CN104214799B - Axial swirl nozzle of combustion chamber of gas turbine - Google Patents

Axial swirl nozzle of combustion chamber of gas turbine Download PDF

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Publication number
CN104214799B
CN104214799B CN201410446283.2A CN201410446283A CN104214799B CN 104214799 B CN104214799 B CN 104214799B CN 201410446283 A CN201410446283 A CN 201410446283A CN 104214799 B CN104214799 B CN 104214799B
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fuel
fuel injection
rotational flow
gas
axial rotational
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CN104214799A (en
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张龙
张珊珊
查筱晨
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China United Heavy Gas Turbine Technology Co Ltd
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Beijing Huatsing Gas Turbine and IGCC Technology Co Ltd
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Abstract

The invention relates to the technical field of a gas turbine, and provides an axial swirl nozzle of a combustion chamber of the gas turbine. The axial swirl nozzle has a structure of comprising an outer wall of the nozzle and a fuel injection body inserted into the outer wall of the nozzle, wherein the fuel injection body is internally provided with a center fuel channel; a plurality of fuel spraying pipes which are communicated with the center fuel channel are arranged along the radial direction of the fuel injection body; the side wall of each fuel spraying pipe is provided with fuel spraying holes; a first stage ring-shaped airflow channel is formed between the tops of the fuel spraying pipes and the outer wall of the nozzle; an axial rotational flow device is arranged on the inner wall of the outer wall of the nozzle behind the fuel spraying pipes along the air inlet direction; a second stage ring-shaped airflow channel is formed between the axial rotational flow device and the fuel injection body. Due to the combined action of the fuel spraying pipes and the axial rotational flow device, the fluid speed is reasonably distributed at a fuel spraying outlet, the fuel and the air are evenly mixed, and a combustion area is reasonably controlled, so that combustion stability and good exit temperature distribution are guaranteed.

Description

Gas-turbine combustion chamber axial rotational flow nozzle
Technical field
The present invention relates to gas turbine technology field, especially provide a kind of gas-turbine combustion chamber axial rotational flow nozzle.
Background technology
In the current energy resource structure of China, most shares are occupied using the thermal power generation of traditional coal combustion technology. But it is low to there is generating efficiency in this traditional generation technology, pollutant emission height (especially noxDischarge), expend freshwater resources Many the shortcomings of.Gas turbine power generation technology using natural gas as fuel one of as clean energy technology, can generate electricity meeting While burden requirement, effectively reduce the discharge of pollutant, among these the design of gas-turbine combustion chamber axial rotational flow nozzle Particularly important for tissue burning, reduction pollutant emission.
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 mates rational fuel-air mixture example, enters combustion chamber tissue burning, is formed steady Fixed flow field and combustion field.Currently, the design form to gas-turbine combustion chamber axial rotational flow nozzle, such as patent Cn100567823c, using the notched air swirling vanes in bottom, improves the speed of air duct inner circumferential side, coupling nozzle goes out Mouth velocity profile and fuel-air mixture example.
But, because air swirling vanes bottom has breach, the air flow deflector angle of passage inner circumferential side is little, swirl strength Weak, lead to this side fuel and the mixing effect of air to be deteriorated;Fuel gas is in hollow blade two STH spray, fuel gas simultaneously Shorter with the blending of air distance, and increased difficulty, the tissue of impact burning and the generation of pollutant of blade processing.Cause This is it is still desirable to more effectively gas-turbine combustion chamber axial rotational flow form of nozzle is burnt and control pollutant to organize Discharge.
Content of the invention
(1) technical problem to be solved
Present invention aim to address the air swirling vanes swirl strength of existing gas turbine is weak, the mixing of fuel and air Mixed effect 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 rotational flow nozzle that the present invention provides, includes outer nozzle wall and described in being plugged in Fuel injection body in outer nozzle wall;The inside that described fuel injects body is provided with center fuel passage, injects body in described fuel Be provided with the fuel injection pipe that multiple and described center fuel passage communicates, the side of each described fuel injection pipe in the radial direction Wall is equipped with fuel orifice, is provided with first order annular air-flow path between fuel gas playpipe top and outer nozzle wall;Entering On gas direction, the inwall of the outer nozzle wall at the rear of described fuel injection pipe is provided with axial rotational flow device, axial rotational flow dress with It is provided with second level annular air-flow path between fuel injection body.
Preferably, described axial rotational flow device includes the swirl vane that multiple circumference are laid.
Preferably, the width of described second level annular air-flow path is the 10%~50% of described swirl vane length.
Preferably, the quantity of described swirl vane is 6~12.
Preferably, multiple described swirl vanes and multiple described fuel injection pipes staggered relative setting in the axial direction.
Preferably, the width of described first order annular air-flow path be the height of described fuel injection pipe 10%~ 50%.
Preferably, the distance between opening of described fuel injection pipe and described outer nozzle wall is the length of fuel injection pipe 50%~100%.
Preferably, the distance between described fuel injection pipe and described axial rotational flow device are the length of described fuel injection pipe The 50%~100% of degree.
Preferably, on airintake direction, and have radially positioned at the described combustion chamber at the rear of described axial rotational flow device Contraction section.
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 rotational flow nozzle that the present invention provides, this technical scheme in axial direction cloth successively Put fuel injection pipe and axial rotational flow device, fuel injection pipe top is provided with fuel orifice, and it sets and between outer nozzle wall inwall There is first order annular air-flow path;Axial rotational flow device is fixed on outer nozzle wall face, and axial rotational flow device injects body with fuel Between have second level annular air-flow path, axial rotational flow device is circumferentially evenly arranged.By fuel injection pipe and axial rotational flow dress The collective effect put is it is ensured that fuel injection exit fluid velocity is reasonably distributed, fuel-air blends uniformly, rationally controls burning Region, maintains combustion chamber flow field structure, thus ensureing the stability of burning and good Exit temperature distribution.
Brief description
Fig. 1 is a kind of schematic diagram of gas-turbine combustion chamber axial rotational flow nozzle of the embodiment of the present invention;
Fig. 2 is a kind of three-dimensional cutaway view of gas-turbine combustion chamber axial rotational flow nozzle of the embodiment of the present invention.
Reference: 1, center fuel passage;2nd, annular air channel;3rd, fuel injection body;4th, fuel injection pipe;5th, axle To swirl-flow devices;6th, fuel orifice;7th, outer nozzle wall;8th, first order annular air-flow path;9th, second level annular air-flow path; 10th, gaseous mixture annular air-flow path;11st, radial contraction section;12nd, air inlet passage.
Specific embodiment
With reference to the accompanying drawings and examples, the specific embodiment of the present invention is described in further detail.Hereinafter implement Example is used for the present invention is described, but is not limited to the scope of the present invention.
In describing the invention, unless otherwise stated, term " on ", D score, the orientation of instruction or the shape such as "left", "right" State relation is based on orientation shown in the drawings or state relation, is for only for ease of the description present invention and simplifies description, rather than Indicate or the hint device of indication or element must have specific orientation, with specific azimuth configuration and operation, therefore can not It is interpreted as limitation of the present invention.
In describing the invention, it should be noted that unless otherwise clearly defined and limited, term " connection " should do Broadly understood, for example, it may be being fixedly connected or being detachably connected, or be integrally connected;Can be to be joined directly together, Can also be indirectly connected to by intermediary.For the ordinary skill in the art, can be above-mentioned with concrete condition understanding Term concrete meaning in the present invention.
In conjunction with shown in Fig. 1 and Fig. 2, a kind of gas-turbine combustion chamber axial rotational flow nozzle that the present invention provides, including nozzle Outer wall 7 and one end are plugged in the fuel injection body 3 in outer nozzle wall 7, and outer nozzle wall 7 sends into gases at high pressure by air compressor machine; The inside that fuel injects body 3 is provided with center fuel passage 1, is provided with multiple combustions with center in the radial direction what fuel injected body 3 The fuel injection pipe 4 that material passage 1 communicates, the side wall of each fuel injection pipe 4 is equipped with fuel orifice 6, and fuel passes through fuel Spray-hole 6 is injected in outer nozzle wall 7 and is mixed with air, is formed with first between fuel gas playpipe top and outer nozzle wall 7 Level annular air-flow path 8, and the 10% of the width of the first order annular air-flow path 8 preferably height of fuel injection pipe 4~ 50%, thereby increase the air-flow axial velocity of peripheral annular air duct 2 outer circumferential side, reduce the boundary-layer of internal face of combustion chamber Effect is it is ensured that outer circumferential side gas velocity degree type is distributed.
Air is entered by the air inlet of outer nozzle wall, starts to be mixed with fuel, in nozzle at fuel injection pipe On the inwall of outer wall 7, and the rear positioned at described fuel injection pipe 4, it is provided with axial rotational flow device 5, axial rotational flow device 5 is preferred It is multiple swirl vanes for quantity, the quantity of swirl vane is preferably 6~12, because axial rotational flow device 5 is located at fuel The rear of playpipe airflow direction, can make the fuel of mixing and air be sufficiently mixed;Axial rotational flow device 5 injects body with fuel It is formed with second level annular air-flow path 9, the width of second level annular air-flow path 9 is preferably swirl vane length between 3 10%~50%, thereby increase the air-flow axial velocity of peripheral annular air duct 2 inner circumferential side, reduce fuel injection body 3 attached The impact to nozzle exit velocity type for the surface layer, and fuel inject body 3 to be inserted into one end of outer nozzle wall 7 be taper it is ensured that center Cone downstream does not produce recirculating zone, improves burning reliability.Thus, fuel injection pipe 4 and axial rotational flow device 5 can strengthen combustion The eddy flow mixing of material gas and air is it is ensured that fluid velocity is reasonably distributed, fuel-air blends uniformly, and then lifts flameholding Property.
The staggered relative setting in the axial direction of multiple swirl vanes and multiple fuel injection pipes 4, cooperation fuel orifice 6 height The adjustment of position, can provide broader design space for nozzle, meet the needs that different fuel and air blend, improve nozzle Conical inner body to nozzle outlet portion VELOCITY DISTRIBUTION.
Preferably, the length the distance between opening of fuel injection pipe 4 and outer nozzle wall 7 being fuel injection pipe 4 50%~100%, prevent from shunting fuel jetting nozzle outer wall 7;And thus in the air inlet of fuel injection pipe 4 and outer nozzle wall 7 Between form air inlet passage 12, spray to the fuel gas of air inlet and liquidate and produce vortex with the air entering, thus There is a small amount of mixing in air inlet passage 12.The combustion gas of certainly above-mentioned shunting is only a small amount, the master of air inlet passage 12 Act on the air being to make entrance to recover to axial direction.
Preferably, the distance between fuel injection pipe 4 and axial rotational flow device 5 are the 50% of the length of fuel injection pipe 4 ~100%, between fuel injection pipe 4 and axial rotational flow device 5, thus form annular air-flow path it is achieved that fuel gas and sky Gas enters the premixing before swirl-flow devices, plays facilitation for the mixing effect ensureing jet expansion fuel gas and air.
Preferably, on airintake direction, the combustion chamber at the rear of axial rotational flow device 5 has radial contraction section 11, air There is instantaneous compression with the gaseous mixture of fuel gas when through this mirror image contraction structure, the concentration of fuel gas increases, relatively Increased mixability, in addition compression can also be the warm-up movement aggravation of gas, further increase the melting concn of fuel gas.
The operation principle of the present invention is as follows:
, gas fuel enters center fuel passage 1 taking clean energy resource gas fuel as a example, injects body 3 by fuel Wall perforate enter each fuel injection pipe 4, then sprayed by each fuel orifice 6.Air enters annular air channel 2, leads to Cross air inlet passage 12 airflow direction to recover to axial direction, press close to fuel and inject the passage inner circumferential side air of body 3 in fuel gas blowout Penetrate pipe front end to be mixed with fuel, enter gaseous mixture annular air-flow path 10 and strengthen mixed effect;Sky away from conical inner body The air of gas passage outer circumferential side keeps axial velocity to pass through first order annular air-flow path 8, enters gaseous mixture annular air-flow path 10.Through fuel and the air Mixture of gaseous mixture annular air-flow path 10, outer circumferential side part acts on through axial rotational flow device 5 Produce eddy flow, mixed effect further enhances;Inner circumferential portion keeps original airflow direction to pass through second level annular air-flow path 9, axial velocity is maintained.Fuel and air Mixture blend in axial rotational flow device 5 exit, through nozzle contraction Duan Zhi To jet expansion.Thus formed coupling nozzle exit velocity distribution and fuel-air mixing effect it is ensured that burning stability With good Exit temperature distribution.
The above is only the preferred embodiment of the present invention it is noted that ordinary skill people for the art For member, on the premise of without departing from the technology of the present invention principle, some improvement can also be made and replace, these improve and replace Also should be regarded as protection scope of the present invention.

Claims (10)

1. a kind of gas-turbine combustion chamber axial rotational flow nozzle is it is characterised in that inclusion outer nozzle wall (7) and one end are plugged in Fuel injection body (3) in described outer nozzle wall (7);The inside that described fuel injects body (3) is provided with center fuel passage (1), Described fuel inject body (3) be provided with the fuel injection pipe that multiple and described center fuel passage (1) communicates in the radial direction (4), the side wall of each described fuel injection pipe (4) is equipped with fuel orifice (6), the top of described fuel injection pipe (4) and It is formed with first order annular air-flow path (8) between described outer nozzle wall (7);On the inwall of outer nozzle wall (7), and it is located at institute State the rear of fuel injection pipe (4), be provided with axial rotational flow device (5), between axial rotational flow device (5) and fuel injection body (3) It is formed with second level annular air-flow path (9);
Form air inlet passage (12) between the air inlet of fuel injection pipe (4) and outer nozzle wall (7), spray to air inlet Fuel gas liquidates and produces vortex with the air entering.
2. gas-turbine combustion chamber axial rotational flow nozzle according to claim 1 is it is characterised in that described axial rotational flow fills Putting (5) is swirl vane, and quantity is multiple;Multiple swirl vanes are along the circumference uniform distribution of described outer nozzle wall (7).
3. gas-turbine combustion chamber axial rotational flow nozzle according to claim 2 is it is characterised in that the described second level is annular The width of gas channel (9) is the 10%~50% of described swirl vane length.
4. gas-turbine combustion chamber axial rotational flow nozzle according to claim 2 is it is characterised in that described swirl vane Quantity is 6~12.
5. gas-turbine combustion chamber axial rotational flow nozzle according to claim 2 is it is characterised in that multiple described eddy flow leaf The staggered relative setting in the axial direction of piece and multiple described fuel injection pipes (4).
6. gas-turbine combustion chamber axial rotational flow nozzle according to claim 1 is it is characterised in that the described first order is annular The width of gas channel (8) is the 10%~50% of the height of described fuel injection pipe (4).
7. gas-turbine combustion chamber axial rotational flow nozzle according to claim 1 is it is characterised in that described fuel injection pipe (4) it is the 50%~100% of the length of fuel injection pipe (4) with the distance between the opening of described outer nozzle wall (7).
8. gas-turbine combustion chamber axial rotational flow nozzle according to claim 1 is it is characterised in that described fuel injection pipe (4) it is the 50%~100% of the length of described fuel injection pipe (4) with the distance between described axial rotational flow device (5).
9. the gas-turbine combustion chamber axial rotational flow nozzle according to any one of claim 1-8 is it is characterised in that in air inlet On direction, the described outer nozzle wall (7) at the rear of described axial rotational flow device (5) has radial contraction section.
10. the gas-turbine combustion chamber axial rotational flow nozzle according to any one of claim 1-8 is it is characterised in that described One end that fuel injection body (3) is inserted into described outer nozzle wall (7) is taper.
CN201410446283.2A 2014-09-03 2014-09-03 Axial swirl nozzle of combustion chamber of gas turbine Active CN104214799B (en)

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CN106247408B (en) * 2016-07-27 2019-01-18 中国科学院工程热物理研究所 A kind of nozzle, nozzle array and burner for widening tempering nargin
CN106196059A (en) * 2016-08-26 2016-12-07 中能服能源科技股份有限公司 A kind of low nitrogen oxide burner structure

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US5590529A (en) * 1994-09-26 1997-01-07 General Electric Company Air fuel mixer for gas turbine combustor
US5896739A (en) * 1996-12-20 1999-04-27 United Technologies Corporation Method of disgorging flames from a two stream tangential entry nozzle
EP0935095A3 (en) * 1998-02-09 2000-07-19 Mitsubishi Heavy Industries, Ltd. Gas turbine combustor
JP4508474B2 (en) * 2001-06-07 2010-07-21 三菱重工業株式会社 Combustor
EP1406047A4 (en) * 2001-07-10 2010-04-07 Mitsubishi Heavy Ind Ltd Premixing nozzle, burner and gas turbine
CN204176681U (en) * 2014-09-03 2015-02-25 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 axial rotational flow nozzle

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Denomination of invention: Axial swirl nozzle of combustion chamber of gas turbine

Effective date of registration: 20171115

Granted publication date: 20170118

Pledgee: Tsinghua Holdings Co., Ltd.

Pledgor: Beijing Huatsing Gas Turbine & IGCC Technology Co., Ltd.

Registration number: 2016990000853

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Granted publication date: 20170118

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Date of cancellation: 20191230

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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.

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: 20170118

Pledgee: Tsinghua Holdings Co.,Ltd.

Pledgor: Beijing Huatsing Gas Turbine & IGCC Technology Co.,Ltd.

Registration number: 2016990000853