CN204227463U - Gas-turbine combustion chamber axial admission nozzle - Google Patents
Gas-turbine combustion chamber axial admission nozzle Download PDFInfo
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- CN204227463U CN204227463U CN201420506196.7U CN201420506196U CN204227463U CN 204227463 U CN204227463 U CN 204227463U CN 201420506196 U CN201420506196 U CN 201420506196U CN 204227463 U CN204227463 U CN 204227463U
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- fuel injection
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- injection pipe
- combustion chamber
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Abstract
The utility model relates to gas turbine technology field, provides a kind of gas-turbine combustion chamber axial admission nozzle, comprises outer nozzle wall and is plugged in the fuel injection body in outer nozzle wall; The inside that fuel injects body is provided with center fuel passage, fuel inject body be provided with multiple fuel injection pipe in the radial direction, the sidewall of each fuel injection pipe is equipped with multiple fuel orifice, is provided with first order annular air-flow path between fuel injection pipe top and outer nozzle wall; Be provided with rectification orifice plate in the fuel chamber in the front of fuel injection pipe, ensure the uniformity of axial admission, and as adjusting a kind of method in nozzle interior flow field; The inwall of the outer nozzle wall at the rear of fuel injection pipe is provided with axial rotational flow device, axial rotational flow dress and fuel inject between body and are provided with second level annular air-flow path, by the acting in conjunction of fuel injection pipe and axial rotational flow device, ensure that fuel-air blending is even, the stability of burning and good Exit temperature distribution.
Description
Technical field
The utility model relates to gas turbine technology field, provides a kind of gas-turbine combustion chamber axial admission 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 to there is generating efficiency in this traditional generation technology, high (the especially NO of pollutant emission
xdischarge), expend 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 patent CN 100567823C, adopts the notched air swirling vanes in bottom, improves the speed of air duct inner circumferential side, coupling nozzle exit velocity type and fuel-air mixture example.
But this nozzle lacks corresponding rectification part, and axial admission is uneven.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, causes the mixing effect of this side fuel and air 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, 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 purpose of this utility model solves existing gas turbine to lack corresponding rectification part, and axial admission is uneven, and air swirling vanes swirl strength is weak, and the mixing effect of fuel and air is poor, the problem of the tissue of impact burning and the generation of pollutant.
(2) technical scheme
A kind of gas-turbine combustion chamber axial admission nozzle that the utility model provides, this technical scheme arranges rectification orifice plate at nozzle shaft to annular inlet passageway front end, and in axial direction to inject on body fuel arranged playpipe and axial rotational flow device successively at fuel, fuel injection pipe is fixed on fuel and injects on body, and be communicated with center fuel passage by wall perforate, from the fuel orifice supply fuel of fuel injection pipe both sides.First order annular air-flow path is provided with between the inwall of fuel injection pipe top and outer nozzle wall.Axial rotational flow device is fixed on the inwall of outer nozzle wall, and have second level annular air-flow path bottom swirl-flow devices and between fuel injection body, axial rotational flow device peripherally annular air channel is evenly arranged.The uniformity of axial admission is ensured by rectification orifice plate, and as adjusting a kind of method in nozzle interior flow field.By the acting in conjunction of fuel injection pipe and axial rotational flow device, ensure that nozzle exit velocity distribution is reasonable, fuel-air blending is even, conservative control combustion zone, maintains combustion chamber flow field structure, thus ensures the stability of burning and good Exit temperature distribution.
Preferably, the aperture of described air vent is 1.5mm ~ 10mm.
Preferably, the distance between described rectification orifice plate and described fuel injection pipe is 10 ~ 50 times of the aperture of described air vent.
Preferably, the setting perpendicular to axial direction of described rectification orifice plate, the inside and outside two ends of described arrangement orifice plate inject body with described fuel respectively and outer nozzle wall is connected.
Preferably, the thickness of described rectification orifice plate is 2mm ~ 5mm.
Preferably, the pore size of described fuel orifice is 0.1mm ~ 0.5mm.
Preferably, described axial rotational flow device comprises the swirl vane that multiple circumference is laid, and the width of described second level annular air-flow path is 10% ~ 50% of described swirl vane length.
Preferably, multiple described swirl vane and multiple described fuel injection pipe in the axial direction staggered relative arrange.
Preferably, on airintake direction, and the described fuel chambers being positioned at the rear of described axial rotational flow device has radial contraction structure.
Preferably, one end that described fuel injection body is inserted into described outer nozzle wall is taper.
(3) beneficial effect
A kind of gas-turbine combustion chamber axial admission nozzle that the utility model provides, this technical scheme arranges rectification orifice plate in axial annular inlet channel front end, and in axial direction to inject on body fuel arranged playpipe and axial rotational flow device successively at fuel, fuel injection pipe is fixed on fuel and injects on body, and be communicated with center fuel passage by wall perforate, from the fuel orifice supply fuel of fuel injection pipe both sides.First order annular air-flow path is had between the inwall of fuel injection pipe top and outer nozzle wall.Axial rotational flow device is fixed on the inwall of outer nozzle wall, and have second level annular air-flow path bottom swirl-flow devices and between fuel injection body, axial rotational flow device peripherally annular air channel is evenly arranged.The uniformity of axial admission is ensured by rectification orifice plate, and as adjusting a kind of method in nozzle interior flow field.By the acting in conjunction of fuel injection pipe and axial rotational flow device, ensure that nozzle exit velocity distribution is reasonable, fuel-air blending is even, conservative control combustion zone, maintains combustion chamber flow field structure, thus ensures the stability of burning and good Exit temperature distribution.
Accompanying drawing explanation
Fig. 1 is the schematic diagram of a kind of gas-turbine combustion chamber axial admission nozzle of the utility model embodiment;
Fig. 2 is the three-dimensional cutaway view of a kind of gas-turbine combustion chamber axial admission nozzle of the utility model embodiment.
Reference numeral: 1, center fuel passage; 2, annular air channel; 3, fuel injects body; 4, rectification orifice plate; 5, fuel injection pipe; 6, axial rotational flow device; 7, fuel orifice; 8, outer nozzle wall; 9, first order annular air-flow path; 10, second level annular air-flow path; 11, air annular air-flow path; 12, gaseous mixture air annular air-flow path; 13, radial contraction structure.
Detailed description of the invention
Below in conjunction with drawings and Examples, the specific embodiment of the present invention is described in further detail.Following examples for illustration of the present invention, but are not used for limiting the scope of the invention.
In description of the present utility model, except as otherwise noted, term " on ", the orientation of the instruction such as D score, "left", "right" or state relation be based on orientation shown in the drawings or state relation, only the utility model and simplified characterization for convenience of description, instead of the device of instruction or hint indication or element must have specific orientation, with specific azimuth configuration and operation, therefore can not be interpreted as restriction 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, a kind of gas-turbine combustion chamber axial admission nozzle that the utility model provides, comprise the fuel that outer nozzle wall 8 and one end be plugged in outer nozzle wall 8 and inject body 3, outer nozzle wall 8 sends into gases at high pressure by air compressor machine, the inside that fuel injects body 3 is provided with center fuel passage 1, fuel inject body 3 be provided with multiple fuel injection pipe 5 communicated with center fuel passage 1 in the radial direction, the sidewall of each fuel injection pipe 5 is equipped with fuel orifice 7, the pore size of fuel orifice 7 is Φ 0.1 ~ Φ 0.5, according to actual condition, select the fuel injection amount be applicable to, fuel is injected in outer nozzle wall 8 by fuel orifice 7 and mixes with air, first order annular air-flow path 119 is formed between fuel injection pipe 5 top and outer nozzle wall 8, and the width of first order annular air-flow path 119 is preferably 10% ~ 50% of the height of fuel injection pipe 5, thereby increase the air-flow axial velocity of peripheral annular air duct 2 outer circumferential side, reduce the boundary effect of internal face of combustion chamber, ensure the distribution of outer circumferential side gas velocity degree type.
Along the airintake direction of outer nozzle wall 8, in described outer nozzle wall (8), and the front being positioned at described fuel injection pipe 5 is provided with rectification orifice plate 4, rectification orifice plate 4 setting perpendicular to axial direction, its thickness is 2mm ~ 5mm, arrange the inside and outside two ends of orifice plate and injects body 3 with fuel respectively and outer nozzle wall 8 is connected, make itself and circumference seamless, air is passed into by air vent.Rectification orifice plate 4 can to air inlet rectification, and adjust the VELOCITY DISTRIBUTION of air inlet, the position of fuel orifice 7 is coordinated more easily to form the distribution of rational nozzle exit velocity and mixing effect, the aperture of air vent can be 1.5mm ~ 10mm, according to actual pressure drop needs, select the rectification orifice plate 4 in different air vent aperture; Distance between rectification orifice plate 4 and fuel injection pipe 5 is 10 ~ 50 times of the aperture of air vent, and air is passed through through after each air vent, is more mutually fused into the homogeneous air-flow in direction through a segment distance.
Along the airintake direction of described outer nozzle wall 8, on the inwall of described outer nozzle wall 8, and the rear being positioned at described fuel injection pipe 5 is provided with axial rotational flow device 6, it is multiple and the swirl vane of circumference uniform distribution that axial rotational flow device 6 preferably includes quantity, and the quantity of swirl vane is preferably 6 ~ 12; Axial rotational flow device 6 and fuel inject between body 3 and are formed with second level annular air-flow path 10, the width of second level annular air-flow path 10 is preferably 10% ~ 50% of swirl vane length, thereby increase the air-flow axial velocity of peripheral annular air duct 2 inner circumferential side, reduce fuel and inject body 3 boundary-layer to the impact of nozzle exit velocity type, and one end that fuel injection body 3 is inserted into outer nozzle wall 8 is taper, ensure that fuel injects body 3 downstream and do not produce recirculating zone, improve burning reliability.Thus, fuel injection pipe 5 and axial rotational flow device 6 can the eddy flow of enhanced fuel gas and air mix, ensure fluid velocity distribution rationally, fuel-air blending is even, and then promotes combustion stability.
Multiple swirl vane and multiple fuel injection pipe 5 in the axial direction staggered relative are arranged, coordinate the adjustment of fuel orifice 7 height and position, wider design space can be provided for nozzle, meet the needs of different fuel and air blending, improve the VELOCITY DISTRIBUTION that fuel nozzle injects body 3 to nozzle outlet portion.
Preferably, be 50% ~ 100% of the length of fuel injection pipe 5 by the distance between fuel injection pipe 5 and the opening of outer nozzle wall 8, prevent shunting fuel jetting nozzle outer wall 8; And between fuel injection pipe 5 and the air inlet of outer nozzle wall 8, forming air inlet passage thus, the fuel gas spraying to air inlet and the air entered liquidate and produce eddy current, thus in air inlet passage, a small amount of mixing occur.The combustion gas of certain above-mentioned shunting is just a small amount of, and the Main Function of air inlet passage is that the air making to enter returns to axis.
Preferably, distance between fuel injection pipe 5 and axial rotational flow device 6 is 50% ~ 100% of the length of fuel injection pipe 5, annular air-flow path 11 is formed thus between fuel injection pipe 5 and axial rotational flow device 6, achieve fuel gas and air enter swirl-flow devices before premixed, for ensureing that the mixing effect of jet expansion fuel gas and air plays facilitation.
Preferably, on airintake direction, the combustion chamber at the rear of axial rotational flow device 6 has radial contraction section, instantaneous compression is being there is in the gaseous mixture of air and fuel gas through this mirror image contraction structure, the concentration of fuel gas increases, relatively add mixability, compression can also be the warm-up movement aggravation of gas in addition, further increases the melting concn of fuel gas.
Gas fuel enters axial centre fuel channel 1, injects the perforate of body 3 wall and enters fuel injection pipe 5, spray from the fuel orifice 7 of both sides by fuel.Air extends axially through rectification orifice plate 4, at air annular air-flow path 11 with passing through jet action, form the uniform air flow met the demands, enter peripheral axial annular air duct 2, the passage inner circumferential side air pressing close to fuel injection body 3 mixes with fuel in fuel injection pipe 5 front end, enters gaseous mixture annular air-flow path 12 and strengthens mixed effect; The air injecting the air duct outer circumferential side of body 3 away from fuel keeps axial velocity by first order annular air-flow path 9, enters gaseous mixture annular air-flow path 12.Through fuel and the air Mixture of gaseous mixture annular air-flow path 12, outer circumferential side part acts on through axial rotational flow device 6 and produces eddy flow, and mixed effect strengthens further; Inner periphery side portion divides the original airflow direction of maintenance by second level annular air-flow path 10, and axial velocity is maintained.Fuel and air Mixture in axial rotational flow device 6 exit blending, through nozzle contraction section 13 until jet expansion.Thus form nozzle exit velocity distribution and the fuel-air mixing effect of coupling, ensure the stability of burning and good Exit temperature distribution.
The above is only the preferred embodiment of the present invention; it should be pointed out that for those skilled in the art, under the prerequisite not departing from the technology of the present invention principle; can also make some improvement and replacement, these improve and replace and also should be considered as protection scope of the present invention.
Claims (10)
1. a gas-turbine combustion chamber axial admission nozzle, is characterized in that, comprises the fuel that outer nozzle wall (8) and one end be plugged in described outer nozzle wall (8) and injects body (3); The inside that described fuel injects body (3) is provided with center fuel passage (1), that injects body (3) at described fuel is provided with the fuel injection pipe (5) that multiple and described center fuel passage (1) communicates in the radial direction, the sidewall of each described fuel injection pipe (5) is equipped with multiple fuel orifice (7), is provided with first order annular air-flow path (9) between fuel injection pipe (5) top and outer nozzle wall (8); In described outer nozzle wall (8), and the front being positioned at described fuel injection pipe (5) is provided with rectification orifice plate (4), and described rectification orifice plate (4) is provided with multiple air vent; On the inwall of described outer nozzle wall (8), and the rear being positioned at described fuel injection pipe (5) is provided with axial rotational flow device (6), axial rotational flow dress and fuel inject between body (3) and are provided with second level annular air-flow path (10).
2. gas-turbine combustion chamber axial admission nozzle according to claim 1, is characterized in that, the aperture of described air vent is 1.5mm ~ 10mm.
3. gas-turbine combustion chamber axial admission nozzle according to claim 2, is characterized in that, the distance between described rectification orifice plate (4) and described fuel injection pipe (5) is 10 ~ 50 times of the aperture of described air vent.
4. gas-turbine combustion chamber axial admission nozzle according to claim 1, it is characterized in that, the setting perpendicular to axial direction of described rectification orifice plate (4), the inside and outside two ends of described rectification orifice plate inject body (3) with described fuel respectively and outer nozzle wall (8) is connected.
5. gas-turbine combustion chamber axial admission nozzle according to claim 1, is characterized in that, the thickness of described rectification orifice plate (4) is 2mm ~ 5mm.
6. gas-turbine combustion chamber axial admission nozzle according to claim 1, is characterized in that, the aperture of described fuel orifice (7) is 0.1mm ~ 0.5mm.
7. gas-turbine combustion chamber axial admission nozzle according to claim 1, is characterized in that, described axial rotational flow device (6) is swirl vane, and quantity is multiple; Multiple swirl vane is along the circumference uniform distribution of described outer nozzle wall (7); The width of described second level annular air-flow path (10) is 10% ~ 50% of described swirl vane length.
8. gas-turbine combustion chamber axial admission nozzle according to claim 1, is characterized in that, multiple described swirl vane and multiple described fuel injection pipe (5) in the axial direction staggered relative are arranged.
9. the gas-turbine combustion chamber axial admission nozzle according to any one of claim 1-8, it is characterized in that, on airintake direction, and the described fuel chambers being positioned at the rear of described axial rotational flow device (6) has radial contraction structure (13).
10. the gas-turbine combustion chamber axial admission nozzle according to any one of claim 1-8, is characterized in that, one end that described fuel injection body (3) is inserted into described outer nozzle wall 8 is taper.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420506196.7U CN204227463U (en) | 2014-09-03 | 2014-09-03 | Gas-turbine combustion chamber axial admission nozzle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420506196.7U CN204227463U (en) | 2014-09-03 | 2014-09-03 | Gas-turbine combustion chamber axial admission nozzle |
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| Publication Number | Publication Date |
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| CN204227463U true CN204227463U (en) | 2015-03-25 |
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| CN201420506196.7U Active CN204227463U (en) | 2014-09-03 | 2014-09-03 | Gas-turbine combustion chamber axial admission nozzle |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104214800A (en) * | 2014-09-03 | 2014-12-17 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Axial air inlet nozzle of combustion chamber of gas turbine |
| CN107620983A (en) * | 2017-09-05 | 2018-01-23 | 中国联合重型燃气轮机技术有限公司 | Fuel nozzle |
| CN111706878A (en) * | 2020-06-01 | 2020-09-25 | 滁州帝邦科技有限公司 | Double oil-way opposite-impact direct-injection type nozzle |
| CN113551265A (en) * | 2021-08-11 | 2021-10-26 | 中国联合重型燃气轮机技术有限公司 | Fuel nozzle and gas turbine |
-
2014
- 2014-09-03 CN CN201420506196.7U patent/CN204227463U/en active Active
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104214800A (en) * | 2014-09-03 | 2014-12-17 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Axial air inlet nozzle of combustion chamber of gas turbine |
| CN107620983A (en) * | 2017-09-05 | 2018-01-23 | 中国联合重型燃气轮机技术有限公司 | Fuel nozzle |
| CN107620983B (en) * | 2017-09-05 | 2023-04-25 | 中国联合重型燃气轮机技术有限公司 | Fuel nozzle |
| CN111706878A (en) * | 2020-06-01 | 2020-09-25 | 滁州帝邦科技有限公司 | Double oil-way opposite-impact direct-injection type nozzle |
| CN113551265A (en) * | 2021-08-11 | 2021-10-26 | 中国联合重型燃气轮机技术有限公司 | Fuel nozzle and gas turbine |
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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: Axial air inlet nozzle of combustion chamber of gas turbine Effective date of registration: 20161104 Granted publication date: 20150325 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 | ||
| 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: 20150325 Pledgee: Tsinghua Holdings Co., Ltd. Pledgor: Beijing Huatsing Gas Turbine & IGCC Technology Co., Ltd. Registration number: 2016990000853 |