EP3421885A1 - Chambre de combustion d'une turbine à gaz, turbine à gaz et son procédé de fonctionnement - Google Patents

Chambre de combustion d'une turbine à gaz, turbine à gaz et son procédé de fonctionnement Download PDF

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Publication number
EP3421885A1
EP3421885A1 EP18176189.1A EP18176189A EP3421885A1 EP 3421885 A1 EP3421885 A1 EP 3421885A1 EP 18176189 A EP18176189 A EP 18176189A EP 3421885 A1 EP3421885 A1 EP 3421885A1
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EP
European Patent Office
Prior art keywords
combustion chamber
atomizing
liquid fuel
combustion
decentralized
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.)
Granted
Application number
EP18176189.1A
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German (de)
English (en)
Other versions
EP3421885B1 (fr
Inventor
Frank Reiss
Bernhard Cosic
Gabrielle Tea-Kempf
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.)
Everllence SE
Original Assignee
MAN Diesel and Turbo SE
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Publication of EP3421885A1 publication Critical patent/EP3421885A1/fr
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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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • 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
    • F23R3/34—Feeding into different combustion zones
    • F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D17/00—Burners for combustion simultaneously or alternately of gaseous or liquid or pulverulent fuel
    • F23D17/002—Burners for combustion simultaneously or alternately of gaseous or liquid or pulverulent fuel gaseous or liquid fuel
    • 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
    • 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
    • F23R3/36—Supply of different fuels
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00014—Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00015—Trapped vortex combustion chambers

Definitions

  • the invention relates to a combustion chamber of a gas turbine according to the preamble of claim 1. Furthermore, the invention relates to a gas turbine with such a combustion chamber and a method for operating such a gas turbine.
  • Gas turbines have a combustion chamber and a downstream of the combustion chamber turbine.
  • a fuel is burned and this hot exhaust gas generated.
  • the hot exhaust gas is expanded in the turbine of the gas turbine to thereby gain energy that can serve to provide drive power, for example, to drive a generator for generating electric power.
  • gas turbines already designed as dual-fuel gas turbines are known, such dual-fuel gas turbines comprising a dual-fuel combustion chamber in which a gaseous fuel is combusted in a gaseous fuel operating mode and a liquid fuel is burned in a liquid fuel operating mode.
  • a mixture of a gaseous fuel and combustion air via a swirl body of the combustion chamber can be fed.
  • the combustor of the gas turbine can be supplied with the liquid fuel via a sputtering device and the combustion air via the swirl body.
  • the present invention seeks to provide a novel combustion chamber of a gas turbine, a gas turbine such a combustion chamber and a method for operating such a gas turbine.
  • the atomizing device has a central atomizing lance having at least one atomizing nozzle with respect to a longitudinal central axis of the combustion chamber or with respect to a longitudinal central axis of an antechamber of the combustion chamber.
  • the atomizing device furthermore has a plurality of decentralized atomizing nozzles with respect to the longitudinal central axis of the combustion chamber or with respect to the longitudinal central axis of the prechamber of the combustion chamber.
  • the liquid fuel can be optimally introduced into the combustion chamber via the central atomizing lance, which comprises at least one atomizing nozzle, and via the plurality of decentralized atomizing nozzles, in order to ensure effective combustion of the liquid fuel.
  • the central sputtering lance the liquid fuel can be introduced directly into a central recirculation zone within the combustion chamber or the pre-chamber of the combustion chamber, whereby a stable combustion can be achieved.
  • the introduction of the fuel via the central atomizing lance is not homogeneous to the combustion air, there is no premix of liquid fuel and combustion air here.
  • the liquid fuel can be distributed homogeneously in the combustion air. Furthermore, a partial premix of liquid fuel and combustion air is achieved by the decentralized atomizing nozzles. Due to the decentralized atomizing nozzles, exhaust emissions, in particular nitrogen oxide emissions, can be reduced compared to the central atomizing lance.
  • the decentralized atomizing nozzles are positioned on a circular path extending around the longitudinal central axis of the combustion chamber or about the longitudinal central axis of the pre-chamber of the combustion chamber.
  • a center of the circular path, on which the decentralized atomizing nozzle is positioned is positioned on the longitudinal center axis of the combustion chamber or the prechamber of the combustion chamber.
  • a radius of the circular path on which the decentralized atomizing nozzles are positioned is between 0.4 times and 1.1 times an inner radius of the swirl body.
  • the liquid fuel can be optimally introduced into the combustion chamber while providing a homogeneous distribution thereof with the combustion air and with regard to premixing thereof with the combustion air in order to reduce exhaust emissions such as nitrogen oxide emissions as much as possible.
  • the central sputtering lance has at least two, preferably two, sputtering nozzles which, alone and together, each provide a sputtering cone with a maximum spray angle of 60 °, preferably of at most 55 °.
  • Each of the decentralized atomizing nozzles each provides a sputtering cone with a maximum spray angle of 40 °, preferably a maximum of 30 °.
  • the central sputtering lance is radially surrounded by an adjacent component at least in sections, forming a radial gap, wherein the combustion chamber can be supplied with combustion air via the radial gap while bypassing the swirl body.
  • the gas turbine according to the invention is in claim 9 and the inventive method for operating the same is defined in claim 10.
  • both the central atomizing lance and the decentralized atomizing nozzles are used throughout the operating range between idle and full load in order to supply the liquid fuel to the combustion chamber.
  • This operating variant of the invention is suitable when the gas turbine to be operated is to carry out rapid load changes, since then individual injection nozzles do not have to be switched on or switched off. Flushing procedures, such as are required when turning off individual atomizing nozzles, can thus be avoided. Exhaust emissions can be reduced compared to gas turbines, whose combustion chambers have only one central sputtering lance.
  • both the central atomizing lance and the decentralized atomizing nozzles are used in the liquid fuel operating mode in an operating range below a predetermined load limit to supply liquid fuel to the combustion chamber, whereas in an operating range above the predetermined load limit only the decentralized atomizing nozzles are used to supply the liquid fuel to the combustion chamber.
  • This operating variant of the invention serves to further reduce exhaust emissions, in particular nitrogen oxide emissions.
  • the central sputtering lance for the introduction of the liquid fuel is no longer used, but takes place in the upper load range of the introduction of the liquid fuel exclusively using the decentralized atomizing nozzles.
  • exhaust emissions such as nitrogen oxide emissions can be further reduced, namely in the operating range of high loads.
  • the invention relates to a combustion chamber of a gas turbine, a gas turbine with such a combustion chamber and a method for operating such a gas turbine.
  • Fig. 1 shows a schematic section of a gas turbine in the region of a combustion chamber 1.
  • the combustion chamber 1 is bounded by a wall 2, wherein in the combustion chamber 1, a fuel is burned.
  • Exhaust gas produced during the combustion of the fuel in the combustion chamber 1 can be supplied to a turbine, not shown, of the gas turbine in order to relax the exhaust gas in the turbine and thereby to obtain energy.
  • the combustion chamber 1 is designed as a dual-fuel combustion chamber, which can be operated on the one hand in a gaseous fuel operating mode and on the other hand in a liquid fuel operating mode.
  • a gaseous fuel is burned in the same, wherein a mixture of the gaseous fuel and combustion air of the combustion chamber 1, in Fig. 1 an antechamber 9 of the combustion chamber 1, via a swirler 3 is supplied.
  • the swirl body 3 is preferably designed as a radial swirl body and generates a defined swirl of entering into the pre-chamber 9 of the combustion chamber 1 mixture of combustion air and gaseous fuel.
  • the mixture of the gaseous fuel and the combustion air is ignited in the gaseous fuel operating mode by means of an electric ignition device, not shown.
  • a liquid fuel is burned in the same, wherein the liquid fuel of the combustion chamber 1, in Fig. 1 the antechamber 9 of the combustion chamber 1, with the aid of a sputtering device 4 is supplied.
  • the atomizing device 4 has a central atomizing lance 17, which is positioned approximately in the middle of the prechamber 9 of the combustion chamber 1 or on a longitudinal central axis 20 of the prechamber 9 of the combustion chamber 1 or on a longitudinal central axis 20 of the combustion chamber 1 and the liquid fuel in Direction of the longitudinal central axis 20 with the formation of a Zerstäubungskegels or spray cone 8a in the antechamber 9 of the combustion chamber 1 is injected.
  • the atomizing device 4 has several based on the longitudinal central axis 20 of the combustion chamber 1 or pre-chamber 9 decentralized atomizing nozzles 18, the liquid fuel also in the antechamber 9 of the combustion chamber. 1 can inject, with the formation of a respective spray cone 8b.
  • the atomizing device 4 accordingly has the central atomizing lance 17 and a plurality of decentralized atomizing nozzles 18.
  • the central atomizing lance 17 has at least one atomizing nozzle, preferably a plurality of atomizing nozzles 15, 16 (see FIG Fig. 2 ).
  • Fig. 2 shows a detail of the central sputtering lance 17 of the sputtering device 4.
  • a radial gap 6 is formed, via the combustion air of the combustion chamber 1, namely the prechamber 9, can be supplied, bypassing the swirl body 3.
  • an arrow 13 see Fig. 1
  • That component 5, which defines the annular gap 6 together with the sputtering lance 17 of the atomizing device 4, is preferably designed as a separate sleeve, which is connected to the sputtering lance 17.
  • the mounting wall 12 itself the radially outward of the sputtering lance 17 adjacent component 5, which defines the radial gap 6 together with the sputtering lance 17, provides.
  • the atomizing nozzles 8 of the atomizing device 4, which are decentralized relative to the longitudinal central axis 20 of the combustion chamber 1 or prechamber 9, are preferably arranged on a circular path 19 (see FIG Fig. 3 ), which extends around the longitudinal center axis 20 of the combustion chamber 1 and the longitudinal center axis 20 of the pre-chamber 9 of the combustion chamber 1 around.
  • the decentralized atomizing nozzles 18 accordingly surround the central atomizing lance 17, preferably concentrically.
  • Fig. 3 shows a radius d 18 of the circular path 19, on which the decentralized atomizing nozzles 18 are arranged. It is provided in particular that this radius d 18 of the circular path 19, on which the decentralized atomizing nozzles 18 are positioned, is between 0.4 times and 1.1 times an inner diameter d 3 of the swirl body 3. Then, when the radius d 18 of the circular path 19, on which the decentralized atomizing nozzles 18 are arranged, is between 1.0 times and 1.1 times the inner diameter d 3 of the swirl body 3, the decentralized atomizing nozzles 18 at least partly overlap the swirl body 3 in the region of its exit region.
  • the decentralized atomizing nozzles 18 may also be arranged on a plurality of preferably concentric circular paths or on an elliptical path or a polygon.
  • the central atomizing lance 17 of the atomizing device 4 preferably comprises a plurality of atomizing nozzles, in the exemplary embodiment of FIGS Fig. 2 two atomizing nozzles 15, 16, which are preferably swirl atomizing nozzles.
  • the liquid fuel in liquid fuel operating mode can be supplied from a common liquid fuel supply 21, wherein the guided by the liquid fuel supply 21 fuel in two liquid fuel sub-feeds 21a, 21b is divisible to both atomizing nozzles 15, 16 of the central Atomizing lance 17 to supply liquid fuel.
  • the central atomizing lance 17 with its two atomizing nozzles 15, 16 sprays the liquid fuel in the direction of the combustion chamber 1 with the spray angle ⁇ , which is a maximum of 60 °, preferably a maximum of 55 °.
  • the spray angle ⁇ is in each case a maximum of 60 °, preferably a maximum of 55 °. This ensures that neither walls 2a of the pre-chamber 9 nor walls 2 of the combustion chamber 1 are wetted with liquid fuel, whereby a more effective combustion of the liquid fuel can be provided.
  • combustion air can be supplied to the combustion chamber 1, in particular the prechamber 9, via the gap 6.
  • the air flow 14, which is guided over this annular gap 6, serves on the one hand to cool the central sputtering lance 17 of the atomizing device 4, on the other hand surrounds this air flow 14 at least partially outside the spray cone 8a of the liquid fuel of the sputtering lance 17 and thus bundles the same.
  • the combustion air 14, which the combustion chamber 1, in Fig. 1 the pre-chamber 9, bypassing the swirl body 3 can be supplied via the radial gap 6, in particular between 1% and 10% of the combustion air, which is the combustion chamber via the swirler 3 can be fed.
  • the combustion air flow 14 can be supplied not only in the liquid fuel operating mode of the combustion chamber 1 but also in the gaseous fuel operating mode of the combustion chamber 1 via the radial gap 6, wherein in the gaseous fuel operating mode, the sputtering 4, ie in particular the sputtering lance 17 thereof, is inactive, so then in the gaseous fuel operating mode via the sputtering 4 no fuel is introduced, but only via the swirl body.
  • the sputtering lance 17 is aligned centrally with respect to the longitudinal central axis 20; via the sputtering lance 17 liquid fuel can be introduced into a central recirculation zone in the liquid fuel operating mode. As a result, a very stable combustion can be ensured.
  • the introduction of the liquid fuel via the central atomizing lance 17, which is central with respect to the longitudinal central axis 20, is therefore local, ie not homogeneous to the combustion air, so that no premixing of liquid fuel and combustion air takes place.
  • the combustion chamber 1 comprises in addition to the central atomizing lance 17 a plurality of decentralized atomizing nozzles 18, which are preferably arranged on the circular path 19. These decentralized atomizing nozzles 18 are via a separate liquid fuel supply 22 (see Fig. 1 ) can be supplied with liquid fuel, wherein the decentralized atomizing nozzles 18 introduce the liquid fuel in approximately the same direction in the prechamber 9 or combustion chamber 1, as the central atomizing lance 17, but with a spray angle ⁇ , which is smaller than the spray angle ⁇ , wherein the spray angle ⁇ of the decentralized atomizing nozzles 18 is preferably not more than 40 °, preferably not more than 30 °.
  • the fuel is introduced into the combustion chamber 1, in particular into the prechamber 9, forming a homogeneous distribution with the combustion air, at the same time providing a partial premix of combustion air and liquid fuel, in particular supports the fact that the decentralized atomizing nozzles 18 are arranged adjacent to the outlet of the swirl body 3.
  • This partial premix can be improved if the radius d 18 is greater than the radius d 3 .
  • the radius d 18 can be between 1.0 times and 1.1 times the radius d 3 .
  • decentralized atomizing nozzles 18 preferably find double jet nozzles or. Plain jets use. Via the decentralized atomizing nozzles 18, a homogeneous supply of the liquid fuel to the combustion air is achieved, as well as a partial premix of liquid fuel and combustion air.
  • the combustor 1 when the combustor 1 is to be operated in the gaseous fuel operating mode, the combustor 1 is supplied with a gas-combustion air mixture via the swirler 3.
  • combustion air may be passed over the annular gap 6.
  • combustion air flow 14 is branched off in the region of an air space, a so-called plenum 10, upstream of the swirl body 3.
  • FIG. 1 an air line 11 through which combustion air can be diverted from the plenum 10, wherein the combustion air 14 branched off from the plenum 10 via the air line 11 is fed to an air chamber 7 formed by the wall 12, and then from this air chamber 7 via the atomizing lance 17 the atomizing device 4 and the adjacent component 5 formed annular gap 6 in the antechamber 9 of the combustion chamber 1 to be introduced.
  • the combustion chamber 1 when the combustion chamber 1 is operated in liquid fuel operating mode with active atomizing device 4, the combustion chamber 1 or pre-chamber 9, the liquid fuel via the atomizer 4, combustion air via the swirler 3 and preferably via the annular gap 6 between the central sputtering lance 17 and the Component 5.
  • both the central atomizing lance 17 and the decentralized atomizing nozzles 18 of the atomizing device 4 are used in the entire operating range between idling and full load in order to supply the liquid fuel to the combustion chamber 1.
  • the curve 21 corresponds to the liquid fuel supply 21 via the central atomizing lance 17, wherein the curve 22 corresponds to the liquid fuel supply 22 via the decentralized atomizing nozzles 18, wherein the curve 23 the Load share of the total load L, which can be provided by the combustion of the introduced via the central atomizing lance 17 liquid fuel, and wherein the curve 24 shows the proportion of load on the total load L, which can be provided by the combustion of the fuel, over the decentralized Atomizing nozzles 18 is introduced into the combustion chamber.
  • Fig. 4 shows Fig. 4 in that fuel is supplied to the combustion chamber 1 over the entire load range between 0% (idle) and 100% (full load) both via the central atomizing lance 17 and via the decentralized atomizing nozzles 18 over the entire operating range between idling (0%) and full load (100%) via the central atomizing lance 17 (see curve 21) preferably a constant amount of liquid fuel of the combustion chamber 1 is supplied.
  • the power modulation then takes place by changing the liquid fuel introduced via the decentralized atomizing nozzles 18 (see curve 22) so that with increasing load requirement L the load portion 23 of the central atomizing lance 17 decreases relative to the load portion of the decentralized atomizing nozzles 18 or the corresponding load fraction 24 of the decentralized atomizing nozzles 18 increases.
  • both the central atomizing lance 17 and the decentralized atomizing nozzles 18 are used in the entire load range or operating range between idling and full load, in order to supply the liquid fuel to the combustion chamber, it is provided in particular that during combustion of the gas turbine combustion in the combustion chamber 1 is introduced into the combustion chamber 1 exclusively via one of the two atomizing nozzles 15, 16 of the atomizing lance 17, and that after the acceleration and after reaching a defined rotational speed of the gas turbine, both atomizing nozzles 15, 16 of the atomizing lance 17 are used Fuel via the sputtering lance 17 in the combustion chamber 1 introduce.
  • Fig. 5 illustrates a second operating concept of the combustion chamber according to the invention or the gas turbine according to the invention comprising the inventive combustion chamber. So shows Fig. 5 in that the load range L between the idling (0%) and the full load (100%) is subdivided into two load ranges, namely a load range between idling (0%) and a limit value GW, and into a load range between a limit value GW and Full load (100%).
  • both the central atomizing lance 17 and the decentralized atomizing nozzles 18 are used to supply liquid fuel to the combustion chamber 1.
  • the amount of fuel introduced via the central atomizing lance 17 is preferably constant in this load range, and the power modulation then takes place exclusively via the change in the amount of liquid introduced via the decentralized atomizing nozzles 18 (see curve 22).
  • the central atomizing lance 17 is switched off so that no more fuel is supplied via the same, so that in the upper load range between the load limit GW and full load (100%) liquid fuel exclusively via the decentralized atomizing nozzles 18 of the combustion chamber 1 is supplied.
  • An advantage of this second operating concept according to the invention is that, at loads above the defined load limit GW, the liquid fuel is not centrally introduced into the recirculation zone of the combustion chamber 1, but exclusively decentralized, so that for all the liquid fuel introduced a homogeneous introduction to the combustion air and a partial premix can be ensured with combustion air, which exhaust emissions, especially nitrogen oxide emissions, compared to the operating concept of Fig. 4 can be further reduced.
  • nitrogen oxide emissions of less than 90 vppm, based on 15% oxygen, can be realized.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Combustion Methods Of Internal-Combustion Engines (AREA)
EP18176189.1A 2017-06-28 2018-06-06 Chambre de combustion d'une turbine à gaz, turbine à gaz et son procédé de fonctionnement Active EP3421885B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102017114362.9A DE102017114362A1 (de) 2017-06-28 2017-06-28 Brennkammer einer Gasturbine, Gasturbine und Verfahren zum Betreiben derselben

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Publication Number Publication Date
EP3421885A1 true EP3421885A1 (fr) 2019-01-02
EP3421885B1 EP3421885B1 (fr) 2022-12-21

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EP18176189.1A Active EP3421885B1 (fr) 2017-06-28 2018-06-06 Chambre de combustion d'une turbine à gaz, turbine à gaz et son procédé de fonctionnement

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US (1) US20190003712A1 (fr)
EP (1) EP3421885B1 (fr)
JP (1) JP7128672B2 (fr)
DE (1) DE102017114362A1 (fr)

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CN113551259A (zh) * 2021-07-19 2021-10-26 南昌航空大学 一种带波瓣分隔板的波浪形中缝式v型火焰稳定器

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DE102018125848A1 (de) 2018-10-18 2020-04-23 Man Energy Solutions Se Brennkammer einer Gasturbine, Gasturbine und Verfahren zum Betreiben derselben
CN114791104B (zh) * 2021-01-25 2026-03-10 李华玉 双燃料高温热源与双燃料燃气轮机装置
CN113983496B (zh) * 2021-09-23 2022-11-22 中国联合重型燃气轮机技术有限公司 喷嘴、燃烧室和燃气轮机

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Publication number Priority date Publication date Assignee Title
CN113551259A (zh) * 2021-07-19 2021-10-26 南昌航空大学 一种带波瓣分隔板的波浪形中缝式v型火焰稳定器
CN113551259B (zh) * 2021-07-19 2022-09-30 南昌航空大学 一种带波瓣分隔板的波浪形中缝式v型火焰稳定器

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DE102017114362A1 (de) 2019-01-03
US20190003712A1 (en) 2019-01-03
JP2019007726A (ja) 2019-01-17
JP7128672B2 (ja) 2022-08-31

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