CN110131750A - A kind of gas turbine low discharging burning chamber of using gas fuel - Google Patents
A kind of gas turbine low discharging burning chamber of using gas fuel Download PDFInfo
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- CN110131750A CN110131750A CN201910341915.1A CN201910341915A CN110131750A CN 110131750 A CN110131750 A CN 110131750A CN 201910341915 A CN201910341915 A CN 201910341915A CN 110131750 A CN110131750 A CN 110131750A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means
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- Combustion & Propulsion (AREA)
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Abstract
A kind of gas turbine low discharging burning chamber of using gas fuel, belong to technical field of gas turbine, the combustion chamber includes grade on duty, main combustion stage, isolating high-pressure ignitor, blending hole, air exit, support case, burner inner liner, the outer casing of burner inner liner, flange, No.1 grade gas fuel pipe on duty, main combustion stage gas fuel pipe, main combustion stage fuel manifold, No.1 grade fuel manifold on duty, pipeline support, No. two grade fuel manifolds on duty, No. two grade gas fuel pipes on duty, conditioner, No.1 grade fuel bath on duty, No. two grade fuel baths and main combustion stage fuel bath on duty, when gas turbine is in the Smaller loads states such as starting, only grade on duty works independently, when starting is with first-class big load, grade and main combustion stage on duty work together, the diffusion combustion of grade fuel on duty provides stable incendiary source to primary zone, both low row had been ensure that Put requirement, and fully take into account combustion stability, efficiency of combustion etc., meet the performance requirement of combustion chamber comprehensively.
Description
Technical field
The invention belongs to gas-turbine combustion chamber technical fields, and in particular to a kind of gas turbine of using gas fuel is low
Discharge combustion chamber.
Background technique
Gas turbine originates from the 1960s, it can have heat using pluralities of fuels such as gaseous fuel, liquid fuels
It is high-efficient, discharge amount of pollution is small, it is small in size, start fast, few with water and be suitable for the advantages that using pluralities of fuel, therefore by various countries
Attention.It is a kind of dynamic power machine for being widely used in many industrial circles such as aviation, ship, electric power, in national economy
Play the role of in development vital.Compared with other engines, gas turbine has extremely more advantages, in specific fuel consumption,
Noise, discharge, vibration etc. have huge advantage, while for traditional distributed power generation, can be also used for grid-connected
The various ways such as power generation, it is suitable for city, and is suitable for remote districts.And it is reliable excellent by itself having cleaning
High praise of the point by industry and society.Gas turbine is very wide as advanced motive power machine equipment use scope in recent years
It is general, in addition to being processed in electromechanics, metal material etc. is multi-field application in the communications and transportation such as extra large Lu Bianfang.
In recent years, the theories such as environmental protection, sustainable development can be rooted in the hearts of the people, and the whole world is for haze, the rings such as greenhouse effects
Border problem also growing interest.The environmental problem caused by burning causes global concern, in order to solve the problems, such as this respect,
Combustion with reduced pollutants technical research is carried out in countries in the world.Wherein, poor fuel premixed combustion technology is a kind of main low emission combustion
Burning technology is applied in advanced low emission gas turbine.But there are following several respects in this technology:
1. Flammability limits is narrow, easily occurs flame-out phenomenon especially under the low operating condition of engine；
2. easily occurring spontaneous combustion and tempering problem in pre-compounding process, the damage of engine chamber is caused；
3. lacking adaptability for the gaseous fuel that calorific value fluctuates in a certain range, it cannot be guaranteed that primary zone equivalent proportion is protected
It holds within the scope of 0.6-0.8.
Summary of the invention
The present invention provides the center fractional combustion of gaseous fuel and the low emission combustor of lean fuel premixed combustion can be applied,
The technical solution being capable of stable operation when guaranteeing gas turbine using gas fuel；At the same time it can also be effectively reduced
The exhaust emission of combustion chamber.There are problems that tempering, spontaneous combustion propose premixed combustion to increase tapered partition and increase mixed gas
Speed.Fluctuation for fuel value proposes and increases conditioner in head of combustion chamber.
To achieve the goals above, the present invention adopts the following technical scheme:
A kind of gas turbine low discharging burning chamber of using gas fuel, the head of combustion chamber includes according to concentric manner
The grade and main combustion stage on duty of arrangement, and grade on duty, at center, main combustion stage is arranged in grade periphery on duty, and described value class includes level-one
Axial swirler and grade fuel nozzle ports on duty, level-one axial swirler is installed in the centre bore of flame tube head, outside burner inner liner
Casing is mounted on outside burner inner liner, and burner inner liner and the outer casing of burner inner liner are coaxially disposed, flame drum outer wall and the outer casing of burner inner liner
Air duct is formed between inner wall, and isolating high-pressure ignitor, flame are installed at the outer casing of the burner inner liner and level-one cyclone center
The outer casing head of cylinder or burner inner liner outside casing at level-one axial swirler and level-one cyclone tail portion be provided with it is on duty
Grade fuel nozzle ports, the main combustion stage include second level radial swirler, main combustion stage fuel nozzle ports and partition, second level radial swirler peace
Loaded on flame tube head, it is uniformly arranged in the circumferential direction the spray of main combustion stage fuel respectively at the head and center of second level radial swirler
Mouthful, the main combustion stage fuel conduit of the flame tube head runs through the outer casing head of burner inner liner, and main combustion stage fuel conduit input end
It is connected by main combustion stage gas fuel pipe with main combustion stage fuel manifold outlet side, the outer casing head of the burner inner liner is respectively set
There are No.1 grade fuel conduit on duty and No. two grade fuel conduits on duty, No.1 grade fuel conduit on duty passes through No.1 grade gas on duty
Fuel conduit is connected with No.1 grade fuel manifold on duty outlet side, and No. two grade fuel conduits on duty pass through No. two grade gas combustions on duty
Expects pipe road is connected with No. two grade fuel manifold on duty outlet sides, No.1 grade fuel conduit on duty, No. two grade cartridges on duty
Road and main combustion stage fuel conduit are fixedly mounted on head of combustion chamber, the main combustion stage fuel manifold, No. two grades on duty by flange
Fuel manifold and No.1 grade fuel manifold inlet end on duty are connected with gas source, and the grade combustion on duty of main combustion stage fuel manifold, No.1
General pipeline and No. two grade fuel manifold on duty of material is mounted on pipeline support, and pipeline support is installed in compressor housings, fire
The outlet side of flame cylinder is connect by support case with nozzle ring, and diffuser one end is connected with compressor housings, and the other end is solid
It is scheduled on the outer casing outlet section of burner inner liner, the burner inner liner and nozzle ring collectively constitute air exit, in second level radial vortex
Partition is installed in device tail portion, and burner inner liner inner wall is equipped with the conditioner positioned at partition tail portion one end, in flame drum tail point
Several blending holes of cloth.
The No.1 grade fuel nozzle ports on duty and No. two grade fuel nozzle ports internal diameters on duty are 0.1-0.5mm, number 16-
24.
Angle between No.1 grade fuel nozzle ports axis on duty and level-one axial swirler axis is 0-60 °.
Angle between the axis and level-one axial swirler axis of No. two grade fuel nozzle ports on duty is 0-60 °.
The No.1 main fuel spout and No. two main fuel nozzle pluggages are 0.1-0.5mm, and number is 16-24.
The center line and engine centerline setting angle of the burner inner liner are 0-30 °.
Burner inner liner primary zone equivalent proportion is the poor oil firing of 0.6-0.8, it has lean combustion premix lean combustion concurrently simultaneously and directly sprays
The two-fold advantage penetrated, the temperature of overall reduction main combustion stage, and burner inner liner primary zone ignition temperature are lower than 1800K, effectively inhibition NOX
Especially thermal NOXGeneration.
The invention has the benefit that
1, apparatus of the present invention combustion chamber is classified method of supplying using Central Fuel, and gaseous fuel is divided into two-way and enters burning
Room, wherein gaseous fuel from central value class spout enters combustion chamber all the way, grade on duty uses diffusion+premixed combustion；Second tunnel
Gaseous fuel by the direct axial and radial cavity for injecting main mixed zone of main combustion stage fuel nozzle ports, cavity fuel with
The air come in from second level radial swirler uniformly blends；Uniformly mixed combustible gas flows out mixed zone through partition, due to introducing
Partition, makes constriction in flow area, on the one hand avoids the low regime formed by center adverse pressure gradient, controls flammable mixing
The swirl strength of object, mixed effect is more preferable, on the other hand can pre- anti-backfire, nature and hugging, avoid engine chamber
Damage, combustion mixture enters flame tube head, forms uniform flammable premixed gas body mixture and fires in recirculating zone on the outside
The characteristics of burning, realizing that stablizing for gaseous fuel is burnt, while ensure that high efficiency, low pollution, grade on duty is providing steady fire source, main
It fires grade and realizes combustion with reduced pollutants, reducing the stability that can ensure that gas-turbine combustion chamber while disposal of pollutants.
2, air available air regulating device in burner inner liner primary zone is adjusted, and guarantees to work as using primary zone when fuels with different heat values
Amount ratio is maintained within the scope of 0.6-0.8, the temperature of overall reduction main combustion stage, and ignition temperature control in burner inner liner primary zone is made to exist
1800K is hereinafter, effectively inhibit NOX, CO especially thermal NOXGeneration.
3, when gas turbine is in the Smaller loads states such as starting, only grade on duty works independently, in starting with first-class big load
When, grade and main combustion stage on duty work together, and the diffusion combustion of grade fuel on duty provides stable incendiary source for primary zone,
Not only ensure that low emission requirement, but also fully taken into account combustion stability, efficiency of combustion etc., the performance for meeting combustion chamber comprehensively is wanted
It asks.
4, the low emission of gas fuel combustion room is realized, by using lean premixed combustion technology to control in combustion chamber
The equivalent proportion of combustion zone and the mode of mixture homogeneity achieve the purpose that reduce pollutant emission.Using center fractional combustion side
Case, gaseous fuel are entered combustion chamber by grade nozzle on duty, are guaranteed the combustion stability of entire combustion chamber using diffusion combustion, really
It protects main combustion stage and burns down gas combustion that is complete, and entering primary zone by the fuel nozzle ports of main combustion stage in wide equivalence ratio range internal combustion
Material is blended in primary zone and air, and combustion chamber is given to provide uniformly flammable mixed gas, to control the equivalent proportion and of entire combustion zone
Even property, realizes the low emission of combustion chamber.
5, No.1 grade fuel nozzle ports on duty and No. two grade fuel nozzle ports internal diameters on duty are 0.1-0.5mm, and number is
16-24；The No.1 main fuel spout and No. two main fuel nozzle pluggages are 0.1-0.5mm, and number is 16-24；Combustion
Material and air are bigger in the jet stream relative velocity of entrance, that is, initial velocity field degree of irregularity is higher, and momentum-exchange is got over
By force, more advantageous to mixed process.Change nozzle diameter under conditions of flow is constant, initial jets relative velocity can be realized
Variation.The pore diameter range of selection 0.1-0.5mm, which can guarantee that the effluxvelocity of fuel is sufficiently large, sufficiently to be premixed with incoming air,
Will lead to that fuel jet depth is inadequate higher than this range, the premix uniformity of fuel and air is poor to cause efficiency of combustion to reduce,
Cause in fuel injection to burner inner liner wall surface lower than this range, fuel and air pre-mixing uniformity are poor, lead to primary zone equivalent
Than bad, pollutant emission increase and flammable mixture is easy the combustion damage burner inner liner at wall surface；Increasing number of nozzle can
The mixed of premix section is improved, mainly after number of nozzle increase, the distance of arbitrary point all shortens on nozzle to locating section
, fuel, which is spread, to be completed in shorter premix segment length.But the increase of number of nozzle, it also can be to the structure of concentration field
It has an impact.The mixing efficiency showed when single injector linear degree after number of nozzle increases is deteriorated, so number of nozzle
It cannot be too many.6-24 spout can guarantee that the effluxvelocity of fuel is enough, while be promoted using eddy flow flowing and strong turbulence effect
Into the Convention diffusion of fuel, local low speed vortex structure is eliminated, optimizes air flowing in premixed channel, keeps Uniform Flow, with
Fuel feed matches, and low-speed region is avoided tempering to occur, lower than this range, and fuel is unevenly distributed, and is unable to fully benefit
It is likely to occur local air excess or local burnup's excessive concentration phenomenon with air, is more than this range, not can guarantee fuel
Jet Penetration Depth causes to premix efficiency sharp fall.
6, the angle between No.1 grade fuel nozzle ports axis on duty and level-one axial swirler axis is 0-60 °；Institute
The angle stated between the axis and level-one axial swirler axis of No. two grade fuel nozzle ports on duty is 0-60 °.Simple air rotation
Stream can't change the mixed of this premix section, and influence of the eddy flow to mixing efficiency is mainly axial average by changing
Speed and the turbulivity of fuel and air are realized.So fuel jet direction is with air swirl direction, there are an angles to become
Change the affecting laws to premixing effect.0-60 ° can optimize air Uniform Flow and reduce fuel nozzle downstream local eddy currents,
Air and fuel have enough swirl strengths, and fuel concentration, which is evenly distributed, ensure that full combustion, and equivalent proportion is desired obtains
Within the scope of；Lower than this range, the low velocity eddy in jet pipe downstream is on the one hand expanded, directly weakens air-flow to fuel
Diffusion；On the other hand, assemble the fuel stream from two neighboring spout more, make local concentration is higher can equally reduce
Fuel premixes uniformity；More than this range, the effluxvelocity of fuel is simultaneously not affected by the eddy flow influence of air in addition, higher fuel
Momentum of impinging jet will will affect the local flow near fuel nozzle, change vortex structure and air mass flow, to influence fuel
Concentration distribution, cause premix the poor fuel of uniformity be unable to fully burn.
7, the center line of the burner inner liner and engine centerline setting angle are 0-30 °, are installed within this range, flame
Cylinder installation convenience, is for ease of maintenaince maintained, and the exhaust section of burner inner liner can make full use of diffuser diffusion effect；Lower than range, combustion
Gas-turbine integral layout is unreasonable, and burner inner liner tail gas need to pass through large turn discharge；Higher than this range, tail gas is easy impact exhaust
Section and diffuser structure, may cause danger.
Detailed description of the invention
Fig. 1 is the gas turbine schematic diagram of 1 gas turbine low discharging burning chamber of the embodiment of the present invention；
Fig. 2 is 1 gas turbine low discharging burning chamber schematic diagram of the embodiment of the present invention；
Fig. 3 is enlarged diagram at 1 gas turbine low discharging burning chamber A of the embodiment of the present invention；
Fig. 4 is enlarged diagram at 1 gas turbine low discharging burning chamber B of the embodiment of the present invention；
Fig. 5 is 2 gas turbine low discharging burning chamber schematic diagram of the embodiment of the present invention；
Fig. 6 is enlarged diagram at 2 gas turbine low discharging burning chamber C of the embodiment of the present invention；
1, compressor housings, 2, No.1 grade fuel nozzle ports on duty, 3, No. two grade fuel nozzle ports on duty, 4, the combustion of No.1 main combustion stage
Material spout, 5, No. two main combustion stage fuel nozzle ports, 6, level-one axial swirler, 7, isolating high-pressure ignitor, 8, partition, 9, blending hole, 10,
Air exit, 11, support case, 12, burner inner liner, 13, second level radial swirler, 14, the outer casing of burner inner liner, 15, flange, 16,
No.1 grade gas fuel pipe on duty, 17, main combustion stage gas fuel pipe, 18, main combustion stage fuel manifold, 19, No.1 grade on duty
Fuel manifold, 20, pipeline support, 21, No. two grade fuel manifolds on duty, 22, No. two grade gas fuel pipes on duty, 23, air
Regulating device, 24, No.1 grade fuel bath on duty, 25, No. two grade fuel baths on duty, 26, main combustion stage fuel bath, 27- diffuser.
Specific embodiment
The present invention is described in further detail with reference to the accompanying drawings and examples.
Embodiment 1
As Figure 1-Figure 4, a kind of gas turbine low discharging burning chamber of using gas fuel, the head of combustion chamber packet
The grade and main combustion stage on duty arranged according to concentric manner are included, and grade on duty, at center, main combustion stage is arranged in grade periphery on duty, passes through
Regulated value class, main combustion stage fuel distribution and different spray nozzles between cooperation realize burning when using gas fuel
Stability and low emission, described value class include level-one axial swirler 6 and grade fuel nozzle ports on duty, level-one axial swirler 6
Be installed in the centre bore on the head of burner inner liner 12, the outer casing 14 of burner inner liner is mounted on outside burner inner liner 12, and burner inner liner 12 with
The outer casing 14 of burner inner liner is coaxially disposed, and is respectively arranged with No.1 grade fuel bath 24 on duty on the outer casing 14 of burner inner liner and No. two on duty
Grade fuel bath 25 forms air duct, the outer casing of the burner inner liner between 12 outer wall of burner inner liner and burner inner liner 14 inner wall of outer casing
14 and level-one axial swirler 6 center at isolating high-pressure ignitor 7 is installed, there are two described value class fuel nozzle ports, is respectively
No.1 grade fuel nozzle ports 2 on duty and No. two grade fuel nozzle ports 3 on duty, No. two casing 14 outside burner inner liner of grade fuel nozzle ports 3 on duty
Head is uniformly arranged in the circumferential direction, and the axis of No. two grade fuel nozzle ports 3 on duty is parallel with 6 axis of level-one axial swirler,
It is installed in 6 inner ring of level-one axial swirler on 12 head of burner inner liner and has been uniformly arranged in the circumferential direction No.1 grade fuel nozzle ports 2 on duty,
The main combustion stage includes second level radial swirler 13, main combustion stage fuel nozzle ports and partition 8, and second level radial swirler 13 is installed on fire
12 head of flame cylinder, and the space formed between the two is main combustion stage fuel bath 26, there are two the main combustion stage fuel nozzle ports, respectively
For No.1 main combustion stage fuel nozzle ports 4 and No. two main combustion stage fuel nozzle ports 5, distinguish at the head and center of second level radial swirler 13
It has been uniformly arranged in the circumferential direction No.1 main combustion stage fuel nozzle ports 4 and No. two main combustion stage fuel nozzle ports 5, No.1 main combustion stage fuel nozzle ports 4
Jet direction is in the same direction with incoming air, and No. two 5 jet directions of main combustion stage fuel nozzle ports are vertical with incoming air direction, the flame
The main combustion stage fuel conduit on 12 heads of cylinder runs through outer 14 head of casing of burner inner liner, and main combustion stage fuel conduit input end and main combustion stage
17 outlet side of gas fuel pipe is connected, 17 inlet end of main combustion stage gas fuel pipe and 18 outlet side phase of main combustion stage fuel manifold
Even, outer 14 head of casing of the burner inner liner is respectively arranged with No.1 grade fuel conduit on duty and No. two grade fuel conduits on duty, and one
Number grade fuel conduit on duty is connected with No.1 16 outlet side of grade gas fuel pipe on duty, No.1 grade gas fuel pipe 16 on duty
Inlet end is connected with No.1 19 outlet side of grade fuel manifold on duty, No. two grade fuel conduits on duty and No. two grade gaseous fuels on duty
22 outlet side of pipeline is connected, No. two 22 inlet ends of grade gas fuel pipe on duty and No. two 21 outlet side phases of grade fuel manifold on duty
Even, No.1 grade fuel conduit on duty, No. two grade fuel conduits and main combustion stage fuel conduit on duty are by being installed on combustion gas wheel
Flange 15 on machine shell is fixedly mounted on head of combustion chamber, 18, No. two grade fuel manifolds on duty of the main combustion stage fuel manifold
21 and No.1 19 inlet end of grade fuel manifold on duty be connected with gas source, and main combustion stage fuel manifold 18, No.1 grade fuel on duty
General pipeline 19 and No. two grade fuel manifolds 21 on duty are mounted on pipeline support 20, and pipeline support 20 is installed on compressor housings
On 1, the outlet side of burner inner liner 12 is connect by support case 11 with nozzle ring, 27 one end of diffuser and compressor housings 1
Connection, the other end are fixed on burner inner liner 14 outlet section of outer casing, and the burner inner liner 12 and nozzle ring are collectively constituted and be vented out
Mouth 10 installs partition 8 in 13 tail portion of second level radial swirler, and combustion mixture guarantees to be tempered after 8 speedup of partition, fire
12 inner wall of flame cylinder is equipped with the conditioner 23 positioned at 8 tail portion one end of partition, can be used for adjusting 12 primary zone of burner inner liner sky
Throughput, to change 12 primary zone equivalent proportion of burner inner liner, in several blending holes 9 of 12 tail distribution of burner inner liner, the burner inner liner 12
Center line and engine centerline setting angle be 0 °.
The No.1 grade fuel nozzle ports 2 on duty and No. two 3 internal diameters of grade fuel nozzle ports on duty are 0.1-0.5mm, and number is
16-24.
The No.1 main fuel spout 4 and No. two 5 internal diameters of main fuel spout are 0.1-0.5mm, and number is 16-24.
The 12 primary zone equivalent proportion of burner inner liner is the poor oil firing of 0.6-0.8, it has lean combustion premix lean combustion concurrently simultaneously and directly sprays
Two-fold advantage, the temperature of overall reduction main combustion stage, and 12 primary zone ignition temperature of burner inner liner be lower than 1800K, effectively inhibition NOX
Especially thermal NOXGeneration.
The operation principle of the present invention is that:
Using center fractional combustion mode, the gaseous fuel flowed out from source outlet respectively enters main combustion stage fuel manifold
18, No.1 grade fuel manifold 19 on duty and No. two grade fuel manifolds 21 on duty, the gas in main combustion stage fuel manifold 18 is by master
Combustion grade gas fuel pipe 17 and main combustion stage fuel conduit enter main combustion stage, and the gas into main combustion stage is fired by No.1 main combustion stage
Expect in spout 4 and the direct axial and radial cavity for injecting main mixed zone of No. two main combustion stage fuel nozzle ports 5, in main mixed zone internal combustion
Material and from the air that second level radial swirler 13 is come in uniformly blend after by 8 speedup of partition, it is fast that burning mixture can be improved
Degree, guarantee are not tempered, it is ensured that safety, burning mixture enter 12 head of burner inner liner, uniform flammable premixed gas
Body burns in a combustion chamber, forms the primary zone of poor premix, realizes the low emission of combustion chamber；In No.1 grade fuel manifold 19 on duty
Gaseous fuel enter grade on duty, while No. two by No.1 grade gas fuel pipe 16 on duty and No.1 grade fuel conduit on duty
Gaseous fuel in grade fuel manifold 21 on duty passes through No. two grade gas fuel pipes 22 on duty and No. two grade fuel conduits on duty
Also enter grade on duty, the gaseous fuel into grade on duty passes through No.1 grade fuel nozzle ports 2 on duty and No. two grade fuel nozzle ports 3 on duty
Into combustion chamber, it is diffused+premixed combustion in the combustion chamber, it is true by using diffusion combustion and the efficient combination of premixed combustion
Protect combustion stability with higher in wide equivalence ratio range；Grade and main combustion stage on duty formed in combustion zone two it is coaxial
Ring rotation jet stream, the fuel of grade and main combustion stage on duty are complete in the premixed combustion area for being located at combustion zone on duty and outside respectively
At the function of combustion zone on duty is to improve to start and low-power operating condition down-firing, starting, raising combustion stability；Premixed combustion
The function in area is to form equally distributed premix gaseous mixture, realizes low emissions combustion；Four bursts of entrance of air point in burner inner liner 12
Combustion chamber, first strand is air needed for cooling head of combustion chamber and burner inner liner 12, and second strand of air flows through primary axis to eddy flow
Device 6 and second level radial swirler 13 enter the combustion zone of burner inner liner 12, and third stock air is by the air positioned at 12 head of burner inner liner
Regulating device 23 enters the primary zone of combustion chamber, at the equivalent proportion for meeting combustion zone when using different value heat fuels
In low emission range, the 4th strand of air enters combustion chamber by the blending hole 9 for being located at 12 tail portion of burner inner liner, makes combustor exit temperature
Meet turbine inlet requirement, gaseous fuel passes through full combustion in combustion chamber flame drum 12,12 tail portion of burner inner liner with through mixing
Turbine acting is eventually entered into after the air blending cooling that mixed hole 9 enters.
Embodiment 2
As shown in Figure 5 and Figure 6, the outer casing 14 of the burner inner liner is located at 7 outer ring portion of isolating high-pressure ignitor and close to primary axis
Be uniformly arranged in the circumferential direction No. two grade fuel nozzle ports 3 on duty to 6 one end of cyclone, and No. two 3 axis of grade fuel nozzle ports on duty with
6 axial angle of level-one axial swirler is 60 °.Other structures and connection type are same as Example 1.
Embodiment 3
The center line and engine centerline setting angle of the burner inner liner 12 are 30 °.Other structures and connection type with
Embodiment 1 or embodiment 2 are identical.
Claims (7)
1. a kind of gas turbine low discharging burning chamber of using gas fuel, it is characterised in that: the head of combustion chamber includes pressing
According to the grade and main combustion stage on duty of concentric manner arrangement, and grade on duty, at center, main combustion stage is arranged in grade periphery on duty, described on duty
Grade includes that level-one axial swirler and grade fuel nozzle ports on duty, level-one axial swirler are installed on the centre bore of flame tube head
Interior, the outer casing of burner inner liner is mounted on outside burner inner liner, and burner inner liner and the outer casing of burner inner liner are coaxially disposed, flame drum outer wall and fire
Air duct is formed between the outer casing inner wall of flame cylinder, and high pressure spot is installed at the outer casing of the burner inner liner and level-one cyclone center
Firearm, casing is at level-one axial swirler and level-one cyclone tail portion is all provided with outside for casing head or burner inner liner outside for burner inner liner
Grade fuel nozzle ports on duty are equipped with, the main combustion stage includes second level radial swirler, main combustion stage fuel nozzle ports and partition, and second level is radial
Cyclone is installed on flame tube head, has been uniformly arranged in the circumferential direction main combustion respectively at the head and center of second level radial swirler
Grade fuel nozzle ports, the main combustion stage fuel conduit of the flame tube head run through the outer casing head of burner inner liner, and main combustion stage cartridge
Road input end is connected by main combustion stage gas fuel pipe with main combustion stage fuel manifold outlet side, the outer casing head of the burner inner liner
It is respectively arranged with No.1 grade fuel conduit on duty and No. two grade fuel conduits on duty, No.1 grade fuel conduit on duty passes through No.1 value
Class's gas fuel pipe is connected with No.1 grade fuel manifold on duty outlet side, and No. two grade fuel conduits on duty are on duty by No. two
Grade gas fuel pipe is connected with No. two grade fuel manifold on duty outlet sides, No.1 grade fuel conduit on duty, No. two it is on duty
Grade fuel conduit and main combustion stage fuel conduit by flange are fixedly mounted on head of combustion chamber, the main combustion stage fuel manifold, two
Number grade fuel manifold on duty and No.1 grade fuel manifold inlet end on duty are connected with gas source, and main combustion stage fuel manifold, No.1
Grade fuel manifold on duty and No. two grade fuel manifolds on duty are mounted on pipeline support, and pipeline support is installed on compressor casing
On body, the outlet side of burner inner liner is connect by support case with nozzle ring, and diffuser one end is connected with compressor housings, separately
One end is fixed on the outer casing outlet section of burner inner liner, and the burner inner liner and nozzle ring collectively constitute air exit, in second level diameter
Partition is installed to cyclone tail portion, burner inner liner inner wall is equipped with the conditioner positioned at partition tail portion one end, in burner inner liner
Several blending holes of tail distribution.
2. a kind of gas turbine low discharging burning chamber of using gas fuel according to claim 1, it is characterised in that: institute
It states No.1 grade fuel nozzle ports on duty and No. two grade fuel nozzle ports internal diameters on duty is 0.1-0.5mm, number is 16-24.
3. a kind of gas turbine low discharging burning chamber of using gas fuel according to claim 1, it is characterised in that: institute
The angle stated between No.1 grade fuel nozzle ports axis on duty and level-one axial swirler axis is 0-60 °.
4. a kind of gas turbine low discharging burning chamber of using gas fuel according to claim 1, it is characterised in that: institute
The angle stated between the axis and level-one axial swirler axis of No. two grade fuel nozzle ports on duty is 0-60 °.
5. a kind of gas turbine low discharging burning chamber of using gas fuel according to claim 1, it is characterised in that: institute
It states No.1 main fuel spout and No. two main fuel nozzle pluggages is 0.1-0.5mm, number is 16-24.
6. a kind of gas turbine low discharging burning chamber of using gas fuel according to claim 1, it is characterised in that: institute
The center line and engine centerline setting angle for stating burner inner liner are 0-30 °.
7. a kind of gas turbine low discharging burning chamber of using gas fuel according to claim 1, it is characterised in that: fire
Flame cylinder primary zone equivalent proportion be 0.6-0.8 poor oil firing, it have concurrently simultaneously lean combustion premix lean combustion directly spray it is dual excellent
Point, the temperature of overall reduction main combustion stage, and burner inner liner primary zone ignition temperature are lower than 1800K, effectively inhibition NOXEspecially heating power
Type NOXGeneration.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910341915.1A CN110131750B (en) | 2019-04-26 | 2019-04-26 | Gas turbine low-emission combustion chamber using gas fuel |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910341915.1A CN110131750B (en) | 2019-04-26 | 2019-04-26 | Gas turbine low-emission combustion chamber using gas fuel |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110131750A true CN110131750A (en) | 2019-08-16 |
| CN110131750B CN110131750B (en) | 2020-08-11 |
Family
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Cited By (9)
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| CN110779041A (en) * | 2019-10-09 | 2020-02-11 | 东方电气集团东方汽轮机有限公司 | Nozzle device of combustion chamber of gas turbine |
| CN110836383A (en) * | 2019-11-15 | 2020-02-25 | 中国科学院工程热物理研究所 | High-temperature flue gas generator and control method thereof |
| JP2021055644A (en) * | 2019-10-01 | 2021-04-08 | 三菱パワー株式会社 | Gas turbine combustor and operation method thereof |
| CN112815356A (en) * | 2020-12-31 | 2021-05-18 | 哈尔滨工程大学 | Self-adaptive adjustable hydrogen-rich fuel low-emission micro-flame combustion chamber |
| CN113847622A (en) * | 2020-06-25 | 2021-12-28 | 通用电气公司 | Combustor assembly for a gas turbine engine |
| CN114413283A (en) * | 2021-12-28 | 2022-04-29 | 北京动力机械研究所 | Integrated structure of cyclone sleeve and head plate |
| CN114992672A (en) * | 2022-06-11 | 2022-09-02 | 江苏中科能源动力研究中心 | Micro-premixing type gas turbine combustion chamber |
| CN116293815A (en) * | 2023-03-22 | 2023-06-23 | 无锡明阳氢燃动力科技有限公司 | Low nitrogen hydrogen combustion chamber structure |
| CN114992672B (en) * | 2022-06-11 | 2024-04-26 | 江苏中科能源动力研究中心 | Micro-premixing type combustion chamber of gas turbine |
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| JP2021055644A (en) * | 2019-10-01 | 2021-04-08 | 三菱パワー株式会社 | Gas turbine combustor and operation method thereof |
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| CN110836383B (en) * | 2019-11-15 | 2021-10-26 | 中国科学院工程热物理研究所 | High-temperature flue gas generator and control method thereof |
| CN110836383A (en) * | 2019-11-15 | 2020-02-25 | 中国科学院工程热物理研究所 | High-temperature flue gas generator and control method thereof |
| CN113847622A (en) * | 2020-06-25 | 2021-12-28 | 通用电气公司 | Combustor assembly for a gas turbine engine |
| CN113847622B (en) * | 2020-06-25 | 2023-07-21 | 通用电气公司 | Combustor assembly for a gas turbine engine |
| CN112815356A (en) * | 2020-12-31 | 2021-05-18 | 哈尔滨工程大学 | Self-adaptive adjustable hydrogen-rich fuel low-emission micro-flame combustion chamber |
| CN112815356B (en) * | 2020-12-31 | 2022-07-15 | 哈尔滨工程大学 | Self-adaptive adjustable hydrogen-rich fuel low-emission micro-flame combustion chamber |
| CN114413283A (en) * | 2021-12-28 | 2022-04-29 | 北京动力机械研究所 | Integrated structure of cyclone sleeve and head plate |
| CN114992672A (en) * | 2022-06-11 | 2022-09-02 | 江苏中科能源动力研究中心 | Micro-premixing type gas turbine combustion chamber |
| CN114992672B (en) * | 2022-06-11 | 2024-04-26 | 江苏中科能源动力研究中心 | Micro-premixing type combustion chamber of gas turbine |
| CN116293815A (en) * | 2023-03-22 | 2023-06-23 | 无锡明阳氢燃动力科技有限公司 | Low nitrogen hydrogen combustion chamber structure |
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