CN206176456U - Gas turbine combustor - Google Patents
Gas turbine combustor Download PDFInfo
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- CN206176456U CN206176456U CN201621260263.7U CN201621260263U CN206176456U CN 206176456 U CN206176456 U CN 206176456U CN 201621260263 U CN201621260263 U CN 201621260263U CN 206176456 U CN206176456 U CN 206176456U
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Abstract
The utility model provides a gas turbine combustor, includes an annular flame section of thick bamboo, the annular flame cylindric circularizes the burning chamber, annular burning chamber defines an axial and centers on axial circumferencial direction, and set up a plurality of nozzles of annular burning intracavity, a plurality of nozzles are followed circumferencial direction align to grid, the nozzle is used for going into mixing the mixed gas blowout that has gas and air the burning chamber, every nozzle is equipped with at least one gas mixture export that is used for an orientation adjacent jet gas mixture, sets up a flame between per two adjacent nozzles and stops the structure, is used for stoping the flame direct injection that the gas mixture produced arrives on the adjacent nozzle. The utility model discloses a gas turbine combustor simple structure, the design is novel, but the at utmost reduces the damage to each component of combustion chamber, improves the combustion efficiency of combustion chamber, reduction in 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 matches rational fuel-air mixture example, is burnt into combustor, 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.
Nozzle in gas-turbine combustion chamber is during jet flames to the intracavity that burns, it is possible to can be because in nozzle
Hypertonia, cause the flame that nozzle is ejected can be directly injected to burner inner liner inwall or it is interior set on components and parts, 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 effectively 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：Annular flame tube, the annular flame tube forms annular combustion
Chamber is burnt, the annular firing chamber defines one axially and around the axial circumferencial direction；And it is arranged on the annular firing
Some nozzles of intracavity, some nozzles are evenly distributed along the circumferencial direction, the nozzle be used for be blended with combustion gas and
The gaseous mixture of air sprays into the 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 preventing the gaseous mixture from producing
Flame be directly injected on the adjacent nozzle.
In one embodiment, it is mixed that each nozzle two mixed gas outlet of setting, and described two mixed gas outlets are defined
Close gas jet in opposite direction.
In one embodiment, the flame barrier structure includes hollow body, and the hollow body has internal cavities, the sky
The wall portion of heart body is provided with some through holes in fluid communication with the internal cavities, and an axial end portion of the hollow body is fixed on institute
State on burner inner liner, for receiving the cooling air outside the burner inner liner so that the cooling air is full of the internal cavities.
In one embodiment, another axial end portion of the hollow body is provided with some with internal cavities fluid communication
Through hole.
In one embodiment, the hollow body have one towards an adjacent nozzle blocking surface, the blocking surface be arc
Shape face.
In one embodiment, the hollow body is a hollow cylinder or Elliptic Cylinder, the cylinder or Elliptic Cylinder
With parallel to the axial centrage.
In one embodiment, in a radial section, the center of the hollow body and the nozzle are centrally located at same
On individual circle.
In one embodiment, each nozzle includes：Main burner, 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 runs through the 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, 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 centrage, and each flame barrier structure includes
Heart body, the hollow body have one with the axially in parallel centrage, the centrage of each mixed gas outlet passes through mixed with this
Close the centrage that gas exports corresponding hollow body.
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 sum, the invention provides a kind of gas-turbine combustion chamber and its nozzle, nozzle is including main burner and surround
The outer nozzle wall that main burner is arranged, 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.The present invention nozzle arrangements design it is ingenious, can preferably air mixture and
Air, and the burning intracavity that gaseous mixture spurts into combustor is burnt, it is to avoid infringement of the thermal-flame to flame tube wall.
Secondly, burning interior also sets up some flame barrier structures, flame barrier structure setting between adjacent two nozzle, with prevent from
The flame that nozzle is ejected is directly injected on adjacent nozzle and it is produced damage, extends the service life of combustor.This
Bright gas-turbine combustion chamber simple structure, it is novel, the damage to each element of combustor can be at utmost reduced, improve combustion
The efficiency of combustion of room is burnt, production cost is reduced.
Description of the drawings
Fig. 1 is the schematic top plan view of the combustor along a lateral cross section of one embodiment of the invention.
Fig. 2 is the flame drum outer wall of combustor in Fig. 1 and the structural representation of inwall.
Fig. 3 is the side view of the nozzle of combustor 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 combustor along a lateral cross section of another embodiment of the present invention.
Fig. 6 is the structural representation of the flame drum outer wall of combustor in Fig. 5.
Fig. 7 is the flame drum outer wall of combustor in Fig. 5 and the structural representation of inwall.
Fig. 8 is elevational schematic view of the combustor along a lateral cross section in Fig. 5.
Fig. 9 is the longitudinal sectional view of the hollow body structure of combustor in Fig. 5.
Figure 10 is the simplification that the fuel gas flow of the combustor of another embodiment of the present invention and air draught form 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 or arrangement of elements of description.The present invention can be the embodiment that alternate manner is realized.Furthermore, it is to be understood that this paper institutes
The wording and term for using is solely for describing purposes, should not the explanation of being construed as limiting property." including " used herein, "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 present invention does not limit the quantity of the element as 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 combustor 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 in annular firing chamber 14.More specifically, in shown reality
In applying example, annular flame tube 10 is included with 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, along circumferencial direction arrangement 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, the outer nozzle wall 22 that nozzle 12 includes main burner 20 and arranges around main burner 20, main jet
Mouth 20 forms 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 is in fluid communication with air duct 28, arrange on outer nozzle wall 22 and
An at least mixed gas outlet 30 of the fluid communication of air duct 28, so that the combustion gas sprayed from gas outlet 26 and air duct
Spray 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, so that the combustion gas in blast tube 24 can only spray from gas outlet 26.
In an illustrated embodiment, gas outlet 26 is arranged through main burner cylindrical portion 32, and the quantity of gas outlet 26 is
Two, two gas outlets 26 are respectively facing the direction of adjacent nozzle and arrange, 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, so that the combustion gas sprayed from gas outlet 26 is mixed with the air in air duct 28
Spray 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, 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
Correspondence, and the gaseous mixture injection direction of two definition of mixed gas outlet 30 is contrary.In the present embodiment, the gaseous mixture injection direction
Approximately along the circumferencial direction.Specifically, the 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 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 is 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 with air by the combustion gas of 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 ejected from mixed gas outlet 30 or gaseous mixture 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 combustor
Improve, and propose two kinds of embodiments.
Embodiment one：
As shown in figures 5-9, the combustor also includes that the flame for preventing gaseous mixture or gaseous mixture from producing directly sprays
Some flame barrier structures on adjacent nozzle 12, specifically, arrange a fire between the adjacent nozzle 12 of each two
Flame barrier structure.
As it was previously stated, each nozzle 12 arranges two mixed gas outlets 30, and the mixing of two 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 arranged 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, to connect with extraneous air, for receiving the cooling air outside burner inner liner 10, and then causes cooling 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 pass through hollow body wall portion 44
With axial end portion 48, flame barrier structure is protected not to be burned out.Simultaneously the air of internal cavities 46 can also pass through hollow body wall portion
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 the blocking surface is flame and contacts 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 centrage, and hollow cylinder 42 has parallel
In the axial centrage, the centrage of each mixed gas outlet 30 passes through hollow body 42 corresponding with the mixed gas outlet 30
Centrage, that is to say, that the centrage 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 centrage.
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 described 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 includes 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 the side towards second nozzle 12b, second nozzle 12b
The second mixed gas outlet 56 be located at 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 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 for second air stream of the injection towards outer ring burner inner liner 16
68, the second air stream 68 defines one second airflow direction.
In a radial section, one first injection direction 58 of definition of the first mixed gas outlet 50 of first jet 12a, 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, the first mixed gas outlet 50 of mixed airflow or flame along first jet 12a
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, spray along the first injection direction 58
The mixed airflow penetrated or flame, the mixed airflow or flame, the first air stream 66 and second that spray along the second injection direction 60 are empty
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 first jet 12a and second nozzle 12b of the first injection direction 58
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 sprayed along the second injection direction 60 or flame, the first air
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 pore 62, the pressure-air outside burner inner liner is sprayed into combustion chamber 14 by first pore 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 pore 64, the pressure-air outside burner inner liner is sprayed into combustion chamber 14 by second pore 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, so that outward
Portion's air can Jing Cooling Holes enter combustion chamber 14 in burner inner liner wall formed air film, intercept 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
Design 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
It is the first airflow direction that air stream 66 can change the direct of travel of the first flame, because the first flame itself is with certain
Along the traveling momentum of the first injection direction 58, therefore two strands of air-flows intersect the traveling of the curved path of tailing edge one.The of second nozzle 12b
Two mixed gas outlet 56 spray along the second injection direction 60 advance the second flame with spray from the second air stream injection structure 64
The second air stream 68 for going out intersects, and it is the second airflow direction that the second air stream 68 can change the direct of travel of the second flame,
Because the second flame itself has certain traveling momentum along the second injection direction 60, therefore the intersecting tailing edge of two strands of air-flows is another
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, along the quadrangle tangential circle path circulation, the centre position between adjacent nozzle forms eddy flow, effectively keeps away mixed air-flow
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 combustor
Very little further to reduce, final gas turbine can also have less axial dimension.
As figs 11-13, in order that combustion gas and air can more uniformly mix, in the air duct 28 of nozzle 12
One cyclone 74 is set, so that the air in air inlet passage 28 forms eddy flow, increases air flow intensity so as to 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 the air in air duct can be caused to form eddy flow.
In sum, the invention provides a kind of gas-turbine combustion chamber and its nozzle, nozzle is including main burner and surround
The outer nozzle wall that main burner is arranged, 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.The present invention nozzle arrangements design it is ingenious, can preferably air mixture and
Air, and the burning intracavity that gaseous mixture spurts into combustor is burnt, it is to avoid infringement of the thermal-flame to flame tube wall.
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, it is produced damage to prevent the flame ejected from nozzle from being directly injected on adjacent nozzle, extend combustor
Service life.Again, in certain embodiments, combustor can also arrange 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 formation quadrangle tangential circle for ejecting, air stream can change the direct of travel of jet flames, and then follow along the quadrangle tangential circle
Ring operates, and is prevented effectively from jet flames and combustor and nozzle are caused to damage, and improves the fuel gas buring efficiency of burning intracavity.This
Bright gas-turbine combustion chamber simple structure, it is novel, the damage to each element of combustor 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 exemplary rather than restricted.Therefore, the scope of the present invention be by appended claim,
Rather than be determined according to these descriptions before.Any change in the letter and equivalency range of claim is all
The scope of these claim should be belonged to.
Claims (10)
1. a kind of gas-turbine combustion chamber, including：
Annular flame tube, the annular flame tube forms annular firing chamber, and the annular firing chamber defines one axially and around institute
State axial circumferencial direction；And
Some nozzles of the annular firing intracavity are arranged on, some nozzles are evenly distributed along the circumferencial direction, described
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 least one for spraying the gaseous mixture of gaseous mixture and going out towards an adjacent nozzle
Mouthful, a flame barrier structure is set between the adjacent nozzle of each two, the flame for preventing the gaseous mixture from producing is direct
It is ejected on the adjacent nozzle.
2. gas-turbine combustion chamber as claimed in claim 1, it is characterised in that each nozzle arranges 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, it is characterised in that the flame barrier structure includes hollow body,
The wall portion that the hollow body has internal cavities, the hollow body is provided with some through holes in fluid communication with the internal cavities,
One axial end portion of the hollow body is fixed on the burner inner liner, is caused for receiving the cooling air outside the burner inner liner
The cooling air is full of the internal cavities.
4. gas-turbine combustion chamber as claimed in claim 3, it is characterised in that another axial end portion of the hollow body is provided with
Some through holes in fluid communication with the internal cavities.
5. gas-turbine combustion chamber as claimed in claim 3, it is characterised in that the hollow body has towards adjacent
The blocking surface of nozzle, the blocking surface is arcwall face.
6. gas-turbine combustion chamber as claimed in claim 3, it is characterised in that the hollow body is a hollow cylinder or ellipse
Cylinder, the cylinder or Elliptic Cylinder have parallel to the axial centrage.
7. gas-turbine combustion chamber as claimed in claim 6, it is characterised in that in a radial section, the hollow body
Center and the nozzle are centrally located on same circle.
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
Correspond to upwards so that from the gas outlet spray combustion gas 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 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 include a hollow body, the hollow body have one with the axially in parallel centrage, each mix
Close the centrage of the centrage of gas outlet through hollow body corresponding with the mixed gas outlet.
10. 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.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621260263.7U CN206176456U (en) | 2016-11-21 | 2016-11-21 | Gas turbine combustor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621260263.7U CN206176456U (en) | 2016-11-21 | 2016-11-21 | Gas turbine combustor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206176456U true CN206176456U (en) | 2017-05-17 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621260263.7U Withdrawn - After Issue CN206176456U (en) | 2016-11-21 | 2016-11-21 | Gas turbine combustor |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106338084A (en) * | 2016-11-21 | 2017-01-18 | 深圳智慧能源技术有限公司 | The gas turbine combustion chamber |
| 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 |
| 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 |
| 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 |
| CN110529876A (en) * | 2018-05-23 | 2019-12-03 | 通用电气公司 | Rotate detonation combustion system |
-
2016
- 2016-11-21 CN CN201621260263.7U patent/CN206176456U/en not_active Withdrawn - After Issue
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106338084A (en) * | 2016-11-21 | 2017-01-18 | 深圳智慧能源技术有限公司 | The gas turbine combustion chamber |
| 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 |
| 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 |
| 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 |
| CN106338084B (en) * | 2016-11-21 | 2018-11-20 | 深圳智慧能源技术有限公司 | Gas-turbine combustion chamber |
| CN110529876A (en) * | 2018-05-23 | 2019-12-03 | 通用电气公司 | Rotate detonation combustion system |
| CN110529876B (en) * | 2018-05-23 | 2022-03-22 | 通用电气公司 | Rotary detonation combustion system |
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Granted publication date: 20170517 Effective date of abandoning: 20181120 |