CN106338084A - The gas turbine combustion chamber - Google Patents
The gas turbine combustion chamber Download PDFInfo
- Publication number
- CN106338084A CN106338084A CN201611039147.7A CN201611039147A CN106338084A CN 106338084 A CN106338084 A CN 106338084A CN 201611039147 A CN201611039147 A CN 201611039147A CN 106338084 A CN106338084 A CN 106338084A
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- China
- Prior art keywords
- combustion chamber
- nozzle
- gas outlet
- hollow body
- cylindrical portion
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Classifications
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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
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
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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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
Abstract
A gas turbine combustion chamber includes an annular flame tube that forms an annular combustion chamber defining an axial direction and a circumferential direction around the axial direction, and a plurality of nozzles disposed within the annular combustion chamber. The nozzles are arranged uniformly in the circumferential direction, the nozzles are configured to inject a mixture of gas and air into the combustion chamber, each nozzle is provided with at least one mixture outlet for injecting the mixture toward an adjacent nozzle, and a flame blocking structure between each two adjacent nozzles is arranged for preventing a flame generated by the mixture from being directly sprayed onto the adjacent nozzles. The gas turbine combustion chamber structure in the present invention is simple and novel, which can reduce the damage to the components of the combustion chamber to the maximum extent, improve the combustion efficiency of the combustion chamber and reduce the production cost.
Description
Technical field
The present invention relates to gas turbine, more particularly to a kind of gas-turbine combustion chamber.
Background technology
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 and is burnt, and is formed steady
Fixed flow field and combustion field.However, existing gas-turbine combustion chamber nozzle has combustion gas and air mixing not in premixed channel
Uniform problem, is so easily caused combustion instability, produces more pollutant effulent, and premixed channel is possible to occur back
Fire, to nozzle and be arranged on the elements such as valuable cyclone in premixed channel and cause ablation and breaking-up.
It is possible to meeting is because in nozzle during nozzle in gas-turbine combustion chamber is in jet flames to combustion chamber
Hypertonia, cause the flame that nozzle ejects can be directly injected to burner inner liner inwall or interior set on components and parts, even
It is directly injected on adjacent nozzle, serious ablation and damage are caused to it, substantially reduce gas-turbine combustion chamber and its spray
The service life of mouth.
Therefore, be badly in need of a kind of rationally effectively gas-turbine combustion chamber structure and nozzle arrangements come to solve set forth above extremely
A kind of few problem.
Content of the invention
In view of this, the present invention proposes a kind of gas-turbine combustion chamber to solve at least one problem set forth above.
The present invention proposes a kind of gas-turbine combustion chamber, comprising: annular flame tube, and described annular flame tube forms annular combustion
Burn chamber, described annular firing chamber defines one axially with around described axial circumferencial direction；And it is arranged on described annular firing
Some nozzles in chamber, described some nozzles are evenly distributed along described circumferencial direction, described nozzle be used for being blended with combustion gas and
The gaseous mixture of air sprays into described combustion chamber；Each nozzle is provided with least one for spraying gaseous mixture towards an adjacent nozzle
Mixed gas outlet, a flame barrier structure is set between the adjacent nozzle of each two, for stoping described gaseous mixture from producing
Raw flame is directly injected on described adjacent nozzle.
In one embodiment, it is mixed that two mixed gas outlets of each nozzle setting, and described two mixed gas outlet define
Close gas jet in opposite direction.
In one embodiment, described flame barrier structure includes hollow body, and described hollow body has internal cavities, described sky
The wall portion of heart body is provided with some through holes in fluid communication with described internal cavities, and an axial end portion of described hollow body is fixed on institute
State on burner inner liner, the cooling air for receiving outside described burner inner liner makes described cooling air be full of described internal cavities.
In one embodiment, another axial end portion of described hollow body be provided with fluid communication with described internal cavities some
Through hole.
In one embodiment, described hollow body have one towards an adjacent nozzle blocking surface, described blocking surface be arc
Shape face.
In one embodiment, described hollow body is a hollow cylinder or Elliptic Cylinder, described cylinder or Elliptic Cylinder
Have parallel to described axial center line.
In one embodiment, in a radial section, the center of described hollow body and described nozzle are centrally located at same
On individual circle.
In one embodiment, each nozzle includes: main burner, and described main burner is included along described axially extended main burner
Cylindrical portion, described main burner cylindrical portion end is blind end, and described main burner cylindrical portion has an internal blast tube and passes through
Wear the gas outlet of described main burner cylindrical portion；Outer nozzle wall, described outer nozzle wall includes outer nozzle wall cylindrical portion, described nozzle
Outer wall cylindrical portion is diametrically spaced around described main burner cylindrical portion and with described main burner cylindrical portion thus in described main jet
Form annular air channel, described mixed gas outlet runs through described outer nozzle wall cylinder between mouth cylindrical portion and outer nozzle wall cylindrical portion
Shape portion and diametrically corresponding with described gas outlet so that in combustion gas and described air duct that described gas outlet sprays
Air mixing after from described mixed gas outlet spray.
In one embodiment, each nozzle has two mixed gas outlets, and each mixed gas outlet is towards a corresponding phase
Adjacent flame barrier structure sprays gaseous mixture, and each mixed gas outlet has a center line, and each flame barrier structure includes
Heart body, described hollow body has one with described axially in parallel center line, and the center line of each mixed gas outlet is passed through and mixed with this
Close the center line that gas exports corresponding hollow body.
In one embodiment, described outer nozzle wall has outer nozzle wall end, and described outer nozzle wall end is provided with end and leads to
Described in Kong Bingyu, the blind end of main burner cylindrical portion is spaced apart in the axial direction.
In sum, the invention provides a kind of gas-turbine combustion chamber and its nozzle, nozzle includes main burner and cincture
The outer nozzle wall of main burner setting, main burner forms blast tube, and outer nozzle wall and main burner are diametrically spaced with the two
Between formed air duct, on main burner arrange gas outlet, on outer nozzle wall arrange gaseous mixture corresponding with gas outlet go out
Mouthful so that gas outlet spray combustion gas mix with the air in air duct after from mixed gas outlet ejection, each nozzle
The injection direction of mixed gas outlet is towards adjacent nozzle.The present invention nozzle arrangements design ingenious, can preferably air mixture and
Air, and gaseous mixture is spurted in the combustion chamber of combustion chamber burnt, it is to avoid the infringement to flame tube wall for the thermal-flame.
Secondly, burning interior also sets up some flame barrier structures, flame barrier structure setting between adjacent two nozzles, with stop from
The flame that nozzle ejects is directly injected on adjacent nozzle and it is produced with damage, extends the service life of combustion chamber.This
Bright gas-turbine combustion chamber structure is simple, novel, can at utmost reduce the damage to each element in combustion chamber, improves combustion
Burn the efficiency of combustion of room, reduce production cost.
Brief description
Fig. 1 is the schematic top plan view of the combustion chamber of one embodiment of the invention an along lateral cross section.
Fig. 2 is the flame drum outer wall of combustion chamber in Fig. 1 and the structural representation of inwall.
Fig. 3 is the side view of the nozzle of combustion chamber in Fig. 1.
Fig. 4 is the longitudinal sectional view of nozzle in Fig. 3.
Fig. 5 is the schematic top plan view of the combustion chamber of another embodiment of the present invention an along lateral cross section.
Fig. 6 is the structural representation of the flame drum outer wall of combustion chamber in Fig. 5.
Fig. 7 is the flame drum outer wall of combustion chamber in Fig. 5 and the structural representation of inwall.
Fig. 8 be in Fig. 5 combustion chamber along the elevational schematic view of a lateral cross section.
Fig. 9 is the longitudinal sectional view of the hollow body structure of combustion chamber in Fig. 5.
Figure 10 is the fuel gas flow of the combustion chamber of another embodiment of the present invention and the simplification of air draught formation quadrangle tangential circle
Schematic diagram.
Figure 11 is the structural representation of another embodiment of nozzle arrangements in above-described embodiment.
Figure 12 is the enlarged diagram of the part-structure of nozzle in Figure 11.
Figure 13 is the schematic top plan view of nozzle arrangements in Figure 11.
Specific embodiment
Before describing the embodiments in more detail it should be understood that the invention is not restricted in the application institute hereafter or in accompanying drawing
The detailed construction of description or arrangement of elements.The embodiment that the present invention can realize for alternate manner.Furthermore, it is to be understood that this paper institute
The wording using and term are solely for describing purposes, should not being construed as limiting property explain." inclusion " used herein, "comprising",
The similar wording such as " having " means and comprises items listed thereafter, its equivalent and other additional things.Particularly, work as description
When " certain element ", the present invention does not limit the quantity of this element as one it is also possible to include multiple.
As depicted in figs. 1 and 2, the present invention provides a kind of gas-turbine combustion chamber, and described combustion chamber includes annular flame tube
10 and some nozzles 12, annular flame tube 10 forms annular firing chamber 14, and some nozzles 12 are arranged in annular firing chamber 14, if
Dry nozzle 12 is used for being blended with combustion gas and the gaseous mixture of air sprays in annular firing chamber 14.More specifically, in shown reality
Apply in example, annular flame tube 10 includes thering is radially spaced outer ring burner inner liner 16 and inner ring burner inner liner 18, and combustion chamber 14 is formed
Between inner ring burner inner liner 18 and outer ring burner inner liner 16.
Annular firing chamber 14 defines one axially with around described axial circumferencial direction, and some nozzles 12 are fixed on burner inner liner
On 10 end wall, along the arrangement of described circumferencial direction and along described axially extending.Preferably, some nozzles 12 are along described circumference side
To evenly distributed.
As shown in Figure 3 and Figure 4, nozzle 12 includes main burner 20 and the outer nozzle wall 22 around main burner 20 setting, main jet
Mouth 20 forms an internal blast tube 24 and the gas outlet 26 with internal blast tube 24 fluid communication, outer nozzle wall 22 with
Form air duct 28 between main burner 20, gas outlet 26 is in fluid communication with air duct 28, on outer nozzle wall 22 setting with
At least one mixed gas outlet 30 of air duct 28 fluid communication so that from gas outlet 26 spray combustion gas and air duct
Spray from mixed gas outlet 30 after air mixing in 28.
Specifically, the main burner that main burner 20 includes main burner cylindrical portion 32 and is located at main burner cylindrical portion 32 end
End 34, wherein main burner cylindrical portion 32 define internal blast tube 24, and internal blast tube 24 is along described axially extending, main jet
The fuel gas inlet end of mouth cylindrical portion 32 is connected with outer combustion gas conveyance conduit, to receive external combustion gas.Main burner end 34 is envelope
Closed end, so that the combustion gas in blast tube 24 can only spray from gas outlet 26.
In an illustrated embodiment, gas outlet 26 runs through main burner cylindrical portion 32 and arranges, and the quantity of gas outlet 26 is
Two, two gas outlets 26 are respectively facing the direction setting of adjacent nozzle, and gas outlet 26 is set be located proximate to main jet
Mouth end 34, i.e. described blind end.
The outer nozzle wall that outer nozzle wall 22 includes outer nozzle wall cylindrical portion 36 and is located at outer nozzle wall cylindrical portion 36 end
End 38, outer nozzle wall cylindrical portion 36 is diametrically spaced around main burner 20 and with main burner 20, thus main burner 20 with
Form air duct 28, air duct 28 is in fluid communication with gas outlet 26 between outer nozzle wall 22.In an illustrated embodiment,
Outer nozzle wall end 38 is spaced apart with main burner end 34 in described axial direction, and therefore, air duct 28 also includes outer nozzle wall
The space being formed between end 38 and main burner end 34.
Each nozzle 12 is provided with least one mixed gas outlet 30, namely is formed and air in outer nozzle wall cylindrical portion 36
At least one mixed gas outlet 30 of passage 28 fluid communication.Specifically, mixed gas outlet 30 runs through outer nozzle wall cylindrical portion 36
And diametrically corresponding with gas outlet 26, so that the air in the combustion gas that gas outlet 26 sprays with air duct 28 mixes
Spray from mixed gas outlet 30 after conjunction.
In an illustrated embodiment, the quantity of the mixed gas outlet 30 outer nozzle wall cylindrical portion 36 being formed is two, and
And two mixed gas outlets 30 are diametrically corresponding with two gas outlets 26 respectively, so that spraying from two gas outlets 26
Combustion gas mix with the air in air duct 28 after spray from two mixed gas outlets 30 respectively.
Each mixed gas outlet 30 defines a gaseous mixture injection direction, and in an illustrated embodiment, each nozzle 12 is arranged
Two gas outlets 26 and two mixed gas outlets 30, two gas outlets 26 are respectively with two mixed gas outlets 30 diametrically
Corresponding, and the gaseous mixture injection direction of two mixed gas outlet 30 definition is contrary.In the present embodiment, described gaseous mixture injection direction
Approximately along described circumferencial direction.Specifically, described gaseous mixture injection direction is the direction towards an adjacent nozzle 12, because
This, the gaseous mixture injection direction of two mixed gas outlets 30 of each nozzle 12 is respectively facing two nozzles adjacent with this nozzle 12
Direction.
In an illustrated embodiment, outer nozzle wall end 38 is provided with end through hole 40, and end through hole 40 is led to air simultaneously
Road 28 and annular firing chamber 14 are in fluid communication, and therefore, the air in air duct 28 can flow to annular firing from end through hole 40
In chamber 14, to form the overall flow of air in air duct 28, carry out wall 36 and the cooling of end 38.
In an illustrated embodiment, the gas outlet 26 that nozzle 12 is formed and mixed gas outlet 30 are disposed as circle, and
The aperture of gas outlet 26 is less than the aperture of mixed gas outlet 30, and the jet-flow that such gas outlet 26 is formed can pass through
Form the effect of injection air during mixed gas outlet 30, promote the mixing by the combustion gas of mixed gas outlet 30 and air, and then
Promote burning and the short flamed length that contracts.
As described above, the injection direction of the gaseous mixture ejecting from mixed gas outlet 30 is towards an adjacent nozzle 12
Direction, when flame pressure is larger, the flame that the gaseous mixture ejecting from mixed gas outlet 30 or gaseous mixture produce can
Can be directly injected on adjacent nozzle 12, so nozzle 12 can be produced with larger infringement so that nozzle 12 is easily damaged.For
Avoid the occurrence of this, in order to more steadily solve the above problems, the present invention has been carried out further to combustion chamber
Improve, and propose two kinds of embodiments.
Embodiment one:
As shown in figures 5-9, described combustion chamber is also included for stoping gaseous mixture or the flame of gaseous mixture generation from directly spraying
Some flame barrier structures on adjacent nozzle 12, specifically, arrange a fire between the adjacent nozzle of each two 12
Flame barrier structure.
As it was previously stated, each nozzle 12 arranges two mixed gas outlets 30, and the mixing of two mixed gas outlet 30 definition
Gas jet is in opposite direction.Refer to Fig. 5, the mixing gas jet side of the two relative mixed gas outlets 30 of arbitrary neighborhood two nozzle 12
To having an intersection point, described flame barrier structure setting in described point of intersection, to stop the gaseous mixture of mixed gas outlet 30 injection
The flame producing.
Described flame barrier structure includes a hollow body 42, and hollow body 42 has hollow body wall portion 44 and by hollow body wall
The internal cavities 46 that portion 44 is formed.Hollow body 42 is arranged along described axial direction, and an axial end portion of hollow body 42 is fixed on fire
On flame cylinder 10, specifically it is integrally fixed on that end wall being fixed with nozzle 12 of burner inner liner 10.This axial direction of hollow body 42
End is hatch frame, to connect with extraneous air, for receiving the cooling air outside burner inner liner 10, and then makes cooling empty
Gas is full of internal cavities 46.
As Fig. 9, another axial end portion 48 of hollow body 42 and hollow body wall portion 44 are equipped with and internal cavities 46 fluid phase
Logical some through holes.Using this loose structure, the air of the internal cavities 46 of hollow body 42 can pass through hollow body wall portion 44
With axial end portion 48, flame barrier structure is protected not to be burned out.The air of internal cavities 46 also can pass through hollow body wall portion simultaneously
44 and axial end portion 48 on through hole enter annular firing chamber 14 in so that the fuel gas buring in annular firing chamber 14 more fills
Point.
Hollow body 42 has the blocking surface towards adjacent nozzle 12, and described blocking surface is flame and is contacted with hollow body 42
Surface, the both sides along each hollow body of described circumferencial direction 42 are respectively provided with a nozzle 12, and therefore each hollow body 42 has two
Individual blocking surface.When the flame of wherein one nozzle 12 sprays towards another adjacent nozzle, its flame is ejected into hollow body 42
It is blocked on blocking surface.Because hollow body wall portion 44 is loose structure, the cooling air of hollow body internal cavities 46 can be worn
Cross the through hole of hollow body wall portion 44 and axial end portion 48 and formed on blocking surface and end outer surface and intercept air film, protection is hollow
Body 42 is not burned out.In the present embodiment, described blocking surface is designed as arcwall face, for example, hollow body 42 is designed as open circles
Cylinder 42.In other embodiments, hollow body 42 can also have other shapes, such as Elliptic Cylinder, cuboid, polyhedron etc.
Deng as long as the flame of wherein one nozzle can be stopped and is unlikely to be ejected into an adjacent nozzle.
Please continue to refer to Fig. 5, each nozzle 12 has two mixed gas outlets 30, and each mixed gas outlet 30 is towards a pair
The adjacent hollow body 42 injection gaseous mixture answered, each mixed gas outlet 30 has a center line, and hollow cylinder 42 has parallel
In described axial center line, the center line of each mixed gas outlet 30 passes through and this corresponding hollow body 42 of mixed gas outlet 30
Center line that is to say, that each hollow body 42 center line be located at adjacent two nozzles 12 two relative mixed gas outlets 30
Gaseous mixture injection direction, namely on the intersection point of its center line.
Refer to Fig. 8, in a radial section, the center of all hollow bodies 42 and all nozzles 12 are centrally located at same
On individual circle.Certainly, in other embodiments, hollow body 42 and nozzle 12 can also set in a circumferential direction otherwise
Put, be not necessarily positioned on same circle.
Embodiment two:
As shown in Figure 10, exemplified with a part of structure of annular flame tube 10, including outer ring burner inner liner 16, inner ring burner inner liner
18th, it is formed at the combustion chamber 14 between inner ring burner inner liner 18 and outer ring burner inner liner 16 and be arranged on some sprays in combustion chamber 14
Mouth.Each nozzle is provided with the first mixed gas outlet and the second mixed gas outlet, and each mixed gas outlet defines an injection direction.On
Stating annular flame tube 10 can be identical with the construction in previous embodiment with the construction of nozzle 12, therefore will not be described here.
It is described in detail below taking two nozzles of arbitrary neighborhood as a example.
Two nozzles of described arbitrary neighborhood include first jet 12a and second nozzle 12b, and first jet 12a includes
One mixed gas outlet 50 and the second mixed gas outlet 52, second nozzle 12b includes the first mixed gas outlet 54 and the second gaseous mixture
Outlet 56.Wherein first mixed gas outlet 50 of first jet 12a is located at the side towards second nozzle 12b, second nozzle 12b
The second mixed gas outlet 56 be located at the side towards first jet 12a.
Outer ring burner inner liner 16 is provided with the first air stream injection structure 62, and the first air stream injection structure 62 is used for spraying direction
First air stream 66 of inner ring burner inner liner 18, the first air stream 66 defines one first airflow direction.Inner ring burner inner liner 18 is provided with
Second air stream injection structure 64, the second air stream injection structure 64 is used for the second air stream towards outer ring burner inner liner 16 for the injection
68, the second air stream 68 defines one second airflow direction.
In a radial section, the first mixed gas outlet 50 definition one first injection direction 58 of first jet 12a, first
Injection direction 58 is towards inner ring burner inner liner 18 and one of them lateral deviation of outer ring burner inner liner 16 from first jet 12a and second nozzle
Line l between the center of 12b.Second mixed gas outlet 56 of second nozzle 12b defines one second injection direction 60, the second spray
Penetrate direction 60 and deviate first jet 12a and second nozzle 12b towards inner ring burner inner liner 18 and outer ring burner inner liner 16 wherein opposite side
Center between line l.
It should be appreciated that the injection direction of above-mentioned first air stream 66 is the first airflow direction, the second air stream
68 injection direction as the second airflow direction, mixed airflow or flame are along first mixed gas outlet 50 of first jet 12a
The direction spraying as the first injection direction 58, mixed airflow or flame spray along second mixed gas outlet 56 of second nozzle 12b
The direction going out is the second injection direction 60.
First mixed gas outlet 50 of first jet 12a, second mixed gas outlet 56 of second nozzle 12b, the first air
Stream injection structure 62 and the second air stream injection structure 64 are in quadrangle tangential circle arrangement.In other words, spray along the first injection direction 58
The mixed airflow penetrated or flame, empty along the mixed airflow of the second injection direction 60 injection or flame, the first air stream 66 and second
Air-flow 68 surrounds in quadrangle tangential circle.
In embodiment as shown in Figure 10, the first injection direction 58 deviates first jet 12a towards outer ring burner inner liner 16
Line l and the center of second nozzle 12b between, the first injection direction 58 deviates the circle of first jet 12a and second nozzle 12b
The angle of the line l between the heart is 1 ° -15 °.Second injection direction 60 deviates first jet 12a and the towards inner ring burner inner liner 18
Line l between the center of circle of two nozzle 12b, the second injection direction 60 deviate first jet 12a and second nozzle 12b center it
Between line l angle be 1 ° -15 °.
It should be appreciated that in other embodiments, according to design requirement, the first injection direction 58 can also be towards inner ring
Burner inner liner 18 deviates the line l between first jet 12a and the center of circle of second nozzle 12b, and the second injection direction 60 can also court
Deviate the line l between first jet 12a and the center of circle of second nozzle 12b to outer ring burner inner liner 16, as long as can make along first
Injection direction 58 injection mixed airflow or flame, along the second injection direction 60 injection mixed airflow or flame, the first air
Stream 66 and the second air stream 68 surround the air-flow of formation in quadrangle tangential circle, and the present invention does not limit to this.
In an illustrated embodiment, the first air stream injection structure 62 is one or more on outer ring burner inner liner 16 for being located at
First pore 62, the pressure-air outside burner inner liner is sprayed towards inner ring burner inner liner into combustion chamber 14 by this first pore 62
Penetrate this first air stream 66.Similarly, the second air stream injection structure 64 is one or more on inner ring burner inner liner 18 for being located at
Second pore 64, the pressure-air outside burner inner liner passes through this second pore 64 and sprays towards outer ring burner inner liner into combustion chamber 14
This second air stream 68.Additionally, inner ring burner inner liner 18 and outer ring burner inner liner 16 are provided with some Cooling Holes running through, so that outward
Portion's air can enter in combustion chamber 14 in burner inner liner wall formation air film in cooled hole, intercepts thermal-flame.
In the present embodiment, the aperture of the first pore 62 and the second pore 64 is more than the aperture of Cooling Holes, its concrete numerical value root
According to aerodynamic parameter design.
The carrying out practically principle of described quadrangle tangential circle is: first mixed gas outlet 50 of first jet 12a spray along the
The first flame that one injection direction 58 advances is intersected with the first air stream 66 spraying from the first air stream injection structure 62, and first
Air stream 66 can change the first flame direct of travel be the first airflow direction, due to the first flame have in itself certain
Along the traveling momentum of the first injection direction 58, therefore two strands air-flows are advanced along a curved path after intersecting.The of second nozzle 12b
The second flame advancing along the second injection direction 60 that two mixed gas outlet 56 sprays sprays with from the second air stream injection structure 64
The second air stream 68 going out intersects, and the direct of travel that the second air stream 68 can change the second flame is the second airflow direction,
Because the second flame has certain traveling momentum along the second injection direction 60 in itself, therefore two strands air-flows intersect after along another
Curved path is advanced.Two curved paths surround formation one quadrangle tangential circle path, in the first air stream 66 and the second air stream 68
Under effect, mixed air-flow circulates along this quadrangle tangential circle path, and the centre position between adjacent nozzle forms eddy flow, effectively keeps away
Exempt from the flame that mixed gas outlet ejects to be directly injected on adjacent nozzle 12.Meanwhile, this eddy flow is equivalent to shorter
Axial space in elongated the length of flame, hence in so that burning is more abundant, discharge more preferably, also makes the axial chi of combustion chamber
Very little can reduce further, final gas turbine can also have less axial dimension.
As figs 11-13, so that combustion gas and air can more uniformly mix, in the air duct 28 of nozzle 12
One cyclone 74 is set, so that air in air inlet passage 28 forms eddy flow, increases air flow intensity so as to can
Quickly and evenly mixing with combustion gas, improving efficiency of combustion, thus reducing the discharge of nitrogen oxides.In an illustrated embodiment, revolve
The some blades 76 on outer peripheral face that stream device 74 includes be arranged on main burner cylindrical portion 32, the inner side of blade 76 is fixedly connected on master
On the outer peripheral face of nozzle cylindrical portion 32, the outside of blade 76 is fixedly attached on the inner peripheral surface of outer nozzle wall cylindrical portion 36.At it
In its non-illustrated embodiment, blade can also only with the inner peripheral surface of the outer peripheral face of described main burner cylindrical portion and outer nozzle wall its
One of be fixedly connected.
It should be appreciated that cyclone 74 is embodied as arc strip blade 76 in the present embodiment, in other embodiments,
Cyclone 74 can also implement into other structures, as long as the air in air duct can be made to form eddy flow.
In sum, the invention provides a kind of gas-turbine combustion chamber and its nozzle, nozzle includes main burner and cincture
The outer nozzle wall of main burner setting, main burner forms blast tube, and outer nozzle wall and main burner are diametrically spaced with the two
Between formed air duct, on main burner arrange gas outlet, on outer nozzle wall arrange gaseous mixture corresponding with gas outlet go out
Mouthful so that gas outlet spray combustion gas mix with the air in air duct after from mixed gas outlet ejection, each nozzle
The injection direction of mixed gas outlet is towards adjacent nozzle.The present invention nozzle arrangements design ingenious, can preferably air mixture and
Air, and gaseous mixture is spurted in the combustion chamber of combustion chamber burnt, it is to avoid the infringement to flame tube wall for the thermal-flame.
Secondly, in certain embodiments, burning interior also sets up some flame barrier structures, and flame barrier structure setting is in adjacent two sprays
Between mouth, to stop to be directly injected to adjacent nozzle from the flame that nozzle ejects, it is produced with damage, extend combustion chamber
Service life.Again, in certain embodiments, combustion chamber also can arrange air stream on outer ring burner inner liner and inner ring burner inner liner
Injection structure, air stream injection structure is configured to air stream and two adjacent two nozzles the relative mixed gas outlets that it ejects
The flame ejecting forms quadrangle tangential circle, and air stream can change the direct of travel of jet flames, and then follows along described quadrangle tangential circle
Ring operates, and is prevented effectively from jet flames and combustion chamber and nozzle is caused damage, improves the fuel gas buring efficiency in combustion chamber.This
Bright gas-turbine combustion chamber structure is simple, novel, can at utmost reduce the damage to each element in combustion chamber, improves combustion
Burn the efficiency of combustion of room, reduce production cost.
Concepts described herein may be embodied to other forms in the case of without departing from its spirit and characteristic.Disclosed
Specific embodiment should be considered exemplary rather than restricted.Therefore, the scope of the present invention is by appended claim,
Rather than be determined according to these descriptions before.Any change in the letter of claim and equivalency range is all
The scope of these claims should be belonged to.
Claims (10)
1. a kind of gas-turbine combustion chamber, comprising:
Annular flame tube, described annular flame tube forms annular firing chamber, and described annular firing chamber defines one axially with around institute
State axial circumferencial direction；And
It is arranged on some nozzles in described annular firing chamber, described some nozzles are evenly distributed along described circumferencial direction, described
Nozzle is used for being blended with combustion gas and the gaseous mixture of air sprays into described combustion chamber；
It is characterized in that, each nozzle be provided with least one for towards an adjacent nozzle injection gaseous mixture gaseous mixture go out
Mouthful, a flame barrier structure is set between the adjacent nozzle of each two, direct for stoping the flame that described gaseous mixture produces
It is ejected on described adjacent nozzle.
2. gas-turbine combustion chamber as claimed in claim 1 it is characterised in that each nozzle arrange two mixed gas outlets,
And the gaseous mixture injection direction of described two mixed gas outlet definition is contrary.
3. gas-turbine combustion chamber as claimed in claim 2 is it is characterised in that described flame barrier structure includes hollow body,
Described hollow body has internal cavities, and the wall portion of described hollow body is provided with some through holes in fluid communication with described internal cavities,
One axial end portion of described hollow body is fixed on described burner inner liner, and the cooling air for receiving outside described burner inner liner makes
Described cooling air is full of described internal cavities.
4. gas-turbine combustion chamber as claimed in claim 3 is it is characterised in that another axial end portion of described hollow body is provided with
Some through holes in fluid communication with described internal cavities.
5. gas-turbine combustion chamber as claimed in claim 3 it is characterised in that described hollow body to have one adjacent towards one
The blocking surface of nozzle, described blocking surface is arcwall face.
6. gas-turbine combustion chamber as claimed in claim 3 is it is characterised in that described hollow body is a hollow cylinder or ellipse
Cylinder, described cylinder or Elliptic Cylinder have parallel to described axial center line.
7. gas-turbine combustion chamber as claimed in claim 6 is it is characterised in that in a radial section, described hollow body
Center and described nozzle are centrally located on same circle.
8. gas-turbine combustion chamber as claimed in claim 1 is it is characterised in that each nozzle includes:
Main burner, described main burner includes along described axially extended main burner cylindrical portion, and described main burner cylindrical portion end is
Blind end, described main burner cylindrical portion has an internal blast tube and the gas outlet running through described main burner cylindrical portion；
Outer nozzle wall, described outer nozzle wall includes outer nozzle wall cylindrical portion, and described outer nozzle wall cylindrical portion is around described main burner
Cylindrical portion and be diametrically spaced thus in described main burner cylindrical portion and outer nozzle wall cylindrical portion with described main burner cylindrical portion
Between form annular air channel, described mixed gas outlet runs through described outer nozzle wall cylindrical portion and with described gas outlet in footpath
Corresponding upwards so that from described gaseous mixture after the combustion gas that described gas outlet sprays is mixed with the air in described air duct
Outlet sprays.
9. gas-turbine combustion chamber as claimed in claim 8 is it is characterised in that each nozzle has two mixed gas outlets,
Each mixed gas outlet sprays gaseous mixture towards a corresponding adjacent flame barrier structure, and each mixed gas outlet has a center
Line, each flame barrier structure includes a hollow body, and described hollow body has one and described axially in parallel center line, and each mixes
The center line closing gas outlet passes through the center line of hollow body corresponding with this mixed gas outlet.
10. gas-turbine combustion chamber as claimed in claim 8 is it is characterised in that described outer nozzle wall has outer nozzle wall end
Portion, described outer nozzle wall end is provided with end through hole and the blind end with described main burner cylindrical portion is spaced apart in the axial direction.
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN106679150A (en) * | 2017-02-24 | 2017-05-17 | 广东万家乐燃气具有限公司 | Gas water heater capable of adjusting primary air amount |
| WO2018090384A1 (en) * | 2016-11-21 | 2018-05-24 | 深圳智慧能源技术有限公司 | Combustion chamber of gas turbine engine |
| WO2018090385A1 (en) * | 2016-11-21 | 2018-05-24 | 深圳智慧能源技术有限公司 | Combustion chamber of gas turbine engine |
| WO2018090383A1 (en) * | 2016-11-21 | 2018-05-24 | 深圳智慧能源技术有限公司 | Combustion chamber of gas turbine engine, and nozzle thereof |
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| CN106338084B (en) | 2018-11-20 |
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