CN202675358U - Mixing device, combustion chamber and aeroengine - Google Patents
Mixing device, combustion chamber and aeroengine Download PDFInfo
- Publication number
- CN202675358U CN202675358U CN 201220335198 CN201220335198U CN202675358U CN 202675358 U CN202675358 U CN 202675358U CN 201220335198 CN201220335198 CN 201220335198 CN 201220335198 U CN201220335198 U CN 201220335198U CN 202675358 U CN202675358 U CN 202675358U
- Authority
- CN
- China
- Prior art keywords
- circulation road
- goes out
- fuel inlet
- input pipe
- grades
- 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.)
- Expired - Lifetime
Links
- 238000002485 combustion reaction Methods 0.000 title claims abstract description 101
- 238000002156 mixing Methods 0.000 title claims abstract description 42
- 239000000446 fuel Substances 0.000 claims abstract description 91
- 238000007599 discharging Methods 0.000 claims description 21
- 230000015572 biosynthetic process Effects 0.000 claims description 11
- 238000005452 bending Methods 0.000 claims description 9
- 238000001816 cooling Methods 0.000 claims description 6
- 238000009434 installation Methods 0.000 abstract 5
- 239000003921 oil Substances 0.000 description 39
- 239000000295 fuel oil Substances 0.000 description 28
- 239000007789 gas Substances 0.000 description 12
- MWUXSHHQAYIFBG-UHFFFAOYSA-N nitrogen oxide Inorganic materials O=[N] MWUXSHHQAYIFBG-UHFFFAOYSA-N 0.000 description 11
- 238000005516 engineering process Methods 0.000 description 10
- GQPLMRYTRLFLPF-UHFFFAOYSA-N Nitrous Oxide Chemical compound [O-][N+]#N GQPLMRYTRLFLPF-UHFFFAOYSA-N 0.000 description 6
- UGFAIRIUMAVXCW-UHFFFAOYSA-N Carbon monoxide Chemical compound [O+]#[C-] UGFAIRIUMAVXCW-UHFFFAOYSA-N 0.000 description 5
- 229910002091 carbon monoxide Inorganic materials 0.000 description 5
- 238000000034 method Methods 0.000 description 5
- 239000007921 spray Substances 0.000 description 5
- 229910052799 carbon Inorganic materials 0.000 description 4
- 238000010304 firing Methods 0.000 description 4
- 239000001257 hydrogen Substances 0.000 description 4
- 229910052739 hydrogen Inorganic materials 0.000 description 4
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 3
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 3
- 239000003344 environmental pollutant Substances 0.000 description 3
- 239000002737 fuel gas Substances 0.000 description 3
- 238000002347 injection Methods 0.000 description 3
- 239000007924 injection Substances 0.000 description 3
- JTJMJGYZQZDUJJ-UHFFFAOYSA-N phencyclidine Chemical class C1CCCCN1C1(C=2C=CC=CC=2)CCCCC1 JTJMJGYZQZDUJJ-UHFFFAOYSA-N 0.000 description 3
- 231100000719 pollutant Toxicity 0.000 description 3
- 239000000243 solution Substances 0.000 description 3
- 230000008901 benefit Effects 0.000 description 2
- -1 carbon hydrogen Chemical class 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 239000012530 fluid Substances 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 230000008520 organization Effects 0.000 description 2
- 230000000505 pernicious effect Effects 0.000 description 2
- 239000000843 powder Substances 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 238000000889 atomisation Methods 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 230000009194 climbing Effects 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 239000006185 dispersion Substances 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 239000002245 particle Substances 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
Images
Abstract
The utility model discloses a mixing device, a combustion chamber and an aeroengine which relate to the technical field of aviation and solve the technical problem of the prior art that the combustion efficiency is low. The mixing device comprises a fuel input pipe, a primary input pipe, a secondary input pipe, a tertiary input pipe, a circular installation wall and a positioning wall body; a first outflow channel is formed between the primary input pipe and the fuel input pipe; a second outflow channel is formed between the secondary input pipe and the primary input pipe; a third outflow channel is formed between the tertiary input pipe and the secondary input pipe; an installation gap is formed between the circular installation wall and the tertiary input pipe, and at least one first fuel inlet which is communicated with the third outflow channel and the installation gap is arranged on the tertiary input pipe; and a fourth outflow channel is formed between the positioning wall body and the circular installation wall. The combustion chamber and the aeroengine respectively comprise the mixing device. The mixing device, the combustion chamber and the aeroengine are used for improving the combustion efficiency of the combustion chamber.
Description
Technical field
The utility model relates to the aeronautical technology field, is specifically related to a kind of mixing device, a kind of combustion chamber and a kind of aero-engine that this combustion chamber is set that this mixing device is set.
Background technology
Along with the atmospheric environment problem worldwide receives increasing concern, require more and more stricter especially for the aero-engine pollutant emission.The Aeroengine Products market demand of future generation shows, the discharge capacity of nitrogen oxide (NOx) also will reduce about 50% than existing International Civil Aviation Organization (ICAO) required standard, and other emissions all keep certain nargin than the discharge index of International Civil Aviation Organization's regulation such as carbon monoxide (CO) and unburned carbon hydrogen (UHC) simultaneously.
Studies show that: the indoor fuel gas temperature of control combustion is the key of control nitrogen oxides pollution discharging, and one of Major Technology of control combustion district temperature is exactly to adopt poor oil firing's pattern.Especially under the large operating modes such as climbing, take off, can effectively reduce combustion zone temperature by poor oil firing, reduce discharged nitrous oxides; Under the little operating mode such as ground idle speed, starting ignition, need the combustion zone to adopt local fuel-rich combustion, to guarantee the combustion chamber smooth ignition, also can reduce carbon monoxide and the discharging of unburned carbon hydrogen under the small-power state simultaneously.
In order to solve under the high-power state contradiction of carbon monoxide, the discharging of unburned carbon hydrogen under the discharged nitrous oxides and small-power state, can adopt the pattern of fractional combustion, guarantee that the combustion chamber regional area burns with best fuel-air match pattern under the engine different capacity.The grading combustion technology application of on the aeroengine combustor buring chamber, having succeeded, GE(GENERAL ELECTRIC COMPANY) more work is being done by company aspect the low emission combustor of this type, designed the fuel injection equipment (FIE) that to realize poor oil firing, and be applied at engine, such as: the dicyclo cavity combustion chamber grading combustion technology that the GE90 engine adopts; The center grading combustion technology that the GEnx engine adopts etc.
Employing center grading combustion technology has the advantages such as compact conformation, subregion poor oil firing control nitrogen oxide effect is better, existing two-stage classification is little for classification point place main combustion stage fuel flow in the combustion chamber of oil tech, injection drop is low owing to use, cause Local Oil-gas than on the low side, atomization quality is poor, finally causes efficiency of combustion lower.People have expected having designed three grades of classification fuel feeding technology in the two-stage classification for the basis of oil tech for this reason, but at most only there are two combustion zones (the first combustion zone 21 and the second combustion zone 221,222) in the combustion chamber 1 of three grades of classification fuel feeding of existing application technology as shown in Figure 1, can not really change the oil-gas ratio in downstream, so still there is the low technical problem of efficiency of combustion.
The utility model content
The purpose of this utility model is to propose a kind of mixing device, a kind of combustion chamber and a kind of aero-engine that this combustion chamber is set that this mixing device is set, and has solved prior art and has had the low technical problem of efficiency of combustion.
For achieving the above object, the utility model provides following technical scheme:
The mixing device that the utility model embodiment provides comprises fuel inlet pipe, one-level input pipe, secondary input pipe, three grades of input pipes, annular assembly wall and location wall bodies, wherein:
Described one-level input pipe is sheathed on outside the described fuel inlet pipe, and formation first goes out circulation road between described one-level input pipe and the described fuel inlet pipe;
Described secondary input pipe is sheathed on outside the described one-level input pipe, and formation second goes out circulation road between described secondary input pipe and the described one-level input pipe;
Described three grades of input pipes are sheathed on outside the described secondary input pipe, and formation the 3rd goes out circulation road between described three grades of input pipes and the described secondary input pipe;
Described annular assembly wall is sheathed on outside described three grades of input pipes, and there is assemblage gap between described annular assembly wall and the described three grades of input pipes, is provided with on described three grades of input pipes with the described the 3rd and goes out at least one first fuel inlet that circulation road and described assemblage gap are connected;
Described location wall body is coated on outside the described annular assembly wall, and formation the 4th goes out circulation road between described location wall body and the described annular assembly wall;
Described first goes out circulation road, described second goes out circulation road, the described the 3rd and goes out circulation road, the described the 4th and go out the circulation road flow path direction (go out flow path direction and also can be described as the discharging direction) that goes out separately all the discharging direction with described fuel inlet pipe is consistent.
Preferably, described first goes out circulation road, described second goes out circulation road, the described the 3rd and goes out circulation road and the described the 4th and go out that one of them is provided with cyclone at least in the circulation road, and the air-out direction of described cyclone is consistent with the discharging direction of described fuel inlet pipe.
Preferably, be provided with on the described annular assembly wall with described assemblage gap and the described the 4th and go out at least one second fuel inlet that circulation road is connected, the described the 3rd goes out circulation road and the described the 4th goes out to be provided with described cyclone on the circulation road, the described the 3rd air outlet that goes out the described cyclone in the circulation road is towards described the first fuel inlet, and the described the 4th goes out the air outlet of the described cyclone in the circulation road towards described the second fuel inlet.
Preferably, be provided with at least two described the first fuel inlets on described three grades of input pipes, and described the first fuel inlet distributes evenly along circumferential direction or the axial direction of described three grades of input pipes; Be provided with at least two described the second fuel inlets on the described annular assembly wall, and described the second fuel inlet distributes evenly along circumferential direction or the axial direction of described annular assembly wall.
Preferably, described one-level input pipe is going out length dimension on the flow path direction at the length dimension that goes out on the flow path direction less than described secondary input pipe, and described secondary input pipe is going out length dimension on the flow path direction at the length dimension that goes out on the flow path direction less than described three grades of input pipes.
Preferably, the direction that described secondary input pipe goes out stream is consistent with the discharging direction of described fuel inlet pipe, and the internal diameter size that goes out the head piece place of described secondary input pipe is increased outwardly gradually by interior.
Preferably, described secondary input pipe goes out tapered, the tubaeform or step in head piece place.
Preferably, the direction that described three grades of input pipes go out stream is consistent with the discharging direction of described fuel inlet pipe, the internal diameter size that goes out the head piece place of described three grades of input pipes is increased outwardly gradually by interior, wherein end on the described annular assembly wall axial direction is bending and the outer surface that goes out the head piece place that is connected to described three grades of input pipes, and described annular assembly wall is to form between the outer surface that the head piece place of an end of bending and described three grades of input pipes to cool off circulation road, and described annular assembly wall is that an end of bending is provided with described and cools off the cooling through hole that circulation road is connected.
Preferably, described location wall body comprises the first location wall and the second location wall, wherein:
Described the first location wall is annular plate, and it is sheathed on outside the described annular assembly wall;
Described the second location wall comprises interconnected lateral part and longitudinal component;
The described the 4th described cyclone that goes out in the circulation road is embedded between the longitudinal component and described the first location wall of described the second location wall;
The inner surface of described lateral part parallels with the outer surface of described annular assembly wall.
The combustion chamber that the utility model embodiment provides comprises the mixing device that the arbitrary technical scheme of the utility model embodiment provides, and also comprises the first oil feed line, the second oil feed line, the 3rd oil feed line and feeder, wherein:
The outlet of described the first oil feed line be connected with the entrance of described fuel inlet pipe or the position relative;
Described the second oil feed line and described the 3rd oil feed line all pass through described assemblage gap, and the outlet of described the second oil feed line is connected with described the first fuel inlet or the position is relative;
Be provided with on the described annular assembly wall with described assemblage gap and the described the 4th and go out at least one second fuel inlet that circulation road is connected, the outlet of described the 3rd oil feed line be connected with described the second fuel inlet or the position relative;
Described first goes out circulation road, described second goes out circulation road, the described the 3rd and goes out circulation road and the described the 4th and go out circulation road and all be connected with the gas outlet of described feeder.
The aero-engine that the utility model embodiment provides comprises the combustion chamber that the arbitrary technical scheme of the utility model embodiment provides.
Based on the arbitrary technical scheme in the technique scheme, the utility model embodiment can produce following technique effect at least:
Owing to exist first to go out circulation road in the mixing device that the utility model provides, second goes out circulation road, the 3rd goes out circulation road and the 4th goes out circulation road, and all the discharging direction with fuel inlet pipe is consistent more than to go out the circulation road flow path direction that goes out separately, go out circulation road from first, the second air that goes out the circulation road ejection has formed the first combustion zone (pre-combustion grade) with the zone that the fuel oil (fuel oil also can be replaced by fuel powder or fuel gas) of inputting from fuel inlet pipe burns, formed the second combustion zone (intergrade) from the 3rd zone that goes out the circulation road air that sprays and the oil inflame of inputting from the first fuel inlet, go out the air of circulation road ejection and the zone of oil inflame has formed the 3rd combustion zone (main combustion stage) from the 4th, as seen, go out circulation road and can be three combustion zone independently supplying fuel oils and air by above-mentioned, not only can make like this fuel oil and the air that enter mixing device more abundant, more uniform blended together, but also be convenient to adjust the fuel oil quality that enters different combustion zones and the ratio (abbreviation oil-gas ratio) of air quality, can select part or all of combustion zone from three combustion zones according to the different operating modes of the engine that this mixing device is set thus, and then can guarantee that fuel oil is more high efficiency, more fully burning.
When the engine that this mixing device is set can only adopt the pre-combustion grade fuel feeding in (for example under idling rating, 30% thrust rating) under the little operating mode, only use the first combustion zone at this moment, can form thus local rich oil district to guarantee fuel oil smooth combustion; When engine (for example cruise and march into the arena state) under medium-heavy duty can adopt pre-combustion grade and intergrade fuel feeding, only use the first combustion zone and the second combustion zone this moment, limited fuel oil can be concentrated on pre-combustion grade and intergrade thus, be conducive to like this improve the Local Oil-gas ratio and improve the fuel-oil atmozation quality, and then improve efficiency of combustion and disposal of pollutants performance; When engine can adopt pre-combustion grade, intergrade and main combustion stage fuel feeding in large operating mode lower time, the first combustion zone, the second combustion zone and the 3rd combustion zone have been utilized simultaneously this moment, thereby guarantee that the combustion chamber can discharge enough heats, this shows: with respect to prior art, the coupling design of three grades of more convenient oil gas of fuel system that the utility model provides, make the engine that this mixing device is set in wider oil-gas ratio scope, to realize efficient combustion, have the low technical problem of efficiency of combustion so solved prior art.Because the utility model can improve the efficiency of combustion of fuel oil, so compared with prior art, the utility model combustion chamber obtains in the situation of identical heat energy, the fuel oil that expends still less, and then the pernicious gas (carbon monoxide, unburned carbon hydrogen or nitrogen oxide) of discharging is also less, especially can still less, can also realize low pollution emission thus in engine operation at the pernicious gas of little operating mode discharging of lower time.
Description of drawings
Accompanying drawing described herein is used to provide further understanding of the present utility model, consists of the application's a part, and illustrative examples of the present utility model and explanation thereof are used for explaining the utility model, do not consist of improper restriction of the present utility model.In the accompanying drawings:
The cross-sectional schematic of the combustion chamber of three grades of combustion technologies of application that Fig. 1 provides for prior art;
The cross-sectional schematic of the chief component of mixing device in the combustion chamber that Fig. 2 provides for the utility model embodiment.
Mark among the figure: 1, combustion chamber; 21, the first combustion zone; 221, the second combustion zone; 222, the second combustion zone; 231, the 3rd combustion zone; 232, the 3rd combustion zone; 30, fuel inlet pipe; 31, one-level input pipe; 32, secondary input pipe; 33, three grades of input pipes; 34, annular assembly wall; 35, location wall body; 351, the first location wall; 352, the second location wall; 41, first goes out circulation road; 42, second goes out circulation road; 43, the 3rd goes out circulation road; 44, the 4th goes out circulation road; 45, assemblage gap; 46, cool off circulation road; 5, cyclone; 61, the first fuel inlet; 62, the second fuel inlet; 7, cooling through hole; 81, the first oil feed line; 82, the second oil feed line; 83, the 3rd oil feed line.
The specific embodiment
Below by accompanying drawing Fig. 2 and the mode of enumerating optional embodiment more of the present utility model, the technical solution of the utility model (comprising optimal technical scheme) is described in further detail.Need to prove: any technical characterictic in the present embodiment; any technical scheme all is the technical characterictic of plurality of optional or one or more in the optional technical scheme; can't exhaustive all alternative technical characterictics of the present utility model and alternative technical scheme in order to describe succinct need in the presents; the embodiment that also is not easy to each technical characterictic emphasizes that all it is one of optional numerous embodiments; so those skilled in the art should know: any technical characterictic and any technical scheme in the present embodiment all do not limit protection domain of the present utility model, and protection domain of the present utility model should comprise that those skilled in the art do not pay the thinkable any alternate embodiments of creative work.
The utility model embodiment provides the mixing device that a kind of efficiency of combustion is higher and discharge amount of pollution is little, the aero-engine that the combustion chamber of this mixing device is set and this combustion chamber is set.
As shown in Figure 2, the mixing device that the utility model embodiment provides comprises fuel inlet pipe 30, one-level input pipe 31, secondary input pipe 32, three grades of input pipes 33, annular assembly wall 34 and location wall bodies 35, wherein:
One-level input pipe 31 is sheathed on outside the fuel inlet pipe 30, and formation first goes out circulation road 41 between one-level input pipe 31 and the fuel inlet pipe 30.
Secondary input pipe 32 is sheathed on outside the one-level input pipe 31, and formation second goes out circulation road 42 between secondary input pipe 32 and the one-level input pipe 31.
Three grades of input pipes 33 are sheathed on outside the secondary input pipe 32, and form the 3rd between three grades of input pipes 33 and the secondary input pipe 32 and go out circulation road 43.
Annular assembly wall 34 is sheathed on outside three grades of input pipes 33, and exist between annular assembly wall 34 and the three grades of input pipes 33 to be provided with on 45, three grades of input pipes 33 of assemblage gap with the 3rd and go out at least one first fuel inlet 61 that circulation road 43 and assemblage gap 45 are connected.
Location wall body 35 is coated on outside the annular assembly wall 34, and formation the 4th goes out circulation road 44 between location wall body 35 and the annular assembly wall 34.
First goes out circulation road 41, second goes out circulation road 42, the 3rd and goes out circulation road 43, the 4th and go out circulation road 44 flow path direction (go out flow path direction herein and also can be described as the discharging direction) that goes out separately all the discharging direction with fuel inlet pipe 30 is consistent.
Go out circulation road 41 from first in the present embodiment, the second zone that goes out circulation road 42 air that sprays and the oil inflame of inputting from fuel inlet pipe 30 has formed the first combustion zone 21(pre-combustion grade), formed the second combustion zone 221 from the 3rd air that goes out circulation road 43 ejections with the zone that the fuel oil (fuel oil also can be replaced by fuel powder or fuel gas) of inputting from the first fuel inlet 61 burns, the 222(intergrade), go out the air of circulation road 44 ejection and the zone of oil inflame has formed the 3rd combustion zone 231 from the 4th, the 232(main combustion stage), as seen, go out circulation road and can be three combustion zone independently supplying fuel oils and air by above-mentioned, not only can make like this fuel oil and the air that enter mixing device more abundant, more uniform blended together, but also be convenient to adjust the fuel oil that enters different combustion zones and the ratio (abbreviation oil-gas ratio) of air, can select part or all of combustion zone from three combustion zones according to the different operating modes of the engine that this mixing device is set thus, and then can guarantee that fuel oil is more high efficiency, more fully burning.
First goes out circulation road 41, second and goes out circulation road 42, the 3rd and go out circulation road 43 and the 4th and go out that one of them is provided with cyclone 5 at least in the circulation road 44 in the present embodiment, and the air-out direction of cyclone 5 is consistent with the discharging direction of fuel inlet pipe 30.Cyclone 5 can be used air in the circulation road with mode and the fuel oil blending of vortex gas-flow, so can make air and fuel oil is more abundant, more uniform blended together.
Certainly, do not use cyclone 5 or use other devices that change airflow directions to replace the technical scheme of cyclones 5 yet within protection domain of the present utility model.
Be provided with on the annular assembly wall 34 in the present embodiment with assemblage gap 45 and the 4th and go out at least one second fuel inlet 62 that circulation road 44 is connected, the 3rd goes out circulation road 43 and the 4th goes out to be provided with cyclone 5 on the circulation road 44, the 3rd air outlet that goes out the cyclone (unmarked among the figure) in the circulation road 43 goes out the air outlet of the cyclone 5 in the circulation road 44 towards the second fuel inlet 62 towards the first fuel inlet 61, the four.
Said structure can make fuel oil by the second fuel inlet 62 enter the 4th go out behind the circulation road 44 with the 4th go out in the circulation road 44 air fully, evenly blending, also can make fuel oil by the first fuel inlet 61 can enter the 3rd go out behind the circulation road 43 with the 3rd go out in the circulation road 43 air fully, evenly blending.
Certainly, also within protection domain of the present utility model, at this moment, fuel oil can enter the 4th by the 4th air flow inlet that goes out circulation road 44 with air-flow and go out circulation road 44 technical scheme that the second fuel inlet 62 is not set in the lump.
Be preferably on three grades of input pipes 33 in the present embodiment and be provided with at least two the first fuel inlets 61, and the first fuel inlet 61 evenly distributes along circumferential direction or the axial direction of three grades of input pipes 33, is preferably the first fuel inlet 61 and evenly distributes along circumferential direction and the circumferential direction of three grades of input pipes 33.
With the first fuel inlet 61 in like manner, be provided with at least two the second fuel inlets 62 in this example on the annular assembly wall 34, and the second fuel inlet 62 distributes evenly along circumferential direction or the axial direction of annular assembly wall 34.
This structure makes fuel oil enter the 4th from different a plurality of directions to go out circulation road 44 and the 3rd and go out circulation road 43, so with the 4th go out circulation road 44 or the 3rd and go out quicker, more abundant, more uniform the mixing of air in the circulation road 43.
The length dimension that one-level input pipe 31 is going out on the flow path direction less than secondary input pipe 32 at the length dimension that goes out on the flow path direction in the present embodiment, the length dimension that secondary input pipe 32 is going out on the flow path direction less than three grades of input pipes 33 at the length dimension that goes out on the flow path direction.At this moment, one-level input pipe 31, secondary input pipe 32 and three grades of input pipes 33 have not only all consisted of hierarchic structure in circumferential direction but also at axial direction, so the air that it is exported separately and fuel oil are not only in circumferential direction but also also formed stepped at axial direction, help like this first combustion zone 21, the second combustion zone 221, the 222 and the 3rd combustion zone 231,232 not only all to form hierarchic structure in circumferential direction but also at axial direction, and then fuel is burnt more fully.
The direction that secondary input pipe 32 goes out to flow in the present embodiment is consistent with the discharging direction of fuel inlet pipe 30, and the internal diameter size that goes out the head piece place of secondary input pipe 32 is increased outwardly gradually by interior, and what be preferably secondary input pipe 32 goes out tapered, the tubaeform or step in head piece place.This structure helps to enlarge the second combustion zone 221,222 scope, thereby helps the abundant burning of fuel oil.Discharging direction herein also can be called flow path direction, especially when the fuel by fuel inlet pipe 30 processes be fluid (comprising liquid, gas) or during for the mixture of fluid and particle.One-level input pipe 31 is preferably Venturi tube in this example.Secondary input pipe 32 and other input pipes also can adopt Venturi tube.
To go out the direction of stream consistent with the discharging direction of fuel inlet pipe 30 for three grades of input pipes 33 in the present embodiment, the internal diameter size that goes out the head piece place of three grades of input pipes 33 is increased outwardly gradually by interior, wherein end on annular assembly wall 34 axial directions is bending and the outer surface that goes out the head piece place that is connected to three grades of input pipes 33, and annular assembly wall 34 cools off circulation road 46 for forming between the outer surface that goes out the head piece place of an end of bending and three grades of input pipes 33, and annular assembly wall 34 is provided with and the cooling through hole 7 that cools off circulation road 46 and be connected for an end of bending.Can draw cooling-air from diffuser in this example, the cooling-air that is flowed out by diffuser can effectively reduce the first combustion zone 21 and the second combustion zone 221, the annular assembly wall 34 of 222 junctions (group section) and the temperature of three grades of input pipes 33, the service life of improving annular assembly wall 34 and three grades of input pipes 33 after flowing through and cooling off circulation road 46 and cooling through hole 7.
For improving heat resistance of the present utility model, secondary input pipe 32 is preferably exotic material and makes, and is ablated to prevent in this example.Certainly, other input pipes also can adopt exotic material to make.
Location wall body 35 comprises the first location wall 351 and the second location wall 352 in the present embodiment, and wherein: the first location wall 351 is annular plate, and it is sheathed on outside the annular assembly wall 34.The second location wall 352 comprises interconnected lateral part and longitudinal component.The 4th cyclone 5 that goes out in the circulation road 44 is embedded between the longitudinal component and the first location wall 351 of the second location wall 352.The inner surface of lateral part parallels with the outer surface of annular assembly wall 34.The location wall body 35 of this structure is compact conformation, simple not only, and is convenient to make, and also makes things convenient for the 4th and go out the circulation road 44 interior cyclones 5 that arrange.
The combustion chamber that the utility model embodiment provides comprises the as shown in Figure 2 mixing device that the arbitrary technical scheme of the utility model embodiment provides, and also comprises the first oil feed line 81, the second oil feed line 82, the 3rd oil feed line 83 and feeder, wherein:
The outlet of the first oil feed line 81 be connected with the entrance of fuel inlet pipe 30 or the position relative, be preferably and be connected.The second oil feed line 82 and the 3rd oil feed line 83 all pass through assemblage gap 45, and the outlet of the second oil feed line 82 is connected with the first fuel inlet 61 or the position is relative, is preferably to be connected.
The outlet that annular is provided with on the assembly wall 34 with assemblage gap 45 and the 4th goes out at least one the second fuel inlet 62, the three oil feed line 83 that circulation road 44 is connected be connected with the second fuel inlet 62 or the position relative, be preferably and be connected.First goes out circulation road 41, second goes out circulation road 42, the 3rd and goes out circulation road 43 and the 4th and go out circulation road 44 and all be connected with the gas outlet of feeder.
The outlet of the outlet of the second oil feed line 82 and the 3rd oil feed line 83 is preferably and all adopts simple nozzle in this example.Simple nozzle is preferably the nozzle of the spraying that can spray taper.Because the first fuel inlet 61 is preferably along the circumferential Central Symmetry of three grades of input pipes 33 and arranges, correspondingly, the outlet of the second oil feed line 82 is also arranged along the circumferential Central Symmetry of three grades of input pipes 33, can realize thus multiple spot, the dispersion injection of fuel oil.The 3rd fuel inlet is preferably with the set-up mode of the second fuel inlet 62 similar.
The first oil feed line 81, the second oil feed line 82 and the 3rd oil feed line 83 are preferably with different valves and control its whether conducting, can control the amount that above-mentioned pipeline inputs to the fuel oil of mixing device by the keying of by-pass valve control thus.
The outlet of the first oil feed line 81 also is preferably nozzle in this example, at this moment, beaten after the entering of fuel inlet pipe 30 in the going out on the head piece of the one-level input pipe 31 that adopts Venturi tube by the nozzle of the first oil feed line 81 ejection spray cone at fuel oil, then go out to atomize under the shear action that circulation road 41 and second goes out the swirling eddy that the cyclone in the circulation road 42 provides and spray into the combustion chamber first.
With it in like manner, feeder can go out circulation road 41, second and go out circulation road 42, the 3rd and go out circulation road 43 and the 4th and go out circulation road 44 and supply simultaneously moving air for first, also can be respectively first and go out circulation road 41, second and go out circulation road 42, the 3rd and go out circulation road 43 and the 4th and go out separately supply moving airs of circulation road 44.
In this example in as shown in Figure 2 the mixing device the 4th cyclones 5 and the second location walls 352 that go out in the circulation road 44 weld together (the first location wall 351 can be the part of combustion chamber flame drum) with combustion chamber flame drum, annular assembly wall 34 and second is located to be preferably between the wall 352 and is slidingly matched, and other structures of mixing device can be taken out from burner inner liner.
The aero-engine that the utility model embodiment provides comprises the combustion chamber that the arbitrary technical scheme of the utility model embodiment provides.
Because the combustion chamber that the utility model provides has the efficiency of combustion height, few advantage that discharges pollutants is so be suitable for the efficiency of combustion that improves aero-engine.
Certainly, the mixing device that the utility model is provided or combustion chamber are applied on other engines outside the aero-engine or the mechanical device also within protection domain of the present utility model.
Above-mentioned the utility model disclosed or the interconnected parts or the structural member that relate to, unless otherwise stated, connect and all can be understood as: can be fixedly connected with (for example using bolt or screw to connect) with dismantling, also can be understood as: non-removable being fixedly connected with (for example rivet, weld), also can be understood as: hinged or grafting, certainly, connect also and can be replaced by integral type structure (for example use casting technique is integrally formed to be created) (obviously can't adopt except the integrally formed technique according to this area general knowledge).
In addition, in the disclosed arbitrary technical scheme of above-mentioned the utility model applied term for the expression geometry site unless otherwise stated outer its implication comprise and its approximate, similar or approaching state.
Should be noted that at last: above embodiment is only in order to illustrate that the technical solution of the utility model is not intended to limit; Although with reference to preferred embodiment the utility model is had been described in detail, those of ordinary skill in the field are to be understood that: still can make amendment or the part technical characterictic is equal to replacement the specific embodiment of the present utility model; And not breaking away from the spirit of technical solutions of the utility model, it all should be encompassed in the middle of the technical scheme scope that the utility model asks for protection.
Claims (11)
1. a mixing device is characterized in that, comprises fuel inlet pipe, one-level input pipe, secondary input pipe, three grades of input pipes, annular assembly wall and location wall bodies, wherein:
Described one-level input pipe is sheathed on outside the described fuel inlet pipe, and formation first goes out circulation road between described one-level input pipe and the described fuel inlet pipe;
Described secondary input pipe is sheathed on outside the described one-level input pipe, and formation second goes out circulation road between described secondary input pipe and the described one-level input pipe;
Described three grades of input pipes are sheathed on outside the described secondary input pipe, and formation the 3rd goes out circulation road between described three grades of input pipes and the described secondary input pipe;
Described annular assembly wall is sheathed on outside described three grades of input pipes, and there is assemblage gap between described annular assembly wall and the described three grades of input pipes, is provided with on described three grades of input pipes with the described the 3rd and goes out at least one first fuel inlet that circulation road and described assemblage gap are connected;
Described location wall body is coated on outside the described annular assembly wall, and formation the 4th goes out circulation road between described location wall body and the described annular assembly wall;
Described first goes out circulation road, described second goes out circulation road, the described the 3rd and goes out circulation road, the described the 4th and go out the circulation road flow path direction that goes out separately all the discharging direction with described fuel inlet pipe is consistent.
2. mixing device according to claim 1, it is characterized in that, described first goes out circulation road, described second goes out circulation road, the described the 3rd and goes out circulation road and the described the 4th and go out that one of them is provided with cyclone at least in the circulation road, and the air-out direction of described cyclone is consistent with the discharging direction of described fuel inlet pipe.
3. mixing device according to claim 2, it is characterized in that, be provided with on the described annular assembly wall with described assemblage gap and the described the 4th and go out at least one second fuel inlet that circulation road is connected, the described the 3rd goes out circulation road and the described the 4th goes out to be provided with described cyclone on the circulation road, the described the 3rd air outlet that goes out the described cyclone in the circulation road is towards described the first fuel inlet, and the described the 4th goes out the air outlet of the described cyclone in the circulation road towards described the second fuel inlet.
4. mixing device according to claim 3 is characterized in that, is provided with at least two described the first fuel inlets on described three grades of input pipes, and described the first fuel inlet evenly distributes along circumferential direction or the axial direction of described three grades of input pipes; Be provided with at least two described the second fuel inlets on the described annular assembly wall, and described the second fuel inlet distributes evenly along circumferential direction or the axial direction of described annular assembly wall.
5. according to claim 2 or 3 or 4 described mixing devices, it is characterized in that, described one-level input pipe is going out length dimension on the flow path direction at the length dimension that goes out on the flow path direction less than described secondary input pipe, and described secondary input pipe is going out length dimension on the flow path direction at the length dimension that goes out on the flow path direction less than described three grades of input pipes.
6. mixing device according to claim 5 is characterized in that, the direction that described secondary input pipe goes out stream is consistent with the discharging direction of described fuel inlet pipe, and the internal diameter size that goes out the head piece place of described secondary input pipe is increased outwardly gradually by interior.
7. mixing device according to claim 6 is characterized in that, described secondary input pipe go out tapered, the tubaeform or step in head piece place.
8. mixing device according to claim 6, it is characterized in that, the direction that described three grades of input pipes go out stream is consistent with the discharging direction of described fuel inlet pipe, the internal diameter size that goes out the head piece place of described three grades of input pipes is increased outwardly gradually by interior, wherein end on the described annular assembly wall axial direction is bending and the outer surface that goes out the head piece place that is connected to described three grades of input pipes, and described annular assembly wall is to form between the outer surface that the head piece place of an end of bending and described three grades of input pipes to cool off circulation road, and described annular assembly wall is that an end of bending is provided with described and cools off the cooling through hole that circulation road is connected.
9. mixing device according to claim 3 is characterized in that, described location wall body comprises the first location wall and the second location wall, wherein:
Described the first location wall is annular plate, and it is sheathed on outside the described annular assembly wall;
Described the second location wall comprises interconnected lateral part and longitudinal component;
The described the 4th described cyclone that goes out in the circulation road is embedded between the longitudinal component and described the first location wall of described the second location wall;
The inner surface of described lateral part parallels with the outer surface of described annular assembly wall.
10. a combustion chamber is characterized in that, comprises the arbitrary described mixing device of claim 1-9, also comprises the first oil feed line, the second oil feed line, the 3rd oil feed line and feeder, wherein:
The outlet of described the first oil feed line be connected with the entrance of described fuel inlet pipe or the position relative;
Described the second oil feed line and described the 3rd oil feed line all pass through described assemblage gap, and the outlet of described the second oil feed line is connected with described the first fuel inlet or the position is relative;
Be provided with on the described annular assembly wall with described assemblage gap and the described the 4th and go out at least one second fuel inlet that circulation road is connected, the outlet of described the 3rd oil feed line be connected with described the second fuel inlet or the position relative;
Described first goes out circulation road, described second goes out circulation road, the described the 3rd and goes out circulation road and the described the 4th and go out circulation road and all be connected with the gas outlet of described feeder.
11. an aero-engine is characterized in that, comprises combustion chamber claimed in claim 10.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220335198 CN202675358U (en) | 2012-07-11 | 2012-07-11 | Mixing device, combustion chamber and aeroengine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220335198 CN202675358U (en) | 2012-07-11 | 2012-07-11 | Mixing device, combustion chamber and aeroengine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202675358U true CN202675358U (en) | 2013-01-16 |
Family
ID=47496262
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220335198 Expired - Lifetime CN202675358U (en) | 2012-07-11 | 2012-07-11 | Mixing device, combustion chamber and aeroengine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202675358U (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103196159A (en) * | 2013-03-18 | 2013-07-10 | 哈尔滨工程大学 | Annular grading trapped vortex combustor |
| CN106500130A (en) * | 2016-10-08 | 2017-03-15 | 中国科学院工程热物理研究所 | A kind of three-level layered portion lean premixed combustor of main combustion stage fuel-firing preheating prevapourising |
| CN108204604A (en) * | 2018-03-13 | 2018-06-26 | 中国航空发动机研究院 | Combustion chamber Multi-stage spiral nozzle with mechanical periodicity export structure |
| CN108571747A (en) * | 2017-03-13 | 2018-09-25 | 安萨尔多能源公司 | Burner unit, gas turbine power plant comprising the unit and method of operation thereof |
| CN111425294A (en) * | 2019-01-10 | 2020-07-17 | 中国航发商用航空发动机有限责任公司 | Fuel oil grading device, engine combustion chamber and aircraft engine |
| CN116772239A (en) * | 2023-06-25 | 2023-09-19 | 南昌航空大学 | Powder fuel injection method in afterburner |
-
2012
- 2012-07-11 CN CN 201220335198 patent/CN202675358U/en not_active Expired - Lifetime
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103196159A (en) * | 2013-03-18 | 2013-07-10 | 哈尔滨工程大学 | Annular grading trapped vortex combustor |
| CN103196159B (en) * | 2013-03-18 | 2015-03-11 | 哈尔滨工程大学 | Annular grading trapped vortex combustor |
| CN106500130A (en) * | 2016-10-08 | 2017-03-15 | 中国科学院工程热物理研究所 | A kind of three-level layered portion lean premixed combustor of main combustion stage fuel-firing preheating prevapourising |
| CN108571747A (en) * | 2017-03-13 | 2018-09-25 | 安萨尔多能源公司 | Burner unit, gas turbine power plant comprising the unit and method of operation thereof |
| CN108204604A (en) * | 2018-03-13 | 2018-06-26 | 中国航空发动机研究院 | Combustion chamber Multi-stage spiral nozzle with mechanical periodicity export structure |
| CN108204604B (en) * | 2018-03-13 | 2023-05-23 | 中国航空发动机研究院 | Combustion chamber multi-stage swirl nozzle with periodically varying outlet structure |
| CN111425294A (en) * | 2019-01-10 | 2020-07-17 | 中国航发商用航空发动机有限责任公司 | Fuel oil grading device, engine combustion chamber and aircraft engine |
| CN111425294B (en) * | 2019-01-10 | 2021-05-04 | 中国航发商用航空发动机有限责任公司 | Fuel oil grading device, engine combustion chamber and aircraft engine |
| CN116772239A (en) * | 2023-06-25 | 2023-09-19 | 南昌航空大学 | Powder fuel injection method in afterburner |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103123122B (en) | The lean premixed preevaporated low contamination combustion chamber that a kind of main fuel oil directly sprays | |
| CN104456628B (en) | A kind of layered portion premix low pollution combustor of the lean premix of main combustion stage | |
| CN101799174B (en) | Main combustible stage tangential oil supply premix and pre-evaporation combustion chamber | |
| CN104456627B (en) | A kind of lean premixed preevaporated head of combustion chamber structure using cyclone/pre-lamina membranacea integration main combustion stage | |
| CN206281000U (en) | Pre-combustion grade uses the low emission combustor of double-deck axial swirler | |
| US7757491B2 (en) | Fuel nozzle for a gas turbine engine and method for fabricating the same | |
| CN102022753B (en) | Low-pollution combustion chamber with premixed and pre-evaporated precombustion part | |
| CN101709884B (en) | Premixing and pre-evaporating combustion chamber | |
| CN102200291B (en) | Pneumatic primary level graded low-pollution combustion chamber | |
| CN101275750B (en) | A direct-injection premixed pre-evaporation low-pollution combustion chamber in the turning area of a radial swirler | |
| CN101435585B (en) | Gas turbine combined type fuel evaporating and atomizing combustion apparatus | |
| CN202675358U (en) | Mixing device, combustion chamber and aeroengine | |
| CN102032597B (en) | Premixing pre-vaporization combustion chamber for main combustible stage of discrete pipe | |
| CN102889616B (en) | Multi-point direct spray combustion chamber based on venturi premixing double spiral nozzle | |
| CN106678875B (en) | A low-emission combustor with main combustion stage fueled by fuel injection pipes | |
| CN104406197A (en) | Low-emission reverse flow combustor adopting radial swirl injection and fuel oil grading schemes | |
| CN101694301A (en) | Counter-flow flame combustion chamber | |
| CN103697500B (en) | The premixed preevaporated low contamination combustion chamber of a kind of pair of pre-membrane type main combustion stage of oil circuit four eddy flow | |
| CN103185355B (en) | Premixing pre-evaporation low-pollution combustion chamber with multi-point axial double-stage air auxiliary atomizing nozzle main combustion stage | |
| CN103791518B (en) | A kind of combustion chamber fuel oil sprays and mixing arrangement and aero-engine | |
| CN103629696B (en) | A kind of combustion chamber fuel oil sprays and mixing arrangement and combustion chamber thereof | |
| CN105041539A (en) | Multilevel rotational flow combined type air atomized fuel nozzle device and control method thereof | |
| CN204372988U (en) | A kind of low emission reverse flow type combustor | |
| CN114165814B (en) | A Multipoint Array Synergistic Direct Injection Lean Oil Staged Swirl Combustor | |
| CN108844097A (en) | A kind of oil-poor low pollution combustor directly sprayed of multiple spot |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address |
Address after: 200241 Minhang District Lianhua Road, Shanghai, No. 3998 Patentee after: AECC COMMERCIAL AIRCRAFT ENGINE Co.,Ltd. Address before: 201109 Shanghai city Minhang District Hongmei Road No. 5696 Room 101 Patentee before: AVIC Commercial Aircraft Engine Co.,Ltd. |
|
| CP03 | Change of name, title or address | ||
| CX01 | Expiry of patent term |
Granted publication date: 20130116 |
|
| CX01 | Expiry of patent term |