US20130298564A1 - Cooling system and method for turbine system - Google Patents

Cooling system and method for turbine system Download PDF

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Publication number
US20130298564A1
US20130298564A1 US13/470,556 US201213470556A US2013298564A1 US 20130298564 A1 US20130298564 A1 US 20130298564A1 US 201213470556 A US201213470556 A US 201213470556A US 2013298564 A1 US2013298564 A1 US 2013298564A1
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US
United States
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.)
Abandoned
Application number
US13/470,556
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English (en)
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
Priority to US13/470,556 priority Critical patent/US20130298564A1/en
Assigned to GENERAL ELECTRIC COMPANY reassignment GENERAL ELECTRIC COMPANY ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: Agarwal, Krishna Kant
Priority to JP2013099827A priority patent/JP2013238389A/ja
Priority to EP13167423.6A priority patent/EP2664748A2/de
Priority to RU2013121277/06A priority patent/RU2013121277A/ru
Priority to CN2013101769153A priority patent/CN103422990A/zh
Publication of US20130298564A1 publication Critical patent/US20130298564A1/en
Abandoned 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.
  • 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.
  • FIG. 2 is a cross-sectional view of several portions of a gas turbine system according to one embodiment of the present disclosure
  • FIG. 3 is a perspective exploded view of an insert and a liner according to one embodiment of the present disclosure
  • FIG. 4 is a cutaway perspective assembled view of the insert and liner of FIG. 3 ;
  • FIG. 6 is a cross-sectional view of an insert in a liner according to another embodiment of the present disclosure.
  • FIG. 7 is a cutaway perspective view of an insert in a liner according to another embodiment of the present disclosure.
  • FIG. 8 is a cross-sectional view of the insert and liner of FIG. 7 ;
  • FIG. 9 is a cutaway perspective view of an insert in a liner according to another embodiment of the present disclosure.
  • FIG. 10 is a cross-sectional view of the insert and liner of FIG. 9 .
  • FIG. 1 is a schematic diagram of a gas turbine system 10 .
  • 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.
  • 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.
  • 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 is disposed in the hot side 62 of the liner 60 .
  • 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 .
  • 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 .
  • 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 .
  • 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 .
  • spacer 130 may be arranged in a generally annular array, or alternatively, one, two, three, five, six, seven, eight, nine, ten or more spacers 130 may be utilized, and/or the spacers 130 may have any suitable arrangement.
  • Each spacer 130 may have any suitable shape and or size.
  • the spacers 130 may be welded, mechanically connected or formed as a unitary component with the insert 80 , such as the outer surface 94 of the tube 90 , and/or the liner 60 , such as the peripheral edge 72 of the hole 70 .
  • one or more holes 132 may be defined in each spacer 130 . Holes 132 are particularly necessary in embodiments wherein the spacers 130 connect the insert 80 to the liner 60 , in order to provide and maintain the continuous peripheral gap 98 between the hole 70 and the tube 90 .
  • 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)
US13/470,556 2012-05-14 2012-05-14 Cooling system and method for turbine system Abandoned US20130298564A1 (en)

Priority Applications (5)

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
JP2013099827A JP2013238389A (ja) 2012-05-14 2013-05-10 タービンシステム用の冷却システムおよび方法
EP13167423.6A EP2664748A2 (de) 2012-05-14 2013-05-13 Kühlsystem und Verfahren für ein Turbinensystem
RU2013121277/06A RU2013121277A (ru) 2012-05-14 2013-05-13 Система охлаждения для турбоустановки, камера сгорания и способ охлаждения жаровой трубы
CN2013101769153A CN103422990A (zh) 2012-05-14 2013-05-14 用于涡轮系统的冷却系统和方法

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

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US20130298564A1 true US20130298564A1 (en) 2013-11-14

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US13/470,556 Abandoned US20130298564A1 (en) 2012-05-14 2012-05-14 Cooling system and method for turbine system

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

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2015116269A3 (en) * 2013-11-04 2015-10-08 United Technologies Corporation Quench aperture body for a turbine engine combustor
US20160053998A1 (en) * 2014-08-20 2016-02-25 Mitsubishi Hitachi Power Systems, Ltd. Cylinder of combustor, method of manufacturing of cylinder of combustor, and pressure vessel
US20160123594A1 (en) * 2014-11-04 2016-05-05 United Technologies Corporation Low lump mass combustor wall with quench aperture(s)
US20160201908A1 (en) * 2013-08-30 2016-07-14 United Technologies Corporation Vena contracta swirling dilution passages for gas turbine engine combustor
US20160356500A1 (en) * 2013-09-16 2016-12-08 United Technologies Corporation Controlled variation of pressure drop through effusion cooling in a double walled combustor of a gas turbine engine
CN106716017A (zh) * 2014-09-25 2017-05-24 三菱日立电力系统株式会社 燃烧器、燃气轮机
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
US11073284B2 (en) * 2014-01-03 2021-07-27 Raytheon Technologies Corporation Cooled grommet for a combustor wall assembly
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
US12429221B2 (en) 2021-09-30 2025-09-30 General Electric Company Annular combustor dilution with swirl vanes for lower emissions
US12492821B2 (en) * 2021-06-07 2025-12-09 General Electric Company Combustor for a gas turbine engine

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3064837B1 (de) * 2015-03-05 2019-05-08 Ansaldo Energia Switzerland AG Auskleidung einer Gasturbinenbrennkammer
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

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Cited By (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20160201908A1 (en) * 2013-08-30 2016-07-14 United Technologies Corporation Vena contracta swirling dilution passages for gas turbine engine combustor
US20160356500A1 (en) * 2013-09-16 2016-12-08 United Technologies Corporation Controlled variation of pressure drop through effusion cooling in a double walled combustor of a gas turbine engine
US10731858B2 (en) * 2013-09-16 2020-08-04 Raytheon Technologies Corporation Controlled variation of pressure drop through effusion cooling in a double walled combustor of a gas turbine engine
US10571125B2 (en) 2013-11-04 2020-02-25 United Technologies Corporation Quench aperture body for a turbine engine combustor
US11287132B2 (en) 2013-11-04 2022-03-29 Raytheon Technologies Corporation Quench aperture body for a turbine engine combustor
WO2015116269A3 (en) * 2013-11-04 2015-10-08 United Technologies Corporation Quench aperture body for a turbine engine combustor
US11073284B2 (en) * 2014-01-03 2021-07-27 Raytheon Technologies Corporation Cooled grommet for a combustor wall assembly
US20160053998A1 (en) * 2014-08-20 2016-02-25 Mitsubishi Hitachi Power Systems, Ltd. Cylinder of combustor, method of manufacturing of cylinder of combustor, and pressure vessel
CN106574779A (zh) * 2014-08-20 2017-04-19 三菱日立电力系统株式会社 燃烧器的筒、燃烧器的筒的制造方法、压力容器
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
CN106716017A (zh) * 2014-09-25 2017-05-24 三菱日立电力系统株式会社 燃烧器、燃气轮机
US10584879B2 (en) 2014-09-25 2020-03-10 Mitsubishi Hitachi Power Systems, Ltd. Combustor including a flow guide introduction portion connected to a flow guide main body portion, and a gas turbine
EP3182016A4 (de) * 2014-09-25 2017-07-12 Mitsubishi Hitachi Power Systems, Ltd. Verbrenner und gasturbine
US20160123594A1 (en) * 2014-11-04 2016-05-05 United Technologies Corporation Low lump mass combustor wall with quench aperture(s)
US10451281B2 (en) * 2014-11-04 2019-10-22 United Technologies Corporation Low lump mass combustor wall with quench aperture(s)
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
US12050011B2 (en) 2017-10-04 2024-07-30 Rtx Corporation Dilution holes with ridge feature for gas turbine engines
US11137140B2 (en) 2017-10-04 2021-10-05 Raytheon Technologies Corporation Dilution holes with ridge feature for gas turbine engines
US12460818B2 (en) 2017-10-04 2025-11-04 Rtx 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
US12492821B2 (en) * 2021-06-07 2025-12-09 General Electric Company Combustor for a gas turbine engine
US12429221B2 (en) 2021-09-30 2025-09-30 General Electric Company Annular combustor dilution with swirl vanes for lower emissions
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

Also Published As

Publication number Publication date
JP2013238389A (ja) 2013-11-28
CN103422990A (zh) 2013-12-04
EP2664748A2 (de) 2013-11-20
RU2013121277A (ru) 2014-11-20

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