Strömungskanal ausgebildet, durch welchen im Betrieb der Dampfturbine der Wasserdampf strömt. Die Geschwindigkeitsverteilung der Strömung stromab des Leitschaufelkranzes weist im Bereich der Hinterkanten der Leitschaufeln lokale Geschwindigkeitsminima auf, die als Nachlaufdellen bezeichnet werden. Die Nachlaufdellen können die dem Leitschaufelkranz stromab angeordneten Laufschaufeln zu der Schwingung anregen.Between each two adjacently arranged guide vanes, a flow channel is formed through which the steam flows during operation of the steam turbine. The velocity distribution of the flow downstream of the vane ring has local velocity minima in the region of the trailing edges of the guide vanes, which are referred to as trailing dents. The follower dents can excite the blades disposed downstream of the vane ring to vibrate.
Der Erfindung liegt die Aufgabe zugrunde, eine Stufe für eine Axialturbomaschine, die Axialturbomaschine mit der Stufe und ein Verfahren zum Auslegen der Stufe zu schaffen, wobei die oben genannten Probleme überwunden sind und die Laufschaufeln der Stufe eine lange Lebensdauer haben.The invention has the object of providing a stage for an axial turbomachine, the axial turbomachine with the stage and to provide a method of laying out the step, wherein the above problems are overcome and the blades of the stage have a long life.
Das erfindungsgemäße Verfahren zum Auslegen einer Stufe für eine Axialströmungsmaschine aufweisend einen Leitschaufelkranz und einen dem Leitschaufelkranz stromab angeordneten Laufschaufelkranz weist folgende Schritte auf: Profilieren eines Leitschaufelkranzes mit regelmäßig über den Umfang des Leitschaufelkranzes angeordneten Leitschaufeln gemäß aerodynamischer und mechanischer Randbedingungen; Verschieben von mindestens einem Profilschnitt von mindestens einer der Leitschaufeln in Umfangsrichtung derart, dass der Teilungswinkel für die mindestens eine Leitschaufel und einer ihr benachbart angeordneten Leitschaufel derart über die Schaufelhöhe variiert, dass im Betrieb der Axialströmungsmaschine die dem Leitschaufelkranz stromab ausgebildete Abströmung derart unregelmäßig über den Umfang der Axialströmungsmaschine ausgebildet ist, dass die Schwingungsanregung der Laufschaufeln des Laufschaufelkranzes gering ist.The method for laying out a step for an axial flow machine comprising a vane ring and a blade ring arranged downstream of the guide vane ring comprises the steps of: profiling a vane ring with regularly arranged along the circumference of the vane ring according to aerodynamic and mechanical constraints; Displacing at least one profile section of at least one of the vanes in the circumferential direction such that the pitch angle for the at least one vane and a vane adjacent thereto varies over the vane height such that during operation of the axial flow machine the outflow formed downstream of the vane ring is so irregular about the circumference is formed of the axial flow machine, that the vibration excitation of the blades of the blade ring is low.
Bei der Profilierung werden verschiedene Profilschnitte gemäß der Randbedingungen ausgelegt. Jede Leitschaufel setzt sich aus den Profilschnitten zusammen, wobei jedem Profilschnitt ein Fädelpunkt zugewiesen wird und alle Profilschnitte mit ihren Fädelpunkten auf einer Fädellinie "aufgefädelt" sind. Gemäß der Erfindung erfolgt eine Verschiebung des mindestens einen Profilschnitts, so dass der Fädelpunkt des mindestens einen Profilschnitts nicht mehr auf der ursprünglichen Fädellinie liegt.When profiling various profile sections are designed according to the boundary conditions. Each vane is composed of the profile sections, each profile section being assigned a threading point and all profile sections having their threading points "threaded" onto a threading line. According to the invention, there is a displacement of the at least one profile section, so that the threading point of the at least one profile section no longer lies on the original threading line.
Der Teilungswinkel ist der Winkel zwischen zwei Verbindungslinien, die von einem gemeinsamen Punkt auf der Achse der Axialströmungsmaschine ausgehen sowie senkrecht zu der Achse verlaufen und an entsprechenden Punkten auf den Oberflächen der beiden benachbart angeordneten Leitschaufeln enden. Bei den zwei entsprechenden Punkten handelt es sich um zwei Punkte, die den gleichen radialen Abstand von der Achse der Axialströmungsmaschine haben und jeweils an gleichen Stellen der Leitschaufeln, d.h. beispielsweise ein Punkt entweder auf der Druckseite, auf der Saugseite, auf der Vorderkante oder auf der Hinterkante der jeweiligen Leitschaufel, angeordnet sind. Bei dem Leitschaufelkranz mit regelmäßig über den Umfang angeordneten Leitschaufeln ist der Teilungswinkel der Nominalteilungswinkel 2*II/n, mit der Kreiszahl Π und n der Anzahl der in dem Leitschaufelkranz angeordneten Leitschaufeln.The pitch angle is the angle between two connecting lines that extend from a common point on the axis of the axial flow machine and are perpendicular to the axis and terminate at corresponding points on the surfaces of the two adjacent vanes. The two corresponding points are two points that are the same radial distance from the axis of the Axialströmungsmaschine have and in each case at the same points of the guide vanes, that is, for example, a point either on the pressure side, on the suction side, on the leading edge or on the trailing edge of the respective vane, are arranged. In the vane ring with regularly circumferentially arranged vanes, the pitch angle is the
Die Laufschaufeln können zwei verschiedenen Anregungsmechanismen für Schwingungen ausgesetzt sein, nämlich einem Flattern und einer erzwungenen Schwingung (englisch: "forced response"). Bei dem Flattern handelt es sich um eine selbsterregte Schwingung, bei der Energie von der Strömung in die Schwingungen der Laufschaufeln übertragen wird. Das Flattern wird durch kleine Schaufelschwingungen angeregt, die selbstverstärkend sein können, so dass die Schaufel mit jeder folgenden Schwingungsperiode stärker schwingt. Dies kann zu einem Abriss der Laufschaufeln führen. Dadurch, dass der Teilungswinkel variiert, ergibt sich bei zwei benachbart angeordneten Kanälen ein anderer Umlenkungswinkel der Strömung, wodurch sich die Zuströmung von dem Leitschaufelkranz zu dem Laufschaufelkranz unregelmäßig über den Umfang der Axialströmungsmaschine ausbildet. Dadurch ändert sich die Belastung der Laufschaufeln während einer Umdrehung, wodurch das Flattern vorteilhaft vermindert wird.The blades may be exposed to two different vibrational excitation mechanisms, namely, flutter and forced-response. Fluttering is a self-excited vibration in which energy is transferred from the flow to the vibrations of the blades. The flutter is excited by small blade vibrations, which may be self-energizing, so that the blade vibrates more with each successive oscillation period. This can lead to a demolition of the blades. By varying the pitch angle, with two adjacent channels, another flow deflection angle results, whereby the inflow from the blade ring to the blade ring is irregular over the circumference of the axial flow machine. As a result, the load on the blades changes during one revolution, whereby the flutter is advantageously reduced.
Die erzwungene Schwingung ergibt sich aufgrund einer periodischen Anregung der Laufschaufeln. Zwischen zwei benachbart angeordneten Leitschaufeln ist jeweils ein Kanal angeordnet, durch welchen ein Fluid der Axialströmungsmaschine strömbar ist. Die den beiden Kanälen zugeordneten Nachlaufdellen haben durch den sich ändernden Teilungswinkel eine unterschiedliche Form und Umfangslage. Im Betrieb der Axialströmungsmaschine tauchen die stromab angeordneten Laufschaufeln in die Nachlaufdellen ein, wodurch die Laufschaufeln eine instationäre Anströmung erfahren, die zu einer Schwingungsanregung der Laufschaufeln führen kann. Dadurch, dass die Nachlaufdellen über den Umfang inhomogenisiert sind, erfolgt die Schwingungsanregung unperiodisch, wodurch die erzwungenen Schwingungen der Laufschaufeln ebenfalls vorteilhaft schwach sind.The forced oscillation results from periodic excitation of the blades. Between two adjacently arranged guide vanes, a channel is respectively arranged, through which a fluid of the axial flow machine can be flowed. The trailing shafts assigned to the two channels have a different shape and circumferential position as a result of the changing pitch angle. During operation of the axial flow machine, the downstream blades submerge in the trailing shafts, whereby the blades undergo a transient flow, which leads to a vibration excitation of Can guide blades. Due to the fact that the trailing shafts are inhomogenized over the circumference, the oscillation excitation takes place unperiodically, as a result of which the forced vibrations of the rotor blades are likewise advantageously weak.
Das Verschieben des mindestens einen Profilschnitts erfolgt bevorzugt auf einem Verschiebeweg, der für jede der beiden benachbart angeordneten Leitschaufeln maximal 10% der Erstreckung des Kanals zwischen den beiden Leitschaufeln in Umfangsrichtung beträgt. Die Profilschnitte werden bevorzugt derart verschoben, dass die Leitschaufel gegen eine ihr benachbart angeordnete Leitschaufel geneigt wird. In diesem Fall variiert der Teilungswinkel linear über die Schaufelhöhe.The displacement of the at least one profile section is preferably carried out on a displacement path, which amounts to a maximum of 10% of the extent of the channel between the two guide vanes in the circumferential direction for each of the two adjacently arranged guide vanes. The profile cuts are preferably shifted in such a way that the guide blade is inclined against a guide blade arranged adjacent to it. In this case, the pitch angle varies linearly over the blade height.
Bevorzugtermaßen werden die Profilschnitte derart verschoben, dass mindestens eine von zwei benachbart angeordneten Leitschaufeln gekrümmt ausgeführt wird. Hier variiert der Teilungswinkel nichtlinear über die Schaufelhöhe. Die Leitschaufeln, in denen Profilschnitte verschoben sind, werden bevorzugt symmetrisch um die Achse der Axialströmungsmaschine verteilt angeordnet. Somit ist die stromabwärtige Strömung von dem Leitschaufelkranz symmetrisch.The profile sections are preferably displaced in such a way that at least one of two adjacently arranged guide vanes is curved. Here the pitch angle varies non-linearly over the blade height. The guide vanes, in which profile sections are shifted, are preferably arranged distributed symmetrically about the axis of the axial flow machine. Thus, the downstream flow from the vane ring is symmetrical.
Die Laufschaufeln werden bevorzugt derart ausgelegt, dass keine der Eigenfrequenzen der Laufschaufeln mit der Drehfrequenz der Axialströmungsmaschine oder einem Vielfachen der Drehfrequenz bis einschließlich dem Achtfachen der Drehfrequenz übereinstimmt. Somit ist vorteilhaft sichergestellt, dass es im Betrieb der Axialströmungsmaschine nicht zu einer Kopplung zwischen der Rotation der Axialströmungsmaschine und den Schwingungen der Laufschaufeln kommt. Die Kopplung kann zu einer Vergrößerung eines Energieeintrags von der Strömung in die Schwingungen führen.The blades are preferably designed such that none of the natural frequencies of the blades match the rotational frequency of the axial flow machine or a multiple of the rotational frequency up to and including eight times the rotational frequency. Thus, it is advantageously ensured that there is no coupling between the rotation of the axial flow machine and the vibrations of the rotor blades during operation of the axial flow machine. The coupling can lead to an increase in an energy input from the flow into the vibrations.
Bevorzugtermaßen liegen die Profilschnitte auf einer Zylinderfläche oder einer Kegelfläche, deren Achsen mit der Achse der Axialströmungsmaschine zusammenfallen, auf einer S1-Strö-mungsfläche oder in einer tangentialen Ebene der Axialströmungsmaschine. Die S1-Strömungsfläche erstreckt sich in Umfangsrichtung und in Axialrichtung der Axialströmungsmaschine und beschreibt eine Fläche, der eine idealisierte Strömung folgt. Das Verfahren weist bevorzugt den Schritt auf: Anpassen des mindestens einen Profilschnitts an die nach dem Verschieben geänderten aerodynamischen Randbedingungen.The profile sections on a cylindrical surface or a conical surface whose axes coincide with the axis of the axial flow machine are preferably located on an S 1 flow area or in a tangential plane of the axial flow machine. The S 1 flow area extends in the circumferential direction and in the axial direction of the axial flow machine and describes a surface that follows an idealized flow. The method preferably has the step of: adapting the at least one profile section to the aerodynamic boundary conditions changed after shifting.
Die erfindungsgemäße Stufe ist mit dem erfindungsgemäßen Verfahren ausgelegt. Die erfindungsgemäße Axialströmungsmaschine weist die Stufe auf, insbesondere als die letzte, stromab liegende Stufe der Axialströmungsmaschine. Die Laufschaufeln in der letzten Stufe der Axialströmungsmaschine sind die Laufschaufeln mit den längsten radialen Erstreckungen in der Axialströmungsmaschine und sind somit besonders anfällig für eine Schwingungsanregung. Eine unperiodische Schwingungsanregung der Laufschaufeln ist damit besonders in der letzten Stufe vorteilhaft.The stage according to the invention is designed with the method according to the invention. The axial flow machine according to the invention comprises the step, in particular as the last, downstream stage of the axial flow machine. The blades in the last stage of the axial flow machine are the blades with the longest radial extensions in the axial flow machine and are thus particularly susceptible to vibration excitation. An unperiodic vibration excitation of the blades is thus advantageous, especially in the last stage.
Im Folgenden werden bevorzugte Ausführungsformen der erfindungsgemäßen Stufe anhand der beigefügten schematischen Zeichnungen erläutert. Es zeigen
- Figuren 1 bis 3
- jeweils einen Ausschnitt einer Draufsicht einer der Ausführungsformen eines Leitschaufelkranzes einer erfindungsgemäßen Stufe und
Figur 4- einen Längsschnitt durch die erfindungsgemäße Stufe.
- FIGS. 1 to 3
- in each case a section of a plan view of one of the embodiments of a vane ring of a stage according to the invention and
- FIG. 4
- a longitudinal section through the stage according to the invention.
Wie es aus
In
In
In
Der Leitschaufelkranz 2 aus
In
In
Das Verfahren zum Auslegen einer Stufe 22 für eine Axialströmungsmaschine 1 aufweisend einen Leitschaufelkranz 2 und einen dem Leitschaufelkranz 2 stromab angeordneten Laufschaufelkranz 20 ist bevorzugt wie folgt durchzuführen: Profilieren eines Leitschaufelkranzes 2 mit regelmäßig über den Umfang des Leitschaufelkranzes 2 angeordneten Leitschaufeln 3 gemäß aerodynamischer und mechanischer Randbedingungen; Verschieben von mindestens einem Profilschnitt von mindestens einer der Leitschaufeln 3 in Umfangsrichtung derart, dass der Teilungswinkel 13 für die mindestens eine Leitschaufel 4 und einer ihr benachbart angeordneten Leitschaufel 4 derart über die Schaufelhöhe variiert, dass im Betrieb der Axialströmungsmaschine 1 die dem Leitschaufelkranz 2 stromab ausgebildete Abströmung derart unregelmäßig über den Umfang der Axialströmungsmaschine ausgebildet ist, dass die Schwingungsanregung der Laufschaufeln 19 des Laufschaufelkranzes 20 gering ist; Anpassen des mindestens einen Profilschnitts an die nach dem Verschieben geänderten aerodynamischen Randbedingungen.The method for laying out a
Obwohl die Erfindung im Detail durch die bevorzugten Ausführungsbeispiele näher illustriert und beschrieben wurde, so ist die Erfindung nicht durch die offenbarten Beispiele eingeschränkt und andere Variationen können vom Fachmann hieraus abgeleitet werden, ohne den Schutzumfang der Erfindung zu verlassen.While the invention has been further illustrated and described in detail by the preferred embodiments, the invention is not limited by the disclosed examples, and other variations can be derived therefrom by those skilled in the art without departing from the scope of the invention.
Claims (10)
wobei das Verschieben des mindestens einen Profilschnitts auf einem Verschiebeweg erfolgt, der für jede der beiden benachbart angeordneten Leitschaufeln (4) maximal 10% der Erstreckung des Kanals (14) zwischen den beiden Leitschaufeln (3) in Umfangsrichtung beträgt.Method according to claim 1,
wherein the displacement of the at least one profile section takes place on a displacement path, which is for each of the two adjacently arranged guide vanes (4) a maximum of 10% of the extent of the channel (14) between the two guide vanes (3) in the circumferential direction.
wobei die Profilschnitte derart verschoben werden, dass die Leitschaufel (4) gegen eine ihr benachbart angeordnete Leitschaufel (4) geneigt wird.Method according to one of claims 1 to 2,
wherein the profile cuts are displaced such that the guide vane (4) is inclined against a guide vane (4) arranged adjacent to it.
wobei die Profilschnitte derart verschoben werden, dass mindestens eine von zwei benachbart angeordneten Leitschaufeln (4) gekrümmt ausgeführt wird.Method according to one of claims 1 to 3,
wherein the profile cuts are shifted such that at least one of two adjacently arranged guide vanes (4) is made curved.
wobei die Leitschaufeln (4), in denen Profilschnitte verschoben sind, symmetrisch um die Achse (11) der Axialströmungsmaschine verteilt angeordnet werden.Method according to one of claims 1 to 4,
wherein the guide vanes (4), in which profile sections are displaced, are arranged symmetrically distributed about the axis (11) of the axial flow machine.
wobei die Leitschaufeln (3, 4) derart ausgelegt werden, dass keine der Eigenfrequenzen der Laufschaufeln (19) mit der Drehfrequenz der Axialströmungsmaschine (1) oder einem Vielfachen der Drehfrequenz bis einschließlich dem Achtfachen der Drehfrequenz übereinstimmt.Method according to one of claims 1 to 5,
wherein the guide vanes (3, 4) are designed such that none of the natural frequencies of the blades (19) coincides with the rotational frequency of the axial flow machine (1) or a multiple of the rotational frequency up to eight times the rotational frequency.
wobei die Profilschnitte auf einer Zylinderfläche oder einer Kegelfläche, deren Achsen mit der Achse (11) der Axialströmungsmaschine (1) zusammenfallen, auf einer S1-Strö-mungsfläche oder in einer tangentialen Ebene der Axialströmungsmaschine (1) liegen.Method according to one of claims 1 to 6,
wherein the profile cuts on a cylindrical surface or a conical surface whose axes coincide with the axis (11) of the axial flow machine (1) lie on an S 1 flow area or in a tangential plane of the axial flow machine (1).
mit dem Schritt:
with the step:
die mit einem Verfahren gemäß einem der Ansprüche 1 bis 8 ausgelegt ist.Stage for an axial flow machine (1),
which is designed with a method according to one of claims 1 to 8.
die eine Stufe (22) gemäß Anspruch 9 aufweist, insbesondere als letzte, stromab liegende Stufe der Axialströmungsmaschine (1).axial flow,
which has a step (22) according to claim 9, in particular as the last, downstream stage of the axial flow machine (1).
Priority Applications (8)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP12164299.5A EP2653658A1 (en) | 2012-04-16 | 2012-04-16 | Guide blade assembly for an axial flow machine and method for laying the guide blade assembly |
IN7604DEN2014 IN2014DN07604A (en) | 2012-04-16 | 2013-04-05 | |
JP2015506171A JP6165841B2 (en) | 2012-04-16 | 2013-04-05 | Stator blade ring and design method of stator blade ring for axial flow fluid machine |
PL13717223T PL2805017T3 (en) | 2012-04-16 | 2013-04-05 | Guide blade assembly for an axial flow machine and method for laying the guide blade assembly |
PCT/EP2013/057170 WO2013156322A1 (en) | 2012-04-16 | 2013-04-05 | Guide blade ring for an axial turbomachine and method for designing the guide blade ring |
CN201380020389.XA CN104246137B (en) | 2012-04-16 | 2013-04-05 | The rim of the guide blading for axial flow turbomachine and the method for shaping-orientation blade ring |
EP13717223.5A EP2805017B1 (en) | 2012-04-16 | 2013-04-05 | Guide blade assembly for an axial flow machine and method for laying the guide blade assembly |
US14/391,876 US9951648B2 (en) | 2012-04-16 | 2013-04-05 | Guide blade ring for an axial turbomachine and method for designing the guide blade ring |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP12164299.5A EP2653658A1 (en) | 2012-04-16 | 2012-04-16 | Guide blade assembly for an axial flow machine and method for laying the guide blade assembly |
Publications (1)
Publication Number | Publication Date |
---|---|
EP2653658A1 true EP2653658A1 (en) | 2013-10-23 |
Family
ID=48141941
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP12164299.5A Withdrawn EP2653658A1 (en) | 2012-04-16 | 2012-04-16 | Guide blade assembly for an axial flow machine and method for laying the guide blade assembly |
EP13717223.5A Not-in-force EP2805017B1 (en) | 2012-04-16 | 2013-04-05 | Guide blade assembly for an axial flow machine and method for laying the guide blade assembly |
Family Applications After (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP13717223.5A Not-in-force EP2805017B1 (en) | 2012-04-16 | 2013-04-05 | Guide blade assembly for an axial flow machine and method for laying the guide blade assembly |
Country Status (7)
Country | Link |
---|---|
US (1) | US9951648B2 (en) |
EP (2) | EP2653658A1 (en) |
JP (1) | JP6165841B2 (en) |
CN (1) | CN104246137B (en) |
IN (1) | IN2014DN07604A (en) |
PL (1) | PL2805017T3 (en) |
WO (1) | WO2013156322A1 (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2775097A3 (en) * | 2013-03-04 | 2017-06-21 | Rolls-Royce plc | Stator vane row |
Families Citing this family (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
ITTO20110728A1 (en) * | 2011-08-04 | 2013-02-05 | Avio Spa | STATIC PALLETED SEGMENT OF A GAS TURBINE FOR AERONAUTICAL MOTORS |
ITTO20120517A1 (en) * | 2012-06-14 | 2013-12-15 | Avio Spa | AERODYNAMIC PROFILE PLATE FOR A GAS TURBINE SYSTEM |
US20180094833A1 (en) * | 2016-09-30 | 2018-04-05 | Haier Us Appliance Solutions, Inc. | Water heater appliance |
GB2574493A (en) | 2019-01-22 | 2019-12-11 | Rolls Royce Plc | Stacking of rotor blade aerofoil sections to adjust resonant frequencies |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4253800A (en) * | 1978-08-12 | 1981-03-03 | Hitachi, Ltd. | Wheel or rotor with a plurality of blades |
US20020064458A1 (en) * | 2000-11-30 | 2002-05-30 | Matthew Montgomery | Frequency-mistuned light-weight turbomachinery blade rows for increased flutter stability |
US20090169371A1 (en) * | 2005-11-29 | 2009-07-02 | Ishikawajima-Harima Heavy Industries Co., Ltd. | Stator cascade of turbo type fluid machine |
US20100247310A1 (en) * | 2009-03-26 | 2010-09-30 | Frank Kelly | Intentionally mistuned integrally bladed rotor |
DE102009033618A1 (en) * | 2009-07-17 | 2011-01-20 | Mtu Aero Engines Gmbh | Method for frequency detuning of rotor body of rotor of gas turbine, involves providing rotor raw body that is made of base material |
Family Cites Families (18)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3883264A (en) * | 1971-04-08 | 1975-05-13 | Gadicherla V R Rao | Quiet fan with non-radial elements |
JPH0126068Y2 (en) | 1980-12-11 | 1989-08-03 | ||
JPH0211802U (en) | 1988-07-04 | 1990-01-25 | ||
JPH02118102U (en) | 1989-03-09 | 1990-09-21 | ||
US5167489A (en) * | 1991-04-15 | 1992-12-01 | General Electric Company | Forward swept rotor blade |
GB9210421D0 (en) | 1992-05-15 | 1992-07-01 | Gec Alsthom Ltd | Turbine blade assembly |
JP3132944B2 (en) * | 1993-03-17 | 2001-02-05 | 三菱重工業株式会社 | Three-dimensional design turbine blade |
JPH0861002A (en) | 1994-08-24 | 1996-03-05 | Mitsubishi Heavy Ind Ltd | Diaphragm of stream turbine |
JPH10184304A (en) | 1996-12-27 | 1998-07-14 | Toshiba Corp | Turbine nozzle and turbine moving blade of axial flow turbine |
JP2000045704A (en) | 1998-07-31 | 2000-02-15 | Toshiba Corp | Steam turbine |
JP2000328902A (en) * | 1999-05-19 | 2000-11-28 | Ishikawajima Harima Heavy Ind Co Ltd | Gas turbine engine |
JP4373629B2 (en) | 2001-08-31 | 2009-11-25 | 株式会社東芝 | Axial flow turbine |
JP2004100553A (en) | 2002-09-09 | 2004-04-02 | Mitsubishi Heavy Ind Ltd | Stationary blade structure of rotary machine |
CN1828024A (en) * | 2005-03-04 | 2006-09-06 | 徐大懋 | Impeller mechanical vane design method capable of improving energy conversion efficiency |
US7758306B2 (en) | 2006-12-22 | 2010-07-20 | General Electric Company | Turbine assembly for a gas turbine engine and method of manufacturing the same |
US8678752B2 (en) | 2010-10-20 | 2014-03-25 | General Electric Company | Rotary machine having non-uniform blade and vane spacing |
US20130094942A1 (en) * | 2011-10-12 | 2013-04-18 | Raymond Angus MacKay | Non-uniform variable vanes |
GB201303767D0 (en) * | 2013-03-04 | 2013-04-17 | Rolls Royce Plc | Stator Vane Row |
-
2012
- 2012-04-16 EP EP12164299.5A patent/EP2653658A1/en not_active Withdrawn
-
2013
- 2013-04-05 IN IN7604DEN2014 patent/IN2014DN07604A/en unknown
- 2013-04-05 US US14/391,876 patent/US9951648B2/en not_active Expired - Fee Related
- 2013-04-05 CN CN201380020389.XA patent/CN104246137B/en not_active Expired - Fee Related
- 2013-04-05 EP EP13717223.5A patent/EP2805017B1/en not_active Not-in-force
- 2013-04-05 JP JP2015506171A patent/JP6165841B2/en not_active Expired - Fee Related
- 2013-04-05 PL PL13717223T patent/PL2805017T3/en unknown
- 2013-04-05 WO PCT/EP2013/057170 patent/WO2013156322A1/en active Application Filing
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4253800A (en) * | 1978-08-12 | 1981-03-03 | Hitachi, Ltd. | Wheel or rotor with a plurality of blades |
US20020064458A1 (en) * | 2000-11-30 | 2002-05-30 | Matthew Montgomery | Frequency-mistuned light-weight turbomachinery blade rows for increased flutter stability |
US20090169371A1 (en) * | 2005-11-29 | 2009-07-02 | Ishikawajima-Harima Heavy Industries Co., Ltd. | Stator cascade of turbo type fluid machine |
US20100247310A1 (en) * | 2009-03-26 | 2010-09-30 | Frank Kelly | Intentionally mistuned integrally bladed rotor |
DE102009033618A1 (en) * | 2009-07-17 | 2011-01-20 | Mtu Aero Engines Gmbh | Method for frequency detuning of rotor body of rotor of gas turbine, involves providing rotor raw body that is made of base material |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2775097A3 (en) * | 2013-03-04 | 2017-06-21 | Rolls-Royce plc | Stator vane row |
Also Published As
Publication number | Publication date |
---|---|
US20150063985A1 (en) | 2015-03-05 |
CN104246137A (en) | 2014-12-24 |
IN2014DN07604A (en) | 2015-05-15 |
JP6165841B2 (en) | 2017-07-19 |
PL2805017T3 (en) | 2017-04-28 |
EP2805017B1 (en) | 2016-06-22 |
JP2015519501A (en) | 2015-07-09 |
US9951648B2 (en) | 2018-04-24 |
EP2805017A1 (en) | 2014-11-26 |
CN104246137B (en) | 2016-07-06 |
WO2013156322A1 (en) | 2013-10-24 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP2805017B1 (en) | Guide blade assembly for an axial flow machine and method for laying the guide blade assembly | |
EP2993357B1 (en) | Radial compressor stage | |
DE10359917A1 (en) | Method and device for tuning the natural frequency of turbine blades | |
WO1998044240A1 (en) | Surface structure for the wall of a flow channel or a turbine blade | |
EP2921716B1 (en) | stator blade GROUP | |
EP2725193B1 (en) | Method for detuning the blades in a gas turbine engine and corresponding gas turbine engine. | |
EP2478186B1 (en) | Rotor of a turbomachine | |
EP2921714A1 (en) | Stator blade group | |
DE102014114916A1 (en) | Turbine blade with tip rounding | |
EP3199758B1 (en) | Rotor in blisk or bling structure of an aircraft engine | |
EP2993356A1 (en) | Radial compressor stage | |
EP3404210A1 (en) | Blade cascade segment for a turbomachine with non-axisymmetric platform surface, corresponding blade cascade, blade channel, platform, and turbomachine | |
EP3428393B1 (en) | Rotor of a turbomachine | |
EP2746533A1 (en) | Blade grid and turbomachine | |
EP3064706A1 (en) | Guide blade assembly for a flow engine with axial flow | |
EP3078804A1 (en) | Shroud assembly of a row of stator or rotor blades and corresponding turbine | |
EP3388626B1 (en) | Contouring of a blade row platform | |
EP2410131B1 (en) | Rotor of a turbomachine | |
EP3420199A1 (en) | Turbine blade, associated device, turbomachine and use | |
EP2607625A1 (en) | Turbomachine and stage of turbomachine | |
DE102014203604A1 (en) | Blade row group | |
WO2011026468A2 (en) | Turbomachine, and method for producing a structured abradable coating | |
EP3498972B1 (en) | Turbine module for a turbomachine | |
WO2018069552A1 (en) | Integrally cast turbomachine assembly, and method for producing a turbomachine assembly | |
EP2884052B1 (en) | Rotor for a turbomachine having a closed flow contour ring and method for manufacturing the same |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
|
AK | Designated contracting states |
Kind code of ref document: A1 Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR |
|
AX | Request for extension of the european patent |
Extension state: BA ME |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN |
|
18D | Application deemed to be withdrawn |
Effective date: 20140424 |