EP2597265A1 - Aube directrice pour une turbomachine pouvant s'écouler de manière axiale - Google Patents

Aube directrice pour une turbomachine pouvant s'écouler de manière axiale Download PDF

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Publication number
EP2597265A1
EP2597265A1 EP11190939.6A EP11190939A EP2597265A1 EP 2597265 A1 EP2597265 A1 EP 2597265A1 EP 11190939 A EP11190939 A EP 11190939A EP 2597265 A1 EP2597265 A1 EP 2597265A1
Authority
EP
European Patent Office
Prior art keywords
blade
ring
turbomachine
rotor
blades
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Withdrawn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
EP11190939.6A
Other languages
German (de)
English (en)
Inventor
Fathi Ahmad
Otmar Gossmann
Olaf Hein
Christian Lerner
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 EP11190939.6A priority Critical patent/EP2597265A1/fr
Publication of EP2597265A1 publication Critical patent/EP2597265A1/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Withdrawn legal-status Critical Current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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/20—Actively adjusting tip-clearance
    • 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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/20—Actively adjusting tip-clearance
    • F01D11/22—Actively adjusting tip-clearance by mechanically actuating the stator or rotor components, e.g. moving shroud sections relative to the rotor
    • 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

Definitions

  • the invention relates to a blade for an axially flow-through turbomachine, which along a longitudinal extent successively comprises a blade root a platform and an aerodynamically curved blade arranged thereon with a blade tip, which blade tip is free of cover tape.
  • the object of the invention is therefore to provide a rotor of a turbomachine and a blade for an axially flow-through turbo machine, which used on the rotor of the turbomachine has a lower tendency to vibration than the blade known in the prior art.
  • a shroud-free blade on the blade tip has an element for forming a frictional connection and that all blade tips of a blade ring of the rotor of a turbomachine are surrounded by a ring, in which engage the elements of each blade frictionally.
  • a rotor blade of a rotor of a turbomachine is equipped with a shroud ring produced separately from the rotor blades, in which elements which are preferably hammer-shaped or hook-shaped engage with frictional engagement. Due to the structural separation of blades and shroud as two separately produced components, it is possible to design the ring preferably as a revolving lightweight ring profile. In the course of this, only the element provided on the blade tip is part of the blade and thus monolithically connected thereto. The contact surface between the element and the ring then forms a friction surface, which is suitable for positively influencing the vibration behavior of the rotor blade.
  • the obstruction of the vibration of the blade or the blade of the blade by the introduction of mold elements in the friction surface can be further increased.
  • a corresponding Coating preferably be provided.
  • a particular advantage of the proposed embodiment is that the use of a highly twisted airfoil is possible with the aid of the modular construction.
  • this embodiment makes it possible for the airfoil to continue to rotate under the influence of the flying force, which would lead to mechanical stresses in a rotor blade with an integral shroud.
  • additional sealing tips can be provided on the radially outer surface of the ring profile.
  • a simpler assembly of the rotor is achieved when the ring is split axially. This allows the assembly and disassembly of individual blades.
  • This limitation of movement in the axial direction is important for the function of the sealing tips.
  • the central fixation can also have a positive effect on the vibration behavior of the blade.
  • Another advantage of the device according to the invention is that the weight of the ring is comparatively small compared to conventional integral shrouds. This reduces the mechanical load in the blades and also in their blade roots, so that both the blade itself and the blade carrying unit - usually a rotor disk - is loaded with low centrifugal force. In the rare case, if the centrifugal force acting on the ring profile, not sufficient to produce a correspondingly high frictional force, in addition, a spring element can be installed if necessary.
  • the ring profile allows the use of multiple axial sealing tips to an axial gap to an opposite Seal the side wall and prevent leakage from the working medium.
  • the ring is segmented and held by the elements, which allows easy assembly and disassembly of the ring.
  • FIG. 1 a turbine blade 10 for an axial flow turbomachine is shown in perspective.
  • the turbine blade 10 sequentially includes a blade root 12, an inner platform 14, and an airfoil 16 disposed thereon.
  • the airfoil 16 is aerodynamically curved and terminates at an airfoil tip 22.
  • no shroud is provided, ie, it is shroud free.
  • At the blade tip 22 is monolithically connected to an element 24, which is designed hammer-shaped in the side view.
  • the hammer-shaped element 24 may also be referred to as a hook element.
  • FIG. 2 shows a section through the longitudinal section of a turbomachine 25.
  • the turbomachine 25 is configured as a gas turbine, wherein the position of the cutout is selected so that this the guide vanes the first and second turbine stage and the axially arranged between them blade ring of the first turbine stage represents.
  • the vane of the first turbine stage is designated by reference numeral 28, that of the second turbine stage by the reference numeral 30.
  • the vanes 28, 30 are attached to a vane support 32.
  • the vane support 32 is circular in cross-section, so that radially inward per vane ring a plurality of vanes 28, 30 which extend through an annular cross-sectionally hot gas channel 34 inwardly.
  • Blades 10 shown attached to a support structure of the rotor, such as a turbine disk.
  • an all blade airfoils 22 encompassing ring 36 is provided, in which the elements 24 of each blade 10 engage frictionally and positively.
  • the friction surfaces are identified by the reference numeral 38.
  • the ring 36 is designed as a circumferential, hollow lightweight ring profile.
  • the ring 36 is upstream of a hot gas flow direction axial gap forming a non-rotatable side wall 40 opposite.
  • a seal in the form of an axial labyrinth 44 is provided in order to avoid losses of hot gas through the axial gap 42.
  • Sidewall 40 is axially movably mounted to vane support 32 via a thermo-mechanical unit 46.
  • a over the entire circumference extending seal 48 is provided, which can follow the axial movement of the side wall 40.
  • the ring 36 rotates with the blades 10. If some of the blades 10 are excited to vibrate by the influence of flow, then their element 24 then moves relative to the ring 36, during which a friction arises at the contact surfaces 38, which dissipates the vibration energy. This will cause unwanted vibrational states of blades 10, which ensures safe operation of the turbomachine.
  • the seal 48 and the thermo-mechanical adjustment unit 46 it is also possible to minimize leakage of hot gas through the axial gap 42 and any flow through the gap between ring 36 and thermo-mechanical adjustment unit 46.
  • a distance sensor 50 can be provided in the side wall 40, so that the axial labyrinth 44 can be positioned depending on the operating state. For example, during transient operating conditions, the side wall 40 remains largely retracted in a parking position, which avoids damage to the axial labyrinth 44. After reaching a stable operating point, the side wall 40 can be axially moved up to a narrowest possible gap to the ring 36. In this case, the distance between the side wall and ring 36 can be determined by a device for capacitive distance measurement.
  • An alternative way of minimizing the axial gap 42 to be adjusted provides that the side wall 40 is moved up to the ring 36 until it comes to an electrical contact. If a flashover occurs at the minimum distance, this position can be held. If electrical current flows only when touched, then the side wall 40 must then be pulled back accordingly to prevent excessive wear.
  • the invention provides a rotor blade 10 for an axially flow-through turbomachine and a rotor therefor, in which the rotor blade 10 comprises a blade root 12, a platform 14 and an aerodynamically curved blade 16 arranged thereon with a blade tip 22 successively along a longitudinal extent, which blade blade tip 22 is free of cover tape.
  • the blades of which are particularly prone to oscillate or whose vibration movement can be damped particularly effective, it is provided that at the blade tip 22, a member 24 is provided for forming a frictional connection, and that an all blade blades tips 22 encompassing ring 36 is provided, in which the elements 24 of each blade 10 frictionally engage.
EP11190939.6A 2011-11-28 2011-11-28 Aube directrice pour une turbomachine pouvant s'écouler de manière axiale Withdrawn EP2597265A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP11190939.6A EP2597265A1 (fr) 2011-11-28 2011-11-28 Aube directrice pour une turbomachine pouvant s'écouler de manière axiale

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP11190939.6A EP2597265A1 (fr) 2011-11-28 2011-11-28 Aube directrice pour une turbomachine pouvant s'écouler de manière axiale

Publications (1)

Publication Number Publication Date
EP2597265A1 true EP2597265A1 (fr) 2013-05-29

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ID=45065792

Family Applications (1)

Application Number Title Priority Date Filing Date
EP11190939.6A Withdrawn EP2597265A1 (fr) 2011-11-28 2011-11-28 Aube directrice pour une turbomachine pouvant s'écouler de manière axiale

Country Status (1)

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EP (1) EP2597265A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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 (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4482297A (en) * 1981-11-16 1984-11-13 Terry Corporation Bladed rotor assembly
US5133643A (en) * 1989-11-22 1992-07-28 Ortolano Ralph J Shroud fitting
EP1243756A1 (fr) * 2001-03-23 2002-09-25 Siemens Aktiengesellschaft Turbine
EP1746256A1 (fr) * 2005-07-20 2007-01-24 Siemens Aktiengesellschaft Diminution des pertes dues au jeu en bout d'aubes dans les turbomachines
EP2182174A2 (fr) * 2008-10-29 2010-05-05 General Electric Company Turbine à vapeur avec dispositif d'étanchéité activé par la pression

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4482297A (en) * 1981-11-16 1984-11-13 Terry Corporation Bladed rotor assembly
US5133643A (en) * 1989-11-22 1992-07-28 Ortolano Ralph J Shroud fitting
EP1243756A1 (fr) * 2001-03-23 2002-09-25 Siemens Aktiengesellschaft Turbine
EP1746256A1 (fr) * 2005-07-20 2007-01-24 Siemens Aktiengesellschaft Diminution des pertes dues au jeu en bout d'aubes dans les turbomachines
EP2182174A2 (fr) * 2008-10-29 2010-05-05 General Electric Company Turbine à vapeur avec dispositif d'étanchéité activé par la pression

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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

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