US20140140841A1 - Turbine bucket shroud arrangement and method of controlling turbine bucket interaction with an adjacent turbine bucket - Google Patents

Turbine bucket shroud arrangement and method of controlling turbine bucket interaction with an adjacent turbine bucket Download PDF

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Publication number
US20140140841A1
US20140140841A1 US13/680,974 US201213680974A US2014140841A1 US 20140140841 A1 US20140140841 A1 US 20140140841A1 US 201213680974 A US201213680974 A US 201213680974A US 2014140841 A1 US2014140841 A1 US 2014140841A1
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US
United States
Prior art keywords
contact region
shroud
turbine bucket
tip shroud
thermal expansion
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.)
Abandoned
Application number
US13/680,974
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English (en)
Inventor
Krishna Kishore GUMPINA
Sheo Narain Giri
Sanjeev Kumar Jha
Mahesh Pasupuleti
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 Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Priority to US13/680,974 priority Critical patent/US20140140841A1/en
Assigned to GENERAL ELECTRIC COMPANY reassignment GENERAL ELECTRIC COMPANY ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: GIRI, SHEO NARAIN, Gumpina, Krishna Kishore, JHA, SANJEEV KUMAR, Pasupuleti, Mahesh
Priority to JP2013233585A priority patent/JP2014101880A/ja
Priority to DE201310112791 priority patent/DE102013112791A1/de
Publication of US20140140841A1 publication Critical patent/US20140140841A1/en
Abandoned 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
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding

Definitions

  • the subject matter disclosed herein relates to turbine systems, and more particularly to turbine bucket shroud arrangements, as well as a method of controlling turbine bucket interaction with an adjacent turbine bucket.
  • Turbine systems employ a number of rotating components or assemblies, such as compressor stages and turbine stages that rotate at high speed when the turbine is in operation, for example.
  • a stage includes a plurality of free-floating blades that extend radially outward from a central hub.
  • Some blades include a shroud that limits vibration within a stage and provides sealing to increase efficiency of the overall system.
  • the shroud is typically positioned at a tip portion of the blade, a mid-portion of the blade or at both the mid portion and the tip portion of the blade.
  • the shrouds are designed such that the free-floating blades interlock to form an integral rotating member during operation.
  • a gap between contact surfaces of the shrouds Prior to rotation of the free-floating blades, a gap between contact surfaces of the shrouds is present. The distance of the gap determines how early an interlock of the shrouds occurs upon startup of the turbine system. Too large of a gap inefficiently delays the locking speed, which may result in resonance, for example. Too small of a gap results in undesirable effects at high speed operation of the turbine system. Such effects include lower damping effectiveness and flutter margin, as well as high stresses imposed on the turbine bucket due to increased transfer of forces between the contacting shrouds, for example. Therefore, current efforts to beneficially reduce the gap to provide an early interlock to address potential low speed aeromechanics issues are mitigated by the detrimental effects on tip shroud life that occur at steady state operating conditions.
  • a turbine bucket shroud arrangement for a turbine system includes a contact region of a tip shroud, wherein the contact region is in close proximity to an adjacent tip shroud. Also included is a negative thermal expansion material disposed proximate the contact region, the contact region comprising a first volume during a startup condition and a shutdown condition of the turbine system and a second volume during a steady state condition of the turbine system, wherein the second volume is less than the first volume.
  • a method of controlling turbine bucket interaction with an adjacent turbine bucket includes reducing a gap disposed between a contact region of a tip shroud and an adjacent tip shroud by depositing a negative thermal expansion material proximate the contact region. Also included is engaging the contact region of the tip shroud with the adjacent tip shroud during a startup operating condition and a shutdown operating condition. Further included is decreasing a volume of the contact region during increased temperature operating conditions upon contraction of the negative thermal expansion material, wherein decreasing the volume reduces tip shroud contact forces and stresses during a steady state operating condition.
  • FIG. 1 is a schematic view of a turbine system
  • FIG. 2 is a partial perspective view of a turbine stage of the turbine system
  • FIG. 3 is a top plan view of a turbine bucket shroud arrangement having a contact region
  • FIG. 4 is an enlarged top plan view of the contact region of FIG. 3 ;
  • FIG. 5 is a schematic view of the contact region comprising a composition
  • FIG. 6 is a schematic view of a plurality of layers of the composition.
  • FIG. 7 is a flow diagram illustrating a method of controlling turbine bucket interaction with an adjacent turbine bucket.
  • a turbine system shown in the form of a gas turbine engine, constructed in accordance with an exemplary embodiment of the present invention, is indicated generally at 10 .
  • the turbine system 10 includes a compressor 12 and a plurality of combustor assemblies arranged in a can annular array, one of which is indicated at 14 .
  • the combustor assembly 14 includes an endcover assembly 16 that seals, and at least partially defines, a combustion chamber 18 .
  • a plurality of nozzles 20 - 22 are supported by the endcover assembly 16 and extend into the combustion chamber 18 .
  • the nozzles 20 - 22 receive fuel through a common fuel inlet (not shown) and compressed air from the compressor 12 .
  • the fuel and compressed air are passed into the combustion chamber 18 and ignited to form a high temperature, high pressure combustion product or air stream that is used to drive a turbine 24 .
  • the turbine 24 includes a plurality of stages 26 - 28 that are operationally connected to the compressor 12 through a compressor/turbine shaft 30 (also referred to as a rotor).
  • air flows into the compressor 12 and is compressed into a high pressure gas.
  • the high pressure gas is supplied to the combustor assembly 14 and mixed with fuel, for example process gas and/or synthetic gas (syngas), in the combustion chamber 18 .
  • fuel for example process gas and/or synthetic gas (syngas)
  • the fuel/air or combustible mixture ignites to form a high pressure, high temperature combustion gas stream.
  • the combustor assembly 14 can combust fuels that include, but are not limited to, natural gas and/or fuel oil.
  • the combustor assembly 14 channels the combustion gas stream to the turbine 24 which converts thermal energy to mechanical, rotational energy.
  • stage 26 is shown to include a plurality of rotating members, such as an airfoil 32 , which each extend radially outward from a central hub 34 having an axial centerline 35 .
  • the airfoil 32 is rotatable about the axial centerline 35 of the central hub 34 and includes a base portion 36 and a tip portion 38 .
  • a tip shroud 50 covers the tip portion 38 of the airfoil 32 .
  • the tip shroud 50 is designed to receive, or nest with, tip shrouds on adjacent rotating members in order to form a continuous ring that extends circumferentially about the stage 26 .
  • the continuous ring creates an outer flow path boundary that reduces gas path air leakage over top portions (not separately labeled) of the stage 26 , so as to increase stage efficiency and overall turbine performance.
  • adjacent airfoils interlock through the tip shroud 50 of each respective airfoil by virtue of centrifugal forces and thermal loads created by the operation of the turbine 24 .
  • the tip shroud 50 is illustrated in greater detail and is in close proximity with an adjacent tip shroud 52 .
  • the tip shroud 50 includes a contact region 54 configured to engage the adjacent tip shroud 52 during operation of the turbine system 10 .
  • the contact region 54 engages an adjacent contact region 56 of the adjacent tip shroud 52 .
  • a gap 58 is present between the tip shroud 50 and the adjacent tip shroud 52 , and more particularly between the contact region 54 and the adjacent contact region 56 .
  • the gap 58 is present prior to startup of the turbine system 10 .
  • the gap 58 is dimensionally selected based on a desirable early interlock of the tip shroud 50 and the adjacent tip shroud 52 upon operation of the turbine system 10 and rotation of the airfoil 32 . Subsequent to interlock of the tip shroud 50 and the adjacent tip shroud 52 , the operating environment increases in temperature, thereby resulting in thermal expansion of most components within the turbine 24 .
  • At least one of the contact region 54 and the adjacent contact region 56 include a negative thermal expansion material 60 .
  • the negative thermal expansion material 60 is defined by having a negative coefficient of thermal expansion, such that the material contracts in response to increased temperature exposure, rather than expanding. It is to be appreciated that any material having a negative coefficient of thermal expansion may be suitable for inclusion with the contact region 54 and the adjacent contact region 56 . Examples of such materials include zircon, zirconium tungstate and A 2 (MO 4 ) 3 compounds.
  • Forming at least a portion of the contact region 54 and the adjacent contact region 56 with the negative thermal expansion material 60 advantageously allows for the gap 58 to be dimensionally reduced to facilitate an early interlock between the tip shroud 50 and the adjacent tip shroud 52 , while also reducing the contact forces associated with interaction between the tip shroud 50 and the adjacent tip shroud 52 , thereby reducing stresses imposed on various portions of the tip shroud 50 , the adjacent tip shroud 52 and the airfoil 32 attached thereto.
  • the stress reduction is achieved by maintaining an interlock, but contracting the negative thermal expansion material 60 .
  • the contact region 54 comprises a first volume during a startup condition of the turbine system 10 and a smaller, second volume during a steady state operating condition of the turbine system 10 .
  • the tip shroud 50 includes a base metal region 62 that is coated or integrally formed with the contact region 54 .
  • the contact region 54 is formed of one or more composition layers that typically include a fraction of the negative thermal expansion material 60 and a fraction of a wear resistant material. As noted above, the contact region 54 may include a single composition layer ( FIG. 5 ) or a plurality of composition layers ( FIG. 6 ).
  • distinct volume and/or weight fractions of the negative thermal expansion material 60 may be present in the plurality of composition layers 72 , such as a first layer 64 , a second layer 68 and a third layer 70 , as shown.
  • the fraction of the negative thermal expansion material 60 progressively increases in each layer, relative to moving away from the base metal region 62 .
  • the first layer 64 may include a lower fraction of the negative thermal expansion material 60 than the second layer 68 , with the second layer 68 having a lower fraction than the third layer 70 .
  • each of the plurality of composition layers 72 may vary in thickness from one another and may comprise the negative thermal expansion material 60 in a fraction ranging from about 0% to about 100%.
  • the contact region 54 may be deposited or integrated with the tip shroud 50 in a number of application processes. Examples of such processes include brazing, welding, laser cladding, cold spraying and a plasma transferred arc (PTA) process.
  • PTA plasma transferred arc
  • the method of controlling turbine bucket interaction with an adjacent turbine bucket 100 includes reducing a gap between a contact region of a tip shroud and an adjacent tip shroud by depositing a negative thermal expansion material proximate the contact region 102 .
  • the contact region is engaged with the adjacent tip shroud during a startup operating condition 104 .
  • a volume of the contact region is decreased during increased temperature operating conditions upon contraction of the negative thermal expansion material 106 .

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Butt Welding And Welding Of Specific Article (AREA)
  • Laser Beam Processing (AREA)
US13/680,974 2012-11-19 2012-11-19 Turbine bucket shroud arrangement and method of controlling turbine bucket interaction with an adjacent turbine bucket Abandoned US20140140841A1 (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
US13/680,974 US20140140841A1 (en) 2012-11-19 2012-11-19 Turbine bucket shroud arrangement and method of controlling turbine bucket interaction with an adjacent turbine bucket
JP2013233585A JP2014101880A (ja) 2012-11-19 2013-11-12 タービン動翼シュラウド構成およびタービン動翼と隣接タービン動翼との相互作用を調節する方法
DE201310112791 DE102013112791A1 (de) 2012-11-19 2013-11-19 Turbinenschaufel-Mantelanordnung und Verfahren zur Steuerung der Turbinenschaufelwechselwirkung mit einer benachbarten Turbinenschaufel

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/680,974 US20140140841A1 (en) 2012-11-19 2012-11-19 Turbine bucket shroud arrangement and method of controlling turbine bucket interaction with an adjacent turbine bucket

Publications (1)

Publication Number Publication Date
US20140140841A1 true US20140140841A1 (en) 2014-05-22

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US13/680,974 Abandoned US20140140841A1 (en) 2012-11-19 2012-11-19 Turbine bucket shroud arrangement and method of controlling turbine bucket interaction with an adjacent turbine bucket

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US (1) US20140140841A1 (de)
JP (1) JP2014101880A (de)
DE (1) DE102013112791A1 (de)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10781700B2 (en) 2016-03-08 2020-09-22 Mitsubishi Heavy Industries Compressor Corporation Turbine rotor blade assembly
FR3107722A1 (fr) * 2020-02-27 2021-09-03 Safran Aircraft Engines Critère de non déboîtement
US20220282624A1 (en) * 2021-03-08 2022-09-08 Kabushiki Kaisha Toshiba Turbine rotor blade

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH06116035A (ja) * 1992-10-07 1994-04-26 Hitachi Ltd 炭素繊維束強化炭化ケイ素焼結体とその製造方法
US20040124231A1 (en) * 1999-06-29 2004-07-01 Hasz Wayne Charles Method for coating a substrate
US20080131723A1 (en) * 2004-11-30 2008-06-05 The Regents Of The University Of California Braze System With Matched Coefficients Of Thermal Expansion
US7824763B2 (en) * 2007-03-21 2010-11-02 General Electric Company Composite material for turbine support structure
JP2010285049A (ja) * 2009-06-11 2010-12-24 Nsk Ltd ステアリング装置

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10781700B2 (en) 2016-03-08 2020-09-22 Mitsubishi Heavy Industries Compressor Corporation Turbine rotor blade assembly
FR3107722A1 (fr) * 2020-02-27 2021-09-03 Safran Aircraft Engines Critère de non déboîtement
US20220282624A1 (en) * 2021-03-08 2022-09-08 Kabushiki Kaisha Toshiba Turbine rotor blade
US12006839B2 (en) * 2021-03-08 2024-06-11 Kabushiki Kaisha Toshiba Turbine rotor blade

Also Published As

Publication number Publication date
JP2014101880A (ja) 2014-06-05
DE102013112791A1 (de) 2014-05-22

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AS Assignment

Owner name: GENERAL ELECTRIC COMPANY, NEW YORK

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:GUMPINA, KRISHNA KISHORE;GIRI, SHEO NARAIN;JHA, SANJEEV KUMAR;AND OTHERS;REEL/FRAME:029323/0276

Effective date: 20121108

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION