EP2664748A2 - Cooling system and method for turbine system - Google Patents

Cooling system and method for turbine system Download PDF

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Publication number
EP2664748A2
EP2664748A2 EP13167423.6A EP13167423A EP2664748A2 EP 2664748 A2 EP2664748 A2 EP 2664748A2 EP 13167423 A EP13167423 A EP 13167423A EP 2664748 A2 EP2664748 A2 EP 2664748A2
Authority
EP
European Patent Office
Prior art keywords
tube
plate
liner
hole
combustor
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Withdrawn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
EP13167423.6A
Other languages
German (de)
English (en)
French (fr)
Inventor
Krishna Kant Agarwal
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 EP2664748A2 publication Critical patent/EP2664748A2/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Withdrawn legal-status Critical Current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
    • 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
    • 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/06—Arrangement of apertures along the flame tube

Definitions

  • the present disclosure relates in general to turbine systems, and more particularly to cooling systems for turbine systems and in exemplary embodiments cooling systems for combustors of turbine systems.
  • Turbine systems are widely utilized in fields such as power generation.
  • a conventional gas turbine system includes a compressor section, a combustor section, and at least one turbine section.
  • the compressor section is configured to compress air as the air flows through the compressor section.
  • the air is then flowed from the compressor section to the combustor section, where it is mixed with fuel and combusted, generating a hot gas flow.
  • the hot gas flow is provided to the turbine section, which utilizes the hot gas flow by extracting energy from it to power the compressor, an electrical generator, and other various loads.
  • the combustor liner and transition piece are examples of components defining temperature boundaries.
  • Compressed air flowing through a compressor is typically flowed upstream in a flow passage past the outside surfaces of the combustor liner and transition piece before entering a combustion zone defined by inner surfaces of the combustor liner and transition piece. Due to combustion occurring in the combustion zone, a temperature differential exists between the flow passage and the combustion zone, and the air in the flow passage is utilized to cool the combustor liner and transition piece.
  • portions of the air flowing through the flow passage are diverted through the combustor liner and/or transition piece into the combustion zone, to cool the combustor liner and/or transition piece. It is generally desirable for this air to create a film in the combustion zone adjacent to the inner surfaces of the combustor liner and/or transition piece, such that the combustor liner and/or transition piece are film cooled.
  • the air flowed through the combustor liner and/or transition piece may cause recirculation or stagnation zones to form adjacent on the hot side of the liner.
  • Hot fluids flowing past the liner such as the hot gas flow in the combustor zone, may recirculate or stagnate within these zones, causing hot spots on the liner.
  • the existence of hot spots can lead to uneven thermal stresses in the liner.
  • the thermal stresses can be of a cyclic nature due to system stops and starts, which can lead to crack initiation.
  • cooling systems and methods for turbine systems are desired in the art.
  • systems and methods that provide improved film cooling at temperature boundaries in a turbine system would be advantageous.
  • systems and methods that reduce or eliminate recirculation and stagnation on liners defining the temperature boundaries would be advantageous.
  • a cooling system for a turbine system includes a liner defining a temperature boundary between a hot side and a cold side.
  • the liner includes a hot side surface and a cold side surface and defines a hole extending between the hot side surface and the cold side surface.
  • the hole defines a peripheral edge.
  • the cooling system further includes an insert.
  • the insert includes a tube extending through the hole, the tube including an outer surface. The outer surface and the peripheral edge define a generally continuous peripheral gap therebetween.
  • the insert further includes a plate connected to the tube and disposed in the hot side.
  • the plate extends outwardly from the tube such that working fluid flowing through the gap is redirected by the plate to form a film proximate the hot side surface.
  • a method for cooling a liner in a turbine system includes flowing a working fluid through a generally continuous peripheral gap defined in the liner between an outer surface of a tube disposed in a hole and a peripheral edge of the hole. The method further includes redirecting the working fluid flowed through the gap to form a film proximate a hot side surface of the liner.
  • FIG. 1 is a schematic diagram of a gas turbine system 10. It should be understood that the turbine system 10 of the present disclosure need not be a gas turbine system 10, but rather may be any suitable turbine system 10, such as a steam turbine system or other suitable system.
  • the gas turbine system 10 may include a compressor section 12, a combustor section 14 which may include a plurality of combustors 15 as discussed below, and a turbine section 16.
  • the compressor section 12 and turbine section 16 may be coupled by a shaft 18.
  • the shaft 18 may be a single shaft or a plurality of shaft segments coupled together to form shaft 18.
  • the shaft 18 may further be coupled to a generator or other suitable energy storage device, or may be connected directly to, for example, an electrical grid. Exhaust gases from the system 10 may be exhausted into the atmosphere, flowed to a steam turbine or other suitable system, or recycled through a heat recovery steam generator.
  • the gas turbine system 10 as shown in FIG. 2 comprises a compressor section 12 for pressurizing a working fluid that is flowing through the system 10.
  • the working fluid is typically air, but may be any suitable liquid or gas.
  • Pressurized working fluid discharged from the compressor section 12 flows into a combustor section 14, which may include a plurality of combustors 15 (only one of which is illustrated in FIG. 2 ) disposed in an annular array about an axis of the system 10.
  • the working fluid entering the combustor section 14 is mixed with fuel, such as natural gas or another suitable liquid or gas, and combusted. Hot gases of combustion flow from each combustor 15 to a turbine section 16 to drive the system 10 and generate power.
  • a combustor 15 in the gas turbine 10 may include a variety of components for mixing and combusting the working fluid and fuel.
  • the combustor 15 may include a casing 21, such as a compressor discharge casing 21.
  • a variety of sleeves may be at least partially disposed in the casing 21.
  • a combustor liner 22 may generally define a combustion zone 24 therein. Combustion of the working fluid, fuel, and optional oxidizer may generally occur in the combustion zone 24. The resulting hot gases of combustion may flow downstream in direction 28 through the combustion liner 22 into a transition piece 26 which further defines the combustion zone, and then flow through the transition piece 26 and into the turbine section 16.
  • An impingement sleeve 32 and flow sleeve 34 may generally circumferentially surround combustor liner 22 and transition piece 26, as shown.
  • a flow passage 26 surrounding the combustor liner 22 and transition piece 26, through which working fluid may flow in an upstream direction 28, may thus further be defined be the impingement sleeve 32 and flow sleeve 34.
  • the flow passage 26 may be defined between the sleeve comprising the impingement sleeve 32 and flow sleeve 34 and the sleeve comprising the combustor liner 22 and transition piece 26.
  • the combustor 15 may further include a fuel nozzle 40 or a plurality of fuel nozzles 40. Fuel may be supplied to the fuel nozzles 40 by one or more manifolds (not shown). As discussed below, the fuel nozzle 40 or fuel nozzles 40 may supply the fuel and, optionally, working fluid to the combustion zone 24 for combustion.
  • various holes may be defined in the combustor liner 22 and/or transition piece 26. These holes allow for working fluid flowing past the combustor liner 22 and/or transition piece 26 to be diverted into the combustion zone 24, typically for cooling purposes. Dilution holes 42 are one example of such holes. Dilution holes 42 are defined in the combustor liner 22, as shown.
  • FIGS. 3 through 10 illustrate various embodiments of a cooling system 50 for a turbine system 10 according to the present disclosure.
  • the system 50 includes a liner 60.
  • the liner 60 defines a temperature boundary between a hot side 62 and a cold side 64, and includes a hot side surface 66 and a cold side surface 68.
  • the temperature in the hot side 62 is relatively hotter than the temperature in the cold side 64.
  • the liner 60 is disposed on and defines the temperature boundary, so the hot size surface 66 of the liner 60 faces the hot side 62 and the cold side surface 68 of the liner 60 faces the cold side 64.
  • One or more holes 70 may be defined in the liner 60. Each hole 70 may extend between the hot side surface 66 and the cold side surface 68. A peripheral edge 72 may be defined by the hole 70 in the liner 60. The peripheral edge 72 may define an outer boundary of the hole 70.
  • a hole according to the present disclosure may have any suitable shape and size. For example, in some embodiments, a hole may have a generally circular or oval cross-sectional shape. In other embodiments, a hole may have a generally rectangular, triangular, or other suitable polygonal shape.
  • a liner 60 is a combustor liner 22.
  • the combustor liner 22 defines a temperature boundary between a hot side 62, such as a combustion zone 24, and a cold side surface 64, such as a flow passage 36.
  • One or more holes 70 are defined in the combustor liner 22. It should be understood, however, that the present disclosure is not limited to combustor liners 22 as liners 60. Rather, any suitable liner defining a temperature boundary, such as a transition piece 26 or other suitable liner component, is within the scope and spirit of the present disclosure.
  • a cooling system 50 according to the present disclosure further includes one or more inserts 80.
  • Each insert 80 is disposed in a hole 70 in a liner 60, and facilitates film cooling of the liner 60 adjacent to the hole 70.
  • the use of an insert 80 in a hole 70 in a liner 60 reduces recirculation and stagnation adjacent to the hole 70.
  • the insert 80 directs working fluid 82 flowing through the hole 70, such as a portion of the working fluid 84 as discussed below, to form a film proximate the liner 60, which facilitates film cooling.
  • the use of a cooling system 50 according to the present disclosure may advantageously reduce the existence of hot spots and resulting uneven thermal stresses in liners 60. This may further advantageously reduce the formation of cracks in the liner 60, especially adjacent to the holes 70 in which inserts 80 are disposed.
  • an insert 80 includes a tube 90.
  • the tube 90 may include an inner surface 92, and includes an outer surface 94.
  • the inner surface 92 may define an interior 96 of the tube 90.
  • the interior 96 may be generally hollow as shown, thus allowing working fluid 82 to flow therethrough.
  • the tube 90 may be generally solid, such that no inner surface 92 can be defined.
  • the tube 90 may have any suitable cross-sectional shape and size.
  • the tube 90 may be cylindrical, and thus have a generally circular or oval cross-sectional shape.
  • a hole may have a generally rectangular, triangular, or other suitable polygonal shape.
  • the tube 90 of an insert 80 extends through a hole 70 in a liner 60.
  • the outer surface 94 of the tube 90 and the peripheral edge 72 of the hole 70 define a gap 98 therebetween.
  • the gap 98 is a generally continuous peripheral gap that extends peripherally around the entire tube 90, and thus peripherally about the entire outer surface 94, as well as peripherally around the entire peripheral edge 72.
  • some of the working fluid 82 flowing through the flow passage 26 may flow through the hole 70.
  • this portion 84 of the working fluid 82 may flow between the hole 70 and the outer surface 94 of the tube 90, and thus through the peripheral gap 98. As discussed below, this portion 84 of the working fluid 82 may, after flowing through the peripheral gap 98, be redirected to form a film proximate the hot side surface 66.
  • a insert 80 further includes a plate 100, also known as a first plate 100.
  • the plate 100 is connected to the tube 90, such as to the outer surface 94 thereof.
  • the plate 100 may be welded to the tube 90, mechanically connected to the tube 90 such as through screws, rivets, nut-bolt combinations, etc., or formed with the tube 90 as a singular component.
  • the plate 100 extends around the entire periphery of the tube 90, and is connected to an entire peripheral portion of the outer surface 94.
  • the plate 100 may extend generally outwardly from tube 90, such as from the outer surface 94 away from the inner surface 92.
  • the plate 100 may extend generally transverse to and outwardly from the tube 90.
  • the tube 90 is generally cylindrical, and thus has a circular or oval cross-section
  • the plate 100 may extend radially outward from the tube 90.
  • the plate 100 may extend from the tube 90 at any suitable angle to the transverse or radial direction.
  • the plate 100 may redirect a portion 84 of the working fluid 82 flowing through the hole 70.
  • the portion 84 that flows through the peripheral gap 98 may contact or flow proximate to the plate 100. Due to the positioning of the plate 100, the plate 100 may cause the portion 84 of the working fluid 82 to turn and flow between the plate 100 and the hot side surface 66 of the liner 60. This redirection in flow results in a film of working fluid 82, which includes the portion 84, being formed and flowing proximate the hot side surface 66.
  • Such redirection of the portion 84 of the working fluid 82 by the plate thus facilitates formation of a film of working fluid 82 quickly and proximate the associated hole 70, and thus advantageously reduce the existence of hot spots and resulting uneven thermal stresses in liners 60, particularly proximate holes 70.
  • an insert 80 further includes a second plate 102.
  • the second plate 102 may be connected to the tube 90, such as to the outer surface 94 thereof.
  • the second plate 102 may be welded to the tube 90, mechanically connected to the tube 90 such as through screws, rivets, nut-bolt combinations, etc., or formed with the tube 90 as a singular component.
  • the second plate 102 extends around the entire periphery of the tube 90, and is connected to an entire peripheral portion of the outer surface 94. When the insert 80 is positioned extending through the hole 70, the second plate 102 is disposed in the cold side 64 of the liner 60.
  • the second plate 102 may extend generally outwardly from tube 90, such as from the outer surface 94 away from the inner surface 92.
  • the second plate 102 may extend generally transverse to and outwardly from the tube 90.
  • the second plate 102 may extend radially outward from the tube 90.
  • the second plate 102 may extend from the tube 90 at any suitable angle to the transverse or radial direction.
  • the plate 100 may capture and direct working fluid 82 towards the hole 70.
  • the working fluid 82 may thus flow between the second plate 102 and the cold side surface 68 of the liner.
  • a portion 84 of the working fluid 82 may flow through the hole 70, and specifically through the peripheral gap 98 as discussed above, and then be redirected to form a film as discussed.
  • An insert 80 according to the present disclosure may be connected to a liner 60 using any suitable connection methods or apparatus.
  • one or more studs 110 may be utilized to connect the insert 80 to the liner 60.
  • the studs 110 may extend between the second plate 102 and the cold side surface 68.
  • studs 110 may extend between the first plate 100 and the hot side surface 66.
  • Any number of studs 110 may be utilized, in any suitable pattern that suitably connects the insert 80 to the liner 60.
  • eight studs 110 may be arranged in a generally annular array, as shown in FIG. 3 .
  • one, two, three, four, five, six, seven, nine, ten or more studs 110 may be utilized, and/or the studs 110 may have any suitable arrangement.
  • Each stud 110 may have any suitable shape and or size.
  • the studs 110 may be welded, mechanically connected or formed as a unitary component with the insert 80 and/or the liner 60.
  • one or more ribs 120 may connect the insert 80 and liner 60. Ribs 120 may be utilized in embodiments including or not including a second plate 102. For example, in some embodiments as shown, each rib 120 may extend between and connect the tube 90, such as the outer surface 94 thereof, and the cold side surface 68. Any number of ribs 120 may be utilized, in any suitable pattern that suitably connects the insert 80 to the liner 60. For example, four ribs 120 may be arranged in a generally annular array, or alternatively, one, two, three, five, six, seven, eight, nine, ten or more ribs 120 may be utilized, and/or the ribs 120 may have any suitable arrangement.
  • Each ribs 120 may have any suitable shape and or size.
  • a rib 120 may be generally curvilinear as shown.
  • a rib 120 may be generally linear, and/or may have various linear and/or curvilinear portions.
  • the ribs 120 may be welded, mechanically connected or formed as a unitary component with the insert 80 and/or the liner 60.
  • one or more spacers 130 may be included in the insert 80.
  • the spacers 130 may position the insert 80 within the hole 70, and may in some embodiments further connect the insert 80 to the liner 60.
  • the spacers 130 may connect the insert 80 to the liner 60.
  • Each spacer 130 may extend between and connect the peripheral edge 72 of the hole 70 and the outer surface 94 of the tube 90. Any number of spacers 130 may be utilized, in any suitable pattern that suitably connects the insert 80 to the liner 60.
  • the spacers 130 may not connect the insert 80 to the liner 60, and may rather simply maintain the position of the tube 90 within the hole 70.
  • the spacers 130 in these embodiments may have any suitable shape and size, and any suitable number of spacers 130 in any suitable pattern may be utilized.
  • the spacers 130 may be connected, such as welded, mechanically connected or formed as a unitary component with, either the insert 80, such as the outer surface 94 of the tube 90, as shown or the liner 60, such as the peripheral edge 72 of the hole 70.
  • the spacers 130 may not be connected to the other of the insert 80 and the liner 60, thus maintaining the continuous peripheral gap 98 while serving to position the tube 90 within the hole 70.
  • the present disclosure is further directed to methods for cooling a liner 60 in a turbine system 10.
  • the method may include, for example, flowing a working fluid 82, such as a portion 84 thereof, through a generally continuous peripheral gap 98 defined in the liner 60 between an outer surface 94 of a tube 90 disposed in a hole 70 and a peripheral edge 72 of the hole 70.
  • the method may further include, for example, redirecting the working fluid 82, such as the portion 84 thereof, flowed through the gap 98 to form a film proximate a hot side surface 66 of the liner 60.

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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)
EP13167423.6A 2012-05-14 2013-05-13 Cooling system and method for turbine system Withdrawn EP2664748A2 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/470,556 US20130298564A1 (en) 2012-05-14 2012-05-14 Cooling system and method for turbine system

Publications (1)

Publication Number Publication Date
EP2664748A2 true EP2664748A2 (en) 2013-11-20

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ID=48446100

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13167423.6A Withdrawn EP2664748A2 (en) 2012-05-14 2013-05-13 Cooling system and method for turbine system

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US (1) US20130298564A1 (ja)
EP (1) EP2664748A2 (ja)
JP (1) JP2013238389A (ja)
CN (1) CN103422990A (ja)
RU (1) RU2013121277A (ja)

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WO2015047509A2 (en) * 2013-08-30 2015-04-02 United Technologies Corporation Vena contracta swirling dilution passages for gas turbine engine combustor
EP3047128B1 (en) * 2013-09-16 2018-10-31 United Technologies Corporation Controlled variation of pressure drop through effusion cooling in a double walled combustor of a gas turbine engine
EP3591292B1 (en) 2013-11-04 2022-01-05 Raytheon Technologies Corporation Quench aperture body for a turbine engine combustor
EP3090209B1 (en) * 2014-01-03 2019-09-04 United Technologies Corporation A cooled grommet for a combustor wall assembly of a gas turbine
US9915428B2 (en) * 2014-08-20 2018-03-13 Mitsubishi Hitachi Power Systems, Ltd. Cylinder of combustor, method of manufacturing of cylinder of combustor, and pressure vessel
JP6521283B2 (ja) * 2014-09-25 2019-05-29 三菱日立パワーシステムズ株式会社 燃焼器、ガスタービン
EP3018417B8 (en) * 2014-11-04 2021-03-31 Raytheon Technologies Corporation Low lump mass combustor wall with quench aperture(s)
EP3064837B1 (en) * 2015-03-05 2019-05-08 Ansaldo Energia Switzerland AG Liner for a gas turbine combustor
CN107795383B (zh) * 2016-08-29 2019-08-06 中国航发商用航空发动机有限责任公司 一种燃气轮机冷却气分配系统
US20190024895A1 (en) * 2017-07-18 2019-01-24 General Electric Company Combustor dilution structure for gas turbine engine
US10408453B2 (en) * 2017-07-19 2019-09-10 United Technologies Corporation Dilution holes for gas turbine engines
US11137140B2 (en) 2017-10-04 2021-10-05 Raytheon Technologies Corporation Dilution holes with ridge feature for gas turbine engines
US11255543B2 (en) * 2018-08-07 2022-02-22 General Electric Company Dilution structure for gas turbine engine combustor
CN114135901A (zh) * 2021-11-08 2022-03-04 中国航发四川燃气涡轮研究院 一种防烧蚀的火焰筒大孔射流套筒

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Also Published As

Publication number Publication date
RU2013121277A (ru) 2014-11-20
JP2013238389A (ja) 2013-11-28
US20130298564A1 (en) 2013-11-14
CN103422990A (zh) 2013-12-04

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