CN103104936B - Unit nozzle for organizing combustion of large flow medium and low calorific value fuel - Google Patents
Unit nozzle for organizing combustion of large flow medium and low calorific value fuel Download PDFInfo
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- CN103104936B CN103104936B CN201210566218.4A CN201210566218A CN103104936B CN 103104936 B CN103104936 B CN 103104936B CN 201210566218 A CN201210566218 A CN 201210566218A CN 103104936 B CN103104936 B CN 103104936B
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Abstract
The invention relates to a fuel nozzle, in particular to a unit nozzle for organizing combustion of large flow medium and low calorific value fuel. The aim of the unit nozzle is that operation of the fuel nozzle can be safe, stable and efficient. A central oil nozzle is arranged in a conic shell and coaxial with the conic shell. A conic shell body air swirler is arranged on an outer wall at an outlet end of the conic shell. An outer surface of the conic shell body air swirler is gradually contracted and the gradually contracted direction of the conic shell body air swirler is identical to that of the conic shell. A leaf crown is fixedly connected on an outer edge of an outlet end of the conic shell body air swirler, the leaf crown is coaxial with the conic shell body air swirler and an end face of the leaf crown is aligned to an end face of the conic shell body air swirler. The outlet end of the conic shell is arranged in a sleeve tube and connected with the sleeve tube through the leaf crown. An inner space of the sleeve tube located on the upper portion of the outlet end of the conic shell is a mixing section of compressed air and medium and low calorific value gas. According to the unit nozzle for organizing the combustion of the large flow medium and low calorific value fuel, a first swirl flow relative to the fuel is matched with a second swirl flow relative to air, so that fuel-air mixture is delivered to the fuel nozzle. The fuel nozzle is safe, stable and efficient in operation.
Description
Technical field
The present invention relates to a kind of fuel nozzle, be specifically related to the fuel nozzle that in Integrated gasification combined cycle (IGCC) electricity generation system, gas turbine uses.
Background technology
The combustion system burning medium and low heat value fuel of the gas turbine that some are known is to produce the exhaust that drives turbine.Yet compare with other fuel (as natural gas), most of known medium and low heat value fuel calorific value is low, and the wobbe index that comparing with other fuel of therefore producing also may be lower.In addition, most of known medium and low heat value fuel has larger hydrogen content, causes between fuel flow characterization class hour very shortly, and fuel reaction is very high.Due to this combination of low wobbe index and high fuel reaction, for fuel nozzle can be safely, stable, operation efficiently, control so mixing for the performance of combustion chamber and discharge and all tool being had very important significance of fuel and air.
Summary of the invention
The unit nozzle that the object of this invention is to provide the large flow medium and low heat value fuel burning of the tissue using a kind of combination combustion chamber so that fuel nozzle can be safely, stable, move efficiently.
The present invention solves the problems of the technologies described above the technical scheme of taking to be:
Of the present invention a kind of for organizing the unit nozzle of large flow medium and low heat value fuel burning to comprise center oil nozzle, conical shell, integral shroud and sleeve pipe, described center oil nozzle is placed in conical shell and the two is coaxial, the port of export outer wall of conical shell port of export inwall and center oil nozzle is connected together, the port of export outer wall of conical shell is provided with conical shell air cyclone, and the outer surface of conical shell air cyclone is gradually-reducing shape and consistent with the convergent direction of conical shell; Integral shroud is fixed in conical shell air cyclone port of export outer rim, and the two is coaxial, and end face is concordant; The conical shell port of export is placed in sleeve pipe and between the two and links together by integral shroud, and the inner space that is arranged in the sleeve pipe on conical shell port of export top is the Mixed Zone of compressed air and low heat value gas; The fuel openings end of conical shell is provided with first group of fuel openings along circumferentially spaced and second group of fuel openings along circumferentially spaced, wherein first group of fuel openings along circumferentially spaced is positioned at conical shell air cyclone downstream, second group of fuel openings along circumferentially spaced is positioned at conical shell air cyclone inside, between conical shell and center oil nozzle, space is middle low heat value gas passage, and first group of fuel openings along circumferentially spaced is for allowing the low heat value gas of large volume flow to be injected in Mixed Zone, combustion chamber; Conical shell air cyclone is provided with a plurality of air openings along circumferentially spaced, in order to allow compressed air to inject in Mixed Zone, combustion chamber; Second group of fuel openings along circumferentially spaced enters in Mixed Zone, combustion chamber after low heat value gas is first tentatively mixed with compressed air again.
Described medium and low heat value fuel flow is between 60kg/s to 80kg/s, and main component is H2 (hydrogen) and CO, and wherein H2 volume fraction is about 35%, CO volume fraction is about 45%, because hydrogen self-ignition temperature is low, flame propagation speed, nozzle adopts diffusion combustion mode, guarantee air and fuel jet speed, avoid tempering to produce, and because CO burning velocity is slower, should build enough strong recirculation zone at head, strengthen the blending performance of fuel and air, avoid the length of flame long.
Beneficial effect of the present invention: be provided with a plurality of fuel openings along circumferentially spaced of first and second group on conical shell, in order to guide medium and low heat value fuel to the Mixed Zone in combustion chamber; Conical shell air cyclone is provided with a plurality of air openings along circumferentially spaced, and in order to compressed air is injected to Mixed Zone, the plurality of air openings is oriented and contributes to produce the swirling number that is greater than 0.6 in Mixed Zone.The integral shroud of inner conical and a plurality of air openings form the rectangle air flow channel of directional inclination jointly, strengthen the inscribe directionality of air openings.Utilization of the present invention matches with the second eddy flow for air for the first eddy flow of fuel, produces the fuel-air mixture as for fuel nozzle.Fuel nozzle of the present invention can be safely, stable, operation efficiently.
Accompanying drawing explanation
Fig. 1 is that the master of a kind of large flow medium and low heat value fuel of the present invention unit nozzle looks cutaway view; Fig. 2 has shown the conical shell front view of a kind of large flow medium and low heat value fuel unit nozzle; Fig. 3 has shown the top view of a kind of large flow medium and low heat value fuel unit nozzle; Fig. 4 has shown the stereogram of a kind of large flow medium and low heat value fuel unit nozzle.
The specific embodiment
The specific embodiment one: as shown in Fig. 1～4, described in present embodiment for organizing the unit nozzle of large flow medium and low heat value fuel burning to comprise center oil nozzle 42, described unit nozzle also comprises conical shell 21, integral shroud 31 and sleeve pipe 41, described center oil nozzle 42 is placed in conical shell 21 and the two is coaxial, the port of export (small end) outer wall of conical shell 21 ports of export (small end) inwall and center oil nozzle 42 is connected together, the port of export outer wall of conical shell 21 is provided with conical shell air cyclone 25, the outer surface of conical shell air cyclone 25 is gradually-reducing shape and consistent with the convergent direction of conical shell 21, integral shroud 31 is fixed in conical shell air cyclone 25 port of export outer rims, and the two is coaxial, and end face is concordant, conical shell 21 ports of export are placed in sleeve pipe 41 and between the two and link together by integral shroud 31, and the inner space that is arranged in the sleeve pipe 41 on conical shell 21 port of export tops is the Mixed Zone 11 of compressed air and low heat value gas, the fuel openings end of conical shell 21 is provided with first group of fuel openings 23 along circumferentially spaced and second group of fuel openings 24 along circumferentially spaced, wherein first group of fuel openings 23 along circumferentially spaced is positioned at conical shell air cyclone 25 downstreams, second group of fuel openings 24 along circumferentially spaced is positioned at conical shell air cyclone (25) inside, first group of fuel openings 23 to the second group along circumferentially spaced more approach Mixed Zone 11 along the fuel openings 24 of circumferentially spaced, between conical shell 21 and center oil nozzle 42, space is middle low heat value gas passage, first group of fuel openings 23 along circumferentially spaced is for allowing the low heat value gas (fuel) of large volume flow to be injected in Mixed Zone, combustion chamber 11, conical shell air cyclone 25 is provided with a plurality of air openings 22 along circumferentially spaced, in order to allow compressed air to inject in Mixed Zone, combustion chamber 11, second group of fuel openings 24 along circumferentially spaced enters in Mixed Zone, combustion chamber 11 after low heat value gas is first mixed with compressed air again.
Described conical shell fuel openings 23,24 is in order to guide medium and low heat value fuel to the Mixed Zone 11 in combustion chamber, described conical shell air cyclone 25 comprises one group of a plurality of air openings 22 along circumferentially spaced, in order to compressed air is injected in Mixed Zone 11, each air openings cross sectional shape is rectangle, and each corner of rectangle needs rounding; And being connected to the integral shroud 31 on air openings, this integral shroud, in order to strengthen the guidance quality of rotational flow air inscribe, also comprises circulation compressed air to a plurality of air openings 32 along circumferentially spaced of Mixed Zone, the cross sectional shape that wherein each air openings is rectangle.
Described first group of fuel openings 23 along circumferentially spaced and described second group of fuel openings 24 formation along circumferentially spaced are in order to inject fuel in described Mixed Zone 11 with the flow angle of center line 100 inclined orientation about described unit nozzle.
Described a plurality of air openings 22 is in order to inject compressed air in described Mixed Zone 11 with the through-flow angle of center line 100 inclined orientation about described unit nozzle.
The specific embodiment two: as shown in Fig. 1～4, described in present embodiment, center oil nozzle 42 comprises atomizing air nozzle body 42-1, oil burner nozzle housing 42-2, support 42-3 and spinning disk 42-4, the profile of atomizing air nozzle body 42-1 and oil burner nozzle housing 42-2 is all tapered, oil burner nozzle housing 42-2 is placed in atomizing air nozzle body 42-1 and the space between the two is atomizing air passage, spinning disk 42-4 is arranged on the port of export of oil burner nozzle housing 42-2 by support 42-3, fuel oil mixes with atomizing air from the outlet ejection of oil burner nozzle housing 42-2 through spinning disk 42-4 by the entrance of oil burner nozzle housing 42-2.Other composition and annexation are identical with the specific embodiment one.
The specific embodiment three: as shown in Fig. 1～4, in present embodiment, first group of fuel openings 23 along circumferentially spaced and second group of fuel openings 24 along circumferentially spaced are with the directed flow angle θ obliquely of the center line 100 about conical shell 21
1inject fuel, flow angle θ
1be between 10 ° to 30 °.Other composition and annexation are identical with the specific embodiment one or two.
The specific embodiment four: as shown in Fig. 1～4, the rectangular cross sectional shape of air openings 22 described in present embodiment.Other composition and annexation are identical with the specific embodiment three.
The specific embodiment five: as shown in Fig. 1～4, in present embodiment, arrival end (greatly end) end face of conical shell 21 of take is benchmark, and first group of axial distance 54 along the fuel openings 23 of circumferentially spaced should be greater than conical shell air cyclone 25 top axial distances 53; Second group of axial distance 52 along the fuel openings 24 of circumferentially spaced should be between conical shell air cyclone 25 top axial distances 53 and conical shell air cyclone 25 bottom axial distances 51.Other composition and annexation are identical with the specific embodiment four.
The specific embodiment six: as shown in Fig. 1～4, air openings 22 is with the flow angle θ of center line 100 inclined orientation about conical shell 21 described in present embodiment
2to Mixed Zone, 11 inject compressed air, flow angle θ
2be between 20 ° to 40 °.Other composition and annexation are identical with the specific embodiment one, two, four or five.
The specific embodiment seven: as shown in Fig. 1～4, air openings 22 is with the flow angle θ of center line 100 inclined orientation about conical shell 21 described in present embodiment
2to Mixed Zone, 11 inject compressed air, flow angle θ
2be between 20 ° to 40 °.Other composition and annexation are identical with the specific embodiment three.
The specific embodiment eight: as shown in Fig. 1～4, in present embodiment, described first group of fuel openings 23 along circumferentially spaced and second group of fuel openings 24 along circumferentially spaced are concentric around the center line 100 of described unit nozzle; First group of fuel openings 23 along circumferentially spaced and second group of fuel openings 24 along circumferentially spaced are oriented the swirling number that contributes to be not less than in the interior generation in described Mixed Zone 11 0.4 swirling number.Other composition and annexation are identical with the specific embodiment one or two.
The specific embodiment nine: as shown in Fig. 1～4, described in present embodiment, first group of fuel openings 23 along circumferentially spaced and described second group of fuel openings 24 along circumferentially spaced are in the flow angle guiding fuel between about 10 ° to 30 °, and described a plurality of air openings 22 is in flow angle between about 25 ° to 40 ° guiding compressed air, is oriented and contributes to be not less than 0.6 swirling number in the interior generation in described Mixed Zone 11.Other composition and annexation are identical with the specific embodiment one or two.
The specific embodiment ten: as shown in Fig. 1～4, have a plurality of air openings 32 along circumferentially spaced, the cross sectional shape that wherein each air openings is rectangle on integral shroud 31 described in present embodiment.Other composition and annexation are identical with the specific embodiment one or two.
Described integral shroud 31 is inner conical, in order to strengthen the inscribe directionality of air openings 22, and produces stress for fear of air cyclone 25, after integral shroud welding, in each air swirl conduit center, offers place's air openings 32.
Embodiment: in an exemplary embodiment, unit nozzle 40 comprises conical shell 21 and integral shroud 31, and integral shroud 31 is welded on conical shell air cyclone 25 outer rims, and the two is coaxial, and end face is concordant.
In an exemplary embodiment, conical shell fuel openings comprises first group of a plurality of fuel openings 23 along circumferentially spaced and second group of a plurality of fuel openings 24 along circumferentially spaced, in order to allow the fuel of large volume flow to be injected in Mixed Zone, combustion chamber 11.Fuel openings 23 and 24 is circular, and as alternative, opening 23 and 24 can be any cross sectional shape that can make fuel openings play to act on described in literary composition.Fuel openings 23 and 24 center lines 100 around unit nozzle are coaxial and along circumferentially spaced apart.Particularly, in an exemplary embodiment, upwards, fuel openings 23 is on the circle of the first radius 57 in footpath, and fuel openings 24 is on the circle of the second radius 58, and the first radius 57 to the second radiuses 58 are little; Axially upper, fuel openings 23 is on the height of axial distance 54, and fuel openings 24 is on the height of axial distance 52, and axial distance 54 is greater than axial distance 52, represents that fuel openings 23 more approaches mixed zone 11 than fuel openings 24.
In an exemplary embodiment, fuel openings 23 and 24 is injected into fuel in Mixed Zone, combustion chamber 11.Particularly, fuel openings 23 and 24 is with about center line 100 directed flow angle θ obliquely
1inject fuel.In an exemplary embodiment, flow angle θ
1be between about 10 ° to 30 °.
In an exemplary embodiment, conical shell air cyclone 25, comprises a plurality of air openings 22 along circumferentially spaced, in order to allow compressed air to inject in Mixed Zone, combustion chamber 11.Air openings 22 tools are square-section, and as alternative, air openings 22 can be any shape that air openings 22 can be played act on described in literary composition.Air openings 22 is spaced apart in the circumferential direction around center line 100, particularly, footpath upwards, air openings 22 is outwards spaced apart with radial distance 59 from center line 100, outward flange radius is radial distance 60, in an exemplary embodiment, radial distance 59 is between the first radius 57 and the second radius 58, and the second radius 58 is between radial distance 60 and radial distance 59; Axially upper, air cyclone 25 bottom axial distances 51, top axial distance 53, special declaration, fuel openings 23 axial distances 54 should be greater than air cyclone 25 top axial distances 53; Fuel openings 24 axial distances 52 should be between air cyclone 25 top axial distances 53 and bottom axial distance 51.
In an exemplary embodiment, air openings 22 is injected compressed air in Mixed Zone, combustion chamber 11.Particularly, air openings 22 is with the flow angle θ about center line 100 inclined orientation
2to Mixed Zone, 11 inject compressed air, flow angle θ
2approximately be between 20 ° to 40 °.As alternative, flow angle θ
1and θ
2can be in and can make fuel-air mixture any angle of state as described in the text.
At run duration, center oil nozzle 42 is injected Mixed Zone, combustion chamber 11 by fuel oil during the startup of gas turbine machine and underrun.In an exemplary embodiment, pneumatic fuel is 2# distilled oil.When gas turbine rises to certain load, center oil nozzle stops oil spout, and Fuel switching is to medium and low heat value fuel, medium and low heat value fuel from fuel openings 23,24 with flow angle θ
1inject Mixed Zone 11, compressed air from air openings 22 with flow angle θ
2inject Mixed Zone 11, the two rotation direction is identical, and in Mixed Zone 11, rotation mixes, and generates the stronger eddy flow that is greater than 0.6 left-right rotary fluxion, and stronger eddy flow contributes to medium and low heat value fuel and compressed-air actuated blending, shortens blending time and stroke distances; Contribute to produce stronger recirculating zone, generate shorter the stabilizing the flame of length.
By the above specific embodiment, the present invention be have been described in detail, but should be appreciated that the present invention is not limited to the disclosed embodiments, on the contrary, various modifications and equivalence that the present invention is intended to cover in the spirit and scope that comprise claims arrange.Therefore, to retaining object of the present invention, at other slightly different examples of subtlety, be also suitable for.
Brief introduction of work principle:
Due to easily tempering of hydrogen-rich fuel (middle low heat value gas), spontaneous combustion, so in order to guarantee safety, generally all with fuel oil, light, fuel oil exports high-speed jet by spinning disk from oil burner nozzle, by the atomizing air of high pressure, shearing atomization is silk noil, and burn while mixing with compressed air, for example, when unit is elevated to after certain load (50%), be switched to gradually middle low heat value gas and (reduce gradually fuel oil and atomization air flow, increase the middle low heat value gas of corresponding calorific value), until fuel oil cuts off completely, atomizing air passage remains with the seldom purging air of flow, medium and low heat value fuel is from fuel openings 23, inject to 24 inclined orientation Mixed Zone 11, compressed air from air openings (cyclone) inclined orientation inject Mixed Zone 11, the two rotation direction is identical, in Mixed Zone 11, rotation mixes, generation is greater than the stronger eddy flow of 0.6 left-right rotary fluxion, stronger eddy flow contributes to medium and low heat value fuel and compressed-air actuated blending, shorten blending time and stroke distances, contribute to produce stronger recirculating zone, generate shorter the stabilizing the flame of length.Be raised at full capacity to unit.
Claims (10)
1. one kind for organizing the unit nozzle of large flow medium and low heat value fuel burning, described unit nozzle comprises center oil nozzle (42), it is characterized in that: described unit nozzle also comprises conical shell (21), integral shroud (31) and sleeve pipe (41), described center oil nozzle (42) is placed in conical shell (21) and the two is coaxial, the port of export outer wall of conical shell (21) port of export inwall and center oil nozzle (42) is connected together, the port of export outer wall of conical shell (21) is provided with conical shell air cyclone (25), the outer surface of conical shell air cyclone (25) is gradually-reducing shape and consistent with the convergent direction of conical shell (21), integral shroud (31) is fixed in conical shell air cyclone (25) port of export outer rim, and the two is coaxial, and end face is concordant, conical shell (21) port of export is placed in sleeve pipe (41) and between the two and links together by integral shroud (31), and the inner space that is arranged in the sleeve pipe (41) on conical shell (21) port of export top is the Mixed Zone (11) of compressed air and low heat value gas, the fuel openings end of conical shell (21) is provided with first group of fuel openings along circumferentially spaced (23) and second group of fuel openings along circumferentially spaced (24), wherein first group of fuel openings along circumferentially spaced (23) is positioned at conical shell air cyclone (25) downstream, second group of fuel openings along circumferentially spaced (24) is positioned at conical shell air cyclone (25) inside, between conical shell (21) and center oil nozzle (42), space is middle low heat value gas passage, first group of fuel openings along circumferentially spaced (23) is for allowing the low heat value gas of large volume flow to be injected in Mixed Zone, combustion chamber (11), conical shell air cyclone (25) is provided with a plurality of air openings along circumferentially spaced (22), in order to allow compressed air to inject in Mixed Zone, combustion chamber (11), second group of fuel openings along circumferentially spaced (24) enters in Mixed Zone, combustion chamber (11) after low heat value gas is first tentatively mixed with compressed air again.
2. according to claim 1 a kind of for organizing the unit nozzle of large flow medium and low heat value fuel burning, it is characterized in that: described center oil nozzle (42) comprises atomizing air nozzle body (42-1), oil burner nozzle housing (42-2), support (42-3) and spinning disk (42-4), the profile of atomizing air nozzle body (42-1) and oil burner nozzle housing (42-2) is all tapered, oil burner nozzle housing (42-2) is placed in atomizing air nozzle body (42-1) and the space between the two is atomizing air passage, spinning disk (42-4) is arranged on the port of export of oil burner nozzle housing (42-2) by support (42-3), fuel oil is by entrance outlet ejection from oil burner nozzle housing (42-2) through spinning disk (42-4) of oil burner nozzle housing (42-2), through atomizing air, shear atomization, with compressed air in Mixed Zone (11) mix after-combustion.
3. according to claim 1 and 2 a kind of for organizing the unit nozzle of large flow medium and low heat value fuel burning, it is characterized in that: first group of fuel openings along circumferentially spaced (23) and second group of fuel openings along circumferentially spaced (24) are with the center line about conical shell (21) (100) the flow angle θ of orientation obliquely
1inject fuel, flow angle θ
1be between 10 ° to 30 °.
4. according to claim 3 a kind of for organizing the unit nozzle of large flow medium and low heat value fuel burning, it is characterized in that: the rectangular cross sectional shape of described air openings (22).
5. according to claim 4 a kind of for organizing the unit nozzle of large flow medium and low heat value fuel burning, it is characterized in that: the arrival end end face of conical shell (21) of take is benchmark, and the axial distance (54) of first group of fuel openings along circumferentially spaced (23) should be greater than conical shell air cyclone (25) top axial distance (53); The axial distance (52) of second group of fuel openings along circumferentially spaced (24) should be between conical shell air cyclone (25) top axial distance (53) and conical shell air cyclone (25) bottom axial distance (51).
6. according to a kind of unit nozzle for organizing large flow medium and low heat value fuel to burn described in claim 1,2,4 or 5, it is characterized in that: described air openings (22) is with the flow angle θ of the center line about conical shell (21) (100) inclined orientation
2to Mixed Zone, (11) inject compressed air, flow angle θ
2be between 20 ° to 40 °.
7. according to claim 3 a kind of for organizing the unit nozzle of large flow medium and low heat value fuel burning, it is characterized in that: described air openings (22) is with the flow angle θ of the center line about conical shell (21) (100) inclined orientation
2to Mixed Zone, (11) inject compressed air, flow angle θ
2be between 20 ° to 40 °.
8. according to claim 1 and 2 a kind of for organizing the unit nozzle of large flow medium and low heat value fuel burning, it is characterized in that: described first group of fuel openings along circumferentially spaced (23) and second group of fuel openings along circumferentially spaced (24) are concentric around the center line (100) of described unit nozzle; First group of fuel openings along circumferentially spaced (23) and second group of fuel openings along circumferentially spaced (24) are oriented and contribute to produce the swirling number that is not less than 0.4 in described Mixed Zone (11).
9. according to claim 1 and 2 a kind of for organizing the unit nozzle of large flow medium and low heat value fuel burning, it is characterized in that, described first group of fuel openings along circumferentially spaced (23) and described second group of fuel openings along circumferentially spaced (24) are in the flow angle guiding fuel between 10 ° to 30 °, and described a plurality of air openings (22) is in flow angle between 25 ° to 40 ° guiding compressed air, is oriented and contributes to generation described Mixed Zone (11) in to be not less than 0.6 swirling number.
10. according to claim 1 and 2 a kind of for organizing the unit nozzle of large flow medium and low heat value fuel burning, it is characterized in that: on described integral shroud (31), have a plurality of air openings along circumferentially spaced (32), the cross sectional shape that wherein each air openings is rectangle.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210566218.4A CN103104936B (en) | 2012-12-24 | 2012-12-24 | Unit nozzle for organizing combustion of large flow medium and low calorific value fuel |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210566218.4A CN103104936B (en) | 2012-12-24 | 2012-12-24 | Unit nozzle for organizing combustion of large flow medium and low calorific value fuel |
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| CN103104936A CN103104936A (en) | 2013-05-15 |
| CN103104936B true CN103104936B (en) | 2014-11-05 |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN103939942B (en) * | 2014-03-11 | 2015-12-02 | 哈尔滨工程大学 | The rotational flow strengthening nozzle of a kind of catalyst and plasma body cooperative catalytic fuel |
| CN106838988A (en) * | 2017-01-11 | 2017-06-13 | 南方科技大学 | A kind of fuel nozzle |
| CN111805078B (en) * | 2020-07-23 | 2021-12-21 | 哈尔滨汽轮机厂有限责任公司 | Manufacturing method of 300 MW-level heavy-duty gas turbine nozzle swirler assembly |
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| US8177145B2 (en) * | 2008-11-04 | 2012-05-15 | General Electric Company | Feed injector system |
| US20100281869A1 (en) * | 2009-05-06 | 2010-11-11 | Mark Allan Hadley | Airblown Syngas Fuel Nozzle With Diluent Openings |
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| CN101000145A (en) * | 2006-01-12 | 2007-07-18 | 中国科学院工程热物理研究所 | Combustion chamber of miniature gas turbine with double premixed channel using natural gas |
| WO2008057685A3 (en) * | 2006-10-06 | 2008-09-12 | Gen Electric | Combustor nozzle for a fuel-flexible combustion system |
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| CN103104936A (en) | 2013-05-15 |
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