CN109668173A - A kind of evaporation tubular type compact combustion chamber - Google Patents
A kind of evaporation tubular type compact combustion chamber Download PDFInfo
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- CN109668173A CN109668173A CN201910033416.6A CN201910033416A CN109668173A CN 109668173 A CN109668173 A CN 109668173A CN 201910033416 A CN201910033416 A CN 201910033416A CN 109668173 A CN109668173 A CN 109668173A
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- air film
- film hole
- combustion chamber
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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
- F23R3/30—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices
- F23R3/32—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices being tubular
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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
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/10—Air inlet arrangements for primary air
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Spray-Type Burners (AREA)
Abstract
The invention discloses a kind of evaporation tubular type compact combustion chamber, the inside and outside wall and evaporation tube integrated molding of the combustion chamber mitigate weight, reduce contour dimension, promote overall performance；Inside, interior air film hole and outer air film hole are respectively set on outer wall, interior air film hole and outer air film hole are gradually expanded form air film hole, i.e. interior air film hole and outer air film hole are greater than the area of the other side in the hole area that burner inner liner side is formed, so that the surface area of burner inner liner inner wall increases, strengthen wall surface heat transfer, optimize flow field uniformity, improves efficiency of combustion, combustor exit temperature breadth coefficient is reduced, pollutant emission is reduced.
Description
[technical field]
The invention belongs to microminiature aeroengine combustor buring system fields, and in particular to a kind of evaporation tubular type compact burning
Room.
[background technique]
It is widely used in aero-engine and ground gas turbine combustion chamber using the combustion chamber of evaporation tube structure, especially
It is microminiature power-equipment, foreign countries have conducted extensive research work for micro-satellite cluster, accordingly produce each magnitude
Mature model, form corresponding military, commercial market.Using the combustion chamber of evaporation tube scheme have structure is simple, be easy to plus
The advantages such as work, at low cost and comprehensive combustion performance be good.The weight and volume of combustion chamber itself is that one of aircraft performance is important
Limitation reduces weight and volume while retaining and evaporating tubular type combustion chamber advantage itself, is an important design direction.?
The manufacture of aeroengine combustor buring room and welding in maintenance process or repair welding will lead to material property loss, the welding of some parts or
Properties of product and quality can not be influenced greatly, how to restore or increase by stress-relieving by beat treatment and restorability after repair welding
Strong Weld Performance is always insoluble technological problems.
With the improvement of modern high performance aero-engine performance, turbine-entry temperature is continuously improved.Combustor exit
Combustion gas flows to turbo blade, it is contemplated that the stress that high-speed rotating turbo blade is born is very big, along with rushing for high temperature gas flow
It hits, operating condition is very severe.So combustor exit gas flow temperature field has to comply with the requirement of turbo blade elevated temperature strength, no
There is local hot spot, to guarantee that turbine normally works and the service life.In order to guarantee the normal work of hot-end component, it is necessary to use
The efficient type of cooling.Gaseous film control is exactly the important methods for cooling of current turbine hot-end component.Referring to Fig. 1, traditional cylindrical
Air film hole is under mainstream pressure and frictional force effect, and jet stream is bent and is covered in high-temperature component surface, and formation temperature is lower cold
Air film separates high-temperature fuel gas and wall surface, plays heat-insulated and cooling effect, but flow losses are big, and film overcast rate is low, in height
Jet stream is easy to produce under air blowing ratio and is detached from wall surface, and cooling effect is limited.Cooling efficiency and stream of the shaped film-hole for air film
Field quality has great influence, therefore is important research contents always for the optimization of film hole structure.
[summary of the invention]
It is an object of the invention to overcome the above-mentioned prior art, a kind of evaporation tubular type compact combustion chamber is provided；
The combustion chamber promotes fuel oil and air blending by gradually expanded form air film hole, improves cold air while improving combustion stability and efficiency
In wall surface adhesion, more preferable heat-insulated cooling effect is played.
In order to achieve the above objectives, the present invention is achieved by the following scheme:
A kind of evaporation tubular type compact combustion chamber, including inner and outer wall, inner and outer wall are cylindrical body, inner wall is formed
Cylinder of holster mounted in outer wall formed cylindrical body in, the front end of inner wall is connected with the front end of outer wall by curved wall surface, curved
For wall surface to the external protrusion of combustion chamber, the space that outer wall, inner wall and curved wall surface are formed is burner inner liner；The rear end of outer wall is provided with
Perpendicular to the rear end face of outer wall, rear end face is annular slab, and the outer edge of rear end face is connected with the rear end of outer wall, the inner edge of rear end face
The diameter of a circle that edge is formed is greater than the diameter for the cylindrical body that inner wall is formed；Several are internally provided with from rear end towards burner inner liner
Evaporation tube, circumferentially along rear end face, each evaporation tube is interior inserted with a fuel nozzle for evaporation tube；Inner wall, outer wall, song
Shape wall surface and evaporation tube are integrally formed；
Several interior air film holes are offered on inner wall, several outer air film holes are offered on outer wall；Interior air film hole is in flame
The hole of cylinder one end is interior gas outlet, and the other end is interior air inlet；Outer air film hole is outer gas outlet in the hole of burner inner liner one end, another
End is external admission mouth；The area of interior gas outlet is greater than the area of interior air inlet, and the area of outer gas outlet is greater than the face of external admission mouth
Product.
A further improvement of the present invention is that:
Preferably, interior air inlet and external admission mouth are round or oval；The side wall of interior air film hole and outer air film hole is drawn
It is divided into front side wall and rear wall, the rear wall of interior air film hole is tilted relative to inner wall, and the rear wall of outer air film hole is relative to outer wall
Inclination, front side wall and rear wall are end to end.
Preferably, the angular range of the axis of interior air film hole and inner wall is 28 °~40 °；The axis and outer wall of outer air film hole
Angular range be 28 °~40 °.
Preferably, the area of interior air inlet and external admission mouth is 2mm2~23mm2, the face of interior gas outlet and outer gas outlet
Product is 3mm2~35mm2。
Preferably, interior air film hole with a thickness of 0.3mm~0.6mm, outer air film hole with a thickness of 0.3mm~0.6mm.
Preferably, the spacing ratio between the axis of adjacent interior air film hole 11 is 2~5, the axis of adjacent outer air film hole 12
Spacing ratio between line is 2~5.
Preferably, curved wall surface is evenly arranged with preceding air film hole along its circumferential direction, after rear end face is evenly arranged with along its circumferential direction
Air film hole.
Preferably, the quantity of interior air film hole is 80~100；The quantity of outer air film hole is 180~200；Preceding air film hole
Quantity be 10~15.
Preferably, the axis of the axis of fuel nozzle and evaporation tube is overlapped, the axis of fuel nozzle and burning chamber axis it
Between angle be 15 °~35 °.
Preferably, length of the fuel nozzle inside evaporation tube accounts for the 1%~5% of evaporation tube overall length.
Compared with prior art, the invention has the following advantages:
The invention discloses a kind of evaporation tubular type compact combustion chamber, the inside and outside wall of the combustion chamber and evaporate it is pipe integrated at
Type alleviates the overall weight of equipment, reduces the contour dimension of combustion chamber, reduces the connector usage amount between structural member,
Improve overall performance；Inside, interior air film hole and outer air film hole are respectively set on outer wall, interior air film hole and outer air film hole are gradually
Expanding shape air film hole, i.e., interior air film hole and outer air film hole are greater than the area of the other side in the hole area that burner inner liner side is formed, so that
The surface area of burner inner liner inner wall increases, and strengthens wall surface heat transfer, optimizes flow field uniformity, improve efficiency of combustion, reduces combustion chamber
Exit temperature distribution coefficient reduces pollutant emission.
Further, the flow direction along air from outside to inside, rear wall relative to wall surface tilt so that air from into
Stomata enter gas outlet output, sectional area be a process being gradually increased, i.e., using air film hole flow direction expansion and open up to
Structure is capable of forming a temperature on rear wall and enters the comparable tiny area of air themperature, reduces cold air in air film hole
Exit momentum improves cold air in wall surface adhesion, plays more preferable heat-insulated cooling effect.
Further, the angle of rear wall and wall surface is defined, the flaring hole of different angle develops whirlpool in hole sufficiently,
Optimize jet flow field, combustion gas promotes air-fuel mixture more uniform, greatly by burning indoor external wall surface flaring hole, opposite injection
Degree avoids the appearance of local high temperature zone, promotes burning more stable, efficiency significantly improves.
Further, define that area, the arrangement of air inlet and air outlet, the area and arrangement of air inlet are equal
It is determined by the tolerance of air, and burner inner liner is determined along axial tolerance range of distribution according to design point fuel consumption, in this model
The size and quantity of each round diameter are determined on the basis of enclosing.
Further, it is provided with air film hole on curved wall surface and rear end face, curved wall surface, that is, front end face air inlet can be kept away
Exempt from evaporation tube and be directly exposed to primary zone high-temperature region, reduces the probability of ablation to a certain extent；Rear end face air inlet can promote to fire
Oil and air mixing are more uniform.
Further, evaporation tube is along circumferentially evenly distributed and burner inner liner the axis of combustion chamber flame drum aft bulkhead at certain
Angle, fuel nozzle are inserted in evaporation tube along axial direction, and oil circuit length accounts for the 1%~5% of evaporation tube overall length in evaporation tube, with incoming flow
Air forms contrainjection, using the high-temperature low-oxygen condition in high-temperature fuel gas recirculating zone, realizes the combustion of stability and high efficiency ultra-low contamination
Burning mode.
[Detailed description of the invention]
Fig. 1 is the sectional view of traditional combustion cell structure；
Fig. 2 is combustion chamber three-dimensional structure schematic diagram of the invention；
Fig. 3 is combustion chamber rearview of the invention；
Fig. 4 is the Section A-A perspective view of combustion chamber of the invention；
Fig. 5 is the Section A-A plan view of combustion chamber of the invention；
Fig. 6 is the side sectional view of interior air film hole or outer air film hole of the invention；
Fig. 7 is a kind of structural schematic diagram of interior air film hole or outer air film hole of the invention；
Fig. 8 is another structural schematic diagram of interior air film hole or outer air film hole of the invention；
Wherein: 1- burner inner liner；2- evaporation tube；The curved wall surface of 3-；4- fuel nozzle；5- outer wall；6- inner wall；7- rear end face；
The first rear wall of 8-；9- annular projection；The second rear wall of 10-；Air film hole in 11-；The outer air film hole of 12-；Air film hole before 13-；Gas after 14-
Fenestra；Gas outlet in 15-；Air inlet in 16-；The outer gas outlet 17-；18- external admission mouth；19- front side wall；20- rear wall.
[specific embodiment]
The invention will be described in further detail in the following with reference to the drawings and specific embodiments:
Referring to figs. 2 and 3, the invention discloses a kind of evaporation tubular type compact combustion chambers；The combustion chamber includes 5 He of outer wall
Inner wall 6, outer wall 5 and inner wall 6 are cylinder barrel assembling structure, and the cylinder barrel diameter that inner wall 6 is formed is less than the cylinder barrel that outer wall 5 is formed
Diameter, the cylinder barrel height that inner wall 6 is formed are less than the cylinder barrel height that outer wall 5 is formed, the front end of outer wall 5 and the front end of inner wall 6
It is connected by curved wall surface 3, curved wall surface 3 is protruded to outside, and the radian of curved wall surface 3 is 2 π/3~π, i.e., curved wall surface 3
Degree is 120 °~180 °, so that incoming air is more bonded wall surface, optimizes High Speed Flow Field, keeps velocity field more uniform, avoid
There is high velocity in part；Outer wall 5, curved wall surface 3 and inner wall 6 form an annular cylinder barrel-like structure with bottom surface, outside
The rear end of wall 5 is provided with the rear end face 7 of perpendicular outer wall 5, and rear end face 7 is all annular slice structure, the annular slice structure it is outer
Circular arc chamfering is provided between edge and the rear end of outer wall 5, the inward flange of annular slice structure is provided with the ring outwardly protruded
First rear wall 8 of shape sheet, the first rear wall 8 perpendicular to rear end face 7, the inward flange in the front-end and back-end face 7 of the first rear wall 8 is solid
Fixed connection；Rear end face 7 and the first rear wall 8 are not contacted with inner wall 6；Outer wall 5, curved wall surface 3, inner wall 6 and rear end face 7 form fire
Flame cylinder 1；The inward flange of rear end face 7 is provided with inwardly projecting annular projection 9, i.e., to the annular projection protruded inside burner inner liner 1
9；The rear end of inner wall 6 is provided with the second rear wall 10 of the annular slice outwardly protruded, and the annular diameter of the second rear wall 10 is greater than interior
The cylinder barrel diameter that wall 6 is formed, the front end of the second rear wall 10 is connected with the rear end of inner wall 6 by rounded corners.
Referring to Fig. 3 and Fig. 4, it is provided with air film hole on inner wall 6, outer wall 5, rear end face 7 and curved wall surface 3, wherein inner wall 6
On be provided with interior air film hole 11, interior 11 quantity of air film hole is 80~100, is provided with outer air film hole 12, outer air film hole on outer wall 5
12 number is 180~200；Air film hole 13 before being provided on curved wall surface 3, preceding air film hole 13 are formed along curved wall surface 3
Circumferential equal part be evenly arranged, number be 10~15；It is provided with rear air film hole 14 on rear end face 7, rear air film hole 14 is along rear end
The circumferential direction equal point arrangement in face 7.The burner inner liner of the device is determining according to design point fuel consumption along axial tolerance range of distribution,
The size and quantity of each round diameter are determined on this scope.In the present embodiment, air inlet amount is distributed as, before burner inner liner
End be 1%~4%, primary holes tolerance be 22%~27%, interlude tolerance be 24%~29%, blending section tolerance be 42%~
47%.
Interior air film hole 11 and outer air film hole 12 are special-shaped hole, the inner wall for the barreled that interior air film hole 11 is formed in inner wall 6
Upper is interior air inlet 16, and interior air inlet 16 is ellipse or round, interior air film hole 11 (i.e. 6 shape of inner wall on the wall surface of burner inner liner 1
At barreled outer wall on) be interior gas outlet 15；Outer air film hole 12 is external admission mouth 18 on the barreled outer wall that outer wall 5 is formed,
External admission mouth 18 is ellipse and round, (on the inner wall of barreled that i.e. outer wall 5 is formed) is outer outlet on the wall surface of burner inner liner 1
Mouth 17；Referring to figs. 7 and 8, the side wall of interior air film hole 11 and outer air film hole 12 includes front side wall 19 and rear wall 20, rear wall
20 tilt to the inner wall of burner inner liner 1, and front side wall 19 and rear wall 20 are end to end, and the outer edge of rear wall 20 can be arc
Or straight line；Because of the inclination of rear wall 20, so that interior air film hole 11 and outer air film hole 12 are irregularly-shaped hole, and the face of interior gas outlet 15
Product is greater than the area of interior air inlet 16, and the area of outer gas outlet 17 is greater than the area of external admission mouth 18；When air is outside combustion chamber
Portion is to when burner inner liner internal flow, if rear wall 20, perpendicular to wall surface, Cryogenic air once enters burner inner liner, just by burner inner liner
Interior high-temperature gas, which conducts heat, to heat up, it is difficult to form low temperature air film, if rear wall 20 is inclined-plane, change the entrance of Cryogenic air
It is laminar flow under ideal or microstate so that forming a temperature layer along the inner wall of burner inner liner to the trend of burner inner liner moment
Temperature layer, when quantity of such interior air film hole 11 on inner wall 6 and spacing are according to the size of burner inner liner, air inlet amount is set
When counting reasonable, it will form multiple small ideal laminar flow temperature layers, improve the cooling effect of Cryogenic air；Air is from burning
Room burner inner liner inside and outside wall and front end wall surface enter combustion chamber, are formed inside burner inner liner using tangential admission and stablize burning.Front end
Air inlet can be directly exposed to primary zone high-temperature region to avoid evaporation tube, reduce the probability of ablation to a certain extent.Herein preceding arrives
Identical for the front and rear direction of entire combustion chamber afterwards, curved wall surface 3 is in the front end of combustion chamber, rear end of the rear end face in combustion chamber；I.e.
Along the vertical direction in combustion chamber, the sectional area for entering the gas of burner inner liner 1 from air inlet 18 is the process of an increase,
So that the expansion of air film hole flow direction and outlet exhibition reduce cold air in air film hole exit momentum to structure, improves cold air and attached in wall surface
Property；The area of interior air inlet 16 and external admission mouth 18 is 2mm2~23mm2, the area of interior gas outlet 15 and outer gas outlet 17 is
3mm2~35mm2, the spacing ratio between the axis of adjacent interior air film hole 11 is 2~5, the axis of adjacent outer air film hole 12 it
Between spacing ratio be 2~5, the spacing ratio between the axis of interior air film hole 11 or the spacing between the axis of outer air film hole 12 are than tool
Body is defined as the distance between axis of adjacent air film hole ratio, measures the adjacent air film hole of every two respectively (for interior air film hole 11
Or outer air film hole 12) axis between distance, the ratio of distance and distance is 2~5；Interior air film hole 11 with a thickness of 0.3mm~
0.6mm, outer air film hole 12 with a thickness of 0.3mm~0.6mm, the thickness of interior air film hole 11 herein it is practical be inner wall 6 thickness
Degree, the thickness of the practical as outer wall 5 of the thickness of outer air film hole 12；Referring to Fig. 6, the central point and interior outlet of interior air inlet 16 are defined
Straight line where mouthfuls 15 central point line is the axis of interior air film hole 11, the central point of external admission mouth 18 and outer gas outlet 17
Straight line where central point line is the axis of outer air film hole 12, the axis of interior air film hole 11 and the wall surface angular range of inner wall 6
It is 28 °~40 °, the wall surface angular range of outer air film hole 12 and outer wall 5 is all 28 °~40 °；Air passes through burning indoor external wall surface
Flaring hole, it is opposite to spray, promote air-fuel mixture more uniform, high degree avoids the appearance of local high temperature zone, promotes burning more
Add stabilization, efficiency significantly improves.
Above-mentioned interior air film hole 11 is provided with 80~100 on inner wall 6, along the circumferential direction for the tubbiness that inner wall 16 is formed, layer
The size of layer arrangement, each layer of interior air film hole 11 is arranged according to airflow requirement；Similarly, the outer air film hole 12 on outer wall 5 is layer by layer
Arrangement, the size of each layer of outer air film hole 12 are arranged according to airflow requirement；It is emphasized that the interior air film hole 11 of same layer
Size, tilt angle of the rear wall 20 on inner wall 6 is identical, but the size of the interior air film hole 11 of different layers, and
Inclined angle may be identical on inner wall 6 for rear wall 20, it is also possible to different；The arrangement and thinking of outer air film hole 12 are the same as interior
The arrangement and thinking of air film hole 11, because construction different angle and various sizes of air film hole can make whirlpool in hole abundant
Development, optimization outlet jet flow field；Air is by burning indoor external wall surface flaring hole, and opposite to spray, promotion air-fuel mixture is more
Uniformly, high degree avoids the appearance of local high temperature zone, promotes burning more stable, efficiency significantly improves.
Preceding air film hole 13 and rear air film hole 14 can be round hole or oval hole, be the uniform hole of shape；, curved
Wall surface, that is, front end face air inlet can be directly exposed to primary zone high-temperature region to avoid evaporation tube, reduce the several of ablation to a certain extent
Rate；It is more uniform that rear end face air inlet can promote fuel oil and air to mix.
Referring to Fig. 5, along the circumferential direction of rear end face 7, several evaporation tubes 2 are internally provided with to burner inner liner 1, evaporation tube 2 will
The circumferential equal part of rear end face 7, preferably 12 evaporation tubes in the present embodiment；2 each sections of internal-and external diameters of evaporation tube are identical, exit portion band
There is closing in, the angle between the axis of evaporation tube 2 and the axis of entire combustion chamber is 15 °~35 °；From the outside of evaporation tube 2, edge
The axis of evaporation tube 2, to evaporation tube 2 inside inserted with fuel nozzle 4, length of the fuel nozzle 4 inside evaporation tube 2 accounts for evaporation
The 1%~5% of 2 overall length of pipe, fuel oil is out of fuel nozzle 4 spirt evaporation tube 2, opposite incoming air contrainjection, fuel oil and steaming
The air mixing in pipe 2 is sent out, which inversely sprays into combustion chamber flame drum 1, then and from 1 inner wall of combustion chamber flame drum
6, outer wall 5, the air mixing come is injected on front bulkhead 3 in flaring hole 1, using tangential admission in combustion chamber flame drum 1 shape
At stablizing flame.Contrainjection changes the burning of traditional aeroengine combustor buring chamber-head portion injection fuel oil and swirl stabilized combustion
Organizational form, it realizes the combustion mode of stability and high efficiency ultra-low contamination using the high-temperature low-oxygen condition in high-temperature fuel gas recirculating zone.
The manufacturing process of the device use increasing material manufacturing, increasing material manufacturing technique based on digitizing CAD model, using point
Layer manufacture thought, extracts forming path, and by powder stratified sedimentation to matrix, dimensional accuracy is high, wherein burner inner liner inside and outside wall, steaming
Hair pipe is shaped to lightweight single part using increasing material manufacturing process integration, simplifies connection sealing structure；Using quick solidification
Technology, process carry out in inert gas shielding, can get the metallographic structure of even tissue densification, meet or exceed forging
It is horizontal, it is even more important that the working environment of such device is usually poor, and if vibration amplitude is big, temperature difference of temperature field is big, passes through increasing
Material manufacture is integrally formed, and reduces the usage amount of connector (such as bolt), will greatly improve the globality of structure, is extended and is used
Service life, the metallographic structure of even compact reinforce entire material Anti-temperature difference ability.The manufacturing process simplifies connection and sealing knot
Structure reduces risk caused by vibration, Rig up error, effectively increases the service life, reduces design and processing cost.Simultaneously mitigate weight,
Reduce contour dimension, accelerate iteration, shorten the design cycle, dimensional accuracy is high, promotes combustion chamber overall performance, and mitigating weight can have
Effect reduces material cost and fuel consumption, promotes the market competitiveness.Gradually expanded form air film hole exits open up to flow to expansion structure can
To reduce cold air in air film hole exit momentum, weakens cold air and gas mixing degree, improve cold air in wall face adhesion, play more
Good heat-insulated cooling effect.Cold air passes through and forms vortex structure, the vortices breakdown in adjacent two hole intersection behind the flaring hole continuously arranged
Less, but there is good duration, so that Gas Cooling is close to wall surface and increase film overcast area, leads to the phase between cooling air-flow
The Forward of interaction position, while the characteristic of partial groove slot apertures is shown, improve cooling rates distribution and cold air at hole exits
The vortex structure formed with gas mixing, outlet jet is more evenly.Meanwhile gradually expanded form air film hole cross-sectional area is larger, can incite somebody to action
Whirlpool in hole sufficiently develops, enhanced heat exchange, improves cooling effect.
The correlation data calculation of the combustion chamber enters shown in the following table 1:
A kind of evaporation tubular type compact combustion chamber of table 1 calculates data
Exit temperature distribution coefficient OTDF is the important parameter for evaluating combustor exit thermal field quality, and OTDF is smaller, thermal field
Quality is higher, smaller to the adverse effect of combustion chamber first order turborotor and working-blade life and reliability.From upper
Table 1 can be seen that the OTDF value of conventional firing chamber designs generally below 0.2.Compare traditional cylindrical air film hole, flaring air film
Hole evaporation tubular type compact combustion chamber OTDF reaches 0.11, is much smaller than 0.2, combustor exit thermal field quality is good, is conducive to mention
High moving turbine blade thermal technology transfer efficiency；Because combustion chamber fuel nozzle, using contrainjection to evaporation inside pipe wall, cooperation is empty
Gas increases fuel oil and air mixes turbulivity, improve fuel oil evaporation rate in evaporation tube in evaporation tube internal flow；At the same time
Combustion chamber offers flaring hole on burner inner liner inside and outside wall and front bulkhead, using the gradually expanded form air film hole of different angle and size,
Tangential admission improves flow field, is formed in burner inner liner and stablizes flame, in traditional combustion room model compared to raising efficiency of combustion
0.2%.
The foregoing is merely illustrative of the preferred embodiments of the present invention, is not intended to limit the invention, all in essence of the invention
Within mind and principle, any modification, equivalent replacement, improvement and so on be should all be included in the protection scope of the present invention.
Claims (10)
1. a kind of evaporation tubular type compact combustion chamber, which is characterized in that including inner wall (6) and outer wall (5), inner wall (6) and outer wall
(5) be cylindrical body, the cylinder of holster that inner wall (6) is formed in the cylindrical body that outer wall (5) are formed, the front end of inner wall (6) and
The front end of outer wall (5) is connected by curved wall surface (3), external protrusion of the curved wall surface (3) to combustion chamber, outer wall (5), inner wall
(6) and the space of curved wall surface (3) formation is burner inner liner (1)；The rear end of outer wall (5) is provided perpendicular to the rear end of outer wall (5)
Face (7), rear end face (7) are annular slab, and the outer edge of rear end face (7) is connected with the rear end of outer wall (5), the inner edge of rear end face (7)
The diameter of a circle that edge is formed is greater than the diameter for the cylindrical body that inner wall (6) are formed；It is set from rear end face (7) to the inside of burner inner liner (1)
Several evaporation tubes (2) are equipped with, circumferentially along rear end face (7), each evaporation tube (2) is interior inserted with one for evaporation tube (2)
A fuel nozzle (4)；Inner wall (6), outer wall (5), curved wall surface (3) and evaporation tube (2) are integrally formed；
Several interior air film holes (11) are offered on inner wall (6), several outer air film holes (12) are offered on outer wall (5)；Interior gas
Fenestra (11) is interior gas outlet (15) in the hole of burner inner liner (1) one end, and the other end is interior air inlet (16)；Outer air film hole (12) exists
The hole of burner inner liner (1) one end is outer gas outlet (17), and the other end is external admission mouth (18)；The area of interior gas outlet (15) is greater than interior
The area of air inlet (16), the area of outer gas outlet (17) are greater than the area of external admission mouth (18).
2. a kind of evaporation tubular type compact combustion chamber according to claim 1, which is characterized in that interior air inlet (16) and outer
Air inlet (18) is round or oval；The side wall of interior air film hole (11) and outer air film hole (12) be divided into front side wall (19) and
The rear wall (20) of rear wall (20), interior air film hole (11) is tilted relative to inner wall (6), the rear wall (20) of outer air film hole (12)
It is tilted relative to outer wall (5), front side wall (19) and rear wall (20) are end to end.
3. a kind of evaporation tubular type compact combustion chamber according to claim 2, which is characterized in that the axis of interior air film hole (11)
The angular range of line and inner wall (6) is 28 °~40 °；The angular range of the axis of outer air film hole (12) and outer wall (5) is 28 °~
40°。
4. a kind of evaporation tubular type compact combustion chamber according to claim 1, which is characterized in that interior air inlet (16) and outer
The area of air inlet (18) is 2mm2~23mm2, the area of interior gas outlet (15) and outer gas outlet (17) is 3mm2~
35mm2。
5. a kind of evaporation tubular type compact combustion chamber according to claim 4, which is characterized in that the thickness of interior air film hole (11)
Degree be 0.3mm~0.6mm, outer air film hole (12) with a thickness of 0.3mm~0.6mm.
6. a kind of evaporation tubular type compact combustion chamber according to claim 4, which is characterized in that adjacent interior air film hole 11
Axis between spacing ratio be 2~5, the spacing ratio between the axis of adjacent outer air film hole 12 is 2~5.
7. a kind of evaporation tubular type compact combustion chamber according to claim 1, which is characterized in that curved wall surface (3) is along it
It is circumferentially evenly arranged with preceding air film hole (13), rear end face (7) is evenly arranged with rear air film hole (14) along its circumferential direction.
8. a kind of evaporation tubular type compact combustion chamber according to claim 7, which is characterized in that the number of interior air film hole (11)
Amount is 80~100；The quantity of outer air film hole (12) is 180~200；The quantity of preceding air film hole (13) is 10~15.
9. a kind of evaporation tubular type compact combustion chamber according to claim 1, which is characterized in that the axis of fuel nozzle (4)
The axis of line and evaporation tube (2) is overlapped, and the angle between the axis and burning chamber axis of fuel nozzle (4) is 15 °~35 °.
10. a kind of evaporation tubular type compact combustion chamber according to claim 9, which is characterized in that fuel nozzle (4) is steaming
The internal length of hair pipe (2) accounts for the 1%~5% of evaporation tube (2) overall length.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910033416.6A CN109668173B (en) | 2019-01-14 | 2019-01-14 | A kind of evaporation tubular type compact combustion chamber |
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| CN111023155A (en) * | 2019-12-31 | 2020-04-17 | 西安增材制造国家研究院有限公司 | Secondary flow evaporation tube type combustion chamber structure |
| CN111853854A (en) * | 2020-06-19 | 2020-10-30 | 中国航发湖南动力机械研究所 | Evaporation pipe integrated structure, evaporation pipe type combustion chamber and micro turbojet engine |
| CN112082176A (en) * | 2020-09-14 | 2020-12-15 | 清华大学 | Combustion chamber structure of micro turbojet engine |
| CN112283747A (en) * | 2020-10-29 | 2021-01-29 | 中国航发湖南动力机械研究所 | Combustion chamber and aeroengine |
| CN112945566A (en) * | 2021-03-15 | 2021-06-11 | 南京赛恩通航科技有限公司 | Simulation structure, test platform and test method of gas-distributing type annular combustion chamber |
| CN114234236A (en) * | 2021-12-08 | 2022-03-25 | 中国人民解放军总参谋部第六十研究所 | Combustion chamber with scale-type air film hole structure |
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