EP2725193A1 - Methode pour désaccorder les aubes d'un moteur de turbine à gas et moteur de turbine à gas correspondant. - Google Patents

Methode pour désaccorder les aubes d'un moteur de turbine à gas et moteur de turbine à gas correspondant. Download PDF

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Publication number
EP2725193A1
EP2725193A1 EP20120189768 EP12189768A EP2725193A1 EP 2725193 A1 EP2725193 A1 EP 2725193A1 EP 20120189768 EP20120189768 EP 20120189768 EP 12189768 A EP12189768 A EP 12189768A EP 2725193 A1 EP2725193 A1 EP 2725193A1
Authority
EP
European Patent Office
Prior art keywords
blades
cavity
gas turbine
cavities
arrangement
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.)
Granted
Application number
EP20120189768
Other languages
German (de)
English (en)
Other versions
EP2725193B1 (fr
Inventor
Harald SCHÖNENBORN
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.)
MTU Aero Engines AG
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MTU Aero Engines AG
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Filing date
Publication date
Application filed by MTU Aero Engines AG filed Critical MTU Aero Engines AG
Priority to EP12189768.0A priority Critical patent/EP2725193B1/fr
Priority to ES12189768.0T priority patent/ES2546992T3/es
Priority to US14/060,777 priority patent/US9546552B2/en
Publication of EP2725193A1 publication Critical patent/EP2725193A1/fr
Application granted granted Critical
Publication of EP2725193B1 publication Critical patent/EP2725193B1/fr
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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
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • 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
    • F01D5/14—Form or construction
    • F01D5/16—Form or construction for counteracting blade vibration
    • 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
    • F05D2260/961—Preventing, counteracting or reducing vibration or noise by mistuning rotor blades or stator vanes with irregular interblade spacing, airfoil shape
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making

Definitions

  • the present invention relates to a gas turbine and a method for producing such a gas turbine.
  • blade flutter With blades of gas turbines, so-called blade flutter can occur during operation due to aeroelastic effects.
  • the US 2,916,258 proposes for this purpose a detuned blade arrangement with blades, which all have different masses and thus natural frequencies.
  • the blades may be formed as solid blades with different profile thicknesses or as hollow blades, each having a central cavity, wherein the cavities of different blades are different in size.
  • the object of the present invention is to provide an improved gas turbine, in particular to reduce blade flutter in a gas turbine.
  • a gas turbine according to one aspect of the present invention includes a stage assembly having one or more stages each having circumferentially alternately disposed first and second blades.
  • One or more of these stages may be turbine stages for venting gas, particularly one of these stages may be a high or low pressure turbine stage. Additionally or alternatively, one or more of these stages may be compressor stages for compressing gas, in particular one of these stages may be a high or low pressure compressor stage.
  • the first and second blades may, in particular rotorfest, blades and / or, in particular stator or housing fixed, vanes be.
  • a gas turbine according to the present invention may therefore in particular have a (high or low pressure) turbine stage with first and second turbine blades. Additionally or alternatively, this or another (high or low pressure) turbine stage may include first and second turbine vanes. Additionally or alternatively, a gas turbine according to the present invention may include a (high or low pressure) compressor stage with first and second compressor blades. Additionally or alternatively, this or another (high or low pressure) compressor stage may include first and second compressor vanes.
  • first and second blades have first and second blades.
  • one or more of these stages are comprised of first and second blades, respectively, and do not have third blades having a different cavity arrangement therefrom.
  • alternately arranged first and second blades is correspondingly understood in particular an arrangement in which each first blade on both sides immediately a second blade and each second blade on both sides immediately adjacent a first blade, optionally apart from a blade pair of first or second immediately adjacent blades at an odd number Total number of shovels of the stage.
  • a blade arrangement with only two alternately arranged blade types in one stage has surprisingly been found to be particularly favorable, in particular in order to reduce blade flutter.
  • blade arrangements of different turbine and / or compressor stages in particular adjacent or spaced apart by at least one further stage, and / or vane arrangements of these or different thereof, in particular adjacent and at least one further stage spaced turbine and / or compressor stages, each alternately arranged first and second blades, in particular to further reduce blade flutter.
  • the first (guide and / or barrel) blades each have a first cavity arrangement and the second (guide and / or barrel) blades each have a second cavity arrangement different therefrom.
  • the first and second blades may have different eigenmodes at, at least substantially, the same or similar natural frequency, so that pressure disturbances induced by the vibrating blades are different and propagate differently in the flow.
  • a first natural frequency, in particular the first bending natural frequency, of the first blades may differ by at least 2%, in particular by at least 3%, from a first natural frequency, in particular the first bending natural frequency, of the second blades. Additionally or alternatively, in one embodiment, this first natural frequency of the first blades may differ by at most 9%, in particular by at most 8%, from this first natural frequency of the second blades.
  • a vane arrangement with such natural frequency differences in one stage has surprisingly been found to be particularly favorable, in particular to reduce blade flutter.
  • the first and second cavity arrangement may differ in particular in the number of cavities.
  • the one (first / second) cavity assembly may not have a cavity, ie, the one (first / second) vanes may be full vanes, or may have one or two cavities.
  • the other (second / first) cavity arrangement may comprise one or more cavities more than the one (first / second) cavity arrangement, in particular a cavity, wherein the one (first / second) cavity arrangement has no cavity, two cavities, wherein the one (first / second) cavity assembly a cavity, or three cavities, wherein the one (first / second) cavity assembly comprises two cavities.
  • the or the cavities may in particular, at least substantially, extend parallel to a stacking axis of the respective blade.
  • Two or more cavities of a cavity assembly may communicate with each other over a limited radial length, particularly at a blade tip and / or blade root near end of the cavities.
  • a cavity in the sense of the present invention is defined in particular in at least one development cut or a section at a radial height of a blade by a closed circumferential contour and distinguished from one or more further cavities of this blade, which then according to the present invention has a plurality of cavities ,
  • the first and second cavity assemblies may in one embodiment, at least substantially, have the same volume.
  • the same volumes can also be formed by cavities with different cut surfaces or contours in at least one development cut, in that the cavities have different extensions in the longitudinal or stacking direction of the blade and / or the cut surface difference is compensated for at a different radial height.
  • first and second blades can have, at least substantially, the same weight, which can be realized in particular by the same total volumes explained above and thus the same amount of solid material, but equally also by, at least in sections, different blade materials.
  • Two cavities of a cavity arrangement can have different shapes, in particular in at least one development cut or a cut a radial height of a blade non-congruent contours.
  • a cavity of one (first / second) cavity assembly and a cavity of the other (second / first) cavity assembly corresponding thereto in its relative position to the blade may have a different shape, in particular in at least one development cut or at a radial height a scoop of non-congruent contours.
  • front edge-next cavities of the first cavity arrangement and trailing-edge-adjacent cavities of the first cavity arrangement and / or front-edge-adjacent cavities of the second cavity arrangement can have a different shape.
  • the first and second blades can be connected to one another in a materially bonded manner or, in particular, can be ur- or reshaped or welded together.
  • the first and second blades may form a so-called Blisk (Blade Integrated Disk).
  • the first and / or second cavity assemblies may be formed in one embodiment with the respective blades.
  • the blades may be cast and the cavity assemblies defined by cores.
  • the first and / or second blades are produced generatively, in particular by hardening layer-wise material locally, in particular optically, thermally and / or chemically. As a result, even more complex, in particular hermetically sealed cavity arrangements can advantageously be produced or be.
  • first and / or second cavity arrangements can also be produced after a prototyping of the blades, in particular material-removing and / or destroying, preferably by machining or vaporizing.
  • the cavity assemblies in particular their shape, placement within the blades, and / or their volume, will be to reduce vane traps from a step having at least two adjacent ones Blades matched with the first or second cavity assembly. This can be done in particular simulatively and / or experimentally.
  • Fig. 1 shows a development cut or a section at a constant radial height of a stage of a gas turbine according to an embodiment of the present invention.
  • the stage may in particular be a turbine or compressor stage.
  • the blades 10, 12 may in particular be rotor-fixed blades or stator or housing-fixed vanes.
  • the second blades 10 each have a second cavity arrangement, each with a cavity 20 which is parallel to a stacking axis of the blade 10, in particular can be aligned with this.
  • the first blades 12 each have a different first cavity arrangement.
  • the first cavity arrangement consists of two cavities 21A, 21B, which in the section of the Fig. 1 are separated from each other. In one cut at a different radial height, they can communicate with each other in one embodiment. Likewise, they may also be completed, particularly if in one embodiment the blades are made generative so that the first and second cavity assemblies are formed into urethra with the blades.
  • the first and second cavity arrangement thus has a different number of cavities. Nevertheless, the first and second cavity arrangements, at least essentially, the same volume. In particular, they have on average the Fig. 1 the same total sectional area, that is, the sectional area of the cavity 20 corresponds, at least substantially, the sum of the sectional areas of the cavities 21A, 21B, wherein the extension of the cavities 20, 21A, 21B in the radial direction (perpendicular to the image plane of the Fig. 1 ) also corresponds to each other, at least substantially. Equally, in one embodiment, the cavities of the first and second cavity arrangement may also have different total areas in at least one development cut. This may be compensated for in other development cuts and / or by the radial extent of the cavities to form, at least substantially, equal volumes of first and second cavity assemblies.
  • first and second blades correspond to each other structurally, in particular in their outer contour and their material, they have, at least substantially, the same weight.
  • first edge cavity 21A of the first cavity assembly and the cavity 21B of the first cavity assembly having a trailing edge are of a different shape.
  • the forward edge-closest cavity 21A of the first cavity arrangement and the forward edge-closest cavity 20 of the second cavity arrangement have a different shape.
  • the cavity assemblies are tuned to reduce blade flutter over a step having at least two adjacent blades with the first or second cavity assembly.
  • the first bending natural frequency of the first blades 12 deviates by 5% from the first bending natural frequency of the second blades 10.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP12189768.0A 2012-10-24 2012-10-24 Méthode pour désaccorder les aubes d'un moteur de turbine à gas et moteur de turbine à gas correspondant. Active EP2725193B1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP12189768.0A EP2725193B1 (fr) 2012-10-24 2012-10-24 Méthode pour désaccorder les aubes d'un moteur de turbine à gas et moteur de turbine à gas correspondant.
ES12189768.0T ES2546992T3 (es) 2012-10-24 2012-10-24 Método para desintonizar los álabes de un motor de turbina de gas
US14/060,777 US9546552B2 (en) 2012-10-24 2013-10-23 Gas turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP12189768.0A EP2725193B1 (fr) 2012-10-24 2012-10-24 Méthode pour désaccorder les aubes d'un moteur de turbine à gas et moteur de turbine à gas correspondant.

Publications (2)

Publication Number Publication Date
EP2725193A1 true EP2725193A1 (fr) 2014-04-30
EP2725193B1 EP2725193B1 (fr) 2015-07-29

Family

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Family Applications (1)

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EP12189768.0A Active EP2725193B1 (fr) 2012-10-24 2012-10-24 Méthode pour désaccorder les aubes d'un moteur de turbine à gas et moteur de turbine à gas correspondant.

Country Status (3)

Country Link
US (1) US9546552B2 (fr)
EP (1) EP2725193B1 (fr)
ES (1) ES2546992T3 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2942481A1 (fr) * 2014-05-07 2015-11-11 Rolls-Royce Corporation Rotor pour un moteur à turbine à gaz
WO2019199320A1 (fr) * 2018-04-13 2019-10-17 Siemens Aktiengesellschaft Désaccordage d'aubes de turbine avec une ou plusieurs cavités internes
EP3102792B1 (fr) * 2014-01-24 2021-09-01 Raytheon Technologies Corporation Désaccordage d'ailette de stator de moteur à turbine à gaz

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3052182B1 (fr) * 2016-06-06 2018-06-15 Safran Roue aubagee de turbomachine a comportement vibratoire ameliore
EP3477048B1 (fr) 2017-10-27 2021-08-18 MTU Aero Engines AG Agencement d'étanchéité d'une interstice entre aubes de turbomachine et de réduction des vibrations des aubes de turbomachine
FR3096398B1 (fr) * 2019-05-20 2021-10-22 Arianegroup Sas Secteur de roue à aubes statorique pour turbomachine
US11371358B2 (en) 2020-02-19 2022-06-28 General Electric Company Turbine damper
US11624287B2 (en) * 2020-02-21 2023-04-11 Raytheon Technologies Corporation Ceramic matrix composite component having low density core and method of making
US20230382539A1 (en) * 2022-05-30 2023-11-30 Pratt & Whitney Canada Corp. Aircraft engine with stator having varying geometry
US11939886B2 (en) 2022-05-30 2024-03-26 Pratt & Whitney Canada Corp. Aircraft engine having stator vanes made of different materials
US12017782B2 (en) 2022-05-30 2024-06-25 Pratt & Whitney Canada Corp. Aircraft engine with stator having varying pitch

Citations (4)

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Publication number Priority date Publication date Assignee Title
US2916258A (en) * 1956-10-19 1959-12-08 Gen Electric Vibration damping
US4097192A (en) * 1977-01-06 1978-06-27 Curtiss-Wright Corporation Turbine rotor and blade configuration
US6042338A (en) * 1998-04-08 2000-03-28 Alliedsignal Inc. Detuned fan blade apparatus and method
US20020064458A1 (en) * 2000-11-30 2002-05-30 Matthew Montgomery Frequency-mistuned light-weight turbomachinery blade rows for increased flutter stability

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US1970435A (en) * 1932-01-09 1934-08-14 Baldwin Southwark Corp Balanced turbine or pump runner and method of balancing
US4878810A (en) * 1988-05-20 1989-11-07 Westinghouse Electric Corp. Turbine blades having alternating resonant frequencies
US5286168A (en) * 1992-01-31 1994-02-15 Westinghouse Electric Corp. Freestanding mixed tuned blade
DE10301755A1 (de) 2003-01-18 2004-07-29 Rolls-Royce Deutschland Ltd & Co Kg Fanschaufel für ein Gasturbienentriebwerk
US6854959B2 (en) * 2003-04-16 2005-02-15 General Electric Company Mixed tuned hybrid bucket and related method
US7008179B2 (en) 2003-12-16 2006-03-07 General Electric Co. Turbine blade frequency tuned pin bank
US7147437B2 (en) * 2004-08-09 2006-12-12 General Electric Company Mixed tuned hybrid blade related method
GB2450937B (en) * 2007-07-13 2009-06-03 Rolls Royce Plc Component with tuned frequency response
EP2161411A1 (fr) 2008-09-05 2010-03-10 Siemens Aktiengesellschaft Aube de turbine dotée d'une fréquence propre adaptée à l'aide d'un élément d'insertion

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2916258A (en) * 1956-10-19 1959-12-08 Gen Electric Vibration damping
US4097192A (en) * 1977-01-06 1978-06-27 Curtiss-Wright Corporation Turbine rotor and blade configuration
US6042338A (en) * 1998-04-08 2000-03-28 Alliedsignal Inc. Detuned fan blade apparatus and method
US20020064458A1 (en) * 2000-11-30 2002-05-30 Matthew Montgomery Frequency-mistuned light-weight turbomachinery blade rows for increased flutter stability

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3102792B1 (fr) * 2014-01-24 2021-09-01 Raytheon Technologies Corporation Désaccordage d'ailette de stator de moteur à turbine à gaz
EP2942481A1 (fr) * 2014-05-07 2015-11-11 Rolls-Royce Corporation Rotor pour un moteur à turbine à gaz
US9932840B2 (en) 2014-05-07 2018-04-03 Rolls-Royce Corporation Rotor for a gas turbine engine
WO2019199320A1 (fr) * 2018-04-13 2019-10-17 Siemens Aktiengesellschaft Désaccordage d'aubes de turbine avec une ou plusieurs cavités internes
JP2021521372A (ja) * 2018-04-13 2021-08-26 シーメンス アクチエンゲゼルシヤフトＳｉｅｍｅｎｓ Ａｋｔｉｅｎｇｅｓｅｌｌｓｃｈａｆｔ 一つまたは複数の内部空洞を有するタービン翼のミスチューン
US11319815B2 (en) 2018-04-13 2022-05-03 Siemens Energy Global GmbH & Co. KG Mistuning of turbine blades with one or more internal cavities

Also Published As

Publication number Publication date
US9546552B2 (en) 2017-01-17
US20140112769A1 (en) 2014-04-24
EP2725193B1 (fr) 2015-07-29
ES2546992T3 (es) 2015-09-30

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