CN106439914A - Combustion chamber of combustion gas turbine - Google Patents
Combustion chamber of combustion gas turbine Download PDFInfo
- Publication number
- CN106439914A CN106439914A CN201611039146.2A CN201611039146A CN106439914A CN 106439914 A CN106439914 A CN 106439914A CN 201611039146 A CN201611039146 A CN 201611039146A CN 106439914 A CN106439914 A CN 106439914A
- Authority
- CN
- China
- Prior art keywords
- nozzle
- air stream
- gas outlet
- inner liner
- combustion chamber
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Classifications
-
- 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
-
- 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
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Gas Burners (AREA)
Abstract
A combustion chamber of a combustion gas turbine comprises a combustion cavity and a plurality of nozzles. The combustion cavity is formed between an inner ring flame cylinder and an outer ring flame cylinder. An axial direction and a circumferential direction around the axial direction are defined for the combustion cavity. The nozzles are arranged in the combustion cavity and evenly arrayed in the circumferential direction. Each nozzle is provided with a first gas mixture outlet and a second gas mixture outlet. For any two adjacent first nozzle and second nozzle, the first gas mixture outlet of the first nozzle is located in the side facing the second nozzle, the second gas mixture outlet of the second nozzle is located in the side facing the first nozzle, the outer ring flame cylinder is provided with a first air flow injection structure, the inner ring flame cylinder is provided with a second air flow injection structure, and the first gas mixture outlet, the second gas mixture outlet, the first air flow injection structure and the second air flow injection structure are distributed in a corner tangential mode.
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 combustor 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.
Nozzle in gas-turbine combustion chamber is during jet flames to the intracavity that burns it is possible in can be because of nozzle
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 propose a kind of gas-turbine combustion chamber, includings combustion chamber, described combustion chamber be formed at inner ring burner inner liner with
Between the burner inner liner of outer ring, described combustion chamber defines one axially with around described axial circumferencial direction；And it is arranged on described ring
Some nozzles of shape burning intracavity, described some nozzles are evenly distributed along described circumferencial direction, and described nozzle is used for being blended with
The gaseous mixture of combustion gas and air sprays into described combustion chamber；Each nozzle is provided with the first mixed gas outlet and the second mixed gas outlet,
For any two adjacent first jet and second nozzle, the first mixed gas outlet of described first jet is located at towards described the
The side of two nozzles, the second mixed gas outlet of described second nozzle is located at the side towards described first jet；Described outer ring
Burner inner liner is provided with the first air stream injection structure, and described first air stream injection structure is used for injection towards described inner ring burner inner liner
The first air stream；Described inner ring burner inner liner is provided with the second air stream injection structure, and described second air stream injection structure is used for
Injection is towards the second air stream of described outer ring burner inner liner；Described first mixed gas outlet, the second mixed gas outlet, the first air
Stream injection structure and the second air stream injection structure are in that quadrangle tangential circle is arranged.
In one embodiment, in a radial section, the first spray of the first mixed gas outlet definition of described first jet
Penetrate direction towards one of them lateral deviation of described inner ring burner inner liner and outer ring burner inner liner from described first jet and second nozzle circle
Line between the heart, the second injection direction of the second mixed gas outlet definition of described second nozzle is towards described inner ring burner inner liner
With burner inner liner wherein opposite side in outer ring deviates the line between described first jet and the center of circle of second nozzle.
In one embodiment, the angle of the described first injection direction described line of deviation is 1 °～15 °, described second injection
The angle that described line is deviateed in direction is 1 °～15 °.
In one embodiment, described first air stream is intersected with the first flame advancing along described first injection direction to change
Become the direction into described first air stream for the direct of travel of described first flame；Described second air stream is sprayed with along described second
Progressive second flame in side intersects the direction being described second air stream with the direct of travel changing described second flame.
In one embodiment, described first air stream injection structure is some first pores on the burner inner liner of described outer ring,
Described second air stream injection structure is some second pores on described inner ring burner inner liner.
In one embodiment, described inner ring burner inner liner and outer ring burner inner liner be provided with some Cooling Holes running through, described
The aperture of one pore and the second pore is more than the aperture of described Cooling Holes.
In one embodiment, what the first mixed gas outlet of described first jet sprayed advances along described first injection direction
The first flame intersect with the first air stream spraying from described first air stream injection structure, described first flame and described the
One air stream intersects tailing edge one curved path advances；What the second mixed gas outlet of described second nozzle sprayed sprays along described second
Progressive second flame in the side of penetrating is intersected with the second air stream spraying from described second air stream injection structure, described second fire
Flame intersects another curved path of tailing edge with described second air stream advances；Described two curved paths surround formation quadrangle tangential circle road
Footpath.
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, 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 one embodiment, the aperture of described gas outlet is less than the aperture of described mixed gas outlet.
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 the burning intracavity that gaseous mixture is spurted into combustor burnt, it is to avoid the infringement to flame tube wall for the thermal-flame.
Secondly, combustor also can arrange air stream injection structure, air stream injection structure structure on outer ring burner inner liner and inner ring burner inner liner
Cause the flame formation quadrangle tangential circle that its air stream ejecting is ejected with two adjacent two nozzles relative mixed gas outlets,
Air stream can change the direct of travel of jet flames, and then along described quadrangle tangential circle cycle operation, is prevented effectively from jet flames pair
Combustor and nozzle cause to damage, and improve the fuel gas buring efficiency of burning intracavity.The gas-turbine combustion chamber structure letter of the present invention
Single, novel, can at utmost reduce the damage to each element of combustor, improve the efficiency of combustion of combustor, reduce and produce
Cost.
Brief description
Fig. 1 is the schematic top plan view of the combustor of one embodiment of the invention an along lateral cross section.
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 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 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 be in Fig. 5 combustor along the elevational schematic view of a lateral cross section.
Fig. 9 is the longitudinal sectional view of the hollow body structure of combustor in Fig. 5.
Figure 10 is the fuel gas flow of the combustor 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 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 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 combustor
Improve, and propose two kinds of embodiments.
Embodiment one：
As shown in figures 5-9, described combustor 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 centrage, and hollow cylinder 42 has parallel
In described axial centrage, the centrage of each mixed gas outlet 30 passes through and this corresponding hollow body 42 of mixed gas outlet 30
Centrage that is to say, that each hollow body 42 centrage be located at adjacent two nozzles 12 two relative mixed gas outlets 30
Gaseous mixture injection direction, namely on the intersection point of its centrage.
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 intersect tailing edge one curved path advances.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, it is another that therefore two strands air-flows intersect tailing edge
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 combustor
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 the burning intracavity that gaseous mixture is spurted into combustor 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 combustor
Service life.Again, in certain embodiments, combustor 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 formation quadrangle tangential circle ejecting, 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 combustor and nozzle is caused damage, improves the fuel gas buring efficiency of burning intracavity.This
Bright gas-turbine combustion chamber structure is simple, novel, can at utmost reduce the damage to each element of combustor, 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 claim should be belonged to.
Claims (10)
1. a kind of gas-turbine combustion chamber, including：
Combustion chamber, described combustion chamber is formed between inner ring burner inner liner and outer ring burner inner liner, described combustion chamber define one axially and
Around described axial circumferencial direction；And it is arranged on some nozzles of described annular firing intracavity, described some nozzles are along institute
State that circumferencial direction is evenly distributed, 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 is provided with the first mixed gas outlet and the second mixed gas outlet, for any two adjacent
One nozzle and second nozzle, the first mixed gas outlet of described first jet is located at the side towards described second nozzle, described
Second mixed gas outlet of second nozzle is located at the side towards described first jet；
Described outer ring burner inner liner is provided with the first air stream injection structure, and described first air stream injection structure is used for injection towards institute
State the first air stream of inner ring burner inner liner；
Described inner ring burner inner liner is provided with the second air stream injection structure, and described second air stream injection structure is used for injection towards institute
State the second air stream of outer ring burner inner liner；
Described first mixed gas outlet, the second mixed gas outlet, the first air stream injection structure and the second air stream injection structure
Arrange in quadrangle tangential circle.
2. gas-turbine combustion chamber as claimed in claim 1 is it is characterised in that in a radial section, described first jet
The first mixed gas outlet definition the first injection direction towards one of them lateral deviation of described inner ring burner inner liner and outer ring burner inner liner
Line between described first jet and the center of second nozzle, the of the second mixed gas outlet definition of described second nozzle
Two injection directions deviate described first jet and second nozzle towards described 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 is it is characterised in that described first injection direction deviates described line
Angle be 1～15 °, described second injection direction deviate described line angle be 1～15 °.
4. gas-turbine combustion chamber as claimed in claim 2 is it is characterised in that described first air stream is sprayed with along described first
Progressive first flame in the side of penetrating intersects the direction being described first air stream with the direct of travel changing described first flame；Institute
State the second air stream and intersect to change the traveling side of described second flame with the second flame advancing along described second injection direction
To the direction for described second air stream.
5. the gas-turbine combustion chamber as described in claim 1 or 4 is it is characterised in that described first air stream injection structure is
Some first pores on the burner inner liner of described outer ring, described second air stream injection structure is some on described inner ring burner inner liner
Second pore.
6. gas-turbine combustion chamber as claimed in claim 5 is it is characterised in that described inner ring burner inner liner and outer ring burner inner liner
It is provided with some Cooling Holes running through, the aperture of described first pore and the second pore is more than the aperture of described Cooling Holes.
7. gas-turbine combustion chamber as claimed in claim 2 is it is characterised in that the first mixed gas outlet of described first jet
The first flame along described first injection direction advance spraying is empty with first spraying from described first air stream injection structure
Air-flow intersects, and described first flame intersects tailing edge one curved path with described first air stream advances；The of described second nozzle
Two mixed gas outlets spray along described second injection direction advance the second flame with from described second air stream injection structure
The second air stream spraying intersects, and described second flame intersects another curved path of tailing edge with described second air stream advances；Institute
State two curved paths and surround formation quadrangle tangential circle path.
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 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.
10. gas-turbine combustion chamber as claimed in claim 8 is it is characterised in that the aperture of described gas outlet is less than described
The aperture of mixed gas outlet.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611039146.2A CN106439914A (en) | 2016-11-21 | 2016-11-21 | Combustion chamber of combustion gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611039146.2A CN106439914A (en) | 2016-11-21 | 2016-11-21 | Combustion chamber of combustion gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106439914A true CN106439914A (en) | 2017-02-22 |
Family
ID=58221514
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611039146.2A Pending CN106439914A (en) | 2016-11-21 | 2016-11-21 | Combustion chamber of combustion gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106439914A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| 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 |
| CN110043922A (en) * | 2019-04-24 | 2019-07-23 | 北京航空航天大学 | A kind of micro gas turbine engine and its reverse-flow can type combustor assembly |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101135446A (en) * | 2007-10-09 | 2008-03-05 | 中国计量学院 | Multiple oil gun rounding arrangement micro-oil ignition coal power combusting device |
| CN101818910A (en) * | 2010-03-24 | 2010-09-01 | 北京航空航天大学 | Miniature gas turbine combustion chamber |
| CN103104925A (en) * | 2013-02-01 | 2013-05-15 | 浙江特富锅炉有限公司 | Burner for combustion chemical waste gas |
| CN103363549A (en) * | 2012-04-05 | 2013-10-23 | 通用电气公司 | Combustor and method for supplying fuel to combustor |
| CN203671658U (en) * | 2013-12-11 | 2014-06-25 | 中航商用航空发动机有限责任公司 | Combustion chamber of combustion gas turbine and combustion gas turbine with same |
| CN103998745A (en) * | 2011-08-22 | 2014-08-20 | 马吉德·托甘 | Can-annular combustor with staged and tangential fuel-air nozzles for use on gas turbine engines |
| CN204404240U (en) * | 2014-10-28 | 2015-06-17 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | A kind of gas-turbine combustion chamber nozzle |
| CN106016362A (en) * | 2016-05-16 | 2016-10-12 | 中国科学院工程热物理研究所 | Gas turbine engine mild combustor and control method thereof |
| CN206274175U (en) * | 2016-11-21 | 2017-06-23 | 深圳智慧能源技术有限公司 | Gas-turbine combustion chamber |
-
2016
- 2016-11-21 CN CN201611039146.2A patent/CN106439914A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101135446A (en) * | 2007-10-09 | 2008-03-05 | 中国计量学院 | Multiple oil gun rounding arrangement micro-oil ignition coal power combusting device |
| CN101818910A (en) * | 2010-03-24 | 2010-09-01 | 北京航空航天大学 | Miniature gas turbine combustion chamber |
| CN103998745A (en) * | 2011-08-22 | 2014-08-20 | 马吉德·托甘 | Can-annular combustor with staged and tangential fuel-air nozzles for use on gas turbine engines |
| CN103363549A (en) * | 2012-04-05 | 2013-10-23 | 通用电气公司 | Combustor and method for supplying fuel to combustor |
| CN103104925A (en) * | 2013-02-01 | 2013-05-15 | 浙江特富锅炉有限公司 | Burner for combustion chemical waste gas |
| CN203671658U (en) * | 2013-12-11 | 2014-06-25 | 中航商用航空发动机有限责任公司 | Combustion chamber of combustion gas turbine and combustion gas turbine with same |
| CN204404240U (en) * | 2014-10-28 | 2015-06-17 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | A kind of gas-turbine combustion chamber nozzle |
| CN106016362A (en) * | 2016-05-16 | 2016-10-12 | 中国科学院工程热物理研究所 | Gas turbine engine mild combustor and control method thereof |
| CN206274175U (en) * | 2016-11-21 | 2017-06-23 | 深圳智慧能源技术有限公司 | Gas-turbine combustion chamber |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| 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 |
| CN110043922A (en) * | 2019-04-24 | 2019-07-23 | 北京航空航天大学 | A kind of micro gas turbine engine and its reverse-flow can type combustor assembly |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN206176456U (en) | Gas turbine combustor | |
| CN109404967B (en) | Combustion chamber of gas turbine and gas turbine | |
| CN100554785C (en) | Be used for combustion tube and method that the air of gas turbine is mixed | |
| CN106016364B (en) | A kind of gas turbine dry low pollution combustor unit two divides swirl-flow premixed burner noz(zle) | |
| US7757491B2 (en) | Fuel nozzle for a gas turbine engine and method for fabricating the same | |
| JP3860952B2 (en) | Gas turbine combustor | |
| US9163838B2 (en) | Gas turbine combustion burner | |
| CN105229379B (en) | Gas turbine combustor | |
| JP6196868B2 (en) | Fuel nozzle and its assembly method | |
| US7908863B2 (en) | Fuel nozzle for a gas turbine engine and method for fabricating the same | |
| KR102570807B1 (en) | Fuel injectors with multiple outlet slots for use in gas turbine combustor | |
| WO2012133774A1 (en) | Nozzle, gas turbine combustor and gas turbine | |
| JP2020034271A (en) | Fuel nozzle structure for air assist fuel injection | |
| JP6812240B2 (en) | Air Fuel Premixer for Low Emission Turbine Combustors | |
| CN206274175U (en) | Gas-turbine combustion chamber | |
| CN105705866B (en) | Nozzle, burner and gas turbine | |
| CN106439914A (en) | Combustion chamber of combustion gas turbine | |
| CA2546881A1 (en) | Gas turbine engine combustor with improved cooling | |
| CN106338084B (en) | Gas-turbine combustion chamber | |
| CN102538009A (en) | Combustor premixer | |
| CN106402934A (en) | Gas turbine combustion chamber and nozzle thereof | |
| CN104534515B (en) | Gas-turbine combustion chamber head construction | |
| JP2011196681A (en) | Combustor with pre-mixing primary fuel-nozzle assembly | |
| CN106524225B (en) | The three vortex system tissue burned flame cylinders suitable for advanced low pollution turbogenerator | |
| CN205825112U (en) | A kind of two points of swirl-flow premixed burner noz(zle)s of gas turbine dry low pollution combustor unit |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20170222 |
|
| WD01 | Invention patent application deemed withdrawn after publication |