CN106693876B - A kind of supersonic nozzle - Google Patents
A kind of supersonic nozzle Download PDFInfo
- Publication number
- CN106693876B CN106693876B CN201710113905.3A CN201710113905A CN106693876B CN 106693876 B CN106693876 B CN 106693876B CN 201710113905 A CN201710113905 A CN 201710113905A CN 106693876 B CN106693876 B CN 106693876B
- Authority
- CN
- China
- Prior art keywords
- segment
- flow
- accelerating tube
- nozzle
- air
- 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 - Fee Related
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
- B01J—CHEMICAL OR PHYSICAL PROCESSES, e.g. CATALYSIS OR COLLOID CHEMISTRY; THEIR RELEVANT APPARATUS
- B01J19/00—Chemical, physical or physico-chemical processes in general; Their relevant apparatus
- B01J19/26—Nozzle-type reactors, i.e. the distribution of the initial reactants within the reactor is effected by their introduction or injection through nozzles
Landscapes
- Chemical & Material Sciences (AREA)
- Organic Chemistry (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Physical Or Chemical Processes And Apparatus (AREA)
- Disintegrating Or Milling (AREA)
Abstract
The present invention relates to a kind of supersonic nozzles, it is constituted by cyclic annular convergent-divergent nozzle, by injection charge pipe, accelerating tube, target head, using the supersonic flow of cyclic annular convergent-divergent nozzle, by the low speed flow of centre charging round tube, the injection in accelerating tube accelerates to supersonic speed state, make material particles that air-flow be followed to obtain enough kinetic energy and is gathered in air-flow center, the focusing fixation target head for colliding downstream, to solve the problems, such as that the charging encountered in high-speed flow solid phase reaction is difficult, material particles kinetic energy is low and crash response low efficiency.
Description
Technical field
This patent is related to hydrodynamics and solid state reaction field, and in particular to supersonic flow accelerates rare earth anti-
Using supersonic nozzle.
Background technique
Solid state reaction is a kind of important chemical synthesis process, be people's development of new solid phase material means it
One, it has the characteristics that highly selective, high yield, process engineering are simple.Its preparation process mainly has high-temperature calcination and mechanical grinding
Mill method, these methods are all the energy of raising reactant to ensure the generation of solid phase reaction.Supersonic flow accelerates low-heat solid
Phase reaction method is a kind of new technology for organically combining hypersonic flow body technique and rare earth chemical synthesising technology, can be big
The big feed-in density for improving energy is a kind of important green synthesis techniques, has potential huge applications value.
It is that reactant is added in air-flow that supersonic flow, which accelerates low heating solid state reaction basic principle, passes through air-flow band
Dynamic reaction mass movement, finally collides in fixed target head, realizes solid phase reaction during high velocity impact.Realize Supersonic Gas
Two conditions of stream acceleration low fever solid phase reaction are: reaction mass feed-in acceleration air-flow is accelerated to supersonic speed by one, and two will make
Material stream in air-flow has stable fluid properties, guarantees that it occurs high velocity impact in target head and completes transient state chemical reaction.It can
See, designing reasonable structure of reactor is the key that realize that supersonic flow accelerates low fever solid phase reaction.About structure of reactor
Design, traditional high speed jet mill mostly sprays high pressure gas from jet pipe obtains one high-speed flow, and under jet pipe
Feed inlet is opened up on the side wall of trip, material particles enter air-flow by feed inlet, follow high-speed flow to flow together, and in downstream
Hit target (publication CN105107595A).In addition, also there is patent (US2014/0058176A1) to disclose supersonic flow
The method for colliding synthesized micromolecule compound (such as acetylene etc.), wherein the raw material used is gas (such as water vapour, hydrogen
Gas, CO etc.), from the point of view of disclosed technical solution, the structure of reactor is as shown in Fig. 1, and unstrpped gas still takes side wall to open
The mode that mouth is added, this mode do not influence significantly for gas reaction raw material, but for low described in the present invention
For heating solid-state reaction, there are many problems: first is that destroying the uniformity in flow field, air-flow since feed inlet is opened on side wall
Disorder causes material to be difficult to obtain enough kinetic energy so that the flow field in downstream is difficult to reach or be maintained supersonic speed state；Two
It is that material is added by side wall, material is randomly dispersed in entire pipeline with the air-flow of disorder, does not converge to air-flow center, make
Target probability reduction must be hit.As it can be seen that needing to redesign reactant introduces the mode for accelerating air-flow, and it is whole to design completely new reactor
Body structure.
Summary of the invention
The main object of the present invention is to design a kind of jet pipe reactor for accelerating low fever solid phase reaction for supersonic flow,
Solve the problems, such as that the charging encountered in conventional air pulverizer is difficult, material particles kinetic energy is low and crash response low efficiency.
A kind of supersonic nozzle, along air current flow direction annular constrictions expanding nozzle and accelerating tube first segment, accelerating tube the
Two sections of sequential connections, and the inner cavity of perforation is formed, coaxial direction is drawn for one through setting inside annular constrictions expanding nozzle
Charging round tube is penetrated, by the arrival end of injection charging round tube for introducing solid particle or powder and normal pressure carrier gas stream, outlet end is prolonged
Accelerating tube first segment is extended to, annular constrictions expanding nozzle inner space is divided by injection charging round tube inner flow passage and cyclic annular receipts
Contracting expansionary channel；In accelerating tube second segment end, target head is set.
The annular constrictions expanding nozzle is integrally formed, including contraction section and expansion segment, and two sections of transition junctions are larynx
Road, venturi are at the smallest cross-sectional of contraction section and expansion segment, and high pressure draught is accelerated by contraction section air-flow, pressure reduction, in larynx
Reach the velocity of sound at road, expansion segment is then entered with supersonic speed state, air-flow is further speeded up, and pressure further decreases, out a kind of horse raised north of the Grean Wall
Conspicuous several M byIt is calculated, wherein AexFor annular constrictions slag nozzle divergence cone discharge area,
A*For 4 area of section of venturi, γ is the specific heat specific ray constant of working gas, for air γ=1.4, Aex/A*Expanded by annular constrictions
The diameter ratio D3/D2 for opening nozzle divergence cone outlet and throatpiston is calculated.High pressure draught passes through contraction section air-flow
Accelerate, pressure reduction enters expansion segment with supersonic speed state, and air-flow is further speeded up, and pressure further decreases, finally in annular
Convergent-divergent nozzle exit static pressure pexByIt is calculated, p0For incoming flow stagnation pressure, according to calculating
To pressure difference determine the additional amount of solid material particle stream.
By the injection charging diameter D1 of round tube, nozzle throat diameter of section D2, accelerating tube first segment entrance section diameter D3,
The preferred relationship of accelerating tube second segment entrance section diameter D4 are as follows: D1 < D2 < D3 < D4.The ring-type of annular constrictions expanding nozzle
Shrink segment length L1, the expansion segment length L2 of annular constrictions expanding nozzle, the first segment length of accelerating tube L3, second section of accelerating tube long
Spend L4 preference relation are as follows: L1 < L4 < L2 < L3.
The accelerating tube first segment and accelerating tube second segment are the horn-like pipe of two sections of different tapers, and two sections of pipes are integrated into
Type or sealed connection, it is 0.1~0.3 ° that the circular cone of the accelerating tube first segment, which expands angle α, the conical expander of accelerating tube second segment
Angle beta is 5~15 °, and the opening direction of two sections of pipes is consistent, is open along air current flow direction.
Preferably, it is 0.2 ° that the circular cone of the accelerating tube first segment, which expands angle α, the conical expander angle beta of accelerating tube second segment
It is 10 °.
The main function of annular constrictions expanding nozzle is the high pressure draught by toroidal nozzle outlet inflow in shrinkage expansion mistake
Accelerate to be supersonic flow in journey, guarantees that nozzle exit obtains a subatmospheric static pressure.
Main function by injection charging round tube is will be from 1 reaction mass of material particles carrier gas inflow entrance containing material particles
The center of particle addition supersonic flow.Due to being atmospheric pressure by the upstream of injection charging round tube 5, downstream ultrasonic speed jet pipe goes out
Mouthful, there is pressure difference between the two, which can suck material particles, and in accelerating tube first segment and accelerating tube second segment
Accelerate in air-flow.
The effect of accelerating tube first segment and accelerating tube second segment: first is that allowing the subsonic airflow in charge pipe in annular constrictions
One uniform supersonic flow is mixed under the ejector action of supersonic flow in expanding nozzle；Second is that charge pipe is allowed to come out
Material particles follow supersonic flow sufficiently to accelerate in accelerating sections；Third is that assembling in the gas flow when material particles being allowed to accelerate
Centre.
The supersonic flow of tube inlet is being accelerated to be flowing axially into, air-flow deflects when by charging nozzle, can pole
Big reduction pressure is capable of the subsonic airflow containing material particles at fine injection center.Two strands of air-flows mix in accelerating tube
One supersonic flow is obtained, material can follow the supersonic flow adequately to accelerate in accelerating sections, to obtain enough
Big kinetic energy.Since two strands of air-flows are all along axial flowing, radial velocity is very little, so entering flow field from charging round tube
The radial velocity very little of material particles can guarantee that material particles are gathered in the center of air-flow always in accelerator in this way
Centre.
The effect of target head is collided with material particles.Material particles follow air-flow to obtain sufficiently large kinetic energy, most
It accurately collides in the target head in center afterwards, and the reaction zone before target head induces solid phase reaction.
In use, upstream high gas source is docked with the entrance of toroidal nozzle, high pressure draught passes through at venturi and reaches the velocity of sound,
Supersonic flows are being expanded to by accelerating sections first segment, toroidal nozzle outlet generates one relative to material particles carrier gas inflow entrance
A negative pressure generates ejector action to the low speed flow in charge pipe, and low speed flow is made to accelerate and mix in outlet and supersonic flow
It closes.Two strands of air-flows accelerate pipeline in further mix so that the velocity profile at center with ring-type mainstream it is suitable, material particles with
Central gas stream constantly accelerate to supersonic speed state, and obtain sufficiently large kinetic energy；Due to the axis pair of upstream and acceleration pipeline
Claim property, make entire flow process all along axial flowing, radial velocity can be ignored, and material particles are all gathered in the center of flowing
Centre.Material particles follow air-flow finally with supersonic speed collision in downstream central target head, and anti-in target head reaction zone induction solid phase
It answers.Fine particle after collision carries out circulation and stress by the recovery channel of lower exit.
Supersonic nozzle basic functional principle of the invention is will to blend solid using the ejector action of supersonic flow
The low speed flow of grain material accelerates to supersonic speed, so that material particles also accelerated to supersonic speed state with air-flow, so that material
Particle has sufficiently large kinetic energy, since material particles are added from the center injection of supersonic flow, and in entire pipeline
Even flow field can accurately collide the target in downstream central so material particles still accumulate in the center of jet pipe after accelerating
Head simultaneously realizes solid phase reaction.
When being tested using supersonic nozzle of the invention, the stagnation pressure of incoming flow is 15atm, total temperature 300K, jet pipe
Work Mach 2 ship 3, and jet pipe shows excellent technical effect, is in particular in:
(1) annular constrictions expanding nozzle can make air-flow reach supersonic speed state, and obtain a negative pressure in nozzle exit,
Material is more conducive to be inhaled into, such as: when the absolute pressure of nozzle exit is 0.408atm, speed can achieve 622m/
s。
(2) pressure difference for being about 0.596atm is generated in upstream and downstream, by the pressure difference for the round tube upstream and downstream that feeds, can be made
In material particles unobstructed ground feed-in injection air-flow.
(3) material particles injection enters after accelerating tube, and air velocity can be accelerated under the drive of air-flow, to obtain
Obtain very high kinetic energy.
(4) material particles accumulate in air-flow center after accelerating, to realize focusing collision, induce efficient solid phase
Reaction.
Detailed description of the invention
The nozzle structure schematic diagram for the lateral addition reaction mass that Fig. 1 takes in the prior art, wherein 1 ' feeds for top
Mouthful, 2 ' be lower part feed inlet, and 3 ' be reaction mass feed zone, and 4 ' be accelerating sections.
Fig. 2 is suitable for the nozzle structure schematic diagram that supersonic flow accelerates low fever solid phase reaction, wherein 1- contains material particles
Low-pressure air current entrance；2- high pressure injection gas access；3- annular constrictions expanding nozzle；4- venturi；5- is fed round tube by injection；
The outlet of 6- toroidal nozzle；7- supersonic flow；8- accelerating tube first segment；9- high speed gas-solid is mutually flowed；10- accelerating tube second segment；11-
High speed solid phase stream collision area；12- target head；13- air stream outlet；D1 is by the diameter of injection charging round tube；D2 is nozzle throat
Diameter of section；D3 is accelerating tube first segment entrance section diameter；D4 is accelerating tube second segment entrance section diameter；L1 is jet pipe ring
Shape shrinks segment length；L2 is that jet pipe ring-type expands segment length；L3 is the first segment length of accelerating tube；L4 is second section of accelerating tube long
Degree；α is that accelerating tube first segment circular cone expands angle；β is that accelerating tube second segment circular cone expands angle.
Velocity profile of Fig. 3 different-grain diameter particle along flow direction.Wherein, in figure the zero point of reference axis at nozzle exit 8.
Specific embodiment
Supersonic nozzle, along air current flow direction annular constrictions expanding nozzle 3 and accelerating tube first segment 8, accelerating tube second
Section 10 is linked in sequence, and forms the inner cavity of perforation, is drawn for one in 3 inside coaxial direction of annular constrictions expanding nozzle through setting
Charging round tube 5 is penetrated, is extended by the arrival end connection solid particle of injection charging round tube 5 or powder and normal pressure carrier gas stream, outlet end
To accelerating tube first segment 8,3 inner space of annular constrictions expanding nozzle is divided by injection charging 5 inner flow passage of round tube and ring-type
Shrinkage expansion runner；In 10 end of accelerating tube second segment, cylinder target head 12 is set.Annular constrictions expanding nozzle 3 is integrally formed,
Including contraction section and expansion segment, two sections of transition junctions are venturi 4, and venturi 4 is height at the smallest cross-sectional of contraction section and expansion segment
Pressure gas stream is accelerated by contraction section air-flow, pressure reduction, and the velocity of sound is reached at venturi 4, then enters expansion with supersonic speed state
Section, air-flow further speeds up, and pressure further decreases, exit Mach number M byIt is calculated,
Wherein, AexFor annular constrictions slag nozzle divergence cone discharge area, A*For 4 area of section of venturi, γ is the specific heat of working gas
Specific ray constant, for air γ=1.4, Aex/A*By annular constrictions expanding nozzle (3) expansion segment outlet and venturi (4) section
Diameter ratio D3/D2 be calculated.High pressure draught is accelerated by contraction section air-flow, pressure reduction, with the entrance of supersonic speed state
Expansion segment, air-flow are further speeded up, and pressure further decreases, finally the static pressure p at toroidal nozzle outlet 6exByIt is calculated, p0For incoming flow stagnation pressure, solid material particle stream is determined according to the pressure difference being calculated
Additional amount.
By diameter D1,4 diameter of section D2 of nozzle throat, the 8 entrance section diameter of accelerating tube first segment of injection charging round tube 5
The preferred relationship of D3,10 entrance section diameter D4 of accelerating tube second segment are as follows: D1 < D2 < D3 < D4.Annular constrictions expanding nozzle 3
Cyclic annular shrink segment length L1, the expansion segment length L2 of annular constrictions expanding nozzle 3,8 length L3 of accelerating tube first segment, accelerating tube
10 length L4 preference relation of second segment are as follows: L1 < L4 < L2 < L3.The accelerating tube first segment 8 and accelerating tube second segment 10 are two
The horn-like pipe of Duan Butong taper, two sections of pipes are integrally formed or are tightly connected, and the circular cone of the accelerating tube first segment 8 expands angle
α is 0.1~0.3 °, and the conical expander angle beta of accelerating tube second segment 10 is 5~15 °, and the opening direction of two sections of pipes is consistent, along gas
Flow flow direction opening.Preferably, it is 0.2 ° that the circular cone of the accelerating tube first segment 8, which expands angle α, the circle of accelerating tube second segment 10
Boring angle of flare β is 10 °.
In use, upstream high gas source is docked with the entrance 6 of toroidal nozzle, high pressure draught is by reaching sound at venturi 4
Speed is being expanded to supersonic flows by accelerating sections first segment 8, and toroidal nozzle outlet 6 is relative to solid particle carrier gas inflow entrance 1
Generate a negative pressure, ejector action generated to the low speed flow in charge pipe, make low speed carrier gas stream and solid particle accelerate and
Outlet is mixed with supersonic flow 9.Two strands of air-flows further mix in accelerating pipeline, so that the velocity profile at center and ring-type
Mainstream is suitable, and solid particle constantly accelerates to supersonic speed state with central gas stream, and obtains sufficiently large kinetic energy.Due to upper
Trip and accelerate pipeline axial symmetry, make entire flow process all along axial flowing, radial velocity can be ignored, material particles
All it is gathered in the centre 9 of flowing.Solid particle follows air-flow finally with supersonic speed collision in downstream central target head 12, and
Target head reaction zone 11 induces solid phase reaction.Fine particle after collision is recycled back to by the recovery channel of lower exit 13
It receives.
The main function of annular constrictions expanding nozzle 3 is the high pressure draught that flows into high pressure entry 6 in shrinkage expansion process
It is middle to accelerate to be supersonic flow, guarantee that nozzle exit 8 obtains a subatmospheric static pressure.By the master of injection charging round tube 5
Act on be by from containing material particles 1 reaction mass particle of material particles carrier gas inflow entrance be added supersonic flow center
The heart.Due to being atmospheric pressure by the upstream of injection charging round tube 5, there is pressure difference, the pressure in downstream ultrasonic speed nozzle exit between the two
Difference can suck material particles, and accelerate in the air-flow of accelerating tube first segment 8 and accelerating tube second segment 10.Accelerating tube first
The effect of section 8 and accelerating tube second segment 10: first is that allowing the subsonic airflow in charge pipe 2 in annular constrictions expanding nozzle 3
One uniform supersonic flow is mixed under the ejector action 7 of supersonic flow；Second is that the material particles for allowing charge pipe to come out
Supersonic flow is followed sufficiently to accelerate in accelerating sections；Third is that being gathered in air-flow center 9 when material particles being allowed to accelerate.In accelerating tube
The supersonic flow of entrance is flowing axially into, and air-flow deflects when by charging nozzle, and pressure can be greatly reduced, can
The subsonic airflow containing material particles at fine injection center.Two strands of air-flows are mixed to get one Supersonic Gas in accelerating tube
Stream, material can follow the supersonic flow adequately to accelerate in accelerating sections, to obtain sufficiently large kinetic energy.Due to two strands
Air-flow is all along axial flowing, and radial velocity is very little, so entering the radial speed of the material particles in flow field from charging round tube
Very little is spent, can guarantee that material particles are gathered in the centre of air-flow always in accelerator in this way.The effect of target head 11 is
It collides with material particles.Material particles follow air-flow to obtain sufficiently large kinetic energy, and last accurately collision is in center
Reaction zone 11 in target head, and before target head induces solid phase reaction.
It is tested using supersonic nozzle of the invention, the stagnation pressure of incoming flow is 15atm, total temperature 300K, jet pipe work
Mach 2 ship 3, select respectively 1 μm, 5 μm, 10 μm, 15 μm, 20 μm of silicon powder particles are in the Supersonic Gas for being mounted with supersonic nozzle
Stream accelerates to test in low fever solid phase reaction device, and monitors the accelerator accelerated in pipeline, as shown in figure 3, five kinds of granularities
Solid particle can be accelerated to supersonic speed in very short distance, with the increase of solid grain size, be accelerated to ultrasound
Accelerating travel required for speed is longer, but can reach required supersonic speed, such as 20um in a complete accelerating sections
Speed of the particle in downstream can achieve about 500m/s.Annular constrictions expanding nozzle can make air-flow reach supersonic speed state,
And a negative pressure is obtained in nozzle exit, it is more conducive to material and is inhaled into, when the absolute pressure of nozzle exit is 0.408atm
When, speed can achieve 622m/s, and the pressure difference for being about 0.596atm is generated in upstream and downstream, pass through the pressure for the round tube upstream and downstream that feeds
Power is poor, can make in the unobstructed feed-in injection air-flow of material particles, material particles injection enters after accelerating tube, in the drive of air-flow
Under can accelerate to air velocity, to obtain very high kinetic energy, material particles accumulate in air-flow center after accelerating, to realize
Focusing collision induces efficient solid phase reaction.
Claims (5)
1. a kind of supersonic nozzle, including annular constrictions expanding nozzle (3), accelerating tube first segment (8), accelerating tube second segment
(10), three is successively linked in sequence along airflow direction and forms the inner cavity of perforation, internal coaxial in annular constrictions expanding nozzle (3)
Direction is fed round tube (5) through setting by injection, by the arrival end of injection charging round tube (5) for introducing solid particle or powder
With normal pressure carrier gas stream, the inlet of accelerating tube first segment (8), the annular are extended to by the outlet end of injection charging round tube (5)
Convergent-divergent nozzle (3) is integrally formed, including contraction section and expansion segment, and two sections of transition junctions are venturi, and venturi is to shrink
At section and the smallest cross-sectional of expansion segment, annular constrictions expanding nozzle makes air-flow reach supersonic speed state, and obtains in nozzle exit
To a negative pressure, annular constrictions expanding nozzle (3) inner space is divided by injection charging round tube (5) inner flow passage and cyclic annular receipts
Target head (12) are arranged in accelerating tube second segment (10) end, the contraction segment length of annular constrictions expanding nozzle (3) in contracting expansionary channel
L1, the expansion segment length L2 of annular constrictions expanding nozzle (3), accelerating tube first segment (8) length L3, accelerating tube second segment (10) are long
Spend the relationship of L4 are as follows: L1 < L4 < L2 < L3, the accelerating tube first segment (8) are two sections of different cones with accelerating tube second segment (10)
The horn-like pipe of degree, two sections of pipes are integrally formed or are tightly connected, and it is 0.1 that the circular cone of the accelerating tube first segment (8), which expands angle α,
~0.3 °, the conical expander angle beta of accelerating tube second segment (10) is 5~15 °, and the opening direction of two sections of pipes is consistent, along air-flow stream
Dynamic direction opening.
2. jet pipe according to claim 1, which is characterized in that the annular constrictions expanding nozzle (3) is integrally formed, by
Contraction section and expansion segment are constituted, and two sections of transition junctions are venturi (4), and venturi (4) is the smallest cross-sectional of contraction section and expansion segment
Place, high pressure draught are accelerated by contraction section air-flow, and pressure reduction reaches the velocity of sound at venturi (4), subsequently into expansion segment, gas
Stream is further speeded up, and pressure further decreases, exit Mach number M byIt is calculated, wherein
AexFor annular constrictions expanding nozzle (3) expansion segment discharge area, A*For venturi (4) area of section, γ is the specific heat of working gas
Specific ray constant, for air γ=1.4, Aex/A*By annular constrictions expanding nozzle (3) expansion segment outlet and venturi (4) section
Diameter ratio D3/D2 be calculated.
3. jet pipe according to claim 2, which is characterized in that high pressure draught is accelerated by contraction section air-flow, pressure reduction,
Air-flow is further speeded up after into expansion segment, and pressure further decreases, finally the static pressure at annular constrictions expanding nozzle outlet (6)
pexByIt is calculated, p0For incoming flow stagnation pressure, solid material is determined according to the pressure difference being calculated
The additional amount of grain stream.
4. jet pipe according to claim 1, which is characterized in that by diameter D1, the nozzle throat of injection charging round tube (5)
(4) diameter of section D2, accelerating tube first segment (8) entrance section diameter D3, accelerating tube second segment (10) entrance section diameter D4
Relationship are as follows: D1 < D2 < D3 < D4.
5. jet pipe according to claim 1, which is characterized in that the circular cone of the accelerating tube first segment (8) expands angle α and is
0.2 °, the conical expander angle beta of accelerating tube second segment (10) is 10 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710113905.3A CN106693876B (en) | 2017-02-28 | 2017-02-28 | A kind of supersonic nozzle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710113905.3A CN106693876B (en) | 2017-02-28 | 2017-02-28 | A kind of supersonic nozzle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106693876A CN106693876A (en) | 2017-05-24 |
| CN106693876B true CN106693876B (en) | 2019-11-12 |
Family
ID=58917889
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710113905.3A Expired - Fee Related CN106693876B (en) | 2017-02-28 | 2017-02-28 | A kind of supersonic nozzle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106693876B (en) |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| PL421044A1 (en) | 2017-03-30 | 2018-10-08 | General Electric Company | System and method for an engine jet pump, powered by the interchangeable air-flow system |
| CN107598754B (en) * | 2017-10-20 | 2019-02-15 | 中国人民解放军国防科技大学 | Hypersonic velocity laminar flow spray pipe molded surface mirror surface machining process |
| CN108999725B (en) * | 2018-07-19 | 2020-07-24 | 北京航空航天大学 | Jet nozzle with double-bell-shaped jet sleeve |
| CN108757217B (en) * | 2018-07-19 | 2020-07-14 | 北京航空航天大学 | Double-bell-shaped expansion deflection spray pipe |
| CN113750930B (en) * | 2021-08-24 | 2023-02-17 | 化学与精细化工广东省实验室 | Inlet connecting structure of ultrasonic pipeline reactor |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1781610A (en) * | 2004-08-23 | 2006-06-07 | 德尔菲技术公司 | Continuous in-line manufacturing process for high speed coating deposition via kinetic spray process |
| CN1830576A (en) * | 2005-03-09 | 2006-09-13 | Snt株式会社 | Nozzle for cold spray and cold spray apparatus using the same |
| CN2925627Y (en) * | 2006-07-27 | 2007-07-25 | 绵阳流能粉体设备有限公司 | Nozzle for accelerating grain during process of flow crushing |
| CN102744173A (en) * | 2012-07-05 | 2012-10-24 | 西安交通大学 | Solid particle pre-whirl mixing pneumatic acceleration device and method |
| CN102814248A (en) * | 2012-08-01 | 2012-12-12 | 中国船舶重工集团公司第七二五研究所 | Nozzle for axial siphon powder delivering type cold spray |
| CN206897412U (en) * | 2017-02-28 | 2018-01-19 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of supersonic nozzle |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP5573505B2 (en) * | 2010-09-01 | 2014-08-20 | 株式会社Ｉｈｉ | Ejector nozzle for cold spray device and cold spray device |
| US10100412B2 (en) * | 2014-11-06 | 2018-10-16 | United Technologies Corporation | Cold spray nozzles |
-
2017
- 2017-02-28 CN CN201710113905.3A patent/CN106693876B/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1781610A (en) * | 2004-08-23 | 2006-06-07 | 德尔菲技术公司 | Continuous in-line manufacturing process for high speed coating deposition via kinetic spray process |
| CN1830576A (en) * | 2005-03-09 | 2006-09-13 | Snt株式会社 | Nozzle for cold spray and cold spray apparatus using the same |
| CN2925627Y (en) * | 2006-07-27 | 2007-07-25 | 绵阳流能粉体设备有限公司 | Nozzle for accelerating grain during process of flow crushing |
| CN102744173A (en) * | 2012-07-05 | 2012-10-24 | 西安交通大学 | Solid particle pre-whirl mixing pneumatic acceleration device and method |
| CN102814248A (en) * | 2012-08-01 | 2012-12-12 | 中国船舶重工集团公司第七二五研究所 | Nozzle for axial siphon powder delivering type cold spray |
| CN206897412U (en) * | 2017-02-28 | 2018-01-19 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of supersonic nozzle |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106693876A (en) | 2017-05-24 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106693876B (en) | A kind of supersonic nozzle | |
| CN104110325B (en) | Combined cycle engine | |
| CN106370432B (en) | A kind of exhaust apparatus of supersonic speed nozzle exhaust simulation test | |
| CN108195544B (en) | A kind of impulse type wind-tunnel tandem jet pipe | |
| CN106407571A (en) | A hypersonic velocity air-breathing type ramjet pneumatic thrust analysis method | |
| CN206897412U (en) | A kind of supersonic nozzle | |
| CN106525627A (en) | Supersonic sand blasting gun | |
| CN102581291B (en) | Circumferential seam type supersonic nozzle for metal gas atomization | |
| CN104847708B (en) | Supersonic Ejector | |
| CN105268569B (en) | A kind of mixing device of gas-liquid two-phase annular flow jet and mainstream gas | |
| CN112474094B (en) | Remote jetting method and device for supersonic airflow and rotational flow negative pressure coupling | |
| CN206793439U (en) | A kind of microbubble generating mechanism | |
| CN103678774B (en) | Designing method for supersonic velocity thrust exhaust nozzle considering inlet parameter unevenness | |
| CN106678179A (en) | Cylindrically symmetric internal circumferential jet flow pressure stabilizing chamber supplying gas to high-pressure disc gas bearing | |
| CN114738796A (en) | Air atomizing nozzle with rotary oil pipe | |
| CN204041270U (en) | Combined cycle engine | |
| CN206002316U (en) | Injector for engine testsand gas extraction system | |
| CN106743674A (en) | A kind of device that solid powder is sent into high velocity air | |
| CN111760476A (en) | Aeroengine high-altitude cabin gas mixing method and gas mixer based on Venturi tube | |
| CN108240898A (en) | A kind of impulse type wind-tunnel tandem jet pipe | |
| CN104019957B (en) | Nano-particle Fluidizer and supersonic wind tunnel system | |
| CN207161224U (en) | A kind of unsteady annular jet jet pipe for improving pulse detonation engine thrust coefficient | |
| CN206793438U (en) | A kind of spiral through hole microbubble generating apparatus | |
| CN112827687B (en) | Spiral pipeline oscillation atomizer based on bionic surface | |
| US3187501A (en) | Method of and apparatus for augmenting thrust and suppressing sound in aircraft, rockets, and the like |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20191112 Termination date: 20200228 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |