CN103867340B - A kind of double-cyclone ejector filler - Google Patents
A kind of double-cyclone ejector filler Download PDFInfo
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- CN103867340B CN103867340B CN201210570009.7A CN201210570009A CN103867340B CN 103867340 B CN103867340 B CN 103867340B CN 201210570009 A CN201210570009 A CN 201210570009A CN 103867340 B CN103867340 B CN 103867340B
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Abstract
The invention provides a kind of double-cyclone ejector filler, including top cover, nozzle, upper bottom, midsole, gas turbulator and ejector filler cavity.Ejector filler cavity is the hollow cylinder of one " tubbiness "；Ejector filler top cover and upper bottom form and form gaseous oxidant chamber on fuel cavity, ejector filler between bottom and midsole, ejector filler midsole and ejector filler base formation water cavity；Inner nozzle is threadedly secured on bottom through the mounting hole on upper bottom, midsole and ejector filler cavity；Air cyclone is installed on nozzle by screw thread；(operating) water nozzle is the water hole of circumference uniform distribution on ejector filler base；Ejector filler provided by the present invention is simple in construction, cost is low, with atomization is good, flame stabilization the characteristics of.
Description
Technical field
The present invention relates to liquid-propellant rocket engine and the ejector filler of gas generator, and in particular to liquid-propellant rocket engine and
Gas generator propellant spray is atomized.
Background technology
Ejector filler is that propellant is sprayed into combustion chamber with state in the proper ratio, to produce efficient, stable burning
Device.It is the important component of liquid-propellant rocket engine and gas generator, is the core in above-mentioned engine design.
The widely used spray unit of current liquid-propellant rocket engine is impacting type and coaxial-type.《Liquid-propellant rocket engine
Modern engineering design》The various spray unit forms on liquid-propellant rocket engine are carried out in (Chinese Yuhang Publishing House, 2003)
Introduce.Wherein impacting type spray unit guides another stock of one impinging jet or several strands of jets so that jet crushing is atomized to be formed
Spray field with certain limit and Size Distribution.Further, jet can be that same fuel can also be different fuel, can
To be all gas phase or liquid phase, or different phases.The ejector filler that impacting type spray unit is constituted is designated as A class ejector fillers.A classes
Ejector filler is difficult to intersect on theoretical rum point due to jet-core region line so that the shape of spray fan changes, and is atomized and mixes
Close uneven, so as to easily induce combustion instability.
SSME and other hydrogen oxygen engine ejector fillers then generally use coaxial-type spray unit.Coaxially
Formula spray unit generally has the concentric slices of liquid propellant center stream that one slowly flows and the gaseous propellant around it
Stream.Center stream can be oxidant or fuel, and corresponding concentric slices stream is another propellant, the center of hydrogen oxygen engine
Stream is usually liquid oxygen, and concentric slices stream is Gaseous Hydrogen.B class ejector fillers will be designated as using the ejector filler of coaxial-type spray unit.B
Make it that the atomization and mixing of propellant are preferable due to there is the shear action of high speed between fuel and oxidant in class ejector filler, but
It is less suitable when propellant is liquid or gaseous propellant is very sticky.The now atomization and mixing of propellant
Performance is seriously deteriorated, so as to reduce the ignition performance and efficiency of combustion of engine.
Document " ignition of gas generator and combustibility research [D] Changsha：The National University of Defense Technology, 2008. " intermediaries
Continued a kind of gas generator ejector filler of use coaxial eccentricity formula spray unit, is designated as C class ejector fillers.With B class ejector fillers
Spray unit is compared, and liquid center's stream of C class ejector filler spray units is with circumferentially tangential speed, thus gas-liquid effect is more
By force, the atomization of ejector filler is more preferable.But for this kind of not volatile fuel of kerosene, when oxidant oxygen content is relatively low,
Its atomization is not met by the requirement of gas generator reliable ignition and efficient burning.
As a whole, have been used to or be possibly used at present liquid-propellant rocket engine or gas generator propellant spray mist
The ejector filler of change, for the atomization also Shortcomings of not light volatile fuel, and without the ability for stablizing flame.
The content of the invention
Present invention aims at a kind of double-cyclone ejector filler is provided, adopted with solving liquid-propellant rocket engine or gas generator
During with not light volatile fuel (such as kerosene) and the relatively low oxidant of oxygen content (such as air), ejector filler atomization deficiency and
The problem of such ignition of gas generator and difficult flame stabilization.The spray atomization of not light volatile fuel is improved, and is worked as
During using the relatively low oxidant of oxygen content, produce the recirculating zone of a low speed to stablize flame.
A kind of double-cyclone ejector filler of the present invention, including top cover, rotarytype injector, upper bottom, midsole, gas turbulator, spray
Device cavity and sleeve；
The upper bottom, midsole are connected as one with ejector filler cavity respectively, and ejector filler top cover is connected with upper bottom, top cover with it is upper
Fuel cavity is constituted between bottom, there is a liquid propellant entrance upper end of top cover；Gaseous oxidant chamber is constituted between upper bottom and midsole；
It is water cavity between ejector filler cavity and midsole；
The sleeve passes through midsole and ejector filler cavity, and its two ends is respectively welded at the bottom surface of midsole and ejector filler cavity
Sealing is fixed, rotarytype injector is threadedly secured on bottom, and rotarytype injector sequentially passes through bottom and sleeve；
The gas turbulator is cooperated solid by the internal thread of its inwall with the external screw thread on rotarytype injector housing
It is fixed, the flow channel of oxidant gas is formd between gas turbulator and sleeve；
One group of straight-through water spray orifice being uniformly distributed along the circumference on the ejector filler cavity, water enters water cavity through water inlet and distributes entrance
Water spray orifice simultaneously sprays ejector filler；
The rotarytype injector is swirler rotarytype injector；
The gas turbulator includes swirl vane and the installation screw thread between rotarytype injector.
Further, the rotarytype injector is made up of swirler and nozzle body；Nozzle body is included between upper bottom
Fixed screw thread, the installation screw thread of gas turbulator and the tangential seal groove with gas turbulator.
Further, the rotarytype injector is single or multiple；When fuel total mass flow rate is more than 400g/s using many
Nozzle configuration, otherwise using single injector；
If multiinjector configuration, fuel total mass flow rate (kg/s) should meet following formula：
In formula, N represents nozzle quantity, and nozzle quantity is adjacent from inside to outside 1,3,6,18,36,60,90,126 or 168
Enclose 6 nozzles incremented by successively.
Further, the rotarytype injector (2) is tangential hole rotarytype injector or swirler rotarytype injector.
Further, the number of blade n of the gas turbulator will be met
D in formula --- cyclone external diameter, L --- cyclone length, θ --- blade angle；
Gas turbulator blade established angle θ should meet following formula：
D in formula --- cyclone internal diameter, S to characterize the dimensionless number that flow rotation is strong and weak, blade angle θ is 50 °~
70°。
Further, the diameter d of the water spray orifice (61)lDetermined by below equation：
In formulaFor water-carrying capacity, Cd --- straight hole discharge coefficient, take 0.7~0.85, ρlFor water density (kg/m3),
Δpl--- pressure drop when water injects, take chamber pressure 30%~50%, nl--- the number of water spray orifice, water spray orifice (61)
Diameter d1＜ 1mm.
Following technique effect can be obtained using the present invention：
1. the present invention makes gaseous oxidant rotate spray using gas turbulator, the interaction of gas and fuel is stronger,
So that the spray atomization of ejector filler is more preferably, so as to enhance the liquid-propellant rocket engine using this ejector filler, combustion gas hair
The igniting of raw device and combustibility；
2. gaseous oxidant rotation spray can form the recirculating zone of a low pressure in the present invention, recirculating zone can stablize fire
Flame, so that more preferable using the liquid-propellant rocket engine and gas generator flame holding of this ejector filler；
3. water spray orifice of the present invention is distributed in around ejector filler base, gaseous film control chamber wall can be formed in combustion chamber
Face, therefore use the liquid-propellant rocket engine of this ejector filler and gas generator combustion chamber to design the cooling knot of complexity
Structure.
4. ejector filler water cavity of the present invention plays cooling effect so that the ability of ejector filler anti-yaw damper is stronger, simultaneously because spray
Note device does not design cooling structure specially, and overall structure is simple, and manufacturing cost is low.
Brief description of the drawings
Fig. 1：Prior art A class ejector filler structural representations；
Fig. 2：Prior art B class ejector filler structural representations；
Fig. 3：Prior art C class ejector filler spray cell schematics；
Fig. 4：Swirler rotarytype injector design parameter schematic diagram in the present invention；
Fig. 5：Swirler forward spin flow slot number amount schematic diagram in the present invention；
Fig. 6：Swirler helix, lift angle, pitch schematic diagram in the present invention；
Fig. 7：Swirler rotarytype injector spray cone angle is illustrated in the present invention；
Fig. 8 a：Swirler structure in the present invention
Fig. 8 b：Eddy flow slot cross-section schematic diagram in the present invention；
Fig. 9：Tangential hole rotarytype injector structural parameters schematic diagram in the present invention
(left figure：Front view；Right figure：Longitudinal cross section)；
Figure 10：Tangential hole rotarytype injector front view and the sectional view of tangential hole is cut through in the present invention；
Figure 11：Tangential hole rotarytype injector three-dimensional longitudinal sectional view in the present invention；
Figure 12：The single injector general structure schematic diagram of ejector filler preferred embodiment of the present invention；
Figure 13：The multiinjector general structure schematic diagram of ejector filler preferred embodiment of the present invention；
Figure 14：Swirler rotarytype injector schematic diagram of the present invention；
Figure 15：The upward view of single injector ejector filler preferred embodiment of the present invention；
Figure 16：The upward view of multiinjector ejector filler preferred embodiment of the present invention；
Figure 17：The gas turbulator structural representation of ejector filler preferred embodiment of the present invention；
Figure 18：Gas turbulator design parameter schematic diagram of the present invention；
Marginal data：
Top cover 1, nozzle 2, upper bottom 3, midsole 4, gas turbulator 5, ejector filler cavity 6, sleeve 7, gaseous oxidant entrance
8th, water inlet 9, liquid propellant entrance 10, swirler 21, nozzle body 22, external screw thread 221, tangential seal groove 222, fixed spiral shell
Line 223, swirl vane 51, internal thread 52, water spray orifice 61, flange mounting hole 62.
Embodiment
Embodiments of the invention are described in detail below in conjunction with accompanying drawing, but the present invention can be defined by the claims
Implement with the multitude of different ways of covering.
First, single injector double-cyclone ejector filler
The preferred embodiments of the present invention one are single injector double-cyclone ejector filler, referring specifically to Figure 12.When liquid fuel flow
When smaller, i.e. liquid fuel flow ＜ 400g/s use single injector configuration；Single injector configuration is Properties of Coaxial Swirling Injectors, beneficial to kerosene etc.
The not spray atomization of light volatile fuel, while coaxially arranged one low speed recirculating zone of gas turbulator formation, beneficial to combustion
Burn the flame stabilization of room.
The ejector filler include top cover 1, rotarytype injector 2, upper bottom 3, midsole 4, gas turbulator 5, ejector filler cavity 6 and
Sleeve 7, there is stainless steel material processing.
Upper bottom 3, midsole 4 are connected as one with ejector filler cavity 6 by welding manner respectively, ejector filler top cover 1 and upper bottom 3
Connected by flange, fuel cavity is constituted between top cover 1 and upper bottom 3, there is a liquid propellant entrance 10 upper end of top cover 1；Upper bottom 3
Gaseous oxidant chamber is constituted between midsole 4；It is water cavity between ejector filler cavity 6 and midsole 4.
Sleeve 7 passes through midsole 4 and ejector filler cavity 6, and its two ends is respectively welded at the bottom of midsole 4 and ejector filler cavity 6
Sealing is fixed in face, and rotarytype injector 2 is threadedly secured on bottom 3, and rotarytype injector 2 sequentially passes through bottom 3 and set
Cylinder 7.External screw thread 221 is designed with rotarytype injector housing, as shown in figure 14, the inwall of gas turbulator 5 is designed with internal thread 52,
As shown in figure 17, by the cooperation of the external screw thread on the housing of rotarytype injector 2 and the internal thread of gas turbulator inwall, realization pair
The fixation of gas turbulator, forms the flow channel of oxidant gas between gas turbulator and sleeve.Gas cyclone is installed
To ensure that air-flow is consistent with hand of spiral to the torque direction of gas turbulator 5 during device, i.e., aerodynamic force twists gas turbulator 5
Tightly.In addition, can also tangentially be sealed by O-ring between gas turbulator 5 and rotarytype injector 2.
After gaseous oxidant enters oxidant cavity through gaseous oxidant entrance 8, by between gas turbulator and sleeve
Flow channel, the rotation spray of gaseous oxidant is carried out through gas turbulator 5.
Figure 15 is the upward view of embodiment one.Water spray orifice 61 is one group of clear opening being uniformly distributed along the circumference on ejector filler cavity 6,
Water enters water cavity distribution into water spray orifice 61 through water inlet 9 and sprays ejector filler.Flange mounting hole is also included on ejector filler cavity 6
62。
Figure 14 is the structure chart of the rotarytype injector 2 of the present embodiment.Rotarytype injector 2 is swirler rotarytype injector, by
Swirler 21 and nozzle body 22 are constituted.Nozzle body 22 includes the fixation screw thread 223 between the upper bottom 3, gas turbulator 5
External screw thread 221 and the tangential seal groove 222 with gas turbulator 5.
Figure 17 is the structural representation of the gas turbulator 5 of the present embodiment.Gas turbulator 5 comprising swirl vane 51 and with
Internal thread 52 between rotarytype injector 2.
2nd, multiinjector double-cyclone ejector filler
Multiinjector configuration is used as embodiment is general when fuel total mass flow rate is more than 400g/s, is of the invention
Embodiment two.It for details, reference can be made to Figure 13, Figure 16.The nozzle of individual pen 3 or 6 nozzles can be chosen according to the size of design discharge；Two circles
18 nozzles, wherein inner ring 6, outer ring 12；Three 36 nozzles of circle, wherein inner ring 6, centre circle 12, outer ring 18, successively class
Push away.That is adjacent turn 6 nozzles incremented by successively from inside to outside.Such as Figure 13 and Figure 16 show the nozzle configuration ejector filler of individual pen 6, is distributed
Circular diameter D should cause the beeline between each nozzle installed to be more than 2mm, to ensure enough structural strengths, from Figure 13
Partial view B from the point of view of, each nozzle arrangements form of multiinjector structure is identical with single injector.
Fuel enters each nozzle through fuel inlet incoming fuel chamber, distribution.In order to obtain preferably injection, sprayability
Can, while requiring that ejector filler is simple in construction, fuel total mass flow rate (kg/s) should meet following formula：
In formula, N represents nozzle quantity.Under the conditions of above formula is met, nozzle quantity 1,3,6,18,36,60,90,126 and
Select to determine in 168 sequences.
3rd, the design of fuel nozzle
Fuel nozzle is rotarytype injector, can also use whirlpool using tangential hole rotarytype injector according to actual needs
Device rotarytype injector is flowed, it can also be clockwise counterclockwise that fuel direction of rotation, which can be,.Rotarytype injector is according to monograph
《Liquid-propellant rocket engine is designed》In design criteria and formula be designed, it is specific as follows：
1) swirler rotarytype injector
For swirler rotarytype injector, its design parameter mainly includes nozzle outlet diameter dh, eddy flow slot number amount n, eddy flow
Groove size, spin chamber diameter D, the lift angle β of eddy flow groove and swirler length L, referring to Fig. 4, Fig. 5 and Fig. 6.
Wherein eddy flow slot number amount n refers to the quantity of flow channel on swirler, and n typically chooses n=2~6, such as Fig. 5 institutes
Show, Fig. 5 respectively illustrates swirler graphics during eddy flow slot number amount n=1,2,3, the most obvious feature reflection of eddy flow slot number amount
In channel entrance quantity, swirler is overlooked, there are several eddy flow grooves, just there are several channel entrances；The lift angle β of eddy flow groove is referred to
Threaded line and horizontal angle, as shown in fig. 6, in geometrical relationship, lift angle β be exactly with pitch t and central diameter girth (2 π R, its
Middle R is central diameter) be right-angle side triangle in hypotenuse and central diameter girth angle, wherein pitch t be adjacent two grooves corresponding points between
Distance, R is helical duct radius, in Machine Design be generally referred to as central diameter.
The shown liquid film schematic diagrames to be formed of being sprayed from jet expansion of Fig. 7.Spray cone angle is 2 α, and the α of spray cone angle 2 is taken during design
=90 °, it generally also can use 90 °, 100 °, 110 °, 120 ° of equivalences.
Delivery nozzle geometrical property A and flow coefficient C d can be calculated according to Abramowicz theoretical formula (5)~(7),
φ is the effective cross-section coefficient of jet expansion in formula；Again by flow formula (8).Flow according to design objective requirementAnd pressure drop
Δ p can draw nozzle outlet diameter d with inverseh.Define c=2R/dh, c values are chosen, c=1.5~4 are typically taken, so as to
To the radius R of helical duct；Swirler forward spin flow slot number amount n is chosen, works as flowIn below 100g/s, n takes 2~3, works as stream
Amount100 between 200g/s when, n takes 3~4, works as flowIn more than 200g/s, n takes 4~6；Swirler forward spin flow groove
Lift angle β be usually taken to be 15~20 °, the cross section of passage is taken as trapezoidal.According to formula (9) determine in swirler passages perpendicular to
In the cross-sectional area A s of flow direction, formula, rhFor jet expansion radius, then
According to trapezoidal each bar side and high basic geometric relationship, referring to Fig. 8 (b), can obtain following relational expression (10)~
(11)：
b2=b1+2h tanθ (10)
In formula：b1--- the trapezoidal upper bottom of eddy flow groove；b2--- the trapezoidal bottom of eddy flow groove；H --- the trapezoidal height of eddy flow groove；
The angle of θ --- the trapezoidal waist of eddy flow groove and upper bottom normal.Generally selected b2With θ values, b is calculated1With h values.The pitch of eddy flow groove
T is determined that spin chamber diameter D is obtained by formula (13) by formula (12), and swirler length generally takes L=(0.5~1) D.
T=2 π R tan β (12)
D=2 (R+h/2) (13)
2) tangential hole rotarytype injector
For tangential hole nozzle, its design parameter mainly includes waiting straight section diameter dh, spin chamber diameter Ds, spin chamber's length
Ls, tangential pore radius rt(diameter dt), tangential hole number n, referring to Fig. 9, Figure 10, Figure 11.
Flow coefficient C d (typically choosing Cd=0.14~0.22) is selected when designing tangential hole nozzle first, by nozzle flow
Formula (8) can be obtained
In formulaFor nozzle design discharge, dhStraight section diameter is waited for tangential hole nozzle, Cd is discharge coefficient, p are nozzle
Pressure drop, ρ is fluid density.Pressure drop Δ p, the flow that design objective is requiredSubstitution formula, it may be determined that wait straight section diameter dh.It is right
It is equally applicable in tangential hole rotarytype injector Abramowicz theoretical formula, meaning and swirler nozzle phase that A is represented
Together.Cd value is substituted into formula (7) can obtain φ values, and φ values are substituted into formula (5) respectively, A values can be obtained；Define c=2R/dh, select c
Value, typically takes c=1.5~4, can obtain import jet rotary radius R size, as shown in figure 11, and import jet rotary radius R determines
Justice is distance of the tangential hole inlet axis to nozzle-axis, then selectes tangential hole count n (often taking 2~3), and the nozzle shown in Figure 10 is cut
It is n=3 to hole count.
By the A being the previously calculated, R,Determination tangential hole half can be calculated by substituting into formula (15) with selected n
Footpath rt And then spin chamber diameter D can be obtaineds=2 (R+rt), spin chamber's length often takes Ls=Ds.Spin chamber is straight with waiting
Section is typically using 90 ° of circular conical surface transition.
4th, the design of gas turbulator
Oxidized dose of entrance 8 of gaseous oxidant is pooled to up to gaseous oxidant chamber into ejector filler, in oxidant cavity and rotation
Under the pressure difference for flowing device outlet, gaseous oxidant passes through the guide vane of cyclone, forms swirling eddy, and final rotation sprays spray
Device, the air-flow of rotation can form the recirculating zone of a low pressure, to the liquid-propellant rocket engine using the type ejector filler or combustion gas
For generator, the recirculating zone of low pressure contributes to the flame stabilization of combustion chamber.Gas turbulator is sprayed by being threadably mounted at fuel
On mouth, its number is identical with fuel nozzle, and the direction of rotation of gas can in the same direction can also be reverse with fuel.Referring to Figure 17 and figure
18, the number of blade n of gas turbulator, which chooses, should meet the principle observed along cyclone axis and be unable to printing opacity, referred to as can not translucency
Principle, the number of blade will be met during specific designD in formula --- cyclone external diameter, L --- cyclone length,
θ --- blade angle；Gas turbulator blade established angle θ selection needs to consider internal diameter blade d and outer diameter D (leaf
The difference of piece internal-and external diameter is the high h=D-d of blade), it should meet following formula in design：
D in formula --- cyclone internal diameter, S is characterizes the dimensionless number that flow rotation is strong and weak, referred to as swirling number, by calculating
Checking learns that swirling number is mainly determined that influence of the diameter than d/D to swirling number is smaller by blade angle, therefore in actual design
Shi Shouxian chooses a blade angle θ (often taking 50 °~70 °), then selected number of blade n and vane thickness δ.According to design discharge
Circulation area A is can determine that with the parameters such as pressure drop are designeds, design selectes outer blade diameter D according to installation requirement often (can also select leaf
Piece internal diameter d), then can obtain internal diameter blade d by formula (17), then calculate swirling number S by formula (16), and whether the result meets 0.6
＜ S ＜ 3 requirement, needs modification blade angle θ to recalculate if being unsatisfactory for.
5th, water parameters of injector holes is designed
The diameter d of water spray orifice 61lPublished by Yuhang Publishing House, Zhu Ningchang chief editor monograph《Liquid-propellant rocket engine is designed》
In the below equation that provides determine：
In formulaFor water-carrying capacity, Cd --- straight hole discharge coefficient (0.7~0.85), ρlFor water density (kg/m3), Δ
pl--- pressure drop when water injects, take chamber pressure 30%~50%, n1--- the number of water spray orifice, in order to ensure atomization effect
Really, d is usually required that1＜ 1mm.
The preferred embodiments of the present invention are the foregoing is only, are not intended to limit the invention, for the skill of this area
For art personnel, the present invention can have various modifications and variations.Within the spirit and principles of the invention, that is made any repaiies
Change, equivalent substitution, improvement etc., should be included in the scope of the protection.
Claims (6)
1. a kind of double-cyclone ejector filler, including top cover (1), rotarytype injector (2), upper bottom (3), midsole (4), ejector filler cavity
And sleeve (7) (6)；
The upper bottom (3), midsole (4) are connected as one with ejector filler cavity (6) respectively, and ejector filler top cover (1) connects with upper bottom (3)
Connect, fuel cavity is constituted between top cover (1) and upper bottom (3), there is a liquid propellant entrance (10) upper end of top cover (1)；Upper bottom (3)
Gaseous oxidant chamber is constituted between midsole (4)；It is water cavity between ejector filler cavity (6) and midsole (4)；
The sleeve (7) passes through midsole (4) and ejector filler cavity (6), and its two ends is respectively welded at midsole (4) and ejector filler cavity
(6) sealing is fixed in bottom surface, and rotarytype injector (2) is threadedly secured on bottom (3), rotarytype injector (2) according to
It is secondary to pass through upper bottom (3) and sleeve (7)；
Characterized by further comprising gas turbulator (5), the gas turbulator (5) includes swirl vane (51) and internal thread
(52) internal thread (52) and the external screw thread on rotarytype injector (2) housing that, the gas turbulator (5) passes through its inwall
(221) cooperate and fix, the flow channel of oxidant gas is formd between gas turbulator and sleeve (7)；
One group of straight-through water spray orifice (61) being uniformly distributed along the circumference on the ejector filler cavity (6), water enters water cavity point through water inlet (9)
(61) and ejector filler is sprayed with water spray orifice is entered；
The rotarytype injector (2) is swirler rotarytype injector.
2. a kind of double-cyclone ejector filler as claimed in claim 1, it is characterised in that the rotarytype injector (2) is by swirler
(21) constituted with nozzle body (22)；Nozzle body (22) includes fixation screw thread (223), the gas cyclone between upper bottom (3)
The external screw thread (221) of device (5) and the tangential seal groove (222) with gas turbulator (5).
3. a kind of double-cyclone ejector filler as claimed in claim 1 or 2, it is characterised in that the rotarytype injector (2) is single
Or it is multiple；Multiinjector configuration is used when fuel total mass flow rate is more than 400g/s, otherwise using single injector；
If multiinjector configuration, fuel total mass flow rate (kg/s) should meet following formula：
In formula, N represents nozzle quantity, nozzle quantity 1,3,6,18,36,60,90,126 or 168, from inside to outside adjacent turn according to
It is secondary to be incremented by 6 nozzles.
4. a kind of double-cyclone ejector filler as claimed in claim 1, it is characterised in that the number of blade n of the gas turbulator will expire
Foot
D in formula --- cyclone external diameter, L --- cyclone length, θ --- blade angle；
Gas turbulator blade established angle θ should meet following formula：
D in formula --- cyclone internal diameter, S is the strong and weak dimensionless number of sign flow rotation,
Blade angle θ is 50 °~70 °.
5. a kind of double-cyclone ejector filler as claimed in claim 1, it is characterised in that the diameter d of the water spray orifice (61)lBy following
Formula is determined：
In formula--- it is water-carrying capacity, Cd --- straight hole discharge coefficient takes 0.7~0.85, ρlFor water density (kg/m3), Δ
pl--- pressure drop when water injects, take chamber pressure 30%~50%, nl--- the number of water spray orifice.
6. a kind of double-cyclone ejector filler as claimed in claim 5, it is characterised in that the diameter d of the water spray orifice (61)1＜ 1mm.
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| CN201210570009.7A CN103867340B (en) | 2012-12-12 | 2012-12-12 | A kind of double-cyclone ejector filler |
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| CN201210570009.7A CN103867340B (en) | 2012-12-12 | 2012-12-12 | A kind of double-cyclone ejector filler |
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| CN103867340B true CN103867340B (en) | 2017-07-25 |
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| US11846253B2 (en) | 2018-10-30 | 2023-12-19 | Aerojet Rocketdyne, Inc. | Injector with injector elements in circumferential rows that alternate between counter-clockwise and clockwise swirl |
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| CN207795422U (en) * | 2017-12-25 | 2018-08-31 | 深圳光启空间技术有限公司 | Nozzle arrangements, injection apparatus and engine |
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