EP2613006A1 - Turbinenanordnung und Verfahren zur Verringerung der Flüssigkeitströmung zwischen Turbinenkomponenten - Google Patents

Turbinenanordnung und Verfahren zur Verringerung der Flüssigkeitströmung zwischen Turbinenkomponenten Download PDF

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Publication number
EP2613006A1
EP2613006A1 EP12197661.7A EP12197661A EP2613006A1 EP 2613006 A1 EP2613006 A1 EP 2613006A1 EP 12197661 A EP12197661 A EP 12197661A EP 2613006 A1 EP2613006 A1 EP 2613006A1
Authority
EP
European Patent Office
Prior art keywords
fluid
stator
rotor
flow
passage
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Withdrawn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
EP12197661.7A
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English (en)
French (fr)
Inventor
Ramesh Kempanna Babu
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 EP2613006A1 publication Critical patent/EP2613006A1/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Withdrawn legal-status Critical Current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
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • F01D11/04—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type using sealing fluid, e.g. steam
    • 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
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • F01D11/04—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type using sealing fluid, e.g. steam
    • F01D11/06—Control thereof
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling

Definitions

  • the subject matter disclosed herein relates to turbines. More particularly, the subject matter relates to reducing fluid flow between components of 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 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.
  • 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 performance of the turbine.
  • a turbine assembly includes a stator and a rotor adjacent to the stator.
  • the turbine assembly also includes a passage formed in a member coupled to the rotor to form a fluid curtain between the rotor and stator, wherein the fluid curtain reduces a flow between the stator and rotor.
  • a method for reducing fluid flow between turbine components includes flowing a hot gas across a stator and flowing the hot gas across a rotor adjacent to the stator.
  • the method also includes flowing a cooling air flow through radially inner portions of the stator and rotor and flowing a fluid from a member on the rotor to the stator to reduce leaking of the flow of cooling air and the flow of hot gas between the stator and rotor.
  • 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 allow for thermal expansion and relative movement of the parts while hot gas flows through the turbine 106.
  • turbine efficiency is improved.
  • 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.
  • Methods, systems and arrangements to reduce fluid leakage between turbine parts, such as stators and rotors, are discussed in detail below with reference to FIGS. 2-4 .
  • the depicted arrangements provide a fluid curtain or seal to reduce fluid leakage into the hot gas flow, thereby increasing the work available to be extracted from the hot gas.
  • the fluid curtain is substantially lower maintenance as compared to other seals made of rubber and/or other material, which may wear out over time.
  • 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.
  • the turbine assembly 200 includes a rotor 202 and a stator 204 disposed about an axis 206.
  • the stator 204 includes a base 210 with an airfoil 208 (also referred to as a "nozzle") extending from the base 210.
  • the rotor 202 includes a disk 212 and a member 214 coupled to the disk 212.
  • the member 214 may be any suitable structure, such as a cover plate, and is configured to restrict flow of cooling fluid 224, such as air, into a hot gas flow 228 (also referred to as "hot gas path").
  • the disk 212 and member 214 include a passage 216 to receive a fluid from a fluid source 218, wherein the fluid is directed into a cavity 221 to form a fluid curtain 222.
  • the fluid curtain 222 (also referred to as "fluid barrier”, “fluid seal” or “fluid flow”) forms a restriction between the rotor 202 and stator 204 to reduce flow of the cooling fluid 224 and 226 into the hot gas flow 228. Further, the fluid curtain 222 reduces hot gas flow 228 radially inward between the rotor 202 and stator 204, thereby reducing thermal stress on assembly parts.
  • the fluid flows through the passage 216 through a projection 220 of the member 214, wherein the fluid curtain 222 flows at an angle with respect to the axis 206.
  • the angle may be any suitable angle for forming the fluid curtain 222 and may be altered based on a variety of factors, such as fluid type, temperatures, geometry of cavity 221 and/or projection 220. In an embodiment, the angle may range from about -45 to about 45 degrees. In another embodiment, the angle may range from about 15 to about 70 degrees. In yet another embodiment, the angle may range from about 20 to about 60 degrees. In another embodiment, the angle may range from about -15 to about 30 degrees.
  • the fluid curtain 222 may be formed by a fluid flow from any suitable fluid source, such as the fluid source 218 (e.g., air, water or other coolant) for temperature control of turbine components.
  • the fluid source 218 e.g., air, water or other coolant
  • the depicted formation of fluid curtain 222 between the rotor 202 and stator 204 provides improved performance by increasing the amount of work available to be extracted from the hot gas flow 228 while also providing a low maintenance seal or barrier that will not wear out or need replacement.
  • FIG. 3 is a side sectional view of a portion of an exemplary turbine assembly 300.
  • the turbine assembly 300 includes a rotor 302 and a stator 304 disposed about an axis 306.
  • the stator 304 includes a base 310 with an airfoil 308 (also referred to as a "nozzle") extending from the base 310.
  • the rotor 302 includes a disk 312 and a member 314 coupled to the disk 312.
  • the member 314 may be any suitable structure, such as a cover plate, and is configured to restrict flow of cooling fluid 324, such as air, into a hot gas flow 328.
  • the fluid curtain 322 reduces hot gas flow 328 radially inward between the rotor 302 and stator 304, thereby reducing thermal stress on assembly parts.
  • the disk 312 and member 314 include a passage 316 to receive a fluid from the passage 316, where the passage receives the cooling fluid 324 through an inlet 350.
  • the fluid flows through a projection and into a cavity 321 to form a fluid curtain 322.
  • the fluid curtain 322 (also referred to as "fluid barrier", “fluid seal” or “fluid flow”) forms a restriction between the rotor 302 and stator 304 to reduce flow of the cooling fluid 324 and 326 into the hot gas flow 328.
  • the cooling fluid 324 and 326 is fluid that flows through radially inner portions of the rotor 302 and stator 304 to control temperatures of the components.
  • the passage 316 is a narrowing passage to cause an increased fluid flow velocity within the passage, thereby increasing flow velocity of the fluid curtain 322.
  • the fluid flows through the passage 316 through the projection 320 of the member 314, wherein the fluid curtain 322 flows at an angle with respect to the axis 306. As discussed above with reference to FIG. 2 , the angle may be any suitable angle to restrict fluid flow into the hot gas flow 328.
  • FIG. 4 is a side sectional view of a portion of an exemplary turbine assembly 412 including a member 414 disposed in a rotor 416.
  • the member 414 includes a passage 408 to receive a cooling fluid 400 from an inlet 402.
  • the passage 408 directs the cooling fluid through an outlet 404 in the member 314 to form the fluid curtain 406.
  • the fluid curtain 406 forms a restrictive barrier between the rotor 416 and stator 304, thereby reducing fluid leakage across the turbine assembly 412.
  • the turbine assembly may have one or more passage form one or more fluid curtain, such as the curtains 406 and 322, reduce fluid flow between the rotor 416 and stator 304.
EP12197661.7A 2012-01-04 2012-12-18 Turbinenanordnung und Verfahren zur Verringerung der Flüssigkeitströmung zwischen Turbinenkomponenten Withdrawn EP2613006A1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/343,145 US20130170960A1 (en) 2012-01-04 2012-01-04 Turbine assembly and method for reducing fluid flow between turbine components

Publications (1)

Publication Number Publication Date
EP2613006A1 true EP2613006A1 (de) 2013-07-10

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EP12197661.7A Withdrawn EP2613006A1 (de) 2012-01-04 2012-12-18 Turbinenanordnung und Verfahren zur Verringerung der Flüssigkeitströmung zwischen Turbinenkomponenten

Country Status (5)

Country Link
US (1) US20130170960A1 (de)
EP (1) EP2613006A1 (de)
JP (1) JP2013139815A (de)
CN (1) CN103195500A (de)
RU (1) RU2012158336A (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3009613B1 (de) * 2014-08-19 2019-01-30 United Technologies Corporation Kontaktlose dichtungen für gasturbinenmotoren

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2837856B1 (de) * 2013-08-14 2016-10-26 General Electric Technology GmbH Flüssigkeitsdichtungsanordnung und Verfahren zum Einziehen einer Leckageströmung durch eine Leckagekluft
EP3073056B1 (de) * 2015-03-25 2018-01-03 Ansaldo Energia IP UK Limited Drahtplombe

Citations (3)

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US20020159880A1 (en) * 2001-04-26 2002-10-31 Honeywell International, Inc. Gas turbine disk cavity ingestion inhibitor
US20100008760A1 (en) * 2008-07-10 2010-01-14 Honeywell International Inc. Gas turbine engine assemblies with recirculated hot gas ingestion
US20110193293A1 (en) * 2010-02-10 2011-08-11 Rolls-Royce Plc Seal arrangement

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US1819864A (en) * 1930-03-24 1931-08-18 Gen Electric Elastic fluid turbine
US2489683A (en) * 1943-11-19 1949-11-29 Edward A Stalker Turbine
US3291447A (en) * 1965-02-15 1966-12-13 Gen Electric Steam turbine rotor cooling
FR2732405B1 (fr) * 1982-03-23 1997-05-30 Snecma Dispositif pour refroidir le rotor d'une turbine a gaz
US5018943A (en) * 1989-04-17 1991-05-28 General Electric Company Boltless balance weight for turbine rotors
US5232335A (en) * 1991-10-30 1993-08-03 General Electric Company Interstage thermal shield retention system
WO1996006266A1 (en) * 1994-08-24 1996-02-29 Westinghouse Electric Corporation Gas turbine blade with cooled platform
US5575616A (en) * 1994-10-11 1996-11-19 General Electric Company Turbine cooling flow modulation apparatus
JP3495579B2 (ja) * 1997-10-28 2004-02-09 三菱重工業株式会社 ガスタービン静翼
GB0513468D0 (en) * 2005-07-01 2005-08-10 Rolls Royce Plc A mounting arrangement for turbine blades
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US8708652B2 (en) * 2007-06-27 2014-04-29 United Technologies Corporation Cover plate for turbine rotor having enclosed pump for cooling air
US8206114B2 (en) * 2008-04-29 2012-06-26 United Technologies Corporation Gas turbine engine systems involving turbine blade platforms with cooling holes
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Patent Citations (3)

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Publication number Priority date Publication date Assignee Title
US20020159880A1 (en) * 2001-04-26 2002-10-31 Honeywell International, Inc. Gas turbine disk cavity ingestion inhibitor
US20100008760A1 (en) * 2008-07-10 2010-01-14 Honeywell International Inc. Gas turbine engine assemblies with recirculated hot gas ingestion
US20110193293A1 (en) * 2010-02-10 2011-08-11 Rolls-Royce Plc Seal arrangement

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3009613B1 (de) * 2014-08-19 2019-01-30 United Technologies Corporation Kontaktlose dichtungen für gasturbinenmotoren

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US20130170960A1 (en) 2013-07-04
RU2012158336A (ru) 2014-07-10
JP2013139815A (ja) 2013-07-18
CN103195500A (zh) 2013-07-10

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