EP2019188A1 - Etage de rotor comprenant un dispositif d'amortissement - Google Patents

Etage de rotor comprenant un dispositif d'amortissement Download PDF

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Publication number
EP2019188A1
EP2019188A1 EP07014624A EP07014624A EP2019188A1 EP 2019188 A1 EP2019188 A1 EP 2019188A1 EP 07014624 A EP07014624 A EP 07014624A EP 07014624 A EP07014624 A EP 07014624A EP 2019188 A1 EP2019188 A1 EP 2019188A1
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EP
European Patent Office
Prior art keywords
groove
damping element
blade stage
cross
blade
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Withdrawn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
EP07014624A
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German (de)
English (en)
Inventor
Walter Gehringer
Richard Geist
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 EP07014624A priority Critical patent/EP2019188A1/fr
Publication of EP2019188A1 publication Critical patent/EP2019188A1/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Withdrawn legal-status Critical Current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
    • 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
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • 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
    • F01D5/24—Blade-to-blade connections, e.g. for damping vibrations using wire or the like
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/31—Application in turbines in steam turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise

Definitions

  • the invention relates to a blade stage of a turbomachine with arranged over the circumference of a rotor blades, which blades each have a circumferentially extending recess so that the individual recesses of the blades are on a circular perimeter, wherein in the recesses extending in the circumferential direction Damping element is arranged.
  • the blades of turbomachinery are regularly subject to high mechanical loads.
  • High speeds produce in the blade profile due to the centrifugal forces enormous tensile stresses, which lead to deformations, in particular for elongation of the blades.
  • Pressure differences across the blades, especially at reaction stages, also generate a force acting in the axial direction.
  • These loads are superimposed by dynamic loads resulting, for example, from a vibration excitation.
  • the vibration excitation can be generated, for example, with long low-pressure paddles, only from periodic passing of adjacent components, for example by passing a Leitbeschaufelung.
  • Particularly high loads from the excitation arise for so-called control wheels which are arranged behind a nozzle group, as is often the case, for example, with steam turbines.
  • the nozzle group acts on the control wheel usually at several points of the circumference with a steam flow, so that the control wheel sweeps over the steam flow at periodic intervals depending on the speed.
  • This extreme load leads even to massive blade assemblies, for example, with blade stages with shroud, to a vibrational excitation that can exceed allowable loads.
  • a constructive solution to counteract this suggestion is the blade assembly to be provided with a circumferentially extending damping mechanism.
  • a circumferentially extending damping wire is provided, which is regularly formed with a round cross section and is inserted into a recess located in the circumferential direction of a closed shroud.
  • the damping wire is not driven away from the centrifugal force from this recess, it is common to deform the cover plates of the shroud composite by means of a rolling process to the extent that the radially outwardly facing opening of the recess at least partially closes and the damping wire is anchored positively in the shroud , Due to the centrifugal forces occurring during operation, the damping wire engages the components of the shroud closing the recess and makes it difficult to move the blades relative to each blade as a result of the frictional forces between the damping wire and the firing inner wall of the recess.
  • this new damping element can be expanded by separating in the middle, without having to make a new blade stage as usual today.
  • the object is achieved by means of a blade stage of the type mentioned, in which the damping element has a cross-sectional profile with respect to the lateral end portions substantially protruding center part, wherein the middle part points radially inward.
  • the particular advantage of the damping element according to the invention is that the cross-sectional profile of the damping element is deformed under the action of centrifugal force such that increases the distance between the two end portions and reduces the board of the middle part relative to the lateral end portions. This allows an application of the damping element to boundary surfaces of the recess, so that the force required for a friction force normal force as a function of the centrifugal force and the damping element is able to reduce the vibrations resulting from excitation.
  • the damping element according to the invention can be used for example from radially outside into the circumferential groove.
  • the damping element acts by the centrifugal force, it is expedient if it is not a closed ring but is designed to be open in the circumferential direction.
  • the groove can essentially have any desired cross-sectional shape, a depth extension being defined starting from the slot opening to the lowest point of the groove.
  • the lowest point of the groove is at the same time the groove base and, if appropriate, laterally adjoining side walls of the groove, which extend up to the slot opening, are referred to as flanks.
  • a radial depth of the groove wherein in particular in a design with shroud a depth extension of the groove, starting from the groove opening radially inward makes sense, the middle part of the Dämpyogngsijns projecting towards the groove bottom.
  • An advantageous development of the invention provides that the groove widens laterally in the depth direction, such that the slot opening is narrowed on both sides by a circumferentially extending projection on lateral flanks of the groove and one lateral end section of the damping element is arranged in the groove behind the projection , so that the damping element is anchored positively in the groove against radial leakage.
  • the advantage of this embodiment is that the end portions can be supported against the projection on both sides under the action of centrifugal force and thus a particularly good investment of the damping element is made to the blade, resulting in a particularly efficient damping result.
  • the cross-sectional profile of the damping element is a curved cross-sectional profile having a substantially convex and a substantially concave side, the concave side advantageously pointing radially outward.
  • the cross-sectional profile of this training will have the tendency under the influence of centrifugal force widening, which in a prescribed manner improves the damping effect.
  • the groove is undercut on both sides, with a first undercut and a second undercut, wherein in each case a lateral end portion of the cross section of the damping element is arranged behind an undercut in the groove.
  • These undercuts have the same effect as the narrowing projections of the embodiment already described above.
  • the damping element is designed elastically such that the two end portions of the cross section can be elastically approach each other.
  • This embodiment allows under an elastic deformation insertion of the damping element in an undercut groove shape or a groove shape with narrowing on both sides in the region of the slot opening, so that the damping element is held positively in the groove. This can lead to a latching of the damping element in the groove when the narrowing projections are formed accordingly. It is also conceivable that the groove is not provided with narrowing projections and the damping element is held only non-positively in the groove.
  • the form-fitting design has the advantage that the damping element itself is exposed on the one hand less strong in the circumferential direction resulting tensile stresses and on the other hand attenuates particularly efficient due to the investment in the constrictions or undercuts.
  • FIG. 1 shows a blade 1 with a recess 2, wherein the blade 1 is part of a running stage 3 forming blade assembly.
  • the blade 1 is anchored by means of a blade root 4 in a rotor 5, wherein in the radial extent to the outside of the blade root 4, an airfoil 6 connects, which is provided with the recess 2.
  • a cover plate 7, which together with the cover plates 7 of the adjacent blades 1 of the blade stage 3 is a circumferentially extending 8 shroud 9 results.
  • the recesses 2 in the blades 1 according to the FIG. 1 of all the blades 1 of the blade stage 3 lie on a circular circumferentially extending line. Through these recesses 2 extends through a damping element 10 of substantially U-shaped cross-section in the illustrated manner.
  • the damping element 10 is not formed closed in the circumferential direction and the joints of the damping element 10 are unconnected to a circumferential position, not shown.
  • the damping element 10 has a cross-sectional profile 12 with a middle part 13 and two lateral end sections 14.
  • the middle part 13 protrudes radially inwards relative to the lateral end sections 14 and accordingly lies on a small diameter.
  • Both the groove 11 and the recess 2 are to its radially outer opening or groove opening 15 on both sides of narrows a projection 16.
  • the groove 11 and the recess 2 are adapted in shape to the shape of the damping element 10, so that it comes to a possible flat contact between the two elements.
  • the groove 11 of two oblique edges 17 which extend in the depth direction 18 to the groove bottom 19, limited.
  • the two projections 16, which narrow the slot opening 15 with respect to the width of the groove 11 in a further depth extension 18, are formed as undercuts 20,21.
  • the damping element 10 is elastic and is pressed in the course of assembly in the groove 11 and the recess 2 under elastic deformation, so that it engages with the end portions 14 behind the projections 16 and the undercuts 20,21.
  • the centrifugal force pulls the damping element 10 radially outwardly, widening in the width direction of the cross-sectional profile and the contact pressure between the projections 16 and the end portions 14 increases with increasing centrifugal force.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP07014624A 2007-07-25 2007-07-25 Etage de rotor comprenant un dispositif d'amortissement Withdrawn EP2019188A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP07014624A EP2019188A1 (fr) 2007-07-25 2007-07-25 Etage de rotor comprenant un dispositif d'amortissement

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP07014624A EP2019188A1 (fr) 2007-07-25 2007-07-25 Etage de rotor comprenant un dispositif d'amortissement

Publications (1)

Publication Number Publication Date
EP2019188A1 true EP2019188A1 (fr) 2009-01-28

Family

ID=39047558

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EP07014624A Withdrawn EP2019188A1 (fr) 2007-07-25 2007-07-25 Etage de rotor comprenant un dispositif d'amortissement

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EP (1) EP2019188A1 (fr)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2218875A1 (fr) * 2009-02-17 2010-08-18 Siemens Aktiengesellschaft Bandage d'aube dans une turbomachine
CN103758579A (zh) * 2014-01-26 2014-04-30 中国船舶重工集团公司第七�三研究所 船用汽轮机自带冠叶片外包拉筋减振结构及其装配方法
CN109695479A (zh) * 2018-08-22 2019-04-30 杭州汽轮机股份有限公司 一种工业汽轮机用高转速高负荷低压级动叶片
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
CN114922695A (zh) * 2022-04-22 2022-08-19 沈阳德瓦特汽轮动力有限责任公司 一种工业汽轮机调节级动叶片围带及其优化方法
US11536144B2 (en) 2020-09-30 2022-12-27 General Electric Company Rotor blade damping structures
US11739645B2 (en) 2020-09-30 2023-08-29 General Electric Company Vibrational dampening elements

Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1165005A (en) * 1914-05-14 1915-12-21 Westinghouse Machine Co Blade construction for elastic-fluid turbines.
DE477319C (de) * 1927-01-29 1929-06-05 Escher Wyss Maschf Ag Schaufelung fuer Laufraeder von Dampf- und Gasturbinen, bei denen das Treibmittel die Laufschaufelungen in allen Stufen in demselben axialen Sinn durchstroemt
GB797521A (en) * 1954-11-08 1958-07-02 Parsons C A & Co Ltd Improvements in and relating to turbine blades
GB898175A (en) * 1960-03-28 1962-06-06 Parsons & Marine Eng Turbine Improvements in and relating to the blading of turbines or like fluid flow machines
DE1551180A1 (de) * 1965-12-06 1969-06-19 Gen Electric Leitschaufelkranz fuer Turbomaschinen,insbesondere Gasturbinen-Triebwerke
GB1287223A (en) * 1970-02-02 1972-08-31 Ass Elect Ind Improvements in or relating to turbine blading
JPS60195301A (ja) * 1984-03-16 1985-10-03 Hitachi Ltd 動翼連結構造
FR2674569A1 (fr) * 1991-03-27 1992-10-02 Snecma Disque ailete monobloc avec amortissement des vibrations pour turbomachine.
DE29701592U1 (de) * 1996-02-05 1997-03-27 Asea Brown Boveri Ag, Baden, Aargau Thermische Strömungsmaschine
JPH09324603A (ja) * 1996-06-10 1997-12-16 Mitsubishi Heavy Ind Ltd 高速回転機械のタービン動翼
EP1441108A2 (fr) * 2003-01-27 2004-07-28 United Technologies Corporation Amortisseur pour stator de turbomachine

Patent Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1165005A (en) * 1914-05-14 1915-12-21 Westinghouse Machine Co Blade construction for elastic-fluid turbines.
DE477319C (de) * 1927-01-29 1929-06-05 Escher Wyss Maschf Ag Schaufelung fuer Laufraeder von Dampf- und Gasturbinen, bei denen das Treibmittel die Laufschaufelungen in allen Stufen in demselben axialen Sinn durchstroemt
GB797521A (en) * 1954-11-08 1958-07-02 Parsons C A & Co Ltd Improvements in and relating to turbine blades
GB898175A (en) * 1960-03-28 1962-06-06 Parsons & Marine Eng Turbine Improvements in and relating to the blading of turbines or like fluid flow machines
DE1551180A1 (de) * 1965-12-06 1969-06-19 Gen Electric Leitschaufelkranz fuer Turbomaschinen,insbesondere Gasturbinen-Triebwerke
GB1287223A (en) * 1970-02-02 1972-08-31 Ass Elect Ind Improvements in or relating to turbine blading
JPS60195301A (ja) * 1984-03-16 1985-10-03 Hitachi Ltd 動翼連結構造
FR2674569A1 (fr) * 1991-03-27 1992-10-02 Snecma Disque ailete monobloc avec amortissement des vibrations pour turbomachine.
DE29701592U1 (de) * 1996-02-05 1997-03-27 Asea Brown Boveri Ag, Baden, Aargau Thermische Strömungsmaschine
JPH09324603A (ja) * 1996-06-10 1997-12-16 Mitsubishi Heavy Ind Ltd 高速回転機械のタービン動翼
EP1441108A2 (fr) * 2003-01-27 2004-07-28 United Technologies Corporation Amortisseur pour stator de turbomachine

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2218875A1 (fr) * 2009-02-17 2010-08-18 Siemens Aktiengesellschaft Bandage d'aube dans une turbomachine
CN103758579A (zh) * 2014-01-26 2014-04-30 中国船舶重工集团公司第七�三研究所 船用汽轮机自带冠叶片外包拉筋减振结构及其装配方法
CN103758579B (zh) * 2014-01-26 2015-12-02 中国船舶重工集团公司第七�三研究所 船用汽轮机自带冠叶片外包拉筋减振结构的装配方法
CN109695479A (zh) * 2018-08-22 2019-04-30 杭州汽轮机股份有限公司 一种工业汽轮机用高转速高负荷低压级动叶片
CN109695479B (zh) * 2018-08-22 2023-12-29 杭州汽轮动力集团股份有限公司 一种工业汽轮机用高转速高负荷低压级动叶片
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
US11536144B2 (en) 2020-09-30 2022-12-27 General Electric Company Rotor blade damping structures
US11739645B2 (en) 2020-09-30 2023-08-29 General Electric Company Vibrational dampening elements
CN114922695A (zh) * 2022-04-22 2022-08-19 沈阳德瓦特汽轮动力有限责任公司 一种工业汽轮机调节级动叶片围带及其优化方法

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