CN204313313U - Gas-turbine combustion chamber nozzle - Google Patents
Gas-turbine combustion chamber nozzle Download PDFInfo
- Publication number
- CN204313313U CN204313313U CN201420735547.1U CN201420735547U CN204313313U CN 204313313 U CN204313313 U CN 204313313U CN 201420735547 U CN201420735547 U CN 201420735547U CN 204313313 U CN204313313 U CN 204313313U
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- Prior art keywords
- fuel
- fuel injection
- channel
- gas
- combustion chamber
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Abstract
The utility model relates to combustion engine turbine technical field, provides a kind of gas-turbine combustion chamber nozzle.This nozzle comprises the center fuel body that inlet chamber and one end are inserted in inlet chamber, annular air channel is formed between center fuel body and the inwall of inlet chamber, the inside of center fuel body is provided with the first fuel channel and the second fuel channel, and all sides are provided with multiple second fuel injection pipe; On the outer wall of center fuel body, circumference is laid with multiple the first fuel injection passages be communicated with the first fuel channel, and the first fuel injection passages is positioned at the rear of the first fuel injection passages; The periphery of multiple first fuel injection passages is covered with catch ring.The fuel distribution that catch ring makes the first fuel channel eject is in the inner side of inlet chamber, the fuel that second fuel channel ejects mainly is distributed in the outside of inlet chamber, different fuel collocation modes can be selected thus under different loads, can be substituting under specific operating mode select two kinds of fuel, make combustion efficiency reach better.
Description
Technical field
The utility model relates to gas turbine technology field, provides a kind of gas-turbine combustion chamber nozzle especially.
Background technology
In the energy resource structure that China is current, the thermal power generation of traditional coal combustion technology is adopted to occupy most share.But it is low that this traditional generation technology exists generating efficiency, pollutant emission high (especially NOx emission), expends the shortcomings such as freshwater resources are many.Be that the gas turbine power generation technology of fuel is as one of clean energy technology with natural gas, can while meeting generation load requirement, effectively reduce the discharge of pollutant, this wherein gas-turbine combustion chamber nozzle design for tissue burning, reduce pollutant emission particularly important.
In gas-turbine combustion chamber, fuel gas and air realize the change of premixed and velocity profile by nozzle, reach rational VELOCITY DISTRIBUTION at jet expansion, and mate rational fuel-air mixture example, enter combustion chamber tissue burning, form stable flow field and combustion field.Current, to the design form of gas-turbine combustion chamber nozzle, such as, have in prior art and adopt the notched air swirling vanes in bottom, improve the speed of air duct inner circumferential side, coupling nozzle exit velocity type and fuel-air mixture example.
But owing to there is breach bottom air swirling vanes, the air flow deflector angle of passage inner circumferential side is little, and swirl strength is weak, the mixing effect of this side fuel and air is caused to be deteriorated; Fuel gas is in the spray of hollow blade two STH simultaneously, and the blending distance of fuel gas and air is shorter, and adds the difficulty of blade processing, the tissue of impact burning and the generation of pollutant.Therefore, more rationally effective gas-turbine combustion chamber form of nozzle is still needed to organize burning and control polluted articles discharge.
Utility model content
(1) technical problem that will solve
The technical problems to be solved in the utility model is to provide a kind of gas-turbine combustion chamber nozzle can optimizing fuel distribution form.
(2) technical scheme
For solving the problems of the technologies described above, the utility model provides a kind of gas-turbine combustion chamber nozzle, comprise the center fuel body that inlet chamber and one end are inserted in described inlet chamber, be formed with annular air channel between described center fuel body and the inwall of described inlet chamber, the inside of described center fuel body is provided with the first fuel channel and the second fuel channel;
The external circumferential of described center fuel body is provided with multiple second fuel injection pipe, and the outer wall of described second fuel injection pipe is provided with the second fuel orifice leading to described second fuel channel;
On the outer wall of described center fuel body, circumference is laid with multiple first fuel injection passages, multiple described first fuel injection passages is communicated with described first fuel channel respectively, on the airintake direction of described annular air channel, described first fuel injection passages is positioned at the rear of described second fuel injection pipe;
The outer race of described center fuel body is provided with catch ring, and the position of described catch ring is relative with the position of described first fuel injection passages, has gap between described catch ring and described center fuel body.
Preferably, in the outside of described center fuel body, and be provided with multiple one-level swirl vane between multiple described second fuel injection pipe and multiple described first fuel injection passages.
Preferably, described catch ring is connected on the inwall of described inlet chamber by multiple secondary swirl vane.
Preferably, be provided with axial rotational flow device in described annular air channel, on the airintake direction of described annular air channel, described axial rotational flow device is between multiple described second fuel injection pipe and multiple described first fuel injection passages.
Preferably, described second fuel channel is fuel gallery.
Preferably, described first fuel channel is natural gas passage.
Preferably, described center fuel body one end of being inserted into described inlet chamber is tapered.
Preferably, described first fuel injection passages is positioned at the center of described catch ring axial length.
Preferably, described inlet chamber is provided with a radial contraction section, and on the airintake direction of described annular air channel, described radial contraction section is positioned at the rear of multiple described first fuel injection passages.
Preferably, described inlet chamber also comprises a rectification section, and on the airintake direction of described annular air channel, described rectification section is positioned at the rear of described radial contraction section.
(3) beneficial effect
The utility model provides a kind of gas-turbine combustion chamber nozzle, comprise the center fuel body that inlet chamber and one end are inserted in inlet chamber, be 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 first fuel channel and the second fuel channel; All sides of center fuel body are provided with multiple second fuel injection pipe, and the outer wall of the second fuel injection pipe is provided with the second fuel orifice leading to the second fuel channel; On the outer wall of center fuel body, circumference is laid with multiple first fuel injection passages, multiple first fuel injection passages is communicated with the first fuel channel respectively, on the airintake direction of annular air channel, multiple first fuel injection passages is positioned at the rear of multiple first fuel injection passages; The periphery of multiple first fuel injection passages is covered with catch ring.By the stop of catch ring, the fuel distribution that first fuel channel ejects is in the inner side of inlet chamber, the follow-up center being injected into combustion chamber, the fuel that second fuel channel ejects mainly is distributed in the outside of inlet chamber, the follow-up edge being injected into combustion chamber, can select different fuel collocation modes thus under different loads, can be substituting under specific operating mode select two kinds of fuel, two groups of fuel distributions in a combustion chamber can be adjusted, make combustion efficiency reach better.
Accompanying drawing explanation
Fig. 1 is the sectional view of a kind of gas-turbine combustion chamber nozzle of the utility model embodiment;
Fig. 2 is the 3-D view of a kind of gas-turbine combustion chamber nozzle of the utility model embodiment.
Fig. 3 is the structural representation of the air-inlet cavity of the utility model embodiment.
Reference numeral:
1, center fuel body; 2, annular air channel; 3, the second fuel channel; 4, the first fuel channel; 5, the second fuel orifice; 6, one-level swirl vane; 7, the second fuel injection pipe; 8, the first fuel injection passages; 9, catch ring; 10, radial contraction section; 11, air inlet structure; 12, air exhaust passage; 13, rectification section; 14, outer tube; 15, interior pipe; 16, annular gap; 17, air-inlet cavity; 18, demarcation strip; 19, secondary swirl vane.
Detailed description of the invention
Below in conjunction with drawings and Examples, detailed description of the invention of the present utility model is described in further detail.Following examples for illustration of the utility model, but are not used for limiting scope of the present utility model.
In description of the present utility model, it should be noted that, unless otherwise clearly defined and limited, term " connection " should be interpreted broadly, and such as, can be fixedly connected with, also can be removably connect, or connect integratedly; Can be directly be connected, also indirectly can be connected by intermediary.For the ordinary skill in the art, concrete condition the concrete meaning of above-mentioned term in the utility model can be understood.
Shown in composition graphs 1 and Fig. 2, the utility model embodiment provides a kind of gas-turbine combustion chamber nozzle, comprise the center fuel body 1 that inlet chamber and one end are inserted in inlet chamber, one end of inlet chamber has air inlet, center fuel body 1 is inserted by this air inlet, be formed with annular air channel 2 between center fuel body 1 and the inwall of inlet chamber, air is passed in annular air channel 2 by the air inlet of inlet chamber.
Center fuel body 1 comprises interior pipe 15, outer tube 14 and demarcation strip 18, and interior pipe 15 is arranged on the inside of outer tube 14, and one end of interior pipe 15 and outer tube 14 is equipped with opening, and one end that interior pipe 15 and outer tube 14 have opening is fixed by nozzle suspension flange; The inner space of interior pipe 15 is formed with the first fuel channel 4, and the openend by interior pipe 15 passes into a kind of fuel; Demarcation strip 18 is annular, and be connected between interior pipe 15 and outer tube 14, the space between interior pipe 15 and outer tube 14 is separated into two parts, a part of space of the opening of demarcation strip 18 to outer tube 14, as the second fuel channel 3, can be used for passing into another kind of fuel; The other end of demarcation strip 18 to outer tube 14 is as air-inlet cavity 17.
The outer circumference of center fuel body 1 is laid with multiple second fuel injection pipe 7, fuel injection pipe is provided with the second fuel orifice 5 leading to the second fuel channel 3, the quantity of the second fuel orifice 5 is multiple, on the airintake direction of annular air channel 2, multiple second fuel orifices 5 are arranged on the differing heights place of the both sides of the second fuel injection pipe 7, fuel, by after multiple second playpipe ejection, can be formed with the air in whole annular air channel 2 and mix; Fuel in second fuel channel 3 is suitable for selecting the fuel being easy to gasify, and in the present embodiment, the fuel in the second fuel channel 3 can select natural gas.
Again shown in composition graphs 3, the outside of center fuel body 1 is provided with the air inlet structure 11 be communicated with air-inlet cavity 17, air inlet structure 11 is a cavity body structure, the side of air inlet structure 11 has air inlet, and air inlet is relative with the airintake direction of annular air channel 2, when annularly air duct 2 enters air, the inside cavity of air inlet structure 11 forms blast, because air inlet structure 11 is communicated with air-inlet cavity 17, the air in air inlet structure 11 is pressed in air-inlet cavity 17, and then the air pressure in air-inlet cavity 17 raises; On the outer wall of center fuel body 1, circumference is laid with multiple first fuel injection passages 8, multiple first fuel injection passages 8 is communicated with the first fuel channel 4 respectively, on the airintake direction of annular air channel 2, multiple first fuel injection passages 8 is positioned at the rear of multiple second fuel injection pipe 7.
The outer wall of center fuel body 1 is provided with multiple air exhaust passage 12 leading to air-inlet cavity 17, and the circumference of multiple air exhaust passage 12 centrally fuel body 1 is evenly arranged; Pressure-air in air-inlet cavity 17 is ejected in annular air channel 2 by air exhaust passage 12.First fuel injection passages 8 is limited by multiple first fuel injection pipes distributed in the first fuel channel 4 external circumferential, the top of the first fuel injection passages 8 is provided with the first spray-hole leading to the first fuel channel 4, multiple first fuel injection passages 8 circumference are laid in the outside of the first fuel channel 4, and the position of multiple first fuel injection passages 8 is relative with multiple air exhaust passage 12 respectively; The top of multiple first fuel injection passages 8 is plugged in multiple air exhaust passage 12 respectively, between the first fuel injection passages 8 and the inwall of air exhaust passage 12, form annular gap 16, and this annular gap 16 sprays for making the pressure-air in inlet chamber.After the fuel in the first fuel channel 4 is sprayed by the first spray-hole, fuel dispels and nebulizes by the gases at high pressure around fuel, and fuel is fully mixed with air; First fuel channel 4 is suitable for passing into the fuel not easily gasified, the Fuel Selection fuel oil in first fuel channel 4 of the present embodiment.
Preferably, the centrally direction of the Inside To Outside of fuel body 1, above-mentioned annular gap 16 is inwardly shunk gradually, because the first fuel injection passages 8 is plugged in air exhaust passage 12, namely the first fuel injection passages 8 does not wear out air exhaust passage 12, from annular gap 16, eject ring-type pressure-air like this form inside convection current above the first spray-hole, under the effect of this convection current, the fuel oil that sprays in first spray-hole is formed more fine and closely woven vaporific, advantageously in the Homogeneous phase mixing of fuel oil and air.
In annular air channel 2, also can axial rotational flow device be set, on the airintake direction of annular air channel 2, axial rotational flow device is between multiple second fuel injection pipe 7 and multiple first fuel injection passages, axial rotational flow device can make the gas passed through form eddy flow, can improve the mixability of natural gas and the air ejected in the second fuel injection pipe 7.
Preferably, one-level swirl vane 6 is set to hollow structure, offers air inlet at one-level swirl vane 6 towards the side of the opening of inlet chamber, described air inlet structure 11 is the cavity body structure internally set out along the edge of one-level swirl vane 6; Can make each one-level swirl vane 6 that an air inlet structure 11 is set, to increase air inflow, make to reach in air-inlet cavity 17 enough pressure, with guarantee, fuel oil is blown out fine mist.
Should be noted that, in scheme of the present utility model, only the fuel such as the fuel oil in the first fuel channel 4 need be accomplished to be injected into vaporific, realize this functional structure form in this programme and be incessantly limited in by above-mentioned air inlet structure 11, air-inlet cavity 17, air exhaust passage 12 and the first fuel injection passages 8, can also be other spray structures, on the airintake direction of annular air channel 2, and be positioned at the rear of the second fuel injection pipe 7, only on the outer wall of center fuel body 1, multiple the first fuel injection passages be communicated with the second fuel channel 3 need be laid by circumference, first fuel injection passages can select ultrasonic wave atomizing nozzle, high-frequency vibration atomizing nozzle, or other structures that can spray.
Preferably, catch ring 9 is covered with in the periphery of multiple described air exhaust passage 12, catch ring 9 is for being arranged on the circulus between center fuel body 1 and the inwall of inlet chamber, stop for being formed the vaporific fuel oil ejected in air exhaust passage 12, between catch ring 9 and described center fuel body 1, there is gap, on the axial direction of center fuel body 1, first fuel injection passages is preferably placed at the center of catch ring 9 axial length, oil burning jet can be prevented to be mapped on the inwall of inlet chamber on the one hand, fuel vapor can also be made to be distributed near the axis of inlet chamber on the one hand in addition, the outer shroud of inlet chamber then mainly distributes natural gas, like this when fuel gas flow is follow-up be injected in combustion chamber time, fuel oil-gas is injected into the center of combustion chamber just, natural gas is then placed in the edge of combustion chamber, different fuel collocation modes is selected under different loads, can be substituting under specific operating mode select two kinds of fuel, two groups of fuel distributions in a combustion chamber can be adjusted, combustion efficiency is made to reach better.
Preferably, catch ring 9 is fixed on the inwall of inlet chamber by multiple secondary swirl vane 19, and secondary swirl vane 19 can make the natural gas being positioned at inlet chamber outer shroud mix further with air; On the axial direction of center fuel body 1, multiple one-level swirl vane 6 can also be set to the position staggered relative with multiple secondary swirl vane 19, each secondary swirl vane 19 is made to lay respectively at interval between each one-level swirl vane 6 in the axial direction like this, each secondary swirl vane 19 can form shunting to each mist through the first swirl vane, can improve the composite rate of fuel and air to a certain extent; The quantity of one-level swirl vane 6 and secondary swirl vane 19 all elects 4 ~ 6 as, so both can not hinder the patency of air-flow, does not lose good mixed effect again.
Preferably, to be inserted into one end of inlet chamber tapered for center fuel body 1; The profile of the center fuel body 1 that tail end is tapered is smooth, and gaseous mixture can not form eddy current when flowing through the tail end of center fuel body 1, thus can not cause disturbance to the distribution of fuel oil air-flow and gas flow, also makes the circulation of gaseous mixture more unobstructed simultaneously.
Preferably, inlet chamber is provided with a radial contraction section 10, on the airintake direction of annular air channel 2, radial contraction section 10 is positioned at the rear of multiple second swirl vane, radial contraction section 10 makes the volume of air and fuel gas compress to a certain extent, increase the fuel of unit volume and the concentration of oxygen, thermal efficiency during burning can be improved.
In addition, inlet chamber also comprises a rectification section 13, on the airintake direction of annular air channel 2, rectification section 13 is positioned at the rear of radial contraction section 10, the eddy flow produced when the one-level eddy flow leaf and secondary swirl vane 19 by fuel gas calms down, form level and smooth air-flow, the follow-up combustion chamber that enters into is conducive to burning.
The above is only preferred embodiment of the present utility model; should be understood that; for those skilled in the art; under the prerequisite not departing from the utility model know-why; can also make some improvement and replacement, these improve and replace and also should be considered as protection domain of the present utility model.
Claims (10)
1. a gas-turbine combustion chamber nozzle, it is characterized in that, comprise the center fuel body (1) that inlet chamber and one end are inserted in described inlet chamber, be formed with annular air channel (2) between described center fuel body (1) and the inwall of described inlet chamber, the inside of described center fuel body (1) is provided with the first fuel channel (4) and the second fuel channel (3);
The external circumferential of described center fuel body (1) is provided with multiple second fuel injection pipe (7), and the outer wall of described second fuel injection pipe (7) is provided with the second fuel orifice (5) leading to described second fuel channel (3);
On the outer wall of described center fuel body (1), circumference is laid with multiple first fuel injection passages (8), multiple described first fuel injection passages (8) is communicated with described first fuel channel (4) respectively, on the airintake direction of described annular air channel (2), described first fuel injection passages (8) is positioned at the rear of described second fuel injection pipe (7);
The outer race of described center fuel body (1) is provided with catch ring (9), the position of described catch ring (9) is relative with the position of described first fuel injection passages (8), has gap between described catch ring (9) and described center fuel body (1).
2. gas-turbine combustion chamber nozzle according to claim 1, it is characterized in that, in the outside of described center fuel body (1), and be positioned between multiple described second fuel injection pipe (7) and multiple described first fuel injection passages (8) and be provided with multiple one-level swirl vane (6).
3. gas-turbine combustion chamber nozzle according to claim 1, is characterized in that, described catch ring (9) is connected on the inwall of described inlet chamber by multiple secondary swirl vane (19).
4. gas-turbine combustion chamber nozzle according to claim 1, it is characterized in that, described annular air channel is provided with axial rotational flow device in (2), on the airintake direction of described annular air channel (2), described axial rotational flow device is positioned between multiple described second fuel injection pipe (7) and multiple described first fuel injection passages (8).
5. gas-turbine combustion chamber nozzle according to claim 1, is characterized in that, described second fuel channel (3) is fuel gallery.
6. gas-turbine combustion chamber nozzle according to claim 1, is characterized in that, described first fuel channel (4) is natural gas passage.
7. gas-turbine combustion chamber nozzle according to claim 1, is characterized in that, one end that described center fuel body (1) is inserted into described inlet chamber is tapered.
8. gas-turbine combustion chamber nozzle according to claim 1, is characterized in that, described first fuel injection passages (8) is positioned at the center of described catch ring (9) axial length.
9. the gas-turbine combustion chamber nozzle according to any one of claim 1-8, it is characterized in that, described inlet chamber is provided with a radial contraction section (10), on the airintake direction of described annular air channel (2), described radial contraction section (10) is positioned at the rear of multiple described first fuel injection passages (8).
10. gas-turbine combustion chamber nozzle according to claim 9, it is characterized in that, described inlet chamber also comprises a rectification section (13), on the airintake direction of described annular air channel (2), described rectification section (13) is positioned at the rear of described radial contraction section (10).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420735547.1U CN204313313U (en) | 2014-11-27 | 2014-11-27 | Gas-turbine combustion chamber nozzle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420735547.1U CN204313313U (en) | 2014-11-27 | 2014-11-27 | Gas-turbine combustion chamber nozzle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204313313U true CN204313313U (en) | 2015-05-06 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420735547.1U Withdrawn - After Issue CN204313313U (en) | 2014-11-27 | 2014-11-27 | Gas-turbine combustion chamber nozzle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204313313U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104501208A (en) * | 2014-11-27 | 2015-04-08 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Nozzle of gas turbine combustor |
| CN106196170A (en) * | 2016-07-21 | 2016-12-07 | 中国航空动力机械研究所 | Centrifugal oil swirling atomization structure |
| CN107655033A (en) * | 2017-09-05 | 2018-02-02 | 中国联合重型燃气轮机技术有限公司 | fuel nozzle and rectifier |
-
2014
- 2014-11-27 CN CN201420735547.1U patent/CN204313313U/en not_active Withdrawn - After Issue
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104501208A (en) * | 2014-11-27 | 2015-04-08 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Nozzle of gas turbine combustor |
| CN104501208B (en) * | 2014-11-27 | 2018-02-06 | 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 |
| CN106196170A (en) * | 2016-07-21 | 2016-12-07 | 中国航空动力机械研究所 | Centrifugal oil swirling atomization structure |
| CN106196170B (en) * | 2016-07-21 | 2018-08-31 | 中国航空动力机械研究所 | Centrifugal oil swirling atomization structure |
| CN107655033A (en) * | 2017-09-05 | 2018-02-02 | 中国联合重型燃气轮机技术有限公司 | fuel nozzle and rectifier |
| CN107655033B (en) * | 2017-09-05 | 2020-07-14 | 中国联合重型燃气轮机技术有限公司 | Fuel nozzle and flow straightener |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of utility model: Nozzle for minisize gas-turbine combustor Effective date of registration: 20161104 Granted publication date: 20150506 Pledgee: Tsinghua Holdings Co., Ltd. Pledgor: Beijing Huatsing Gas Turbine & IGCC Technology Co., Ltd. Registration number: 2016990000853 |
|
| PLDC | Enforcement, change and cancellation of contracts on pledge of patent right or utility model | ||
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20150506 Effective date of abandoning: 20180206 |
|
| AV01 | Patent right actively abandoned |
Granted publication date: 20150506 Effective date of abandoning: 20180206 |
|
| PC01 | Cancellation of the registration of the contract for pledge of patent right | ||
| PC01 | Cancellation of the registration of the contract for pledge of patent right |
Date of cancellation: 20191211 Granted publication date: 20150506 Pledgee: Tsinghua Holdings Co., Ltd. Pledgor: Beijing Huatsing Gas Turbine & IGCC Technology Co., Ltd. Registration number: 2016990000853 |