EP2613009A2 - Turbine assembly and method for reducing fluid flow between turbine components - Google Patents

Turbine assembly and method for reducing fluid flow between turbine components Download PDF

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Publication number
EP2613009A2
EP2613009A2 EP12198421.5A EP12198421A EP2613009A2 EP 2613009 A2 EP2613009 A2 EP 2613009A2 EP 12198421 A EP12198421 A EP 12198421A EP 2613009 A2 EP2613009 A2 EP 2613009A2
Authority
EP
European Patent Office
Prior art keywords
slashface
pin
bucket
turbine
turbine assembly
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Withdrawn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
EP12198421.5A
Other languages
German (de)
English (en)
French (fr)
Inventor
Mahesh Pasupuleti
Shadab Ali
Mohankumar Banakar
Viswanathan Venkatachalapathy
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
Publication of EP2613009A2 publication Critical patent/EP2613009A2/en
Withdrawn legal-status Critical Current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
    • 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
    • F05D2240/55—Seals
    • 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
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/32—Retaining components in desired mutual position by means of magnetic or electromagnetic forces
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/507—Magnetic properties

Definitions

  • the subject matter disclosed herein relates to gas turbines. More particularly, the subject matter relates to reducing fluid flow between components or regions of gas turbines.
  • a combustor converts chemical energy of a fuel or an air-fuel mixture into thermal energy.
  • the thermal energy is conveyed by a fluid, often compressed hot air from a compressor, to a turbine where the thermal energy is converted to mechanical energy.
  • leakage of fluid between components into the compressed hot air causes a reduced power output and lower efficiency for the turbine.
  • leakage of compressed hot air into regions that are typically cooled by cooling fluid can cause component wear, which can lead to downtime for component repair or replacement. Leaks of fluid may be caused by thermal expansion of certain components and relative movement between components during operation of the gas turbine. Accordingly, reducing fluid leaks between components can improve efficiency and durability of the gas turbine.
  • a turbine assembly includes a first bucket with a first slashface and a second bucket including a recess formed in a second slashface of the second bucket, wherein the second slashface is adjacent to the first slashface when the first bucket is positioned adjacent to the second bucket.
  • the turbine assembly also includes a pin configured to be placed in the recess, wherein the pin is magnetically urged toward the first slashface to reduce fluid flow between the first and second buckets.
  • a method for reducing fluid flow between turbine components includes flowing a hot gas across a first bucket and second bucket, wherein the first and second buckets are adjacent. The method also includes flowing a cooling air flow through a radially inner portion of the first and second buckets and positioning a pin between the first and second buckets, wherein a magnetic property urges the pin toward a first slashface of the first bucket, wherein the pin reduces fluid flow between the first and second buckets.
  • FIG. 1 is a schematic diagram of an embodiment of a gas turbine system 100.
  • the system 100 includes a compressor 102, a combustor 104, a turbine 106, a shaft 108 and a fuel nozzle 110.
  • the system 100 may include a plurality of compressors 102, combustors 104, turbines 106, shafts 108 and fuel nozzles 110.
  • the compressor 102 and turbine 106 are coupled by the shaft 108.
  • the shaft 108 may be a single shaft or a plurality of shaft segments coupled together to form shaft 108.
  • the combustor 104 uses liquid and/or gas fuel, such as natural gas or a hydrogen rich synthetic gas, to run the engine.
  • fuel nozzles 110 are in fluid communication with an air supply and a fuel supply 112.
  • the fuel nozzles 110 create an air-fuel mixture, and discharge the air-fuel mixture into the combustor 104, thereby causing a combustion that heats a pressurized gas.
  • the combustor 104 directs the hot pressurized exhaust gas through a transition piece into a turbine nozzle (or "stage one nozzle") and then a turbine bucket, causing turbine 106 rotation.
  • the rotation of turbine 106 causes the shaft 108 to rotate, thereby compressing the air as it flows into the compressor 102.
  • the turbine components or parts are configured to be assembled with tolerances or gaps to allow for thermal expansion and relative movement of the parts while hot gas flows through the turbine 106.
  • turbine efficiency is improved. Specifically, reducing leakage of fluid into the hot gas path or compressed gas flow increases the volume of hot gas flow along the desired path, enabling more work to be extracted from the hot gas. Further, restricting or reducing flow of hot gas into cooling air enables a pressure difference betweent he fluids to be maintained and allows the cooling air to be directed to various parts of the turbine for cooling.
  • downstream and upstream are terms that indicate a direction relative to the flow of working fluid through the turbine.
  • downstream refers to a direction that generally corresponds to the direction of the flow of working fluid
  • upstream generally refers to the direction that is opposite of the direction of flow of working fluid.
  • radial refers to movement or position perpendicular to an axis or center line. It may be useful to describe parts that are at differing radial positions with regard to an axis. In this case, if a first component resides closer to the axis than a second component, it may be stated herein that the first component is "radially inward" of the second component.
  • first component resides further from the axis than the second component, it may be stated herein that the first component is “radially outward” or “outboard” of the second component.
  • axial refers to movement or position parallel to an axis.
  • circumferential refers to movement or position around an axis.
  • FIG. 2A is a front view of a first bucket 202 while FIG. 2B is a rear view of a second bucket 204 and members, such as pins 206, to be placed between the first bucket 202 and second bucket 204.
  • the first bucket 202 includes a shank 208, a platform 210 and an airfoil 212 or blade.
  • a slashface 214 of the first bucket 202 is configured to be adjacent to a slashface 216 of the second bucket 204 when the buckets are installed on a wheel or disk with the slashface surfaces facing each other.
  • the second bucket 204 includes a shank 218, a platform 220 and an airfoil 222 or blade.
  • Recesses 224 and 226 are located in the slashface 216 to receive pins 206, wherein the pins 206 reduce or restrict fluid flow between the first and second buckets 202, 204 when adjoining each other in the turbine.
  • the pins 206 are placed in the recesses 224, 226 to reduce flow of a hot gas 228 radially inward into a cooling air 230 and reduce flow of the cooling air 230 radially outward into the hot gas 228.
  • the pins 206 reduce axial flow 232 (i.e. along a turbine axis 250) of fluid between the adjacent buckets 202, 204.
  • Reducing fluid flow across the shanks 208 and 218 can help maintain a pressure (referred to as “positive pressure” or “pressure difference”) in the cooling air 230 relative to the hot gas 228, thereby enabling distribution of the cooling air 230 throughout the turbine to reduce thermal fatigue and wear. Moreover, preventing cooling fluid 230 from entering the hot gas 228 flow enables more work to be extracted from the hot gas 228 to improve turbine efficiency.
  • the pins 206 have a magnetic property, such as a magnetic layer 234, that urges the pins toward the slashfaces 214 to improve the seal or flow restriction.
  • the slashface 214 has a magnetic property, such as a magnetic layer 236, that urges the pins toward the slashface 214 to improve the seal or flow restriction.
  • a magnetic property in the slashface 216, such as magnetic layer 238, may also urge the pins 206 toward slashface 214.
  • the magnetic property in slashface 216 and recesses 224, 226 repel the pins from the slashface surface.
  • the magnetic properties and corresponding layers may be on a portion or substantially the entire surface of the pins 206, slashface 214 and slashface 216.
  • the pins 206 are urged toward the slashface 214 via at least one of the magnetic properties of the pins 206, slashface 214 and slashface 216.
  • the slashfaces 214 and 216, pins 206 and/or their magnetic layers include magnetic material that provides the desired magnetic properties, including, but not limited to, Alnico and Samarium Cobalt (SmCo 5 ).
  • Alnico or Samarium Cobalt may be applied as a layer or added to the part materials as powders, wherein the powders are capable of retaining magnetic properties at about 1000 degrees Fahrenheit.
  • the magnetic properties of the buckets 202, 204 and/or pins 206 are retained at about 1200 degrees Fahrenheit.
  • the magnetic field strength of the magnetized Alnico buckets 202, 204 and/or pins 206 is a BHmax (the magnetic field strength at the point of maximum energy product of a magnetic material) of about 5 Mega Gauss Oersteds (MGOe).
  • the magnetic field strength of the magnetized SmCo 5 buckets 202, 204 and/or pins 206 has a BHmax of about 32 MGOe.
  • the magnetic properties of the buckets 202, 204 and/or pins 206 may be provided by any suitable method.
  • the magnetic property is a characteristic of the material used to form the buckets or pins.
  • the magnetic property is applied to the member as a layer (e.g., layers 234, 236, 238) or coating, wherein the layer is applied to at least part of the surface of the member.
  • the magnetic layer may be an alloy (e.g., Alnico) powder, applied by sintering, cladding, adhesives and/or a spray, such as a cold spray.
  • the alloy powder is blended with a wax lubricant before the blend or mixture is compacted to the desired shape of the strip.
  • One or more strips are compacted to a thickness of 30 mils and sintered at a protective hydrogen atmosphere.
  • the sintered strips may be tested to ensure the desired magnetic properties are provided.
  • the strip may also be treated to achieve the desired strength properties. Further, the strips may be machined down to achieve a desired thickness to account for part expansion during heat treatment.
  • the magnetic layer is clad to the bucket shank or pin using a laser.
  • a spray technique such as cold spraying, may be used to apply the layer or coating of magnetic alloy powder to the slashface and/or pins.
  • Alnico and/or SmCo 5 powders are sprayed directly on to the shank of the buckets or pins and are then heat treated.
  • the application process may use a High Velocity Oxygen Fuel (HVOF) spray or cold spray depending on the application.
  • HVOF High Velocity Oxygen Fuel
  • FIG. 3 is a detailed side section view of an embodiment of a turbine assembly 300.
  • the turbine assembly 300 includes a first bucket 302 and second bucket 304.
  • a member, such as a pin 310, is positioned in a recess 312 of the first bucket to reduce fluid flow between the buckets.
  • the assembled parts include the first bucket 302 with a slashface 306 adjacent to a slashface 308 of the second bucket 304.
  • the slashfaces 306 and 308 may be oriented at a variety of angles with respect to a radius 314 of the turbine and, therefore, the pin 310 may be subjected to a variety of forces that may affect the pin's sealing properties.
  • a force such as a normal force, occurs at a contact point 322, wherein the force acts to move the pin 310 away from the slashface 308, thereby leading to an increased fluid flow between the buckets.
  • a centrifugal force caused by rotation of the buckets 302, 304 may also urge the pin 310 away from the slashface 308.
  • the slashface 308 has a magnetic property such as a magnetic layer 318 that urges the pin 310 in a tangential direction 316 toward the slashface 308.
  • the recess 312 has a magnetic property, such as a magnetic layer 320 to repel or urge the pin 310 toward the slashface 308.
  • the pin 310 may also have a magnetic property, such as magnetic layer 324, which urges the pin 310 in the direction 316 toward the slashface 308.
  • magnetic properties of the recess 312 (in slashface 306), slashface 308, pin 310 or any combination thereof provide urging of the pin 310 toward slashface 308.
  • the magnetic properties may include any suitable material or treatment of material, including layers and/or strips, applied by any suitable method to one or more parts of the turbine bucket assembly.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Coating By Spraying Or Casting (AREA)
EP12198421.5A 2012-01-04 2012-12-20 Turbine assembly and method for reducing fluid flow between turbine components Withdrawn EP2613009A2 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/343,301 US20130170944A1 (en) 2012-01-04 2012-01-04 Turbine assembly and method for reducing fluid flow between turbine components

Publications (1)

Publication Number Publication Date
EP2613009A2 true EP2613009A2 (en) 2013-07-10

Family

ID=47665822

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12198421.5A Withdrawn EP2613009A2 (en) 2012-01-04 2012-12-20 Turbine assembly and method for reducing fluid flow between turbine components

Country Status (5)

Country Link
US (1) US20130170944A1 (ja)
EP (1) EP2613009A2 (ja)
JP (1) JP2013139792A (ja)
CN (1) CN103195488A (ja)
RU (1) RU2012158304A (ja)

Cited By (1)

* 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

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP6256836B2 (ja) * 2014-01-24 2018-01-10 三菱重工業株式会社 回転機械翼及び回転機械
JP6270531B2 (ja) * 2014-02-21 2018-01-31 三菱日立パワーシステムズ株式会社 動翼体及び回転機械
JP6185031B2 (ja) * 2015-09-28 2017-08-23 京セラ株式会社 携帯機器、制御方法及び制御プログラム

Family Cites Families (8)

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Publication number Priority date Publication date Assignee Title
US2912223A (en) * 1955-03-17 1959-11-10 Gen Electric Turbine bucket vibration dampener and sealing assembly
US5675874A (en) * 1996-02-16 1997-10-14 Chen; Chi-Yueh Magnetic fastener
US7575416B2 (en) * 2006-05-18 2009-08-18 United Technologies Corporation Rotor assembly for a rotary machine
CN101174494B (zh) * 2006-10-31 2010-05-12 富士康(昆山)电脑接插件有限公司 线缆及其制造方法
US7819666B2 (en) * 2008-11-26 2010-10-26 Schlumberger Technology Corporation Rotating electrical connections and methods of using the same
US8657574B2 (en) * 2010-11-04 2014-02-25 General Electric Company System and method for cooling a turbine bucket
US8790086B2 (en) * 2010-11-11 2014-07-29 General Electric Company Turbine blade assembly for retaining sealing and dampening elements
US8684695B2 (en) * 2011-01-04 2014-04-01 General Electric Company Damper coverplate and sealing arrangement for turbine bucket shank

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None

Cited By (1)

* 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

Also Published As

Publication number Publication date
CN103195488A (zh) 2013-07-10
US20130170944A1 (en) 2013-07-04
RU2012158304A (ru) 2014-07-10
JP2013139792A (ja) 2013-07-18

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