WO2016093430A1 - Ensemble appareil de tourbillonnement - Google Patents

Ensemble appareil de tourbillonnement Download PDF

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Publication number
WO2016093430A1
WO2016093430A1 PCT/KR2015/002024 KR2015002024W WO2016093430A1 WO 2016093430 A1 WO2016093430 A1 WO 2016093430A1 KR 2015002024 W KR2015002024 W KR 2015002024W WO 2016093430 A1 WO2016093430 A1 WO 2016093430A1
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WO
WIPO (PCT)
Prior art keywords
base plate
liquid fuel
vane
vanes
fuel
Prior art date
Application number
PCT/KR2015/002024
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English (en)
Korean (ko)
Inventor
안철주
Original Assignee
한화테크윈 주식회사
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Filing date
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Application filed by 한화테크윈 주식회사 filed Critical 한화테크윈 주식회사
Publication of WO2016093430A1 publication Critical patent/WO2016093430A1/fr

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    • 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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/22—Fuel supply systems
    • 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
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • Embodiments of the present invention relate to a swirler assembly, and more particularly, to a swirler assembly of a gas turbine combustor that mixes fuel and air.
  • a gas turbine is a heat engine that operates a turbine with high-temperature and high-pressure combustion gases, and generally consists of a compressor, a combustor, and a turbine.
  • the air is first compressed by a compressor, which is then premixed with the compressed high-pressure air and the fuel supplied from the fuel system in a pre-chamber to lower the flame temperature and inject the fuel inside the main chamber. Burn the air mixture.
  • the turbine is rotated by expanding the high-temperature and high-pressure gas while blowing out the turbine. At this time, a swirler is used to evenly distribute the uniform fuel-air mixture in the combustion chamber in order to burn fuel efficiently and quickly.
  • the swirler facilitates the combustion reaction of the fuel-air mixture by allowing the compressed air and fuel to be mixed quickly and uniformly, and when the mixing degree of the fuel-air mixture supplied to the flame becomes uneven, The part with high flame temperature is generated and the emission of NOx is high. Since nitrogen oxide is one of the main causes of air pollution, strict emission standards are being applied worldwide.
  • Embodiments of the present invention provide a swirler assembly with improved mixing performance between air and fuel.
  • the base plate A plurality of vanes spaced apart along a circumferential direction of the base plate on one surface of the base plate extending in a direction crossing the center of the base plate; A cover plate disposed to cover the plurality of vanes opposite the base plate; And a plurality of air injection holes penetrating the outer surfaces of at least one of the base plate and the cover plate and formed to be inclined with respect to the base plate and the cover plate so as to open toward a space between adjacent vanes.
  • each of the vanes includes a gas fuel receiving unit storing gas fuel introduced from a gas fuel inlet formed on the one surface of the base plate, and radially from the gas fuel receiving unit so that the gas fuel is injected to the outside.
  • a gas fuel injection hole extending toward the wall surface of the vane, a liquid fuel receiving portion storing liquid fuel introduced from a liquid fuel injection hole formed on the one surface of the base plate, and allowing the liquid fuel to be injected to the outside.
  • a liquid fuel injection orifices extending towards the wall of the vane, end portions of the vane adjacent the outer periphery of the base plate provides a swirler assembly having a curved shape.
  • each of the air injection holes and the angle formed with the one surface of the base plate or the cover plate may be 90 degrees or less.
  • the vanes may be disposed spirally on the one surface of the base plate.
  • air may be introduced into the space between the vanes adjacent to the outer circumference of the base plate.
  • the vane may have a front end portion having the curved shape and a rear end portion connected to the front end portion and having a width that decreases in the longitudinal direction of the vane.
  • the gaseous fuel is injected from the gaseous fuel injection port into the space between the adjacent vanes, and the liquid fuel may be injected from the liquid fuel injection port into the space between the adjacent vanes.
  • the gas fuel receiving portion may be formed in the front end portion, the liquid fuel receiving portion may be formed in the rear end portion.
  • the gas fuel receiving portion and the liquid fuel receiving portion may be formed to a height lower than the overall height of the vane.
  • the volume of the gas fuel containing portion may be larger than the volume of the liquid fuel containing portion.
  • the angle of the gas fuel injection port formed radially around the gas fuel receiving portion may be 270 degrees or less.
  • At least one gas fuel injection hole may be disposed at the front end portion to extend along the center line in the longitudinal direction of the vane.
  • a plurality of gas fuel injection holes are formed on the wall surface of the front end portion to be connected to the gas fuel receiving portion, a plurality of the liquid fuel injection holes are formed on the wall surface of the rear end portion to be connected to the liquid fuel receiving portion Can be.
  • the gas fuel injection port may be arranged to form a plurality of layers on the wall surface of the front end portion along the height of the vane.
  • the angle of the liquid fuel injection port formed radially around the liquid fuel receiving portion may be 90 degrees or less.
  • a groove portion may be formed in the height direction of the vane at an end portion of the rear end portion facing the center of the base plate.
  • the liquid fuel injection port may be disposed at least one groove.
  • the gas fuel injection port and the liquid fuel injection port may be arranged to be symmetrical with respect to the center line in the longitudinal direction of the vane.
  • a cover plate disposed to cover the vanes may face the base plate.
  • a penetrating portion penetrating the cover plate in the thickness direction of the cover plate may be formed in the center of the cover plate.
  • the mixture of the gaseous fuel, the liquid fuel and air may pass through the through portion of the cover plate.
  • Embodiments of the present invention can supply fuel uniformly on the air flow path.
  • the fuel supply time is faster to ensure the time required for mixing between air and fuel.
  • FIG. 1 is a perspective view schematically showing a swirler assembly according to an embodiment of the present invention.
  • FIG. 2 is an exploded view schematically showing a portion of a gas turbine having the swirler assembly of FIG. 1.
  • FIG. 3 is a schematic cross-sectional view of air and fuel supplied to the swirler assembly of FIG. 1.
  • FIG. 4 is a cross-sectional view taken along line IV-IV of FIG. 3.
  • FIG. 5 is a perspective view schematically illustrating the vanes of the swirler assembly of FIG. 1.
  • FIG. 6 is a cross-sectional view of the vane of the swirler assembly of FIG. 1 viewed in a direction crossing the Z-axis direction.
  • FIG. 7 is a cross-sectional view of the fuel flow of the swirler assembly according to the comparative example viewed from a direction crossing the Z-axis direction.
  • FIG. 1 is a perspective view schematically showing a swirler assembly according to an embodiment of the present invention.
  • FIG. 2 is an exploded view schematically showing a portion of a gas turbine having the swirler assembly of FIG. 1.
  • the swirler assembly 200 covers a base plate 210, a plurality of vanes 230 and a base plate 210 disposed spaced apart from one surface of the base plate 210.
  • Plate 290 is provided.
  • the swirler assembly 200 may be disposed between the burner 204 and the combustors 205 and 206.
  • the base plate 210 may be coupled to the burner 204. In this case, fuel may be supplied to the plurality of vanes 230 to be described later through the base plate 210 from the burner 204.
  • the base plate 210 may have a shape of a disc, but is not necessarily limited thereto.
  • the material of the base plate 210 is not limited to a specific material, but a material resistant to heat and pressure may be used.
  • the base plate 210 supports the plurality of vanes 230.
  • the plurality of vanes 230 may be disposed on one surface of the base plate 210 extending in the direction transverse to the center O of the base plate 210. As shown in FIG. 2, the vanes 230 may be disposed.
  • the burner 204 may be coupled to the opposite side of the disposed surface.
  • the plurality of vanes 230 may be spaced apart along the circumferential direction of the base plate 210.
  • each of the plurality of vanes 230 may be disposed in a spiral shape on one surface of the base plate 210.
  • the direction in which the space between the adjacent vanes 231 and 232 is formed may be formed to have a predetermined angle with respect to the radial direction of the base plate 210.
  • the residence time at is also longer, so that the mixing performance of the mixture can be improved.
  • each of the plurality of vanes 230 is illustrated to be disposed in a spiral toward the center O of the base plate 210, but is not necessarily limited thereto. That is, each of the plurality of vanes 230 may be disposed radially toward the center O of the base plate 210.
  • the cover plate 290 may be disposed to cover the vanes 230 to face the base plate 210.
  • the shape and material of the cover plate 290 may be the same as the shape and material of the base plate 210 described above, but is not limited thereto.
  • a through part 291 penetrating the cover plate 290 may be formed at the center of the cover plate 290.
  • the penetrating portion 291 penetrates the cover plate 290 in the thickness direction of the cover plate 290.
  • the penetrating portion 291 may have various shapes such as a circle, a polygon, and the like.
  • compressed air may be introduced from a compressor (not shown) into a space between adjacent vanes 231 and 232 from an outer circumference of the base plate 210.
  • the air here is mixed with the fuel supplied from the burner 204 and this mixture produces a high temperature and high pressure gas to be sent to a turbine (not shown) while continuously passing through the preburner 205 and the main combustor 206.
  • a turbine not shown
  • FIG. 3 is a schematic cross-sectional view of air and fuel supplied to the swirler assembly of FIG. 1.
  • the portion X shown in FIG. 3 represents a space between adjacent vanes 231 and 232 and adjacent vanes 231 and 232. Referring to part X of FIG. 3, air is introduced into a space between adjacent vanes 231 and 232, and gas fuel G and liquid fuel L are supplied to the space.
  • each of the vanes 230 has a shape in which a portion of the vanes 230 is curved.
  • a plurality of air injection holes 220 may be formed in at least one of the base plate 210 and the cover plate 290 to open toward the space between the adjacent vanes 231 and 232.
  • the shape and arrangement of the air injection holes 220 will be described.
  • FIG. 4 is a cross-sectional view taken along line IV-IV of FIG. 3.
  • the air injection holes 220 are formed to open toward the space between adjacent vanes 231 and 232 while penetrating the outer surface of at least one of the base plate 210 and the cover plate 290.
  • a passage formed by the air injection holes 220 passing through the base plate 210 and the cover plate 290 may be formed to be inclined with respect to the base plate 210 and the cover plate 290.
  • the inclination angle ⁇ of the air injection holes 220 with respect to the base plate 210 and the cover plate 290 may be 90 degrees or less.
  • the inclination angle ⁇ corresponds to an angle at which air is injected toward the space between the adjacent vanes 231 and 232 through the air injection holes 220.
  • the air injection holes 220 may be formed such that at least one row or more is disposed in a space between adjacent vanes 231 and 232.
  • the air injection holes 220 By forming the air injection holes 220 as described above, it is possible to enhance the turbulence characteristics of the air flowing into the space between the adjacent vanes 231 and 232. That is, turbulence may occur as the air injected through the air injection holes 220 meets the air introduced into the space between the adjacent vanes 231 and 232. In this case, the intensity of the turbulence strength may be increased by making the direction in which air is injected from the air injection holes 220 and the direction in which air is introduced into the space between adjacent vanes 231 and 232 be opposite to each other. As such, the turbulent flow characteristics of the air passing between the adjacent vanes 231 and 232 are enhanced, so that the mixing between the air and the fuel supplied to the air is much smoother.
  • the air injection holes 220 may be formed in both the base plate 210 and the cover plate 290, but are not necessarily limited thereto, and thus may be formed only in one of the base plate 210 and the cover plate 290. It may be.
  • the direction in which the air injection holes 220 penetrate both plates is taken along the line AA of FIG. It can be symmetrical with respect to the centerline of. At this time, each of the inclination angle ( ⁇ ) made with respect to both plates may be formed differently.
  • FIG. 5 is a perspective view schematically illustrating the vanes of the swirler assembly of FIG. 1.
  • FIG. 6 is a cross-sectional view of the vane of the swirler assembly of FIG. 1 viewed in a direction crossing the Z-axis direction.
  • an end 231a adjacent to the outer circumference of the base plate 210 of the ends 231a and 231b of the vane 231 may have a curved shape. That is, the vane 231 may have a front end portion 231a having a curved shape and a rear end portion 231b connected to the front end portion 231a and decreasing in width in the longitudinal direction of the vane 231. .
  • the shape of each of the front end portion 231a and the rear end portion 231b may be symmetrical with respect to the longitudinal center line of the vane 231.
  • each of the vanes 230 includes a gas fuel container 240 and a gas fuel injection port 260, a liquid fuel container 250, and a liquid fuel injection port 270. It can be provided.
  • the gas fuel G and the liquid fuel L each have a space between the vanes 231 and 232 adjacent from the gas fuel injection port 260 and the liquid fuel injection port 270, that is, air passes. It can be injected into the passage.
  • the liquid fuel (L) is sprayed on the downstream side of the air flow path than the gas fuel (G), so that the flow of air flowing upstream of the air flow path is not hindered by the liquid fuel (L).
  • the air injection holes 220 may be separately formed in at least one of the base plate 210 and the cover plate 290 instead of the vanes 231.
  • the structure of the swirler may be simplified so that the flow from the fuel injection holes 260 and 270 is not tangled.
  • the gaseous fuel receiver 240 may be formed at the front end 231a of the vane 231, and the liquid fuel receiver 250 may be formed at the rear end 231b of the vane. At this time, the gas fuel receiving portion 240 and the liquid fuel receiving portion 250 is formed to a height lower than the overall height of the vanes 231. As a result, the fuel temporarily stored in each of the fuel receivers 240 and 250 may be prevented from leaking to the outside.
  • the volume of the gaseous fuel accommodating part 240 may be larger than the volume of the liquid fuel accommodating part 250. If the inflow of the liquid fuel (L) is increased, the flow rate of air and gaseous fuel (G) is caused, so that the volume of the liquid fuel receiving portion 250 smaller than the volume of the gas fuel receiving portion 240 to accommodate the liquid fuel It is necessary to adjust the supply amount of the unit 240.
  • the gas fuel receiving unit 240 and the liquid fuel receiving unit 250 may be formed in parallel to each other inside the vane 231, but is not necessarily limited thereto.
  • the gas fuel receiving unit 240 may store the gas fuel (G) introduced from the gas fuel inlet 241 formed on one surface of the base plate 210. That is, the gaseous fuel G may be temporarily stored in the gaseous fuel receiving unit 240 before being injected into the space between the adjacent vanes 231 and 232.
  • the gas fuel inlet 241 is connected to the burner 204 shown in FIG. 2 to supply the gas fuel G from the burner 204 to the gas fuel receiving unit 240.
  • a plurality of gas fuel injection holes 260 may be formed on the wall surface of the front end portion 231a of the vane 231 to be connected to the gas fuel receiving portion 240.
  • the gas fuel injection hole 260 may be formed to extend radially from the gas fuel receiving portion 240 toward both side walls of the vanes 231. As a result, the gas fuel G temporarily stored in the gas fuel receiving unit 240 may be injected to the outside of the vane 231 through the gas fuel injection hole 260.
  • an angle ⁇ of the gas fuel injection hole 260 radially formed around the gas fuel receiving part 240 may be 270 degrees or less. That is, the gaseous fuel (G) can be injected in a relatively wide range.
  • At least one gaseous fuel injection hole 260 may be disposed at the front end portion 231a to extend along the longitudinal center line of the vane 231.
  • the gas fuel injection hole 260 is disposed so as to correspond to the center line, which means that the gas fuel injection hole 260 is disposed at the most curved portion of the front end portion 231a of the vane 231.
  • the gas fuel (G) can be supplied from the time when air is introduced from the outside.
  • the mixing time between air and fuel is further increased.
  • the gas fuel injection hole 260 may be arranged to form a plurality of layers on the wall surface of the front end portion 231a along the height of the vane 231. As the number of gas fuel injection holes 260 increases, the uniformity of the fuel supply may be further improved. In addition, as the number of the gas fuel injection holes 260 increases, the mixing time between the air and the fuel may be sufficiently secured by actively inducing the generation of the recirculation zone to be described later.
  • a plurality of liquid fuel injection holes 270 may be formed on the wall surface of the rear end portion 231b of the vane 231 so as to be connected to the liquid fuel container 250.
  • the liquid fuel receiver 250 may store the liquid fuel L introduced from the liquid fuel inlet 251 formed on one surface of the base plate 210. That is, the liquid fuel L may be temporarily stored in the liquid fuel accommodating part 250 before being injected into the space between the adjacent vanes 231 and 232.
  • the liquid fuel inlet 251 may be connected to the burner 204 shown in FIG. 2 similarly to the gas fuel inlet 241.
  • the liquid fuel injection hole 270 may be formed to extend radially from the liquid fuel receiving portion 250 toward both wall surfaces of the vanes 231. As a result, the liquid fuel L may be temporarily stored in the liquid fuel accommodating part 250 and then injected to the outside of the vane 231 through the liquid fuel injection hole 270.
  • the angle ⁇ of the liquid fuel injection hole 270 formed radially around the liquid fuel accommodating part 250 may be about 90 degrees or less. That is, the liquid fuel (L) may be injected in a relatively narrow range compared to the gas fuel (G).
  • the groove 280 may be formed at the end of the rear end 231b of the vane 231. That is, the groove 280 may be formed at an end portion of the base plate 210 toward the center O. As shown in FIG. 5, the groove 280 may be formed at the end of the rear end 231b of the vane 231. That is, the groove 280 may be formed at an end portion of the base plate 210 toward the center O. As shown in FIG. 5, the groove 280 may be formed at the end of the rear end 231b of the vane 231. That is, the groove 280 may be formed at an end portion of the base plate 210 toward the center O. As shown in FIG.
  • the groove 280 may be formed at the end of the rear end 231b in the height direction of the vane 231, and may be formed at some of the sharp edges of the end of the rear end 231b.
  • At least one of the liquid fuel injection holes 270 may be disposed in the groove 280. That is, the groove portion 280 is a flat portion formed at the sharp edge of the rear end portion 231 b so as to easily arrange the liquid fuel injection hole 270 at the rear end portion 231 b, and the liquid fuel injection hole 270 disposed at the groove portion 280. ) May be disposed at the rear end 231b to extend along the longitudinal centerline of the vane 231. Accordingly, by forming the groove 280 in the rear end 231b and arranging the at least one liquid fuel injection hole 270 in the groove 280, the liquid fuel L can be stably supplied without disturbing the air flow. Can be.
  • the gas fuel injection port 260 and the liquid fuel injection port 270 formed on the wall surface of the vane 231 may be arranged to be symmetrical with respect to the longitudinal center line of the vane 231. Therefore, the fuel supply to the air flow through the space between the adjacent vanes 231 and 232 can be made uniform by the angle and the position at which the fuel is injected from the respective fuel inlets 260 and 270.
  • Gas fuel (G), liquid fuel (L) and air are mixed in the space between the adjacent vanes 231, 232 to produce a fuel-air mixture near the center O of the base plate 210. do.
  • the fuel can be supplied from the upstream of the air flowing into the swirler assembly 200, thereby sufficiently securing the time required for mixing the air and the fuel.
  • a mixture of the above-described gas fuel G, liquid fuel L, and air may pass therethrough. That is, the fuel-air mixture generated while passing through the space between adjacent vanes 231 and 232 passes through the through portion 291 to exit the swirler assembly 200.
  • the space between the adjacent vanes 231 and 232 is formed in a spiral shape on one surface of the base plate 210 so that the gas fuel (G), the liquid fuel (L) introduced from the space, and The mixture of air may produce a swirl flow F that rotates about the Z-axis direction shown in FIG. 1.
  • the linearly introduced air in the swirler assembly 200 forms the swirl flow F, thereby slowing the flow rate of the air and increasing the reaction surface area between the air and the fuel. This may facilitate the combustion reaction in the combustor.
  • FIG. 7 is a cross-sectional view of the fuel flow of the swirler assembly 100 according to the comparative example viewed from a direction crossing the Z-axis direction.
  • the gaseous fuel flow I is injected from the outer end of the vane 131, that is, the end adjacent to the outer circumference of the base plate 110.
  • a substantial portion of the gaseous fuel flow I injected from the vanes 131 is directed to the space between adjacent vanes 131, 132. However, some of the gaseous fuel flow I changes to the vortex R near the outer end of the vane 131 to form a recirculation zone. This recirculation zone not only increases the mixing time between air and fuel, but also helps to form a continuous and stable ignition.
  • the swirler assembly 100 according to the comparative example has a vane 131 having a simple triangular prism shape.
  • the front end portion 231a of the vane 231 in which the recycle region is formed has a curved shape.
  • the contact area between the vortex R in the recirculation region and the wall surface of the front end portion 231a is reduced, so that the flame is placed on the wall surface of the vane 231.
  • the risk of attachment can be significantly reduced.
  • embodiments of the present invention can supply fuel uniformly to the air flow path.
  • embodiments of the present invention can secure a sufficient time required for mixing between air and fuel by advancing the fuel supply time.
  • embodiments of the present invention can improve the mixing performance between air and fuel by increasing the residence time of the fuel-air mixture in the preburner.
  • Embodiments of the present invention relate to a swirler assembly, and more particularly, to a swirler assembly of a gas turbine combustor that mixes fuel and air.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)

Abstract

Ensemble appareil de tourbillonnement comprenant : une plaque de base ; une pluralité d'aubes agencées le long de la direction circonférentielle de la plaque de base ; une plaque de protection agencée de manière à recouvrir les aubes ; et des trous de pulvérisation d'air qui pénètrent à travers une surface extérieure de la plaque de base et/ou de la plaque de protection et qui sont ouverts entre des aubes adjacentes, les aubes étant pourvues d'une partie d'accueil de combustible gazeux pour stocker du combustible gazeux, d'un orifice de pulvérisation de combustible gazeux, d'une partie d'accueil de combustible liquide pour stocker le combustible liquide, d'un orifice de pulvérisation de combustible liquide qui est radialement étendu à partir de la partie d'accueil de combustible liquide, et une partie d'extrémité de l'aube qui est adjacente à la circonférence de la plaque de base ayant une forme incurvée.
PCT/KR2015/002024 2014-12-12 2015-03-03 Ensemble appareil de tourbillonnement WO2016093430A1 (fr)

Applications Claiming Priority (2)

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KR1020140179369A KR102050414B1 (ko) 2014-12-12 2014-12-12 스월러 어셈블리
KR10-2014-0179369 2014-12-12

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WO2016093430A1 true WO2016093430A1 (fr) 2016-06-16

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106958813A (zh) * 2017-03-20 2017-07-18 中国科学院工程热物理研究所 一种旋流器叶片、喷嘴、喷嘴阵列及燃烧器

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR20180070210A (ko) 2016-12-16 2018-06-26 한국항공우주연구원 연료막 형성을 통해 연소 안정성을 유지하는 연료인젝터
KR102607177B1 (ko) * 2022-01-28 2023-11-29 두산에너빌리티 주식회사 연소기용 노즐, 연소기 및 이를 포함하는 가스터빈

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1918638A1 (fr) * 2006-10-25 2008-05-07 Siemens AG Brûleur, en particulier pour une turbine à gaz
US20090025395A1 (en) * 2006-02-22 2009-01-29 Ulf Nilsson Swirler for Use in a Burner of a Gas Turbine Engine
US20090111063A1 (en) * 2007-10-29 2009-04-30 General Electric Company Lean premixed, radial inflow, multi-annular staged nozzle, can-annular, dual-fuel combustor
US20100074757A1 (en) * 2008-09-25 2010-03-25 Paul Headland Swirler vane
JP2013231582A (ja) * 2012-04-30 2013-11-14 General Electric Co <Ge> タービンエンジン用の燃料／空気予混合システム

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20090025395A1 (en) * 2006-02-22 2009-01-29 Ulf Nilsson Swirler for Use in a Burner of a Gas Turbine Engine
EP1918638A1 (fr) * 2006-10-25 2008-05-07 Siemens AG Brûleur, en particulier pour une turbine à gaz
US20090111063A1 (en) * 2007-10-29 2009-04-30 General Electric Company Lean premixed, radial inflow, multi-annular staged nozzle, can-annular, dual-fuel combustor
US20100074757A1 (en) * 2008-09-25 2010-03-25 Paul Headland Swirler vane
JP2013231582A (ja) * 2012-04-30 2013-11-14 General Electric Co <Ge> タービンエンジン用の燃料／空気予混合システム

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106958813A (zh) * 2017-03-20 2017-07-18 中国科学院工程热物理研究所 一种旋流器叶片、喷嘴、喷嘴阵列及燃烧器
CN106958813B (zh) * 2017-03-20 2019-09-24 中国科学院工程热物理研究所 一种旋流器叶片、喷嘴、喷嘴阵列及燃烧器

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