EP1154125B1 - Aubage avec des éléments amortisseurs - Google Patents

Aubage avec des éléments amortisseurs Download PDF

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Publication number
EP1154125B1
EP1154125B1 EP01109099A EP01109099A EP1154125B1 EP 1154125 B1 EP1154125 B1 EP 1154125B1 EP 01109099 A EP01109099 A EP 01109099A EP 01109099 A EP01109099 A EP 01109099A EP 1154125 B1 EP1154125 B1 EP 1154125B1
Authority
EP
European Patent Office
Prior art keywords
rotor
damping
damping elements
blade
damping element
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.)
Expired - Lifetime
Application number
EP01109099A
Other languages
German (de)
English (en)
Other versions
EP1154125A3 (fr
EP1154125A2 (fr
Inventor
Herbert Brandl
Rudolf Dr. Kellerer
Brammajyosula Dr. Ravindra
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.)
General Electric Technology GmbH
Original Assignee
Alstom Technology 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 Alstom Technology AG filed Critical Alstom Technology AG
Publication of EP1154125A2 publication Critical patent/EP1154125A2/fr
Publication of EP1154125A3 publication Critical patent/EP1154125A3/fr
Application granted granted Critical
Publication of EP1154125B1 publication Critical patent/EP1154125B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • 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

Definitions

  • the present invention relates to a vane arrangement with damping elements.
  • the damping elements are used for vibration damping of the blade assembly.
  • the blade assembly comprises a rotor and vanes arranged on the circumference of the rotor, wherein damping elements are loosely arranged between the blades, which are in contact with the blades during rotation of the rotor about a rotor axis by a centrifugal force acting in the radial direction.
  • Such blade arrangements are used in particular in turbomachines such as gas turbines.
  • the individual blades consist of the blade leaf, a blade platform and the blade root, which is suspended in corresponding recesses on the circumference of the rotor.
  • undesirable bending and torsional vibrations which can lead to premature material fatigue and thus to a shortened service life of the blade arrangement, are produced by various sources of excitation.
  • the present invention relates to a vane arrangement with damping elements for damping these unwanted vibrations.
  • damping elements which act between the individual blades.
  • These damping elements are usually loose body, resting in the resting state, first between the blade roots of the blades on the rotor or on corresponding support structures and are pressed during operation of the rotor due to acting in the radial direction centrifugal force against the underside of the blade platforms of adjacent blades ,
  • Each damping element is at the same time in contact with both adjacent blade platforms. Thereby, the kinetic energy of a caused relative to vibration relative movement between the blades in the frictional energy between the respective blade platforms and the adjacent damping element can be converted. This dampens the vibrations and leads overall to a reduced vibration load of the blade assembly.
  • Such a blade arrangement with damping elements is known for example from US 4,917,574.
  • the blade platforms of adjacent blades with their underside form recesses into which spherical bodies are pressed as damping elements during rotation by the centrifugal force.
  • damping elements are formed them as rod-shaped elements with a round cross-section, which are parallel are arranged to the rotor axis between adjacent blades.
  • the arrangement can in this case take place, for example, in a corresponding lateral recess of the blade root or the blade platform of one of the adjacent blades.
  • This frequently used form of the damping elements with a circular cross-section additionally causes a sealing of the gas flow of a gas turbine relative to the rotor and is therefore also referred to as a so-called "seal-pin damper".
  • damping elements can jam. As a result, relative movements are prevented, whereby large stresses arise at the transition points from the damping element to the blades. These stresses lead to premature material fatigue and may favor the formation of cracks in the blades.
  • these circular cross-section-shaped damping elements do not act in all the vibrations occurring a blade assembly in the same way, so that certain vibration conditions can occur almost unattenuated. In particular, it is in these circular cross-section damping elements that no relative movement between the contact surfaces occurs or roll the damping elements on the contact surface instead of performing a sliding movement.
  • edge areas form opposite sides adjacent bucket platforms a tapered in the radial direction recess or guide, in which the damping element is pressed by the centrifugal force.
  • the damping element is in this case formed with a wedge-shaped cross-section, wherein the wedge angle corresponds to the angle of the V-shaped recess formed by the two edge regions of the blade platforms.
  • GB 2 112 466, US 5,700,133 and US 5,143,517 disclose blade assemblies in which three damping elements are disposed between two blades.
  • the damping effect of the device shown in SU 1127979 is based on a spreading action of Dämpfangsiata.
  • the damping effect of the arrangements proposed in EP 0 918 139 and US 2,942,842 is based on a wedging action of the damping elements on adjacent blades.
  • the object of the present invention is to provide a blade assembly with damping elements, with the good damping of a variety of different vibration states can be achieved.
  • the vane arrangement with damping elements comprises a rotor and vanes arranged on the circumference of the rotor. Between the blades damping elements are arranged, which are brought into contact with the blades during a rotation of the rotor about the rotor axis by the radially acting centrifugal force.
  • the blade arrangement is characterized in that two damping elements in the circumferential direction of the rotor are arranged one behind the other at least between two adjacent blades.
  • damping elements are configured and arranged in such a way that, during a rotation of the rotor, the damping elements arranged one behind the other touch via one or more contact surfaces and a first of the damping elements arranged one behind another with a first friction surface of one and a second of the damping elements arranged one behind the other with a second friction surface contact other of the adjacent blades.
  • the first and the second damping element differ in terms of their geometric shape, wherein the first damping element has a wedge-shaped cross-section and the second damping element has a circular or elliptical cross-section.
  • the mass center of gravity of the group of damping elements arranged one behind the other can be selected such that it is not symmetrical in the circumferential direction of the rotor between the two adjacent blades or friction surfaces. This allows the load unevenly distributed to the damping elements.
  • the asymmetry can be adjusted specifically by the different geometric design or by different masses of the two damping elements. Due to the large number of possible combinations, the groups of damping elements can be optimally configured for every application. In particular, it can be ensured by the appropriate choice of the friction or contact surfaces, the mass and the position of the mass center of gravity that the damping elements do not bind.
  • the damping elements should also have a high stiffness / weight ratio. This can also be achieved by a hollow shape of these elements.
  • the damping elements of a group can consist of different materials.
  • one of two damping elements cobalt can be selected as the base material, as the base material of the other damping element nickel. This allows different coefficients of friction on the respective friction surfaces with the blades, so that a further adaptation possibility for achieving optimal vibration damping is available through the choice of material.
  • the damping elements are in this case, as in the known arrangements of the prior art, pressed by the centrifugal force during the rotation of the rotor, for example against the underside of the blade platforms.
  • the blade platforms should be suitably shaped on their undersides for this purpose in adaptation to the shape of the damping elements or guide grooves form.
  • other areas of the blade root can be formed by suitable shaping for receiving the damping elements.
  • the damping elements can also be held by suitable restraint systems.
  • a combination of a rod-shaped damping element with a circular cross-section and a wedge-shaped damping element ie a rod-shaped damping element with a wedge-shaped cross section.
  • This combination of two differently acting damping elements effectively attenuates a large number of different vibration states. While with the rod-shaped damping element with a circular cross-section primarily in-phase vibrations are effectively damped, the wedge-shaped damping element acts especially on vibrations that do not occur in phase.
  • the group according to the invention arranged behind one another damping elements can be used only between individual or between all adjacent blades of the blading. Recently, it has also been found that mistuning the damper can reduce or prevent flutter.
  • the possibility of an asymmetric damper configuration of the present invention offers significant advantages.
  • the damping elements of a group arranged one behind the other can consist of different materials and / or have different geometric shapes, wherein this material or pattern pattern repeats in a reversed manner over the entire blading.
  • the relative position of a damping element with wedge-shaped Swap cross-section to a damping element of circular cross section from blade to blade to achieve the desired mismatch can be used only between individual or between all adjacent blades of the blading.
  • two or more groups of successively arranged damping elements can be arranged in an identical or different configuration between the adjacent blades via the axial extension of the blades. This gives you the ability to effectively dampen a variety of waveforms.
  • the damper configurations of the individual groups are optimized in each case in the form and / or the mass ratio and / or the geometric dimensions corresponding to the waveform to be damped.
  • Figure 1 shows a first embodiment of an embodiment of the damping elements in the blade assembly according to the invention.
  • the figure shows a section of the blade arrangement in a sectional plane perpendicular to the rotor axis.
  • the blade platforms 1 adjacent blades can be seen, which - not shown - are mounted on the rotor blade and have a small distance from each other.
  • the undersides of the two blade platforms 1 form friction surfaces 4, 5, against which the two damping elements 2, 3 are pressed during a rotation of the rotor by the centrifugal force.
  • the friction surfaces 4, 5 are in this example at an angle of approximately 45 ° to the plane which is spanned by the radial direction and the rotor axis, inclined.
  • Both damping elements are rod-shaped in the axial direction, as is known from the prior art.
  • Such a configuration and arrangement allows a relative movement of the damping elements to each other and to the blade platforms in the radial direction for optimal damping of in-phase bending vibrations. At the same time, the problem of settling occurring with damping elements having a circular cross-section is avoided without having to comply with a specific angle of inclination of the friction surface 5 on the blade platform.
  • FIG. 2 shows a further example of the design and arrangement of the damping elements in the present blade arrangement.
  • the surface of the wedge-shaped damping element 2 which comes into contact with the friction surface 4 of the blade platform, provided with elevations or raised areas 7. These raised areas serve to prevent a tilting of the wedge-shaped damping element with respect to the friction surface 4, as might occur under certain vibration conditions. By this configuration, therefore, possible tilting of the damping element are avoided, which lead to a deterioration of the damping behavior.
  • the inclination of the friction surface 4 on the side of the wedge-shaped damping element 2 to a direction perpendicular to the radial direction plane can be in this as well as in the other embodiments between 45 ° and 80 ° and is chosen such that a setting of the damping element 2 is prevented.
  • the angle ⁇ between the contact surface 6 of wedge-shaped 2 and circular damping element 3 and the plane perpendicular to the radial direction plane can be chosen arbitrarily in order to achieve the required stability and to prevent the setting of the damping element 3. This angle ⁇ can be chosen in particular also significantly smaller than 90 °.
  • FIG. 1 Another example of an embodiment of the damping elements of the present blade arrangement is shown in FIG.
  • the first damping element 2 - again wedge-shaped - designed such that it comes into contact with two friction surfaces 4, 5 of the two adjacent blade platforms 1 in a rotation of the rotor.
  • a further damping element with a circular cross-section 3 is used, which likewise has the friction surface 5 of a blade platform 1 frictionally engages in contact.
  • the diameter of the circular damping element 4 must be smaller in otherwise identical geometric conditions than in the embodiments of FIGS. 1 and 2.
  • the wedge-shaped damping element 2 is in turn provided with raised areas 7 in order to avoid the tilt instability already explained.
  • Figure 4 finally shows schematically an example of the arrangement of two groups of damping elements over the axial extent of the blades.
  • the blade 8, the blade platform 1 and the blade root 9 can be seen.
  • the positions of two groups 10, 11 of successively arranged damping elements are indicated, which are designed according to the patent claims, for example as in the preceding examples.
  • the first group 10 is in this example at the leading edge 14 of the blade, the second group 11 at the trailing edge 15.
  • the flow direction 13 is through a Arrow indicated.
  • the embodiments of the present blade assembly are suitable for damping a variety of possible resonant and non-resonant vibrational excitations, such as fluttering, shaking, or stochastic excitation.
  • the possibility of divergent geometric design of the two damping elements allows optimal adaptation to the particular circumstances. Even with respect to the rotor axis inclined platforms, the damping elements can be used in a corresponding inclined position or orientation.
  • the damping elements are suitable for use in low-pressure as well as high-pressure turbines and for compressor blades. They can be used as simple damping elements or for additional sealing as damping and sealing elements.

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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 (10)

  1. Aubage avec des éléments amortisseurs, qui comprend un rotor et des aubes disposées sur la périphérie du rotor, des éléments amortisseurs (2, 3) étant disposés entre les aubes, lesquels sont en contact avec les aubes lors d'une rotation du rotor autour d'un axe de rotor sous l'effet d'une force centrifuge agissant dans la direction radiale, au moins entre deux aubes voisines étant disposé un groupe de précisément deux éléments amortisseurs (2, 3) disposés l'un derrière l'autre dans la direction périphérique du rotor, de sorte que dans le cas d'une rotation du rotor, les éléments amortisseurs (2, 3) disposés l'un derrière l'autre dans la direction périphérie du rotor soient en contact par le biais d'une ou de plusieurs surfaces de contact (6) et que le premier (2) des éléments amortisseurs disposés l'un derrière l'autre dans la direction périphérie du rotor vienne en contact avec une première surface de frottement (4) d'une aube voisine et que le deuxième (3) des éléments amortisseurs disposés l'un derrière l'autre dans la direction périphérie du rotor vienne en contact avec une deuxième surface de frottement (5) de l'autre des aubes voisines, le premier élément amortisseur (2) et le deuxième élément amortisseur (3) se distinguant par leur forme géométrique,
    caractérisé en ce que
    le premier élément amortisseur (2) présente une section transversale en forme de cale et le deuxième élément amortisseur (3) présente une section transversale en forme d'ellipse.
  2. Aubage selon la revendication 1,
    caractérisé en ce que
    l'angle de cale de la section transversale en forme de cale du premier élément amortisseur (2) correspond à l'angle entre la première surface de frottement (4) et le plan formé par la direction radiale et l'axe du rotor.
  3. Aubage selon la revendication 1,
    caractérisé en ce que
    le premier élément amortisseur (2) est réalisé et disposé de telle sorte qu'il vienne en contact également avec la deuxième surface de frottement (5) dans le cas d'une rotation du rotor.
  4. Aubage selon la revendication 3,
    caractérisé en ce que
    l'angle de cale de la section transversale en forme de cale du premier élément amortisseur (2) correspond à l'angle entre la première surface de frottement (4) et la deuxième surface de frottement (5).
  5. Aubage selon l'une quelconque des revendications 1, 2 et 4,
    caractérisé en ce que
    les surfaces du premier élément amortisseur (2) qui viennent en contact avec la ou les surfaces de frottement (4, 5), présentent des rehaussements (7).
  6. Aubage selon l'une quelconque des revendications 1 à 5,
    caractérisé en ce que
    la première (4) et la deuxième surface de frottement (5) sont respectivement formées par un côté inférieur d'une plate-forme d'aube (1) de l'aube respective, les surfaces de frottement (4, 5) étant inclinées vers le plan formé par la direction radiale et l'axe du rotor de telle sorte qu'elles forment entre elles une coulisse en forme de V dans laquelle sont pressés les éléments amortisseurs (2, 3) sous l'effet de la force centrifuge.
  7. Aubage selon l'une quelconque des revendications 1 à 6,
    caractérisé en ce que
    le centre de masse du groupe constitué d'éléments amortisseurs (2, 3) disposés l'un derrière l'autre dans la direction périphérique du rotor n'est pas situé symétriquement entre les deux aubes voisines ou les surfaces de frottement (4, 5), dans la direction périphérique du rotor.
  8. Aubage selon l'une quelconque des revendications 1 à 7,
    caractérisé en ce que
    deux groupes des éléments amortisseurs (2, 3) disposés l'un derrière l'autre dans la direction périphérique du rotor, ou plus de deux groupes, sont disposés suivant une configuration identique ou différente sur toute l'étendue axiale des aubes.
  9. Aubage selon l'une quelconque des revendications 1 à 8,
    caractérisé en ce qu'un ou plusieurs groupes des éléments amortisseurs (2, 3) disposés l'un derrière l'autre dans la direction périphérique du rotor sont disposés entre d'autres aubes voisines.
  10. Aubage selon la revendication 9,
    caractérisé en ce que
    quelques-uns des groupes d'éléments amortisseurs (2, 3) disposés l'un derrière l'autre dans la direction périphérique du rotor entre des aubes voisines différentes ont une configuration différente.
EP01109099A 2000-05-08 2001-04-12 Aubage avec des éléments amortisseurs Expired - Lifetime EP1154125B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10022244 2000-05-08
DE10022244A DE10022244A1 (de) 2000-05-08 2000-05-08 Schaufelanordnung mit Dämpfungselementen

Publications (3)

Publication Number Publication Date
EP1154125A2 EP1154125A2 (fr) 2001-11-14
EP1154125A3 EP1154125A3 (fr) 2003-10-29
EP1154125B1 true EP1154125B1 (fr) 2006-03-15

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EP01109099A Expired - Lifetime EP1154125B1 (fr) 2000-05-08 2001-04-12 Aubage avec des éléments amortisseurs

Country Status (3)

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US (1) US6478544B2 (fr)
EP (1) EP1154125B1 (fr)
DE (2) DE10022244A1 (fr)

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US10472975B2 (en) * 2015-09-03 2019-11-12 General Electric Company Damper pin having elongated bodies for damping adjacent turbine blades
US10584597B2 (en) 2015-09-03 2020-03-10 General Electric Company Variable cross-section damper pin for a turbine blade
US10385701B2 (en) 2015-09-03 2019-08-20 General Electric Company Damper pin for a turbine blade
US10662784B2 (en) * 2016-11-28 2020-05-26 Raytheon Technologies Corporation Damper with varying thickness for a blade
US10677073B2 (en) 2017-01-03 2020-06-09 Raytheon Technologies Corporation Blade platform with damper restraint
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JP7039355B2 (ja) * 2018-03-28 2022-03-22 三菱重工業株式会社 回転機械
CN113227539B (zh) * 2018-12-20 2023-08-29 西门子能源全球两合公司 带叶片的转子系统及对应的维修方法
CN110925030B (zh) * 2019-12-05 2022-03-08 中国航发四川燃气涡轮研究院 一种带嵌入式叶冠阻尼的低压涡轮模拟叶片
CN113803115B (zh) * 2020-06-16 2024-04-05 中国航发商用航空发动机有限责任公司 涡轮叶片缘板阻尼器、涡轮叶片和航空发动机
CN114382549B (zh) * 2020-10-21 2024-04-23 中国航发商用航空发动机有限责任公司 涡轮和航空发动机
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Also Published As

Publication number Publication date
DE10022244A1 (de) 2001-11-15
EP1154125A3 (fr) 2003-10-29
DE50109189D1 (de) 2006-05-11
EP1154125A2 (fr) 2001-11-14
US20010038793A1 (en) 2001-11-08
US6478544B2 (en) 2002-11-12

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