EP1589191B1 - Verfahren zum Einstellen gezielter unterschiedlicher Eigenfrequenzen eines beschaufelten Rotors einer Turbomachine sowie Rotor - Google Patents

Verfahren zum Einstellen gezielter unterschiedlicher Eigenfrequenzen eines beschaufelten Rotors einer Turbomachine sowie Rotor Download PDF

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EP1589191B1
EP1589191B1 EP05103148A EP05103148A EP1589191B1 EP 1589191 B1 EP1589191 B1 EP 1589191B1 EP 05103148 A EP05103148 A EP 05103148A EP 05103148 A EP05103148 A EP 05103148A EP 1589191 B1 EP1589191 B1 EP 1589191B1
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Prior art keywords
vanes
wheel
frequency
value
mistuning
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English (en)
French (fr)
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EP1589191A1 (de
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Jérôme Dupeux
Christian Dupont
Jean-Pierre Lombard
Eric Seinturier
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Safran Aircraft Engines SAS
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SNECMA SAS
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    • 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
    • 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
    • F01D5/16—Form or construction for counteracting blade vibration
    • 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
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S416/00—Fluid reaction surfaces, i.e. impellers
    • Y10S416/50—Vibration damping features
    • 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
    • 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
    • Y10T29/49318—Repairing or disassembling
    • 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
    • Y10T29/49321—Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member
    • 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
    • Y10T29/49764—Method of mechanical manufacture with testing or indicating
    • Y10T29/49771—Quantitative measuring or gauging
    • Y10T29/49774—Quantitative measuring or gauging by vibratory or oscillatory movement

Definitions

  • the present invention relates to turbomachine rotors, and in particular the rotors comprising vanes at their periphery which are subjected during the operation of the turbomachine to vibratory phenomena.
  • the turbomachine bladed wheels have a structure with a quasi-cyclic symmetry. They are generally composed of a series of geometrically identical sectors, with a tolerance that is related to the manufacturing tolerances of their various components and their assembly.
  • the vibratory energy is located on one or a few vanes instead of spreading over the entire wheel.
  • This expression denotes the vibratory response to an external excitation.
  • the external excitation finds its origin most often in a dissymmetry in the aerodynamic flow. It can be due for example to the upstream stators or downstream stator, distortion, air intake in the compressor, reintroductions of air, the combustion chamber or the structural arms.
  • the vane blade response levels can vary by a factor of 10 and the maximum on the bladed wheel can be double or triple what would have been achieved on a perfectly symmetrical wheel.
  • the evolution of the response to an excitation source as a function of the detuning follows a curve as represented on the figure 1 . It represents the maximum response in amplitude of vibration of the bladed wheel determined for different values of standard deviation of the eigenfrequencies of the vanes distributed on the wheel. For a discrepancy of 0%, the response is standardized to 1.
  • the standard deviation standard deviation that is encountered on wheels in use is of the order of 0.5%. It is generally found on this graph that it corresponds to the most unfavorable case. Trying to reduce it to get closer to the symmetry is very expensive because it implies in particular a reduction in manufacturing tolerances.
  • This graph also shows that from a certain level of detuning b, the effect on the dynamics of the bladed wheel fades and the maximum levels observed on the wheel decrease.
  • the object of the invention is to introduce a voluntary detuning on the bladed wheel so as to reduce the maximum response on the wheel, and to no longer depend on the involuntary, weak, always present detuning.
  • EP 1 211 382 describes a rotor of the turbomachine whose blades have eigenfrequencies of different vibration so as to reduce the vibratory levels in forced response.
  • the standard deviation discrepancy introduced is advantageously greater than this optimal value b.
  • the value b depends on the wheel studied, the stiffness of the disc and the value of the damping present on the bladed wheel. It can be considered that in most cases the value of b is of the order of 1 to 2% of standard deviation in frequency. In these cases, the standard deviation discrepancy introduced is greater than 2%.
  • the Campbell diagram aims to determine the frequency situation of the structure with respect to possible excitations. It includes the frequencies of the vibration modes of the bladed wheel as a function of the speed of rotation of the wheel on the one hand, and the possible excitation frequencies on the other hand. The crossings between these two types of curves correspond to the resonances.
  • ⁇ is the rotation frequency of the rotor.
  • the geometric and structural parameters of the mobile wheel concerned are determined so as to move the resonances out of the operating range with a margin of safety.
  • the invention therefore also aims to determine the minimum value of b so that its effect on vibration levels is significant while spreading the least possible modes of the structure to facilitate design.
  • the problem that the invention aims to solve consists for a given maximum amplitude of vibration value to determine the corresponding value of b on the curve.
  • said detuning value is determined by a statistical calculation method.
  • the invention also relates to a bladed wheel with a voluntary detuning.
  • a bladed wheel whose deliberate detuning has been determined according to the method of the invention has blades of different natural frequencies, the number of different frequencies, excluding manufacturing tolerances, being at most 3.
  • the vanes are distributed in patterns with vanes of natural frequency f1 and vanes of natural frequency f2, f2 being different from f1.
  • the successive patterns are identical or with a slight variation from one pattern to another.
  • each pattern comprises (s1 + s2) blades, s1 blades of frequency f1 and s2 blades of frequency f2.
  • each pattern comprises (s1 + s2 +/- 1) vanes with (s1 +/- 1) frequency vanes f1 and (s2 +/- 1) blades of frequency f2.
  • the wheel being subjected to a harmonic excitation n smaller than the number N of vanes of the wheel divided by two (n ⁇ N / 2) the vanes are distributed in n identical patterns or with a small variation from one pattern to another.
  • the wheel being subjected to a harmonic excitation n, n being greater than the number N of blades of the wheel divided by two (n> N / 2), the number of patterns is equal to the number of diameters of the mode concerned.
  • step 10 an initial value ⁇ j of the standard deviation in detuning frequencies is chosen.
  • ⁇ j the average of the differences between the natural frequency of vibration of each blade and the average frequency.
  • a distribution R i is randomly generated numerically. For a predefined value of standard deviation ⁇ j of a bladed wheel, there exists an infinity both of distributions R i of the vanes on the wheel MR i and of eigenfrequencies of the latter satisfying this condition of standard deviation ⁇ j .
  • step 30 for this distribution R i , the determination is made by a known numerical method to calculate the amplitude response to an excitation. For example, it may be for a turbojet compressor the response to distortions in the incident flow resulting from a side wind.
  • the maximum M ⁇ j is extracted from the values R i max ⁇ j . From the set of values R i max, we determine the maximum value of the amplification which will not be statistically exceeded in a percentage of cases higher than a fixed rate, for example 99.99%. This result is achieved by plotting the values on a cumulative probability curve.
  • the cloud of points is advantageously smoothed by a route of Weibull probability which makes it possible to reduce the number of necessary prints, for example to 150.
  • the introduction of a voluntary detuning improves the aeroelastic stability of the wheel.
  • the average of the damping coefficients corresponding to each possible phase angle between the blades is calculated, and it is verified that the mode concerned by the floating is lower than said average.
  • the detuning is optimized to minimize the forced response on a resonance, making sure that the impact on stability and the Campbell diagram (for the other resonances) is acceptable or the detuning is optimized with respect to stability by ensuring that the impact on the Campbell diagram is acceptable.
  • the detuning reflects an asymmetry of the structure.
  • the classical cyclic symmetry analysis approaches which allow to model only one sector of the structure and then reconstruct the behavior of the complete wheel, are therefore not directly applicable.
  • Steps A) and B) are long enough to calculate but the calculation is done only once.
  • steps C) and D) are very fast, which allows rapid analyzes for different detuning vectors. This method is therefore particularly suitable for statistical approaches.
  • the total “disconnected” aeroelastic effort is obtained by combining the “basic” efforts, according to the same superposition rule as that used in step D). (The representation base is the same).
  • the stability calculation therefore requires a large number of unsteady aerodynamic calculations that are quite expensive.
  • the detuned analyzes are very fast.
  • this detuning is advantageously carried out in one of the following ways.
  • a blade distribution is selected on the wheel whose eigenfrequencies satisfy the standard deviation condition b.
  • all the blades are positioned symmetrically on the disk in particular in terms of angle, pitch and axial position.
  • the wheel is asymmetrical from the point of view of frequencies only.
  • the number of different blades is limited to two or three types.
  • the nominal frequency of the blades is f0, f1 the eigenfrequency of the blades with increased frequency with respect to f0 and f2 the natural frequency of the vanes with reduced frequency.
  • the vanes are distributed according to the pattern: [f1 f1 f2 f2] is a distribution f1f1f2f2 f1 f1 f2 f2 etc .; on the rotor alternatively has two blades of frequency f1 then two blades of frequency f2, or according to the pattern [f1 f1 f1 f2 f2 f2]; alternation is three blades. etc.
  • a pattern of (s1 + s2) vanes with s1 vanes of frequency f1 and s2 vanes of frequency f2 which is repeated on the wheel is defined.
  • the successive patterns vary slightly from one pattern to another, in particular of +/- 1 blades or +/- 2 blades.
  • 36 vanes may be distributed in successive patterns: (4f1 4f2) (5f1 5f2) (4f1 4f2) (5f1 5f2) or according to the patterns (4f1 Sf2) (4f1 Sf2) (5f1 5f2) (4f1 4f2). other solutions are possible.
  • s1 s2 and s1 is at most N / 4.
  • the wheel being subjected to a harmonic excitation n, ie n perturbations per revolution, n being smaller than the number N of vanes of the wheel divided by two (n ⁇ N / 2), the vanes are arranged in a distribution which tends to have the same order of symmetry as the excitation on the wheel. They are divided into n identical or distribution groups that vary little from one group to another.
  • the average frequency is f0 or close to f0.
  • the blades are arranged in approximately identical patterns: 4 groups of 7 blades and a group of 8 blades such as for example (4f1 3f2) (3f1 4f2) (4f1) 3f2) (3f1 4f2) and (4f1 4f2). Other distributions are possible.
  • the vanes are distributed according to a number of repeating units equal to the number of diameters of the mode concerned. For example 24 excitations per turn on a moving wheel of 32 blades involve a dynamic response of the so-called 8-diameter bladed wheel. We therefore use a detuning distribution with 8 repetitive patterns.
  • the frequency can be modified by acting on the material constituting the blade.
  • This solution makes it possible to make the vanes geometrically identical to the manufacturing tolerances and not to modify the stationary aerodynamic flow.
  • the blade is made from materials having different Young's moduli or densities.
  • the frequencies being related to the ratio stiffness on mass, the simple change of material thus has an impact on the frequencies.
  • the texture of the zone composite is affected.
  • Another range of solutions consists in modifying the foot of the blade without affecting the blade; we can change the length or the thickness of the stilt, the shape of the bottom of the platform its thickness. In particular a punctual addition of masses under the platform makes it possible to shift the frequencies of the first modes of vibration.

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

Claims (16)

  1. Verfahren zum Einstellen gezielter unterschiedlicher Eigenfrequenzen in einem beschaufelten Rotor einer bestimmten Turbomaschine, um die Vibrationsniveaus des Rotors mit gezwungener Response zu reduzieren, gemäß dem auf dem Rotor mindestens teilweise Schaufeln mit verschiedenen Eigenfrequenzen mit einer Frequenzverteilung gemäß einer Standardabweichung zur Verfügung stehen, die mindestens gleich einem gewählten Wert ist, dadurch gekennzeichnet, dass es darin besteht, je nach den Betriebsbedingungen des Rotors im Inneren der Turbomaschine einen optimalen Wert der Standardabweichung der unterschiedlichen Eigenfrequenzen hinsichtlich der maximalen Response der Vibrationsamplitude, die auf dem Rotor gewünscht wird, festzulegen, wobei die Schaufeln mit unterschiedlichen Eigenfrequenzen so verteilt sind, dass die Frequenzen der gesamten Schaufeln eine Standardabweichung aufweisen, die mindestens gleich dem Wert der unterschiedlichen Eigenfrequenzen ist, wobei der Wert der falschen Abstimmung statistisch festgelegt ist.
  2. Verfahren nach dem vorhergehenden Anspruch, in dem
    ■ sein erster Wert σj der Standardabweichung der unterschiedlichen Eigenfrequenzen definiert wird,
    ■ eine Anzahl R mit statistischer Relevanz der zufälligen Verteilungen der unterschiedlichen Eigenfrequenzen in dieser Abweichung Typ σj erzeugt wird,
    ■ für jede der R zufälligen Verteilungen die gezwungene Response, je nach den Betriebsbedingungen des Rotors im Inneren der Turbomaschine mit unterschiedlichen Eigenfrequenzen, berechnet wird,
    ■ der maximale Wert extrahiert wird,
    ■ ein anderer Wert σj gewählt und die vorhergehende Berechung wiederholt wird, wobei die Anzahl der Wiederholungen ausreichend ist, um eine Nachverfolgung der Responsewerte je nach den Werten σj durchzuführen.
  3. Verfahren nach einem der vorhergehenden Ansprüche, nach dem im Voraus festgelegt wird, ob das Einstellen von gezielten unterschiedlichen Eigenfrequenzen die aeroelastische Stabilität verbessert, indem der Mittelwert des Abschwächungskoeffizienten, die jedem möglichen Phasenwinkel zwischen den Schaufeln entsprechen, berechnet wird und überprüft wird, ob die aeroelastische Abschwächung des Modus, der von der Schwingung betroffen ist, geringer als der Mittelwert ist.
  4. Verfahren nach einem der Ansprüche 1 bis 2, wobei die Anzahl der Eigenfrequenzen der verschiedenen Schaufeln außerhalb der Fabrikationstoleranzen höchstens 3 beträgt.
  5. Verfahren nach Anspruch 4, wobei die Schaufeln nach Mustern mit Schaufeln mit der Eigenfrequenz f1 und Schaufeln mit der Eigenfrequenz f2 verteilt sind, wobei f2 verschieden von f1 ist.
  6. Verfahren nach Anspruch 5, wobei die aufeinander folgenden Muster identisch oder mit einer geringfügigen Variation von einem Muster zum anderen sind.
  7. Verfahren nach dem vorhergehenden Anspruch, wobei jedes Muster (s1+s2) Schaufeln umfasst, s1 Schaufeln mit der Frequenz f1 und s2 Schaufeln mit der Frequenz f2.
  8. Verfahren nach dem vorhergehenden Anspruch, wobei s1 = s2 und s1 höchstens gleich der gesamten Anzahl N der Schaufeln der Turbine, geteilt durch 4, ist.
  9. Verfahren nach Anspruch 6, wobei jedes Muster (s1 +s2 +/-2) Schaufeln mit (s1 +/-1) Schaufeln der Frequenz f1 und (s2+/-1) Schaufeln der Frequenz f2 umfasst.
  10. Verfahren nach einem der vorhergehenden Ansprüche, wobei der Rotor einer harmonischen Oberschwingung n kleiner der Anzahl N der Schaufeln des Rotors, geteilt durch zwei (n < N/2) unterzogen wird, und wobei die Schaufeln in n Mustern verteilt sind, die identisch sind oder von Muster zu Muster eine geringfügige Variation aufweisen.
  11. Verfahren nach einem der vorhergehenden Ansprüche, wobei der Rotor einer harmonischen Oberschwingung n unterzogen wird, wobei n größer als die Anzahl N der Schaufeln des Rotors, geteilt durch zwei (n > N/2) ist, und wobei die Anzahl der Muster gleich der Anzahl der Durchmesser des betroffenen Modus ist.
  12. Verfahren nach einem der vorhergehenden Ansprüche, wobei die Resonanzfrequenz der Schaufeln insbesondere durch eine geometrische Veränderung ihres Blatts geändert wird.
  13. Verfahren nach einem der vorhergehenden Ansprüche, wobei die Resonanzfrequenzen der Schaufeln insbesondere durch eine geometrische Veränderung ihres Fußes geändert werden, wobei das Blatt nicht geändert wird, um seine Steifheit zu ändern.
  14. Verfahren nach einem der Ansprüche 4 bis 11, wobei die Resonanzfrequenzen der Schaufeln durch Veränderung der Masse oder des Materials, aus dem die Schaufeln hergestellt sind, verändert werden.
  15. Verfahren nach dem vorhergehenden Anspruch, wobei die Schaufeln hohl oder ausgespart sind, wobei die Veränderung durch Füllen eines Teils der Hohlräume mit einem Material mit angepasstem Volumen erzeugt wird.
  16. Verfahren nach einem der Ansprüche 12 bis 15, wobei die Übergangszone zwischen dem Blatt und dem Nabenstück von einem Blatt zum anderen verändert ist.
EP05103148A 2004-04-20 2005-04-19 Verfahren zum Einstellen gezielter unterschiedlicher Eigenfrequenzen eines beschaufelten Rotors einer Turbomachine sowie Rotor Active EP1589191B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0404130 2004-04-20
FR0404130A FR2869069B1 (fr) 2004-04-20 2004-04-20 Procede pour introduire un desaccordage volontaire sur une roue aubagee de turbomachine roue aubagee presentant un desaccordage volontaire

Publications (2)

Publication Number Publication Date
EP1589191A1 EP1589191A1 (de) 2005-10-26
EP1589191B1 true EP1589191B1 (de) 2010-09-08

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EP05103148A Active EP1589191B1 (de) 2004-04-20 2005-04-19 Verfahren zum Einstellen gezielter unterschiedlicher Eigenfrequenzen eines beschaufelten Rotors einer Turbomachine sowie Rotor

Country Status (7)

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US (1) US7500299B2 (de)
EP (1) EP1589191B1 (de)
CA (1) CA2503659C (de)
DE (1) DE602005023373D1 (de)
ES (1) ES2351507T3 (de)
FR (1) FR2869069B1 (de)
RU (1) RU2372492C2 (de)

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RU2372492C2 (ru) 2009-11-10
FR2869069A1 (fr) 2005-10-21
RU2005111685A (ru) 2006-10-27
US20050249586A1 (en) 2005-11-10
US7500299B2 (en) 2009-03-10
FR2869069B1 (fr) 2008-11-21
CA2503659A1 (fr) 2005-10-20
ES2351507T3 (es) 2011-02-07
DE602005023373D1 (de) 2010-10-21
EP1589191A1 (de) 2005-10-26
CA2503659C (fr) 2013-01-29

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