EP2098687A1 - Rotor pour une turbomachine - Google Patents

Rotor pour une turbomachine Download PDF

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Publication number
EP2098687A1
EP2098687A1 EP08004272A EP08004272A EP2098687A1 EP 2098687 A1 EP2098687 A1 EP 2098687A1 EP 08004272 A EP08004272 A EP 08004272A EP 08004272 A EP08004272 A EP 08004272A EP 2098687 A1 EP2098687 A1 EP 2098687A1
Authority
EP
European Patent Office
Prior art keywords
rotor
damping element
blade
blades
projection
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Withdrawn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
EP08004272A
Other languages
German (de)
English (en)
Inventor
Markus Kupetz
Heinrich Dr. Stüer
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 EP08004272A priority Critical patent/EP2098687A1/fr
Publication of EP2098687A1 publication Critical patent/EP2098687A1/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Withdrawn legal-status Critical Current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
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
    • 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
    • F05D2220/70—Application in combination with
    • F05D2220/72—Application in combination with a steam turbine
    • 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
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades
    • 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
    • F05D2250/10—Two-dimensional
    • F05D2250/12—Two-dimensional rectangular
    • 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
    • F05D2250/10—Two-dimensional
    • F05D2250/13—Two-dimensional trapezoidal
    • 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
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/182—Two-dimensional patterned crenellated, notched
    • 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 rotor for a turbomachine, wherein the rotor has circumferentially adjacent blades, wherein the rotor is formed along an axial direction, wherein the blades have a curved blade root, wherein the blade root is arranged in a blade groove in the rotor.
  • a steam turbine as an embodiment of a turbomachine, essentially two components are responsible for the conversion of the thermal energy of the steam into rotational energy.
  • this would be the rotatably mounted rotor and a housing arranged around the rotor.
  • the rotor has so-called. Blades, wherein guide vanes are arranged on the housing.
  • the operating frequencies are 50 Hz and 60 Hz, respectively, for steam turbines used in the municipal power supply area.
  • the rotational frequencies occurring during operation lead to unwanted vibrations of the blades in connection with the thermodynamic conditions of the steam. As a rule, cracks occur in the rotor blades, in the airfoil and / or in the blade roots.
  • the blade feet can be designed as so-called double-T, hammer or pine-tree feet. All these feet have in common that they are placed in a corresponding groove in the rotor. Furthermore, turbine blade feet are known which are bent. The bend results in a distribution of the transfer area between the rotor and the turbine blades. The transmitted forces can be better distributed, resulting in an extension of the life.
  • the turbine blades are arranged adjacent to each other on the circumference.
  • the turbine blades have blade plates disposed between the blade roots and the airfoil.
  • the rotor is formed according to the prior art such that between each two blade plates, a projection of the rotor is arranged.
  • the invention begins, the object of which is to provide a rotor which has blades arranged in such a way that vibrations of the blades during operation are effectively reduced.
  • a rotor for a turbomachine having circumferentially adjacent blades, wherein the rotor is formed along an axial direction, wherein the blades have a curved blade root, wherein the blade root is arranged in a blade groove in the rotor, wherein a damping element is arranged between the blades.
  • the invention thus goes the way to enable a power transmission not only between the blades and the rotor, but also to realize a power transmission between adjacent blades.
  • the power transmission takes place via the damping element, which is arranged between the blades.
  • the damping element is arranged such that a counterforce from the damping element leads to the blade to a damping of the vibration.
  • the damping element between the blade roots is caulked, with the applied clamping force leads to a pressing apart of the blades.
  • the damping element is arranged between two adjacent blade plates.
  • the blade plates are shaped in the blades so as to form a base that covers the blade root opposite the blade.
  • An arranged between the blade plates damping element can dampen vibration between two blades optimally.
  • the damping element is formed from a resilient material.
  • a resilient material has the advantage that a bending force is required in a bending of the damping element. If a damping element made of a resilient material is arranged between two blade plates and thereby inevitably has to be bent, a force is created on the blade plates after installation of the damping element. This force leads to a pressing apart of adjacent blades. A vibration of adjacent blades is thereby reduced.
  • the damping element essentially has the shape of a rod.
  • the damping element has a rectangular cross-section. As a result, the damping element is comparatively easy to manufacture.
  • the damping element has a trapezoidal or conical cross section. This leads to the advantage that during operation, a centrifugal force acting on the damping element due to the trapezoidal or conical sides arranged obliquely to the centrifugal force direction a force arises in the direction of the blade plates. This force caused by centrifugal force is a lateral force that further supports a pushing apart of the blades. As a result, a vibration during operation is further reduced.
  • the damping element has a projection which is arranged in a recess in the blade plate.
  • the protrusion of the damping element arranged in the protrusion constitutes an axial securing which is intended to prevent the damping element from becoming detached in an axial direction.
  • the damping element has a kink, which is arranged in a recess in the blade plate. Since the damping element is made of a resilient material, a kink in the damping element, which has a substantially triangular shape, can be used to serve as an axial securing element.
  • a trained as a simple kink securing element has the advantage that engages in the projection as a result of the elastic material of the damping element of the kink. Damage to the damping element is therefore almost impossible. In addition, an excellent axial securing of the damping element is ensured.
  • the FIG. 1 discloses a part of a rotor 1.
  • the rotor 1 is in the FIG. 1 shown in a plan view. To see several grooves 2, which are designed to receive a blade, not shown.
  • the rotor 1 is formed along an axial direction 3.
  • the groove 2 is designed so bent to the axial direction 3 that a curved curve 4 is formed.
  • a likewise bent blade root 5 of a blade is arranged.
  • FIG. 7 is a cross-sectional view of a portion of the rotor 1 according to the prior art shown.
  • the axial direction 3 points to the normal of the plane of the drawing.
  • the Blade feet 5, which may have a fir tree root, a double T-shape or the like, have a blade plate 6.
  • the blade plate 6 adjoins an end face 7 of a rotor projection 8 of the rotor 1.
  • the blade plate 6 and the rotor projection 8 are in this case designed such that a force between the blade plate 6 and the rotor projection 8 is formed.
  • FIG. 3 is also shown a cross-sectional view of the rotor 1 according to the prior art.
  • the circular section A is in the FIG. 7 magnified reproduced.
  • FIG. 2 is an inventive design of the rotor 1 can be seen.
  • the rotor 1 is initially developed in such a way that the rotor projection 8 is removed.
  • a damping element 9 is arranged between the blade plates 6.
  • FIG. 9 a cross-sectional view of the damping element 9 can be seen.
  • the damping element 9 may have a rectangular cross-section in a first embodiment. Accordingly, the blade plates 6 corresponding recesses 10 for receiving the damping element 9.
  • the damping element 9 is made of a resilient material that can be bent along the curved curve 4. However, due to the bending of the damping element 9 along the curved curve 4, a bending force is generated which generates a force between the blade plates 6. This results in each case a bending force 11 in the direction of the blade plates 6.
  • the in the FIG. 9 Arrows shown symbolically show the direction of the bending force 11, which are caused by the elastic properties of the damping element 9.
  • the damping element 9 is trapezoidal or conical in cross-section, which in the FIG. 8 is shown.
  • the recesses 10 have for this purpose also a complementary shape to the damping element 9.
  • the damping element 9 and the recess 10 are formed such that the smallest possible gap forms therebetween.
  • damping element 9 is shown in the non-installed state. When installed, the damping element 9 would be shown bent. This in FIG. 4 shown damping element 9 has a rectangular cross-section. In addition, the damping element 9 is formed as a rod. This has the advantage that the damping element 9 can be made comparatively quickly.
  • the damping element 9 has a trapezoidal or conical cross section 12.
  • the damping element 9 comprises two support flanks 13, wherein in the FIGS. 4 to 6 only a support edge 13 can be seen.
  • the support flanks 13 are in accordance with the embodiment FIG. 4 formed parallel to each other, whereas in the embodiment according to FIG. 5 the support flanks 13 are formed at an angle ⁇ against each other.
  • a centrifugal force 14 acts on the damping element 9.
  • the centrifugal force 14 causes a force in the direction of the blade plates 6, which points in the direction of the bending force 11. This means that the bending force 11 is supported by the trapezoidal design of the damping element 9 with the centrifugal force. Dampings are thereby further increased, resulting in a reduction of the vibrations.
  • FIG. 6 shows a damping element 9 with a trapezoidal cross-section 12, wherein the damping element 9 has a kink 15.
  • the bend 15 leads to a formation of a projection 16.
  • This projection 16 relative to the support flank 13 is in a corresponding recess 17 in the Blade plate 6 adapted. As a result, slipping of the damping element 9 in a longitudinal direction 18 is avoided.
  • the projection 16 is achieved essentially by three bends 19 of the damping element 9. For this purpose, first the damping element 9 is bent along a first bend 19 '. Subsequently, the damping element 9 is bent back in an opposite direction along the second bend 19 'and then bent along the third bend 19' '' again such that the damping element 9 is substantially aligned again in a straight longitudinal direction 18.
  • damping element 9 As a material for the damping element 9, for example spring steel can be used. In alternative embodiments, well-known blade steels, such as e.g. X20Cr13 can be used.
  • the use of the damping elements 9 offers, inter alia, the advantage that the main flow is not disturbed. Another advantage is that the damping element 9 can be dismantled without destruction from the rotor 1. It is also an advantage that no additional grooves in the rotor 1 must be incorporated.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP08004272A 2008-03-07 2008-03-07 Rotor pour une turbomachine Withdrawn EP2098687A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP08004272A EP2098687A1 (fr) 2008-03-07 2008-03-07 Rotor pour une turbomachine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP08004272A EP2098687A1 (fr) 2008-03-07 2008-03-07 Rotor pour une turbomachine

Publications (1)

Publication Number Publication Date
EP2098687A1 true EP2098687A1 (fr) 2009-09-09

Family

ID=39495232

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08004272A Withdrawn EP2098687A1 (fr) 2008-03-07 2008-03-07 Rotor pour une turbomachine

Country Status (1)

Country Link
EP (1) EP2098687A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3342983A1 (fr) * 2017-01-03 2018-07-04 United Technologies Corporation Aube rotorique, moteur à turbine à gaz et procédé associé d'amortissement de vibrations entre aubes rotoriques contiguës
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
US10851661B2 (en) 2017-08-01 2020-12-01 General Electric Company Sealing system for a rotary machine and method of assembling same

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2235272A1 (fr) * 1973-06-26 1975-01-24 Rolls Royce
DE19940556A1 (de) * 1999-08-26 2001-03-01 Asea Brown Boveri Vorrichtung zum Kühlen von Leit- oder Laufschaufeln in einer Gasturbine
EP1124038A1 (fr) * 2000-02-09 2001-08-16 Siemens Aktiengesellschaft Aubage de turbine
US6371727B1 (en) * 2000-06-05 2002-04-16 The Boeing Company Turbine blade tip shroud enclosed friction damper

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2235272A1 (fr) * 1973-06-26 1975-01-24 Rolls Royce
DE19940556A1 (de) * 1999-08-26 2001-03-01 Asea Brown Boveri Vorrichtung zum Kühlen von Leit- oder Laufschaufeln in einer Gasturbine
EP1124038A1 (fr) * 2000-02-09 2001-08-16 Siemens Aktiengesellschaft Aubage de turbine
US6371727B1 (en) * 2000-06-05 2002-04-16 The Boeing Company Turbine blade tip shroud enclosed friction damper

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10662784B2 (en) 2016-11-28 2020-05-26 Raytheon Technologies Corporation Damper with varying thickness for a blade
EP3342983A1 (fr) * 2017-01-03 2018-07-04 United Technologies Corporation Aube rotorique, moteur à turbine à gaz et procédé associé d'amortissement de vibrations entre aubes rotoriques contiguës
US10677073B2 (en) 2017-01-03 2020-06-09 Raytheon Technologies Corporation Blade platform with damper restraint
US10731479B2 (en) 2017-01-03 2020-08-04 Raytheon Technologies Corporation Blade platform with damper restraint
US10851661B2 (en) 2017-08-01 2020-12-01 General Electric Company Sealing system for a rotary machine and method of assembling same

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