CN114969627A - Method for designing molded surface of supersonic circumferential seam spray pipe for gas atomization powder preparation - Google Patents
Method for designing molded surface of supersonic circumferential seam spray pipe for gas atomization powder preparation Download PDFInfo
- Publication number
- CN114969627A CN114969627A CN202210493767.7A CN202210493767A CN114969627A CN 114969627 A CN114969627 A CN 114969627A CN 202210493767 A CN202210493767 A CN 202210493767A CN 114969627 A CN114969627 A CN 114969627A
- Authority
- CN
- China
- Prior art keywords
- supersonic
- spray pipe
- seam
- section
- outlet
- 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.)
- Pending
Links
- 239000007921 spray Substances 0.000 title claims abstract description 39
- 239000000843 powder Substances 0.000 title claims abstract description 36
- 238000000034 method Methods 0.000 title claims abstract description 20
- 238000002360 preparation method Methods 0.000 title claims abstract description 12
- 238000009689 gas atomisation Methods 0.000 title claims abstract description 11
- 230000008602 contraction Effects 0.000 claims abstract description 17
- 238000013461 design Methods 0.000 claims description 26
- 238000012937 correction Methods 0.000 claims description 5
- 238000006073 displacement reaction Methods 0.000 claims description 4
- 238000000465 moulding Methods 0.000 claims description 3
- XOOUIPVCVHRTMJ-UHFFFAOYSA-L zinc stearate Chemical compound [Zn+2].CCCCCCCCCCCCCCCCCC([O-])=O.CCCCCCCCCCCCCCCCCC([O-])=O XOOUIPVCVHRTMJ-UHFFFAOYSA-L 0.000 claims description 3
- 238000002474 experimental method Methods 0.000 claims 1
- 239000002184 metal Substances 0.000 abstract description 11
- 238000007639 printing Methods 0.000 abstract description 7
- 239000007789 gas Substances 0.000 description 16
- 239000007788 liquid Substances 0.000 description 3
- 238000010146 3D printing Methods 0.000 description 2
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 description 2
- 238000013459 approach Methods 0.000 description 2
- 238000000889 atomisation Methods 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 238000009826 distribution Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000002844 melting Methods 0.000 description 2
- 239000000956 alloy Substances 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 229910052786 argon Inorganic materials 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 238000012938 design process Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 230000006698 induction Effects 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 239000002245 particle Substances 0.000 description 1
- 238000010298 pulverizing process Methods 0.000 description 1
- 238000012887 quadratic function Methods 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
- 230000005514 two-phase flow Effects 0.000 description 1
Images
Classifications
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F17/00—Digital computing or data processing equipment or methods, specially adapted for specific functions
- G06F17/10—Complex mathematical operations
- G06F17/11—Complex mathematical operations for solving equations, e.g. nonlinear equations, general mathematical optimization problems
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F9/00—Making metallic powder or suspensions thereof
- B22F9/02—Making metallic powder or suspensions thereof using physical processes
- B22F9/06—Making metallic powder or suspensions thereof using physical processes starting from liquid material
- B22F9/08—Making metallic powder or suspensions thereof using physical processes starting from liquid material by casting, e.g. through sieves or in water, by atomising or spraying
- B22F9/082—Making metallic powder or suspensions thereof using physical processes starting from liquid material by casting, e.g. through sieves or in water, by atomising or spraying atomising using a fluid
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B33—ADDITIVE MANUFACTURING TECHNOLOGY
- B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
- B33Y40/00—Auxiliary operations or equipment, e.g. for material handling
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F9/00—Making metallic powder or suspensions thereof
- B22F9/02—Making metallic powder or suspensions thereof using physical processes
- B22F9/06—Making metallic powder or suspensions thereof using physical processes starting from liquid material
- B22F9/08—Making metallic powder or suspensions thereof using physical processes starting from liquid material by casting, e.g. through sieves or in water, by atomising or spraying
- B22F9/082—Making metallic powder or suspensions thereof using physical processes starting from liquid material by casting, e.g. through sieves or in water, by atomising or spraying atomising using a fluid
- B22F2009/088—Fluid nozzles, e.g. angle, distance
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
- Y02P10/00—Technologies related to metal processing
- Y02P10/25—Process efficiency
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Mathematical Physics (AREA)
- General Physics & Mathematics (AREA)
- Mathematical Optimization (AREA)
- Pure & Applied Mathematics (AREA)
- Theoretical Computer Science (AREA)
- Mathematical Analysis (AREA)
- Computational Mathematics (AREA)
- Data Mining & Analysis (AREA)
- Chemical & Material Sciences (AREA)
- Operations Research (AREA)
- Algebra (AREA)
- Manufacturing & Machinery (AREA)
- Databases & Information Systems (AREA)
- Software Systems (AREA)
- General Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Application Of Or Painting With Fluid Materials (AREA)
Abstract
The invention relates to a method for designing the molded surface of a supersonic circumferential weld nozzle for gas atomization powder preparation, wherein the gas jet formed by the circumferential weld nozzle structure has slow decay, high jet quality and high powder forming rate of prepared metal powder for 3d printing. The invention discloses a method for designing a molded surface of a supersonic circumferential seam spray pipe for gas atomization powder preparation, which comprises the following steps of: determining the molded surface of the subsonic annular seam contraction section by adopting a bicubic curve; the profile of the supersonic annular seam expansion section is determined by the circular arc section and the quadratic power function curve; the size of each part of the supersonic annular seam spray pipe is determined by estimating the maximum Mach number of the supersonic expansion section outlet of the annular seam spray pipe. By adopting the novel atomizing nozzle structure designed by the technical scheme of the patent, the prepared 3d printing metal powder forming rate reaches 60 percent.
Description
Technical Field
The invention relates to the field of powder preparation by gas atomization, in particular to a design method of a circumferential seam profile of a supersonic atomizing nozzle.
Background
With the development of 3D technology, the demand for high performance metal powders is increasing. The vacuum induction melting gas atomization powder preparation technology is a main preparation method of conventional metal powder at present, and the core component atomizing nozzle structure determines key technical indexes of particle size distribution, sphericity, satellite powder rate and the like of the prepared metal powder.
In the actual production process, due to the limitation of the structure of the powder making nozzle, the powder yield of the metal powder in the specific section for the 3D printing process is generally low, so that a large amount of re-melting powder is generated, and finally, the production cost is sharply increased and a large amount of energy is wasted.
The key for improving the powder yield of the metal powder for 3d printing is to optimize the structure of the powder making nozzle and improve the gas jet velocity and quality of atomized metal liquid flow. The profile structure of the circular seam airflow channel of the atomizing nozzle is a key factor for limiting the speed and the quality of the gas jet, but the specific design method is not published in the field. Therefore, the design method for the molded surface of the supersonic annular seam spray pipe for gas atomization powder preparation has urgent and important practical significance.
Disclosure of Invention
The invention aims to provide a design method of a key position of a supersonic nozzle and a molded surface of an airflow channel of a circular seam spray pipe, which ensures that a high-quality supersonic gas jet is formed by an atomizing nozzle and improves the powder forming rate of metal powder in a specific section for preparing 3d printing.
The invention provides a method for designing a molded surface of a supersonic circumferential seam spray pipe for gas atomization powder preparation, which is characterized by comprising the following steps of:
the molded surface of the supersonic speed circular seam spray pipe mainly comprises a subsonic speed circular seam contraction section and a supersonic speed circular seam expansion section, and the middle part of the supersonic speed circular seam spray pipe is limited by a throat part;
the molding surface of the subsonic annular seam contraction section is determined by adopting a bicubic curve;
the profile of the supersonic annular seam expansion section is determined by the circular arc section and the quadratic power function curve;
the size of each part of the supersonic annular seam spray pipe is determined by estimating the maximum Mach number of the supersonic expansion section outlet of the annular seam spray pipe.
Further preferably, the estimation of the maximum mach number of the outlet of the supersonic expansion section of the circular seam nozzle specifically comprises the following steps,
firstly, the total pressure P of the inlet of the spray pipe is given 0 Ambient pressure and preset mach numberMaRange, iteratively estimating the maximum Mach number corresponding to the closest approach of the outlet pressure P to the ambient pressure by equation (2)Ma max (ii) a Then, the estimated maximum Mach numberMa max Substituting into equation (1), calculating area ratio A/A, and calculating the size of annular seam nozzle throat, supersonic expansion section outlet, subsonic contraction section inlet, and annular seam nozzle throat distance to the center of the flow guide pipe 1 The length L from the supersonic expansion section of the circular seam spray pipe to the center of the flow guide pipe 2 Calculating to obtain the outlet width of the circular seam spray pipe, determining the position of the spray pipe and the coordinates of an outlet point,
in the formula, A is the cross section area of the outlet of the supersonic expansion section;
a is the cross-sectional area of the throat part of the circular seam jet pipe;
gamma is the specific heat ratio of the gas in the circular seam spray pipe;
Mathe gas mach number.
Further preferably, the profile of the subsonic circular seam contraction section is determined by a bicubic curve, and a control equation of the profile is as follows:
in the formulax m Is a front and back connection point of two curves;D i is an axial distance ofx0.5 < the cross-sectional diameter ofx m L < 0.6, D is the initial diameter, set between 3 and 10mm, wherexThe position of =0 is the starting point of the subsonic annular seam contraction section, and L is the length of the subsonic annular seam contraction section.
Further preferably, the circular arc segment is formed by a circular arc half angleθRadius ofρ t Determining, wherein,θthe initial value of the pre-estimated design is 15-45 degrees,ρ t the estimated design initial value is 5-20 mm.
Further preferably, the second power function curve isy=a+bx+cx 2 Wherein coefficients are determineda，b，cFirst, the position of the connection point a of the quadratic function curve and the circular arc segment is determined (x a ，y a ) Connecting angleθ a And exit edge angle θ e Wherein the location of the connection point a is determined by the following equation:
x a =ρ t sinθ a； （4）
y a =r t +（1-cosθ a ）ρ t， （5）
whereinr t The ordinate of the throat is based on the gas jet flow rate required for atomizing powder, generallyr t The value is 0.3-0.5mm,θ a the pre-estimated design initial value is 30-40 degrees. In order to ensure uniform velocity of gas jet at the outlet of the circular seam spray pipe, the edge angle theta of the outlet e Typically at 0 ℃. Radius of arc according to designρ t Can determinex a、 y a, And substituting the position coordinates of the outlet of the expansion section and the edge angle theta into the following equation e It is known that coefficients can be determined jointlya，bAndc。
y=a+bx+cx 2 （6）
tanθ a =b+2cx （7）
tanθ e =b+2cx （8）
preferably, the profile of the supersonic annular seam expanding section is corrected by adopting a viscous boundary layer correction theory; the concrete requirements are as follows:
d * (x) The boundary layer displacement thickness at point x, typically α = 0.5.
The invention has the beneficial effects that: the novel profile structure of the circular seam airflow channel of the atomizing nozzle designed by the method has the advantages that the quality and the gas speed of the formed supersonic gas jet are remarkably improved, and the powder forming rate of the prepared metal powder in the 3D printing powder section is greatly improved.
Drawings
For the purpose of clearly illustrating the technical solution of the embodiments of the present invention, the drawings used in the embodiments will be described in detail below.
FIG. 1 is an overall view of the nozzle of the method for designing the profile of a circular seam nozzle according to the present invention.
FIG. 2 is a schematic view of the profile of the circumferential seam nozzle of the present invention.
FIG. 3 is a general design flow chart of the method for designing the circumferential seam nozzle profile according to the present invention.
Wherein, 1, the honeycomb duct; 2. a circular seam spray pipe; 3. a subsonic contraction section curve of a circular seam nozzle; 4. a circular seam nozzle throat curve; 5. the circular seam spray pipe is a supersonic expansion section curve.
Detailed Description
Based on the nozzle gas-liquid two-phase flow atomization mechanism, the key for improving the powder forming rate of the 3d printing section is the nozzle circular seam airflow channel structure which has the condition of forming high-quality gas jet flow with high speed and uniform speed distribution, so that the invention provides the design method of the supersonic speed circular seam spray pipe profile for gas atomization powder preparation. For clearly illustrating a specific technical design of the embodiment of the present invention, the embodiment will be described in detail below with reference to the accompanying drawings.
Please refer to fig. 1 to 3 for description.
Referring to fig. 1, the overall structure of the atomizing powder-making nozzle mainly includes a guide pipe 1 of a metal liquid flow channel, a key part formed by gas jet, and a supersonic annular seam nozzle 2;
referring to fig. 2, the supersonic annular-seam nozzle mainly comprises a subsonic contraction section and a supersonic expansion section, and the profile curve comprises a subsonic contraction section curve 3 of the annular-seam nozzle, a throat curve 4 of the annular-seam nozzle and a supersonic expansion section curve 5 of the annular-seam nozzle.
The subsonic velocity contraction section 3 of the circular seam nozzle is generally determined by a bicubic curve, and a control equation is as follows:
in the formulax m Is a front and back connection point of two curves;D i is an axial distance ofxThe cross-sectional diameter of (A) is generally 0.5 < (R) >x m /L＜0.6，DThe initial diameter is typically set between 3-10 mm.
Referring to fig. 3, the design process of the supersonic annular seam expansion section is to estimate the maximum mach number at the outlet of the annular seam nozzle, and is mainly determined by a quasi-constant isentropic flow formula:
the mach number of the nozzle expansion section depends only on the area ratio:
(1)
nozzle expanderThe static pressure of the flare depends only on mach number:
(2)
in the formula, A is the cross section area of an outlet of the supersonic expansion section;
a is the cross-sectional area of the throat part of the circular seam jet pipe;
gamma is the specific heat ratio of the gas in the circular seam spray pipe;
Mathe gas mach number.
During design, total pressure P of the inlet of the spray pipe is firstly given 0 The environmental pressure and the preset Mach number range, and MAT-
Programming the LAB software to iteratively estimate the maximum Mach number corresponding to the closest approach of the outlet pressure P to the ambient pressure by equation (2)Ma max . Secondly, the estimated Mach numberMa max Substituting into equation (1), calculating area ratio A/A, and calculating throat size d of annular seam nozzle 2 2 Supersonic expansion section outlet size d 3 Subsonic constriction entrance dimension d 1 The length L of the throat part of the annular seam spray pipe 2 from the center of the flow guide pipe 1 1 The length L of the ultrasonic expansion section of the annular seam spray pipe 2 from the center of the flow guide pipe 1 2 And calculating to obtain the outlet width of the circular seam spray pipe, and preliminarily determining the position of the spray pipe and the coordinates of an outlet point.
Assuming the initial profile of the expansion section of the annular nozzle as a combination of a throat arc section and a quadratic power function curve, please refer to fig. 2, wherein the arc section: by arc half angleθRadius ofρ t Determining the number of the first and second groups, wherein,θthe initial value of the pre-estimated design is 15-45 degrees,ρ t estimating a design initial value to be 5-20 mm; curve of the second power function:y=a+bx+cx 2 ，determining coefficientsa，b，cThe value of (c) needs to know: position of connection point A: (x a ，y a ) Connecting angleθ a And exit edge angleθ e 。Wherein the location of the connection point a is determined by the following equation:
x a =ρ t sinθ a； （4）
y a =r t +（1-cosθ a ）ρ t， （5）
whereinr t The ordinate of the throat, according to the gas jet flow rate required for pulverization by atomization, is generallyr t The value is 0.3-0.5mm,θ a an estimated design initial value is adopted, and the design is generally 30-40 degrees. In order to ensure that the gas jet velocity at the outlet of the circular seam spray pipe is uniform, the edge angle of the outlet is generally 0 degree. Radius of arc according to designρ t Can determinex a、 y a, And substituting the position coordinates of the outlet of the expansion section and the edge angle theta into the following equation e It is known that coefficients can be determined jointlya，bAndc。
y=a+bx+cx 2 （6）
tanθ a =b+2cx （7）
tanθ e =b+2cx （8）
thus, the initial profile structure of the expansion section is further determined.
Considering the influence of the boundary on the fluid, the profile of the supersonic expansion section of the circular seam nozzle is further corrected, and the wall coordinates are corrected mainly by adopting a viscous boundary layer correction theory. The viscous boundary layer correction theory is:
assuming that the boundary layer displacement thickness satisfies along with the linear development of the axis:
the environment pressure of the powder-making atomizing nozzle is atmospheric pressure, so the Mach number of the outlet isMa4 or less, final setting
。
d * (x) Boundary layer displacement thickness at point x;
arepresenting a linear correction angle;
| mach number of test section | 1.5~4 | 6 | 8 | 10 |
 |
0.5 | 0.7 | 1.5 | 2.0 |
According to the atomizing nozzle with the annular seam airflow channel profile structure designed by the technical scheme, argon is selected as atomizing gas, and GH3536 original powder D is prepared when the main injection pressure is 4MPa 50 =31mm, realizes printing in 3dThe powder forming rate of the printing section is up to 60%. Meanwhile, the prepared alloy powder has high sphericity and extremely low satellite powder rate.
Claims (6)
1. A method for designing a molded surface of a supersonic circumferential seam spray pipe for gas atomization powder preparation is characterized by comprising the following steps:
the molded surface of the supersonic annular seam spray pipe mainly comprises a subsonic annular seam contraction section and a supersonic annular seam expansion section, and the middle part of the supersonic annular seam spray pipe is limited by a throat part;
the molding surface of the subsonic annular seam contraction section is determined by adopting a bicubic curve;
the profile of the supersonic annular seam expansion section is determined by the circular arc section and the quadratic power function curve;
the size of each part of the supersonic annular seam spray pipe is determined by estimating the maximum Mach number of the supersonic expansion section outlet of the annular seam spray pipe.
2. The design method according to claim 1, wherein:
the estimation of the maximum Mach number of the outlet of the supersonic velocity expansion section of the circular seam nozzle specifically comprises the following steps,
firstly, the total pressure P of the inlet of the spray pipe is given 0 Ambient pressure and a preset mach number range, and iteratively estimating the maximum mach number corresponding to the outlet pressure P closest to the ambient pressure through equation (2)Ma max (ii) a Then, the estimated Mach number is calculatedMa max Substituting into equation (1), calculating area ratio A/A, and calculating the size of annular seam nozzle throat, supersonic expansion section outlet, subsonic contraction section inlet, and annular seam nozzle throat distance to the center of the flow guide pipe 1 The length L from the supersonic expansion section of the circular seam spray pipe to the center of the flow guide pipe 2 And calculating to obtain the outlet width of the circular seam spray pipe, and determining the position of the spray pipe and the coordinates of an outlet point.
In the formula, A is the cross section area of the outlet of the supersonic expansion section;
a is the cross-sectional area of the throat part of the circular seam jet pipe;
gamma is the specific heat ratio of the gas in the circular seam spray pipe;
Mathe gas mach number.
3. The design method according to claim 1, wherein:
the molding surface of the subsonic annular seam contraction section is determined by adopting a bicubic curve, and the control equation is as follows:
in the formulax m Is a front and back connection point of two curves;D i is an axial distance ofx0.5 < the cross-sectional diameter ofx m L < 0.6, D is the initial diameter, set between 3 and 10mm, wherexThe position of =0 is the starting point of the subsonic annular seam contraction section, and L is the length of the subsonic annular seam contraction section.
4. The design method according to claim 1, wherein:
the arc section is composed of arc half anglesθRadius ofρ t Determining, wherein,θthe initial value of the pre-estimated design is 15-45 degrees,ρ t the estimated design initial value is 5-20 mm.
5. The design method according to claim 4, wherein:
the second power function curve isy=a+bx+cx 2 Wherein coefficients are determineda，b，cFirst determining the connecting point A of the quadratic power function curve and the circular arc segmentPosition (x a ，y a ) Connecting angleθ a And exit edge angle θ e Wherein the location of the connection point a is determined by the following equation:
x a =ρ t sinθ a； （4）
y a =r t +（1-cosθ a ）ρ t， （5）
whereinr t The longitudinal coordinate of the throat part is that the value of the gas atomization powder preparation experiment is 0.3-0.5mm,θ a the pre-estimated design initial value is 30-40 degrees. In order to ensure uniform velocity of gas jet at the outlet of the circular seam spray pipe, the edge angle theta of the outlet e Typically at 0 ℃. Radius of arc according to designρ t Can determinex a、 y a, And substituting the position coordinates of the outlet of the expansion section and the edge angle theta into the following equation e It is known that coefficients can be determined jointlya，bAndc。
y=a+bx+cx 2 （6）
tanθ a =b+2cx （7）
tanθ e =b+2cx （8）
6. the design method according to claim 1, wherein:
correcting the molded surface of the supersonic annular seam expansion section by adopting a viscous boundary layer correction theory; the concrete requirements are as follows:
（9）
wherein d is * (x) The boundary layer displacement thickness at point x, typically α = 0.5.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210493767.7A CN114969627A (en) | 2022-05-08 | 2022-05-08 | Method for designing molded surface of supersonic circumferential seam spray pipe for gas atomization powder preparation |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210493767.7A CN114969627A (en) | 2022-05-08 | 2022-05-08 | Method for designing molded surface of supersonic circumferential seam spray pipe for gas atomization powder preparation |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114969627A true CN114969627A (en) | 2022-08-30 |
Family
ID=82980917
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210493767.7A Pending CN114969627A (en) | 2022-05-08 | 2022-05-08 | Method for designing molded surface of supersonic circumferential seam spray pipe for gas atomization powder preparation |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114969627A (en) |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108421649A (en) * | 2018-02-27 | 2018-08-21 | 辽宁科技大学 | A kind of rectangle superonic flow nozzzle and its design method |
| JP2019084523A (en) * | 2017-11-10 | 2019-06-06 | 福岡県 | Jet nozzle and jet method |
| CN110899713A (en) * | 2019-12-20 | 2020-03-24 | 北京机科国创轻量化科学研究院有限公司 | Novel close coupling gas atomizing nozzle |
-
2022
- 2022-05-08 CN CN202210493767.7A patent/CN114969627A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2019084523A (en) * | 2017-11-10 | 2019-06-06 | 福岡県 | Jet nozzle and jet method |
| CN108421649A (en) * | 2018-02-27 | 2018-08-21 | 辽宁科技大学 | A kind of rectangle superonic flow nozzzle and its design method |
| CN110899713A (en) * | 2019-12-20 | 2020-03-24 | 北京机科国创轻量化科学研究院有限公司 | Novel close coupling gas atomizing nozzle |
Non-Patent Citations (2)
| Title |
|---|
| 刘文广等: "收缩段线型对超音速喷管氟原子气相复合的影响", 《力学学报》, vol. 38, no. 3, 30 May 2006 (2006-05-30), pages 392 - 397 * |
| 荆卓寅;赵俭;李海燕;: "超音速校准风洞中的喷管设计", 计测技术, no. 05, 28 October 2016 (2016-10-28), pages 21 - 25 * |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102323961B (en) | Asymmetric supersonic velocity spray pipe and design method thereof | |
| CN102218378B (en) | Ultrasonic nonuniform flow nozzle and design method thereof | |
| CN103150423B (en) | Rotational symmetry becomes Mach number nozzle and wall defining method thereof continuously | |
| CN109927917B (en) | Integrated design method for internal rotation type wave-rider forebody air inlet channel of supersonic aircraft | |
| CN108182319B (en) | Supersonic velocity integrated spray pipe design method | |
| CN108019279B (en) | Design method of hypersonic air inlet channel | |
| CN108421649B (en) | Rectangular supersonic nozzle and design method thereof | |
| CN112035952B (en) | Design method of ejector nozzle experimental device for simulating outflow of aircraft | |
| CN102302989B (en) | Supersonic velocity spray pipe with shared throat part and design method of supersonic velocity spray pipe | |
| CN107091159B (en) | The design method of the adjustable Supersonic Inlet of axial symmetry based on flexible central body | |
| CN108563896A (en) | A kind of expansion segment method for designing profile improving rocket tube performance | |
| CN114112286B (en) | Hypersonic wind tunnel axisymmetric profile spray pipe fitting throat section design method | |
| CN110633522A (en) | Supersonic thrust nozzle reverse design method based on maximum thrust theory | |
| CN114969627A (en) | Method for designing molded surface of supersonic circumferential seam spray pipe for gas atomization powder preparation | |
| CN103678774A (en) | Designing method for supersonic velocity thrust exhaust nozzle considering inlet parameter unevenness | |
| CN114861121A (en) | Method for optimizing profile of supersonic circumferential seam spray pipe for gas atomization powder preparation | |
| CN109815564B (en) | Reverse design method of supersonic thrust nozzle capable of simulating outlet pneumatic parameter distribution and determining outlet shape | |
| CN110059410B (en) | Belly air intake hypersonic precursor optimization design method based on B spline | |
| CN117329147A (en) | Impeller integrated structure and design method thereof | |
| CN108280264B (en) | Design method of transonic velocity spray pipe | |
| CN109977513B (en) | Suction surface three-arc blade molding method for fan and gas compressor | |
| CN109711047B (en) | Design method for aerodynamic performance of S2 flow surface of helium compressor | |
| CN113076610A (en) | Design method of binary adjustable air inlet channel | |
| CN207840127U (en) | A kind of air intake duct for SLM device working chamber | |
| CN109670232B (en) | Method for rapidly estimating size and weight of attitude control bipropellant thrust chamber |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |