EP2730748A2 - Système de refroidissement d'un composant de gaz chaud, chambre de combustion de turbine à gaz et procédé de refroidissement associés - Google Patents

Système de refroidissement d'un composant de gaz chaud, chambre de combustion de turbine à gaz et procédé de refroidissement associés Download PDF

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Publication number
EP2730748A2
EP2730748A2 EP13192280.9A EP13192280A EP2730748A2 EP 2730748 A2 EP2730748 A2 EP 2730748A2 EP 13192280 A EP13192280 A EP 13192280A EP 2730748 A2 EP2730748 A2 EP 2730748A2
Authority
EP
European Patent Office
Prior art keywords
hot gas
cooling
gas path
cooling chamber
path component
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Withdrawn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
EP13192280.9A
Other languages
German (de)
English (en)
Inventor
Wei Chen
Roy Marshall Washam
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 EP2730748A2 publication Critical patent/EP2730748A2/fr
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/002—Wall structures
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
    • 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
    • F05D2240/00—Components
    • F05D2240/35—Combustors or associated equipment
    • 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
    • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
    • 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
    • F05D2260/205—Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes

Definitions

  • the present invention generally relates to a hot gas path component disposed within a combustor of a gas turbine. More particularly, this invention relates to impingement cooling a portion of the hot gas component.
  • a typical gas turbine includes a compressor section, a combustion section downstream from the compressor section, and a turbine section downstream from the combustor.
  • the combustion section generally includes a combustor having various annular shaped hot gas path components such as a combustion liner and/or a transition duct that at least partially define a hot gas path that extends between the combustion section and the turbine section.
  • Each of the hot gas path components generally includes an inner surface and an outer surface.
  • the combustion section further includes a casing that surrounds the hot gas path components and defines a plenum that is in fluid communication with the compressor section.
  • a compressed working fluid such as ambient air is routed from the compressor section into the plenum of the combustion section.
  • a portion of the compressed working fluid is mixed with a fuel to form a combustible mixture in a combustion chamber that is typically defined within the combustion liner.
  • the combustible mixture is burned to produce a high temperature and high velocity hot gas that flows through the hot gas path and into the turbine section.
  • a portion of the compressed working fluid is used as a cooling medium to cool the outer surfaces and other hot segments of the various hot gas path components.
  • the cooling medium may be directed across the outer surfaces of the various hot gas path components so as to convectively and/or conductively cool those surfaces.
  • Certain areas of the hot gas path components such as an aft end of the combustion liner or an aft end of the transition duct may be particularly sensitive to thermal stress. As a result, those areas gain significant benefit from focusing a jet of the cooling medium onto the outer surface of the hot gas path component, thereby significantly increasing the rate of heat transfer or cooling effectiveness between the cooling medium and the hot gas path component.
  • This method of cooling is known in the industry as impingement or jet impingement cooling.
  • the cooling medium is routed through one or more cooling passages that are configured to impinge/focus the compressed working fluid onto a particular area of the outer surface of one of the hot gas path components.
  • the cooling medium impinges on the outer surface of one of the hot gas path components and is then routed directly into the hot gas path and/or it is reintroduced back into the stream of the compressed working fluid where it may be mixed with the fuel for combustion.
  • One embodiment of the present invention is a system for cooling a hot gas path component for a combustor.
  • the system generally includes an impingement sleeve that circumferentially surrounds an outer surface of the hot gas path component.
  • a first cooling chamber is defined between the impingement sleeve and a first portion of the outer surface of the hot gas path component.
  • a second cooling chamber is disposed downstream from the first cooling chamber.
  • the second cooling chamber is defined between the impingement sleeve and a second portion of the outer surface of hot gas path component.
  • An inlet extends through the impingement sleeve so as to define a first flow path into the first cooling chamber.
  • An outlet defines a second flow path between the first cooling chamber and the second cooling chamber.
  • FIG. 1 Another embodiment of the present invention is a combustor for a gas turbine having an outer casing and an annular hot gas path component circumferentially surrounded by the casing.
  • the hot gas path component is radially separated from the casing so as to at least partially define a flow passage therebetween.
  • the hot gas path component includes a main body that defines a first cooling chamber and a second cooling chamber along an outer surface of the main body. The second cooling chamber being downstream from the first cooling chamber.
  • An impingement sleeve circumferentially surrounds the first and the second cooling chambers.
  • An inlet extends through the impingement sleeve.
  • the inlet defines a first flow path between the flow passage and the first cooling chamber.
  • An outlet extends through the impingement sleeve downstream from the inlet.
  • the outlet defines a second flow path between the first cooling chamber and the second cooling chamber.
  • Another embodiment of the present invention includes a method for cooling a portion of an outer surface of a hot gas path component disposed within a combustor of a gas turbine.
  • the method includes routing a cooling medium through an inlet that extends through an impingement sleeve.
  • the cooling medium is impinged onto a first portion of the outer surface of the hot gas path component.
  • the cooling medium is routed through an outlet that extends through the impingement sleeve.
  • the cooling medium is re-impinged onto a second portion of the outer surface of the hot gas path component.
  • Various embodiments of the present disclosure include a system for cooling a portion of a combustor hot gas path component such as a combustion liner or a transition duct.
  • the system generally includes an impingement sleeve that circumferentially surrounds the hot gas component.
  • a first cooling chamber is positioned upstream from a second cooling chamber. The first and the second cooling chambers are surrounded by the impingement plate.
  • a cooling medium flows through an inlet into the first cooling chamber and is impinged onto a portion of an outer surface of the hot gas path component.
  • the cooling medium is then routed through an outlet that extends through the impingement plate.
  • the cooling medium is re-focused and impinged onto a second portion of the outer surface of the hot gas path component, thereby further utilizing the cooling medium for cooling the hot gas path component.
  • Fig. 1 provides a simplified cross-section of an exemplary combustion section 10, such as may be included in a gas turbine
  • Fig. 2 provides a perspective, partial cut-away view of a portion of a combustor 12 of the combustion section as shown in Fig. 1
  • the combustion section 10 generally includes a casing 14 that surrounds the combustor 12.
  • An end cover 16 is connected to a portion of the casing 14 at one end of the combustor 12.
  • At least one fuel nozzle 18 extends axially downstream from the end cover 16.
  • the at least one fuel nozzle 18 extends through a cap assembly 20 that extends radially within the casing 14.
  • the hot gas path components 22 extend downstream from the cap assembly 20 so as to define a hot gas path 24 through the combustor 12.
  • the hot gas path components 22 generally include an annular combustion liner 26 and an annular transition duct 28.
  • the combustion liner 26 extends downstream from the cap assembly 20.
  • a combustion chamber 30 is at least partially defined within the combustion liner 26 downstream from the at least one fuel nozzle 18.
  • the transition duct 28 extends downstream from the combustion liner 26 and terminates adjacent to a first stage nozzle 32 that is disposed adjacent to an inlet 34 of a turbine 36.
  • a first flow sleeve 38 at least partially surrounds the transition duct 28, and a second flow sleeve 40 at least partially surrounds the combustion liner 26.
  • An annular flow passage 42 is defined between the first flow sleeve 38 and the transition duct 28, and the second flow sleeve 40 and the combustion liner 26.
  • the first flow sleeve 38 generally includes a plurality of cooling passages 44 that define a flow path between a plenum 46 defined within the combustion section casing 14 and the annular flow passage 42.
  • the second flow sleeve 40 may include one or more cooling passages 48 that define a flow path between the plenum 46 and the annular flow passage 42.
  • a working fluid such as compressed air 50 is routed into the plenum 46 of the combustion section 10 from a compressor (not shown) such as an axial compressor positioned upstream from the combustion section 10.
  • a compressor such as an axial compressor positioned upstream from the combustion section 10.
  • a primary portion of the compressed air 50 is routed through the cooling passages 44, 48 into the annular flow passage.
  • the compressed air 50 is used as a cooling medium 52 to provide impingement, convective, and/or conductive cooling to an outer surface 54 ( Fig. 2 ) of the transition duct 28 and/or to an outer surface 56 ( Fig. 2 ) of the combustion liner 26.
  • the cooling medium 52 travels along the annular flow passage 42 before reversing direction at the end cover 16.
  • the cooling medium 52 then flows past the one or more fuel nozzles 18 and through the end cap 20 where it is mixed with a fuel and burned in the combustion chamber 30, thereby producing a hot gas 58 that flows through the hot gas path 24, across the first stage nozzle 32 and into the inlet 34 of the turbine 36.
  • the hot gas 58 results in high thermal stresses on the combustion liner 26 and/or the transition duct 28, thereby limiting the mechanical life of those hot gas path components 22. More specifically, as shown in Fig. 2 , an aft end 60 of the combustion liner 26 and/or an aft end 62 of the transition duct 28 may be particularly sensitive to the high thermal stresses produced by the hot gas 58.
  • the combustion liner 26 generally includes an annular main body 64 and a forward end 66 that is axially separated from the aft end 60.
  • the outer surface 56 of the combustion liner generally extends between the forward and aft ends 66, 60.
  • the transition duct 28 generally includes an annular main body 68 and a forward end 70 that is upstream from the aft end 62.
  • the aft end 60 of the combustion liner 26 is generally seated within the forward end 70 of the transition duct 28.
  • Fig. 3 illustrates a cross section side view of a system for cooling the various hot gas path components 72, herein referred to as "the system 72", according to one embodiment of the present disclosure.
  • Fig. 4 illustrates a cross section perspective view of an impingement sleeve 74 portion of the system 72 as shown in Fig. 3
  • Fig. 5 illustrates a cross section perspective view of a portion of the aft end 60 of the combustion liner 26 as shown in Fig. 2 , according to one embodiment of the present disclosure.
  • the system 72 may be deployed at the aft end 60 of the combustion liner and/or on the transition duct 28.
  • the system 72 is deployed at the aft end 60 of the combustion liner 26.
  • the system 72 generally includes an impingement sleeve 74 having an upper portion 76 and a lower portion 78.
  • the impingement sleeve 74 at least partially circumferentially surrounds the outer surface 56 of the combustion liner 26.
  • a first cooling chamber 80 is defined between the upper portion 76 of the impingement sleeve 74 and a first portion 82 of the outer surface 56 of the combustion liner 26.
  • a second cooling chamber 84 is defined downstream from the first cooling chamber 80 between the lower portion 78 of the impingement sleeve 74 and a second portion 86 of the outer surface 56 of the combustion liner 26.
  • the second cooling chamber 84 is disposed generally adjacent to the aft end 60 of the combustion liner 26.
  • the annular main body 64 of the combustion liner 26 at least partially defines at least one of the first cooling chamber 80 or the second cooling chamber 84.
  • at least one of the first or the second cooling chambers 80, 84 may be cast and/or machined into the main body 64 of the combustion liner 26.
  • the system 72 may comprise of separate components such as a liner extension that at least partially defines at least one of the first or the second cooling chambers 80, 84. The separate components may be welded or otherwise joined to the aft end 60 of the combustion liner 26.
  • a transversely extending rail member 88 at least partially separates the first cooling chamber 80 from the second cooling chamber 84.
  • the rail member 88 may at least partially provide a seating surface for supporting and/or joining the impingement sleeve 74 to the main body 64 of the combustion liner 26.
  • a first radially extending support member 90 extends between the first portion 80 of the outer surface 56 and the upper portion 76 of the impingement sleeve 74.
  • the first support member 90 provides radial separation between the upper portion 76 of the impingement sleeve 74 and the rail member 88.
  • the first support member 90 may at least partially define a seating surface for supporting and/or joining the impingement sleeve 74 to the main body 64 of the combustion liner 26.
  • a second radially extending support member 92 extends between the second portion 86 of the outer surface 56 of the combustion liner 26 and an end portion 94 of the impingement sleeve 74. As shown in Fig.
  • the second support member 92 may provide radial separation between the lower portion 78 and/or the end portion 94 of the impingement sleeve 74 and the second portion 86 of the outer surface 56.
  • the second support member 92 may at least partially provide a seating surface for supporting and/or joining the impingement sleeve 74 to the combustion liner 26.
  • the lower portion 78 of the impingement sleeve 74 is radially separated from the upper portion 76 of the impingement sleeve 74.
  • the lower portion 78 extends substantially axially downstream from the rail member 88 and is generally parallel to the upper portion 76 of the impingement sleeve 74.
  • a flow channel 95 is at least partially defined between the upper portion 76 and the lower portion 78 of the impingement sleeve 74.
  • an inlet or cooling passage 96 extends through the upper portion 76 of the impingement sleeve 74. As shown in Fig. 3 , the inlet 96 defines a cooling flow path 98 between the annular flow passage 42 and the first cooling chamber 80. In operation, the annular flow passage 42 is generally held at a higher pressure than the first cooling chamber 80. As a result, the cooling medium 52 flows along the cooling flow path 98 and into the first cooling chamber 80. In particular embodiments, as shown in Figs.
  • the inlet is configured to focus or impinge the cooling medium 52 onto a small area of the first portion 82 of the outer surface 56 of the combustion liner 26 at a high velocity, thereby increasing the heat transfer rate of the cooling medium 52.
  • the inlet 96 may be tapered, chamfered or concaved from a top surface 100 of the upper portion 76 of the impingement sleeve 74. In this manner, the cooling medium 52 may be concentrated into a cooling jet to more effectively cool the first portion 82 of the outer surface 56 within the first cooling chamber 80.
  • a scoop or other flow catching device 102 may extend radially outward from and at least partially surround the inlet 96.
  • the scoop 102 generally faces the direction of flow of the cooling medium 52 flowing through the annular flow passage 42 ( Fig. 3 ).
  • friction reduces the velocity of a portion of the cooling medium 52 flowing closest to the outer surfaces 54, 56 of the transition duct 28 and/or the combustion liner 26.
  • the scoop 102 captures a portion of the cooling medium 52 that is radially separated from those surfaces 54, 56, thereby increasing the velocity of the cooling medium 52 flowing into the first cooling chamber 80 ( Fig. 3 ).
  • the heat transfer rate of the cooling medium 52 is increased, thereby providing improved cooling to the first portion 82 of the outer surface 56 of the combustion liner 26 disposed within the first cooling chamber 80.
  • an outlet or cooling passage 104 extends through the lower portion 78 of the impingement sleeve 74.
  • the outlet 104 defines a cooling flow path 106 that extends between the first cooling chamber 80 and the second cooling chamber 84.
  • the first cooling chamber 80 is generally at a higher pressure than the second cooling chamber 84.
  • the cooling medium 52 flows from the first cooling chamber 80 along the cooling flow path 106 and into the second cooling chamber 84.
  • the outlet 104 is configured to focus or impinge the cooling medium 52 from the first cooling chamber 80 onto a small or concentrated area of the second portion 86 of the outer surface 56 of combustion liner 26, thereby increasing the heat transfer rate of the cooling medium 52.
  • the outlet 104 may be tapered, chamfered or concaved radially inward from an outer surface 107 ( Fig. 4 ) of the lower portion 78 of the impingement sleeve 74.
  • the cooling medium 52 may be concentrated into a cooling jet and re-impinged on the second portion 86 of the outer surface 56 within the second cooling chamber 84 so as to further utilize the cooling capability of the cooling medium 52 routed from the first cooling chamber 80.
  • an exhaust outlet 108 is at least partially defined between the end portion 94 and/or the lower portion 78 of the impingement sleeve 74 and the second portion 86 of the outer surface 56 of the combustion liner 26.
  • the exhaust outlet 108 defines a flow path 110 between the second cooling chamber 84 and the transition duct 28. In this manner, the cooling medium 52 is routed from the exhaust passage 110 along an inner surface 112 of the transition duct 28 so as to provide film cooling to the transition duct 28 inner surface 112.
  • the exhaust outlet 108 routes the cooling medium 52 from the second cooling chamber 84 to the first stage of stationary vanes 32 ( Fig. 1 ) disposed at the aft end 62 of the transition duct 28.
  • the cooling medium 52 may provide film cooling to the first stage of stationary nozzles 32 ( Fig. 1 ).
  • the cooling medium 52 flows from the annular flow passage 42 along the flow path 98 through the inlet 98 that extends through the upper portion 76 of the impingement sleeve 74.
  • the cooling medium 52 is impinged onto the first portion 82 of the outer surface 56 of the combustion liner 26 and heat is transferred from the first portion 82 of the outer surface 56 to the cooling medium 52.
  • the cooling medium 52 is then routed from the first cooling chamber 80 along the flow path 106 that extends between the first cooling chamber 80 and the second cooling chamber 84.
  • the cooling medium 52 flows through the outlet 104 of the lower portion 78 of the impingement sleeve 74 and into the second cooling chamber 84, the cooling medium 52 is focused so that it is re-impinged onto the second portion 86 of the outer surface 56 of the combustion liner 26. In this manner, heat is transferred from the second portion 86 of the outer surface 56 to the cooling medium 52.
  • the cooling medium 52 is then routed through the exhaust passage 108 and into the hot gas path 24 and/or along the inner surface 112 of the transition duct 28, thereby providing a cooling film that flows along the inner surface 112 of the transition duct 28.
  • the various embodiments presented in Figs. 3 through 6 also provide a method for cooling an aft portion of various hot gas path components 22 such as the combustion liner 26 and/or the transition duct 28.
  • the method generally includes routing the cooling medium 52 through the inlet 96 extending through the impingement sleeve 74 and into the first cooling chamber 80.
  • the cooling medium 52 is then impinged onto the first portion 82 of the outer surface 56 of the hot gas path component 22.
  • the cooling medium 52 is then routed from the first cooling chamber and through the outlet 104 that extends through the impingement sleeve 74.
  • the cooling medium 52 is then impinged onto the second portion 86 of the outer surface 56 of the hot gas path component 22 disposed within the second cooling chamber 84.
  • the method may further include routing the cooling medium 52 through the exhaust passage 108 and filming the cooling medium 52 onto an inner surface of a second hot gas path component 22.
  • the method may further include routing the cooling medium 52 from the second cooling chamber 84 through the exhaust passage 108 and into the hot gas path 24.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Gas Burners (AREA)
EP13192280.9A 2012-11-12 2013-11-11 Système de refroidissement d'un composant de gaz chaud, chambre de combustion de turbine à gaz et procédé de refroidissement associés Withdrawn EP2730748A2 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/674,255 US20140130504A1 (en) 2012-11-12 2012-11-12 System for cooling a hot gas component for a combustor of a gas turbine

Publications (1)

Publication Number Publication Date
EP2730748A2 true EP2730748A2 (fr) 2014-05-14

Family

ID=49596068

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13192280.9A Withdrawn EP2730748A2 (fr) 2012-11-12 2013-11-11 Système de refroidissement d'un composant de gaz chaud, chambre de combustion de turbine à gaz et procédé de refroidissement associés

Country Status (4)

Country Link
US (1) US20140130504A1 (fr)
EP (1) EP2730748A2 (fr)
JP (1) JP2014095381A (fr)
CN (1) CN103807023A (fr)

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EP3306038A1 (fr) * 2016-10-10 2018-04-11 General Electric Company Cadre arrière pour une chambre de combustion
EP3457029A1 (fr) * 2017-09-19 2019-03-20 United Technologies Corporation Capture de particules pour chambres de combustion

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US11187105B2 (en) * 2017-02-09 2021-11-30 General Electric Company Apparatus with thermal break
US10975724B2 (en) * 2018-10-30 2021-04-13 General Electric Company System and method for shroud cooling in a gas turbine engine
KR102314661B1 (ko) * 2020-02-27 2021-10-19 두산중공업 주식회사 라이너 냉각장치, 연소기 및 이를 포함하는 가스터빈
KR102661014B1 (ko) * 2022-03-30 2024-04-25 한국기계연구원 덕트 조립체 및 이를 포함하는 연소기

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EP3306038A1 (fr) * 2016-10-10 2018-04-11 General Electric Company Cadre arrière pour une chambre de combustion
US10830142B2 (en) 2016-10-10 2020-11-10 General Electric Company Combustor aft frame cooling
EP3457029A1 (fr) * 2017-09-19 2019-03-20 United Technologies Corporation Capture de particules pour chambres de combustion
US10823417B2 (en) 2017-09-19 2020-11-03 Raytheon Technologies Corporation Combustor with particle collection panel having a plurality of particle collection chambers

Also Published As

Publication number Publication date
JP2014095381A (ja) 2014-05-22
US20140130504A1 (en) 2014-05-15
CN103807023A (zh) 2014-05-21

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