CN104534515B - Gas-turbine combustion chamber head construction - Google Patents
Gas-turbine combustion chamber head construction Download PDFInfo
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- CN104534515B CN104534515B CN201410727617.3A CN201410727617A CN104534515B CN 104534515 B CN104534515 B CN 104534515B CN 201410727617 A CN201410727617 A CN 201410727617A CN 104534515 B CN104534515 B CN 104534515B
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- jet
- nozzle
- swirl
- fuel
- jet stream
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 51
- 238000010276 construction Methods 0.000 title claims abstract description 14
- 239000000446 fuel Substances 0.000 claims description 59
- 239000003344 environmental pollutant Substances 0.000 abstract description 6
- 231100000719 pollutant Toxicity 0.000 abstract description 6
- MWUXSHHQAYIFBG-UHFFFAOYSA-N nitrogen oxide Inorganic materials O=[N] MWUXSHHQAYIFBG-UHFFFAOYSA-N 0.000 description 15
- 239000000203 mixture Substances 0.000 description 7
- 239000007789 gas Substances 0.000 description 6
- 239000007921 spray Substances 0.000 description 4
- 238000002347 injection Methods 0.000 description 3
- 239000007924 injection Substances 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- GQPLMRYTRLFLPF-UHFFFAOYSA-N Nitrous Oxide Chemical class [O-][N+]#N GQPLMRYTRLFLPF-UHFFFAOYSA-N 0.000 description 2
- 238000001816 cooling Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000002156 mixing Methods 0.000 description 2
- UGFAIRIUMAVXCW-UHFFFAOYSA-N Carbon monoxide Chemical compound [O+]#[C-] UGFAIRIUMAVXCW-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000005842 biochemical reaction Methods 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- 230000009514 concussion Effects 0.000 description 1
- 239000000686 essence Substances 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 239000003546 flue gas Substances 0.000 description 1
- 239000001257 hydrogen Substances 0.000 description 1
- 229910052739 hydrogen Inorganic materials 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 239000003345 natural gas Substances 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 238000005496 tempering Methods 0.000 description 1
Abstract
The present invention relates to gas-turbine combustion chamber technical field, a kind of gas-turbine combustion chamber head construction is disclosed, including head end plate, be arranged on the central nozzle of the head end plate and the multiple jet nozzle circles being looped around around the central nozzle；A swirl nozzle circle is equipped between the jet nozzle circle of arbitrary neighborhood two；Each swirl nozzle circle includes multiple swirl nozzle modules being intervally arranged；The central nozzle is also a swirl nozzle module；Often enclosing the jet nozzle circle includes an annular jet nozzle or multiple spaced jet nozzle modules.The present invention sets multiple swirl nozzle circles and jet nozzle circle, and when burning forms distributed flame, obtains the overall uniform flame of a lifting, combustion chambers burn pattern is in distribution flame zone, effectively reduce the pollutant emission of whole combustion chamber.
Description
Technical field
The present invention relates to gas-turbine combustion chamber technical field, is tied more particularly to a kind of gas-turbine combustion chamber head
Structure.
Background technology
For industrial heavy gas turbine, developing goal is always the average temperature of combustor exit of higher between many decades
Degree (calibration gas turbine technology grade) and the discharge of more low stain thing；Above-mentioned technical indicator is closely related with combustion chamber and itself
Conflicting, the combustor exit mean temperature of higher means that more multi fuel participates in combustion process, and burn average indoor temperature
Higher, and the nitrogen oxides as combustion chamber major pollutants and combustion chamber thermal procession are closely related.Gas turbine fires
Burn room basic function in the confined space high intensity by organizing fuel and air flow concurrently biochemical reaction, will fire
Chemical energy is converted into thermal energy in combustion gas so as to promote turbine to do work in material.Its core is turbulent mixing process and chemical reaction kinetics
The reciprocation of process.Existing combustion chamber uses swirl-flow premixed structure, and further with combustion chamber mean outlet temperature raises,
This kind of head of combustion chamber structure is limited for control combustion chamber discharged nitrous oxides effect.Compare in the world the 1990s with
Present newest combustion chamber product understands that it exports about 200 DEG C of mean temperature increase, although combustion chamber by series of optimum with
Improve, but the emission level of its nitrogen oxides maintains an equal level or even slightly raises, this illustrates that current combustion room design structure is directed to
During following more high parameter combustion chamber, its limited potential, is faced with the risk that cannot meet discharge standard.
The content of the invention
(1) technical problems to be solved
The object of the present invention is to provide a kind of gas-turbine combustion chamber head knot that can effectively reduce discharged nitrous oxides
Structure.
(2) technical solution
In order to solve the above technical problem, the present invention provides a kind of gas-turbine combustion chamber head construction, including head end
Plate, the central nozzle for being arranged on the head end plate and the multiple jet nozzle circles being looped around around the central nozzle；Appoint
Anticipate and be equipped with a swirl nozzle circle between the two neighboring jet nozzle circle；Each swirl nozzle circle includes multiple intervals
The swirl nozzle module of arrangement；The central nozzle is also a swirl nozzle module；Often enclosing the jet nozzle circle includes one
A annular jet nozzle or multiple spaced jet nozzle modules.
Wherein, the swirl nozzle module includes swirl cylinder, eddy flow cartridge and multiple swirl vanes, the eddy flow fuel
Pipe is arranged on the center of the swirl cylinder；Multiple swirl vanes are installed on the eddy flow cartridge；Each eddy flow
Blade is equipped with multiple fuel swirl holes, and the fuel swirl hole is connected with eddy flow cartridge.
Wherein, circumferential uniformly arrangement of multiple swirl vanes along the eddy flow cartridge.
Wherein, the center of the jet nozzle circle and the center of the central nozzle coincide.
Further, the jet nozzle module includes jet stream cartridge and jet stream cylinder, one end of the jet stream cylinder and institute
The connection of jet stream cartridge is stated, the other end is equipped with outlet end plate；It is equipped with inlet baffle in the jet stream cylinder, the inlet baffle is by institute
State jet stream cylinder and be separated into front chamber and rear chamber, the side wall of the front chamber is equipped with air intake；The outlet end plate is equipped with sky
Gas jet hole and fuel jet hole, the fuel jet hole are connected by small fluidic conduit with rear chamber.
Wherein, the cross section of the jet stream cylinder is rectangle, circle, sector or ellipse.
Wherein, the air intake, air jet hole and fuel jet hole are multiple.
Wherein, the diameter in the air jet hole and fuel jet hole is 1~1.5mm.
Further, the annular jet nozzle includes interior jet stream cylinder, outer jet stream cylinder and jet stream cartridge, described interior
Jet stream cylinder and outer jet stream cylinder are arranged concentrically；Jet chamber is formed between the interior jet stream cylinder and outer jet stream cylinder；It is described to penetrate
Stream chamber is equipped with front apron, middle baffle and rear baffle, forms front chamber and rear chamber；The jet stream cartridge connects with the rear chamber
It is logical；The side wall of the front chamber is equipped with air intake；The front apron is equipped with air jet hole and fuel jet hole, the combustion
Material jet hole is connected by small fluidic conduit with rear chamber.
(3) beneficial effect
Gas-turbine combustion chamber head construction provided by the invention, head of combustion chamber set multiple swirl nozzle circles and jet stream
Nozzle ring, when burning, form distributed flame, obtain the overall uniform flame of a lifting, combustion chambers burn pattern is in point
Cloth flame zone, effectively reduces the pollutant emission of whole combustion chamber.
Brief description of the drawings
Fig. 1 is the structural perspective of the embodiment of the present invention 1；
Fig. 2 is the schematic elevation view of the embodiment of the present invention 1；
Fig. 3 is the sectional view of the embodiment of the present invention 1；
Fig. 4 is the sectional view of the jet nozzle module of the embodiment of the present invention 1；
Fig. 5 is the schematic elevation view of the another embodiment of the embodiment of the present invention 1；
Fig. 6 is the schematic elevation view of the embodiment of the present invention 2；
Fig. 7 is the sectional view of the embodiment of the present invention 2.
In figure, 1：Head end plate；10：Central nozzle；20：Jet nozzle circle；30：Swirl nozzle circle；11：Swirl nozzle mould
Block；12：Jet nozzle module；110：Swirl cylinder；111：Eddy flow cartridge；112：Swirl vane；113：Fuel swirl hole；120：
Jet stream cylinder；121：Air intake；122：Jet stream cartridge；123：Inlet baffle；124：Small fluidic conduit；125：Export end plate；
126：Fuel jet hole；127：Air jet hole；128：Rear chamber；129：Front chamber；13：Annular jet module；130：Inside penetrate
Flow cylinder；131：Jet stream cartridge；132：Front apron；133：Middle baffle；134：Rear baffle；135：Air intake；136：Back cavity
Room；137：Front chamber；138：Small fluidic conduit；139：Outer jet stream cylinder；1321：Air jet hole；1322：Fuel jet hole.
Embodiment
With reference to the accompanying drawings and examples, the embodiment of the present invention is described in further detail.Following instance
For illustrating the present invention, but it is not limited to the scope of the present invention.
Embodiment 1：
Referring to figs. 1 to shown in 4, gas-turbine combustion chamber head construction of the invention, including head end plate 1, central nozzle
10th, jet nozzle circle 20 and swirl nozzle circle 30.Head end plate 1 is equipped with multiple fuel air passages, central nozzle 10, jet stream spray
Mouth circle 20 and swirl nozzle circle 30 are installed on head end plate 1, and are connected with fuel air passage, and outside leads to for fuel apparatus
Cross fuel air passage and fuel is provided.Jet nozzle circle 20 is multiple, and multiple jet nozzle circles 20 are looped around central nozzle 10 weeks
Enclose, and the center of the Center-to-Center nozzle 10 of jet nozzle circle 20 coincides.I.e. multiple jet nozzle circles 20 are arranged concentrically, in
Heart nozzle 10 is arranged on the center of innermost circle jet nozzle circle 20.One is equipped between two jet nozzle circles 20 of arbitrary neighborhood
A swirl nozzle circle 30 so that jet nozzle circle 20 and swirl nozzle circle 30 are staggered on head end plate 1, and outmost turns
Nozzle ring is jet nozzle circle 20.Each swirl nozzle circle 30 includes multiple swirl nozzle modules 11 being intervally arranged.Spray at center
Mouth 10 is also a swirl nozzle module 11.In the present embodiment, jet nozzle circle 20 includes multiple jet nozzles being intervally arranged
Module 12.
Further, swirl nozzle module 11 includes swirl cylinder 110, eddy flow cartridge 111 and multiple swirl vanes 112,
Eddy flow cartridge 111 is inserted into from the rear end of swirl cylinder 110, and is arranged on the center of swirl cylinder 110；Before eddy flow cartridge 111
End seal is closed, and rear end is used to be installed on head end plate 1.Multiple swirl vanes 112 are installed on eddy flow cartridge 111, it is preferred that
Swirl vane 112 is installed between eddy flow cartridge 111 and the inner wall of swirl cylinder 110.Each swirl vane 112 is equipped with multiple combustions
Expect whirl hole 113, fuel swirl hole 113 is connected with eddy flow cartridge 111.In the present embodiment, swirl vane 112 is 8,8
Circumferential uniformly arrangement of the swirl vane 112 along eddy flow cartridge 111.Preferably, in order to control the air stream in swirl cylinder 110
Amount, cowling panel or restriction orifice are equipped with the rear end of swirl cylinder 110.
Further, each jet nozzle module 12 includes jet stream cartridge 122 and jet stream cylinder 120.The horizontal stroke of jet stream cylinder 120
Section is circle.One end of jet stream cylinder 120 is connected with one end of jet stream cartridge 122, and the other end is equipped with outlet end plate 125.Penetrate
122 rear end of stream cartridge is connected with head end plate 1.Fuel used in the present invention is natural gas or natural gas-hydrogen mixture fuel.
Inlet baffle 123 is equipped with jet stream cylinder 120.Jet stream cylinder 120 is separated into front chamber 129 and rear chamber 128 by inlet baffle 123,
The side wall of front chamber 129 is equipped with air intake 121；Outlet end plate 125 is equipped with air jet hole 127 and fuel jet hole 126, fires
Material jet hole 126 is connected by small fluidic conduit 124 with rear chamber 128.Fuel is supplied from jet stream cartridge 122 to rear chamber 128
Enter, and projected by small fluidic conduit 124 from fuel jet hole 126, air from air intake 121 enter front chamber 129, and from
Project in air jet hole 127.Fuel injection is injected in each jet nozzle module with air and separates, it is necessary to from nozzle head
Remote position could mix, and combustion zone is reduced the cooling structure design of nozzle head away from nozzle head region, is saved
Film-cooled heat, ensures that more air can participate in burning, reduces the generation of nitrogen oxides, so as to meet greater degree combustion chamber
Demand；Fuel injection is injected in each nozzle module with air at the same time separates, and certain region is needed in nozzle module downstream
Blended, this segment distance greatly reduces the possibility that tempering occurs.In fuel, 11 fuel quantity of swirl nozzle module accounts for entirely
The 10~15% of chamber fuel amount, the eddy flow fuel ratio of whole combustion chamber is relatively low, makes the swirl mixture of whole combustion chamber
Equivalent proportion be unlikely to too high, further control pollutant emission.
Preferably, air intake 121, air jet hole 127 and fuel jet hole 126 are multiple, air jet hole 127
Diameter with fuel jet hole 126 is 1~1.5mm.
The cross section of jet stream cylinder 120 is in addition to it can be circle, acceptable sector as shown in Figure 5, alternatively, it is also possible to be
Cross section can also be rectangle or ellipse.
Using the present invention gas-turbine combustion chamber head construction when, into the partial air of combustion chamber from air intake
121 enter inside jet nozzle module 12, and exporting the air jet hole 127 on end plate 125 from jet nozzle module 12 sprays, portion
Divide fuel to enter from jet stream cartridge 122 inside jet nozzle module 12 and small penetrate is entered by the hole on fuel inlet baffle 123
Conductance pipe 124 is simultaneously projected from the fuel jet hole 126 on the outlet end plate 125 of jet nozzle module 12, and air is being penetrated with fuel
12 mixed downstream of flow nozzle module is into high-speed jet mixture；Remaining part of fuel and air enter 11 shape of swirl nozzle module
Into rotational flow air fuel mixture, act flame of lighting a fire and stablize, on the one hand its high-temperature flue gas formed is used for lighting height
Rapid fire stream mixture, is on the other hand diluted blending to high-speed jet mixture, and integral combustion room flame front is disperseed, makes combustion
Burn room combustion mode and be in distribution flame zone, reduce the generation of nitrogen oxides, effectively reduce the pollutant emission of whole combustion chamber,
Reduce the risk of thermoacoustic concussion.
Embodiment 2：
The present embodiment is substantially the same manner as Example 1, and institute's difference is, as shown in Figures 6 and 7, in the present embodiment, jet stream
Nozzle ring includes an annular jet nozzle 13.Annular jet nozzle 13 includes interior jet stream cylinder 130, outer 139 and of jet stream cylinder
Jet stream cartridge 131, interior jet stream cylinder 130 and outer jet stream cylinder 139 are arranged concentrically, and the outside diameter of interior jet stream cylinder 130 is less than outer
The internal diameter of jet stream cylinder 139, jet chamber is formed between interior jet stream cylinder 130 and outer jet stream cylinder 139, and front is equipped with jet chamber
Plate 132, middle baffle 133 and rear baffle 134, front apron 132 and middle baffle 133 are by interior jet stream cylinder 130 and outer jet stream cylinder 139
Between jet chamber be divided into front chamber 137, middle baffle 133 and rear baffle 134 are by interior jet stream cylinder 130 and outer jet stream cylinder 139
Between jet chamber be divided into rear chamber 136.The front end of jet stream cartridge 131 is connected with rear chamber 136, jet stream cartridge 131
Rear end is used to be installed on head end plate 1, is connected with the fuel air passage being arranged on head end plate 1.The side of front chamber 137
Wall is equipped with air intake 135, and with reference to shown in Fig. 7, air intake is set in interior jet stream cylinder 130 and outer jet stream cylinder 139
135, air intake 135 is connected with front chamber 137, and the air in combustion chamber is flowed into front chamber 137 by air intake 135
In, the quantity of air intake 135 is multiple, and multiple air intakes 135 are evenly distributed.Front apron 132 is equipped with air jet hole
1321 and fuel jet hole 1322, fuel jet hole 1322 connected by small fluidic conduit 138 with rear chamber 136.Fuel is from penetrating
Stream cartridge 131 flows to rear chamber 136, then by rear chamber 136 by small fluidic conduit 138 after, penetrated from fuel jet hole 1322
Go out, improve the effluxvelocity of fuel.Air is flowed into front chamber 137 from air intake 135, then the air from front apron 132
Projected in jet hole 1321.
In burning, combustion is passed through to eddy flow cartridge and jet stream cartridge respectively from the fuel air passage of head end plate
Gas.In swirl nozzle module, air is entered in swirl cylinder by the rear end of swirl cylinder, and fuel is sprayed from the fuel swirl hole of swirl vane
Go out, form stable swirl flame.Fuel enters rear chamber by jet stream cartridge, and by small fluidic conduit from fuel jet
Sprayed in hole, form the fuel injection of high speed, meanwhile, air enters front chamber from air intake, and by air jet hole at a high speed
Spray, fuel jet and air jet can just be mixed to form burning gases from jet nozzle larger distance, and light and to be formed
Jet flame.The combustion flame of annular jet nozzle from nozzle head farther out, reduces the cooling structure of nozzle head, saves cold
But area, ensures that more air participate in burning, reduces the generation of nitrogen oxides.
The gas-turbine combustion chamber head construction of the present invention, is provided with multiple swirl nozzle circles and jet nozzle circle, burns
When form distributed flame, obtain the overall uniform flame of a lifting, make combustion chambers burn pattern be in distribution flame zone, have
Effect reduces the pollutant emission of whole combustion chamber.
The foregoing is merely illustrative of the preferred embodiments of the present invention, is not intended to limit the invention, all essences in the present invention
With within principle, any modification, equivalent replacement, improvement and so on, should all be included in the protection scope of the present invention god.
Claims (6)
1. a kind of gas-turbine combustion chamber head construction, it is characterised in that including head end plate, be arranged on the head end plate
Central nozzle and the multiple jet nozzle circles being looped around around the central nozzle；The jet nozzle circle of arbitrary neighborhood two
Between be equipped with a swirl nozzle circle；Each swirl nozzle circle includes multiple swirl nozzle modules being intervally arranged；It is described
Central nozzle is also a swirl nozzle module；Often enclosing the jet nozzle circle includes an annular jet nozzle or multiple
Every the jet nozzle module of arrangement；
The swirl nozzle module includes swirl cylinder, eddy flow cartridge and multiple swirl vanes, and the eddy flow cartridge is arranged on
The center of the swirl cylinder；Multiple swirl vanes are installed on the eddy flow cartridge；Each swirl vane is equipped with
Multiple fuel swirl holes, the fuel swirl hole are connected with eddy flow cartridge；
The annular jet nozzle includes interior jet stream cylinder, outer jet stream cylinder and jet stream cartridge, the interior jet stream cylinder and outer
Jet stream cylinder is arranged concentrically；Jet chamber is formed between the interior jet stream cylinder and outer jet stream cylinder；The jet chamber is equipped with front
Plate, middle baffle and rear baffle, form front chamber and rear chamber；The jet stream cartridge is connected with the rear chamber；The ante-chamber
The side wall of room is equipped with air intake；The front apron is equipped with air jet hole and fuel jet hole, and the fuel jet hole leads to
Too small fluidic conduit is connected with rear chamber；
The jet nozzle module includes jet stream cartridge and jet stream cylinder, and one end of the jet stream cylinder connects with the jet stream cartridge
Connect, the other end is equipped with outlet end plate；Inlet baffle is equipped with the jet stream cylinder, the jet stream cylinder is separated into by the inlet baffle
Front chamber and rear chamber, the side wall of the front chamber are equipped with air intake；The outlet end plate is equipped with air jet hole and fuel
Jet hole, the fuel jet hole are connected by small fluidic conduit with rear chamber.
2. gas-turbine combustion chamber head construction as claimed in claim 1, it is characterised in that multiple swirl vanes are along institute
State the circumferential uniformly arrangement of eddy flow cartridge.
3. gas-turbine combustion chamber head construction as claimed in claim 1, it is characterised in that the center of the jet nozzle circle
Coincide with the center of the central nozzle.
4. gas-turbine combustion chamber head construction as claimed in claim 1, it is characterised in that the cross section of the jet stream cylinder is
Rectangle, circle, sector or ellipse.
5. gas-turbine combustion chamber head construction as claimed in claim 1, it is characterised in that the air intake, air are penetrated
Discharge orifice and fuel jet hole are multiple.
6. gas-turbine combustion chamber head construction as claimed in claim 1, it is characterised in that the air jet hole and fuel
The diameter of jet hole is 1~1.5mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410727617.3A CN104534515B (en) | 2014-12-03 | 2014-12-03 | Gas-turbine combustion chamber head construction |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410727617.3A CN104534515B (en) | 2014-12-03 | 2014-12-03 | Gas-turbine combustion chamber head construction |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104534515A CN104534515A (en) | 2015-04-22 |
| CN104534515B true CN104534515B (en) | 2018-04-20 |
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| CN201410727617.3A Active CN104534515B (en) | 2014-12-03 | 2014-12-03 | Gas-turbine combustion chamber head construction |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2023200479A3 (en) * | 2021-11-03 | 2023-12-14 | Power Systems Mfg., Llc | Multitube pilot injection into trapped vortices in a gas turbine engine |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110631049B (en) * | 2019-10-12 | 2020-12-11 | 中国科学院工程热物理研究所 | Gas Turbine Soft Combustor |
| CN113483358B (en) * | 2021-07-21 | 2023-02-21 | 中国联合重型燃气轮机技术有限公司 | Nozzle head for gas turbine and nozzle for gas turbine |
| CN113483359B (en) * | 2021-07-21 | 2023-02-24 | 中国联合重型燃气轮机技术有限公司 | Nozzle head for gas turbine and nozzle for gas turbine |
| CN113551263B (en) * | 2021-07-21 | 2023-02-24 | 中国联合重型燃气轮机技术有限公司 | Nozzle head for gas turbine and nozzle for gas turbine |
| CN113776084A (en) * | 2021-10-08 | 2021-12-10 | 浙江浙能技术研究院有限公司 | Integrated low-pollution combustion chamber nozzle structure and method |
| CN115095885B (en) * | 2022-06-06 | 2024-02-09 | 中国船舶集团有限公司系统工程研究院 | Combined multi-point LDI inclined combustion chamber |
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| Publication number | Publication date |
|---|---|
| CN104534515A (en) | 2015-04-22 |
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