CN109356723B - Closed return flow line flow field control method - Google Patents
Closed return flow line flow field control method Download PDFInfo
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- CN109356723B CN109356723B CN201811427187.8A CN201811427187A CN109356723B CN 109356723 B CN109356723 B CN 109356723B CN 201811427187 A CN201811427187 A CN 201811427187A CN 109356723 B CN109356723 B CN 109356723B
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- intake duct
- air intake
- flow line
- return flow
- hypersonic
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/042—Air intakes for gas-turbine plants or jet-propulsion plants having variable geometry
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/057—Control or regulation
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
- F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
- F02K7/14—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines with external combustion, e.g. scram-jet engines
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- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/81—Modelling or simulation
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- 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
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Mechanical Engineering (AREA)
- Geometry (AREA)
- Theoretical Computer Science (AREA)
- Computer Hardware Design (AREA)
- Evolutionary Computation (AREA)
- General Physics & Mathematics (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The present invention relates to a kind of closed return flow line flow field control methods, which comprises the following steps: a. is required according to design parameter, designs hypersonic inlet geometry profile, sunykatuib analysis air intake duct self-starting characteristic；Static pressure distribution different in compressing surface before import rule, using the Pressure difference distribution after shock wave front, back cavity is opened up inside air intake duct and is controlled air intake duct flow field when b. based on hypersonic intake duct starting/non-starting；C. simulation analysis return flow line entrance location, outlet port and the back cavity cross section parameter, optimize the geometry profile parameter of the return flow line；D. return flow line geometry profile parameter is adjusted, determines final inlet structure.Closed return flow line flow field control method according to the present invention can improve the starting capability under hypersonic inlet low mach, widen air intake duct work range of Mach numbers.
Description
Technical field
The present invention relates to hypersonic aircraft air inlet system and exhaust system design field more particularly to a kind of closed return flow lines
Flow field control method widens air intake duct work Mach for improving the starting capability under hypersonic inlet low mach
Number range.
Background technique
As various countries are (long-range fast to informationization operation (communication, monitoring, scouting, information, electronic warfare) and three-dimensional system attacking and defending
Fast efficiently strike platform, the reusable platform of high speed, the relaying platform for passing in and out space) demand it is growing day by day, development closes on
Space hypersonic aircraft technology becomes ever more important.The U.S., Russia, European Countries all put into a large amount of funds to closing on sky
Between hypersonic aircraft technology research in.Hypersonic aircraft technology mainly includes overall design technique, aerodynamic force/heat
Thermal protection technology, high-precision GNC technology and engine technology etc. when technology, high temperature are long.
Currently, various countries mainly select scramjet engine as the dynamical system of hypersonic aircraft, ultra-combustion ramjet
Engine has bigger safety, economy and flexibility compared with rocket engine, and can carry more effectively loads
Lotus.Scramjet engine is mainly made of air intake duct, combustion chamber and jet pipe three parts.Air intake duct is as punching engine
Important component carries the task of capture, the free incoming flow of compression, the air-flow of enough high-quality is provided for combustion chamber, to guarantee
Stable burning in combustion chamber.For using airbreathing motor as the hypersonic aircraft of power, the design of air-inlet system
It is most important.If air intake duct is high-efficient, the payload of aircraft can be significantly improved, is flown if inlet efficiency is low
The resistance balance that pushes away of device all may be difficult to achieve.Therefore, high performance air intake duct to the efficient operation of scramjet engine or even
The entire stable flight of aircraft security has conclusive effect.
Intake duct starting/inoperative is the important flow phenomenon of hypersonic airbreathing motor.Hypersonic inlet
It is inoperative to be mainly characterized by occurring intense shock wave system near import, so that normal hypersonic flow can not be organized in air intake duct
Dynamic, the traffic capture of air intake duct, total pressure recovery sharply decline at this time, and flow field quality degenerates.
In order to widen the working range of air intake duct, domestic and foreign scholars have carried out more research.Current measure mainly includes
Following two: the first scheme is that the geometry profile of air intake duct is adjusted according to different inlet flow conditions using geometry air intake duct is become
(such as rotation lip), makes air intake duct be in optimum Working always, so that the starting performance of air intake duct be made to significantly improve, but becomes
Structural change amplitude is big during the work time for geometry air intake duct, and structure is complicated, therefore there are a series of controls and sealing problems；
Second scheme is to utilize the passive flow field control method (such as overflow launder, suction hole) of pressure difference between inlet and outlet, this scheme energy
Effectively eliminate air intake duct it is inoperative when separation packet lead to motor power decline, aircraft resistance but there are biggish flow loss
Power increases.
Summary of the invention
The purpose of the present invention is to solve the above problem, and providing one kind can improve under hypersonic inlet low mach
Starting capability, widen air intake duct work range of Mach numbers closed return flow line flow field control method.
For achieving the above object, the present invention provides a kind of closed return flow line flow field control method, including following
Step:
A. joined according to the designs such as hypersonic aircraft cruise Mach number Ma and height H and air intake duct leading edge compression angle δ
Number requires, and designs hypersonic inlet geometry profile, sunykatuib analysis air intake duct self-starting characteristic；
Static pressure distribution different in compressing surface before import rule when b. based on hypersonic intake duct starting/non-starting, benefit
With the Pressure difference distribution after shock wave front, back cavity is opened up inside air intake duct, air intake duct flow field is controlled；
C. simulation analysis return flow line entrance location, outlet port and the back cavity cross section parameter, optimization is described to return
The geometry profile parameter of circulation road；
D. return flow line geometry profile parameter is adjusted, determines final inlet structure.
According to an aspect of the present invention, in a step, monitor the critical inoperative Mach number of air intake duct, analyze into
Pressure distribution after separating zone position, and induction shock wave front when air flue is inoperative.
According to an aspect of the present invention, when hypersonic inlet is inoperative, the static pressure after induction shock wave front is utilized
Difference draws the low energy stream in Disengagement zone.
According to an aspect of the present invention, in the Step d, there is particular cross section cavity based on what simulation analysis obtained
Air intake duct model, design hypersonic inlet testpieces, formulate wind tunnel test scheme simultaneously carry out the wind-tunnel under typicalness
Verification experimental verification is adjusted return flow line geometric parameter, and determines final inlet structure.
Closed return flow line flow field control method according to the present invention, effectively improves the starting characteristic of air intake duct,
The Start mach number for namely reducing air intake duct, improves the self-starting ability of air intake duct, extends the work of hypersonic inlet
Make range, operates normally it in wide range of Mach numbers.And the present invention is controlled by flow field that is simple and effective and easily realizing
Measure processed come widen air intake duct work range of Mach numbers.
Detailed description of the invention
Fig. 1 schematically illustrates the Mach number cloud atlas under typical intake duct starting state；
Fig. 2 schematically illustrates the Mach number cloud atlas under the inoperative state of typical air intake duct；
Fig. 3 schematically shows a kind of stream of the closed return flow line flow field control method of embodiment according to the present invention
Cheng Tu；
Fig. 4 schematically shows a kind of return flow line flow field with particular cross section cavity of embodiment according to the present invention
Control figure；
Fig. 5 schematically shows a kind of return flow line flow field control flow chart of embodiment according to the present invention；
Fig. 6 schematically shows a kind of return flow line geometry profile structure chart of embodiment according to the present invention.
Specific embodiment
It, below will be to embodiment in order to illustrate more clearly of embodiment of the present invention or technical solution in the prior art
Needed in attached drawing be briefly described.It should be evident that the accompanying drawings in the following description is only of the invention some
Embodiment for those of ordinary skills without creative efforts, can also be according to these
Attached drawing obtains other attached drawings.
When being described for embodiments of the present invention, term " longitudinal direction ", " transverse direction ", "upper", "lower", " preceding ",
" rear ", "left", "right", "vertical", "horizontal", "top", "bottom" "inner", orientation or positional relationship expressed by "outside" are based on phase
Orientation or positional relationship shown in the drawings is closed, is merely for convenience of description of the present invention and simplification of the description, rather than instruction or dark
Show that signified device or element must have a particular orientation, be constructed and operated in a specific orientation, therefore above-mentioned term cannot
It is interpreted as limitation of the present invention.
The present invention is described in detail with reference to the accompanying drawings and detailed description, embodiment cannot go to live in the household of one's in-laws on getting married one by one herein
It states, but therefore embodiments of the present invention are not defined in following implementation.
Fig. 1 and Fig. 2 schematically illustrates the Mach number cloud atlas under typical intake duct starting and inoperative state.Such as Fig. 1 and
Shown in Fig. 2, inlet mouth traffic capture area is larger under starting state, without at inlet mouth under starting state exist compared with
Big low mach recirculating zone causes to be jammed at inlet mouth, and air captures flow and significantly reduces.Hypersonic flight
Device flight must undergo low mach flight course, therefore face the inoperative problem of low mach.The size of Start mach number
The starting capability of hypersonic inlet is reflected, Start mach number is bigger, and the starting capability of air intake duct is poorer.For high ultrasound
For fast Design of Inlet, Start mach number is the important performance indexes of air intake duct optimization design, so to take certain arrange
It applies to improve the starting characteristic of air intake duct, that is, reduces the Start mach number of air intake duct, improve the self-starting ability of air intake duct,
This is conducive to the working range for extending hypersonic inlet, operates normally it in wide range of Mach numbers.
Based on the above, the present invention provides a kind of closed return flow line flow field control side with particular cross section cavity
Method, for improving the starting capability under hypersonic inlet low mach, to widen air intake duct work range of Mach numbers.
Fig. 3 schematically shows a kind of stream of the closed return flow line flow field control method of embodiment according to the present invention
Cheng Tu.As shown in figure 3, closed return flow line flow field control method according to the present invention the following steps are included:
A. joined according to the designs such as hypersonic aircraft cruise Mach number Ma and height H and air intake duct leading edge compression angle δ
Number requires, and designs hypersonic inlet geometry profile, sunykatuib analysis air intake duct self-starting characteristic；
Static pressure distribution different in compressing surface before import rule when b. based on hypersonic intake duct starting/non-starting, benefit
With the Pressure difference distribution after shock wave front, back cavity is opened up inside air intake duct, air intake duct flow field is controlled；
C. simulation analysis return flow line entrance location, outlet port and the back cavity cross section parameter, optimization is described to return
The geometry profile parameter of circulation road；
D. return flow line geometry profile parameter is adjusted, determines final inlet structure.
A kind of embodiment according to the present invention, in above-mentioned a step, certainly by fining numerical simulation analysis air intake duct
Starting characteristic, the observation monitoring critical inoperative Mach number of air intake duct, analysis air intake duct separate zone position, and induction when inoperative
Pressure distribution after shock wave front.
Fig. 4 schematically shows a kind of return flow line flow field with particular cross section cavity of embodiment according to the present invention
Control figure.The back cavity that opens up inside air intake duct in above-mentioned steps b controls i.e. based on such as institute in Fig. 4 air intake duct flow field
The back cavity shown controls air intake duct flow field.
Fig. 5 schematically shows a kind of return flow line flow field control flow chart of embodiment according to the present invention.Such as Fig. 5 institute
Show, in the present embodiment, when air intake duct is inoperative, using the static pressure difference after induction shock wave front by the low energy stream in Disengagement zone
It draws, specifically can be described as Disengagement zone bottom and swashing after back cavity under differential pressure action close to the low energy stream on wedge surface
Wavefront compression wedge surface refills, and forms an enclosed internal circulation flow, transports as low energy stream is constantly refluxed channel
It walks, separate bubble is progressively smaller until disappearance, improves hypersonic inlet in low mach by the above flow field control measure
Under starting characteristic, achieved the purpose that reduce air intake duct self-starting Mach number.
Preliminary simulating, verifying is carried out to air intake duct add-back circulation road, confirms it to intake duct starting characteristic under low mach
Improvement result, and to containing return flow line air intake duct flow field carry out preliminary analysis, pay close attention to inlet throat nearby and return
Flow Field Distribution situation in circulation road.
Fig. 6 schematically shows a kind of return flow line geometry profile structure chart of embodiment according to the present invention.In conjunction with figure
6, in above-mentioned step c, for the air intake duct that design parameter requires, regularity is carried out to return flow line typical case's geometry profile parameter
Research is carried out mainly for return flow line entrance location L1, outlet port L2 and back cavity cross section parameter S1, S2, S3 and D
Simulation analysis optimizes the geometry profile parameter of return flow line.
Wherein, return flow line entrance location L1 and back cavity width D are affected to intake duct starting characteristic.When reflux is logical
Road import is close to separate bubble tail portion, then return flow line import direction and swirl flow directional velocity in Disengagement zone are almost consistent, draws
Smooth, the easy elimination of separate bubble is flowed, air intake duct self-starting performance improvement is obvious.When back cavity width D is larger, it is easily formed air-flow
Low-pressure area, facilitate low energy stream from aspirating, but crossing conference keeps the effect of cavity inside vortex obvious, has an adverse effect.Pass through
Simulation analysis is carried out to the air intake duct model with different return flow line parameters, crucial type face parameter is extracted and obtains its design
Selection range and optimized parameter proportion, and analysis comparison is carried out with the performance without return flow line air intake duct.
A kind of embodiment according to the present invention has particular cross section based on what simulation analysis obtained in above-mentioned Step d
The air intake duct model of cavity designs hypersonic inlet testpieces, formulates wind tunnel test scheme and carries out under typicalness
Wind tunnel test verifying, is adjusted return flow line geometric parameter, and determines final inlet structure.
Closed return flow line flow field control method according to the present invention passes through flow field control that is simple and effective and easily realizing
Air intake duct work range of Mach numbers has been widened in measure.
Above content is only the example of concrete scheme of the invention, for the equipment and structure of wherein not detailed description, is answered
When being interpreted as that the existing common apparatus in this field and universal method is taken to be practiced.
The foregoing is merely a schemes of the invention, are not intended to restrict the invention, for the technology of this field
For personnel, the invention may be variously modified and varied.All within the spirits and principles of the present invention, made any to repair
Change, equivalent replacement, improvement etc., should all be included in the protection scope of the present invention.
Claims (1)
1. a kind of closed return flow line flow field control method, which comprises the following steps:
A. it is wanted according to hypersonic aircraft cruise Mach number Ma and height H and air intake duct leading edge compression angle δ design parameter
It asks, designs hypersonic inlet geometry profile, sunykatuib analysis air intake duct self-starting characteristic；
Different static pressure distribution rules in compressing surface before import when b. based on hypersonic intake duct starting/non-starting, using swashing
Pressure difference distribution after wavefront opens up back cavity inside air intake duct and controls air intake duct flow field；
C. it is logical to optimize the reflux for simulation analysis return flow line entrance location, outlet port and the back cavity cross section parameter
The geometry profile parameter in road；
D. return flow line geometry profile parameter is adjusted, determines final inlet structure；
In a step, the critical inoperative Mach number of air intake duct is monitored, analysis air intake duct separates zone position when inoperative, with
And the pressure distribution after induction shock wave front；
When hypersonic inlet is inoperative, the low energy stream in Disengagement zone is drawn using the static pressure difference after induction shock wave front；
In the Step d, based on the air intake duct model with particular cross section cavity that simulation analysis obtains, design hypersonic
Air intake test part formulates wind tunnel test scheme and carries out the verifying of the wind tunnel test under typicalness, to return flow line geometric parameters
Number is adjusted, and determines final inlet structure.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201811427187.8A CN109356723B (en) | 2018-11-27 | 2018-11-27 | Closed return flow line flow field control method |
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| CN201811427187.8A CN109356723B (en) | 2018-11-27 | 2018-11-27 | Closed return flow line flow field control method |
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| CN109356723B true CN109356723B (en) | 2019-10-25 |
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| CN110082056A (en) * | 2019-04-12 | 2019-08-02 | 北京空天技术研究所 | The Numerical Predicting Method of air intake duct self-starting critical point |
| CN113623086B (en) * | 2021-07-19 | 2022-08-02 | 南京航空航天大学 | Shock wave/boundary layer interference controller |
| CN114320661B (en) * | 2021-12-21 | 2023-01-31 | 哈尔滨工业大学 | Backflow injection pressurization system based on detonation combustion excitation and pressurization method thereof |
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| GB1228213A (en) * | 1968-04-16 | 1971-04-15 | ||
| CN100430584C (en) * | 2007-03-22 | 2008-11-05 | 南京航空航天大学 | Fixed geometrical supersonic-speed and high supersonic-speed adjusting air inlet |
| US9429071B2 (en) * | 2011-06-23 | 2016-08-30 | Continuum Dynamics, Inc. | Supersonic engine inlet diffuser with deployable vortex generators |
| CN102953825B (en) * | 2012-11-22 | 2013-09-25 | 南京航空航天大学 | Pneumatic supersonic velocity/hypersonic velocity adjustable air inlet passage for self-circulation of forebody |
| CN103953448B (en) * | 2014-04-15 | 2016-05-18 | 南京航空航天大学 | A kind of hypersonic inlet |
| CN106021831B (en) * | 2016-07-26 | 2018-11-13 | 厦门大学 | Adaptive connection reverse backflow slot Design of Inlet method |
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