CN206274175U - Gas-turbine combustion chamber - Google Patents
Gas-turbine combustion chamber Download PDFInfo
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- CN206274175U CN206274175U CN201621266384.2U CN201621266384U CN206274175U CN 206274175 U CN206274175 U CN 206274175U CN 201621266384 U CN201621266384 U CN 201621266384U CN 206274175 U CN206274175 U CN 206274175U
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- gas outlet
- combustion chamber
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Abstract
A kind of gas-turbine combustion chamber, including combustion chamber, the combustion chamber are formed between inner ring burner inner liner and outer ring burner inner liner, and the combustion chamber defines one axially and around the axial circumferencial direction；And it is arranged on some nozzles in the combustion chamber, some nozzles are evenly distributed along the circumferencial direction, each nozzle is provided with the first mixed gas outlet and the second mixed gas outlet, the first jet adjacent for any two and second nozzle, first mixed gas outlet of the first jet is located at towards the side of the second nozzle, second mixed gas outlet of the second nozzle is located at towards the side of the first jet, the outer ring burner inner liner is provided with the first air stream injection structure, the inner ring burner inner liner is provided with the second air stream injection structure, first mixed gas outlet, second mixed gas outlet, first air stream injection structure and the second air stream injection structure are arranged in quadrangle tangential circle.
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 matches rational fuel-air mixture example, is burnt into combustion chamber, forms 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 can be occurred back
Fire, the element such as valuable cyclone causes ablation and breaking-up to nozzle and in premixed channel.
During nozzle in gas-turbine combustion chamber is in the jet flames to combustion chamber, it is possible to can be because in nozzle
Hypertonia, the flame for causing nozzle to eject can be directly injected to burner inner liner inwall or it is interior set on component, even
It is directly injected on adjacent nozzle, serious ablation and damage is caused to it, substantially reduces gas-turbine combustion chamber and its spray
The service life of mouth.
Therefore, be badly in need of a kind of rationally effective gas-turbine combustion chamber structure and nozzle arrangements solve it is set forth above extremely
A kind of few problem.
The 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, including combustion chamber, the combustion chamber be formed at inner ring burner inner liner and
Between the burner inner liner of outer ring, the combustion chamber defines one axially and around the axial circumferencial direction；And it is arranged on the ring
Some nozzles in shape combustion chamber, some nozzles are evenly distributed along the circumferencial direction, and the nozzle is used to be blended with
The gaseous mixture of combustion gas and air sprays into the combustion chamber；Each nozzle is provided with the first mixed gas outlet and the second mixed gas outlet,
The first jet adjacent for any two and second nozzle, the first mixed gas outlet of the first jet are located at towards described the
The side of two nozzles, the second mixed gas outlet of the second nozzle is located at towards the side of the first jet；The outer ring
Burner inner liner is provided with the first air stream injection structure, and the first air stream injection structure is used to spray towards the inner ring burner inner liner
The first air stream；The inner ring burner inner liner is provided with the second air stream injection structure, and the second air stream injection structure is used for
Spray the second air stream towards the outer ring burner inner liner；First mixed gas outlet, the second mixed gas outlet, the first air
Stream injection structure and the second air stream injection structure are arranged in quadrangle tangential circle.
In one embodiment, in a radial section, the first spray of the first mixed gas outlet definition of the first jet
Direction is penetrated towards one of the inner ring burner inner liner and outer ring burner inner liner lateral deviation from the first jet and the circle of second nozzle
Line between the heart, the second injection direction of the second mixed gas outlet definition of the second nozzle is towards the inner ring burner inner liner
And burner inner liner wherein opposite side in outer ring deviates the line between the first jet and the center of circle of second nozzle.
In one embodiment, the angle that first injection direction deviates the line is 1 °~15 °, second injection
The angle that the line is deviateed in direction is 1 °~15 °.
In one embodiment, first air stream intersects to change with the first flame advanced along first injection direction
It is the direction of first air stream to become the direct of travel of first flame；Second air stream is sprayed with along described second
The second flame that direction is advanced intersects to change the direction that the direct of travel of second flame is second air stream.
In one embodiment, the first air stream injection structure is some first stomatas on the outer ring burner inner liner,
The second air stream injection structure is some second stomatas on the inner ring burner inner liner.
In one embodiment, the inner ring burner inner liner and outer ring burner inner liner are provided with some Cooling Holes for running through, described
Aperture of the aperture of one stomata and the second stomata more than the Cooling Holes.
In one embodiment, what the first mixed gas outlet of the first jet sprayed advances along first injection direction
The first flame intersect with the first air stream sprayed from the first air stream injection structure, first flame and described
Advanced along a curved path after one air stream is intersecting；What the second mixed gas outlet of the second nozzle sprayed sprays along described second
The second flame for penetrating direction advance intersects with the second air stream sprayed from the second air stream injection structure, second fire
Flame is advanced after intersecting with second air stream along another curved path；Two curved path surrounds to form quadrangle tangential circle road
Footpath.
In one embodiment, each nozzle includes main burner, and the main burner is included along the axially extending main burner
Cylindrical portion, the main burner cylindrical portion end is blind end, and the main burner cylindrical portion has an inside blast tube and passes through
Wear the gas outlet of the main burner cylindrical portion；Outer nozzle wall, the outer nozzle wall includes outer nozzle wall cylindrical portion, the nozzle
Outer wall cylindrical portion is diametrically spaced so as in the main jet around the main burner cylindrical portion and with the main burner cylindrical portion
Annular air channel is formed between mouth cylindrical portion and outer nozzle wall cylindrical portion, the mixed gas outlet is through outer nozzle wall cylinder
Shape portion and diametrically corresponding with the gas outlet so that in the combustion gas sprayed from the gas outlet and the air duct
Air mixing after from the mixed gas outlet spray.
In one embodiment, the outer nozzle wall has outer nozzle wall end, and the outer nozzle wall end is provided with end and leads to
The blind end of main burner cylindrical portion is spaced apart in the axial direction described in Kong Bingyu.
In one embodiment, aperture of the aperture of the gas outlet less than the mixed gas outlet.
In sum, the invention provides a kind of gas-turbine combustion chamber and its nozzle, nozzle includes main burner and surround
The outer nozzle wall that main burner is set, main burner forms blast tube, and outer nozzle wall is diametrically spaced with the two with main burner
Between form air duct, gas outlet is set on main burner, corresponding with gas outlet gaseous mixture is set on outer nozzle wall and
Mouthful so that the combustion gas that gas outlet sprays sprays after mixing with the air in air duct from mixed gas outlet, each nozzle
The injection direction of mixed gas outlet is towards adjacent nozzle.Nozzle arrangements of the invention design is ingenious, can preferably air mixture and
Air, and gaseous mixture is spurted into the combustion chamber of combustion chamber burnt, it is to avoid infringement of the thermal-flame to flame tube wall.
Secondly, combustion chamber can also set air stream injection structure, air stream injection structure structure on outer ring burner inner liner and inner ring burner inner liner
The air stream that it is ejected is caused to form quadrangle tangential circle with the flame that the two relative mixed gas outlets of adjacent two nozzles are ejected,
Air stream can change the direct of travel of jet flames, and then along the quadrangle tangential circle cycle operation, be prevented effectively from jet flames pair
Combustion chamber and nozzle cause to damage, and improve the fuel gas buring efficiency in combustion chamber.Gas-turbine combustion chamber structure letter of the invention
It is single, it is novel, the damage to each element in combustion chamber can be at utmost reduced, the efficiency of combustion of combustion chamber is improved, reduce production
Cost.
Brief description of the drawings
Fig. 1 is the combustion chamber of one embodiment of the invention along the schematic top plan view of a 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 combustion chamber of another embodiment of the present invention along the schematic top plan view of a 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 a lateral cross section elevational schematic view.
Fig. 9 is the longitudinal sectional view of the hollow body structure of combustion chamber in Fig. 5.
Figure 10 is the simplification of fuel gas flow and air draught the formation quadrangle tangential circle of the combustion chamber of another embodiment of the present invention
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 to institute hereafter or in accompanying drawing in the application
The detailed construction or arrangement of elements of description.The present invention can be the embodiment that other manner is realized.Furthermore, it is to be understood that this paper institutes
The wording and term for using are solely for describing purposes, should not the explanation of being construed as limiting property.It is used herein " including ", "comprising",
The similar wording such as " having " is meant comprising items listed thereafter, its equivalent and other additional things.Particularly, description is worked as
When " certain element ", the quantity that the present invention does not limit the element is one, it is also possible to including multiple.
As depicted in figs. 1 and 2, the present invention provides a kind of gas-turbine combustion chamber, and the 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 to be blended with combustion gas and the gaseous mixture of air is sprayed into 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 and around the axial circumferencial direction, and some nozzles 12 are fixed on burner inner liner
On 10 end wall, arranged along the circumferencial direction and along described axially extending.Preferably, some nozzles 12 are along the 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 set around main burner 20, main jet
Mouth 20 formed an inside blast tube 24 and the gas outlet 26 with the fluid communication of internal blast tube 24, outer nozzle wall 22 with
Air duct 28 is formed between main burner 20, gas outlet 26 and air duct 28 are in fluid communication, set on outer nozzle wall 22 with
An at least mixed gas outlet 30 of the fluid communication of air duct 28, to cause the combustion gas and the air duct that are sprayed from gas outlet 26
Sprayed from mixed gas outlet 30 after air mixing in 28.
Specifically, main burner 20 includes main burner cylindrical portion 32 and the main burner positioned at the end of main burner cylindrical portion 32
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 connects with outer combustion gas conveyance conduit, to receive external combustion gas.Main burner end 34 is envelope
Closed end, to cause that the combustion gas in blast tube 24 can only spray from gas outlet 26.
In an illustrated embodiment, gas outlet 26 is set through main burner cylindrical portion 32, and the quantity of gas outlet 26 is
Two, the direction that two gas outlets 26 are respectively facing adjacent nozzle is set, and gas outlet 26 is set be located proximate to main jet
Mouth end 34, i.e., described blind end.
Outer nozzle wall 22 includes outer nozzle wall cylindrical portion 36 and the outer nozzle wall positioned at the end of outer nozzle wall cylindrical portion 36
End 38, outer nozzle wall cylindrical portion 36 around main burner 20 and being diametrically spaced with main burner 20, so as to main burner 20 with
Air duct 28 is formed between outer nozzle wall 22, air duct 28 is in fluid communication with gas outlet 26.In an illustrated embodiment,
Outer nozzle wall end 38 is spaced apart on the axial direction with main burner end 34, therefore, air duct 28 also includes outer nozzle wall
The space 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
An at least mixed gas outlet 30 of the fluid communication of passage 28.Specifically, mixed gas outlet 30 runs through outer nozzle wall cylindrical portion 36
And it is diametrically corresponding with gas outlet 26, to cause that the combustion gas sprayed from gas outlet 26 is mixed with the air in air duct 28
Sprayed from mixed gas outlet 30 after conjunction.
In an illustrated embodiment, the quantity of the mixed gas outlet 30 for being formed in outer nozzle wall cylindrical portion 36 is two, and
And two mixed gas outlets 30 are diametrically corresponding with two gas outlets 26 respectively, to cause to be sprayed from two gas outlets 26
Combustion gas mix with the air in air duct 28 after sprayed 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 set
Two gas outlets 26 and two mixed gas outlets 30, two gas outlets 26 are respectively with two mixed gas outlets 30 diametrically
Correspondence, and the gaseous mixture injection direction of two definition of mixed gas outlet 30 is opposite.In the present embodiment, the gaseous mixture injection direction
Approximately along the circumferencial direction.Specifically, the gaseous mixture injection direction be towards the direction of 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 the 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 simultaneously logical with air
Road 28 and annular firing chamber 14 are in fluid communication, 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, the cooling of wall 36 and end 38 is carried out.
In an illustrated embodiment, the gas outlet 26 and mixed gas outlet 30 that nozzle 12 is formed 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
The effect of injection air is formed during mixed gas outlet 30, promotes the mixing of the combustion gas and air by mixed gas outlet 30, and then
Promote burning and the short flamed length that contracts.
As described above, the injection direction of the gaseous mixture ejected from mixed gas outlet 30 is towards an adjacent nozzle 12
Direction, when flame pressure is larger, the flame that the gaseous mixture or gaseous mixture ejected from mixed gas outlet 30 are produced can
Can be directly injected on adjacent nozzle 12, can so produce larger infringement to nozzle 12 so that nozzle 12 is easily damaged.For
The generation of such case is avoided, 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, the combustion chamber also includes directly being sprayed for the flame for preventing gaseous mixture or gaseous mixture from producing
Some flame barrier structures on to adjacent nozzle 12, specifically, set a fire between the adjacent nozzle 12 of each two
Flame barrier structure.
As it was previously stated, each nozzle 12 sets two mixed gas outlets 30, and two mixing of the definition of mixed gas outlet 30
Gas jet is in opposite direction.Refer to Fig. 5, the mixing gas jet side of the two relative mixed gas outlets 30 of the nozzle 12 of arbitrary neighborhood two
To with an intersection point, the flame barrier structure setting in the point of intersection, to stop the gaseous mixture that mixed gas outlet 30 sprays
The flame of generation.
The 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 set along the axial direction, and an axial end portion of hollow body 42 is fixed on fire
On flame cylinder 10, being fixed with that end wall of nozzle 12 for burner inner liner 10 is specifically integrally fixed at.The axial direction of hollow body 42
End is hatch frame, is connected with extraneous air, for receiving the cooling air outside burner inner liner 10, and then causes that cooling is empty
Gas is full of internal cavities 46.
Such as Fig. 9, another axial end portion 48 and hollow body wall portion 44 of hollow body 42 are equipped with and the fluid phase of internal cavities 46
Logical some through holes.Using this loose structure, the air of the internal cavities 46 of hollow body 42 can be by 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 can also be by hollow body wall portion simultaneously
44 and axial end portion 48 on through hole enter annular firing chamber 14 in, with cause annular firing chamber 14 in fuel gas buring more fill
Point.
Hollow body 42 has the blocking surface towards adjacent nozzle 12, and the blocking surface is flame and is contacted with hollow body 42
Surface, be respectively provided with a nozzle 12 along the both sides of each hollow body 42 of the circumferencial direction, therefore each hollow body 42 has two
Individual blocking surface.When the flame of a wherein 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, protect hollow
Body 42 is not burned out.In the present embodiment, the blocking surface is designed as arcwall face, for example, hollow body 42 is designed as into 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 wherein flame of a nozzle can be stopped and be unlikely to be ejected into an adjacent nozzle.
Please continue to refer to Fig. 5, each nozzle 12 has two mixed gas outlets 30, each mixed gas outlet 30 towards a pair
The injection gaseous mixture of adjacent hollow body 42 answered, each mixed gas outlet 30 has a center line, and hollow cylinder 42 has parallel
In the axial center line, the center line of each mixed gas outlet 30 passes through hollow body 42 corresponding with the mixed gas outlet 30
Center line, that is to say, that the center line of each hollow body 42 be located at adjacent two nozzle 12 two relative mixed gas outlets 30
Gaseous mixture injection direction, namely on the intersection point of its center line.
Fig. 8 is refer to, in a radial section, the center of all hollow bodies 42 is centrally located at same with all nozzles 12
On individual circle.Certainly, in other embodiments, hollow body 42 can also set otherwise in a circumferential direction with nozzle 12
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, the combustion chamber 14 being formed between inner ring burner inner liner 18 and outer ring burner inner liner 16 and some sprays being arranged 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
The construction for stating annular flame tube 10 and nozzle 12 can be identical with the construction in previous embodiment, therefore will not be repeated here.
It is described in detail by taking two nozzles of arbitrary neighborhood as an example below.
Two nozzles of the arbitrary neighborhood include that first jet 12a and second nozzle 12b, first jet 12a include the
One mixed gas outlet 50 and the second mixed gas outlet 52, second nozzle 12b include the first mixed gas outlet 54 and the second gaseous mixture
Outlet 56.First mixed gas outlet 50 of wherein first jet 12a is located at towards the side of second nozzle 12b, second nozzle 12b
The second mixed gas outlet 56 be located at towards the side of 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 to spray 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 to spray the second air stream towards outer ring burner inner liner 16
68, the second air stream 68 defines one second airflow direction.
In a radial section, first mixed gas outlet 50 of first jet 12a defines one first injection direction 58, first
Injection direction 58 is towards one of inner ring burner inner liner 18 and outer ring burner inner liner 16 lateral deviation 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 is the second airflow direction, mixed airflow or flame along first jet 12a the first mixed gas outlet 50
The direction of ejection is the first injection direction 58, and mixed airflow or flame spray along second mixed gas outlet 56 of second nozzle 12b
The direction for 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
The stream air stream injection structure 64 of injection structure 62 and second is arranged in quadrangle tangential circle.In other words, sprayed along the first injection direction 58
The mixed airflow or flame penetrated, the mixed airflow or flame, the first air stream 66 and the second sky that are sprayed along the second injection direction 60
Air-flow 68 is surrounded 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
And the line L between the center of second nozzle 12b, the circle of the deviation of the first injection direction 58 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 cause along first
The mixed airflow or flame of the injection of injection direction 58, the mixed airflow or flame, the first air sprayed along the second injection direction 60
The air stream 68 of stream 66 and second surrounds the air-flow to be formed in quadrangle tangential circle, and the present invention is not limited this.
In an illustrated embodiment, the first air stream injection structure 62 is one or more being located on outer ring burner inner liner 16
First stomata 62, the pressure-air outside burner inner liner is sprayed in combustion chamber 14 by first stomata 62 towards inner ring burner inner liner
Penetrate first air stream 66.Similarly, the second air stream injection structure 64 is one or more being located on inner ring burner inner liner 18
Second stomata 64, the pressure-air outside burner inner liner is sprayed in combustion chamber 14 by second stomata 64 towards outer ring burner inner liner
Second air stream 68.Additionally, inner ring burner inner liner 18 and outer ring burner inner liner 16 are provided with some Cooling Holes for running through, it is outer to cause
Portion's air can enter in combustion chamber 14 in burner inner liner wall formation air film through Cooling Holes, intercept thermal-flame.
In the present embodiment, the aperture of the aperture more than Cooling Holes of the first stomata 62 and the second stomata 64, its concrete numerical value root
Designed according to aerodynamic parameter.
The carrying out practically principle of the 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 intersects with the first air stream 66 sprayed from the first air stream injection structure 62, and first
The direct of travel that air stream 66 can change the first flame is the first airflow direction, is had in itself due to the first flame certain
Advanced along a curved path along the traveling momentum of the first injection direction 58, therefore after two strands of air-flows are intersecting.The of second nozzle 12b
The second flame advanced 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 for 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 along another after two strands of air-flows are intersecting
Curved path is advanced.Two curved paths surround to form a quadrangle tangential circle path, in the first air stream 66 and the second air stream 68
Under effect, mixed air-flow is circulated along the 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 fully, discharge is more preferable, also causes the axial chi of combustion chamber
Very little further to reduce, final gas turbine can also have smaller axial dimension.
As figs 11-13, can more uniformly mix in order that obtaining combustion gas and air, in the air duct 28 of nozzle 12
One cyclone 74 is set, to cause that the air in air inlet passage 28 forms eddy flow, increases air flow intensity, can
Quickly and evenly mix with combustion gas, efficiency of combustion is improved, so as to reduce the discharge of nitrogen oxides.In an illustrated embodiment, revolve
Stream device 74 includes some blades 76 being arranged on the outer peripheral face of main burner cylindrical portion 32, and 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 the 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 can cause that the air in air duct forms eddy flow.
In sum, the invention provides a kind of gas-turbine combustion chamber and its nozzle, nozzle includes main burner and surround
The outer nozzle wall that main burner is set, main burner forms blast tube, and outer nozzle wall is diametrically spaced with the two with main burner
Between form air duct, gas outlet is set on main burner, corresponding with gas outlet gaseous mixture is set on outer nozzle wall and
Mouthful so that the combustion gas that gas outlet sprays sprays after mixing with the air in air duct from mixed gas outlet, each nozzle
The injection direction of mixed gas outlet is towards adjacent nozzle.Nozzle arrangements of the invention design is ingenious, can preferably air mixture and
Air, and gaseous mixture is spurted into the combustion chamber of combustion chamber burnt, it is to avoid infringement of the thermal-flame to flame tube wall.
Secondly, some flame barrier structures are also set up in certain embodiments, in combustion chamber, and flame barrier structure setting is in adjacent two sprays
Between mouth, damage is produced on adjacent nozzle to it to prevent the flame ejected from nozzle from being directly injected to, extend combustion chamber
Service life.Again, in certain embodiments, combustion chamber can also set air stream on outer ring burner inner liner and inner ring burner inner liner
Injection structure, air stream injection structure is configured to the two relative mixed gas outlets of air stream that it ejects and adjacent two nozzle
The flame for ejecting forms quadrangle tangential circle, and air stream can change the direct of travel of jet flames, and then be followed along the quadrangle tangential circle
Ring is operated, and is prevented effectively from jet flames and combustion chamber and nozzle are caused to damage, and improves the fuel gas buring efficiency in combustion chamber.This hair
Bright gas-turbine combustion chamber simple structure, it is novel, the damage to each element in combustion chamber can be at utmost reduced, improve combustion
The efficiency of combustion of room is burnt, production cost is reduced.
Concepts described herein may be embodied to other forms in the case of without departing from its spirit and characteristic.It is disclosed
Specific embodiment should be considered as exemplary rather than restricted.Therefore, the scope of the present invention be by appended claim,
It is determined rather than these descriptions before basis.Any change in the letter and equivalency range of claim is all
The scope of these claims should be belonged to.
Claims (10)
1. a kind of gas-turbine combustion chamber, including：
Combustion chamber, the combustion chamber is formed between inner ring burner inner liner and outer ring burner inner liner, the combustion chamber define one axially and
Around the axial circumferencial direction；And some nozzles in the combustion chamber are arranged on, some nozzles are along the circle
Circumferential direction is evenly distributed, and the nozzle is used to be blended with combustion gas and the gaseous mixture of air sprays into the combustion chamber；
Characterized in that, each nozzle is provided with the first mixed gas outlet and the second mixed gas outlet, adjacent for any two
One nozzle and second nozzle, the first mixed gas outlet of the first jet are located at towards the side of the second nozzle, described
Second mixed gas outlet of second nozzle is located at towards the side of the first jet；
The outer ring burner inner liner is provided with the first air stream injection structure, and the first air stream injection structure is used to spray towards institute
State the first air stream of inner ring burner inner liner；
The inner ring burner inner liner is provided with the second air stream injection structure, and the second air stream injection structure is used to spray towards institute
State the second air stream of outer ring burner inner liner；
First mixed gas outlet, the second mixed gas outlet, the first air stream injection structure and the second air stream injection structure
Arranged in quadrangle tangential circle.
2. gas-turbine combustion chamber as claimed in claim 1, it is characterised in that in a radial section, the first jet
The definition of the first mixed gas outlet the first injection direction towards one of the inner ring burner inner liner and outer ring burner inner liner lateral deviation
Line between the first jet and the center of second nozzle, the of the second mixed gas outlet definition of the second nozzle
Two injection directions deviate the first jet and second nozzle towards the inner ring burner inner liner and outer ring burner inner liner wherein opposite side
Center between line.
3. gas-turbine combustion chamber as claimed in claim 2, it is characterised in that first injection direction deviates the line
Angle be 1~15 °, the angle that second injection direction deviates the line is 1~15 °.
4. gas-turbine combustion chamber as claimed in claim 2, it is characterised in that first air stream with along the described first spray
The first flame for penetrating direction advance is intersecting to change the direction that the direct of travel of first flame is first air stream；Institute
State the second air stream and intersect to change the traveling side of second flame with the second flame advanced along second injection direction
To the direction for second air stream.
5. the gas-turbine combustion chamber as described in claim 1 or 4, it is characterised in that the first air stream injection structure is
Some first stomatas on the outer ring burner inner liner, the second air stream injection structure is some on the inner ring burner inner liner
Second stomata.
6. gas-turbine combustion chamber as claimed in claim 5, it is characterised in that the inner ring burner inner liner and outer ring burner inner liner
It is provided with the aperture of the aperture more than the Cooling Holes of some Cooling Holes for running through, first stomata and the second stomata.
7. gas-turbine combustion chamber as claimed in claim 2, it is characterised in that the first mixed gas outlet of the first jet
The first flame advanced along first injection direction for spraying and the first sky from the first air stream injection structure ejection
Air-flow intersects, and first flame is advanced after intersecting with first air stream along a curved path；The of the second nozzle
The second flame advanced along second injection direction that two mixed gas outlets spray with from the second air stream injection structure
The second air stream for spraying intersects, and second flame is advanced after intersecting with second air stream along another curved path；Institute
Two curved paths are stated to surround to form quadrangle tangential circle path.
8. gas-turbine combustion chamber as claimed in claim 1, it is characterised in that each nozzle includes：
Main burner, the main burner includes that along the axially extending main burner cylindrical portion main burner cylindrical portion end is
Blind end, the main burner cylindrical portion has an inside blast tube and the gas outlet through the main burner cylindrical portion；
Outer nozzle wall, the outer nozzle wall includes outer nozzle wall cylindrical portion, and the outer nozzle wall cylindrical portion is around the main burner
Cylindrical portion and diametrically it is spaced so as in the main burner cylindrical portion and outer nozzle wall cylindrical portion with the main burner cylindrical portion
Between form annular air channel, the mixed gas outlet is through the outer nozzle wall cylindrical portion and with the gas outlet in footpath
Correspondence upwards so that the combustion gas sprayed from the gas outlet mix with the air in the air duct after from the gaseous mixture
Outlet sprays.
9. gas-turbine combustion chamber as claimed in claim 8, it is characterised in that the outer nozzle wall has outer nozzle wall end
Portion, the outer nozzle wall end is provided with end through hole and is spaced apart in the axial direction with the blind end of the main burner cylindrical portion.
10. gas-turbine combustion chamber as claimed in claim 8, it is characterised in that the aperture of the gas outlet is less than described
The aperture of mixed gas outlet.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621266384.2U CN206274175U (en) | 2016-11-21 | 2016-11-21 | Gas-turbine combustion chamber |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621266384.2U CN206274175U (en) | 2016-11-21 | 2016-11-21 | Gas-turbine combustion chamber |
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| CN206274175U true CN206274175U (en) | 2017-06-23 |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106439914A (en) * | 2016-11-21 | 2017-02-22 | 深圳智慧能源技术有限公司 | Combustion chamber of combustion gas turbine |
| 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 |
| 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 |
-
2016
- 2016-11-21 CN CN201621266384.2U patent/CN206274175U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106439914A (en) * | 2016-11-21 | 2017-02-22 | 深圳智慧能源技术有限公司 | Combustion chamber of combustion gas turbine |
| 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 |
| 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 |
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