EP2434098A1 - Schaufelanordnung und zugehörige Gasturbine - Google Patents

Schaufelanordnung und zugehörige Gasturbine Download PDF

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Publication number
EP2434098A1
EP2434098A1 EP10179376A EP10179376A EP2434098A1 EP 2434098 A1 EP2434098 A1 EP 2434098A1 EP 10179376 A EP10179376 A EP 10179376A EP 10179376 A EP10179376 A EP 10179376A EP 2434098 A1 EP2434098 A1 EP 2434098A1
Authority
EP
European Patent Office
Prior art keywords
blade
blades
group
pairs
pair
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Withdrawn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
EP10179376A
Other languages
German (de)
English (en)
French (fr)
Inventor
Andreas Kayser
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 EP10179376A priority Critical patent/EP2434098A1/de
Priority to PL11766921T priority patent/PL2603669T3/pl
Priority to RU2013118726/06A priority patent/RU2580447C2/ru
Priority to CN201180046192.4A priority patent/CN103119248B/zh
Priority to US13/825,357 priority patent/US9341067B2/en
Priority to EP11766921.8A priority patent/EP2603669B1/de
Priority to JP2013529627A priority patent/JP5543032B2/ja
Priority to PCT/EP2011/066287 priority patent/WO2012038406A1/de
Priority to ES11766921.8T priority patent/ES2533069T3/es
Publication of EP2434098A1 publication Critical patent/EP2434098A1/de
Withdrawn legal-status Critical Current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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/26—Antivibration means not restricted to blade form or construction or to blade-to-blade connections or to the use of particular materials
    • 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

Definitions

  • the invention relates to a blade assembly, comprising a rotor and a plurality of blades distributed along the circumference of the rotor in a ring, wherein two immediately adjacent blades of the ring form a blade pair, between the blades of a damping element is arranged and wherein by a centrifugal force acting in the radial direction a rotation of the rotor about a rotor axis, the respective damping element comes into contact with the two blades of the blade pair associated therewith.
  • damping elements generally loose body are used, which rest in the idle 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 relative movement between the blades due to vibrations can be converted into heat energy due to the friction between the respective blade platforms and the adjacent damping element. This dampens the vibrations and leads overall to a reduced vibration load of the blade assembly.
  • a vane arrangement in which at least two damping elements are arranged in succession between adjacent blades in the circumferential direction of the rotor in order to achieve effective damping of the entire blade arrangement.
  • the damping elements disclosed in this document are designed in divergent form in order to be able to damp as many different vibration modes as possible.
  • contact areas can be converted to vibration damping by friction effect vibration energy in heat energy.
  • the contact areas formed between the individual damping elements only have the form of a line contact, with which an only moderately pronounced damping effect is associated.
  • the invention has for its object to provide a blade assembly with damping elements, damped even more effectively with the unwanted vibrations and reduces the tendency of the blades to vibrate due to excitation or even avoided.
  • the blade ring has at least two blade pairs with different damping elements.
  • the invention is based on the finding that the coupling of the blades with damping elements also increases the natural frequencies in relation to the freestanding blades.
  • all blades of a blade ring are detuned to an identical extent.
  • identical blades with inherent identical frequencies for different vibration modes behave in the blade ring as if the respective blades have different natural frequencies for the vibration modes, but uncoupled.
  • the size of the natural frequencies of adjacent blades can be adjusted so that immediately adjacent blades differ significantly in terms of their natural frequencies.
  • the damping elements are pressed against the lower side of adjacent blade platforms by blades by the centrifugal force.
  • the relative motion of adjacent blades creates friction between the damper and the blade platform, causing a coupling.
  • the finding is based on the fact that in addition to the dissipation also causes a frequency shift of the natural frequencies of adjacent blades by the coupling. This effect can be used to alternately detune the blades alternately. Alternating detuned blades are especially prone to flutter.
  • the achievable with the damping elements stroke of the frequency shift is significantly greater than in the previous measures.
  • a tendency Blade rim according to the invention significantly less flutter than blade rings with blades, in which the blades themselves have different natural frequencies.
  • the blade ring according to the invention due to the use of different damping elements between a pair of blades is much more resistant to self-excited vibrations and the so-called flutter than conventional blade rings.
  • the different damping elements can replace the otherwise common and conventional measures for adjusting the natural frequencies, which is also known as "Mistuning". These were z.
  • the shortening of the trailing edge on the blade tip the grinding of the blade profile or the drilling of blade tip side holes in the blade.
  • the invention has the particular advantage that the blade profile of the relevant blade can remain unchanged by misting the blades with the two damping elements associated with each blade and thus no performance losses, neither in the stage nor in the turbomachine, as in shortening the trailing edges, go along ,
  • the previous measures for adjusting the natural frequencies of the blades can thus be omitted.
  • time and cost savings occur because the iterative process of repeatedly machining the blades with repeated vibration measurements can be completely eliminated.
  • each blade of the blade ring is associated with two pairs of blades, wherein two or more groups of blade pairs are provided, within which the damping elements are identical and their damping elements differ from group to group.
  • a first group and a second group of blade pairs are provided, wherein, provided that the number of blades of the blade ring this allows each vane pair of one group to be circumferentially adjacent to one vane pair of the other group. Unless the number of blades makes this possible, only a majority of the blades of the blade ring is arranged in the order given. As a result, an at least largely circulating ABAB series of blade pairs or damping elements is given, which applies to the following advantageous embodiments in an analogous manner.
  • a particularly preferred embodiment provides that a first group and a second group of blade pairs are provided, wherein each pair of blades of the first group of a pair of blades of the first group and a blade pair of the second group is adjacent (AABBAABB series).
  • An equally effective frequency detuning can be achieved if a first group, a second group and a third group of pairs of blades are provided, wherein each pair of blades is adjacent to one of the three groups of two pairs of blades, which respectively belong to one of the two other groups (ABCABC-). Line).
  • the different damping elements differ in terms of size, mass, the cross-sectional contour of the material and / or the coupling contact with the blades.
  • damping elements can be produced with little effort, without adapting the casting and the contour of blades for the different groups.
  • the damping elements differ in their geometric shape.
  • the damping elements can also differ in their masses to effectively damp by combining with suitable geometric shapes as large a number of different vibration modes.
  • the friction conditions coefficient of friction, roughness
  • the contact areas can be influenced in order to also enable a targeted damping of several modes, even in increased frequency ranges.
  • damping elements are preferably rod-shaped.
  • the damping element of a blade pair is designed in several parts. It comprises - seen in the circumferential direction of the rotor - two (or more) successively arranged sub-elements, which are preferably rod-shaped.
  • one of the sub-elements has a cross-section in the form of a wedge and the other sub-element has a cross section in the form of a quarter circle.
  • the advantages of the invention can be achieved particularly efficiently.
  • the damping elements made of steel or ceramic, ie materials with which an effective damping can be realized.
  • FIG. 1 a part of the blade ring 10 is shown by of a rotor 12 along the circumference U distributed blades 14 of an axial turbomachine not shown.
  • the axial turbomachine can be designed, for example, as a compressor, steam turbine or stationary gas turbine, which comprises the blade arrangement 11 with the rim 10 of blades 14. These each have a blade root 16 for attachment of the respective blade 14 on the rotor 12.
  • the blade root 16 is designed in a known manner dovetail-shaped or fir tree-shaped. For positive attachment to the rotor 12, this is inserted into corresponding to the blade root 16 retaining grooves of the rotor 12, so that upon rotation of the rotor 12, the blades 14 are held securely.
  • the retaining grooves and thus also the blade roots 16 extend mainly in the axial direction and are inclined with respect to a machine axis at an angle of attack.
  • the blade root 16 merges into a blade neck (not further described), to which a platform 18 adjoins.
  • Their platform surface 20 limits the flow channel of the axial turbomachine.
  • An aerodynamic curved airfoil 22 is freestanding on the platform surface 20.
  • either damping elements of type A or B are provided between the platforms 18 of immediately adjacent blades 14.
  • Both types A, B of damping elements are rod-shaped, for example as damper wires.
  • the damping elements A, B each have a circular cross-section.
  • the type A attenuation elements have a larger diameter than the type B attenuation elements. Both damping elements A, B are therefore cylindrical.
  • each damping element A is applied to two immediately adjacent vanes pair a forming blades 14.
  • each damping element B abuts against two immediately adjacent vanes 14 forming a blade pair b. Due to the circular cross-section of the damping elements A, B they are each to form a line contact on each blade 14 at. Since each blade 14 has a damping element A, B on both sides of the blade neck, each blade 14 belongs to both blade pairs a, b. According to the in FIG.
  • a first group 24 of pairs of blades a and a second group 26 of pairs of blades b is provided, wherein each pair of blades a (or b) of the one group 24 (or 26) seen in the circumferential direction of a blade pair b (or a) is adjacent to the other group 26 (or 24). Due to this configuration, the damping elements A, B in the circumferential direction U are alternately lined up in succession between two immediately adjacent blades 14. This embodiment is also referred to as an arrangement with an ABAB pattern.
  • FIG. 2 and the other figures are identical features with the same reference numerals.
  • the embodiment according to FIG. 2 differs from the design FIG. 1 only in the form and shape of the respective second damping element.
  • damping elements B ' are provided, which in principle have the same diameter as the damping elements of the type A, but the cross-sectional shape of the damping elements B' is not circular, but circular segment-shaped.
  • the shape of the circle segment is chosen so that the center of the complete circle is still enclosed by the circular segment cross-sectional area. Due to the circular segment shape, the damping element B 'is located on the one (the in FIG. 2 vane 14 of the pair of blades b shown on the right) and on the other (the in FIG.
  • the blade arrangement 11 shown thus comprises a first group 24 of blade pairs a and a second group 26 of blade pairs b ', wherein each blade pair a (or b') of the one group 24 (or 26) seen in the circumferential direction U, of a blade pair b '(or a) is adjacent to the other group 26 (or 24).
  • each blade pair a (or b') of the one group 24 (or 26) seen in the circumferential direction U, of a blade pair b '(or a) is adjacent to the other group 26 (or 24).
  • it is a series with an ABAB pattern, in which the specified sequence of the damping elements A, B 'or the blade pairs a, b' along the circumference U of the blade ring 10 is repeated in a regular sequence.
  • FIG. 3 shows the section of the development of the blade ring 10 with blades 14 after FIG. 2 , wherein instead of the damping elements A and B 'in the replacement model of the damping elements A, B' to be used springs 28, 30 are shown.
  • the damping element A is a symmetrical or cylindrical damper
  • a translational spring 28 for coupling the two blades 14 of the blade pair a is shown in the replacement model.
  • the translation springs 28 have a coupling stiffness C1, C3, and the torsion spring has a coupling stiffness C2.
  • the entire coupling rigidity of a single blade 14 is then obtained by the parallel connection of the coupling stiffness C3 on the one hand and the coupling stiffnesses C2 and C1.
  • the springs can also have non-linear properties.
  • the row with the ABAB pattern of damping elements A, B and A, B ' causes an alternating Frequency detuning of blades 14, whereby the natural frequencies of immediately adjacent blades 14 are shifted solely by the use of different damping elements A, B, B '.
  • the shift of the frequencies in operation prevents the propagation of circulating vibration waves in the shovel, which makes it difficult to flutter the blades 22. This increases the operating range of the axial turbomachine and ensures safe operation.
  • FIG. 4 Further embodiments for detuning the natural frequencies of vibration modes of blades 14 are shown in FIG. 4 .
  • FIG. 5 FIG. 6 and FIG. 7 shown. Therein, further rows with different patterns are given by way of example.
  • FIG. 4 shows a new series with three groups 24, 26, 27 of blade pairs a, b, d, each pair of blades a and b and d of a group 24 and 26 and 27 of two blade pairs b, d and a, d or a, b is adjacent, each one of the other two groups 26, 27 and 24, 27 and 24, 26 are associated.
  • a damping element of the type A is provided between the two blades 14 of each blade pair a. This is circular in cross-section and has a rather larger diameter.
  • Each pair of blades b is assigned a damping element of the type B, which is also circular in cross-section. However, compared with the damping element of type A, the diameter of the damping element of type B is smaller.
  • Each pair of blades d is assigned a damping element of type D.
  • This embodiment corresponds to its configuration of the embodiment of the damping element of the type B 'from FIG. 2 , This embodiment therefore has an ABCABC series.
  • FIG. 5 a further vane assembly 11 is shown in which a first group 24 and a second group 26 of vane pairs a, b "are provided, each vane pair a of the first group 24 of a vane pair a of the first group 24 and a vane pair b" of the second Group 26 is adjacent.
  • a damping element of the type A is provided between the two blades 14 of each blade pair a. This is circular in cross-section and has a rather larger diameter.
  • Each pair of blades b is associated with a damping element of the type B" whose cross section is circular segmented. This embodiment can be described as AABBAABB series.
  • FIG. 6 An alternative embodiment with an ABBABB series is shown in FIG. 6 shown schematically. Again, the different types A, A, B "of the damping elements are distributed along the circumference between the blades 14 of the blade ring 10 in a recurring order.
  • FIG. 7 another ABAB series of modified damping elements E, H in a blade ring.
  • a first group 24 of pairs of blades e 14 has, in each case, a damping element of type E between the respectively associated blades 14. Also, the damping element E is designed in principle rod-shaped.
  • each blade 14 of the blade pair e associated with it H is designed in several parts and comprises in each case two parts H1, H2
  • the part H1 is triangular in cross-section and the part H2 has the contour of a circular sector in the form of a quarter circle in cross-section This results in two surface contacts and one line contact per damping element H.
  • FIGs. 4 . 5 . 6 and 7 shown blade assemblies 11 have higher coupling stiffness than the embodiments FIG. 1 respectively.
  • these blade arrangements 11 are particularly suitable if a frequency detuning of blades 14 of a blade ring 10 is to be brought about with the aid of different damping elements in order to prevent the flutter excitation of the blades 14.
  • one of the aforementioned blade assemblies 11 is particularly applicable.
  • the number of blades in the ring is not divisible by two or by three, to use a larger number of damping element types per blade ring 10.
  • the blade ring 10 has a number of blades 14 which is not an integral multiple of the number of damping element types of the row, it goes without saying for all embodiments that only a majority of the successive blade pairs (a, b, b ', b ", d), e, h) are members of the series and form them, the remaining pair of blades are then provided with suitable damping elements which can not be subordinate to the row, in which case it is also possible for the blade ring 10 to have two adjacent blades 14 having identical or approximate frequency characteristics.
  • damping element types are conceivable and can be combined with each other, so that the embodiments shown here are in no way to be understood as limiting. Even the circumferentially alternating arrangement of damping elements of the type B 'and of the type B "leads to an alternating frequency detuning due to the coupling rigidity already mentioned above, which varies from blade to blade.
  • grooves grooved damping elements
  • other series of damping element types are also possible, for example an ABCBABCBA series.
  • the invention thus relates to a blade assembly 11 having a rotor 12 and a plurality of blades 14 distributed along the circumference U of the rotor 12 in a ring 10, wherein two immediately adjacent blades 14 of the ring 10 a Shovel pair a, b, b ', b ", d, e, h form, between whose blades 14, a damping element A, B, B', B", D, E, H is arranged, and wherein by acting in the radial direction R.
  • the blade ring 10 have at least two blade pairs a, b, b ', b ", d, e, h with different damping elements A, B, B ', B ", D, E, H has.

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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)
EP10179376A 2010-09-24 2010-09-24 Schaufelanordnung und zugehörige Gasturbine Withdrawn EP2434098A1 (de)

Priority Applications (9)

Application Number Priority Date Filing Date Title
EP10179376A EP2434098A1 (de) 2010-09-24 2010-09-24 Schaufelanordnung und zugehörige Gasturbine
PL11766921T PL2603669T3 (pl) 2010-09-24 2011-09-20 Zespół łopatkowy i odpowiednia turbina gazowa
RU2013118726/06A RU2580447C2 (ru) 2010-09-24 2011-09-20 Система лопаток и соответствующая газовая турбина
CN201180046192.4A CN103119248B (zh) 2010-09-24 2011-09-20 叶片装置和所属的燃气轮机
US13/825,357 US9341067B2 (en) 2010-09-24 2011-09-20 Blade arrangement and associated gas turbine
EP11766921.8A EP2603669B1 (de) 2010-09-24 2011-09-20 Schaufelanordnung und zugehörige Gasturbine
JP2013529627A JP5543032B2 (ja) 2010-09-24 2011-09-20 ブレード配列、及び当該ブレード配列を具備するガスタービン
PCT/EP2011/066287 WO2012038406A1 (de) 2010-09-24 2011-09-20 Schaufelanordnung und zugehörige gasturbine
ES11766921.8T ES2533069T3 (es) 2010-09-24 2011-09-20 Disposición de palas y turbina de gas correspondiente

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP10179376A EP2434098A1 (de) 2010-09-24 2010-09-24 Schaufelanordnung und zugehörige Gasturbine

Publications (1)

Publication Number Publication Date
EP2434098A1 true EP2434098A1 (de) 2012-03-28

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Family Applications (2)

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EP10179376A Withdrawn EP2434098A1 (de) 2010-09-24 2010-09-24 Schaufelanordnung und zugehörige Gasturbine
EP11766921.8A Active EP2603669B1 (de) 2010-09-24 2011-09-20 Schaufelanordnung und zugehörige Gasturbine

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP11766921.8A Active EP2603669B1 (de) 2010-09-24 2011-09-20 Schaufelanordnung und zugehörige Gasturbine

Country Status (8)

Country Link
US (1) US9341067B2 (ja)
EP (2) EP2434098A1 (ja)
JP (1) JP5543032B2 (ja)
CN (1) CN103119248B (ja)
ES (1) ES2533069T3 (ja)
PL (1) PL2603669T3 (ja)
RU (1) RU2580447C2 (ja)
WO (1) WO2012038406A1 (ja)

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EP3078808A1 (de) * 2015-04-07 2016-10-12 Siemens Aktiengesellschaft Laufschaufelreihe für eine strömungsmaschine
WO2020131062A1 (en) * 2018-12-20 2020-06-25 Siemens Aktiengesellschaft Bladed rotor system and corresponding method of servicing

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US9194238B2 (en) * 2012-11-28 2015-11-24 General Electric Company System for damping vibrations in a turbine
EP2762678A1 (de) * 2013-02-05 2014-08-06 Siemens Aktiengesellschaft Verfahren zum Verstimmen eines Laufschaufelgitters
JP6366310B2 (ja) * 2014-03-18 2018-08-01 三菱日立パワーシステムズ株式会社 シール構造、動翼、及び回転機械
DE102014214270A1 (de) 2014-07-22 2016-02-18 MTU Aero Engines AG Schaufelgitter für eine Turbomaschine
US20170067347A1 (en) * 2015-09-03 2017-03-09 General Electric Company Slotted damper pin for a turbine blade
US10823192B2 (en) * 2015-12-18 2020-11-03 Raytheon Technologies Corporation Gas turbine engine with short inlet and mistuned fan blades
GB201702698D0 (en) 2017-02-20 2017-04-05 Rolls Royce Plc Fan
WO2018175356A1 (en) * 2017-03-22 2018-09-27 Siemens Aktiengesellschaft Alternately mistuned blades with modified under-platform dampers
JP7039355B2 (ja) * 2018-03-28 2022-03-22 三菱重工業株式会社 回転機械
JP6985197B2 (ja) * 2018-03-28 2021-12-22 三菱重工業株式会社 回転機械
DE102018208229A1 (de) * 2018-05-24 2019-11-28 MTU Aero Engines AG Turbomaschinenbaugruppe mit einer Verstimmeinrichtung zur unterschiedlichen Verstimmung von Eigenfrequenzen der Schaufeln
JP7235536B2 (ja) * 2019-02-28 2023-03-08 三菱重工業株式会社 回転機械
CN114542522A (zh) * 2022-02-21 2022-05-27 杭州汽轮机股份有限公司 一种压气机叶片阻尼器及装配方法

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Publication number Priority date Publication date Assignee Title
EP3078808A1 (de) * 2015-04-07 2016-10-12 Siemens Aktiengesellschaft Laufschaufelreihe für eine strömungsmaschine
WO2020131062A1 (en) * 2018-12-20 2020-06-25 Siemens Aktiengesellschaft Bladed rotor system and corresponding method of servicing
US11401815B2 (en) 2018-12-20 2022-08-02 Siemens Energy Global GmbH & Co. KG Bladed rotor system and corresponding method of servicing

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CN103119248B (zh) 2016-01-20
WO2012038406A1 (de) 2012-03-29
EP2603669B1 (de) 2015-01-28
JP5543032B2 (ja) 2014-07-09
PL2603669T3 (pl) 2015-07-31
RU2580447C2 (ru) 2016-04-10
US9341067B2 (en) 2016-05-17
US20130177427A1 (en) 2013-07-11
RU2013118726A (ru) 2014-10-27
ES2533069T3 (es) 2015-04-07
JP2013537953A (ja) 2013-10-07
CN103119248A (zh) 2013-05-22
EP2603669A1 (de) 2013-06-19

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