EP2716876A1 - Joint d'étancheité refroidi - Google Patents

Joint d'étancheité refroidi Download PDF

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Publication number
EP2716876A1
EP2716876A1 EP13186957.0A EP13186957A EP2716876A1 EP 2716876 A1 EP2716876 A1 EP 2716876A1 EP 13186957 A EP13186957 A EP 13186957A EP 2716876 A1 EP2716876 A1 EP 2716876A1
Authority
EP
European Patent Office
Prior art keywords
seal
high pressure
cooling
components
cooling air
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Withdrawn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
EP13186957.0A
Other languages
German (de)
English (en)
Inventor
Ibrahim Sezer
Randall Richard Good
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 EP2716876A1 publication Critical patent/EP2716876A1/fr
Withdrawn legal-status Critical Current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
    • F01D11/003—Preventing or minimising internal leakage of working-fluid, e.g. between stages by packing rings; Mechanical seals
    • 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
    • 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
    • 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
    • F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
    • 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
    • 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
    • F05D2260/20—Heat transfer, e.g. cooling

Definitions

  • the present application and resultant patent relate generally to gas turbine engines and more particularly relate to solid seals and the like having cooling pathways extending therethrough.
  • turbo-machinery such as gas turbine engines and the like include a main gas flow path extending therethrough.
  • Gas leakage either out of the gas flow path or into the gas flow path, may lower overall gas turbine efficiency, increase fuel costs, and possibly increase emission levels.
  • Secondary flows also may be used within the gas turbine engine to cool the various heated components.
  • cooling air may be extracted from the later stages of the compressor for use in cooling the heated components and for purging gaps and cavities between adjacent components.
  • seals may be placed between turbine components such as stators and the like. These locations, however, may face very high temperatures and velocities that may lead to heavy oxidation and even seal failure. This potential damage may be mitigated somewhat by providing purge air to the gap with the seal therein. This purge air, however, may be a largely inefficient use of the cooling air.
  • Such a solid seal may be cooled with less flow than is generally necessary to purge the gap therein for higher overall efficiency and with increased component lifetime.
  • the present application and the resultant patent thus provide a seal for use between components facing a high pressure cooling air flow and a hot gas path in a gas turbine engine and the like.
  • the seal may include a first surface facing the high pressure cooling air flow, a second surface having a second surface air plenum facing the hot gas path, and a number of cooling pathways extending from the first surface to the second surface air plenum of the second surface for the high pressure cooling air flow to pass therethrough.
  • the present application and the resultant patent further provide a method of cooling a seal positioned between components in a gas turbine engine.
  • the method may include the steps of flowing high pressure cooling air about a first surface of the seal, drawing the high pressure cooling air through a number of cooling pathways in the seal, and drawing the high pressure cooling air through an air plenum about a second surface of the seal towards a hot gas path.
  • the method may include the further step of cooling the components with the high pressure cooling air passing through the air plenum.
  • the present application and the resultant patent further provide a solid seal for use between components facing a high pressure cooling air flow and a hot gas path in a gas turbine engine.
  • the solid seal may include a first surface with a first surface air plenum facing the high pressure cooling air flow, a second surface with a second surface air plenum facing the hot gas path, and a number of cooling pathways extending from the first surface air plenum of the first surface to the second surface air plenum of the second surface for the high pressure cooling air flow to pass therethrough.
  • Fig. 1 shows a schematic view of gas turbine engine 10 as may be used herein.
  • the gas turbine engine 10 may include a compressor 15.
  • the compressor 15 compresses an incoming flow of air 20.
  • the compressor 15 delivers the compressed flow of air 20 to a combustor 25.
  • the combustor 25 mixes the compressed flow of air 20 with a pressurized flow of fuel 30 and ignites the mixture to create a flow of combustion gases 35.
  • the gas turbine engine 10 may include any number of combustors 25.
  • the flow of combustion gases 35 is in turn delivered to a turbine 40.
  • the flow of combustion gases 35 drives the turbine 40 so as to produce mechanical work.
  • the mechanical work produced in the turbine 40 drives the compressor 15 via a shaft 45 and an external load 50 such as an electrical generator and the like.
  • the gas turbine engine 10 may use natural gas, various types of syngas, and/or other types of fuels.
  • the gas turbine engine 10 may be any one of a number of different gas turbine engines offered by General Electric Company of Schenectady, New York, including, but not limited to, those such as a 7 or a 9 series heavy duty gas turbine engine and the like.
  • the gas turbine engine 10 may have different configurations and may use other types of components.
  • Other types of gas turbine engines also may be used herein.
  • Multiple gas turbine engines, other types of turbines, and other types of power generation equipment also may be used herein together.
  • the seal 100 may have a substantial "I-beam" like shape 180.
  • the seal 100 may include a first plenum 190 defined by a first peripheral lip 200 about the top surface 110 thereof and a second plenum 210 defined by a second peripheral lip 220 about the bottom surface 120 thereof.
  • the plenums 190, 210 thus may be recessed areas within the top surface 110 and the bottom surface 120 of the seal.
  • the plenums 190, 210 and the peripheral lips 200, 220 may have any size, shape, or configuration. Multiple plenums 190, 210 also may be used.
  • the peripheral lips 200, 220 may define a first blocked end 230 on the first end 150 and a second blocked end 240 on the second end 160.
  • the blocked ends 220, 240 may have any size, shape, or configuration. One or more open ends also may be used. Alternatively, the blocked ends 220, 240 may have cooling holes or slots positioned therein. Other components and other configurations may be used herein.
  • the seal 100 also may include a number of cooling pathways 250 extending therethrough from the first plenum 190 to the second plenum 210. Any number of the cooling pathways 250 may be used herein.
  • the cooling pathways 250 may have any suitable size, shape, or configuration. Further, the cooling pathways 250 may extend through the seal 100 at a straight and/or an angled configuration. Any angle or combinations of angles may be used.
  • the cooling pathways 250 may be formed by drilling or other types of manufacturing techniques. Cooling pathways 250 of differing configurations may be used herein together. Other components and other configurations may be used herein.
  • the seal 100 may be positioned between the first component 92 and the second component 94 within the seal slot 95.
  • the top surface 110 of the seal 100 may face the high pressure cooling air 96 while the bottom surface 120 may face the lower pressure hot gas path 98.
  • the seal 100 may have any number of the cooling pathways 250 extending therethrough in any configuration.
  • the seal cooling pathways 250 extending into the second plenum 210 also act as impingement holes and/or purge holes for the seal slot 95.
  • the pressure differential between the high pressure cooling air 96 and the lower pressure hot gas path 98 draws the high pressure cooling air 96 through the cooling pathways 250 and into the second plenum 210 about the bottom surface 120 of the seal 100.
  • the high pressure cooling air 96 thus enhances heat transfer through the seal 100 and impinges upon/purges the seal slot 95 via the impingement holes.
  • the cooling pathways 250 may be positioned strategically near localized hot spots or uniformly along the length of the seal 100.
  • the cooling pathways 250 may have any prescribed pitch along the length of the seal 100.
  • the use of the blocked ends 230, 240 also substantially limits any gap leakage about the ends 150, 160 of the seal 100.
  • the seal 100 and the cooling pathways 250 therethrough thus provide purging and cooling of the bottom surface 120 or the slash face as well as about the sealing slot 95 in an efficient manner.
  • the seal 100 described herein may provide increased seal lifetime, reduced secondary flows, higher overall engine efficiency, and a reduced heat rate.
  • the seal 100 may be original equipment or part of a retro-fit. Different configurations of the seals 100 may be used together herein.
  • the seal 100 also may be applicable for use in other types of sealing locations. Specifically, the seal 100 may be used between any two components with a pressure differential therebetween for a flow of cooling air.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP13186957.0A 2012-10-03 2013-10-01 Joint d'étancheité refroidi Withdrawn EP2716876A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/633,890 US20140093353A1 (en) 2012-10-03 2012-10-03 Solid seal with cooling pathways

Publications (1)

Publication Number Publication Date
EP2716876A1 true EP2716876A1 (fr) 2014-04-09

Family

ID=49322199

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13186957.0A Withdrawn EP2716876A1 (fr) 2012-10-03 2013-10-01 Joint d'étancheité refroidi

Country Status (4)

Country Link
US (1) US20140093353A1 (fr)
EP (1) EP2716876A1 (fr)
JP (1) JP2014074406A (fr)
CN (1) CN103711530A (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3088681A1 (fr) * 2015-04-28 2016-11-02 General Electric Company Joints avec voies de refroidissement et refroidissement dosé

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20130234396A1 (en) * 2012-03-09 2013-09-12 General Electric Company Transition Piece Aft-Frame Seals
GB201603556D0 (en) * 2016-03-01 2016-04-13 Rolls Royce Plc An intercomponent seal for a gas turbine engine
JP6650849B2 (ja) 2016-08-25 2020-02-19 三菱日立パワーシステムズ株式会社 ガスタービン

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2195403A (en) * 1986-09-17 1988-04-07 Rolls Royce Plc Improvements in or relating to sealing and cooling means
US5388962A (en) * 1993-10-15 1995-02-14 General Electric Company Turbine rotor disk post cooling system
EP1521018A1 (fr) * 2003-10-02 2005-04-06 ALSTOM Technology Ltd Joint d'étanchéité haute températures
US20060083620A1 (en) * 2004-10-15 2006-04-20 Siemens Westinghouse Power Corporation Cooling system for a seal for turbine vane shrouds
US20080118346A1 (en) * 2006-11-21 2008-05-22 Siemens Power Generation, Inc. Air seal unit adapted to be positioned adjacent blade structure in a gas turbine
DE102007062681A1 (de) * 2007-12-24 2009-06-25 Man Turbo Ag Dichtsegment sowie Dichtsegmentenanordnung

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8382424B1 (en) * 2010-05-18 2013-02-26 Florida Turbine Technologies, Inc. Turbine vane mate face seal pin with impingement cooling

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2195403A (en) * 1986-09-17 1988-04-07 Rolls Royce Plc Improvements in or relating to sealing and cooling means
US5388962A (en) * 1993-10-15 1995-02-14 General Electric Company Turbine rotor disk post cooling system
EP1521018A1 (fr) * 2003-10-02 2005-04-06 ALSTOM Technology Ltd Joint d'étanchéité haute températures
US20060083620A1 (en) * 2004-10-15 2006-04-20 Siemens Westinghouse Power Corporation Cooling system for a seal for turbine vane shrouds
US20080118346A1 (en) * 2006-11-21 2008-05-22 Siemens Power Generation, Inc. Air seal unit adapted to be positioned adjacent blade structure in a gas turbine
DE102007062681A1 (de) * 2007-12-24 2009-06-25 Man Turbo Ag Dichtsegment sowie Dichtsegmentenanordnung

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3088681A1 (fr) * 2015-04-28 2016-11-02 General Electric Company Joints avec voies de refroidissement et refroidissement dosé
US9581037B2 (en) 2015-04-28 2017-02-28 General Electric Company Seals with cooling pathways and metered cooling

Also Published As

Publication number Publication date
US20140093353A1 (en) 2014-04-03
JP2014074406A (ja) 2014-04-24
CN103711530A (zh) 2014-04-09

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