CN109733634A - Design method of three-dimensional inward-turning four-channel hypersonic combined intake port - Google Patents
Design method of three-dimensional inward-turning four-channel hypersonic combined intake port Download PDFInfo
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Abstract
Turn the design method of the hypersonic combination intake of four-way in three-dimensional.Design work range of Mach numbers is the punching press channel of Ma=4~6；Rocket ejector corridor diversion plate and turbine channel flow distribution plate are designed, adjusts into the air-flow of Rocket ejector channel and turbine channel by flow distribution plate rotation, to be designed in conjunction with the layout of Rocket ejector channel, turbine channel when designing flow distribution plate；Design work range of Mach numbers is the turbine channel expansion segment of Ma=0~2；Design work range of Mach numbers is the Rocket ejector channel expansion segment of Ma=2~4.Turning the hypersonic combination intake of four-way in three-dimensional includes that air flue compression-type face, the expansion of punching press channel distance piece, turbine channel shunting section, turbine channel class rectangle is adjustable expansion segment, turbine channel is adjustable non-adjustable expansion segment, Rocket ejector corridor diversion section, Rocket ejector channel class rectangle is adjustable expansion segment, the non-adjustable expansion segment in Rocket ejector channel are rotated into three-dimensional.
Description
Technical field
The present invention relates to the hypersonic inlet of wide fast domain aviation aircraft, more particularly, to turning four-way height in three-dimensional
The design method of supersonic speed combination intake.
Background technique
Since aviation aircraft is born, it always has been that the object of development is fallen over each other in countries in the world, has either been transported as traffic
Defeated or defence equipment, the status of aviation aircraft are all very important.The mankind are to the pursuit of aircraft performance and speed
It is endless, a large amount of Technological research and innovation make aircraft promptly from subsonic flight develop to transonic speed, supersonic speed with
And it is numerous at present national all in the hypersonic flight greatly developed.The fast domain of hypersonic aircraft flight is wider, previous single
The engine of mode is unable to satisfy the demand of hypersonic aircraft, so there is combination power device, it is intended to be Gao Chaosheng
Fast aircraft provides reliable power ([1] Zhang Huajun, Guo Rongwei, Li Bo .TBCC air intake duct present Research and its key technology
[J] air force journal, 2010,28 (05): 613-620).
The appearance of combination power device is greatly promoted the development of hypersonic aircraft, previous single mode into
Air flue can not provide stable high-quality air-flow also for multi-modal combination power device.Air intake duct is hypersonic propulsion system
In important component part, only air intake duct provides stable high-quality incoming flow, and combined engine could high performance work.
([2] Peng little Bo assembly power vehicle technology develops [J] guided missile and carrying space technology, 2016 (5): 1-6) is with TBCC group
Close the development of engine (combination of turbine, punching engine), the relatively simple twin-channel inside and outside air intake duct hair in parallel of structure
Exhibition is relatively more, and binary channels air intake duct is the rotation for passing through control flow distribution plate, to realize the conversion of air intake duct mode.But due to
The Start mach number of punching engine is higher, and turbogenerator needs work just to can be carried out mode conversion to very high Mach number,
And existing turbogenerator can not reach its requirement, so will appear thrust when the type air intake duct carries out mode conversion
Insufficient phenomenon.In order to make up this defect, Trijet combined engine (combination of turbine, Rocket ejector, punching engine), together
When air intake duct is developed as triple channel combination intake, increase Rocket ejector mode on the basis of bimodal, form turbine mode
Transition between punching press mode makes up aircraft and has suffered thrust deficiency from turbine to punching press mode conversion process, wherein typical
A hypersonic triple channel for upper, middle and lower formula (upper, middle and lower is respectively turbine channel, Rocket ejector channel, punching press channel)
Air intake duct.Although the assembly power of the type improves the insufficient situation of thrust in mode conversion process to a certain extent,
Also to bring new problem simultaneously, as air intake duct flow distribution plate in mode conversion process rotation angle spend and cause air-flow office greatly
The problems such as excessive expansion in portion, turbine channel inlet area too small underfed.Due to the deficiency of Design of Inlet, cause combination dynamic
Power can not high performance work, so a high performance air intake duct can promote the hair of hypersonic aircraft to a certain extent
Exhibition.
In view of the deficiency of binary channels air intake duct and triple channel Design of Inlet, turbine, Rocket ejector, punching press are equally used
Three kinds of power device combinations of engine, select new inlet passageway layout type, are by hypersonic inlet optimization design
Four-way combination intake.Four-way air intake duct two sides are turbine channel, i.e. two turbogenerators work at the same time, guarantee to be winged
Row device provides sufficient thrust；Intermediate upside is Rocket ejector channel, using Rocket ejector boosting, realizes turbine to punching press mode
Smooth transition, it is ensured that engine turns going on smoothly for grade process；Intermediate downside is punching press channel, is sent out using high performance punching press
Motivation provides sufficient thrust for the aircraft under fast state.The flow distribution plate of the four-way combination intake is opened in punching respectively
The upside and the left and right sides of pressure passageway avoid single flow distribution plate rotation angle and spend big the problems such as generating expansion, can be effectively
Improve the design defect of triple channel air intake duct.The four-way inlet structure of such distribution form is compact, mode conversion process is steady
Fixed reliable, working performance is good, promotes the research to air intake duct mode conversion, for assembly power technology and hypersonic flight
The development of device has great significance.
Summary of the invention
It can be improved that mode conversion process stability, distribution form be more compact, each mould the purpose of the present invention is to provide one kind
Turn the design method of the hypersonic combination intake of four-way under state in the higher three-dimensional of working performance.
The present invention the following steps are included:
1) design work range of Mach numbers is the punching press channel of Ma=4~6；
In step 1), the design work range of Mach numbers is that the specific method in the punching press channel of Ma=4~6 can are as follows:
(1) turn class rectangle compression-type face in design three-dimensional: the design in punching press channel will be rushed using the flow field ICFD as design basis
The design Mach 2 ship inlet flow conditions of pressure passageway, in face of required free stream Mach number, venturi Mach number and compression-type
The initial angle of wedge is held, the wall surface molded line of a contract basic flow field is obtained in the flow field ICFD, is chosen according to design requirement basic
The live part of flow field streamline；Axial symmetry contract basic flow field is solved with the method for characteristic curves again, obtains interior inner wave rider type air inlet channel taking
Incident shock and axial symmetry contract basic flow field reflected shock wave, the intersection point of incident shock and basic flow field centre of gyration line
It is designed as the lip of air intake duct, the intersection point of the live part of incident shock and basic flow field streamline is designed as air intake duct leading edge point
It sets, the intersection point of the live part of reflected shock wave and basic flow field streamline is the effective terminal of contract basic flow field；Then basis is set
Turn class rectangle compression-type face shoulder, the streamline tracked out in obtained basic flow field with reverse streamline back tracking method in meter three-dimensional
It is to turn class rectangle compression in the three-dimensional of class rectangle that the point set being separated by basic streamline live part, which forms inlet and outlet section,
Type face；
(2) punching press channel separation section: it is expanding face that isolator design is led in punching press, according to the expansion of punching press channel separation section
The requirement for opening ratio and the outlet of punching press channel separation section ellipse designs punching press channel separation section, turns class rectangle compression-type in three-dimensional
Using the raw forming surface of area even transition between face shoulder and the outlet of punching press channel separation section ellipse.
2) Rocket ejector corridor diversion plate and turbine channel flow distribution plate are designed, into Rocket ejector channel and turbine channel
Air-flow is adjusted by flow distribution plate rotation, to be set in conjunction with the layout of Rocket ejector channel, turbine channel when designing flow distribution plate
Meter；
In step 2), the design Rocket ejector corridor diversion plate and turbine channel flow distribution plate are logical into Rocket ejector
Road and the air-flow of turbine channel are adjusted by flow distribution plate rotation, logical in conjunction with Rocket ejector channel, turbine when designing flow distribution plate
The specific method that the layout in road is designed can be divided into:
(1) design Rocket ejector corridor diversion plate and turbine channel flow distribution plate: Rocket ejector channel and turbine channel be not total
With same flow distribution plate, Rocket ejector corridor diversion plate is arranged in the upper wall surface for turning class rectangle compression-type face in three-dimensional, two whirlpools
Wheel corridor diversion plate is arranged in the left and right sides for turning class rectangle compression-type face in three-dimensional；The tip type of Rocket ejector corridor diversion plate
The compression ratio that air flue compression-type face shoulder area is rotated into vertical section area and three-dimensional where line is controlled 1.1 hereinafter, knot
It closes design requirement and selectes Rocket ejector corridor diversion plate end, according to the face of the outlet of preset Rocket ejector corridor diversion section
Product, while guaranteeing that the rotation angle of Rocket ejector corridor diversion plate is only big, out of the extension of postrotational tip forward and three-dimensional
Turn the intersection of class rectangle compression-type face, intersection is the rotary shaft for being designed as Rocket ejector corridor diversion plate；Turbine channel flow distribution plate
Rotary shaft and the control of the rotary shaft of Rocket ejector corridor diversion plate are in same section, according to going out for preset turbine channel shunting section
Open area, and guarantee the rotation angle only big requirement of turbine channel flow distribution plate, determine the end of turbine channel flow distribution plate；
(2) design Rocket ejector corridor diversion plate rotation angle and turbine channel flow distribution plate rotate angle: rotation angle takes
Certainly in Rocket ejector corridor diversion plate, turbine channel flow distribution plate tip length and Rocket ejector channel expansion segment and turbine channel
The inlet area requirement of expansion segment, in order to reduce the influence of expansion, control rotation angle is no more than 10 °, sets according in step (1)
The rotary shaft of the Rocket ejector corridor diversion plate of meter and the rotary shaft of turbine channel flow distribution plate, determine Rocket ejector corridor diversion plate
Rotation angle and turbine channel flow distribution plate rotation angle；
(3) design flow distribution plate rotation mode: Rocket ejector corridor diversion plate and turbine channel shunt in mode conversion process
The rotation of plate can impact the air-flow passed through, can generate local swelling, influence to reduce, and make flow to end can
It can be smoothly introduced into turbine channel, Rocket ejector channel and punching press channel, the mode at the uniform velocity rotated is selected to adjust flow distribution plate.
3) design work range of Mach numbers is the turbine channel expansion segment of Ma=0~2；
In step 3), the design work range of Mach numbers is the specific method of the turbine channel expansion segment of Ma=0~2
It can are as follows:
(1) design the adjustable expansion segment of turbine channel class rectangle: the rotary-type face of turbine channel class rectangle is adjustable expansion segment exists
It rotates adjustable in mode conversion, controls that it is synchronous with the adjusting of turbine channel flow distribution plate, improve the leakproofness of mode conversion process；
Since the rotary-type face of the adjustable expansion segment of turbine channel class rectangle rotates in mode conversion process, the expansion segment is designed as class
Rectangle；According to the rotation angle within the divergence ratio of the expansion segment of design and 15 °, in conjunction with the outlet of turbine channel shunting section
Section determines the length of the adjustable expansion segment of turbine channel and the rotary shaft in turbine channel class rectangle adjustable expansion segment rotation face；Root
According to the shape of the determining adjustable expansion segment outlet of turbine channel class rectangle, using area uniform excessive form and turbine channel point
Flow remaining type face that the adjustable expansion segment of turbine channel class rectangle is generated between the outlet of section；
(2) design the non-adjustable expansion segment of turbine channel: the outlet of turbine channel class rectangle is adjustable expansion segment is class rectangle, whirlpool
Taking turns channel outlet section is circle, expands smoothly transitting for segment type face to guarantee that turbine channel is non-adjustable, uses cubic curve；
It is raw with the slope at the outlet tangential of the outlet of both ends and the adjustable expansion segment of turbine channel class rectangle and turbine channel setting endpoint
At the cubic curve of the non-adjustable expansion segment inlet and outlet of connection turbine channel, the form of area even transition is then used, whirlpool is generated
Take turns the type face of the non-adjustable expansion segment in channel.
4) design work range of Mach numbers is the Rocket ejector channel expansion segment of Ma=2~4.
In step 4), the design work range of Mach numbers is the specific of the Rocket ejector channel expansion segment of Ma=2~4
Method can are as follows:
(1) the adjustable expansion segment of Rocket ejector channel class rectangle: the rotation of the adjustable expansion segment of Rocket ejector channel class rectangle is designed
Transition face rotates adjustable in mode conversion, controls that its is synchronous with the adjusting of Rocket ejector corridor diversion plate, improves mode conversion
The leakproofness of process；Since the rotary-type face of the adjustable expansion segment of Rocket ejector channel class rectangle rotates in mode conversion process,
The expansion segment is designed as class rectangle；According to the rotation angle within the divergence ratio of the expansion segment of design and 20 °, in conjunction with drawing
Penetrate length and Rocket ejector channel class rectangle that rocket corridor diversion section outlet determines the adjustable expansion segment in Rocket ejector channel
The rotary shaft in the rotary-type face of adjustable expansion segment；Go out the degree of lip-rounding according to the determining adjustable expansion segment of Rocket ejector channel class rectangle
Shape, can using Rocket ejector channel class rectangle is generated between the uniform excessive form of area and the outlet of Rocket ejector corridor diversion section
Adjust remaining type face of expansion segment；
(2) design the non-adjustable expansion segment in Rocket ejector channel: the outlet of the adjustable expansion segment of Rocket ejector channel class rectangle is cut
Face is class rectangle, and the outlet in Rocket ejector channel is circle, in order to guarantee the non-adjustable expansion segment type face in Rocket ejector channel
Smoothly transit, use cubic curve.With the outlet of both ends and the adjustable expansion segment of Rocket ejector channel class rectangle and draw
The slope at the tangent setting endpoint in outlet in rocket channel is penetrated, the non-adjustable expansion segment disengaging in connection Rocket ejector channel is generated
The cubic curve of mouth then uses the form of area even transition, generates the type face of the non-adjustable expansion segment in Rocket ejector channel.
The present invention is considering on interior binary channels in parallel and the insufficient basis of triple channel hypersonic inlet, proposes
A kind of layout is novel, compact-sized, turns the design method of the hypersonic combination intake of four-way in the reasonable three-dimensional of design.
Turn the hypersonic combination intake of four-way in a kind of three-dimensional that the present invention designs, structure includes: to turn in three-dimensional
Air intake duct compression-type face, the expansion of punching press channel distance piece, turbine channel shunting section, turbine channel class rectangle is adjustable expansion segment, whirlpool
Take turns the adjustable non-adjustable expansion segment in channel, Rocket ejector corridor diversion section, Rocket ejector channel class rectangle is adjustable expansion segment, injection fire
The non-adjustable expansion segment in arrow channel.It is raw using the method for characteristic curves and reverse streamline tracer technique that air flue compression-type face is wherein rotated into three-dimensional
At, it shunts segment type face and is generated by rotation, the even transition generation according to area of other type faces.
The present invention has the following advantages: turning the hypersonic combination intake of four-way in three-dimensional, to be designed as twin turbines logical
Road can provide more reliable thrust in low speed for aircraft and guarantee, turbine, punching press, Rocket ejector assembly power dress
Setting makes aircraft possess the fast domain of broader flight.Each flow distribution plate controls the shunting in single channel, and flow distribution plate rotation angle is small, solution
Triple channel of having determined flow distribution plate rotation angle spends big bring expansion issues and turbine channel and Rocket ejector channel capacity is insufficient
Problem.The distance piece in punching press channel is expanding face, improves the anti-reflective pressure energy power in punching press channel to a certain extent；Turbine is logical
The expansion segment in road and Rocket ejector channel is both designed as adjustable class rectangle expansion segment and non-adjustable class rectangle turns circular dilator section
Combination, adjustable expansion segment and flow distribution plate synchronous rotary during mode conversion, the compactedness and mode for improving structure turn
The leakproofness of process is changed, improves the performance of air intake duct mode conversion to a certain extent.The channel cloth of the four-way air intake duct
Office is compact, reduces front face area and external drag, structure type more meets the demand of future aircraft.
Detailed description of the invention
Fig. 1 is the basic flow field schematic diagram for turning the hypersonic combination intake of four-way in three-dimensional.
Fig. 2 is to turn to turn class rectangle compression-type face entrance and shoulder in the hypersonic combination intake three-dimensional of four-way in three-dimensional
Two-dimension projection.
Fig. 3 is the punching press channel design schematic diagram for turning the hypersonic combination intake of four-way in three-dimensional.
Fig. 4 is Rocket ejector channel and the turbine channel design principle for turning the hypersonic combination intake of four-way in three-dimensional
Figure.
Fig. 5 is the rotation for turning the flow distribution plate and adjustable expansion segment rotation wall surface of the hypersonic combination intake of four-way in three-dimensional
Turn schematic diagram.
Fig. 6 is the entrance front view for turning the hypersonic combination intake of four-way in three-dimensional.
Fig. 7 is the full mould view for turning the hypersonic combination intake of four-way in three-dimensional.
It is each to mark in Fig. 1~7 are as follows: to hold the initial angle of wedge, 2 to indicate the wall of contract basic flow field in face of 1 expression compression-type
Face molded line, 3 indicate the live part of basic flow field streamlines, 4 indicate the effective terminal of contract basic flow fields, 5 indicate reflected shock waves,
6 indicate that the lip of air intake duct, 7 indicate that incident shock, 8 indicate that basic flow field centre of gyration line, 9 indicate air intake duct leading edge point
It sets, 10 expression air intake duct leading edges capture the two-dimensional projection of molded line, 11 indicate the two dimension for turning class rectangle compression-type face shoulder in three-dimensional
Projection, 12 indicate point set, 14 tables that streamline, the 13 basic streamline live parts of expression that reverse streamline back tracking method tracks out are separated into
Show that axial symmetry contract basic flow field, the streamline projection on the 15 first cone of origin sections of expression air intake ducts, 16 indicate to turn class square in three-dimensional
The two-dimensional projection in shape compression-type face, 17 indicate to turn class rectangle compression-type face, 18 expression Rocket ejector corridor diversion plates, 19 in three-dimensional
Indicate that the punching press channel of air intake duct, 20 indicate that the outlet of punching press channel separation section ellipse, 21 indicate punching press channel separation section, 22 tables
Show turn in three-dimensional class rectangle compression-type face shoulder, 23 indicate turbine channel flow distribution plates end, 24 indicate turbine channel flow distribution plates,
25 indicate that the rotary shaft of turbine channel flow distribution plate, 26 indicate that the rotary shaft of Rocket ejector corridor diversion plate, 27 indicate Rocket ejector
The rotation angle of corridor diversion plate, 28 indicate the outlet of Rocket ejector corridor diversion section, 29 Rocket ejector channel class rectangles
The rotary-type face of adjustable expansion segment, 30 indicate that the adjustable expansion segment of Rocket ejector channel class rectangle, 31 indicate Rocket ejector channel class
Outlet that the rotary shaft in rectangle is adjustable expansion segment rotation face, 32 indicate the adjustable expansion segments of Rocket ejector channel class rectangle,
33 indicate that the non-adjustable expansion segment in Rocket ejector channel, 34 indicate that the outlet in Rocket ejector channel, 35 indicate turbine channel
Outlet, 36 indicate that the non-adjustable expansion segment of turbine channel, 37 indicate the outlet of the adjustable expansion segment of turbine channel class rectangle, 38 tables
Show that the rotary shaft in turbine channel class rectangle adjustable expansion segment rotation face, 39 indicate the rotation of the adjustable expansion segment of turbine channel class rectangle
Transition face, 40 indicate that the adjustable expansion segment of turbine channel class rectangle, 41 indicate that the outlet of turbine channel shunting section, 42 indicate whirlpool
Take turns the rotation angle of corridor diversion plate, the front end compression-type face of 43 expression four-way air intake ducts, 44 expression Rocket ejector channels point
Position of the flowing plate in mode conversion process is illustrated, 45 indicate Rocket ejector corridor diversion plate and injections in mode conversion process
The gap for expansion segment rotation face formation that rocket channel is adjustable, 46 indicate the adjustable expansion segment swivel plates in Rocket ejector channel in mode
The position of position signal, the 47 expression adjustable expansion segment swivel plates of turbine channel in mode conversion process in conversion process shows
Meaning, the 48 expressions seam that turbine channel flow distribution plate and turbine channel adjustable expansion segment rotation face are formed in mode conversion process
Gap, 49 indicate that position of the turbine channel flow distribution plate in mode conversion process is illustrated, 50 indicate Rocket ejector corridor diversion sections, 51
Indicate that Rocket ejector channel, 52 indicate that Rocket ejector channel expansion segment, 53 indicate that turbine channel expansion segment, 54 indicate that turbine is logical
Road, 55 indicate turbine channel shunting section.
Specific embodiment
Following embodiment will the present invention is further illustrated in conjunction with attached drawing.
Referring to Fig. 1~7, the embodiment of the present invention includes following steps:
1) design work range of Mach numbers is the punching press channel 19 of Ma=4~6, is specifically included that
(1) turn class rectangle compression-type face 17 in design three-dimensional: the design in punching press channel 19 using the flow field ICFD as design basis,
By the design Mach 2 ship inlet flow conditions in punching press channel 19, according to required free stream Mach number, venturi Mach number and compression
The initial angle of wedge 1 is held in face of type, the wall surface molded line 2 of a contract basic flow field is obtained in the flow field ICFD, according to design requirement
Choose the live part 3 of basic flow field streamline；Axial symmetry contract basic flow field 14 is solved with the method for characteristic curves again, obtains interior multiply
The incident shock 7 of waves air intake duct and the reflected shock wave 5 of axial symmetry contract basic flow field 14, incident shock 7 and basic flow field
The intersection point of centre of gyration line 8 is designed as the lip 6 of air intake duct, the intersection point of the live part 3 of incident shock 7 and basic flow field streamline
It is designed as air intake duct leading edge point position 9, the intersection point of the live part 3 of reflected shock wave 5 and basic flow field streamline is that contract is basic
The effective terminal 4 in flow field；Then it according to class rectangle compression-type face shoulder 22 is turned in design three-dimensional, is used in obtained basic flow field
The streamline 12 that reverse streamline back tracking method tracks out forms inlet and outlet section by the point set 13 that basic streamline live part is separated into
Be to turn class rectangle compression-type face 17 in the three-dimensional of class rectangle, the air intake duct just streamline projection 15 on cone of origin section in structure, into
Turn in two-dimensional projection 11 and the three-dimensional of class rectangle compression-type face shoulder in the two-dimensional projection 10 of air flue leading edge capture molded line, three-dimensional
The two-dimensional projection 16 for turning class rectangle compression-type face indicates in Fig. 2.
(2) design punching press channel separation section 21: distance piece 21 is led into punching press and is designed as expanding face, according to punching press channel every
The requirement of divergence ratio from section 21 and punching press channel separation section ellipse outlet 20 designs punching press channel separation section 21, in three-dimensional
Turn between class rectangle compression-type face shoulder 22 and punching press channel separation section ellipse outlet 20 using area even transition generation type
Face.
2) Rocket ejector corridor diversion plate 18 and turbine channel flow distribution plate 24 are designed, into Rocket ejector channel 51 and turbine
The air-flow in channel 54 is adjusted by flow distribution plate rotation, and Rocket ejector channel 51, turbine are combined when designing flow distribution plate
The layout in channel 54 is designed respectively, is specifically included that
(1) design Rocket ejector corridor diversion plate 18 and turbine channel flow distribution plate 24: Rocket ejector channel 51 and turbine are logical
Road 54 does not share same flow distribution plate, and Rocket ejector corridor diversion plate 18 is arranged in and turns the upper of class rectangle compression-type face 17 in three-dimensional
Wall surface, two turbine channel flow distribution plates 24 are arranged in the left and right sides for turning class rectangle compression-type face 17 in three-dimensional.Rocket ejector is logical
The pressure of 22 area of air flue compression-type face shoulder is rotated into vertical section area and three-dimensional where the end molded line of road flow distribution plate 18
Contracting is than control 1.1 hereinafter, 18 end of Rocket ejector corridor diversion plate is selected in conjunction with design requirement, according to preset Rocket ejector
The area of the outlet of corridor diversion section 50, while guaranteeing that the rotation angle of Rocket ejector corridor diversion plate 18 is only big, from rotation
Turn class rectangle compression-type face 17 in tip forward extension and three-dimensional afterwards to intersect, intersection is designed as Rocket ejector corridor diversion plate
Rotary shaft 26；The rotary shaft 25 of turbine channel flow distribution plate and the rotary shaft 26 of Rocket ejector corridor diversion plate are controlled at same section
Face according to the discharge area of preset turbine channel shunting section 55, and guarantees the rotation angle of turbine channel flow distribution plate 24 not
Excessive requirement determines the end 23 of turbine channel flow distribution plate.
(2) the rotation angle 27 of Rocket ejector corridor diversion plate and the rotation angle 42 of turbine channel flow distribution plate are designed: rotation
Gyration depends on the inlet area of Rocket ejector channel expansion segment 52 and turbine channel expansion segment 53, in order to reduce the shadow of expansion
It rings, control rotation angle is no more than 10 °, according to the rotary shaft 26 of the Rocket ejector corridor diversion plate designed in step (1) and whirlpool
The rotary shaft 25 for taking turns corridor diversion plate, determines the rotation angle 27 of Rocket ejector corridor diversion plate and the rotation of turbine channel flow distribution plate
Gyration 42.
(3) flow distribution plate rotation mode is designed: Rocket ejector corridor diversion plate 18 and turbine channel point in mode conversion process
The rotation of flowing plate 24 can impact the air-flow passed through, and air-flow is made to generate the expansion of part, influence to reduce, make incoming flow
It is smoothly introduced into turbine channel 54, Rocket ejector channel 51 and punching press channel 19 as far as possible, the mode at the uniform velocity rotated is selected to adjust
Save flow distribution plate.
3) design work range of Mach numbers is the turbine channel expansion segment 53 of Ma=0~2, is specifically included that
(1) the adjustable expansion segment 40 of turbine channel class rectangle: the rotary-type face of turbine channel class rectangle is adjustable expansion segment is designed
39 rotate adjustable in mode conversion, control that it is synchronous with the adjusting of turbine channel flow distribution plate 24, improve mode conversion process
Leakproofness.Since the rotary-type face 39 of the adjustable expansion segment of turbine channel class rectangle rotates in mode conversion process, section design
For class rectangle.According to the rotation angle within the divergence ratio of this section of design and 15 °, in conjunction with the outlet of turbine channel shunting section
Section 41 determines the length of the adjustable expansion segment 40 of turbine channel and the rotation in turbine channel class rectangle adjustable expansion segment rotation face
Shaft 38.According to the shape of the outlet 37 of the determining adjustable expansion segment of turbine channel class rectangle, using the uniform excessive shape of area
Remaining type face of the adjustable expansion segment 40 of turbine channel class rectangle is generated between formula and the outlet 41 of turbine channel shunting section.
(2) design the non-adjustable expansion segment 36 of turbine channel: the outlet 37 of turbine channel class rectangle is adjustable expansion segment is class square
The outlet 35 of shape, turbine channel is circle, in order to guarantee smoothly transitting for the non-adjustable 36 type face of expansion segment of turbine channel, is made
Use cubic curve.It is tangent with both ends and the outlet 37 of the adjustable expansion segment of turbine channel class rectangle and the outlet 35 of turbine channel
Slope at endpoint is set, generates the cubic curve that the non-adjustable expansion segment 36 of connection turbine channel is imported and exported, then uses area
The form of even transition generates the type face of the non-adjustable expansion segment 36 of turbine channel.
4) design work range of Mach numbers is the Rocket ejector channel expansion segment 52 of Ma=2~4, is specifically included that
(1) the adjustable expansion segment 30 of Rocket ejector channel class rectangle is designed: the adjustable expansion segment of Rocket ejector channel class rectangle
Rotary-type face 29 rotates adjustable in mode conversion, controls that its is synchronous with the adjusting of Rocket ejector corridor diversion plate 18, improves mould
The leakproofness of state conversion process.Since the rotary-type face 29 of the adjustable expansion segment of Rocket ejector channel class rectangle is in mode conversion process
Middle rotation, the section are designed as class rectangle.According to the rotation angle within the divergence ratio of this section of design and 20 °, in conjunction with injection fire
The outlet 28 of arrow corridor diversion section determines the length and Rocket ejector channel class square of the adjustable expansion segment 30 in Rocket ejector channel
The rotary shaft 31 in the rotary-type face of shape is adjustable expansion segment.According to the outlet of the determining adjustable expansion segment of Rocket ejector channel class rectangle
The shape in section 32 is drawn using generating between the area uniformly outlet 28 of excessive form and Rocket ejector corridor diversion section
Penetrate remaining type face of the adjustable expansion segment 30 of rocket channel class rectangle.
(2) the non-adjustable expansion segment 33 in Rocket ejector channel: the outlet of the adjustable expansion segment of Rocket ejector channel class rectangle is designed
Section 32 is class rectangle, and the outlet 34 in Rocket ejector channel is circle, in order to guarantee the non-adjustable expansion in Rocket ejector channel
Smoothly transitting for 33 segment type faces, uses cubic curve.It is cut with the outlet of both ends and the adjustable expansion segment of Rocket ejector channel class rectangle
Slope at the tangent setting endpoint in the outlet 34 in face 32 and Rocket ejector channel, it is non-adjustable to generate connection Rocket ejector channel
The cubic curve that expansion segment 33 is imported and exported then uses the form of area even transition, generates the non-adjustable expansion in Rocket ejector channel
Open the type face of section 33.
During turbine mode is to rocket mode conversion, turbine channel flow distribution plate 24 and turbine channel class rectangle are adjustable
The rotary-type face 39 of expansion segment rotates simultaneously, position of the turbine channel flow distribution plate in mode conversion process in mode conversion process
The position signal 47 of signal 49 and the adjustable expansion segment swivel plate of turbine channel in mode conversion process is set in the table in Fig. 5
Show, since the rotary-type face 39 of the adjustable expansion segment of turbine channel class rectangle is non-telescoping, it may appear that the whirlpool in mode conversion process
Take turns the gap 48 of corridor diversion plate and the formation of turbine channel adjustable expansion segment rotation face；In rocket mode to punching press mode conversion
During, the rotary-type face 29 of Rocket ejector corridor diversion plate 18 and the adjustable expansion segment of Rocket ejector channel class rectangle is revolved simultaneously
Turn, position signal 44 and Rocket ejector of the Rocket ejector corridor diversion plate in mode conversion process in mode conversion process
Channel is adjustable, and position signal 46 of the expansion segment swivel plate in mode conversion process is indicating in Fig. 5, due to Rocket ejector
The rotary-type face 29 of channel class rectangle is adjustable expansion segment is non-telescoping, it may appear that the turbine channel flow distribution plate in mode conversion process
The gap 45 formed with turbine channel adjustable expansion segment rotation face.
Specific embodiment is given below.
With reference to the design method for turning the hypersonic combination intake of four-way in three-dimensional, the present embodiment is using design Mach number
Ma=5 is as free stream Mach number, and 7 ° of the initial angle of wedge, for contract than 6, designing working range as shown in Figure 7 is Ma=0~6 (its
Middle turbine Modality work Mach 2 ship Ma=0~2, Rocket ejector mode Mach 2 ship Ma=2~4, punching press Modality work Mach
Number be Ma=4~6) assembly power in turn four-way air intake duct, the air intake duct is led to by high speed stamping channel 19, Rocket ejector
51, two, road low speed turbine channel 54 forms.It is found by CFD numerical simulation calculation, the air intake duct is in design Mach 2 ship
It can be realized Three-Dimensional Shock Wave patch mouth and full flow capture, performance with higher in the case where stream condition.
Claims (5)
1. turning the design method of the hypersonic combination intake of four-way in three-dimensional, it is characterised in that the following steps are included:
1) design work range of Mach numbers is the punching press channel of Ma=4~6；
2) Rocket ejector corridor diversion plate and turbine channel flow distribution plate are designed, into the air-flow in Rocket ejector channel and turbine channel
It rotates and adjusts by flow distribution plate, to be designed in conjunction with the layout of Rocket ejector channel, turbine channel when designing flow distribution plate；
3) design work range of Mach numbers is the turbine channel expansion segment of Ma=0~2；
4) design work range of Mach numbers is the Rocket ejector channel expansion segment of Ma=2~4.
2. turning the design method of the hypersonic combination intake of four-way in three-dimensional as described in claim 1, it is characterised in that
In step 1), the design work range of Mach numbers is the punching press channel of Ma=4~6 method particularly includes:
(1) turn class rectangle compression-type face in design three-dimensional: the design in punching press channel leads to punching press using the flow field ICFD as design basis
The design Mach 2 ship inlet flow conditions in road are held just according in face of required free stream Mach number, venturi Mach number and compression-type
The beginning angle of wedge obtains the wall surface molded line of a contract basic flow field in the flow field ICFD, chooses basic flow field according to design requirement
The live part of streamline；Axial symmetry contract basic flow field is solved with the method for characteristic curves again, obtains entering for interior inner wave rider type air inlet channel taking
Penetrate the reflected shock wave of shock wave and axial symmetry contract basic flow field, the intersection point design of incident shock and basic flow field centre of gyration line
For the lip of air intake duct, the intersection point of the live part of incident shock and basic flow field streamline is designed as air intake duct leading edge point position,
The intersection point of the live part of reflected shock wave and basic flow field streamline is the effective terminal of contract basic flow field；Then according to design three
Turn class rectangle compression-type face shoulder in dimension, passes through in obtained basic flow field with the streamline that reverse streamline back tracking method tracks out
It is to turn class rectangle compression-type face in the three-dimensional of class rectangle that the point set that basic streamline live part is separated into, which forms inlet and outlet section,；
(2) punching press channel separation section: it is expanding face that isolator design is led in punching press, according to the divergence ratio of punching press channel separation section
And the requirement of punching press channel separation section ellipse outlet designs punching press channel separation section, turns class rectangle compression-type face shoulder in three-dimensional
Using the raw forming surface of area even transition between portion and the outlet of punching press channel separation section ellipse.
3. turning the design method of the hypersonic combination intake of four-way in three-dimensional as described in claim 1, it is characterised in that
In step 2), the design Rocket ejector corridor diversion plate and turbine channel flow distribution plate are logical into Rocket ejector channel and turbine
The air-flow in road by flow distribution plate rotation adjust, when design flow distribution plate will combine Rocket ejector channel, turbine channel layout into
The specific method of row design is divided into:
(1) design Rocket ejector corridor diversion plate and turbine channel flow distribution plate: Rocket ejector channel and turbine channel do not share together
Rocket ejector corridor diversion plate, is arranged in the upper wall surface for turning class rectangle compression-type face in three-dimensional by one flow distribution plate, and two turbines are logical
Road flow distribution plate is arranged in the left and right sides for turning class rectangle compression-type face in three-dimensional；The end molded line institute of Rocket ejector corridor diversion plate
Vertical section area and three-dimensional in rotate into air flue compression-type face shoulder area compression ratio control 1.1 hereinafter, in conjunction with setting
Meter requires selected Rocket ejector corridor diversion plate end, according to the area of the outlet of preset Rocket ejector corridor diversion section, together
When guarantee Rocket ejector corridor diversion plate rotation angle it is only big, from postrotational tip forward extend with three-dimensional in turn class square
The intersection of shape compression-type face, intersection are the rotary shaft for being designed as Rocket ejector corridor diversion plate；The rotary shaft of turbine channel flow distribution plate
It controls with the rotary shaft of Rocket ejector corridor diversion plate in same section, according to the exit face of preset turbine channel shunting section
Product, and guarantee the rotation angle only big requirement of turbine channel flow distribution plate, determine the end of turbine channel flow distribution plate；
(2) design Rocket ejector corridor diversion plate rotation angle and turbine channel flow distribution plate rotate angle: rotation angle depends on
Rocket ejector corridor diversion plate, turbine channel flow distribution plate tip length and Rocket ejector channel expansion segment and turbine channel expansion
The inlet area requirement of section, in order to reduce the influence of expansion, control rotation angle is no more than 10 °, according to what is designed in step (1)
The rotary shaft of Rocket ejector corridor diversion plate and the rotary shaft of turbine channel flow distribution plate, determine the rotation of Rocket ejector corridor diversion plate
The rotation angle of gyration and turbine channel flow distribution plate；
(3) flow distribution plate rotation mode is designed: Rocket ejector corridor diversion plate and turbine channel flow distribution plate in mode conversion process
Rotation, can impact the air-flow passed through, can generate local swelling, influence to reduce, flow incoming flow smoothly
Enter turbine channel, Rocket ejector channel and punching press channel, the mode at the uniform velocity rotated is selected to adjust flow distribution plate.
4. turning the design method of the hypersonic combination intake of four-way in three-dimensional as described in claim 1, it is characterised in that
In step 3), the design work range of Mach numbers is the turbine channel expansion segment of Ma=0~2 method particularly includes:
(1) design the adjustable expansion segment of turbine channel class rectangle: the rotary-type face of turbine channel class rectangle is adjustable expansion segment is in mode
It rotates adjustable in conversion, controls that it is synchronous with the adjusting of turbine channel flow distribution plate, improve the leakproofness of mode conversion process；Due to
The rotary-type face of turbine channel class rectangle is adjustable expansion segment rotates in mode conversion process, and the expansion segment is designed as class square
Shape；According to the rotation angle within the divergence ratio of the expansion segment of design and 15 °, cut in conjunction with the outlet of turbine channel shunting section
Face determines the length of the adjustable expansion segment of turbine channel and the rotary shaft in turbine channel class rectangle adjustable expansion segment rotation face；According to
The shape for expansion segment outlet that determining turbine channel class rectangle is adjustable is shunted using area uniform excessive form and turbine channel
Remaining type face of the adjustable expansion segment of turbine channel class rectangle is generated between the outlet of section；
(2) design the non-adjustable expansion segment of turbine channel: the outlet of turbine channel class rectangle is adjustable expansion segment is class rectangle, and turbine is logical
Road outlet is circle, expands smoothly transitting for segment type face to guarantee that turbine channel is non-adjustable, uses cubic curve；With two
End and the slope at the outlet of the adjustable expansion segment of turbine channel class rectangle and the outlet tangential setting endpoint of turbine channel, the company of generation
The cubic curve for connecing the non-adjustable expansion segment inlet and outlet of turbine channel, then uses the form of area even transition, it is logical to generate turbine
The type face of the non-adjustable expansion segment in road.
5. turning the design method of the hypersonic combination intake of four-way in three-dimensional as described in claim 1, it is characterised in that
In step 4), the design work range of Mach numbers is the Rocket ejector channel expansion segment of Ma=2~4 method particularly includes:
(1) design the adjustable expansion segment of Rocket ejector channel class rectangle: the adjustable expansion segment of Rocket ejector channel class rectangle it is rotary-type
Face rotates adjustable in mode conversion, controls that its is synchronous with the adjusting of Rocket ejector corridor diversion plate, improves mode conversion process
Leakproofness；It is described since the rotary-type face of the adjustable expansion segment of Rocket ejector channel class rectangle rotates in mode conversion process
Expansion segment is designed as class rectangle；According to the rotation angle within the divergence ratio of the expansion segment of design and 20 °, in conjunction with injection fire
Arrow corridor diversion section outlet determines that the length of the adjustable expansion segment in Rocket ejector channel and Rocket ejector channel class rectangle are adjustable
The rotary shaft in the rotary-type face of expansion segment；According to the outlet shapes of the determining adjustable expansion segment of Rocket ejector channel class rectangle, adopt
The adjustable expansion of Rocket ejector channel class rectangle is generated between the uniform excessive form of area and the outlet of Rocket ejector corridor diversion section
Open remaining type face of section；
(2) design the non-adjustable expansion segment in Rocket ejector channel: the outlet of the adjustable expansion segment of Rocket ejector channel class rectangle is
Class rectangle, the outlet in Rocket ejector channel are circle, in order to guarantee the light in the non-adjustable expansion segment type face in Rocket ejector channel
It slips over and crosses, using cubic curve, with the outlet and injection fire of both ends and the adjustable expansion segment of Rocket ejector channel class rectangle
Slope at the tangent setting endpoint in the outlet in arrow channel generates the non-adjustable expansion segment inlet and outlet in connection Rocket ejector channel
Cubic curve then uses the form of area even transition, generates the type face of the non-adjustable expansion segment in Rocket ejector channel.
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| CN111619820A (en) * | 2019-12-02 | 2020-09-04 | 中国人民解放军国防科技大学 | Hypersonic speed precursor design method based on two-region flow field |
| CN112960123A (en) * | 2021-03-26 | 2021-06-15 | 中国商用飞机有限责任公司 | Air inlet valve device of airplane auxiliary power unit |
| CN113738511A (en) * | 2020-05-27 | 2021-12-03 | 厦门大学 | Splitter plate design method for improving modal transformation airtightness of TBCC (TBCC) air inlet channel |
| CN113931747A (en) * | 2020-06-29 | 2022-01-14 | 厦门大学 | Design method of high-performance dual-channel TBCC intake port for three-dimensional internal rotation and expansion wave elimination |
| CN117823281A (en) * | 2024-03-06 | 2024-04-05 | 中国空气动力研究与发展中心空天技术研究所 | Multi-channel wide-speed-range adjustable air inlet channel in delta arrangement |
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| CN117823281B (en) * | 2024-03-06 | 2024-06-04 | 中国空气动力研究与发展中心空天技术研究所 | Multi-channel wide-speed-range adjustable air inlet channel in delta arrangement |
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