EP1136653A2 - Aubage avec éléments amortisseurs - Google Patents

Aubage avec éléments amortisseurs Download PDF

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Publication number
EP1136653A2
EP1136653A2 EP01105747A EP01105747A EP1136653A2 EP 1136653 A2 EP1136653 A2 EP 1136653A2 EP 01105747 A EP01105747 A EP 01105747A EP 01105747 A EP01105747 A EP 01105747A EP 1136653 A2 EP1136653 A2 EP 1136653A2
Authority
EP
European Patent Office
Prior art keywords
blade
damping element
region
area
rotor
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP01105747A
Other languages
German (de)
English (en)
Other versions
EP1136653A3 (fr
Inventor
Jaroslaw Dr. Szwedowicz
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
Alstom Power NV
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, Alstom Power NV filed Critical Alstom Technology AG
Publication of EP1136653A2 publication Critical patent/EP1136653A2/fr
Publication of EP1136653A3 publication Critical patent/EP1136653A3/fr
Withdrawn legal-status Critical Current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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/04—Antivibration arrangements
    • F01D25/06—Antivibration arrangements for preventing 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
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/70—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
    • 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 blading with damping elements, a rotor and am
  • the circumference of the rotor is inserted in the radial direction extending blades with blade platform and blade base includes. At least between some of each a damping element is arranged adjacent to blades, that with a rotation of the rotor via friction with at least a first area of a first and a second region of a second one of the neighboring ones Buckets communicates.
  • Such blading is used in particular at Turbomachines such as gas turbines are used.
  • the single ones Blades consist of the blade, the bucket platform, the bucket neck and the Blade foot, which in corresponding recesses on the circumference of the rotor is used.
  • the present invention relates to blading with damping elements that reduce these vibrations.
  • Such blading with damping elements is described for example in US 5,156,528.
  • the edge regions form more adjacent ones Bucket platforms one in the radial direction tapering recess into which the damping element is pressed by the centrifugal force.
  • the damping element is so similar to that in its geometric form Shape of this recess is adapted to that when operating the blading in this recess is present.
  • the smallest distance between the neighboring ones Bucket platforms are of course smaller than the dimensions of the damping element, so that this cannot separate itself from the blading.
  • the object of the present invention is in providing blading with damping elements, where the damping elements between neighboring blades work and even at low Vibration modes cause sufficient damping.
  • the present blading points in known Way a rotor and inserted on the circumference of the rotor, blades extending in the radial direction with shovel platform, shovel neck and shovel foot on, at least between some of each neighboring Paddles arranged a damping element is that when the rotor rotates via friction with at least a first area of a first and a second area of a second of the neighboring Buckets communicates.
  • the blading is characterized in that the damping element so designed and between the first and the second Shovel is arranged that the first area and the second area clearly in the radial direction from each other spaced positions.
  • the Relative movement of the surfaces of the Damping element and the respective blades low vibration modes can be increased that the areas of contact, lines of contact or points of contact with the neighboring blades radially spaced apart.
  • This radial distance increases the relative movements at low vibration modes, so one stronger energy dissipation and thus a better and more effective vibration damping can be achieved.
  • This technique is therefore particularly useful for small relative movements adjacent blades or at low Vibration modes, as they often occur, of great Advantage.
  • this technique also stronger relative movements or higher vibration modes can be damped well.
  • the present damping element is as well as the known damping elements of the stand of technology, formed from a rigid body, the due to the centrifugal forces acting on the rotation pressed against the first and second area becomes. In this position, part of the energy becomes a vibration movement in friction work on the damping element implemented.
  • the distance in radial Direction should be at least a third of the distance from the top of one Bucket platform up to the surface of the rotor circumference is present. This gap is determined by the thickness of the Blade platform and an upper area of the blade root, the scoop neck. The lower area of the blade root is in the holder or recess inserted on the circumference of the rotor. One too small distance between the first and second area leads to low vibration modes the vibration energy is insufficient in friction energy can be converted.
  • the damping element be dimensioned so that it when operating the blading only in the desired Position pressed against the neighboring blades becomes.
  • the damping element has a cross section preferably an elongated shape in the radial plane with a length that is greater than the distance between neighboring ones Blade feet in the circumferential direction of the rotor.
  • the damping element can be between insert the blades that there is one end at the Underside of the platform that a bucket is resting on, while the other end is at a significantly different radial position against the blade root the other neighboring shovel pushes.
  • the shape or Configuration of the damping elements in the axial direction that is in the direction parallel to the axis of the rotor, can be both straight and curved. This applies to everyone in the arrangement according to the invention usable damping elements.
  • In the radial position is the distance of one in the present application To understand the point to the rotor axis in a radial plane.
  • a radial plane makes a plane perpendicular to the rotor axis.
  • the damping elements can be particularly advantageous Use when your focus is close to first or second range. Through this required asymmetry of the damping element achieve that the vibration energy at a Relative movement between adjacent blades only at the contact area with the damping element converts into frictional energy, which is further from the center of gravity of the damping element is removed than the other Contact area. By choosing a focus of the damping element as close as possible to one of these Contact areas occur at this area no or very little frictional movement on. This leads to an increase in effectiveness of energy conversion.
  • the damping element has a widened at one end Range on which between the operation of the rotor both platforms is pressed and thus like one Damping element according to the state mentioned at the beginning works.
  • the dimensions of this widened area and the shape of the edge areas of the platforms should be suitably matched to one another.
  • the invention Damping element has one of these widened area outgoing foothills on the up to one clearly in the radial direction from the Platforms spaced area of the blade root enough.
  • the distribution of the center of gravity in the damping element is chosen so that the end of the foothills pressed against the blade root during operation of the rotor becomes.
  • the damping properties the known elements of the stand the technology combined with the damping properties, as with the damping elements shown above can be achieved.
  • the damping element At the first and / or second areas of the Blade feet or blade platforms are preferred Depressions or grooves provided in which the damping element can be used or in rotary operation engages, and the movement of the damping element prevent in the axial direction.
  • the damping element should be the first and the second area as large a distance as possible have in the radial direction. The maximum distance is made possible by the first area at or just below the platform of the first blade and just above the rotor surface on the blade neck the second blade is in contact.
  • the damping element extends quasi diagonally in the radial plane over the one present between adjacent blade roots Space. The best damping effect can can of course only be achieved if between all neighboring blades of the blading Damping elements are arranged.
  • the mass, focus distribution, Shape and the material of the damping element depending on the desired damping properties and the properties of the rotor and the Number of blades selected.
  • FIG. 1 shows a first example of an embodiment of the blading according to the invention in the detail.
  • a section through the blading parallel to the rotor axis is shown in the left part of the figure.
  • the cutting plane contains the rotor axis.
  • the rotor 5 can be seen, into which the blade root 8 of a blade 6 is inserted in a manner known per se.
  • the blade neck 14 and the blade platform 7 extend between the blade blade 10, which is only indicated, and the rotor 5.
  • the same arrangement is shown in the right part of the figure in a section perpendicular to the rotor axis, that is to say in a radial plane.
  • a section of the rotor 5 with two inserted blades 6 (blade i; adjacent blade i + 1) with the blade platforms 7 and the blade necks 14 protruding from the rotor can also be seen here.
  • a damping element 9 is arranged between the adjacent blades, which is shown again in a perspective view in the top right corner.
  • This damping element has an elongated, stick-like shape in cross section in the radial plane, so that its center of gravity 12 is clearly shifted towards one end.
  • the arrangement of this damping element 9 during operation of the blading that is to say when the rotor rotates, is shown.
  • One end of the damping element is pressed against the contact areas 1 and 2 of the blade neck or the blade platform of the right blade while the other end abuts the contact area 3 of the left blade.
  • these contact areas can be 9 surfaces, points or lines. In the present example it is a linear contact. In the left part of the figure, this linear contact is indicated by the connecting lines between points 1, 2 and 3 and points 1 ', 2' and 3 '.
  • a groove 11 on the scoop neck 14 can also be seen, in which the damping element is arranged, thereby preventing axial movements of the damping element.
  • the damping element 9 is designed such that it can only be in contact with the contact areas 1, 2 and 3 in the position shown when the rotor is in operation. In the idle state, the damping element initially rests on the rotor 5 with the widened region and is forced into the position shown by the centrifugal force during a rotational movement.
  • the dimensions of the damping element are chosen such that the smallest possible distance 13 to the rotor surface remains.
  • the transition between the bucket neck 14 and the bucket platform 7 also be rounded, so the damping element 9 in a form-fitting manner in these areas can concern.
  • FIG. 2 shows a further embodiment of the blading according to the invention.
  • the damping element 9 is designed with a widened region on one side, which is pressed between a recess formed by the spaced-apart blade platforms 7 during operation of the rotor.
  • This can be seen in the right part of the figure, wherein in addition to a contact with the right vane platform in area 1, there is also a contact with the left vane platform in area 4.
  • This achieves the effect of the damping elements known from the prior art, which act in the same way on the blade platforms at the same height.
  • the present damping element does not only consist of this widened area which engages between the two blades.
  • the damping element has an elongated shape or an extension in the radial plane, as shown, a lower region being in contact with the left vane neck in region 3.
  • the center of gravity 12 of the damping element 9 must lie in the circumferential direction between the contact point 2 and the contact point 3, since the damping element is then only pressed against the left blade neck by the centrifugal force in the manner shown.
  • the geometric shape of the damping element 9 used in this exemplary embodiment is shown again in a perspective view in the upper right part of the figure. The recognizable asymmetry is necessary in this case in order to achieve the frictional connection with the illustrated contact points or contact surfaces 1, 3 and 4 under the action of the centrifugal force.
  • the damping element 9 is dimensioned such that it is only a short distance 13 from the rotor 5. In the present case, this small distance enables a large distance - in the radial direction - between the contact area 3 and the contact area 1. This clear distance is advantageous for achieving the effect according to the invention.
  • the effect of the damping element 9 known from the prior art on the two adjacent platforms 7 can also be achieved via the contact surfaces 1 and 4 by a different design of the edge regions of the platforms or the upper end of the damping element 9. It is essential in this embodiment that the damping element extends towards the rotor in order to achieve frictional contact with the contact surface 3 during operation.
  • the vibration of the blading is damped simultaneously in all three areas 1, 3 and 4.
  • a groove 11 is provided in the blade platform 7, as is indicated in the left part of the figure.
  • FIG. 3 finally shows a further embodiment of the blading according to the invention, the same cross-sectional views being shown here as in FIG. 1.
  • the damping element 9 has an angled shape which approximately corresponds to that of a golf club. With this shape, two essentially parallel surfaces are provided on the damping element 9, a first of which rests on the underside of the blade platform 7 in area 1, while a second rests on the underside of a projection on the adjacent shovel neck 14 (contact area 3).
  • the illustration relates to the operating state of the blading, in which the damping element 9 is pressed against the surfaces 1 and 3 by the centrifugal force.
  • the damping element 9 is dimensioned such that the smallest possible distances 13 to the rotor 5 or to the left blade neck 14 occur.
  • the center of gravity 12 in the lower region of the damping element that is to say close to the contact surface 3
  • the reaction force acting on the contact surface 3 when the two adjacent blades 6 move relative to one another is very much greater than the force acting on the contact surface 1.
  • an oscillation of the blades at area 1 is converted into friction energy.
  • a frictional movement in area 3 should be prevented or minimized. This is achieved by the asymmetrical design for shifting the center of gravity as close as possible to area 3.
  • reaction forces are shown in the lower part of the figure again on an enlarged view of the damping element 9 and the adjacent blade platforms or blade necks.
  • the reaction force R1 acting on the contact surface 1 is substantially smaller than the reaction force R3 acting on the contact surface 3. This distribution of forces results from the position of the center of gravity 12, at which the centrifugal force N acts, in conjunction with the ratio of the dimensions a - d indicated in the figure.
  • a blade damper is realized, which is particularly effective when adjacent blades only small relative movements to each other To run. This is achieved in that the damping element on clearly different radial positions on the adjacent blades attacks.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP01105747A 2000-03-22 2001-03-08 Aubage avec éléments amortisseurs Withdrawn EP1136653A3 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10014198 2000-03-22
DE10014198A DE10014198A1 (de) 2000-03-22 2000-03-22 Beschaufelung mit Dämpfungselementen

Publications (2)

Publication Number Publication Date
EP1136653A2 true EP1136653A2 (fr) 2001-09-26
EP1136653A3 EP1136653A3 (fr) 2003-10-15

Family

ID=7635892

Family Applications (1)

Application Number Title Priority Date Filing Date
EP01105747A Withdrawn EP1136653A3 (fr) 2000-03-22 2001-03-08 Aubage avec éléments amortisseurs

Country Status (3)

Country Link
US (1) US6450769B2 (fr)
EP (1) EP1136653A3 (fr)
DE (1) DE10014198A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2149674A2 (fr) 2008-08-01 2010-02-03 Rolls-Royce plc Amortisseur de vibrations
US10851661B2 (en) 2017-08-01 2020-12-01 General Electric Company Sealing system for a rotary machine and method of assembling same
CN114026311A (zh) * 2019-05-29 2022-02-08 赛峰飞机发动机公司 具有阻尼器的涡轮机组件

Families Citing this family (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN1252376C (zh) * 1999-05-14 2006-04-19 西门子公司 带有转子密封系统的流体机械
US6851932B2 (en) * 2003-05-13 2005-02-08 General Electric Company Vibration damper assembly for the buckets of a turbine
US7367123B2 (en) * 2005-05-12 2008-05-06 General Electric Company Coated bucket damper pin and related method
US7270517B2 (en) * 2005-10-06 2007-09-18 Siemens Power Generation, Inc. Turbine blade with vibration damper
DE102006041322A1 (de) * 2006-09-01 2008-04-24 Rolls-Royce Deutschland Ltd & Co Kg Dämpfungs- und Dichtungssystem für Turbinenschaufeln
US8137072B2 (en) * 2008-10-31 2012-03-20 Solar Turbines Inc. Turbine blade including a seal pocket
US8393869B2 (en) 2008-12-19 2013-03-12 Solar Turbines Inc. Turbine blade assembly including a damper
US8834123B2 (en) * 2009-12-29 2014-09-16 Rolls-Royce Corporation Turbomachinery component
FR2962481B1 (fr) * 2010-07-12 2012-08-31 Snecma Propulsion Solide Amortisseur de vibrations a bras de levier pour aube d'un rotor de moteur a turbine a gaz
US8876478B2 (en) 2010-11-17 2014-11-04 General Electric Company Turbine blade combined damper and sealing pin and related method
US8915718B2 (en) * 2012-04-24 2014-12-23 United Technologies Corporation Airfoil including damper member
US9140132B2 (en) 2012-05-31 2015-09-22 Solar Turbines Incorporated Turbine blade support
DE102012106789B4 (de) * 2012-07-26 2022-10-27 Ihi Charging Systems International Gmbh Verstellbarer Leitapparat für eine Turbine, Turbine für einen Abgasturbolader und Abgasturbolader
US9309782B2 (en) 2012-09-14 2016-04-12 General Electric Company Flat bottom damper pin for turbine blades
US9353629B2 (en) 2012-11-30 2016-05-31 Solar Turbines Incorporated Turbine blade apparatus
US10385701B2 (en) 2015-09-03 2019-08-20 General Electric Company Damper pin for a turbine blade
US10443408B2 (en) 2015-09-03 2019-10-15 General Electric Company Damper pin for a turbine blade
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
DE102016205997A1 (de) * 2016-04-11 2017-10-12 MTU Aero Engines AG Leitschaufelsegment
US10662784B2 (en) 2016-11-28 2020-05-26 Raytheon Technologies Corporation Damper with varying thickness for a blade
US10731479B2 (en) * 2017-01-03 2020-08-04 Raytheon Technologies Corporation Blade platform with damper restraint
US10677073B2 (en) 2017-01-03 2020-06-09 Raytheon Technologies Corporation Blade platform with damper restraint
GB2573520A (en) * 2018-05-08 2019-11-13 Rolls Royce Plc A damper
DE102018221533A1 (de) 2018-12-12 2020-06-18 MTU Aero Engines AG Turbomaschinen Schaufelanordnung

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3666376A (en) * 1971-01-05 1972-05-30 United Aircraft Corp Turbine blade damper
US4182598A (en) * 1977-08-29 1980-01-08 United Technologies Corporation Turbine blade damper
SU1127979A1 (ru) * 1983-02-23 1984-12-07 Предприятие П/Я Р-6837 Рабочее колесо турбомашины
EP0509838A1 (fr) * 1991-04-19 1992-10-21 General Electric Company Amortissement des vibrations des aubes de turbines à gaz

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4872812A (en) * 1987-08-05 1989-10-10 General Electric Company Turbine blade plateform sealing and vibration damping apparatus
US4872810A (en) * 1988-12-14 1989-10-10 United Technologies Corporation Turbine rotor retention system
US4936749A (en) * 1988-12-21 1990-06-26 General Electric Company Blade-to-blade vibration damper
US5478207A (en) * 1994-09-19 1995-12-26 General Electric Company Stable blade vibration damper for gas turbine engine
US6042336A (en) * 1998-11-25 2000-03-28 United Technologies Corporation Offset center of gravity radial damper

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3666376A (en) * 1971-01-05 1972-05-30 United Aircraft Corp Turbine blade damper
US4182598A (en) * 1977-08-29 1980-01-08 United Technologies Corporation Turbine blade damper
SU1127979A1 (ru) * 1983-02-23 1984-12-07 Предприятие П/Я Р-6837 Рабочее колесо турбомашины
EP0509838A1 (fr) * 1991-04-19 1992-10-21 General Electric Company Amortissement des vibrations des aubes de turbines à gaz

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2149674A2 (fr) 2008-08-01 2010-02-03 Rolls-Royce plc Amortisseur de vibrations
EP2149674A3 (fr) * 2008-08-01 2013-05-01 Rolls-Royce plc Amortisseur de vibrations
US10851661B2 (en) 2017-08-01 2020-12-01 General Electric Company Sealing system for a rotary machine and method of assembling same
CN114026311A (zh) * 2019-05-29 2022-02-08 赛峰飞机发动机公司 具有阻尼器的涡轮机组件
CN114026311B (zh) * 2019-05-29 2024-04-02 赛峰飞机发动机公司 具有阻尼器的涡轮机组件

Also Published As

Publication number Publication date
US20010024614A1 (en) 2001-09-27
US6450769B2 (en) 2002-09-17
EP1136653A3 (fr) 2003-10-15
DE10014198A1 (de) 2001-09-27

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