CN205388321U - A flame surely fires device for combustion chamber - Google Patents
A flame surely fires device for combustion chamber Download PDFInfo
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- CN205388321U CN205388321U CN201620159675.5U CN201620159675U CN205388321U CN 205388321 U CN205388321 U CN 205388321U CN 201620159675 U CN201620159675 U CN 201620159675U CN 205388321 U CN205388321 U CN 205388321U
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- bluff body
- body portion
- combustion chamber
- flow path
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Abstract
The utility model provides a flame surely fires device for combustion chamber is equipped with the nozzle in the antetheca portion of combustion chamber, flame surely fire the device include a plurality of set up in the blunt body of ventilating in the antetheca portion of combustion chamber, it is a plurality of the blunt body of ventilating centers on the lateral surface of nozzle is evenly arranged, ventilate be equipped with on the terminal surface that admits air of the blunt body with the runner of ventilating of the inside intercommunication of combustion chamber, the runner of ventilating is followed the outside of nozzle along radial outside extension of nozzle, the runner of ventilating is outwards expanded along the gas flow direction gradually. Adopt the utility model discloses a device can form two and stay the whirlpool in the combustion chamber, the utility model discloses a flame surely fires device and flame and surely fires the method and compare with current structure and have the better surely ability of firing.
Description
Technical field
This utility model relates to gas-turbine combustion chamber technical field, particularly relates to a kind of flame smooth combustion apparatus for gas-turbine combustion chamber.
Background technology
Gas turbine, due to the advantage such as have simple in construction, single-machine capacity is big, weight and size is little, mobility is good, is widely used in many industrial circles such as aviation, boats and ships, electric power, oil.Combustor is as the critical piece of gas turbine, structurally there is essentially identical feature, the common prescription of the basic law the two aspect that aerothermodynamic aspect factor when the version of combustor is based on combustion chamber operational and combustion process are followed considers and designs, aerothermodynamic aspect factor such as combustor exit temperature, stability, starting ignition, efficiency of combustion, durability, disposal of pollutants characteristic etc..The main function of combustor is that diffusion reduction of speed, fuel prepare, and forms low regime or flame is stablized in recirculating zone.Optimize design, advanced fuel-oil atmozation mode and the advanced combustor cooling technology of head of combustion chamber structure are the important channels solving above-mentioned technological challenge.
According to Theory of Combustion, flame to be stablized in high velocity air, it is necessary to inside burner inner liner, be at least the region that some spatial point places structure local air flow speed is equal with the flame propagation velocity of this place's combustion mixture, namely commonly called incendiary source.In a combustion chamber, the designing points of flame smooth combustion apparatus is structure low speeds flow region.The method in conventional structure low speeds flow region can be divided into two kinds, and one is to adopt entity structure, and such as strong eddy flow, sudden expansion, groove etc., another kind then adopts pneumatic structure, such as contrainjection, transverse injection etc..The method in existing structure low speeds flow region can be only formed a standing vortex, and the ability of smooth combustion is very limited.
The effect in a combustion chamber of flame smooth combustion apparatus can be summarized as following three points: 1) forming recirculating zone at burner inner liner head, being lowered into the air velocity of combustor, thus forming stable ignition source at burner inner liner head, it is ensured that combustor stably and reliably works；2) coordinate with pressure atomized fog jet, play an important role in promoting the broken atomization of fuel oil；3) appropriate air is provided for burner inner liner head, it is ensured that head has applicable excess air coefficient.As can be seen here, as the significant components of combustion chamber flame drum, the service behaviour of combustor is had comprehensive impact by flame smooth combustion apparatus, and the lifting of combustor overall performance is greatly facilitated effect.Existing chamber structure can be only formed a standing vortex, and the ability of smooth combustion is very limited.
Utility model content
The shortcoming of prior art in view of the above, the technical problems to be solved in the utility model is in that to provide one to be capable of two standing vortexes, has the better steady flame smooth combustion apparatus for gas-turbine combustion chamber firing ability.
In order to solve above-mentioned technical problem, this utility model provides a kind of flame smooth combustion apparatus for gas-turbine combustion chamber, the front wall portion of combustor is provided with nozzle, described flame smooth combustion apparatus includes the ventilation bluff body on multiple front wall portion being arranged at described combustor, and multiple described ventilation bluff bodies are evenly arranged around the lateral surface of described nozzle；The air inlet end face of described ventilation bluff body is provided with the venting flow path that the inside with described combustor connects, and described venting flow path is from outside the extending radially outwardly along described nozzle of described nozzle；Described venting flow path expands outwardly gradually along gas circulating direction.
Preferably, the radial section at the place, gas outlet of described venting flow path is vertical with described front wall portion.
Preferably, the gas outlet of described venting flow path is on the medial surface of the front wall portion of described combustor.
Preferably, each described ventilation bluff body includes the first bluff body portion and the second bluff body portion that one end is connected, described second bluff body portion is obliquely installed relative to described first bluff body portion, and the peristome formed between the other end and the other end in described second bluff body portion in described first bluff body portion is towards nozzle；The air inlet end face in described first bluff body portion is provided with first flow, and the air inlet end face in described second bluff body portion is provided with the second runner；Described first flow and described second flow passage, constitute venting flow path；The angle formed between described first flow and described second runner is runner angle；Described runner angle is gradually increased along with the gas circulating direction of described venting flow path.
Further, described first bluff body portion and described second bluff body portion are plate body, and the angle between lateral surface and lateral surface and the described front wall portion in the second bluff body portion in described first bluff body portion is all higher than 90 degree.
As it has been described above, the flame smooth combustion apparatus for gas-turbine combustion chamber of the present utility model, have the advantages that
Flame smooth combustion apparatus of the present utility model has the venting flow path of multiple expansion shape, when gas is by forming air-flow after venting flow path, there will be in the gas outlet of venting flow path by wind region, a part of air-flow is the axial axial flow in the same direction with described combustor, and axial flow can formed one-level standing vortex by wind region；The fuel oil gushed out from nozzle first passes around one-level standing vortex, carries out prevapourising and pre-cracking under the effect of high temperature reflux, contributes to combustion oil atomization and fully burning；Another part air-flow is the oblique air-flow being affixed to wall flowing, when oblique air current flow is to the middle part of described combustor, by the jet action of primary holes, mutually blend, define two grades of standing vortex regions, two grades of standing vortexes are as stable flame region, at stable flame region, fuel oil burns in a large number, combustion process by rich oil to oil-poor transition, stablize flame region and be equivalent to the primary zone of traditional combustion room so that fuel and air fully react.Adopting device of the present utility model can form two standing vortexes in a combustion chamber, flame smooth combustion apparatus of the present utility model and flame smooth burning method have better steady combustion ability compared with existing structure.
Accompanying drawing explanation
Fig. 1 be shown as the present embodiment for gas-turbine combustion chamber flame smooth combustion apparatus use time structural representation.
Fig. 2 is shown as the perspective view of the air inlet end of the ventilation bluff body of the flame smooth combustion apparatus for gas-turbine combustion chamber of the present embodiment.
Fig. 3 is shown as the perspective view at the gas outlet place of the venting flow path of the ventilation bluff body of the flame smooth combustion apparatus for gas-turbine combustion chamber of the present embodiment.
Fig. 4 is shown as the schematic cross-section of the air inlet end of the ventilation bluff body of the flame smooth combustion apparatus for gas-turbine combustion chamber of the present embodiment.
Fig. 5 is shown as the schematic cross-section at the gas outlet place of the venting flow path of the ventilation bluff body of the flame smooth combustion apparatus for gas-turbine combustion chamber of the present embodiment.
Fig. 6 is shown as the flame smooth combustion apparatus for gas-turbine combustion chamber of the present embodiment when using, and forms the schematic diagram of one-level standing vortex and two grades of standing vortexes.
Drawing reference numeral explanation
100 combustor
110 front wall portions
The medial surface of 111 front wall portions
120 combustion barrel bodies
121 primary holes
200 nozzles
210 jets
300 ventilation bluff bodies
310 air inlet end faces
320 venting flow path
321 gas outlets
410 first bluff body portions
411 first flows
420 second bluff body portions
421 second runners
510 one-level standing vortexes
520 2 grades of standing vortexes
α runner angle
Detailed description of the invention
By particular specific embodiment, embodiment of the present utility model being described below, those skilled in the art the content disclosed by this specification can understand other advantages of the present utility model and effect easily.
Refer to accompanying drawing.Notice, the structure of this specification institute accompanying drawings depicted, ratio, size etc., all only in order to coordinate the disclosed content of description, understand for those skilled in the art and read, it is not limited to the enforceable qualifications of this utility model, therefore do not have technical essential meaning, the adjustment of the modification of any structure, the change of proportionate relationship or size, under not affecting effect that this utility model can be generated by and the purpose that can reach, all should still drop on the disclosed technology contents of this utility model and obtain in the scope that can contain.Simultaneously, in this specification cited as " on ", D score, "left", "right", " centre " and " one " etc. term, it is merely convenient to understanding of narration, and it is not used to limit the enforceable scope of this utility model, the change of its relativeness or adjustment, changing under technology contents without essence, when being also considered as the enforceable category of this utility model.
As shown in Figures 1 to 6, the flame smooth combustion apparatus for gas-turbine combustion chamber 100 of the present embodiment, combustor 100 includes combustion barrel body 120 and the front wall portion 110 being arranged on combustion barrel body 120, front wall portion 110 is provided with nozzle 200, and the jet 210 of nozzle 200 stretches in combustion barrel body 120；The side of combustion barrel body 120 is circumferentially evenly arranged several primary holes 121, and several primary holes 121 have been in the middle part of combustion barrel body 120；In the present embodiment, the aperture of primary holes 121 is 8mm, and combustion barrel body 120 is cylindrical；
Flame smooth combustion apparatus includes the ventilation bluff body 300 on multiple front wall portion 110 being arranged at combustor 100, and multiple ventilation bluff bodies 300 are evenly arranged around the lateral surface of nozzle 200；The air inlet end face 310 of ventilation bluff body 300 is provided with the venting flow path 320 that the inside with combustor 100 connects, and venting flow path 320 is from outside the extending radially outwardly along nozzle 200 of nozzle 200；Venting flow path 320 expands outwardly gradually along gas circulating direction, and the size of venting flow path 320 is gradually increased along gas circulating direction.
Flame smooth combustion apparatus has the venting flow path 320 of multiple expansion shape, owing to venting flow path 320 is from outside the extending radially outwardly along nozzle 200 of nozzle 200, venting flow path 320 expands outwardly gradually along gas circulating direction, and the size of venting flow path 320 is gradually increased along gas circulating direction；So, when gas is by forming air-flow after expanding outwardly venting flow path 320 gradually, there will be in the gas outlet 321 of venting flow path 320 by wind region, a part of air-flow is the axial axial flow in the same direction with combustor 100, and axial flow can formed one-level standing vortex 510 by wind region；The fuel oil gushed out from nozzle 200 first passes around one-level standing vortex 510, carries out prevapourising and pre-cracking under the effect that the internal high temperature of combustion barrel body 120 refluxes, and contributes to combustion oil atomization and fully burning；Another part air-flow is the oblique air-flow being affixed to wall flowing, when oblique air current flow is to the middle part of combustor 100, jet action by primary holes 121, defining two grades of standing vortex 520 regions, two grades of standing vortexes 520 are as stable flame region, at stable flame region, fuel oil burns in a large number, combustion process to oil-poor transition by rich oil, is stablized flame region and is equivalent to the primary zone of traditional combustion room 100 so that fuel and air fully react.
The radial section at the place, gas outlet 321 of venting flow path 320 is vertical with front wall portion 110.This structure can be easy to form one-level standing vortex 510 and two grades of standing vortexes 520, then the region that one-level standing vortex 510 and two grades of standing vortexes 520 are formed can be clearly distinguished from.
The gas outlet 321 of venting flow path 320 is on the medial surface 111 of the front wall portion 110 of combustor 100.This structure enables axial flow to form one-level standing vortex 510 in the position of the jet 210 closer to nozzle 200.
In the present embodiment, each ventilation bluff body 300 includes the first bluff body portion 410 and the second bluff body portion 420 that one end is connected, second bluff body portion 420 is obliquely installed relative to the first bluff body portion 410, and the peristome formed between the other end and the other end in the second bluff body portion 420 in the first bluff body portion 410 is towards nozzle 200；The air inlet face in the first bluff body portion 410 is provided with first flow 411, and the air inlet face in the second bluff body portion 420 is provided with the second runner 421；First flow 411 connects with the second runner 421, constitutes venting flow path 320；The angle formed between first flow 411 and the second runner 421 is runner angle α；Runner angle α is gradually increased along with the gas circulating direction of venting flow path 320.
Each ventilation bluff body 300 is to be formed the structure with angle by the first bluff body portion 410 and the second bluff body portion 420, and multiple ventilation bluff bodies 300 are evenly arranged around the lateral surface of nozzle 200, it becomes possible to form star structure；The quantity of ventilation bluff body 300 is even number, in the present embodiment, the quantity of ventilation bluff body 300 is 6, due to runner angle α along with the gas circulating direction of venting flow path 320 is gradually increased, namely defining the star structure with the venting flow path 320 expanded gradually, the structure making the flame smooth combustion apparatus of the present embodiment is more compact.The structure with angle formed is connected by the first bluff body portion 410 and the second bluff body portion 420, the oblique air-flow enabling to first flow 411 and the discharge of the second runner 421 is converged, the oblique air-flow making each ventilation bluff body 300 is more concentrated, improve flow and the flow velocity of oblique air-flow, it is simple to form stable two grade standing vortex 520.
In the present embodiment, the distance of the lateral surface of ventilation bluff body 300 and nozzle 200 is less than the distance of ventilation bluff body 300 with front wall portion 110 edge, so, the axial flow forming one-level standing vortex 510 can near the jet 210 of nozzle 200, and fuel oil can be carried out prevapourising and pre-cracking by one-level standing vortex 510 fully.
Due in the present embodiment, the radial section of first flow 411 and the second runner 421 is rectangle, first bluff body portion 410 and the second bluff body portion 420 are disposed as plate body, and the angle between lateral surface and lateral surface and the front wall portion 110 in the second bluff body portion 420 in the first bluff body portion 410 is all higher than 90 degree.This structure makes the first bluff body portion 410 consistent with the structure of the venting flow path 320 expanded gradually with the overall structure in the second bluff body portion 420.
Adopting the flame smooth burning method of the flame smooth combustion apparatus for gas-turbine combustion chamber 100 of the present embodiment, nozzle 200 sprays into fuel oil to the inside of combustor 100, and the inside of combustor 100 carries out combustion reaction；Primary holes 121 passes into air, simultaneously, air enters the inside of combustor 100 also by the venting flow path 320 expanded outwardly gradually of ventilation bluff body 300, and forms the axially axial flow in the same direction with combustor 100 and be affixed to the oblique air-flow that wall flows, axial flow formation one-level standing vortex 510；When oblique air current flow is to the middle part of combustor 100, it is subject to the effect of the air-spray of primary holes 121, mutually blends, form two grades of standing vortexes 520；One-level standing vortex 510 is subject to the effect of the high temperature reflux of the inside of combustor 100, and the fuel oil of nozzle 200 ejection is carried out prevapourising, cracked in advance；Two grades of standing vortexes 520 are for stablize flame region, and fuel oil burns steadily at stable flame region.
In the present embodiment, each ventilation bluff body 300 is to be connected, by the first bluff body portion 410 and the second bluff body portion 420, the structure with angle formed, the axially symmetric structure that even number ventilation bluff body 300 is is axis of symmetry with the axis of nozzle 200, each ventilation bluff body 300 structure is identical, the medial surface 111 of each venting flow path 320 and combustor 100 front wall portion 110 forms bluff body structure, after venting flow path 320 passes into air, reflux being there will be undersized standing vortex by wind face axial flow, i.e. one-level standing vortex 510, fuel oil can be formed prevapourising by this region, pre-splitting action.Multiple venting flow path 320 form a circle into star structure, the middle part of combustion barrel body 120 is owing to being provided with primary holes 121, the air-spray effect of primary holes 121 makes low-pressure area centered by the middle part of combustion barrel body 120, oblique air-flow acceptor center low-pressure area effect, form two grades of standing vortexes 520, become the main recirculating zone of combustor 100.Adopting device of the present utility model can form two standing vortexes in combustor 100, flame smooth combustion apparatus of the present utility model and flame smooth burning method have better steady combustion ability compared with existing structure.
To sum up, this utility model effectively overcomes various shortcoming of the prior art and has high industrial utilization.
Above-described embodiment only illustrative principle of the present utility model and effect thereof, not for restriction this utility model.Above-described embodiment all under spirit of the present utility model and category, can be modified or change by any those skilled in the art.Therefore, art has all equivalence modification or changes that usually intellectual completes under the spirit disclosed without departing from this utility model with technological thought such as, must be contained by claim of the present utility model.
Claims (5)
1., for a flame smooth combustion apparatus for gas-turbine combustion chamber, the front wall portion (110) of combustor (100) is provided with nozzle (200), it is characterised in that
Described flame smooth combustion apparatus includes the ventilation bluff body (300) on multiple front wall portion (110) being arranged at described combustor (100), and multiple described ventilation bluff bodies (300) are evenly arranged around the lateral surface of described nozzle (200)；
The air inlet end face (310) of described ventilation bluff body (300) is provided with the venting flow path (320) that the inside with described combustor (100) connects, and described venting flow path (320) is from outside the extending radially outwardly along described nozzle (200) of described nozzle (200)；Described venting flow path (320) expands outwardly gradually along gas circulating direction.
2. the flame smooth combustion apparatus for gas-turbine combustion chamber according to claim 1, it is characterised in that: the radial section at gas outlet (321) place of described venting flow path (320) is vertical with described front wall portion (110).
3. the flame smooth combustion apparatus for gas-turbine combustion chamber according to claim 1, it is characterised in that: the gas outlet (321) of described venting flow path (320) is on the medial surface (111) of the front wall portion (110) of described combustor (100).
4. the flame smooth combustion apparatus for gas-turbine combustion chamber according to claim 1, it is characterized in that: each described ventilation bluff body (300) includes the first bluff body portion (410) and the second bluff body portion (420) that one end is connected, described second bluff body portion (420) is obliquely installed relative to described first bluff body portion (410), and the peristome formed between the other end and the other end in described second bluff body portion (420) in described first bluff body portion (410) is towards described nozzle (200)；
Described first bluff body portion (410) is provided with first flow (411), and described second bluff body portion (420) is provided with the second runner (421)；Described first flow (411) connects with described second runner (421), constitutes venting flow path (320)；
The angle formed between described first flow (411) and described second runner (421) is runner angle；Described runner angle is gradually increased along with the gas circulating direction of described venting flow path (320).
5. the flame smooth combustion apparatus for gas-turbine combustion chamber according to claim 4, it is characterized in that: described first bluff body portion (410) and described second bluff body portion (420) are plate body, and the angle between lateral surface and lateral surface and the described front wall portion (110) in the second bluff body portion (420) in described first bluff body portion (410) is all higher than 90 degree.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620159675.5U CN205388321U (en) | 2016-03-02 | 2016-03-02 | A flame surely fires device for combustion chamber |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620159675.5U CN205388321U (en) | 2016-03-02 | 2016-03-02 | A flame surely fires device for combustion chamber |
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| CN205388321U true CN205388321U (en) | 2016-07-20 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105588144A (en) * | 2016-03-02 | 2016-05-18 | 上海电气燃气轮机有限公司 | Flame steady combustion device and method for combustion chamber of gas turbine |
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2016
- 2016-03-02 CN CN201620159675.5U patent/CN205388321U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105588144A (en) * | 2016-03-02 | 2016-05-18 | 上海电气燃气轮机有限公司 | Flame steady combustion device and method for combustion chamber of gas turbine |
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