WO2018175356A1 - Pales désaccordées en alternance avec des amortisseurs d'une plateforme inférieure modifiés - Google Patents

Pales désaccordées en alternance avec des amortisseurs d'une plateforme inférieure modifiés Download PDF

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Publication number
WO2018175356A1
WO2018175356A1 PCT/US2018/023218 US2018023218W WO2018175356A1 WO 2018175356 A1 WO2018175356 A1 WO 2018175356A1 US 2018023218 W US2018023218 W US 2018023218W WO 2018175356 A1 WO2018175356 A1 WO 2018175356A1
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WO
WIPO (PCT)
Prior art keywords
dampers
blades
damper
platform
rotor system
Prior art date
Application number
PCT/US2018/023218
Other languages
English (en)
Inventor
Yuekun ZHOU
Jr. Nicholas F. MARTIN
Original Assignee
Siemens Aktiengesellschaft
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 Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Publication of WO2018175356A1 publication Critical patent/WO2018175356A1/fr

Links

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
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/027—Arrangements for balancing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/324—Blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/666—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by means of rotor construction or layout, e.g. unequal distribution of blades or vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/668—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps damping or preventing mechanical vibrations
    • 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

Definitions

  • the present invention is relates to rotating blades in a turbomachine, and in particular, to a row of blades with alternate frequency mistuning for improved flutter resistance.
  • Turbomachines such as gas turbine engines include multiple stages of flow directing elements along a hot gas path in a turbine section of the gas turbine engine.
  • Each turbine stage comprises a circumferential row of stationary vanes and a circumferential row of rotating blades arranged along an axial direction of the turbine section.
  • Each row of blades may be mounted on a respective rotor disc, with the blades extending radially outward from the rotor disc into the hot gas path.
  • a blade includes an airfoil extending span-wise along the radial direction from a root portion to a tip of the airfoil.
  • Typical turbine blades at each stage are designed to be identical aerodynamically and mechanically. These identical blades are assembled together into the rotor disc to form a bladed rotor system.
  • the bladed rotor system vibrates in system modes. This vibration may be more severe in large blades, such as in low pressure turbine stages.
  • An important source of damping in the modes is from aerodynamic forces acting on the blades when the blades vibrate. Under certain conditions, the aerodynamic damping in some of the modes may become negative, which may cause the blades to flutter. When this happens, the vibratory response of the system tends to grow exponentially until the blades either reach a limit cycle or break. Even if the blades achieve a limit cycle, their amplitudes can still be large enough to cause the blades to fail from high cycle fatigue.
  • Alternate frequency mistuning can cause system modes to be distorted, so that the resulting new, mistuned system modes are stable, i.e., they all have positive aerodynamic damping. It is therefore desirable to be able to design blades with a certain amount of predetermined alternate mistuning. Alternate mistuning may be implemented in blades by having the blades in the blade row alternate between high and low frequencies in periodic fashion in the circumferential direction. So far, alternate mistuning of blades has been implemented by modifying the mass and/or geometry of the airfoil in alternate blades in a blade row.
  • aspects of the present invention are directed to a row of blades with modified under-platform dampers to provide alternate frequency mistuning for improved flutter resistance.
  • a bladed rotor system for a turbomachine comprises a circumferential row of blades mounted on a rotor disc.
  • Each blade comprises a platform, a root extending radially inward from the platform for mounting the blade to the rotor disc, and an airfoil extending span-wise radially outward from the platform.
  • platforms of adjacent blades align circumferentially to define an inner diameter boundary for a working fluid flow path.
  • the bladed rotor system further includes a plurality of dampers, each damper being located between adjacent platforms and frictionally contacting a radially inner surface of said adjacent platforms.
  • the plurality of dampers comprise a first set of dampers and a second set of dampers.
  • the dampers of the first set are distinguished from the dampers of the second set by a geometry of the damper that is unique to the respective set.
  • Dampers of the first set and the second set are positioned alternately in a periodic fashion in a circumferential direction, to provide a frequency mistuning to stabilize flutter of the blades.
  • the bladed rotor system comprises a circumferential row of blades mounted on a rotor disc, each blade comprising a platform, a root extending radially inward from the platform for mounting the blade to the rotor disc, and an airfoil extending span-wise radially outward from the platform.
  • the bladed rotor system further comprises a plurality of dampers, each damper being installed between adjacent platforms and frictionally contacting a radially inner surface of said adjacent platforms.
  • the method comprises modifying a geometry of at least a subset of the plurality of installed dampers or providing replacement dampers for at least a subset of the plurality of installed dampers.
  • first and second sets of dampers are obtained, in which the dampers of the first set are distinguished from the dampers of the second set by a geometry of the damper that is unique to the respective set.
  • the method further comprises installing the modified or replacement dampers, such that dampers of the first set and the second set are positioned alternately in a periodic fashion in a circumferential direction, to provide a frequency mistuning to stabilize flutter of the blades.
  • FIG. 1 schematically illustrates, in axial view, a portion of a bladed rotor system comprising under-platform dampers
  • FIG. 2 schematically illustrates, in perspective view, an embodiment of the present invention implementing mistuning of under-platform dampers
  • FIG. 3 is a perspective view, looking from the pressure side, illustrating an assembly of an under-platform damper
  • FIG. 4 is a perspective sectional view, along the section IV in FIG. 3;
  • FIG. 5 is a radial bottom view of an under-platform damper according an exemplary configuration
  • FIG. 6, 7 and 8 illustrate exemplary embodiments of different damper cross-sections along the section line C-C in FIG. 5;
  • FIG. 9 graphically illustrates alternate mistuning in a row of turbine blades.
  • the direction A denotes an axial direction parallel to an axis of the turbine engine
  • the directions R and C respectively denote a radial direction and a circumferential direction with respect to said axis of the turbine engine.
  • the bladed rotor system 10 includes a circumferential row of blades 14 mounted on a rotor disc 12.
  • Each blade 14 comprises an airfoil 16 extending span-wise along a radial direction from a platform 24 to an airfoil tip 20.
  • the airfoil 16 may comprise a generally concave pressure side 2 and a generally convex suction side 4, joined at a leading edge 6 and at a trailing edge (not shown).
  • the blade 14 is mounted on the disc 12 via an attachment structure, referred to as a blade root, which extends radially inward from the platform 24.
  • each blade 14 of the blade row has essentially identical fir-tree attachments.
  • Each platform 24 comprises a radially inner surface 24a and a radially outer surface 24b.
  • the platforms 24 of adjacent blades 14 align circumferentially, without necessarily contacting each other.
  • the circumferential alignment of the radially outer surfaces 24b of neighboring platforms 24 form an inner diameter flow path boundary for a working fluid of the turbomachine.
  • the airfoils 16 extend radially outward into the flow path and extract energy from the working fluid, which causes the blades 14 to rotate about a rotation axis 22.
  • the working fluid exerts a loading force on the airfoils 16. Variations in the loading force cause the blades 14 to deflect and vibrate. This vibration has a broad spectrum of frequency components, with greatest amplitude at the natural resonant frequency of the blades 14. When the blades 14 are unshrouded, the vibration is primarily tangential to the direction of rotation, i.e. the circumferential direction. There, is also a secondary vibration component in the direction of fluid flow, i.e. the axial direction. The above- mentioned vibrations may be reduced by incorporating under-platform dampers 30.
  • Each damper 30 may be constructed as a rigid element which spans the gap between a pair of adjacent platforms 24, and contacting the radially inner surfaces 24a of the adjacent platforms 24. A friction force is thereby applied by the damper 30 to the platforms 24. This friction force reduces blade to blade vibration and consequently reduces individual blade vibration. Conventionally, the dampers 30 of the blade row were designed to be geometrically identical to each other.
  • An underlying idea of the illustrated embodiments involves designing the bladed rotor system 10 to have alternate mistuning of blade frequencies by modifying the geometry of the dampers 30 in an alternating pattern. Modifying the geometry may include, for example, modifying the axial length and/or axial position and/or cross-sectional shape of the dampers 30.
  • the dampers 30 of the bladed rotor system 10 may be divided into first and second sets of dampers 30, designated respectively as H and L.
  • the dampers 30 of the first set H are distinguished from the dampers 30 of the second set L by a geometry of the damper 30 that is unique to the respective set H or L.
  • Dampers 30 of the first set H and the second set L may be positioned alternately in a periodic fashion in the circumferential direction, to provide a frequency mistuning to stabilize flutter of the blades 14.
  • the term "alternately” may refer to every other damper, or include a continuous group of dampers with similar vibratory characteristics.
  • the dampers 30 of the first set H and the second set L alternate in groups of two in a circumferential direction, in a pattern HHLLHH.
  • groups of one or more dampers of the first set H and the second set L may alternate in a periodic fashion along the circumferential direction in the blade row, for example in patterns including HHLLHH, HHHLLHHH, HHHLLLHHH etc.
  • Illustrated embodiments of the present invention are directed to freestanding blades.
  • a free-standing blade may be understood to be an unshrouded blade, i.e., a rotatable blade comprising an airfoil extending span-wise radially outward from a blade platform to an airfoil tip, without any shroud attached to the airfoil at the tip or at any point between the platform and the airfoil tip.
  • the illustrated embodiments are exemplary, and aspects of the present invention may be extended to shrouded blades.
  • the above-described alternate mistuning may be achieved without modifying the geometry of the airfoils. That is, all the airfoils 16 in the circumferential row of blades 14 may have essentially identical cross-sectional geometry about a rotation axis 22. This makes it easier to design the airfoil to have optimum aerodynamic efficiency since a uniform airfoil geometry has to be considered.
  • the illustrated embodiments make it possible to employ alternate mistuning for blades with hollow airfoils, for example, containing internal cooling channels.
  • the design of hollow airfoils is more constrained than the design of solid airfoils.
  • the use of mistuned under-platform dampers provide a possibility for implementing alternate mistuning for such hollow blades without compromising the aero-efficiency.
  • FIG. 2 schematically illustrates an arrangement of mistuned under-platform dampers 30 according an example embodiment of the invention.
  • the dampers 30 of the first set H and the dampers 30 of the second set L differ in their axial lengths, i.e., the damper length along the longitudinal axis of the turbine.
  • the dampers 30 of the first set L have an axial length t
  • the dampers 30 of the second set L have a reduced axial length t- ⁇ .
  • the difference At in the axial length results in different damped frequencies produced by the dampers 30 of the first set H and the dampers 30 of the second set L, which is due to the differences in mass and contact loading between the dampers of the two sets.
  • the damped frequency of the blades 14 may be changed, so as to achieve alternate mistuning without changing the airfoil geometry.
  • each damper 30 may be installed in an under- platform pocket 50, such that a radially outer surface 30b of the damper 30 contacts the radially inner surface 24a of the platform 24.
  • the damper 30 may be secured in position by axially spaced tabs 52a, 52b provided on the under-side of the platform 24.
  • the radially inner surface 30a of the damper may be provided with axially spaced projections 34a, 34b that engage in corresponding recesses (not shown) in the tabs 52a, 52b.
  • the location of tabs 52a and 52b may provide a "fool proofing" installation safeguard.
  • the damper length for the second set of dampers L may be reduced by reducing a free length tei, and/or t e2 between a projection 34a, 34b and the nearest respective axial end 36a, 36b of the damper 30.
  • a free length tei, and/or t e2 between a projection 34a, 34b and the nearest respective axial end 36a, 36b of the damper 30.
  • the dampers 30 of the first set H and the second set L may be positioned at different axial locations in relation to the respective platforms 24.
  • the dampers 30 of both sets H, L may have the same (reduced) axial length, whereby a frequency mistuning is achieved simply based on the differences in contact loading between the first and second set of dampers.
  • FIG. 5 illustrates a damper 30 with a generally rectangular or trapezoidal cross-sectional shape along the section C-C perpendicular to the axial length of the damper 30.
  • the contact loading may be modified by providing different cross-sectional damper geometries, which may include for example, a circular shape (see FIG. 5), a wedge shape (see FIG. 7), or an asymmetrical shape (see FIG. 8), among many other shapes.
  • alternate frequency mistuning may be implemented by having different damper cross-sectional shapes between the first and second sets H, L.
  • the cross-sectional shape of each of the dampers 30 in the first set H and the second set L may be uniform across the entire axial length of the respective damper 30.
  • the cross- sectional shape of each of the dampers 30 in the first set H, or the second set L, or both may vary across an axial length of the respective damper 30, such that the variation of the cross-sectional shape along an axial direction is unique to the particular set H, L.
  • Having the same length damper allows for a uniform under-platform geometry for the entire row of blades, as well as straight forward installations.
  • a frequency mistuning may be achieved on the basis of the differences in contact loading between the first and second sets H, L.
  • aspects of the present invention may be incorporated in a service upgrade method, whereby an intentional alternate mistuning may be introduced in an existing row of blades, to improve flutter resistance of the blades. This may be achieved by modifying the geometry of at least a subset of the existing dampers, or by providing replacement dampers, such that one or more of the inventive concepts described above are realized.
  • the under-platform damper geometries may be modified to achieve a mistuning of about 1.5 - 2 % above manufacturing tolerances.
  • FIG. 9 graphically illustrates alternate mistuning in a row of 40 turbine blades.
  • the odd number blades have a frequency of 250Hz
  • the even numbered blades have a frequency of 255 Hz.
  • the difference in blade frequencies is 5 Hz. Consequently, the frequency of even numbered blades is 2% than the frequency of odd numbered blades, i.e., the amount of mistuning is 2%.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L'invention concerne un système de rotor à pales (10) pour une turbomachine comprenant des pales (14) montées de manière circonférentielle sur un disque de rotor (12), et une pluralité d'amortisseurs d'une plateforme inférieure (30). Chaque amortisseur (30) est situé entre des plateformes de pales adjacentes (24) et entre en contact par frottement avec une surface radialement interne (24a) des plateformes des pales adjacentes (24). La pluralité d'amortisseurs (30) comprend un premier ensemble (H) d'amortisseurs (30) et un second ensemble (L) d'amortisseurs (30). Les amortisseurs (30) du premier ensemble (H) se distinguent des amortisseurs (30) du second ensemble (L) soit par la géométrie des amortisseurs (30) soit par leurs positions respectives, qui est unique à l'ensemble respectif (H, L). Les amortisseurs (30) du premier ensemble (H) et du second ensemble (L) sont positionnés de façon alternée de manière périodique dans une direction circonférentielle, ce qui permet d'obtenir un désaccord de fréquence pour stabiliser les vibrations des pales (30).
PCT/US2018/023218 2017-03-22 2018-03-20 Pales désaccordées en alternance avec des amortisseurs d'une plateforme inférieure modifiés WO2018175356A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US201762474649P 2017-03-22 2017-03-22
US62/474,649 2017-03-22

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WO2018175356A1 true WO2018175356A1 (fr) 2018-09-27

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Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20190345830A1 (en) * 2018-05-08 2019-11-14 Rolls-Royce Plc Damper
WO2020131062A1 (fr) * 2018-12-20 2020-06-25 Siemens Aktiengesellschaft Système de rotor à pales et procédé de service correspondant
JP2020139477A (ja) * 2019-02-28 2020-09-03 三菱重工業株式会社 回転機械
US11174739B2 (en) 2019-08-27 2021-11-16 Solar Turbines Incorporated Damped turbine blade assembly

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2223277A (en) * 1988-09-30 1990-04-04 Rolls Royce Plc Aerofoil blade damping
US20160024928A1 (en) * 2014-07-22 2016-01-28 MTU Aero Engines AG Blade cascade for a turbomachine
US9341067B2 (en) * 2010-09-24 2016-05-17 Siemens Aktiengesellschaft Blade arrangement and associated gas turbine

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2223277A (en) * 1988-09-30 1990-04-04 Rolls Royce Plc Aerofoil blade damping
US9341067B2 (en) * 2010-09-24 2016-05-17 Siemens Aktiengesellschaft Blade arrangement and associated gas turbine
US20160024928A1 (en) * 2014-07-22 2016-01-28 MTU Aero Engines AG Blade cascade for a turbomachine

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20190345830A1 (en) * 2018-05-08 2019-11-14 Rolls-Royce Plc Damper
WO2020131062A1 (fr) * 2018-12-20 2020-06-25 Siemens Aktiengesellschaft Système de rotor à pales et procédé de service correspondant
CN113227539A (zh) * 2018-12-20 2021-08-06 西门子能源全球两合公司 带叶片的转子系统及对应的维修方法
JP2022513252A (ja) * 2018-12-20 2022-02-07 シーメンス エナジー グローバル ゲゼルシャフト ミット ベシュレンクテル ハフツング ウント コンパニー コマンディートゲゼルシャフト ブレードロータシステムと対応する保守点検方法
US11401815B2 (en) 2018-12-20 2022-08-02 Siemens Energy Global GmbH & Co. KG Bladed rotor system and corresponding method of servicing
JP7267427B2 (ja) 2018-12-20 2023-05-01 シーメンス エナジー グローバル ゲゼルシャフト ミット ベシュレンクテル ハフツング ウント コンパニー コマンディートゲゼルシャフト ブレードロータシステムと対応する保守点検方法
CN113227539B (zh) * 2018-12-20 2023-08-29 西门子能源全球两合公司 带叶片的转子系统及对应的维修方法
JP2020139477A (ja) * 2019-02-28 2020-09-03 三菱重工業株式会社 回転機械
JP7235536B2 (ja) 2019-02-28 2023-03-08 三菱重工業株式会社 回転機械
US11174739B2 (en) 2019-08-27 2021-11-16 Solar Turbines Incorporated Damped turbine blade assembly

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