EP2642080A1 - Aube de turbomachine et procédé d'exploitation associé - Google Patents

Aube de turbomachine et procédé d'exploitation associé Download PDF

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Publication number
EP2642080A1
EP2642080A1 EP12160343.5A EP12160343A EP2642080A1 EP 2642080 A1 EP2642080 A1 EP 2642080A1 EP 12160343 A EP12160343 A EP 12160343A EP 2642080 A1 EP2642080 A1 EP 2642080A1
Authority
EP
European Patent Office
Prior art keywords
sealing element
blade
blades
turbomachine
positive
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Withdrawn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
EP12160343.5A
Other languages
German (de)
English (en)
Inventor
Sven Schofer
Ronald Wifling
Manfred Knorr
Rudolf Kellerer
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
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 filed Critical Alstom Technology AG
Priority to EP12160343.5A priority Critical patent/EP2642080A1/fr
Publication of EP2642080A1 publication Critical patent/EP2642080A1/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Withdrawn legal-status Critical Current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
    • 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
    • F05D2240/81—Cooled platforms

Definitions

  • the present invention relates to a blade of a turbomachine according to the preamble of claim 1. It further relates to a method according to the preamble of claim 9.
  • the invention aims to remedy this situation.
  • the invention as characterized in the claims, the object is to propose measures in which a subsequent correction resp. Processing of the turbine blades due to a necessary shift of the original status with respect to the natural frequencies no longer needs to be taken by hand.
  • rotary blades of a turbomachine which essentially consists of an airfoil and a blade root integrally formed thereon, it intervenes with autonomous means, thereby reducing to a geometrical Change or other adjustment of the blades can be dispensed with.
  • the blade root profile is provided with a lower shroud, which is generally formed as a platform, which is autonomously in operative connection with the platforms of the adjacent blades in the circumferential direction along a row of blades from the installation ago.
  • a sealing element is installed below the paddle-side platform between two adjacent blades in the circumferential direction along a row of blades, which bridges the adjacent gap between two platforms.
  • the blade-blade-side surface of the sealing element is the working fluid, so the hot gases exposed to the turbomachine.
  • the geometric design and the mass of this sealing element are chosen so that the centrifugal force resulting from the operation of the blades exerts a mass-dependent centrifugal force acting on the sealing element, which leads to a higher coupling stiffness of the individual blades with each other.
  • the sealing element relative to the substantially groove-shaped recesses in the platforms of the blades usually a positive connection, respectively. Fit on.
  • the sealing element can sometimes be geometrically and materially interpreted so that at least during operation comes to a non-positive or quasi-positive connection with respect to the said recesses in the adjacent platforms. Is opted for the latter design, it is usually provided that, starting from a positive connection in the cold state of the system successively during commissioning the connection resp. Fit between the sealing element and recess can mutate to a frictional connection.
  • Another geometrical and material design of the sealing element may consist in that during the operation of the system comes to a cohesive connection with respect to the recess.
  • the underlying design of the sealing element with respect to the recess must always be able to fulfill two tasks: First, it is important here that the sealing element fulfills the sealing task assigned to it, and, secondly, the sealing element has to fulfill a second task, which consists of Natural frequencies in a particular area to influence sustainable, ie to move here concretely.
  • Another advantage of the invention is the fact that the sealing element can be well acted upon by its integral blade-side adjustment between two platforms with a cooling medium, and thereby can be acted upon by a temperature control on the degree of fit quality against the recesses, thereby On the one hand, it is possible to influence each other very specifically on the natural frequencies that occur and, on the other hand, on the degree of coupling rigidity of the blades.
  • a further significant advantage of the invention is the fact that the sealing element forms a so-called "inter-platform” seal, that is, this sealing element is arranged in recesses formed by grooves below the inner platform, such that it is on the blade root side, ie on the underside, in the Contact with a guided there cooling medium is, and scoop blade side forms a seal against the hot gases flowing there, wherein the geometric integration of the sealing element is designed in the platforms so that its top does not protrude into the hot gas path.
  • Another significant advantage of the invention is the fact that the sealing element, which is generally used in rotating components to prevent leakage of the cooling medium in the hot gas path, or to avoid impingement of the rotor by the hot gases, now according to the invention to fulfill other functions is able to move natural frequencies occurring outside the original design to the desired extent, in such a way that the original resonance-free design of the system can be recreated.
  • this sealing element is designed in accordance with the invention to fulfill the function of coupling two adjacent blades in such a way that the natural frequencies can be acted upon. and moreover, the stresses in the blades are reduced by the sealing element.
  • Fig. 1 shows a summary of a blade 1, with an airfoil 2 and a blade root 4.
  • the actual blade root 4 is separated from the blade 2 by a platform 3 arranged therebetween.
  • a sealing element 5 is installed over not shown here grooves, which essentially fulfills two main functions:
  • the sealing element fulfills the function for blades, blocking of the cooling medium with respect to the hot gas path and vice versa.
  • the sealing element is used to shift occurring natural frequencies from the operation of the blades. This provision is inherent in the application, as in operation acting on the sealing element independent centrifugal forces, which are able to push at least the sealing element against the radially formed outer walls of the grooves not shown here, and causally cause a substantial shift in the indexed by the blades natural frequencies, so that the system can be operated resonance-free even when made subsequent adjustments, which no further systemic precautions must be taken against disturbing natural frequencies by such an installation (sealing element).
  • Fig. 2 shows a side view of two adjacent blades in the circumferential direction, which are anchored on a rotor not shown in detail.
  • the adjacent blades have below the blade 2 each have a platform 3, which largely bridge the gap in the circumferential direction of the rotor.
  • an intermediate gap is provided in order to absorb the installation tolerances and the calorific-related expansions.
  • a double-sided groove is provided below the blade-side outer radial surface of the platforms, which together forms a substantially rectangular recess 6a in the composite of two platforms. In this recess then the sealing element 5a place, which is here of rectangular shape and forms a positive fit against the recess 6a.
  • the blade-side surface of the sealing element is the working fluid, ie the hot gases, the turbomachine facing respectively. exposed.
  • the geometric design and the mass of this sealing element 5a are selected such that a centrifugal force 7 acting on the sealing element 5a is exerted by the centrifugal force arising during operation of the blades, which results in a higher coupling rigidity of the individual blades. This counteracts directly the emergence or potential emergence of natural frequencies insofar as they can be deliberately shifted, so that the original resonance-free design of the system can be recreated or has continuity.
  • This sealing element 5a can also be designed so that, at least during operation, a frictional or quasi-positive connection with respect to the recesses formed by the adjacent platforms can occur.
  • Another geometrical and material design of the sealing element may consist in that during the operation of the system comes to a cohesive connection with respect to the recess.
  • the seal member must fulfill the sealing task assigned to it, and second, the seal member must be able to perform a second task it is to counteract the natural frequencies in a certain way.
  • the seal member must fulfill the sealing task assigned to it, and second, the seal member must be able to perform a second task it is to counteract the natural frequencies in a certain way.
  • a minimization of the stresses occurring during operation can be achieved on the elements of the turbomachine, in particular of the blades, by means of such more precise designs of the sealing element with respect to the recess.
  • Fig. 3 shows a further sealing element 5b
  • the blade leaf side has a roof-shaped end.
  • the recess 6b is also designed in this sense. Even with such a fit, the scoop blade-side surface of the sealing element 5b faces the working medium, ie the hot gases, of the turbomachine, respectively. is exposed.
  • the geometric design and the mass of this sealing element 5b are chosen so that a centrifugal force acting on the sealing element 5b centrifugal force 7 is exerted by the centrifugal force generated during operation of the blades, which results in a higher coupling stiffness of the individual blades with each other. This counteracts directly the emergence or potential emergence of natural frequencies insofar as they can be deliberately shifted, so that the original resonance-free design of the system can be recreated or has continuity.
  • This sealing element 5b can also be designed so that, at least during operation, a frictional or quasi-positive connection with respect to the recesses 6b formed by the adjacent platforms occurs.
  • Another geometric and material design of the sealing element 5b may consist in that during operation of the system comes to a cohesive connection with respect to the recess 6b.
  • seal member 5b must always take into account two aspects: first, the seal member satisfies the sealing task assigned to it, and second, the seal member must be able to perform a second task; which is to counteract the natural frequencies in a certain way.
  • a minimization of the stresses occurring during operation from the elements of the blades can be achieved by such more precise designs of the sealing element in relation to the recess.
  • the specific roof shape construction of the sealing element 5b can increase the effect of the centrifugal force 7 accentuated with exact fit.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP12160343.5A 2012-03-20 2012-03-20 Aube de turbomachine et procédé d'exploitation associé Withdrawn EP2642080A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP12160343.5A EP2642080A1 (fr) 2012-03-20 2012-03-20 Aube de turbomachine et procédé d'exploitation associé

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP12160343.5A EP2642080A1 (fr) 2012-03-20 2012-03-20 Aube de turbomachine et procédé d'exploitation associé

Publications (1)

Publication Number Publication Date
EP2642080A1 true EP2642080A1 (fr) 2013-09-25

Family

ID=45932140

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12160343.5A Withdrawn EP2642080A1 (fr) 2012-03-20 2012-03-20 Aube de turbomachine et procédé d'exploitation associé

Country Status (1)

Country Link
EP (1) EP2642080A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10851661B2 (en) 2017-08-01 2020-12-01 General Electric Company Sealing system for a rotary machine and method of assembling same
CN113503190A (zh) * 2021-09-13 2021-10-15 中国航发上海商用航空发动机制造有限责任公司 航空发动机静子叶片缘板封严条，静子叶片及封严结构

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5226784A (en) * 1991-02-11 1993-07-13 General Electric Company Blade damper
EP1221539A2 (fr) * 2001-01-09 2002-07-10 Mitsubishi Heavy Industries, Ltd. Dispositif d'étanchéité d'une virole de turbine
EP2280151A1 (fr) * 2009-06-23 2011-02-02 Alstom Technology Ltd Procédé d'exploitation d'une turbine à gaz et rotor de turbine à gaz

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5226784A (en) * 1991-02-11 1993-07-13 General Electric Company Blade damper
EP1221539A2 (fr) * 2001-01-09 2002-07-10 Mitsubishi Heavy Industries, Ltd. Dispositif d'étanchéité d'une virole de turbine
EP2280151A1 (fr) * 2009-06-23 2011-02-02 Alstom Technology Ltd Procédé d'exploitation d'une turbine à gaz et rotor de turbine à gaz

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10851661B2 (en) 2017-08-01 2020-12-01 General Electric Company Sealing system for a rotary machine and method of assembling same
CN113503190A (zh) * 2021-09-13 2021-10-15 中国航发上海商用航空发动机制造有限责任公司 航空发动机静子叶片缘板封严条，静子叶片及封严结构
CN113503190B (zh) * 2021-09-13 2022-02-15 中国航发上海商用航空发动机制造有限责任公司 航空发动机静子叶片缘板封严条，静子叶片及封严结构

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