EP2280151A1 - Betriebsverfahren für eine Gasturbine und Rotor einer Gasturbine - Google Patents

Betriebsverfahren für eine Gasturbine und Rotor einer Gasturbine Download PDF

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Publication number
EP2280151A1
EP2280151A1 EP09163488A EP09163488A EP2280151A1 EP 2280151 A1 EP2280151 A1 EP 2280151A1 EP 09163488 A EP09163488 A EP 09163488A EP 09163488 A EP09163488 A EP 09163488A EP 2280151 A1 EP2280151 A1 EP 2280151A1
Authority
EP
European Patent Office
Prior art keywords
rotor
rotor blades
couple
seat
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Withdrawn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
EP09163488A
Other languages
English (en)
French (fr)
Inventor
Sven Schofer
Rudolf Kellerer
Roland Wifling
Manfred Knorr
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 EP09163488A priority Critical patent/EP2280151A1/de
Publication of EP2280151A1 publication Critical patent/EP2280151A1/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Withdrawn legal-status Critical Current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
    • 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
    • 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 present invention relates to a rotor of a gas turbine and a method for operating a gas turbine.
  • the present invention addresses the problem of rotor blade vibrations during operation.
  • Gas turbines are known to comprise a compressor, a combustion chamber and a turbine. During operation a main air flow is compressed and mixed with a fuel to form a mixture that is combusted in the combustion chamber; the hot gases are then expanded in the turbine.
  • the gas turbine comprises a compressor, a combustion chamber and a high pressure turbine; downward of the high pressure turbine this gas turbine comprises a second combustion chamber and a low pressure turbine.
  • the main air flow is compressed and mixed with a fuel to form a mixture that is combusted in the first combustion chamber; the hot gases are then only partially expanded in the high pressure turbine; afterwards the hot gases partially expanded are fed to the second combustion chamber, where further fluid is injected and combusted; the hot gases generated in the second combustion chamber are expanded in the low pressure turbine.
  • Each turbine comprises a plurality of stages, each comprising stator vanes and rotor blades.
  • the rotor blades have a root connected to the rotor body, a platform and an airfoil extending from the platform and arranged to exchange mechanical power with the hot gases.
  • the platforms of the rotor blades (with the turbine casing that contains the stages) define an annular duct in which the hot gases flow; in particular the platforms define the inner surface of the duct and the turbine casing defines the outer surface of the duct.
  • thin sealing plates are arranged between two adjacent platforms.
  • the sealing plates are housed in seats placed at the two opposite sides of the platforms in a zone towards the root.
  • Each sealing plate has a part housed in a seat of a rotor blade, and the other part housed in a seat of the adjacent rotor blade.
  • sealing plates are housed in the seats very loosely and, during operation, centrifugal forces press them against the platforms and guarantee the sealing.
  • the natural frequencies of each rotor blade can be measured and/or calculated, and the frequencies of the forces that during operation excite the blades can be foreseen such that a correct design of the rotor blades can keep the natural frequencies of the same rotor blade away from the frequencies of the exciting forces.
  • blades are in some cases provided with damping systems that absorb the vibrations.
  • the technical aim of the present invention is therefore to provide a rotor and a method by which the said problems of the known art are eliminated.
  • an object of the invention is to provide a rotor and a method that let reliable rotor blades, with a long working life, be manufactured.
  • Another object of the invention is to provide a rotor and a method that let rotor blades be manufactured having costs lower than equivalent traditional reworked rotor blades.
  • a further object of the present invention is to provide a rotor and a method that let rotor blades be manufactured in a short time (when compared to the corresponding traditional rotor blades that need reworking).
  • the excitation vibrations are not absorbed as usual in the prior art, but on the contrary the natural frequencies of the rotor blades are shifted away from the excitation vibrations during operation.
  • a rotor of a gas turbine is shown identified by the reference number 1.
  • the rotor 1 has a plurality of rotor blades row comprising a plurality of rotor blades 2.
  • Each rotor blade 2 is provided with a root 3 connected to a rotor body 4, a platform 5 that defines, with the platforms 5 of the other rotor blades 2 and the casing 6 of the turbine, a duct 7 in which the hot gases flow flows (the duct 7 has an annular cross section, the platforms 5 define the inner surface of the duct and the casing 6 defines the outer surface of the duct 7).
  • the rotor blades 2 also comprise an airfoil 8 which exchanges mechanical power with the hot gases flow.
  • the rotor blades 2 comprise beneath the platform 5 and at opposite side zones towards the root 3, a seat 9 housing a couple element 10 arranged to lie between two adjacent rotor blades 2 to connect them each other and seal the duct 7.
  • the rotor blades 2 are all connected each other by the couple elements 10 and vibrate together as a coupled system, such that the natural frequencies of the rotor blades 2 vibrating together are different from the natural frequencies of each free rotor blade (i.e. not connected to other rotor blades) and are away from the excitation vibrations.
  • the plates 10 perfectly fit the seats 9.
  • the couple elements 10 vary in weight and/or shape from traditional sealing elements and, in particular, they are heavier than traditional sealing elements.
  • the couple elements 10 are twice as heavy as traditional sealing plates or more.
  • the couple elements 10 (see figures 4-7 ) have an elongated shape, with diagonal end walls 13.
  • couple elements 10 have a symmetrical cross section with respect to a transversal axis 12.
  • the couple elements 10 have a rectangular cross section.
  • the couple elements 10 also have a projection 15 that has a diagonal base 16 that is inserted in a recess 17 of the seat 9.
  • the couple elements 10 have no projection 15.
  • the couple elements 10 have similar features to the couple elements already described but, in addition, they have a side with two sloped walls 20, 22 defining a thicker portion 23 at its centre.
  • the side with the two sloped portions 20, 22 of the couple element 10 is that towards the platforms 5 and the duct 7.
  • each seat 9 has one sloped wall 25 that fits one sloped wall 20 or 22 of the couple element 10.
  • each seat 9 defines a bottom surface 26 of the seat 9 that is smaller than an open surface 27 of the same seat 9.
  • the seat 9 is defined by the inner surface 9a of the platform 5, by a first elements 9b (defining the recess 17) and by a second element 9c placed at the opposite ends on the seat 9. It is anyhow clear that the seat may also have different shapes; for example the seat can be a slot or the first element 9b can define a recess arranged to house the whole cross section of the couple element 10 (i.e. without the need of the projection 15).
  • the rotor blades 2 are housed with their root 3 inserted in the seats of the rotor body 4 and the couple elements 10 housed in the seats 9 of the platforms 5.
  • the rotor body 4 rotates and the centrifugal forces that are generated by the rotation urge the couple elements 10 outwardly, towards the platforms 5.
  • this also lets the zones between two adjacent platforms 5 be sealed preventing the hot gases flowing within the duct 7 from passing through the slots defined between two adjacent platforms 5 and entering the rotor body area.
  • the couple elements 10 let a rigid connection between adjacent blades 2 be achieved such that the blades react to forces together (as a coupled system), whereas using traditional sealing plates each blade reacts to forces independently from one another.
  • the present invention also relates to method for operating a gas turbine.
  • the rotor blades 2 are connected each other by the couple elements 10 and vibrate together as a coupled system.
  • each couple element 10 is urged by the centrifugal forces against the platforms 5 of two adjacent rotor blades 2.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP09163488A 2009-06-23 2009-06-23 Betriebsverfahren für eine Gasturbine und Rotor einer Gasturbine Withdrawn EP2280151A1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP09163488A EP2280151A1 (de) 2009-06-23 2009-06-23 Betriebsverfahren für eine Gasturbine und Rotor einer Gasturbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP09163488A EP2280151A1 (de) 2009-06-23 2009-06-23 Betriebsverfahren für eine Gasturbine und Rotor einer Gasturbine

Publications (1)

Publication Number Publication Date
EP2280151A1 true EP2280151A1 (de) 2011-02-02

Family

ID=40833487

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09163488A Withdrawn EP2280151A1 (de) 2009-06-23 2009-06-23 Betriebsverfahren für eine Gasturbine und Rotor einer Gasturbine

Country Status (1)

Country Link
EP (1) EP2280151A1 (de)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2642080A1 (de) * 2012-03-20 2013-09-25 Alstom Technology Ltd Schaufel einer Strömungsmaschine und zugehöriges Betriebsverfahren
EP2848770A1 (de) * 2013-09-17 2015-03-18 MTU Aero Engines GmbH Laufradschaufel einer axialen Strömungsmaschine und Dämpfungselement
US10851661B2 (en) 2017-08-01 2020-12-01 General Electric Company Sealing system for a rotary machine and method of assembling same

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2836392A (en) * 1953-06-03 1958-05-27 United Aircraft Corp Disc vibration damping means
US2912223A (en) * 1955-03-17 1959-11-10 Gen Electric Turbine bucket vibration dampener and sealing assembly
US5302085A (en) * 1992-02-03 1994-04-12 General Electric Company Turbine blade damper
US5478207A (en) * 1994-09-19 1995-12-26 General Electric Company Stable blade vibration damper for gas turbine engine
EP1167691A2 (de) * 2000-06-30 2002-01-02 General Electric Company Schwingungsdämpfer für Turbinenschaufeln und dessen Herstellungsweise
US20050186074A1 (en) * 2004-02-23 2005-08-25 Mitsubishi Heavy Industries, Ltd. Moving blade and gas turbine using the same
EP2009247A2 (de) * 2007-06-28 2008-12-31 United Technologies Corporation Turbinenschaufel mit einer Dichtungs- und Dämpfungsvorrichtung

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2836392A (en) * 1953-06-03 1958-05-27 United Aircraft Corp Disc vibration damping means
US2912223A (en) * 1955-03-17 1959-11-10 Gen Electric Turbine bucket vibration dampener and sealing assembly
US5302085A (en) * 1992-02-03 1994-04-12 General Electric Company Turbine blade damper
US5478207A (en) * 1994-09-19 1995-12-26 General Electric Company Stable blade vibration damper for gas turbine engine
EP1167691A2 (de) * 2000-06-30 2002-01-02 General Electric Company Schwingungsdämpfer für Turbinenschaufeln und dessen Herstellungsweise
US20050186074A1 (en) * 2004-02-23 2005-08-25 Mitsubishi Heavy Industries, Ltd. Moving blade and gas turbine using the same
EP2009247A2 (de) * 2007-06-28 2008-12-31 United Technologies Corporation Turbinenschaufel mit einer Dichtungs- und Dämpfungsvorrichtung

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2642080A1 (de) * 2012-03-20 2013-09-25 Alstom Technology Ltd Schaufel einer Strömungsmaschine und zugehöriges Betriebsverfahren
EP2848770A1 (de) * 2013-09-17 2015-03-18 MTU Aero Engines GmbH Laufradschaufel einer axialen Strömungsmaschine und Dämpfungselement
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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