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EP2805017A1 - Guide blade ring for an axial turbomachine and method for designing the guide blade ring - Google Patents

Guide blade ring for an axial turbomachine and method for designing the guide blade ring

Info

Publication number
EP2805017A1
EP2805017A1 EP13717223.5A EP13717223A EP2805017A1 EP 2805017 A1 EP2805017 A1 EP 2805017A1 EP 13717223 A EP13717223 A EP 13717223A EP 2805017 A1 EP2805017 A1 EP 2805017A1
Authority
EP
European Patent Office
Prior art keywords
guide
vane
axial flow
blades
ring
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.)
Granted
Application number
EP13717223.5A
Other languages
German (de)
French (fr)
Other versions
EP2805017B1 (en
Inventor
Christoph Hermann Richter
Heinrich STÜER
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
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 AG filed Critical Siemens AG
Priority to PL13717223T priority Critical patent/PL2805017T3/en
Priority to EP13717223.5A priority patent/EP2805017B1/en
Publication of EP2805017A1 publication Critical patent/EP2805017A1/en
Application granted granted Critical
Publication of EP2805017B1 publication Critical patent/EP2805017B1/en
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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
    • 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
    • F01D5/02—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
    • F01D5/141—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
    • F01D5/12—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 guide vane ring for an axial flow machine, the axial flow machine and a Ver ⁇ drive 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 rotor blades.
  • the blades are mounted on the shaft of the steam turbine and rota ⁇ ren in the 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.
  • Vibration is particularly high at the blade roots, so that material fatigue can occur at the blade roots, which necessitates expensive replacement of the stator blades.
  • a flow channel is formed through which the steam flows during operation of the steam turbine.
  • the VELOCITY ⁇ speed distribution of the flow downstream of the guide vane ring has in the region of the trailing edge of the vanes to local velocity minima, referred to as a tracking dents.
  • the follower dents may excite the rotor blade disposed downstream of the nozzle vane 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.
  • the inventive method for laying out a stage for axial flow rotary machine comprising a stator blade ⁇ wreath and the ring of guide vanes arranged downstream blade ring comprises the steps of: profiling a vane ring having regularly arranged over the circumference of the vane ring guide vanes according Aerody ⁇ namischer and mechanical boundary conditions; Moving at least one profile section of at least one of the Leit ⁇ blades in the circumferential direction such that the pitch angle for the at least one vane and a neighboring vane so varied on the blade height vari ⁇ iert that during operation of the axial flow downstream of the vane ring trained outflow is formed irregularly over the circumference of the axial flow from ⁇ that the vibration excitation of the blades of the blade ring is low.
  • Each guide 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.
  • the at least one profile section is displaced such that the threading point of the at least one profile section does not is more on the original threadline.
  • the pitch angle is the angle between two connection ⁇ lines emanating from a common point on the axis of the axial flow rotary machine, as well as perpendicular to the axis and terminating at corresponding points on the surfaces of the two adjacently disposed guide vanes.
  • the two corresponding points are two
  • the pitch angle is the nominal pitch angle 2 * ⁇ / ⁇ , with the circle number ⁇ and n of the number of vanes arranged in the vane ring.
  • the blades may be subject to two different excitation mechanisms for vibration, namely, flutter and forced-vibration, which is a self-excited vibration in which energy flows from the flow into the air
  • Vibrations of the blades is transmitted. Flapping is stimulated by small blade vibrations which may be ⁇ reinforcing itself, so that the blade with each fol ⁇ constricting oscillation period swings stronger. This can lead to a demolition of the blades. Because of that
  • Dividing angle varies, results in two adjacently to ⁇ ordered channels another deflection angle of the flow, whereby the inflow from the vane ring to the blade ring formed irregularly over the circumference of the Axialströ- mungsmaschine.
  • 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.
  • the oscillations ⁇ supply excitation is aperiodic, so that the forced vibrations of the blades are also advantageous weak.
  • the displacement of the at least one profile section preferably takes place on a displacement path, which amounts to a maximum of 10% of the extent of the passage between the two guide vanes in the circumferential direction for each of the two adjacently arranged guide vanes.
  • the profile sections are preferably displaced in such a way that the guide blade is inclined against a guide blade arranged adjacently to it be ⁇ . In this case, the pitch angle varies linearly over the blade height ⁇ .
  • Preferred dimensions of the profile sections are moved so that at least one of two adjacently arranged Leit ⁇ blades is performed curved.
  • Tei ⁇ development angle varies nonlinearly over the blade height.
  • the Leitschau- fine, in which profile sections are shifted, are preferably symmetrically arranged ver ⁇ divides around the axis of the axial flow.
  • 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, the axes of which coincide with the axis of the axial flow machine, are preferably located on an S i flow. mung surface or in a tangential plane of the Axialströ ⁇ tion machine.
  • the S i 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 includes the step of: ANPAS ⁇ sen of at least one profile section to the changed after Ver ⁇ push aerodynamic constraints.
  • 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 Schwingungsanre ⁇ tion of the blades is thus advantageous, especially in the last stage.
  • Figures 1 to 3 are each a detail of a plan view of one of the embodiments of a vane ring of a stage according to the invention.
  • 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.
  • Darge ⁇ represents is in Figures 1 to 3 respectively the trailing edge of the vanes 3, 4th
  • a pitch angle 13 of the axial ⁇ flow machine 1 is shown by way of example.
  • a surface is represented in each dot 15 on the trailing edges of the vanes 3 4.
  • the two surface points 15 have here the moving ⁇ chen distance from the axis 11 of the axial flow rotary machine 1.
  • two connecting lines 16 in figure arising respectively from the two surface points 15, perpendicular to the axis 11 of the axial flow rotary machine 1 extend 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.
  • Figures 1 to 3 of 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.
  • Ge ⁇ shows are in the figures 1 to 3 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.
  • Nominal pitch angle 12 is 2 * ⁇ / ⁇ , where n is the number of vanes 3 in 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 show ⁇ fel tip 6 is displaced in the other circumferential direction, which is directed against a circumferential direction.
  • the other guide blade 4 of the pair is opposite to said one guide blade 4 of the pair of inclined, that is, the blade root 5 of the other routing ⁇ blade 4 of the pair is ver ⁇ pushed in the other circumferential direction and the blade tip 6 of the other guide vane 4 is displaced in the circumferential direction ,
  • the thus-arranged vanes 4 result in a linear variation of the pitch angle 13 over the blade height, ie in Depending ⁇ ness of the radial distance in Figure 1 of the guide vane ring 2 is completely formed by the same pairs of the axis 11 of Axialströ ⁇ mung machine 1. It is also conceivable that the vane ring 2 is formed alternately by the pairs and the guide vanes 3 without shifted profile ⁇ sections . In this case, between each pair a vane 3 or a plurality of Leitschau ⁇ blades 3 can be provided, wherein the disturbance of the aeroelastic coupling is more effective if only one vane 3 is provided.
  • the vane ring 2 of Figure 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 Leitschau- fine 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 ⁇ wreath 2 is formed entirely from the pairs and also here is conceivable that between two pairs one or a plurality of Guide vanes 3 is arranged. It is also conceivable that a curved running guide vane 4 and a vane 3 are arranged alternately from ⁇ . In Figure 3, every other one of the vanes 3, 4 is in the
  • Vane ring 2 inclined relative to the corresponding vanes 3.
  • the guide vanes 4, which are inclined in such a way, are alternately shifted with their blade roots 5 alternately in the one circumferential direction or in the other circumferential direction and with their blade tips 6 in the other circumferential direction or in the one circumferential direction.
  • the deviations of the guide vanes 4 relative to the guide vanes 3 amount to 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 i flow surface.
  • 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 guide blade 18 is attached to the housing 7, while the moving blade 19 is attached to the hub 17. During operation of the axial flow machine 1, a flow with an inhomogeneous velocity distribution is formed downstream of the vane ring 2. As a result, the load on the rotor blade 19 changes during one revolution, which advantageously reduces chattering of the rotor blade 19.
  • the method for laying out a step 22 for an axial flow machine 1 comprising a guide vane ring 2 and a rotor ring 20 arranged downstream of the guide vane ring 2 is preferably carried out as follows:

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

The invention relates to a method for designing a stage (22) for an axial turbomachine (1) having a guide blade ring (2) and a rotor blade ring (20) arranged downstream of the guide blade ring (2) having the following steps: profiling a guide blade ring (2) having guide blades (3) arranged regularly over the circumference of the guide blade ring (2) in accordance with basic aerodynamic and mechanical conditions; moving at least one profile section of at least one of the guide blades (3) in the circumferential direction in such a way that the pitch angle (13) for the at least one guide blade (4) and a guide blade (4) arranged adjacent thereto varies over the blade height in such a way that during operation of the axial turbomachine (1) the departing flow formed downstream of the guide blade ring (2) is irregularly formed over the circumference of the axial turbomachine, such that the vibration excitation of the rotor blades (19) of the rotor blade ring (20) is low.

Description

Beschreibung description
Leitschaufelkranz für eine Axialströmungsmaschine und Guide vane for an axial flow machine and
Verfahren zum Auslegen des Leitschaufelkranzes Method for laying out the vane ring
Die Erfindung betrifft einen Leitschaufelkranz für eine Axialströmungsmaschine, die Axialströmungsmaschine und ein Ver¬ fahren zum Auslegen des Leitschaufelkranzes. The invention relates to a guide vane ring for an axial flow machine, the axial flow machine and a Ver ¬ drive 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 Laufschaufein aufweist. Die Laufschaufeln sind an der Welle der Dampfturbine angebracht und rotie¬ ren 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 Schwin- gung angeregt werden. Die Schwingung zeichnet sich dadurch aus, dass an den Schaufelfüßen der Schaufeln ein Schwingungsknoten angeordnet ist. Die Spannungsbelastung durch die 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 rotor blades. The blades are mounted on the shaft of the steam turbine and rota ¬ ren in the 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 load by the
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. Vibration is particularly high at the blade roots, so that material fatigue can occur at the blade roots, which necessitates expensive replacement of the stator blades.
Zwischen jeweils zwei benachbart angeordneten Leitschaufeln ist ein Strömungskanal ausgebildet, durch welchen im Betrieb der Dampfturbine der Wasserdampf strömt. Die Geschwindig¬ keitsverteilung 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 Laufschaufein 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 ¬ speed distribution of the flow downstream of the guide vane ring has in the region of the trailing edge of the vanes to local velocity minima, referred to as a tracking dents. The follower dents may excite the rotor blade disposed downstream of the nozzle vane 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. Das erfindungsgemäße Verfahren zum Auslegen einer Stufe für eine Axialströmungsmaschine aufweisend einen Leitschaufel¬ kranz und einen dem Leitschaufelkranz stromab angeordneten Laufschaufelkranz weist folgende Schritte auf: Profilieren eines Leitschaufelkranzes mit regelmäßig über den Umfang des Leitschaufelkranzes angeordneten Leitschaufeln gemäß aerody¬ namischer und mechanischer Randbedingungen; Verschieben von mindestens einem Profilschnitt von mindestens einer der Leit¬ schaufeln in Umfangsrichtung derart, dass der Teilungswinkel für die mindestens eine Leitschaufel und einer ihr benachbart angeordneten Leitschaufel derart über die Schaufelhöhe vari¬ iert, dass im Betrieb der Axialströmungsmaschine die dem Leitschaufelkranz stromab ausgebildete Abströmung derart unregelmäßig über den Umfang der Axialströmungsmaschine aus¬ gebildet ist, dass die Schwingungsanregung der Laufschaufeln des Laufschaufelkranzes gering ist. 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. The inventive method for laying out a stage for axial flow rotary machine comprising a stator blade ¬ wreath and the ring of guide vanes arranged downstream blade ring comprises the steps of: profiling a vane ring having regularly arranged over the circumference of the vane ring guide vanes according Aerody ¬ namischer and mechanical boundary conditions; Moving at least one profile section of at least one of the Leit ¬ blades in the circumferential direction such that the pitch angle for the at least one vane and a neighboring vane so varied on the blade height vari ¬ iert that during operation of the axial flow downstream of the vane ring trained outflow is formed irregularly over the circumference of the axial flow from ¬ 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 Fädel- linie liegt. When profiling various profile sections are designed according to the boundary conditions. Each guide 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, the at least one profile section is displaced such that the threading point of the at least one profile section does not is more on the original threadline.
Der Teilungswinkel ist der Winkel zwischen zwei Verbindungs¬ linien, 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 The pitch angle is the angle between two connection ¬ lines emanating from a common point on the axis of the axial flow rotary machine, as well as perpendicular to the axis and terminating at corresponding points on the surfaces of the two adjacently disposed guide vanes. The two corresponding points are two
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*Π/η, mit der Kreiszahl Π und n der Anzahl der in dem Leitschaufelkranz angeordneten Leitschaufeln . 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 nominal pitch angle 2 * Π / η, with the circle number Π and n of the number of vanes arranged in the vane ring.
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 selbster- regte Schwingung, bei der Energie von der Strömung in dieThe blades may be subject to two different excitation mechanisms for vibration, namely, flutter and forced-vibration, which is a self-excited vibration in which energy flows from the flow into the air
Schwingungen der Laufschaufeln übertragen wird. Das Flattern wird durch kleine Schaufelschwingungen angeregt, die selbst¬ verstärkend sein können, so dass die Schaufel mit jeder fol¬ genden Schwingungsperiode stärker schwingt. Dies kann zu einem Abriss der Laufschaufeln führen. Dadurch, dass derVibrations of the blades is transmitted. Flapping is stimulated by small blade vibrations which may be ¬ reinforcing itself, so that the blade with each fol ¬ constricting oscillation period swings stronger. This can lead to a demolition of the blades. Because of that
Teilungswinkel variiert, ergibt sich bei zwei benachbart an¬ geordneten Kanälen ein anderer Umlenkungswinkel der Strömung, wodurch sich die Zuströmung von dem Leitschaufelkranz zu dem Laufschaufelkranz unregelmäßig über den Umfang der Axialströ- mungsmaschine ausbildet. Dadurch ändert sich die Belastung der Laufschaufeln während einer Umdrehung, wodurch das Flattern vorteilhaft vermindert wird. Dividing angle varies, results in two adjacently to ¬ ordered channels another deflection angle of the flow, whereby the inflow from the vane ring to the blade ring formed irregularly over the circumference of the Axialströ- mungsmaschine. 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 periodi- sehen 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 Schwin¬ gungsanregung 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. Characterized in that the trailing dents are inhomogenisiert over the circumference, the oscillations ¬ supply excitation is aperiodic, so that the forced vibrations of the blades are also advantageous weak.
Das Verschieben des mindestens einen Profilschnitts erfolgt bevorzugt auf einem Verschiebeweg, der für jede der beiden benachbart angeordneten Leitschaufeln maximal 10% der Erstre- ckung des Kanals zwischen den beiden Leitschaufeln in Um- fangsrichtung beträgt. Die Profilschnitte werden bevorzugt derart verschoben, dass die Leitschaufel gegen eine ihr be¬ nachbart angeordnete Leitschaufel geneigt wird. In diesem Fall variiert der Teilungswinkel linear über die Schaufel¬ höhe . The displacement of the at least one profile section preferably takes place on a displacement path, which amounts to a maximum of 10% of the extent of the passage between the two guide vanes in the circumferential direction for each of the two adjacently arranged guide vanes. The profile sections are preferably displaced in such a way that the guide blade is inclined against a guide blade arranged adjacently to it be ¬ . 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 Leit¬ schaufeln gekrümmt ausgeführt wird. Hier variiert der Tei¬ lungswinkel nichtlinear über die Schaufelhöhe. Die Leitschau- fein, in denen Profilschnitte verschoben sind, werden bevorzugt symmetrisch um die Achse der Axialströmungsmaschine ver¬ teilt angeordnet. Somit ist die stromabwärtige Strömung von dem Leitschaufelkranz symmetrisch. 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. Preferred dimensions of the profile sections are moved so that at least one of two adjacently arranged Leit ¬ blades is performed curved. Here Tei ¬ development angle varies nonlinearly over the blade height. The Leitschau- fine, in which profile sections are shifted, are preferably symmetrically arranged ver ¬ divides around the axis of the axial flow. 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. 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 S i-Strö- mungsfläche oder in einer tangentialen Ebene der Axialströ¬ mungsmaschine. Die S i-Strömungsflache erstreckt sich in Um- fangsrichtung und in Axialrichtung der Axialströmungsmaschine und beschreibt eine Fläche, der eine idealisierte Strömung folgt. Das Verfahren weist bevorzugt den Schritt auf: Anpas¬ sen des mindestens einen Profilschnitts an die nach dem Ver¬ schieben geänderten aerodynamischen Randbedingungen. The profile sections on a cylindrical surface or a conical surface, the axes of which coincide with the axis of the axial flow machine, are preferably located on an S i flow. mung surface or in a tangential plane of the Axialströ ¬ tion machine. The S i 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 includes the step of: ANPAS ¬ sen of at least one profile section to the changed after Ver ¬ push aerodynamic constraints.
Die erfindungsgemäße Stufe ist mit dem erfindungsgemäßen Ver- fahren 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 Schwingungsanre¬ gung der Laufschaufeln ist damit besonders in der letzten Stufe vorteilhaft. Im Folgenden werden bevorzugte Ausführungsformen der erfindungsgemäßen Stufe anhand der beigefügten schematischen 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 Schwingungsanre ¬ tion of the blades is thus advantageous, especially in the last stage. In the following, preferred embodiments of the stage according to the invention with reference to the accompanying schematic
Zeichnungen erläutert. Es zeigen Drawings explained. Show it
Figuren 1 bis 3 jeweils einen Ausschnitt einer Draufsicht einer der Ausführungsformen eines Leitschaufelkranzes einer erfindungsgemäßen Stufe und Figures 1 to 3 are each a detail of a plan view of one of the embodiments of a vane ring of a stage according to the invention and
Figur 4 einen Längsschnitt durch die erfindungs- gemäße Stufe. 4 shows a longitudinal section through the inventive step.
Wie es aus Figuren 1 bis 3 ersichtlich ist, weist eine Axial¬ strömungsmaschine 1 einen Leitschaufelkranz 2 und ein Gehäuse 7 auf. Der Leitschaufelkranz 2 weist eine Mehrzahl an Leit- schaufeln 3, 4 auf, wobei jede der Leitschaufeln 3, 4 einen Schaufelfuß 5, eine Schaufelspitze 6, eine Druckseite 9 und eine Saugseite 10 aufweist. Jede der Leitschaufeln 3, 4 ist mit ihrer Schaufelspitze 6 an dem Gehäuse und mit ihrem Schaufelfuß 5 an einem Nabenring 8 fest angebracht. Zwischen zwei benachbart angeordneten Leitschaufeln 3, 4 ist ein Kanal 14 ausgebildet, in dem ein Arbeitsfluid strömbar ist. Darge¬ stellt ist in Figuren 1 bis 3 jeweils die Hinterkante der Leitschaufeln 3, 4. As is apparent from Figures 1 to 3, a ¬ Axial-flow machine 1 to a guide 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. Between two adjacently arranged guide vanes 3, 4, a channel 14 is formed, in which a working fluid is flowable. Darge ¬ represents is in Figures 1 to 3 respectively the trailing edge of the vanes 3, 4th
In Figur 3 ist beispielhaft ein Teilungswinkel 13 der Axial¬ strömungsmaschine 1 dargestellt. An den beiden benachbart an¬ geordneten Leitschaufeln 3, 4 ist jeweils ein Oberflächen- punkt 15 auf den Hinterkanten der Leitschaufeln 3, 4 dargestellt. Die beiden Oberflächenpunkte 15 haben dabei den glei¬ chen Abstand zu der Achse 11 der Axialströmungsmaschine 1. Ebenso sind in Figur 3 zwei Verbindungslinien 16 gezeigt, die jeweils von den beiden Oberflächenpunkten 15 ausgehen, senk- recht zu der Achse 11 der Axialströmungsmaschine 1 verlaufen und jeweils auf demselben Punkt auf der Achse 11 der Axial¬ strömungsmaschine 1 enden. Die beiden Verbindungslinien 16 schließen den Teilungswinkel 13 ein. In Figuren 1 bis 3 ist der Leitschaufelkranz 2 vor einem Verschieben von mindestens einem Profilschnitt und nach dem Verschieben des mindestens einen Profilschnitts dargestellt. Ge¬ zeigt sind in den Figuren 1 bis 3 Leitschaufeln 3 vor dem Verschieben (durchgezogene Linien) und Leitschaufeln 4 nach dem Verschieben (gestrichelte Linien) . Die Leitschaufeln 3 zeichnen sich dadurch aus, dass sie für jede Leitschaufel 3 und für jeden Oberflächenpunkt 15 den gleichen Teilungswinkel 13 aufweisen, nämlich den Nominalteilungswinkel 12. Der Nomi- nalteilungswinkel 12 ergibt sich zu 2*Π/η, wobei n die Anzahl der Leitschaufeln 3 in dem Leitschaufelkranz 2 und Π die Kreiszahl ist. In Figure 3, a pitch angle 13 of the axial ¬ flow machine 1 is shown by way of example. At the two adjacent guide vanes at ¬ parent 3, 4, a surface is represented in each dot 15 on the trailing edges of the vanes 3 4. The two surface points 15 have here the moving ¬ chen distance from the axis 11 of the axial flow rotary machine 1. Likewise 3 are shown two connecting lines 16 in figure arising respectively from the two surface points 15, perpendicular to the axis 11 of the axial flow rotary machine 1 extend 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. In Figures 1 to 3 of 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. Ge ¬ shows are in the figures 1 to 3 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. Nominal pitch angle 12 is 2 * Π / η, where n is the number of vanes 3 in the vane ring 2 and Π is the circle number.
In Figur 1 sind die Profilschnitte derart verschoben, dass die Leitschaufeln 4 im Vergleich zu den Leitschaufeln 3 ge- neigt sind. Dabei weist der Leitschaufelkranz 2 nach dem Verschieben jeweils gleiche Paare von benachbart angeordneten Leitschaufeln 4 auf. Die Paare zeichnen sich dadurch aus, dass der Schaufelfuß 5 der einen Leitschaufel 4 des Paars in eine Umfangsrichtung des Leitschaufelkranzes 2 und die Schau¬ felspitze 6 in die andere Umfangsrichtung verschoben ist, die der einen Umfangsrichtung entgegen gerichtet ist. Die andere Leitschaufel 4 des Paars wird entgegen der einen Leitschaufel 4 des Paars geneigt, d.h. der Schaufelfuß 5 der anderen Leit¬ schaufel 4 des Paars wird in die andere Umfangsrichtung ver¬ schoben und die Schaufelspitze 6 der anderen Leitschaufel 4 wird in die eine Umfangsrichtung verschoben. Die so angeordneten Leitschaufeln 4 führen zu einer linearen Variation des Teilungswinkels 13 über die Schaufelhöhe, d.h. in Abhängig¬ keit des radialen Abstands von der Achse 11 der Axialströ¬ mungsmaschine 1. In Figur 1 ist der Leitschaufelkranz 2 vollständig durch die gleichen Paare gebildet. Es ist ebenso denkbar, dass der Leitschaufelkranz 2 abwechselnd von den Paaren und von den Leitschaufeln 3 ohne verschobene Profil¬ schnitte gebildet ist. Dabei können jeweils zwischen zwei Paaren eine Leitschaufel 3 oder eine Mehrzahl an Leitschau¬ feln 3 vorgesehen werden, wobei die Störung der aeroelasti- schen Kopplung effektiver ist, wenn nur eine Leitschaufel 3 vorgesehen wird. In FIG. 1, the profile sections are shifted in such a way that the guide vanes 4 are inclined in comparison to the guide vanes 3. In this case, 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 show ¬ fel tip 6 is displaced in the other circumferential direction, which is directed against a circumferential direction. The other guide blade 4 of the pair is opposite to said one guide blade 4 of the pair of inclined, that is, the blade root 5 of the other routing ¬ blade 4 of the pair is ver ¬ pushed in the other circumferential direction and the blade tip 6 of the other guide vane 4 is displaced in the circumferential direction , The thus-arranged vanes 4 result in a linear variation of the pitch angle 13 over the blade height, ie in Depending ¬ ness of the radial distance in Figure 1 of the guide vane ring 2 is completely formed by the same pairs of the axis 11 of Axialströ ¬ mung machine 1. It is also conceivable that the vane ring 2 is formed alternately by the pairs and the guide vanes 3 without shifted profile ¬ sections . In this case, between each pair a vane 3 or a plurality of Leitschau ¬ blades 3 can be provided, wherein the disturbance of the aeroelastic coupling is more effective if only one vane 3 is provided.
Der Leitschaufelkranz 2 aus Figur 2 weist ebenfalls Paare von Leitschaufeln 4 auf. Die Leitschaufeln 4 der Paare sind derart gekrümmt, dass die Leitschaufeln 4 einen Bauch aufweisen. Dabei weist eine Leitschaufel 4 des Paars einen Bauch in die eine Umfangsrichtung und die andere Leitschaufel 4 des Paars einen Bauch in die andere Umfangsrichtung auf. Es ist ebenso denkbar, dass die Leitschaufeln 4 eine Mehrzahl an Bäuchen aufweisen, die entweder auf der gleichen Seite der Leitschau- fein 3 in Umfangsrichtung oder auf beiden Seiten der Leitschaufeln 4 in Umfangsrichtung angeordnet sind. Weiterhin ist es möglich, die Form des Bauches von Leitschaufel 4 zu Leit¬ schaufel 4 zu variieren, um die aerolastische Kopplung besonders effektiv zu stören. Indem die Leitschaufeln 4 gekrümmt ausgeführt sind, variiert der Teilungswinkel 13 nichtlinear über die Schaufelhöhe. Auch in Figur 2 ist der Leitschaufel¬ kranz 2 vollständig aus den Paaren gebildet und auch hier ist denkbar, dass zwischen zwei Paare eine oder eine Mehrzahl an Leitschaufeln 3 angeordnet ist. Ebenso ist denkbar, dass ab¬ wechselnd eine gekrümmt ausgeführte Leitschaufel 4 und eine Leitschaufel 3 angeordnet sind. In Figur 3 ist jede zweite der Leitschaufeln 3, 4 in demThe vane ring 2 of Figure 2 also has pairs of vanes 4. The vanes 4 of the pairs are curved such that the vanes 4 have a belly. In this case, 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. It is also conceivable that the guide vanes 4 have a plurality of bellies, which are arranged either on the same side of the Leitschau- fine 3 in the circumferential direction or on both sides of the guide vanes 4 in the circumferential direction. Furthermore, it is possible to vary the shape of the belly of the guide vane 4 to Leit ¬ blade 4 to disturb the aerolastic coupling particularly effective. By making the vanes 4 curved, the pitch angle 13 varies non-linearly across the blade height. Also in Figure 2, the vane ¬ wreath 2 is formed entirely from the pairs and also here is conceivable that between two pairs one or a plurality of Guide vanes 3 is arranged. It is also conceivable that a curved running guide vane 4 and a vane 3 are arranged alternately from ¬. In Figure 3, every other one of the vanes 3, 4 is in the
Leitschaufelkranz 2 im Vergleich zu den entsprechenden Leitschaufeln 3 geneigt. Die derart geneigten Leitschaufeln 4 sind mit ihren Schaufelfüßen 5 abwechselnd in die eine Um- fangsrichtung respektive in die andere Umfangsrichtung und mit ihren Schaufelspitzen 6 abwechselnd in die andere Um- fangsrichtung respektive in die eine Umfangsrichtung verschoben. In den Figuren 1 bis 3 betragen die Abweichungen der Leitschaufeln 4 gegenüber den Leitschaufeln 3 maximal 10% der verfügbaren Erstreckung der Kanäle 14 in Umfangsrichtung . Die Abweichungen werden erhalten, in dem Profilschnitte der Leitschaufeln 3 in Umfangsrichtung verschoben werden. Die Profilschnitte der Leitschaufeln 3 können dabei auf einer um die Achse 11 symmetrischen Zylinderfläche oder Kegelfläche, in einer tangentialen Ebene der Axialströmungsmaschine 1 oder auf einer S i-Strömungsfläche liegen. Vane ring 2 inclined relative to the corresponding vanes 3. The guide vanes 4, which are inclined in such a way, are alternately shifted with their blade roots 5 alternately in the one circumferential direction or in the other circumferential direction and with their blade tips 6 in the other circumferential direction or in the one circumferential direction. In FIGS. 1 to 3, the deviations of the guide vanes 4 relative to the guide vanes 3 amount to 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 i flow surface.
In Figur 4 ist ein Längsschnitt durch die Axialströmungs¬ maschine 1 mit einer Hauptströmungsrichtung 21 und mit der erfindungsgemäßen Stufe 22 dargestellt. Die Stufe 22 weist den Leitschaufelkranz 2 und einen stromab von dem Leitschaufelkranz 2 angeordneten Laufschaufelkranz 20 auf. Gezeigt sind jeweils eine Leitschaufel 18 und eine Laufschaufel 19. Ebenfalls dargestellt ist eine Nabe 17, die sich im Betrieb der Axialströmungsmaschine 1 um die Achse 11 dreht. Die Leit- schaufei 18 ist an dem Gehäuse 7, die Laufschaufel 19 an der Nabe 17 angebracht. Im Betrieb der Axialströmungsmaschine 1 bildet sich stromab des Leitschaufelkranzes 2 eine Strömung mit einer inhomogenen Geschwindigkeitsverteilung aus. Dadurch ändert sich die Belastung der Laufschaufein 19 während einer Umdrehung, wodurch ein Flattern der Laufschaufein 19 vorteilhaft vermindert wird. 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: Profilie- ren eines Leitschaufelkranzes 2 mit regelmäßig über den Um¬ fang 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 Axialströ¬ mungsmaschine 1 die dem Leitschaufelkranz 2 stromab ausgebil¬ dete Abströmung derart unregelmäßig über den Umfang der Axi- alströmungsmaschine ausgebildet ist, dass die Schwingungsan¬ regung der Laufschaufeln 19 des Laufschaufelkranzes 20 gering ist; Anpassen des mindestens einen Profilschnitts an die nach dem Verschieben geänderten aerodynamischen Randbedingungen. 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. 4 shows a longitudinal section through the axial flow ¬ machine 1 with a main flow direction 21, and with the inventive step 22 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 guide blade 18 is attached to the housing 7, while the moving blade 19 is attached to the hub 17. During operation of the axial flow machine 1, a flow with an inhomogeneous velocity distribution is formed downstream of the vane ring 2. As a result, the load on the rotor blade 19 changes during one revolution, which advantageously reduces chattering of the rotor blade 19. The method for laying out a step 22 for an axial flow machine 1 comprising a guide vane ring 2 and a rotor ring 20 arranged downstream of the guide vane ring 2 is preferably carried out as follows: Profiling a guide vane ring 2 with guide vanes 3 arranged regularly over the circumference of the guide vane ring 2 aerodynamic and mechanical boundary conditions; Shifting at least one profile section of at least one of the vanes 3 in the circumferential direction such that the pitch angle 13 for the at least one guide vane 4 and a her arranged adjacent guide blade 4 in such a manner varies over the blade height, that in operation the Axialströ ¬ mung machine 1, the guide vane ring 2 is such irregularly formed downstream ausgebil ¬ end to outflow over the circumference of the AXI alströmungsmaschine that the Schwingungsan ¬ excitation of the blades 19 of the rotor blade ring 20 is low; Adapting the at least one profile section to the changed aerodynamic boundary conditions after shifting. 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

Patentansprüche claims
1. Verfahren zum Auslegen einer Stufe (22) für eine Axialströmungsmaschine (1) aufweisend einen Leitschaufelkranz (2) und einen dem Leitschaufelkranz (2) stromab angeordneten Laufschaufelkranz (20), mit den Schritten: A method of laying out a step (22) for an axial flow machine (1) comprising a vane ring (2) and a vane ring (20) arranged downstream of the vane ring (2), comprising the steps of:
- Profilieren eines Leitschaufelkranzes (2) mit regelmäßig über den Umfang des Leitschaufelkranzes (2) angeordneten Leitschaufeln (3) gemäß aerodynamischer und mechanischer Randbedingungen ;  - Profiling a vane ring (2) with regularly over the circumference of the vane ring (2) arranged vanes (3) according to aerodynamic and mechanical boundary conditions;
- 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 Lauf¬ schaufeln (19) des Laufschaufelkranzes (20) gering ist. - Moving at least one profile section of at least one of the guide vanes (3) in the circumferential direction such that the pitch angle (13) for the at least one vane (4) and a guide vane (4) arranged adjacent thereto varies over the blade height such that in operation the axial flow machine (1) downstream of the guide vane ring (2) formed outflow so irregularly over the circumference of the axial flow machine, that the vibration excitation of the running ¬ blades (19) of the blade ring (20) is low.
2. Verfahren gemäß Anspruch 1, 2. Method according to claim 1,
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.  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.
3. Verfahren gemäß einem der Ansprüche 1 bis 2, 3. The method according to any one of claims 1 to 2,
wobei die Profilschnitte derart verschoben werden, dass die Leitschaufel (4) gegen eine ihr benachbart angeordnete Leitschaufel (4) geneigt wird.  wherein the profile cuts are displaced such that the guide vane (4) is inclined against a guide vane (4) arranged adjacent to it.
4. Verfahren gemäß einem der Ansprüche 1 bis 3, 4. The method according to any one of claims 1 to 3,
wobei die Profilschnitte derart verschoben werden, dass mindestens eine von zwei benachbart angeordneten Leitschau¬ feln (4) gekrümmt ausgeführt wird. wherein the profile sections are shifted in such a way that at least one of two adjacently arranged Leitschau ¬ blades (4) is executed curved.
5. Verfahren gemäß einem der Ansprüche 1 bis 4, wobei die Leitschaufeln (4), in denen Profilschnitte verschoben sind, symmetrisch um die Achse (11) der Axialströ- mungsmaschine verteilt angeordnet werden. 5. The method according to any one of claims 1 to 4, wherein the guide vanes (4), in which profile sections are shifted, symmetrically distributed around the axis (11) of the Axialströ- mungsmaschine be arranged.
6. Verfahren gemäß einem der Ansprüche 1 bis 5, 6. The method according to any one of claims 1 to 5,
wobei die Leitschaufeln (3, 4) derart ausgelegt werden, dass keine der Eigenfrequenzen der Laufschaufeln (19) mit der Drehfrequenz der Axialströmungsmaschine (1) oder einem wherein the guide vanes (3, 4) are designed such that none of the natural frequencies of the blades (19) with the rotational frequency of the axial flow machine (1) or a
Vielfachen der Drehfrequenz bis einschließlich dem Achtfachen der Drehfrequenz übereinstimmt. Multiples of the rotational frequency up to and including eight times the rotational frequency coincides.
7. Verfahren gemäß einem der Ansprüche 1 bis 6, 7. The method according to any one of claims 1 to 6,
wobei die Profilschnitte auf einer Zylinderfläche oder einer Kegelfläche, deren Achsen mit der Achse (11) der Axi¬ alströmungsmaschine (1) zusammenfallen, auf einer S i-Strö- mungsfläche oder in einer tangentialen Ebene der Axialströ¬ mungsmaschine (1) liegen. the profile sections coincide on a cylindrical surface or a conical surface, the axes with the axis (11) of the Axi ¬ alströmungsmaschine (1), on a S i-flow-surface or lie in a tangential plane of the Axialströ ¬ mung machine (1).
8. Verfahren gemäß einem der Ansprüche 1 bis 7, 8. The method according to any one of claims 1 to 7,
mit dem Schritt:  with the step:
- Anpassen des mindestens einen Profilschnitts an die nach dem Verschieben geänderten aerodynamischen Randbedingungen.  - Adapting the at least one profile section to the changed after moving aerodynamic boundary conditions.
9. Stufe für eine Axialströmungsmaschine (1), 9th stage for an axial flow machine (1),
die mit einem Verfahren gemäß einem der Ansprüche 1 bis 8 ausgelegt ist.  which is designed with a method according to one of claims 1 to 8.
10. Axialströmungsmaschine, 10. axial flow machine,
die eine Stufe (22) gemäß Anspruch 9 aufweist, insbesondere als letzte, stromab liegende Stufe der Axialströmungs¬ maschine ( 1 ) . having a step (22) according to claim 9, in particular as the last, downstream stage of the Axialströmungs ¬ machine (1).
EP13717223.5A 2012-04-16 2013-04-05 Guide blade assembly for an axial flow machine and method for laying the guide blade assembly Not-in-force EP2805017B1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
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
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

Applications Claiming Priority (3)

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
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
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

Publications (2)

Publication Number Publication Date
EP2805017A1 true EP2805017A1 (en) 2014-11-26
EP2805017B1 EP2805017B1 (en) 2016-06-22

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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

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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)

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Also Published As

Publication number Publication date
PL2805017T3 (en) 2017-04-28
US20150063985A1 (en) 2015-03-05
IN2014DN07604A (en) 2015-05-15
JP6165841B2 (en) 2017-07-19
CN104246137A (en) 2014-12-24
JP2015519501A (en) 2015-07-09
EP2653658A1 (en) 2013-10-23
US9951648B2 (en) 2018-04-24
CN104246137B (en) 2016-07-06
EP2805017B1 (en) 2016-06-22
WO2013156322A1 (en) 2013-10-24

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