CN111121090A - Swirl combustion chamber structure for improving mixing - Google Patents
Swirl combustion chamber structure for improving mixing Download PDFInfo
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- CN111121090A CN111121090A CN202010057139.5A CN202010057139A CN111121090A CN 111121090 A CN111121090 A CN 111121090A CN 202010057139 A CN202010057139 A CN 202010057139A CN 111121090 A CN111121090 A CN 111121090A
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- swirler
- central body
- vane
- fuel
- blades
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- 238000002156 mixing Methods 0.000 title claims abstract description 45
- 238000002485 combustion reaction Methods 0.000 title abstract description 29
- 239000000446 fuel Substances 0.000 claims abstract description 64
- 238000005507 spraying Methods 0.000 claims description 7
- 238000004891 communication Methods 0.000 claims description 3
- 238000004519 manufacturing process Methods 0.000 abstract description 14
- 238000013461 design Methods 0.000 abstract description 7
- 238000007639 printing Methods 0.000 abstract description 7
- 239000000654 additive Substances 0.000 abstract description 4
- 230000000996 additive effect Effects 0.000 abstract description 4
- 238000005516 engineering process Methods 0.000 abstract description 3
- 238000000034 method Methods 0.000 description 11
- 239000007921 spray Substances 0.000 description 8
- 230000008859 change Effects 0.000 description 5
- 230000006872 improvement Effects 0.000 description 5
- 238000002347 injection Methods 0.000 description 5
- 239000007924 injection Substances 0.000 description 5
- 230000010355 oscillation Effects 0.000 description 5
- 239000000463 material Substances 0.000 description 3
- 238000009792 diffusion process Methods 0.000 description 2
- 239000000243 solution Substances 0.000 description 2
- 230000006641 stabilisation Effects 0.000 description 2
- 238000011105 stabilization Methods 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000004323 axial length Effects 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000015556 catabolic process Effects 0.000 description 1
- 238000004512 die casting Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 238000012827 research and development Methods 0.000 description 1
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means
Abstract
The invention provides a swirl combustion chamber structure for improving mixing, which changes the area of an outer layer flow passage by changing the thicknesses of a blade front edge and a blade tail edge, and makes the area of the outer layer flow passage as close as possible to the area of an inner layer flow passage, so that the mixing is more uniformly distributed along the radial direction. It is also possible to add new fuel nozzles to the outer layers that do not communicate with the center body. Through the design of the invention, the difficulty and complexity of the manufacturing process of the gas turbine cyclone combustion chamber are reduced, and meanwhile, the additive manufacturing printing technology is adopted, so that the invention can be manufactured and applied more widely.
Description
Technical Field
The invention relates to the field of gas turbine combustors, in particular to a swirl combustion chamber structure for improving mixing.
Background
Swirl is often used for flame stabilization in the design of combustors of heavy duty low pollution gas turbines, and since low pollution combustors need to burn in a lean premixed state, the lean premixed flame cannot be anchored at the nozzle like the flame of a diffusion combustor, requiring additional methods for stabilization. A common method is to stabilize the flame by creating a recirculation zone such that the flame propagation velocity at the root of the flame is equal to the local low velocity of the recirculation zone; one method of creating a recirculation zone is to add a swirling flow such that the swirling flow creates a vortex breakdown, one embodiment of which is a central recirculation zone. The requirement for swirl generation is that the momentum defines a swirl number in excess of 0.6. While the swirl can be generated by axial swirlers (commonly used in gas turbine combustors such as GE's DLN, DLE series swirlers, siemens's main flame swirl vanes of hybrid burner), radial swirlers (commonly used in early aero engine diffusion combustion, not mentioned herein), tangential inlet tapered swirlers (ansalder's EV series combustors). The swirl number of the conical cyclone is controlled by the flow of tangential air inlet, and the larger the swirl number is, the larger the required axial length is, the heavier the combustion chamber is, so that the application range is limited. The axial cyclone is widely applied due to simple product structure and large design margin (GE, Siemens and other companies).
Disclosure of Invention
Technical problem to be solved
The invention provides a swirl combustion chamber structure for improving mixing, which is characterized in that the circumferential area of an outer layer of an axial swirler is larger than that of an inner layer, so that the outer layer of the swirler has more air than the inner layer, and the fuel and the air are not uniformly mixed. The invention improves the mixing degree of the head part of the combustion chamber by changing the shape of the swirl vanes by means of additive manufacturing printing (SLM printing) technology, thereby reducing thermal NOx pollution. The method can be directly applied to low-pollution improvement of the combustion chamber of the existing combustion engine, and can also be applied to research and development of new combustion engines.
(II) technical scheme
A swirler combustor structure for improved mixing, comprising: the central body is positioned at the central position, the blades are arranged around the central body, the outer shell is positioned on the outer layer of the blades, and the central body, the blades and the outer shell are fixedly connected;
the vane is provided with a front edge, an opposite tail edge, a suction surface, an opposite pressure surface and a through hole for spraying fuel on the surface of the vane, the outer side of the shell is provided with an annular fixing part and two raised positioning bayonets with an included angle of 90 degrees, and the tail edge of the vane keeps the same thickness inside and outside by gradually increasing the thickness of the front edge of the vane outwards along the radial direction.
Wherein the combustor operates in a region where the mach number is less than 0.3.
A swirler combustor structure for improved mixing, comprising: the central body is positioned at the central position, the blades are arranged around the central body, the outer shell is positioned on the outer layer of the blades, and the central body, the blades and the outer shell are fixedly connected;
the vane is provided with a front edge, an opposite tail edge, a suction surface, an opposite pressure surface and a through hole for spraying fuel on the surface of the vane, the outer side of the shell is provided with an annular fixing part and two raised positioning bayonets with an included angle of 90 degrees, and the thicknesses of the front edge and the tail edge of the vane can be gradually increased along the radial direction outwards.
Wherein the increased thickness of the leading edge of the blade may be different from the increased thickness of the trailing edge of the blade.
Wherein, the fuel jet is arranged on the opening of the tail edge of the vane.
A swirler combustor structure for improved mixing, comprising: the central body is positioned at the central position, the blades are arranged around the central body, the outer shell is positioned on the outer layer of the blades, and the central body, the blades and the outer shell are fixedly connected;
the vane has front edge, tail edge, sucking surface, pressure surface and through hole for spraying fuel, and the outer casing has annular fixing part and two raised locating bayonets with 90 deg included angle.
Wherein the fuel nozzle is free of a fuel passage in communication with the center body.
Wherein, there is general device reserved space at the blade trailing edge department.
The vanes are connected with the central body in a hard mode and are integrally formed, the vanes are fixed on the central body by taking the central body as a circle center, and the central body and the vanes are internally provided with hollow passages which are connected and through which fuel can pass.
(III) advantageous effects
According to the technical scheme, the invention has the following beneficial effects:
according to the invention, the thickness of the front edge and the tail edge of the blade of the swirler is changed, so that the area of the outer side runner of the swirler is changed to be closer to the area of the inner side runner of the swirler, and the mixing degree is more uniform along the radial direction. The fuel ratio of the outer layer of the combustion chamber can be increased by adding a new fuel nozzle on the outer layer of the swirler, so that the blending degree of the outer layer of the swirler is closer to that of the inner layer, and the blending uniformity is improved. Meanwhile, the additive manufacturing printing technology is adopted, the manufacturing process difficulty and complexity are reduced, and the method can be widely applied to manufacturing.
Drawings
FIG. 1 is a schematic view of a downstream view of an axial swirler.
Fig. 2 is a schematic view of an axial swirler according to a first aspect of the present invention.
Fig. 3a is a downstream view of an axial swirler in accordance with a first aspect of the present invention.
Fig. 3b is a cross-sectional view along a-a of fig. 3 a.
Fig. 3c is a side view of an axial swirler in accordance with a first aspect of the invention.
Fig. 3d is a cross-sectional view along B-B of fig. 3 c.
Fig. 4 is a schematic view of an axial swirler according to a second aspect of the invention.
Fig. 5a is a downstream view of an axial swirler in accordance with a second aspect of the present invention.
Fig. 5b is a cross-sectional view along a-a of fig. 5 a.
Fig. 5c is a side view of an axial swirler in accordance with a second aspect of the invention.
Fig. 5d is a cross-sectional view along B-B of fig. 5 c.
Fig. 6 is a schematic view of an axial swirler in accordance with a third aspect of the present invention.
Fig. 7a is a downstream view of an axial swirler in accordance with a third aspect of the present invention.
Fig. 7b is a cross-sectional view along a-a of fig. 7 a.
FIG. 7c is a side view of an axial swirler in accordance with a third aspect of the present invention.
Fig. 7d is a cross-sectional view along B-B of fig. 7 c.
Description of the symbols
100 central body
200 blade
201 through hole
202 suction surface
203 pressure surface
204 trailing edge
205 blade top surface
206 trailing edge fuel port
207 outer layer fuel injection port
207' outer plate
300 support rib plate
400 outer casing
401 casing fixing part
403 positioning bayonet
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to specific embodiments and the accompanying drawings. It should be noted that in the drawings or description, the same drawing reference numerals are used for similar or identical parts. Implementations not depicted or described in the drawings are of a form known to those of ordinary skill in the art. Additionally, while exemplifications of parameters including particular values may be provided herein, it is to be understood that the parameters need not be exactly equal to the respective values, but may be approximated to the respective values within acceptable error margins or design constraints. Directional phrases used in the embodiments, such as "upper," "lower," "front," "rear," "left," "right," and the like, refer only to the orientation of the figure. Accordingly, the directional terminology used is intended to be in the nature of words of description rather than of limitation.
In the combustion chamber structure of the conventional gas turbine, due to the different inner and outer layer flow rates of the combustion chamber of the gas turbine, the mixing is not uniform, as shown in fig. 1, the central body 100 is a central circular part as shown in the figure, the vanes 200 are fixed on the central body 100, the surfaces of the vanes 200 are provided with through holes 201 for ejecting fuel, the vanes 200 are bent along the axial direction of the central body 100, the suction surface of the vanes 200 is 202, the back surface is a pressure surface, and the trailing edge 204, the outer side of the vanes is provided with an annular outer casing 400 and two raised positioning bayonets 403 with an included angle of 90 degrees. In prior axial swirlers, the outer diameter is dimensioned for the amount of inlet air (the power to be achieved by the combustion chamber), the diameter of the central body is determined by the inner design, a common design is to have a class-in-place to stabilize the flame. The thickness of the swirl vane is determined by the manufacturing process and the swirl number (circumferential rotation angle of the vane). When air enters from the air inlet, due to the bending of the blades, tangential speed is generated when the air flow passes through the flow channel at the blades, the air flow is close to the outer shell of the swirler in the radial direction and is an outer layer, the air flow is close to the central body in the radial direction and is an inner layer, the circumferential speed of the outer layer of the air flow is higher than that of the inner layer, the air flow of the outer layer of the swirler is also higher than that of the inner layer, fuel and air are subjected to pressure intensity moving outwards in the radial direction under the centrifugal force action of the swirling flow, and under the medium or higher swirling flow (the range of the swirling flow number is 0.5-0.9), the air and the fuel in the inner layer are forced.
In the existing axial swirler, the outer diameter of the swirler is R, the inner diameter of the swirler is R, the middle gas flow channel is divided into n equal parts, the thickness of the swirler vane is w, the swirler has m vanes, the inlet flow velocity is (Ma < 0.3) U, the swirler is from outside to inside, and the volume flow of the ith layer is as follows:
if the outer diameter of the cyclone is too large or the difference (R-R) between the inner diameter and the outer diameter of the cyclone is too large, the air flow rate of the inner layer and the outer layer of the cyclone has obvious difference. The swirl number through the adjustment blade inlayer and inlayer, blade crookedness has simultaneously been proved to increase swirler outer swirl number, swirler inlayer swirl number is unchangeable or reduces, and the method of the fuel spout quantity of reduction swirler inlayer, can not improve swirler's mixing degree of consistency, because this method only makes the circumferential distance that the blade passed through increase, does not change swirler outer runner's area.
Therefore, when the blade is designed, the thickness of the blade on the inner layer and the outer layer is not the same, but the thickness of the blade on the outer layer is larger, the thickness of the inner layer is thinner, and particularly the air inlet position on the front edge of the blade is arranged. Thereby reducing radial blending non-uniformity.
The axial swirler of the gas turbine needs to be designed to avoid a backflow zone or a low-speed zone in a mixing zone at the head of the combustion chamber, and the backflow zone should be formed in a combustion zone. It is also desirable to avoid flame in the blending zone, which can increase pressure loss and NOx pollution. Therefore, the present invention requires care in designing new combustor designs that the swirl number is not too high, which would otherwise cause the outer flow to flow apart at the vane surfaces. The invention also improves the shape of the convergent channel of the mixing region, reduces the axial speed of the fuel, prolongs the time for the fuel to pass through the mixing region with the same length, improves the mixing efficiency, and reduces the pressure loss and the increase of NOx.
The invention provides a swirl combustion chamber structure for improving mixing, which is characterized in that in order to obtain better mixing performance, when a mixing target is pneumatically designed, multipoint injection is carried out in a multi-nozzle mode, a nozzle is integrated on the surface of a blade, a plurality of spray holes are formed in the surface of the blade, and the multipoint injection is carried out, so that the corresponding air inlet amount is ensured at the same time of a certain fuel spray amount, and the mixing unevenness is reduced. Although the nozzle is integrated on the surface of the blade, the complexity of the structure is reduced, the manufacturing process of the blade is more complex, and the subsequent upgrading and maintenance are more complicated.
According to the embodiment of the invention, on the basis of the existing axial swirler, a mode of changing the area of an outer layer flow passage is provided according to the obvious difference of the air flow of the inner layer and the air flow of the outer layer of the existing axial swirler, so that the difference of the air flow of the inner layer and the air flow of the outer layer of the axial swirler is reduced, and the mixing of fuel and air is more uniform, wherein the mixing can be realized by changing the thickness of the front edge or the tail edge of a blade or by adding a new fuel jet port on the.
The first embodiment is as follows: this embodiment provides a swirler combustion chamber structure of improvement mixing degree of consistency, to the outer air flow difference in current axial swirler, adopt the vibration material disk to make the technique, the printing direction is from the bottom up, make the swirler of this embodiment realize, this embodiment still provides fuel to the blade through the central body, by the through-hole blowout on blade surface, through the thickness along radial outside gradual increase blade leading edge, the blade trailing edge then keeps inside and outside the same thickness, in order to change outer flow area, make the outer air flow difference of the outer air flow of swirler and swirler inlayer reduce, improve the mixing degree of consistency of fuel and air.
As shown in fig. 2 and 3, in the present embodiment, the central body 100 is a central cylindrical portion, the blades 200 are hard-connected to the central body 100, the vanes 200 are integrally formed in the manufacturing process, the vanes 200 are fixed on the central body 100, a hollow channel for fuel to pass through is arranged in the central body 100, a hollow channel for fuel to pass through is also arranged in the vanes 200, the hollow channel and the hollow channel are communicated, so that the fuel can reach the vanes 200 through the central body 100, the surfaces of the vanes 200 are provided with through holes 201 for fuel to spray out, the vanes 200 are bent along the axial direction of the central body 100, the convex cambered surfaces of the vanes 200 are suction surfaces 202, the concave cambered surfaces are pressure surfaces 203, the through holes 201 are communicated with the suction surfaces 202 and the pressure surfaces 203, and a trailing edge 204, wherein the top surface 205 of the vane is contacted and fixed with the casing 400, and the outer side of the casing 400 is provided with an annular fixing part 401 and two raised positioning bayonets 403 with an included angle of 90 degrees for fixing the swirler. In the embodiment, the thickness of the leading edge of the vane 200 is gradually increased radially outwards, the leading edge of the vane is the end of the vane at the air inlet of the cyclone, so that the outer layer flow passage area of the cyclone is gradually reduced, the flow of the entering air is reduced, the difference of the air flow of the inner layer and the outer layer of the cyclone is reduced, the combustion chamber operates in a low mach number (the mach number is less than 0.3), the thickness of the trailing edge 204 of the vane does not need to be increased, and the mixing difference of the inner layer and the outer layer of the. This embodiment is implemented by additive manufacturing printing, and the support rib 300 is removed after manufacturing.
Example two: this embodiment provides a swirler combustion chamber structure of improvement mixing degree of consistency, to the outer air flow difference in current axial swirler, adopt the vibration material disk manufacturing technique, the printing direction is from the bottom up, make the swirler of this embodiment realize, this embodiment still provides fuel to the blade through the central body, spout by the through-hole on blade surface, through the thickness along radial outside gradually increasing blade leading edge and blade trailing edge, in order to change outer runner area, the two thickness that increase can be different, make the outer air flow difference of outer air flow of swirler and swirler inlayer reduce, improve the mixing degree of consistency of fuel and air, simultaneously in order to prevent to cause bluff body backward flow district at the trailing edge, set up the fuel blowout mouth in trailing edge department trompil. And can also be used for adjusting the thermoacoustic oscillation of the combustion chamber.
As shown in fig. 4 and 5, in this embodiment, the same parts as those in the first embodiment are not described again, in this embodiment, the leading edges and the trailing edges 204 of the blades gradually increase in thickness along the radial direction outward, the leading edges of the blades are the ends of the blades at the air inlet of the cyclone, the trailing edges of the blades are the ends of the blades at the air outlet of the cyclone, and the leading edges of the blades are opposite to the trailing edges of the blades, so that the flow passage area of the outer layer of the cyclone is gradually reduced, the flow rate of the entering air is reduced, and the difference between the air flow. On the basis, under the condition of medium and low swirl number (the swirl number is less than 0.6), if the trailing edge 204 of the blade is thin, certain requirements are imposed on the manufacturing process of the blade, and if the trailing edge 204 of the blade is thick, a backflow region caused by a blunt body is formed at the trailing edge of the blade, so that the embodiment adopts the steps of gradually increasing the thickness of the trailing edge 204 outwards along the radial direction, forming a hole at the outer layer of the trailing edge 204, arranging a trailing edge fuel spray port 206, performing fuel injection, pulling the distance from the spray port to flame along the axial direction, and adjusting the proportion of the fuel spray amount on the surface of the blade to the fuel spray amount at the trailing edge of the blade, so that the problem of thermoacoustic oscillation of the combustion chamber can be adjusted and improved. In this embodiment, the fuel still reaches the inside of the vane 200 through the central body 100, and the inside of the vane 200 needs a passage for the fuel to pass through to communicate with the fuel outlet 206 at the trailing edge of the vane, which cannot be satisfied by the traditional die casting process.
Example three: this embodiment provides a swirler combustion chamber structure of improvement mixing degree of consistency, to the outer inlayer air flow difference of current axial swirler, adopt the vibration material disk to make the technique, print the direction for from the bottom up, make the swirler of this embodiment realize, this embodiment is through increasing fuel ejection port in the outer layer of swirler to change outer runner area, do not change blade thickness, make the outer air flow of swirler and the air flow difference of swirler inlayer reduce, improve the mixing degree of consistency of fuel and air. The fuel source for the outer fuel port is not the center body and therefore does not require a fuel passage in communication with the center body. The blade tail edge has certain headspace, can install other devices additional in follow-up upgrading. And can also be used for adjusting the thermoacoustic oscillation of the combustion chamber.
As shown in fig. 6 and 7, in the present embodiment, the central body 100 is used as a central cylindrical portion, the vanes 200 are hard-connected to the central body, the vanes 200 are integrally formed in the manufacturing process, the vanes 200 are fixed on the central body 100, a hollow channel for fuel to pass through is arranged in the central body 100, a hollow channel for fuel to pass through is also arranged in the vanes 200, the hollow channel and the hollow channel are communicated, so that the fuel can reach the vanes 200 through the central body 100, the surfaces of the vanes 200 are provided with through holes 201 for fuel to spray out, the vanes 200 are bent along the axial direction of the central body 100, the convex cambered surfaces of the vanes 200 are suction surfaces 202, the concave cambered surfaces are pressure surfaces 203, the through holes 201 are communicated with the suction surfaces 202 and the pressure surfaces 203, and a trailing edge 204, wherein the top surface 205 of the vane is contacted and fixed with the casing 400, and the outer side of the casing 400 is provided with an annular fixing part 401 and two raised positioning bayonets 403 with an included angle of 90 degrees for fixing the swirler. In this embodiment, a plurality of outer fuel outlets 207 and outer support plates 207 'for supporting the outer fuel outlets are disposed on the inner wall of the swirler case 400 near the air inlet of the combustion chamber, and the outer support plates 207' are fixed on the inner wall of the swirler case 400 to reduce the outer flow passage area of the swirler, so as to reduce the outer air flow of the swirler, increase the fuel spraying ratio, reduce the mixing difference between the inner layer and the outer layer of the swirler, and improve the mixing uniformity. In this embodiment, fuel is injected into the outer flow passage of the swirler through the outer fuel injection port 207 of the combustion chamber, and the fuel passage communicating with the center body 100 is not required inside the vane 200. Because the fuel enters the mixing area from the outer layer of the swirler, the problem of thermoacoustic oscillation of the combustion chamber can be adjusted and improved by adjusting the axial distance d between the outer layer fuel jet 207 and the tail edge 204 of the vane.
According to the embodiment of the invention, the time lag term of the fuel sprayed to the flame is increased by adjusting the flight time of the fuel, so that energy waves with different phases in the swirler are linearly superposed to adjust and improve the thermoacoustic oscillation problem.
The above-mentioned embodiments are intended to illustrate the objects, technical solutions and advantages of the present invention in further detail, and it should be understood that the above-mentioned embodiments are only exemplary embodiments of the present invention, and are not intended to limit the present invention, and any modifications, equivalents, improvements and the like made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (9)
1. A swirler combustor structure for improved mixing, comprising: the central body is positioned at the central position, the blades are arranged around the central body, the outer shell is positioned on the outer layer of the blades, and the central body, the blades and the outer shell are fixedly connected;
the vane is provided with a front edge, an opposite tail edge, a suction surface, an opposite pressure surface and a through hole for spraying fuel on the surface of the vane, the outer side of the shell is provided with an annular fixing part and two raised positioning bayonets with an included angle of 90 degrees, and the tail edge of the vane keeps the same thickness inside and outside by gradually increasing the thickness of the front edge of the vane outwards along the radial direction.
2. The swirler combustor structure for improving blending of claim 1, wherein the combustor operates in a region with a mach number of less than 0.3.
3. A swirler combustor structure for improved mixing, comprising: the central body is positioned at the central position, the blades are arranged around the central body, the outer shell is positioned on the outer layer of the blades, and the central body, the blades and the outer shell are fixedly connected;
the vane is provided with a front edge, an opposite tail edge, a suction surface, an opposite pressure surface and a through hole for spraying fuel on the surface of the vane, the outer side of the shell is provided with an annular fixing part and two raised positioning bayonets with an included angle of 90 degrees, and the thicknesses of the front edge and the tail edge of the vane can be gradually increased along the radial direction outwards.
4. The swirler combustor structure with improved blending of claim 3, wherein the added thickness of the vane leading edge and the vane trailing edge may be different.
5. The swirler combustor structure for improving mixing of claim 3, wherein the fuel outlets are provided at the vane trailing edge openings.
6. A swirler combustor structure for improved mixing, comprising: the central body is positioned at the central position, the blades are arranged around the central body, the outer shell is positioned on the outer layer of the blades, and the central body, the blades and the outer shell are fixedly connected;
the vane has front edge, tail edge, sucking surface, pressure surface and through hole for spraying fuel, and the outer casing has annular fixing part and two raised locating bayonets with 90 deg included angle.
7. The swirler combustor structure with improved blending of claim 6, wherein the fuel nozzle is free of fuel passages in communication with the center body.
8. The swirler combustor structure with improved blending of claim 6, wherein a universal device clearance is provided at the trailing edge of the vanes.
9. The structure of claim 1, 3 or 6, wherein the vanes are rigidly connected to the central body and integrally formed, the vanes are fixed to the central body around the central body, and the central body and the vanes have connected hollow passages for fuel to pass through.
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| CN113701194A (en) * | 2021-08-16 | 2021-11-26 | 中国航发沈阳发动机研究所 | Premixing device for combustion chamber of gas turbine |
| CN113983497A (en) * | 2021-10-22 | 2022-01-28 | 北京航空航天大学 | Supercritical combustion chamber and aircraft engine |
| CN114738796A (en) * | 2022-03-09 | 2022-07-12 | 西北工业大学 | Air atomizing nozzle with rotary oil pipe |
| CN114909676A (en) * | 2022-04-28 | 2022-08-16 | 西北工业大学 | Can regulate and control single-stage axial swirler of whirl intensity |
| CN115183276A (en) * | 2022-07-25 | 2022-10-14 | 清航空天(北京)科技有限公司 | Fuel supply assembly, engine combustion chamber structure and engine |
| CN115200048A (en) * | 2022-05-31 | 2022-10-18 | 北京航空航天大学 | Combustion chamber with two-stage blade enhanced mixing |
| CN116221780A (en) * | 2023-03-22 | 2023-06-06 | 中国科学院工程热物理研究所 | Blending mechanism and combustion device |
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| CN115200048A (en) * | 2022-05-31 | 2022-10-18 | 北京航空航天大学 | Combustion chamber with two-stage blade enhanced mixing |
| CN115200048B (en) * | 2022-05-31 | 2023-09-19 | 北京航空航天大学 | Two-stage blade intensified mixing combustion chamber |
| CN115183276A (en) * | 2022-07-25 | 2022-10-14 | 清航空天(北京)科技有限公司 | Fuel supply assembly, engine combustion chamber structure and engine |
| CN116221780A (en) * | 2023-03-22 | 2023-06-06 | 中国科学院工程热物理研究所 | Blending mechanism and combustion device |
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