CN104501207B - Gas-turbine combustion chamber nozzle - Google Patents
Gas-turbine combustion chamber nozzle Download PDFInfo
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- CN104501207B CN104501207B CN201410705968.4A CN201410705968A CN104501207B CN 104501207 B CN104501207 B CN 104501207B CN 201410705968 A CN201410705968 A CN 201410705968A CN 104501207 B CN104501207 B CN 104501207B
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Abstract
The present invention relates to gas turbine technology field, there is provided a kind of gas-turbine combustion chamber nozzle.The nozzle includes inlet chamber and one end is inserted in the center fuel body of inlet chamber, formed with annular air channel between center fuel body and the inwall of inlet chamber, inside is provided with the first fuel channel and air-inlet cavity, outside is provided with the air inlet structure connected with air-inlet cavity, and the air inlet of air inlet structure is relative with the airintake direction of annular air channel；The outer wall of center fuel body is provided with multiple air exhaust passages for leading to air-inlet cavity, and multiple air exhaust passages are circumferentially arranged；Multiple first fuel injection passages of first fuel passage, its top is provided with the first spray-hole for leading to the first fuel channel, the top of multiple first fuel injection passages is plugged in multiple air exhaust passages respectively, has annular gap between the first fuel injection passages and the inwall of air exhaust passage.The present invention can nebulize fuel injection, increase the mixability of fuel and air, make it advantageously in burning.
Description
Technical field
The present invention relates to gas turbine technology field, especially provides a kind of gas-turbine combustion chamber nozzle.
Background technology
In the current energy resource structure in China, most shares are occupied using the thermal power generation of traditional coal combustion technology.
But generating efficiency to be present low for this traditional generation technology, pollutant emission height (especially NOx emission), freshwater resources are expended
The shortcomings of more.Using the gas turbine power generation technology that natural gas is fuel as one of clean energy technology, generating can met
While burden requirement, the discharge of pollutant is effectively reduced, the design of gas-turbine combustion chamber nozzle is for tissue among these
Burning, reduction pollutant emission are particularly important.
In gas-turbine combustion chamber, fuel gas and air realize premixing and the change of velocity profile by nozzle, in nozzle
Outlet reaches rational VELOCITY DISTRIBUTION, and matches rational fuel-air mixture example, organizes to burn into combustion chamber, is formed steady
Fixed flow field and combustion field.Currently, to the design form of gas-turbine combustion chamber nozzle, such as have in the prior art using bottom
Notched air swirling vanes, the speed of air duct inner circumferential side is improved, match nozzle exit velocity type and fuel-air mixes
Composition and division in a proportion example.
But because air swirling vanes bottom has breach, the flow-deviation angle degree of passage inner circumferential side is small, swirl strength
It is weak, cause the mixing effect of this side fuel and air to be deteriorated；Fuel gas is in the STH spray of hollow blade two, fuel gas simultaneously
It is shorter with the blending distance of air, and the difficulty of blade processing is added, influence the generation of the tissue and pollutant of burning.Cause
This, it is still desirable to more rationally effective gas-turbine combustion chamber form of nozzle comes tissue burning and control pollutant emission.
The content of the invention
(1) technical problems to be solved
Make fuel and combustion gas wheel of the air with more preferably mixed effect the technical problem to be solved in the present invention is to provide a kind of
Machine combustion chamber burner.
(2) technical scheme
In order to solve the above technical problems, the invention provides a kind of gas-turbine combustion chamber nozzle, it is characterised in that including
Inlet chamber and one end are inserted in the center fuel body of the inlet chamber, between the center fuel body and the inwall of the inlet chamber
Formed with annular air channel, the inside of the center fuel body is provided with the first fuel channel and air-inlet cavity；
The outside of the center fuel body is provided with the air inlet structure connected with the air-inlet cavity, the opening of the air inlet structure
Direction is relative with the airintake direction of annular air channel；
Multiple air exhaust passages for leading to the air-inlet cavity are circumferentially with the outer wall of the center fuel body；
First fuel passage has multiple first fuel injection passages, the top of first fuel injection passages
Provided with the first spray-hole for leading to first fuel channel, the top of multiple first fuel injection passages is plugged in respectively
In multiple air exhaust passages, there is annular gap between first fuel injection passages and the inwall of the air exhaust passage.
Preferably, Inside To Outside of the annular gap along the center fuel body is in taper formula structure.
Preferably, the inside of the center fuel body is provided with the second fuel channel；
The outer circumference of the center fuel body is laid with multiple second fuel injection pipes, in the annular air channel
On airintake direction, second fuel injection pipe is located at the front of the air inlet structure, and the fuel injection bar, which is provided with, to lead to
Second fuel orifice of second fuel channel.
Preferably, axial rotational flow device is provided with the annular air channel, in the air inlet side of the annular air channel
Upwards, the axial rotational flow device is located at the rear of the fuel injection bar.
Preferably, the axial rotational flow device includes multiple one-level eddy flows that circumference is laid in the external side of the center fuel
Blade, the air inlet structure are the cavity body structure internally opened up out along the edge of the one-level swirl vane.
Preferably, the periphery of the center fuel body is arranged with blocker ring, the position of the blocker ring and the described first combustion
Expect that the position of injection channel is relative, there is gap between the blocker ring and the center fuel body.
Preferably, first fuel injection passages are located at the center of the blocker ring axial length.
Preferably, the blocker ring is fixed on the inwall of the inlet chamber by multiple two level swirl vanes.
Preferably, first fuel channel is fuel gallery.
Preferably, second fuel channel is natural gas passage.
(3) beneficial effect
The invention provides a kind of gas-turbine combustion chamber nozzle, including inlet chamber and one end to be inserted in the center of inlet chamber
Fuel body, formed with annular air channel between center fuel body and the inwall of inlet chamber, the inside of center fuel body is provided with the
One fuel channel and air-inlet cavity；The outside of center fuel body is provided with the air inlet structure that is connected with air-inlet cavity, air inlet structure include into
Air port, air inlet are relative with the airintake direction of annular air channel；The outer wall of center fuel body leads to air-inlet cavity provided with multiple
Air exhaust passage, multiple air exhaust passages are circumferentially arranged along center fuel body；The multiple first fuel sprays of first fuel passage
Passage is penetrated, the top of the first fuel injection passages is provided with the first spray-hole for leading to the first fuel channel, multiple first fuel sprays
The top for penetrating passage is plugged in multiple air exhaust passages respectively, is had between the first fuel injection passages and the inwall of air exhaust passage
Annular gap.The present invention can nebulize fuel injection, increase the mixability of fuel and air, make it advantageously in combustion
Burn.
Brief description of the drawings
Fig. 1 is a kind of sectional view of gas-turbine combustion chamber nozzle of the embodiment of the present invention；
Fig. 2 is a kind of 3-D view of gas-turbine combustion chamber nozzle of the embodiment of the present invention.
Fig. 3 is the structural representation of the air-inlet cavity of the embodiment of the present invention.
Reference：
1st, center fuel body；2nd, annular air channel；3rd, the second fuel channel；4th, the first fuel channel；5th, the second fuel
Spray-hole；6th, one-level swirl vane；7th, the second fuel injection pipe；8th, the first fuel injection passages；9th, blocker ring；10th, radially receive
Contracting section；11st, air inlet structure；12nd, air exhaust passage；13rd, rectification section；14th, outer tube；15th, inner tube；16th, annular gap；17th, air-inlet cavity；
18th, demarcation strip；19th, two level swirl vane.
Embodiment
With reference to the accompanying drawings and examples, the embodiment of the present invention is described in further detail.Implement below
Example is used to illustrate the present invention, but is not limited to the scope of the present invention.
In the description of the invention, it is necessary to which explanation, unless otherwise clearly defined and limited, term " connection " should be done
It broadly understood, for example, it may be being fixedly connected or being detachably connected, or be integrally connected；Can be joined directly together,
It can also be indirectly connected by intermediary.For the ordinary skill in the art, can be understood with concrete condition above-mentioned
The concrete meaning of term in the present invention.
With reference to shown in Fig. 1 and Fig. 2, the embodiments of the invention provide a kind of gas-turbine combustion chamber nozzle, including inlet chamber
The center fuel body 1 of inlet chamber is inserted in one end, one end of inlet chamber has air inlet, and center fuel body 1 is by the air inlet
Insertion, is led between center fuel body 1 and the inwall of inlet chamber formed with annular air channel 2, air by the air inlet of inlet chamber
Enter into annular air channel 2.
Center fuel body 1 includes inner tube 15, outer tube 14 and demarcation strip 18, and inner tube 15 is arranged on the inside of outer tube 14, interior
One end of pipe 15 and outer tube 14 is equipped with opening, and one end that inner tube 15 and outer tube 14 have opening is consolidated by nozzle suspension flange
It is fixed；The inner space of inner tube 15 can be passed through a kind of fuel formed with the first fuel channel 4 by the openend of inner tube 15；Separate
Plate 18 is annular, is connected between inner tube 15 and outer tube 14, the space between inner tube 15 and outer tube 14 is separated into two parts, point
Dividing plate 18 to a part of space of the opening of outer tube 14 as the second fuel channel 3, available for being passed through another fuel；Demarcation strip
18 to outer tube 14 the other end as air-inlet cavity 17.
The outer circumference of center fuel body 1 is laid with multiple second fuel injection pipes 7, and fuel injection pipe, which is provided with, leads to the
Second fuel orifice 5 of two fuel channels 3, the quantity of the second fuel orifice 5 is multiple, in entering for annular air channel 2
On gas direction, multiple second fuel orifices 5 are arranged at the different height of the both sides of the second fuel injection pipe 7, and fuel passes through
After multiple second playpipes spray, it can be formed and mixed with the air in whole annular air channel 2；In second fuel channel 3
Fuel suitably from the fuel for being easy to gasification, in the present embodiment, natural gas can be selected in fuel in the second fuel channel 3.
In conjunction with shown in Fig. 3, the outside of center fuel body 1 is provided with the air inlet structure 11 connected with air-inlet cavity 17, air intake knot
Structure 11 is a cavity body structure, and the side of air inlet structure 11 has air inlet, air inlet and the airintake direction phase of annular air channel 2
Right, when air enters along annular air channel 2 fashionable, the inside cavity of air inlet structure 11 forms blast, due to air inlet structure 11 with
Air-inlet cavity 17 is connected, and the air in air inlet structure 11 is pressed into air-inlet cavity 17, and then the air pressure rise in air-inlet cavity 17；In
Circumference is laid with multiple first fuel injection passages 8 on the outer wall of heart fuel body 1, multiple first fuel injection passages 8 respectively with
First fuel channel 4 connects, and on the airintake direction of annular air channel 2, multiple first fuel injection passages 8 are positioned at multiple the
The rear of two fuel injection pipes 7.
The outer wall of center fuel body 1 is provided with multiple air exhaust passages 12 for leading to air-inlet cavity 17, multiple edges of air exhaust passage 12
The circumferential uniformly arrangement of center fuel body 1；Pressure-air in air-inlet cavity 17 is ejected into annular air channel 2 by air exhaust passage 12
In.First fuel injection passages 8 are limited by multiple first fuel injection pipes being distributed in the external circumferential of the first fuel channel 4, the
The top of one fuel injection passages 8 is provided with the first spray-hole for leading to the first fuel channel 4, multiple first fuel injection passages 8
Circumference is laid in the outside of the first fuel channel 4, the positions of multiple first fuel injection passages 8 respectively with multiple air exhaust passages 12
Relatively；The top of multiple first fuel injection passages 8 is plugged in multiple air exhaust passages 12 respectively, in the first fuel injection passages
Annular gap 16 is formed between 8 and the inwall of air exhaust passage 12, the annular gap 16 is used to spray the pressure-air in inlet chamber
Go out.After the fuel in the first fuel channel 4 is sprayed by the first spray-hole, fuel is dispelled mist formation by the gases at high pressure around fuel
Shape, fuel is set to be sufficiently mixed with air；First fuel channel 4 is suitable to be passed through the fuel for being not easy to gasify, first combustion of the present embodiment
Expect the Fuel Selection fuel oil in passage 4.
Preferably, along center fuel body 1 Inside To Outside direction, above-mentioned annular gap 16 gradually to contract, by
Being plugged in the first fuel injection passages 8 in air exhaust passage 12, i.e., the first fuel injection passages 8 do not wear out air exhaust passage 12,
Ring-type pressure-air is so ejected from annular gap 16 inside convection current is formed in the top of the first spray-hole, in the convection current
In the presence of, the fuel oil that is sprayed in the first spray-hole formed it is more fine and closely woven vaporific, advantageously in the uniform of fuel oil and air
Mixing.
The also settable axial rotational flow device in annular air channel 2, on the airintake direction of annular air channel 2, axle
To swirl-flow devices between multiple second fuel injection pipes 7 and multiple first fuel injection passages, axial rotational flow device can be with
The gas for making to pass through forms eddy flow, can improve the mixability of the natural gas ejected in the second fuel injection pipe 7 and air.
Preferably, one-level swirl vane 6 is arranged to hollow structure, the opening in one-level swirl vane 6 towards inlet chamber
Side open up air inlet, the air inlet structure 11 is the cavity body structure internally opened up out along the edge of one-level swirl vane 6；
It can make each one-level swirl vane 6 that an air inlet structure 11 is set, to increase air inflow, make to reach enough pressures in air-inlet cavity 17
Power with ensure by fuel oil blow out fine mist.
It should be noted that in the solution of the present invention, need to only accomplish to spray the fuel such as the fuel oil in the first fuel channel 4
Penetrate and nebulize, the functional structure form is realized in this programme and is limited in by above-mentioned air inlet structure 11, air-inlet cavity incessantly
17th, the fuel injection passages 8 of air exhaust passage 12 and first, can also be other spray structures, in the air inlet of annular air channel 2
On direction, and positioned at the rear of the second fuel injection pipe 7, only need on the outer wall of center fuel body 1 circumference lay it is multiple with the
Two fuel channels 3 connection the first fuel injection passages, the first fuel injection passages can select ultrasonic wave atomizing nozzle,
High-frequency vibration atomizing nozzle, or other structures that can spray.
Preferably, blocker ring 9 is covered with the periphery of multiple air exhaust passages 12, blocker ring 9 is centrally disposed combustion
Expect the cyclic structure between body 1 and the inwall of inlet chamber, stop for being formed to the vaporific fuel oil ejected in air exhaust passage 12,
There is gap, on the axial direction of center fuel body 1, the first fuel injection is led between blocker ring 9 and the center fuel body 1
Road is preferably placed at the center of the axial length of blocker ring 9, on the one hand fuel oil can be prevented to be ejected on the inwall of inlet chamber, in addition
On the one hand fuel vapor can also be made to be distributed near the axis of inlet chamber, the outer shroud of inlet chamber is then mainly distributed natural gas, this
For sample when fuel gas flow is subsequently implanted into combustion chamber, fuel oil-gas is injected into the center of combustion chamber just, and natural gas is then placed in
The edge of combustion chamber, different fuel collocation modes is selected under different loads, can be with alternative under specific operating mode
From two kinds of fuel, the distribution of two groups of fuel in a combustion chamber can be adjusted, combustion efficiency is reached more preferably.
Preferably, blocker ring 9 is fixed on the inwall of inlet chamber by multiple two level swirl vanes 19, two level swirl vane
19 can be such that the natural gas positioned at inlet chamber outer shroud is further mixed with air；On the axial direction of center fuel body 1, Duo Geyi
Level swirl vane 6 may be arranged as the position staggered relative with multiple two level swirl vanes 19, so make each two level eddy flow
The interval between each one-level swirl vane 6 respectively in the axial direction of blade 19, each two level swirl vane 19 can be right
Each mixed gas by the first swirl vane forms shunting, can improve the composite rate of fuel and air to a certain extent；
The quantity of one-level swirl vane 6 and two level swirl vane 19 elects 4~6 as, so will not both hinder the patency of air-flow, again
Good mixed effect is not lost.
Preferably, center fuel body 1 be inserted into inlet chamber one end it is tapered；The tapered center fuel body 1 of tail end
Profile is smooth, and gaseous mixture will not form vortex when flowing through the tail end of center fuel body 1, so as to will not to fuel oil air-flow and naturally
The distribution of gas air-flow causes to disturb, while also makes the circulation of gaseous mixture more unobstructed.
Preferably, inlet chamber is provided with a radial contraction section 10, on the airintake direction of annular air channel 2, radially receives
Contracting section 10 is located at the rear of multiple second swirl vanes, and radial contraction section 10 makes the body of air and fuel gas to a certain extent
Contracting is overstock, the fuel of unit volume and the concentration of oxygen is increased, thermal efficiency during burning can be improved.
In addition, inlet chamber also includes a rectification section 13, on the airintake direction of annular air channel 2, rectification section 13 is located at
The rear of radial contraction section 10, caused eddy flow is put down when fuel gas is passed through into one-level eddy flow leaf and two level swirl vane 19
It is multiple, smooth air-flow is formed, subsequently enters in combustion chamber and is advantageous to burn.
Described above is only the preferred embodiment of the present invention, it is noted that for the ordinary skill people of the art
For member, without departing from the technical principles of the invention, some improvement and replacement can also be made, these improve and replaced
Also it should be regarded as protection scope of the present invention.
Claims (10)
1. a kind of gas-turbine combustion chamber nozzle, it is characterised in that be inserted in including inlet chamber and one end in the inlet chamber
Heart fuel body (1), it is described formed with annular air channel (2) between the center fuel body (1) and the inwall of the inlet chamber
The inside of center fuel body (1) is provided with the first fuel channel (4) and air-inlet cavity (17)；
The outside of the center fuel body (1) is provided with the air inlet structure (11) connected with the air-inlet cavity (17), the air intake knot
The opening direction of structure is relative with the airintake direction of the annular air channel (2)；
Multiple air exhaust passages (12) for leading to the air-inlet cavity (17) are circumferentially with the outer wall of the center fuel body (1)；
First fuel channel (4) is communicated with multiple first fuel injection passages (8), first fuel injection passages (8)
Top be provided with and lead to the first spray-hole of first fuel channel (4), the top of multiple first fuel injection passages (8)
Portion is plugged in multiple air exhaust passages (12) respectively, first fuel injection passages (8) and the air exhaust passage (12)
Inwall between there are annular gap (16).
2. gas-turbine combustion chamber nozzle according to claim 1, it is characterised in that the annular gap is along the center
The Inside To Outside of fuel body (1) is in taper formula structure.
3. gas-turbine combustion chamber nozzle according to claim 1 or 2, it is characterised in that the center fuel body (1)
Inside is provided with the second fuel channel (3)；
The outer circumference of the center fuel body (1) is laid with multiple second fuel injection pipes (7), in the annular air channel
(2) on airintake direction, second fuel injection pipe (7) is located at the front of the air inlet structure (11), the fuel injection
Bar is provided with the second fuel orifice (5) for leading to second fuel channel (3).
4. gas-turbine combustion chamber nozzle according to claim 3, it is characterised in that in the annular air channel (2)
Provided with axial rotational flow device, on the airintake direction of the annular air channel (2), the axial rotational flow device is located at the combustion
Expect the rear of jet rod.
5. gas-turbine combustion chamber nozzle according to claim 4, it is characterised in that the axial rotational flow device includes circle
The multiple one-level swirl vanes (6) being laid in week on the outside of the center fuel body (1), the air inlet structure (11) are along described one
The cavity body structure that the edge of level swirl vane (6) internally opens up out.
6. gas-turbine combustion chamber nozzle according to claim 3, it is characterised in that outside the center fuel body (1)
Enclose and be arranged with blocker ring (9), the position of the blocker ring (9) is relative with the position of first fuel injection passages (8), described
There is gap between blocker ring (9) and the center fuel body (1).
7. gas-turbine combustion chamber nozzle according to claim 6, it is characterised in that first fuel injection passages
(8) it is located at the center of the blocker ring (9) axial length.
8. gas-turbine combustion chamber nozzle according to claim 6, it is characterised in that the blocker ring (9) is by multiple
Two level swirl vane is fixed on the inwall of the inlet chamber.
9. gas-turbine combustion chamber nozzle according to claim 1, it is characterised in that first fuel channel (4) is
Fuel gallery.
10. gas-turbine combustion chamber nozzle according to claim 1, it is characterised in that second fuel channel (3) is
Natural gas passage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410705968.4A CN104501207B (en) | 2014-11-27 | 2014-11-27 | Gas-turbine combustion chamber nozzle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410705968.4A CN104501207B (en) | 2014-11-27 | 2014-11-27 | Gas-turbine combustion chamber nozzle |
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| Publication Number | Publication Date |
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| CN104501207A CN104501207A (en) | 2015-04-08 |
| CN104501207B true CN104501207B (en) | 2018-03-06 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201410705968.4A Active CN104501207B (en) | 2014-11-27 | 2014-11-27 | Gas-turbine combustion chamber nozzle |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2769773C2 (en) * | 2018-12-25 | 2022-04-05 | Ансальдо Энергия Свитзерленд Аг | Modular injection head for the combustion chamber of a gas turbine |
| CN117419337B (en) * | 2023-11-10 | 2024-07-26 | 中国矿业大学 | Gas pulsation burner with fire stabilizing device |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0935097B1 (en) * | 1998-02-09 | 2004-09-01 | Mitsubishi Heavy Industries, Ltd. | Combustor |
| JP4476176B2 (en) * | 2005-06-06 | 2010-06-09 | 三菱重工業株式会社 | Gas turbine premixed combustion burner |
| JP4719059B2 (en) * | 2006-04-14 | 2011-07-06 | 三菱重工業株式会社 | Gas turbine premixed combustion burner |
| CN103672969B (en) * | 2013-12-13 | 2017-09-15 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | A kind of gas turbine dual-fuel combustion chamber nozzle of combustion |
| CN104110699B (en) * | 2014-07-09 | 2017-09-15 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | A kind of pre-mixing nozzle of gas-turbine combustion chamber |
| CN204438188U (en) * | 2014-11-27 | 2015-07-01 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Gas-turbine combustion chamber nozzle |
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Effective date of registration: 20200116 Address after: 102209 Beijing Changping District in the future of the national electric investment group Park in the future science city south of Beijing Patentee after: China United heavy-duty gas turbine technology Co., Ltd. Address before: 100084, Beijing, Haidian District science and Technology Park, Tsinghua Science and technology building, block C, 10 Patentee before: Beijing Huatsing Gas Turbine & IGCC Technology Co., Ltd. |
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