CN113032893A - Design method of ejector nozzle device for simulating subsonic/transonic outflow - Google Patents
Design method of ejector nozzle device for simulating subsonic/transonic outflow Download PDFInfo
- Publication number
- CN113032893A CN113032893A CN202110197089.5A CN202110197089A CN113032893A CN 113032893 A CN113032893 A CN 113032893A CN 202110197089 A CN202110197089 A CN 202110197089A CN 113032893 A CN113032893 A CN 113032893A
- Authority
- CN
- China
- Prior art keywords
- flow
- spray pipe
- tertiary
- nozzle
- section
- 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.)
- Granted
Links
- 238000000034 method Methods 0.000 title claims abstract description 21
- 238000013461 design Methods 0.000 title claims abstract description 13
- 239000007921 spray Substances 0.000 claims description 87
- 238000002347 injection Methods 0.000 claims description 13
- 239000007924 injection Substances 0.000 claims description 13
- 238000004364 calculation method Methods 0.000 claims description 7
- 238000004401 flow injection analysis Methods 0.000 claims description 6
- 238000004088 simulation Methods 0.000 claims description 5
- 238000011144 upstream manufacturing Methods 0.000 claims description 4
- 230000002035 prolonged effect Effects 0.000 claims description 2
- 238000005507 spraying Methods 0.000 claims description 2
- 238000012360 testing method Methods 0.000 abstract description 9
- 230000003068 static effect Effects 0.000 abstract description 5
- 230000008878 coupling Effects 0.000 abstract description 2
- 238000010168 coupling process Methods 0.000 abstract description 2
- 238000005859 coupling reaction Methods 0.000 abstract description 2
- 230000000694 effects Effects 0.000 abstract 1
- 239000003570 air Substances 0.000 description 55
- 238000011160 research Methods 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 230000008602 contraction Effects 0.000 description 2
- 238000001816 cooling Methods 0.000 description 2
- 239000012080 ambient air Substances 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 239000000839 emulsion Substances 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 230000005477 standard model Effects 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
Images
Classifications
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/15—Vehicle, aircraft or watercraft design
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/28—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto using fluid jets to influence the jet flow
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
- G06F30/28—Design optimisation, verification or simulation using fluid dynamics, e.g. using Navier-Stokes equations or computational fluid dynamics [CFD]
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2113/00—Details relating to the application field
- G06F2113/08—Fluids
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2113/00—Details relating to the application field
- G06F2113/14—Pipes
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
- G06F2119/14—Force analysis or force optimisation, e.g. static or dynamic forces
-
- 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)
- Theoretical Computer Science (AREA)
- Geometry (AREA)
- General Physics & Mathematics (AREA)
- General Engineering & Computer Science (AREA)
- Evolutionary Computation (AREA)
- Mathematical Analysis (AREA)
- Mathematical Optimization (AREA)
- Pure & Applied Mathematics (AREA)
- Computer Hardware Design (AREA)
- Computational Mathematics (AREA)
- Aviation & Aerospace Engineering (AREA)
- Automation & Control Theory (AREA)
- Algebra (AREA)
- Computing Systems (AREA)
- Fluid Mechanics (AREA)
- Mathematical Physics (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- Jet Pumps And Other Pumps (AREA)
Abstract
The invention discloses a design method of a jet nozzle device for simulating subsonic/transonic outflow, which is characterized in that the flow field in a jet nozzle in an actual flight state is solved, the flow of a third flow path is simplified and equivalent to the flow direction being consistent and the jet coefficients being equal, and an actual flow line is used as the inner surface of an outlet of a ground experimental device of the jet nozzle so as to simulate the binding effect of the actual aircraft rear outflow on the outlet flow of the jet nozzle. The method can realize that the tertiary flow, the in-pipe flow and the flow near the outlet of the ejector nozzle are similar to the real flight state flow under the condition of static ground outflow, and provides a feasible experimental device design method for developing the ground test of the three-flow-path ejector nozzle with subsonic/transonic outflow and disclosing the coupling mechanism of the internal flow and the external flow of the ejector nozzle.
Description
Technical Field
The invention relates to the field of aircraft aerodynamic experiments, in particular to a design method of a jet nozzle device capable of simulating subsonic/transonic outflow.
Background
Since the development of turbojet engines, the ever increasing combustion temperatures and the advent of afterburners have led to the need for efficient cooling of the turbojet exhaust nozzle, where ejectors have been used for cooling the turbojet exhaust nozzle. Hydrodynamic mixing is the primary mode of momentum transfer in an eductor and dominates its ejection phenomenon. The degree of turbulent mixing of the two streams determines the ejector performance, and this mixing occurs in the free shear layer, and most of the performance characteristics of an ejector are generally deduced from the behavior of the associated free shear layer and its relationship to the shoulder wall. Based on the research on the mechanism and the flow field structure of the ejector, students develop a large amount of parameter researches on the ejector nozzle, wherein the parameter researches comprise a pneumatic parameter rule, a geometric parameter rule, the structural design of the ejector nozzle, thrust parameter calculation and the like.
As mentioned in Exhaust nozzles for propulsion systems with emulsion on super sonic nozzle airflows, the ejector nozzle comprises two types: the first type is called auxiliary air inlet ejector jet pipe, which involves opening an auxiliary inlet valve and introducing external air into a cavity connected with an expansion type jet pipe; the second category, called variable jet nozzles, adjusts the flow characteristics within the nozzle by controlling the secondary flow path area and the mixing section angle, with a variable flap hinged on the upstream side. The ejector of a tandem aircraft is also used to regulate the exhaust flow at subsonic conditions and to generate reverse thrust during landing. The OL 593 ejector nozzle trailing edge angle has a large adjustment margin, and this angular difference has a significant impact on the additional drag and internal separation. The research in the prior art mainly focuses on the mechanism of the performance and the flow characteristic of the ejector nozzle, and no design method for ensuring that the internal flow field of the ejector nozzle is similar to the real internal flow field in a ground test is available.
Disclosure of Invention
The purpose of the invention is as follows: aiming at the defects, the invention provides a design method of a jet nozzle device for simulating subsonic/transonic outflow, which can realize that an experimental device can accurately simulate a jet nozzle flow field of subsonic/transonic outflow under the condition of static ground outflow and ensure that the internal flow field of the jet nozzle in a ground test is similar to the real internal flow field.
The technical scheme is as follows: in order to solve the problems, the invention adopts a design method of a jet nozzle device for simulating subsonic/transonic outflow, which comprises the following steps:
(1) providing an actual three-flow path jet nozzle flow field as a reference flow field under a sub/transonic outflow condition, and providing a jet nozzle experimental device which comprises a circular main jet pipe section, a secondary flow jet pipe section surrounding the main jet pipe section and a tertiary flow jet pipe section surrounding the secondary flow jet pipe section; the secondary flow spray pipe section comprises a secondary flow spray pipe air inlet and a secondary flow spray pipe main body; the tertiary flow spray pipe section comprises a tertiary flow spray pipe air inlet, a tertiary flow spray pipe air outlet, a tertiary flow spray pipe main body connected with the tertiary flow spray pipe air inlet and the tertiary flow spray pipe air outlet, and a tertiary flow spray pipe expansion section connected with the rear end of the tertiary flow spray pipe air outlet;
(2) calculating flow field parameters in a reference flow field, and determining inlet flow conditions of a main flow, a secondary flow and a tertiary flow in the reference flow field;
(3) enabling the injection nozzle experimental device to be consistent with the flow field parameters in the step (2), and determining the scaling of the injection nozzle experimental device;
(4) according to the pressure drop ratio of the secondary flow not exceeding 1.0, a secondary flow spraying pipe section is arranged to directly supply air from the environment;
(5) determining the molded line of the air inlet of the secondary flow spray pipe, and determining the equation as (x)1 2+r2)2＝2a2(x1 2-r2) Wherein x is1The coordinate of the flow direction of each point on the air inlet of the secondary flow spray pipe; r is the radial coordinate of each point on the air inlet of the secondary flow spray pipe, and a is a constant;
(6) determining the molded surface of the air inlet pipeline of the tertiary flow spray pipe, and determining an equation:
wherein R is the radius of a circular pipeline at the air inlet section of the tertiary flow spray pipe, R1The radius of the inlet of the air inlet section of the tertiary flow spray pipe is; r is2The radius of an outlet of an air inlet section of the tertiary flow spray pipe is shown, x is a flow direction coordinate of each point of the air inlet of the tertiary flow spray pipe, and L is the length of the air inlet section of the tertiary flow spray pipe;
(7) determining the molded line of the upper wall surface of the expansion section of the tertiary flow spray pipe of the experimental device according to the expansion velocity vector direction of the tertiary flow in the reference flow field and the upstream tracking streamline of the expansion section of the tertiary flow spray pipe;
(8) according to the downstream tracing streamline of the tertiary flow in the reference flow field, the streamline traced by the tail edge of the expansion section of the tertiary flow spray pipe is cut off, and the expansion section of the tertiary flow spray pipe is prolonged according to the trend of the streamline to obtain the tail edge point of the expansion section of the tertiary flow spray pipe of the experimental device;
(9) and (4) determining other molded surfaces of the injection nozzle experimental device according to the scaling conditions in the step (3).
Has the advantages that: compared with the prior art, the experimental device has the obvious advantages that the experimental device can accurately simulate the flow field of the integrated ejector jet pipe with the sub/transonic outflow under the condition of the static outflow of the ground by tracking the streamline of the sub/transonic outflow reference flow field, designing the air inlet structure of the three flow paths of the experimental device and adjusting the equivalent expansion ratio of the expansion section of the tertiary flow nozzle, and the internal flow field of the ejector jet pipe in the ground test is similar to the real internal flow field.
Further, the flow conditions in the step (2) include the pressure drop ratio and the flow rate of the main flow, the secondary flow and the tertiary flow.
Further, the flow field parameters in the step (3) include a main nozzle section pressure drop ratio, a secondary flow injection coefficient and a tertiary flow injection coefficient.
Furthermore, an annular plate in contact with the outer surface of the main nozzle section is arranged between the air inlet of the secondary flow nozzle and the main body of the secondary flow nozzle, the plane where the annular plate is located is parallel to the cross section of the main nozzle section, a plurality of round holes are formed in the annular plate, and in the step (4), the pressure drop ratio of the secondary flow is adjusted by adjusting the porosity of the annular plate.
Furthermore, an annular inlet is arranged at an inlet of the air inlet section of the tertiary flow spray pipe, circular air inlets are uniformly distributed on the annular inlet along the circumferential direction, and the porosity of the annular inlet is not lower than 30%.
Further, the method for designing the ejector nozzle device according to claim 1, wherein the expansion ratio of the tertiary flow nozzle expansion section of the ejector nozzle experimental device is smaller than the reference flow field, the reduction degree of the expansion ratio is determined by numerical simulation, and the expansion ratio of the tertiary flow nozzle expansion section of the ejector nozzle experimental device is obtained through iterative calculation to be 1.125.
Drawings
FIG. 1 is a prior/experimental physical simulation model of a subsonic/transonic outflow three-flow-path ejector nozzle in the present invention;
FIG. 2 is a schematic view of the structure of the annular plate of the present invention;
FIG. 3 is a flow diagram of a sub/transonic outflow three-flow path pilot nozzle flow field configuration of the present invention;
FIG. 4 is a comparison diagram of the flow field structure of the nozzle pipe and the flow field structure of the original nozzle pipe of the experimental simulation model of the invention.
Detailed Description
As shown in fig. 1 to 4, in the design method of the ejector nozzle device for simulating the subsonic/transonic outflow according to the present invention, the actual working condition of the three-flow-path ejector nozzle for the subsonic/transonic outflow is that the incoming flow mach number is 1.2, the ambient air pressure is 30800Pa, and the temperature is 229.73K. The method for designing the Mach number of incoming flow of a ground static test is 0, the ambient pressure is 40000Pa, and the temperature is 300K, and the method comprises the following steps:
(1) providing an actual three-flow-path jet nozzle flow field as a reference flow field under a sub/transonic outflow condition, and providing a jet nozzle experimental device, wherein the experimental device comprises a circular main nozzle section 1, a secondary flow jet pipe section 2 surrounding the main nozzle section, and a tertiary flow jet pipe section 3 surrounding the secondary flow jet pipe section, as shown in fig. 1; the secondary flow spray pipe section 2 comprises a secondary flow spray pipe air inlet 21 and a secondary flow spray pipe main body 22 connected to the rear end of the secondary flow spray pipe air inlet 21 along the air flow direction, a circular ring plate 9 in surface contact with the outer surface of the main spray pipe section is arranged between the secondary flow spray pipe air inlet 21 and the secondary flow spray pipe main body 22, the plane where the circular ring plate 9 is located is parallel to the cross section of the main spray pipe section 1, and the secondary flow spray pipe air inlet 21 is a contraction pipeline with a lip. As shown in fig. 2, the circular plate 9 is provided with a plurality of circular holes along the circumference. The tertiary flow spray pipe section 3 comprises a tertiary flow spray pipe air inlet 31, a tertiary flow spray pipe air outlet 33, a tertiary flow spray pipe main body 32 connected with the tertiary flow spray pipe air inlet 31 and the tertiary flow spray pipe air outlet 33, an annular inlet 5 arranged at the inlet of the tertiary flow spray pipe air inlet 31, and a tertiary flow spray pipe expansion section 34 connected with the tertiary flow spray pipe air outlet 33 at the rear end along the air flow direction, wherein circular air inlets are uniformly arranged at the annular inlet 5 along the circumferential direction, so that the uniformity of tertiary flow air inlet is ensured, the porosity of the annular inlet 5 is not lower than 30%, and the throat choking phenomenon is avoided; the air outlet 33 of the tertiary flow spray pipe is an inclined expansion pipeline, and the tertiary flow passes through the air outlet 33 of the tertiary flow spray pipe and then is mixed with the secondary flow; the connecting intersection point of the tertiary flow spray pipe air outlet 33 and the tertiary flow spray pipe expansion section 34 is a tertiary flow inlet point 6;
(2) calculating flow field parameters in a reference flow field, and determining inlet flow conditions of a main flow, a secondary flow and a tertiary flow in the reference flow field according to the calculation result of the reference flow field, wherein the inlet flow conditions comprise parameters such as pressure drop ratios and flow rates of the main flow, the secondary flow and the tertiary flow; according to the actual cabin pressure, the flow rates of the main flow, the secondary flow and the tertiary flow are determined, and as shown in fig. 3, the structure streamline of the jet pipe flow field is guided by the three flow paths with the sub/transonic outflow.
(3) According to the calculation result of the reference flow field and the conditions of the test bed, ensuring that the drop pressure ratio, the secondary flow injection coefficient and the tertiary flow injection coefficient of the injection nozzle experimental device are consistent with those of the main nozzle section 1 of the flow field parameters in the step (2), and determining the scaling of the injection nozzle experimental device; the actual main flow pressure drop ratio in the reference flow field is 5.36, and the temperature is 1900K. Designing the main flow pressure drop ratio of the experimental device to be 5.36, setting the temperature to be 300K, considering the parameters such as the initial flow, the initial pressure and the throat area of the main flow, the secondary flow and the tertiary flow, and finally determining the nozzle shrinkage ratio between the experimental device and the actual reference flow field to be 1 through repeated iterative calculation: 2.
(4) according to the fact that the pressure drop ratio of the secondary flow is not more than 1.0 and the reference flow field of the injection spray pipe, the actual pressure drop ratio of the secondary flow is 1.03 and is basically close to the environmental pressure, the secondary flow spray pipe section 2 is arranged to supply air directly from the environment, the pressure drop ratio of the secondary flow can be adjusted by adjusting the porosity of the annular plate 9, and the relation between the porosity of the annular plate 9 and the pressure drop ratio of the secondary flow is determined through a standard model test;
(5) determining the molded line of the air inlet of the secondary flow spray pipe, and determining the molded line of the air inlet of the secondary flow spray pipe to ensure that the secondary flow smoothly enters air according to the equation (x)1 2+r2)2＝2a2(x1 2-r2) Wherein x is1The coordinate of the flow direction of each point on the air inlet of the secondary flow spray pipe; r is the radial coordinate of each point on the air inlet of the secondary flow spray pipe, and a is a constant;
(6) determining the pipeline profile of the air inlet of the tertiary flow spray pipe, supplying air by adopting high pressure at the section of the tertiary flow spray pipe, and setting the actual tertiary flow pressure drop ratio in the reference flow field to be 1.70, then setting the tertiary flow pressure drop ratio of the experimental device to be 1.70, injecting air through the annular inlet 5, and in order to reduce the problems of uneven airflow, high turbulence intensity and the like caused by porous air inlet, the air inlet of the tertiary flow spray pipe adopts a contraction pipeline, and the determination equation of the pipeline profile is as follows:
wherein R is the radius of a circular pipeline at the air inlet section of the tertiary flow spray pipe, R1For three times of air flowA mouth section entrance radius; r is2The radius of an outlet of an air inlet section of the tertiary flow spray pipe is shown, x is a flow direction coordinate of each point of the air inlet of the tertiary flow spray pipe, and L is the length of the air inlet section of the tertiary flow spray pipe;
(7) in order to ensure that the tertiary flow of the experimental device in the test state is similar to that in the real flight state and the tertiary flow velocity vector direction of the expansion section of the tertiary flow nozzle of the experimental device is consistent with the real state in the reference flow field, the streamline is traced upstream from the tertiary flow inlet point 6 in the reference flow field to determine the upper wall molded line of the expansion section of the tertiary flow nozzle of the experimental device; in the experimental state, the flow direction of the gas of the third flow path of the injection spray pipe is consistent with the real state, and the flow field of the tertiary flow can be simulated correctly.
(8) In order to ensure that the flow near the outlet of the injection nozzle of the experimental device is similar to the reference flow field, the flow line traced by the tail edge of the expansion section of the tertiary flow nozzle of the reference flow field is cut off according to the downstream tracing flow line of the tail edge point 7 in the reference flow field, and the tail edge point 8 of the expansion section of the tertiary flow nozzle of the experimental device is obtained by prolonging the expansion section of the tertiary flow nozzle according to the flow line trend; in order to ensure that the external flow field of the outlet of the ejector nozzle in the shrinkage ratio experimental device is similar to the real state, the expansion ratio of the expansion section of the tertiary flow nozzle of the ejector nozzle experimental device is smaller than the reference flow field, the reduction degree of the expansion ratio is determined through numerical simulation, and the expansion ratio of the expansion section of the tertiary flow nozzle of the ejector nozzle experimental device is 1.125 through iterative calculation.
(9) And (4) determining other molded surfaces of the injection nozzle experimental device according to the scaling conditions in the step (3). As shown in fig. 4, which is a comparison diagram of a flow field of an experimental device of a jet nozzle and a flow field of an original nozzle under the condition of subsonic/transonic outflow, it can be seen that the experimental device of the jet nozzle designed based on the method of the present invention can realize that three-time flow, in-pipe flow and flow near an outlet of the jet nozzle are similar to real flight state flow under the condition of static outflow on the ground, and a feasible design method of the experimental device is provided for developing a ground test of the three-flow path jet nozzle with subsonic/transonic outflow and disclosing a coupling mechanism of internal and external flows of the jet nozzle.
Claims (6)
1. A design method of a jet nozzle device for simulating subsonic/transonic outflow is characterized by comprising the following steps:
(1) providing an actual three-flow path jet nozzle flow field as a reference flow field under a sub/transonic outflow condition, and providing a jet nozzle experimental device which comprises a circular main jet pipe section, a secondary flow jet pipe section surrounding the main jet pipe section and a tertiary flow jet pipe section surrounding the secondary flow jet pipe section; the secondary flow spray pipe section comprises a secondary flow spray pipe air inlet and a secondary flow spray pipe main body; the tertiary flow spray pipe section comprises a tertiary flow spray pipe air inlet, a tertiary flow spray pipe air outlet, a tertiary flow spray pipe main body connected with the tertiary flow spray pipe air inlet and the tertiary flow spray pipe air outlet, and a tertiary flow spray pipe expansion section connected with the rear end of the tertiary flow spray pipe air outlet;
(2) calculating flow field parameters in a reference flow field, and determining inlet flow conditions of a main flow, a secondary flow and a tertiary flow in the reference flow field;
(3) enabling the injection nozzle experimental device to be consistent with the flow field parameters in the step (2), and determining the scaling of the injection nozzle experimental device;
(4) according to the pressure drop ratio of the secondary flow not exceeding 1.0, a secondary flow spraying pipe section is arranged to directly supply air from the environment;
(5) determining the molded line of the air inlet of the secondary flow spray pipe, and determining the equation as (x)1 2+r2)2＝2a2(x1 2-r2) Wherein x is1The coordinate of the flow direction of each point on the air inlet of the secondary flow spray pipe; r is the radial coordinate of each point on the air inlet of the secondary flow spray pipe, and a is a constant;
(6) determining the molded surface of the air inlet pipeline of the tertiary flow spray pipe, and determining an equation:
wherein R is the radius of a circular pipeline at the air inlet section of the tertiary flow spray pipe, R1The radius of the inlet of the air inlet section of the tertiary flow spray pipe is; r is2Is the radius of the outlet of the air inlet section of the tertiary flow spray pipe, x is the flow direction coordinate of each point of the air inlet of the tertiary flow spray pipe, and L is the length of the air inlet section of the tertiary flow spray pipeDegree;
(7) determining the molded line of the upper wall surface of the expansion section of the tertiary flow spray pipe of the experimental device according to the expansion velocity vector direction of the tertiary flow in the reference flow field and the upstream tracking streamline of the expansion section of the tertiary flow spray pipe;
(8) according to the downstream tracing streamline of the tertiary flow in the reference flow field, the streamline traced by the tail edge of the expansion section of the tertiary flow spray pipe is cut off, and the expansion section of the tertiary flow spray pipe is prolonged according to the trend of the streamline to obtain the tail edge point of the expansion section of the tertiary flow spray pipe of the experimental device;
(9) and (4) determining other molded surfaces of the injection nozzle experimental device according to the scaling conditions in the step (3).
2. The method of designing a pilot nozzle arrangement according to claim 1, wherein the inlet flow conditions in step (2) include pressure drop ratios and flow rates of the primary flow, the secondary flow, and the tertiary flow.
3. The method of designing a pilot nozzle unit according to claim 1, wherein the flow field parameters in step (3) include a main nozzle section pressure drop ratio, a secondary flow injection coefficient, and a tertiary flow injection coefficient.
4. The method for designing the ejector nozzle device according to claim 1, wherein an annular plate in contact with the outer surface of the main nozzle section is arranged between the air inlet of the secondary flow nozzle and the main body of the secondary flow nozzle, the plane of the annular plate is parallel to the cross section of the main nozzle section, a plurality of circular holes are arranged on the annular plate, and in the step (4), the pressure drop ratio of the secondary flow is adjusted by adjusting the porosity of the annular plate.
5. The design method of the injection nozzle device according to claim 4, wherein an annular inlet is arranged at the inlet of the air inlet section of the tertiary flow nozzle, circular air inlets are uniformly arranged on the annular inlet along the circumferential direction, and the porosity of the annular inlet is not lower than 30%.
6. The method for designing the ejector nozzle device according to claim 1, wherein the expansion ratio of the tertiary flow nozzle expansion section of the ejector nozzle experimental device is smaller than the reference flow field, the reduction degree of the expansion ratio is determined by numerical simulation, and the expansion ratio of the tertiary flow nozzle expansion section of the ejector nozzle experimental device is 1.125 through iterative calculation.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110197089.5A CN113032893B (en) | 2021-02-22 | 2021-02-22 | Design method of jet nozzle device for simulating sub/transonic outflow |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110197089.5A CN113032893B (en) | 2021-02-22 | 2021-02-22 | Design method of jet nozzle device for simulating sub/transonic outflow |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113032893A true CN113032893A (en) | 2021-06-25 |
| CN113032893B CN113032893B (en) | 2024-03-29 |
Family
ID=76461152
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110197089.5A Active CN113032893B (en) | 2021-02-22 | 2021-02-22 | Design method of jet nozzle device for simulating sub/transonic outflow |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113032893B (en) |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111042949A (en) * | 2019-11-19 | 2020-04-21 | 南京航空航天大学 | Wide-speed-range injection spray pipe integrated with aircraft and design method |
| CN112035952A (en) * | 2020-08-21 | 2020-12-04 | 南京航空航天大学 | Design method of ejector nozzle experimental device for simulating outflow of aircraft |
-
2021
- 2021-02-22 CN CN202110197089.5A patent/CN113032893B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111042949A (en) * | 2019-11-19 | 2020-04-21 | 南京航空航天大学 | Wide-speed-range injection spray pipe integrated with aircraft and design method |
| CN112035952A (en) * | 2020-08-21 | 2020-12-04 | 南京航空航天大学 | Design method of ejector nozzle experimental device for simulating outflow of aircraft |
Non-Patent Citations (2)
| Title |
|---|
| 蔡佳: "宽速域引射喷管巡航状态流动特性仿真", 火箭推进, vol. 46, no. 6, 15 December 2020 (2020-12-15), pages 22 - 29 * |
| 黄河峡: "带第三流路辅助进气的引射喷管流动特性研究", 推进技术, vol. 41, no. 12, 11 August 2020 (2020-08-11), pages 2729 - 2738 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN113032893B (en) | 2024-03-29 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108168832B (en) | A kind of throat structure improving tube wind tunnel test Reynolds number | |
| Deere et al. | Computational study of fluidic thrust vectoring using separation control in a nozzle | |
| CN109918839B (en) | Modeling method and infrared radiation prediction method for turbofan engine with pilot nozzle | |
| Flamm et al. | Experimental study of an axisymmetric dual throat fluidic thrust vectoring nozzle for supersonic aircraft application | |
| Gorton et al. | Active flow control on a boundary-layer-ingesting inlet | |
| Ran et al. | Preliminary design of a 2D supersonic inlet to maximize total pressure recovery | |
| US8800259B2 (en) | Thrust vector system | |
| CN103149009B (en) | Supersonic speed distance piece flow tunnel testing device | |
| CN112035952B (en) | Design method of ejector nozzle experimental device for simulating outflow of aircraft | |
| GB1182504A (en) | Jet Propulsion Nozzle | |
| Berrier et al. | Experimental and computational evaluation of flush-mounted, S-duct inlets | |
| CN104807610A (en) | Sprayer nozzle used for tail jet flow interference test | |
| CN112240831B (en) | Design method of aero-engine intake temperature distortion generator | |
| Park et al. | Low-order model for buzz oscillations in the intake of a ramjet engine | |
| US9546618B2 (en) | Methods and apparatus for passive thrust vectoring and plume deflection | |
| US4567960A (en) | Fixed geometry controlled entrainment ventilated convergent nozzle and method | |
| CN113032893B (en) | Design method of jet nozzle device for simulating sub/transonic outflow | |
| CN111523201A (en) | Internal and external flow field coupling iterative calculation method in engine reverse thrust state | |
| CN112179605B (en) | Ejector nozzle experimental device for simulating outflow of aircraft | |
| CN114942116B (en) | Method for simulating supersonic flow field of front fuselage of aircraft with layout of air inlet channel under abdomen | |
| CN113062816B (en) | Injection nozzle device for simulating subsonic/transonic outflow | |
| Hromisin et al. | Nozzle Length and Aft Deck Effects on the Aeroacoustics of Dual Stream Supersonic Jets | |
| Wang et al. | Pressure distribution measurements in scramjet isolators under asymmetric supersonic flow | |
| Hromisin et al. | Aeroacoustic and Flow Field Characterization of Dual Stream Rectangular Supersonic Jets | |
| Burrows et al. | Controlled Flow Dynamics in a Serpentine Diffuser with a Cowl Inlet |
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 | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |