CN107013334A - A kind of double combustion chamber's Scramjet Inlet and air intake control method - Google Patents
A kind of double combustion chamber's Scramjet Inlet and air intake control method Download PDFInfo
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- CN107013334A CN107013334A CN201710086436.0A CN201710086436A CN107013334A CN 107013334 A CN107013334 A CN 107013334A CN 201710086436 A CN201710086436 A CN 201710086436A CN 107013334 A CN107013334 A CN 107013334A
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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
- F02C7/057—Control or regulation
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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
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- 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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- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
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- Geometry (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
It is an object of the invention to overcome prior art not enough there is provided a kind of double combustion chamber's Scramjet Inlet and air intake control method, the technical barrier of wide scope non-axis symmetry double combustion chamber's scramjet engine air inlet is solved.The air intake duct uses two dimensional inlet configuration, and sub- combustion runner and super burn runner are divided into by support plate along flow direction, the sub- combustion passage is at least one, the super burn runner at least two and divide equally in Asia combustion runner both sides, by increasing contract section adjustment type face and expansion segment adjustment type face in each runner design, to control inlet throat size, the need for realizing each combustion chamber to different compression degree air, widen engine work range of Mach numbers, improve engine performance, solve the problem difficult with turbogenerator relay.
Description
Technical field
The invention belongs to Aero-Space technical field of engines, it is related to a kind of double combustion chamber's Scramjet Inlet
And air intake control method.
Background technology
With the fast development of hypersonic technology, near space has become the New Frontier that great powers in the world competitively fight for,
As the new strategic high ground of national security, near space hypersonic aircraft is increasingly becoming the national national defence of each advanced technology and built
If pay close attention to direction.Near space hypersonic aircraft be using air suction type combined engine as power, can level rise
Drop, in dense atmosphere, near space and the reusable hypersonic aircraft of LEO maneuvering flight.
In a variety of air suction type combined engines, the assembly power scheme of turbogenerator and wide scope punching engine is most
Future in engineering applications, but " thrust wide gap " is the biggest problem that the program is present.Current wide scope punching engine is mainly used
Dual-mode Scramjet, its work Mach number lower limit is Ma4 or so, and existing shelf turbogenerator work Mach number
The upper limit is in Ma2.5 or so, and the two is difficult to smoothly linking.Solving the Main Means of " thrust wide gap " at present has：One is to use
High-speed turbine technology and the water spray precooling skill upgrading turbogenerator work Mach number upper limit, but high-speed turbine technical difficulty pole
Height, the U.S. is by the still difficult breakthrough that studies for a long period of time, and pre- refrigeration technique of spraying water need to load substantial amounts of water and increase structure complexity；Two are
Introduce rocket engine and make up thrust deficiency, the program make it that combined engine system is more complicated, and need a variety of propellants combustions
Material.
In a variety of air suction type combined engines, the assembly power scheme of turbogenerator and wide scope punching engine is most
Future in engineering applications, but " thrust wide gap " is the biggest problem that the program is present.Current wide scope punching engine is mainly used
Dual-mode Scramjet, its work Mach number lower limit is Ma4 or so, and existing shelf turbogenerator work Mach number
The upper limit is in Ma2.5 or so, and the two is difficult to smoothly linking.Solving the Main Means of " thrust wide gap " at present has：One is to use
High-speed turbine technology and the water spray precooling skill upgrading turbogenerator work Mach number upper limit, but high-speed turbine technical difficulty pole
Height, the U.S. is by the still difficult breakthrough that studies for a long period of time, and pre- refrigeration technique of spraying water need to load substantial amounts of water and increase structure complexity；Two are
Introduce rocket engine and make up thrust deficiency, the program make it that combined engine system is more complicated, and need a variety of propellants combustions
Material.
Double combustion chamber's scramjet engine is lower than Dual-mode Scramjet work Mach number lower limit, is
Ma3.3 or so, by adjustable air intake technology, its work Mach number lower limit can be opened up further down to Ma2.5 or so, therefore turbine is sent out
The assembled scheme of motivation and double combustion chamber's scramjet engine is more conducive to solve " thrust wide gap " problem, based on shelf turbine
The assembly power scheme of engine is more feasible.
Existing double combustion chamber's scramjet engine is axial symmetry configuration, using axialsymmetrical inlet, is more suitable for axle pair
Claim layout, be difficult to that gas handling system is arranged in parallel and shared with turbine channel in terms of runner and structure design, and it is existing
Technology is using fixed geometry air intake duct, it is difficult to adapt to wider work range of Mach numbers.
The content of the invention
It is an object of the invention to overcome prior art deficiency, there is provided a kind of double combustion chamber's scramjet engine air inlet
Road, solves the technical barrier of wide scope non-axis symmetry double combustion chamber's scramjet engine air inlet.
The technical solution of the present invention：
A kind of double combustion chamber's Scramjet Inlet, the air intake duct uses two dimensional inlet configuration, and along stream
Sub- combustion runner and super burn runner are divided into by support plate, the sub- combustion passage is at least one, and the super burn runner is at least two
It is individual and divide equally in Asia combustion runner both sides；
The sub- combustion is consistent with super burn flow passage structure, is made up of fixed face, adjustable type face and connects hinge, wherein, institute
State fixed face including external pressure miniature face, contract segment type face, venturi type face, expansion segment type face, lip type face and with burning
Room connecting-type face；The adjustable type face includes contract section adjustment type face and expansion segment adjustment type face, the contract section regulation
The one end in type face and expansion segment adjustment type face is individually fixed in contract section starting point and expansion segment endpoint, and the other end is respectively activity
End, the connects hinge includes hinge a and b, and the hinge a and b is located at contract section starting point and expansion segment endpoint, and institute respectively
Stating contract section adjustment type face and expansion segment adjustment type face can be revolved respectively around the hinge a and b by the design anglec of rotation
Turn.
Further, during rotation regulation, the activity in the contract section adjustment type face and expansion segment adjustment type face
The vertical range apart from lip type face is held to remain equal.
Further, after the contract section adjustment type face and expansion segment adjustment type face rotate, the contract section regulation
Type face, contract segment type face, venturi type face, expansion segment type face and expansion segment adjustment type face surround a cavity, the shape in cavity
Into pneumatic venturi type face of the vortex as air intake duct runner, the corresponding venturi in pneumatic venturi type face is highly defined as adjustable type face
Runner venturi height H after rotationth, obtained by formula (1)：
Wherein, HthFor runner venturi height, H after the rotation of adjustable type facecHeight is captured for air intake duct runner, q (Ma) is stream
Flow function, Ma0And MathRespectively free stream Mach number and runner venturi Mach number,For discharge coefficient, σthFor runner venturi stagnation pressure
Recovery coefficient.
Further, the anglec of rotation includes the anglec of rotation θ in contract section adjustment type face7With expansion segment adjustment type face
Anglec of rotation θ8, obtained by formula (2)；
Wherein, H7For contract section adjustment type face fixing end and lip type face vertical height, H8It is solid for expansion segment adjustment type face
Fixed end and lip type face vertical height, HthFor runner venturi height, L after the rotation of adjustable type face7For contract section adjustment type face two
Distance between end points, L8For distance, θ between the two-end-point of expansion segment adjustment type face2For contract segment type face two end point connecting line and venturi type face
Between angle (taking acute angle), θ4For the angle (taking acute angle) between expansion segment type face two end point connecting line and venturi type face.
The anglec of rotation θ7And θ8For 0 ° when, contract section adjustment type face and expansion segment adjustment type face respectively with it is interior
Shrink segment type face and the laminating of expansion segment type face；
The anglec of rotation θ7And θ8During for maximum, the contract section adjustment type face and expansion segment adjustment type face are complete
Close the runner.
Further, the air intake duct fixation quasi spline is as follows：Set air intake duct and work range of Mach numbers as Mamin~
Mamax, the air intake duct fixed face is according to MamaxThe requirement of the performance indications such as discharge coefficient, total pressure recovery and MaminRise
Dynamic performance requirement is designed and obtained, this technology being known in the art.
Further, when free stream Mach number is more than MaminWhen, according to engine performance demand and the tune of Design of Inlet
Save rule, the hinge control adjustable type face rotation regulation, until free stream Mach number is Mamax。
The air intake control method of the invention that a kind of above-mentioned double combustion chamber's Scramjet Inlet is also provided, including with
Lower process：
When flight Mach number reaches the first Mach number, the contract section adjustment type face of sub- the combustion runner and super burn runner
It is close to contract segment type face and expansion segment type face respectively with expansion segment adjustment type face, subsonic combustion room and supersonic speed combustion chamber are opened
Initial point fire, the subsonic combustion room and supersonic speed combustion chamber are sub- combustion mode；
When flight Mach number reaches the second Mach number, the contract section adjustment type face of sub- the combustion runner and super burn runner and
Expansion segment adjustment type face proceeds by rotation, with the increase of flight Mach number, the interior receipts of the sub- combustion runner of control and super burn runner
Contracting section adjustment type face and the rotation of expansion segment adjustment type face so that the subsonic combustion room and supersonic speed combustion chamber are in sub- combustion
Mode；
When flight Mach number reaches the 3rd Mach number, the contract section adjustment type face of super burn runner and expansion segment adjustment type face
Stop the rotation regulation, with the increase of flight Mach number, supersonic speed combustion chamber is gradually changed from Asia combustion mode to super burn mode；
When flight Mach number reaches the 4th Mach number, supersonic speed combustion chamber is in super burn mode, completes mode transformation, with
The increase of flight Mach number, the contract section adjustment type face of super burn runner and expansion segment adjustment type face still stop, and regulation is not rotated；
When flight Mach number reaches the 5th Mach number, the contract section adjustment type face of super burn runner and expansion segment adjustment type face
Start rotation regulation, with the increase of flight Mach number so that the supersonic speed combustion chamber is in super burn mode all the time；
When flight Mach number reaches the 6th Mach number, the contract section adjustment type face of sub- the combustion runner and super burn runner and
Expansion segment adjustment type face is stopped the rotation regulation, and shown subsonic combustion room is all the time in sub- combustion mode, and supersonic speed combustion chamber begins
Super burn mode is in eventually；
Between second Mach number and the 6th Mach number, the contract section adjustment type face of the sub- combustion runner of control and expansion segment
Adjustment type face rotates so that the subsonic combustion room is all the time in sub- combustion mode.
Beneficial effects of the present invention：
1st, by the way of two dimensional inlet runner, double combustion chamber's scramjet engine non-axis symmetry configuration is solved
Air inlet problem, and can preferably be applied to parallel turbine base combined engine scheme.
2nd, the regulation measure being combined using geometry regulation and pneumatic regulation preferably resolves double combustion chamber's ultra-combustion ramjet
Engine wide scope work problem, helps to widen engine work Mach number lower limit, is adjusted while the regulation scheme has to mitigate
Many advantages, such as saving additional mass, reduction high temperature dynamic sealing demand.
3rd, air intake duct subsonic combustion room runner and supersonic speed combustion chamber runner are separately adjustable, and air intake duct is sub- to entering
The compression degree of the air-flow of velocity of sound combustion chamber is more than the air-flow for entering supersonic speed combustion chamber, is conducive to matching the respective need of combustion chamber
Ask, be easy to burning tissues, improve engine performance.
4th, intake valve deposit is realized using the existing air inlet adjustment function of combined engine, widens double combustion chamber's ultra-combustion ramjet
The work range of Mach numbers of engine, without extra increase governor motion.
Brief description of the drawings
Included accompanying drawing is used for providing being further understood from the embodiment of the present invention, which constitutes one of specification
Point, for illustrating embodiments of the invention, and the principle for the explaination present invention that comes together with word description.It should be evident that below
Accompanying drawing in description is only some embodiments of the present invention, for those of ordinary skill in the art, is not paying creation
Property work on the premise of, other accompanying drawings can also be obtained according to these accompanying drawings.
Fig. 1 is the aloof ramjet engine air inlet runner schematic layout pattern in double combustion chamber provided in an embodiment of the present invention；
Fig. 2 is the aloof punching engine flow path adjustment scheme schematic diagram in double combustion chamber in the embodiment of the present invention；
Fig. 3 is the aloof punching engine flow path adjustment parameter declaration schematic diagram in double combustion chamber in the embodiment of the present invention.
In figure, A, super burn runner；B, sub- combustion runner；C, super burn runner；1st, external pressure miniature face；2nd, contract segment type face；3、
Venturi type face；4th, expansion segment type face；5th, lip type face；6th, with combustion chamber connecting-type face；7th, contract section adjustment type face；8th, expand
Section adjustment type face；9th, hinge a；10th, hinge b；H7For the fixing end of contract section adjustment type face 7 and the vertical height of lip type face 5；H8
For the fixing end of expansion segment adjustment type face 8 and the vertical height of lip type face 5；HthThe venturi height adjusted for needed for；θ2Received to be interior
Angle (taking acute angle) between the two end point connecting line of contracting segment type face 2 and venturi type face 3；θ4For the two end point connecting line of expansion segment type face 4 with
Angle (taking acute angle) between venturi type face 3.
Embodiment
The specific embodiment of the present invention is described in detail below in conjunction with accompanying drawing.In the following description, for solution
Release and nonrestrictive purpose, elaborate detail, to help to be apparent from the present invention.However, to people in the art
It will be apparent that the present invention can also be put into practice in the other embodiments departing from these details for member.
Herein it should be noted that in order to avoid having obscured the present invention because of unnecessary details, only showing in the accompanying drawings
Gone out with according to the closely related device structure of the solution of the present invention and/or process step, and eliminate with relation of the present invention not
Big other details.
Embodiment 1
The present embodiment provides a kind of aloof ramjet engine air inlet in double combustion chamber, and Fig. 1 is provided in an embodiment of the present invention
The aloof ramjet engine air inlet runner schematic layout pattern in double combustion chamber；Fig. 2 is air intake duct flow path adjustment in the embodiment of the present invention
Scheme schematic diagram；Fig. 3 illustrates flow path adjustment parameter declaration schematic diagram.The air intake duct uses two dimensional inlet configuration, and edge
Flow direction is divided into sub- combustion runner B and super burn runner A and C by support plate, and the B runners are intermediate flow channel, connect subsonic combustion room,
A, C runner is distributed in B runners both sides connection supersonic speed combustion chamber.
Further, arranged by engine blockization, above-mentioned runner layout can also be that AABAA, ABABC, ABBC etc. are more
Plant combining form.
Any runner design of A, B, C is as follows：
The runner is made up of fixed face, adjustable type face and connects hinge, wherein, the fixed face includes external compression
Type face 1, contract segment type face 2, venturi type face 3, expansion segment type face 4, lip type face 5 and with combustion chamber connecting-type face 6；It is described
Adjustable type face includes contract section adjustment type face 7 and expansion segment adjustment type face 8, the contract section adjustment type face 7 and expansion segment
The one end in adjustment type face 8 is individually fixed in contract section starting point and expansion segment endpoint, and the other end is respectively movable end, the connection
Hinge includes hinge a9 and b10, and the hinge a9 and b10 is located at contract section starting point and expansion segment segment endpoint respectively, and described
Contract section adjustment type face 7 and expansion segment adjustment type face 8 can be carried out respectively around the hinge a9 and b10 by the design anglec of rotation
Rotation.
Further, the air intake duct fixation quasi spline is as follows：Set air intake duct and work range of Mach numbers as Mamin~
Mamax, the air intake duct fixed face is according to MamaxThe requirement of the performance indications such as discharge coefficient, total pressure recovery and MaminRise
Dynamic performance requirement is designed and obtained, this technology being known in the art.
Further, when free stream Mach number is more than MaminWhen, according to engine performance demand and the tune of Design of Inlet
Save rule, the hinge control adjustable type face rotation regulation, until free stream Mach number is Mamax。
Pass through the above-mentioned course of work so that air intake duct is in Mamin~MamaxIn the range of can reliable efficient operation, for burning
Room provides the compressed air stream for meeting the requirements such as speed, pressure, it is ensured that engine is in Mamin~MamaxIn the range of can normal work
And produce thrust performance.
Further, during rotation regulation, the work in the contract section adjustment type face 7 and expansion segment adjustment type face 8
Vertical range of the moved end apart from lip type face 5 remains equal.
Further, after the contract section adjustment type face 7 and expansion segment adjustment type face 8 rotate, the contract section is adjusted
Nodal pattern face 7, contract segment type face 2, venturi type face 3, expansion segment type face 4 and expansion segment adjustment type face 8 surround a cavity, recessed
Intracavitary formation vortex, to reduce inlet throat area, increases air intake duct shrinkage ratio as the pneumatic venturi type face of runner, and then
Increase compression to incoming air, the corresponding venturi in the pneumatic venturi type face is highly defined as air intake duct larynx after the rotation of adjustable type face
Road height Hth, obtained by formula (1)：
Wherein, HthFor runner venturi height, H after the rotation of adjustable type facecHeight is captured for air intake duct runner, q (Ma) is stream
Flow function, Ma0And MathRespectively free stream Mach number and runner venturi Mach number,For discharge coefficient, σthFor runner venturi stagnation pressure
Recovery coefficient.
Further, in low mach design conditions, such as Mamin, contract section adjustment type face 7 and expansion segment
Contract segment type face 2 and expansion segment type face 4 are close in adjustment type face 8 respectively, with the increase of free stream Mach number, then need according to next
The parameters such as Mach number, the required inlet throat Mach number of Flow coefficient of inlet and combustion chamber are flowed, are calculated by above-mentioned formula (1)
The inlet throat height of regulation needed for obtaining, then be converted to contract section adjustment type face 7 and expansion segment regulation by geometrical relationship
The angle of rotation needed for type face 8, and free stream Mach number is bigger, contract section adjustment type face 7 and the anglec of rotation of expansion segment adjustment type face 8
Degree is bigger, is formed after pneumatic venturi, inlet throat circulation area is smaller, to stronger to flow compression, is provided for combustion chamber
Desired compressed air is met, is improved beneficial to stable burning and engine performance.In addition, if necessary can be by increasing contract section
Adjustment type face 7 and the anglec of rotation in expansion segment adjustment type face 8, completely close runner.
The above-mentioned anglec of rotation includes the anglec of rotation θ in contract section adjustment type face 77With the rotation in expansion segment adjustment type face 8
Angle, θ8, obtained by formula (2)；
Wherein, H7For the fixing end of contract section adjustment type face 7 and the vertical height of lip type face 5, H8For expansion segment adjustment type face
8 fixing ends and the vertical height of lip type face 5, HthFor runner venturi height, L after the rotation of adjustable type face7For contract section adjustment type
Distance, L between the two-end-point of face 78For distance, θ between the two-end-point of expansion segment adjustment type face 82For the two end point connecting line of contract segment type face 2 with
Angle (taking acute angle) between venturi type face 3, θ4(taken for the angle between the two end point connecting line of expansion segment type face 4 and venturi type face 3
Acute angle).
The anglec of rotation θ7And θ8For 0 ° when, contract section adjustment type face 7 and expansion segment adjustment type face 8 respectively with
Contract segment type face 2 and expansion segment type face 4 are fitted；
The anglec of rotation anglec of rotation θ7And θ8During for maximum, the contract section adjustment type face 7 and expansion segment regulation
Type face 8 completely closes the runner, depending on the state is according to special duty demand.
Further, the subsonic combustion room and supersonic speed combustion chamber can be using the designs of rectangle parallel way.
The design principle of the present invention is：
It is arranged in parallel, is shared into row with turbogenerator with the aloof punching engine in double combustion chamber in view of combined engine
Gas system, while need to need to use non-with lifting body or Waverider aircraft integrated design, the aloof punching engine in double combustion chamber
Axial symmetry configuration, therefore for the nonaxisymmetrical configuration in double combustion chamber, the present invention separately designs corresponding air inlet runner, and is directed to
Each runner is designed, increase contract section adjustment type face and expansion segment adjustment type face, and controls it to rotate by hinge, in rotation
During turning, contract section adjustment type face, contract segment type face, venturi type face, expansion segment type face and expansion segment adjustment type face
A cavity can be surrounded, vortex is formed in cavity using as the pneumatic venturi type face of air inlet runner, by rationally designing interior receipts
The length in contracting segment type face, expansion segment type face and venturi type face, and cause contract section adjustment type face and contract segment type respectively
Face is consistent, and expansion segment adjustment type face is consistent with expansion segment type face length, so that contract section adjustment type face movable end and expansion
The characteristic dimension that distance of the section adjustment type face movable end along flow direction is less than vortex is opened, the characteristic dimension is obtained by CFD calculating,
And then stable vortex is formed in cavity；In addition, according to the size of the anglec of rotation, different pneumatic venturi type faces will be obtained,
And then reduce inlet throat area in this way, increase air intake duct shrinkage ratio, that is, increase the compression to incoming air,
Inlet throat circulation area is smaller, to flow, compression is stronger, is provided for combustion chamber and meets desired compressed air, is beneficial to
Stable burning and engine performance are improved.Pass through above-mentioned regulation so that air intake duct is provided the air-flow for entering subsonic combustion room
Larger compression, enters the tissue burning of subsonic combustion room after a series of wave systems with subsonic speed, to entering the ultrasonic quick burning of bimodal
The air-flow for burning room provides smaller compression, and air-flow realizes that wide scope bimodal is burnt with supersonic speed into supersonic speed combustion chamber, with this
Widen engine work range of Mach numbers, improve engine performance.
Embodiment 2
The present embodiment provides a kind of above-mentioned air intake control method of double combustion chamber's Scramjet Inlet, including：
When flight Mach number reaches the first Mach number, the contract section adjustment type face of sub- the combustion runner and super burn runner
It is close to contract segment type face and expansion segment type face respectively with expansion segment adjustment type face, subsonic combustion room and supersonic speed combustion chamber are opened
Initial point fire, maintains gross thrust to meet aircraft demand, and the subsonic combustion room and supersonic speed combustion chamber are sub- combustion mode；
When flight Mach number reaches the second Mach number, the contract section adjustment type face of sub- the combustion runner and super burn runner and
Expansion segment adjustment type face proceeds by rotation, with the increase of flight Mach number, the interior receipts of the sub- combustion runner of control and super burn runner
Contracting section adjustment type face and the rotation of expansion segment adjustment type face so that the subsonic combustion room and supersonic speed combustion chamber are in sub- combustion
Mode；
When flight Mach number reaches the 3rd Mach number, the contract section adjustment type face of super burn runner and expansion segment adjustment type face
Stop the rotation regulation, with the increase of flight Mach number, supersonic speed combustion chamber is gradually changed from Asia combustion mode to super burn mode；
When flight Mach number reaches the 4th Mach number, supersonic speed combustion chamber is in super burn mode, completes mode transformation, with
The increase of flight Mach number, the contract section adjustment type face of super burn runner and expansion segment adjustment type face still stop, and regulation is not rotated；
When flight Mach number reaches the 5th Mach number, the contract section adjustment type face of super burn runner and expansion segment adjustment type face
Start rotation regulation, with the increase of flight Mach number so that the supersonic speed combustion chamber is in super burn mode all the time；
When flight Mach number reaches the 6th Mach number, this is engine maximum functional Mach number, and runner is fired and super in the Asia
The contract section adjustment type face and expansion segment adjustment type face for firing runner are stopped the rotation regulation, and shown subsonic combustion room is located all the time
Mode is fired in Asia, supersonic speed combustion chamber is in super burn mode all the time；
Between second Mach number and the 6th Mach number, the contract section adjustment type face of the sub- combustion runner of control and expansion segment
Adjustment type face rotates so that the subsonic combustion room is all the time in sub- combustion mode.
It is described so that the subsonic combustion room and supersonic speed combustion chamber refer to so that the Asia in sub- combustion mode all the time
Runner and the corresponding postrotational venturi Mach number of super burn runner is fired to be in 1.2~1.5 scopes all the time；
It is described so that the supersonic speed combustion chamber refers to all the time in super burn mode so that the corresponding rotation of the super burn runner
Venturi Mach number after turning is in 9/20~11/20 scope of flight Mach number all the time；
The first Mach 2 ship Mamin；For punching engine start-up operation Mach number, the venturi horse of its corresponding runner
Conspicuous number is Ma-th1；
The second Mach 2 ship Ma-2, its correspondence venturi Mach number Ma-th2, the Ma-th2 are more than threshold value MaΔ1, institute
State MaΔ1 preferred scope is 1.2~1.5；
The 3rd Mach 2 ship Ma-3, the 4th Mach 2 ship Ma-4, Ma-3 and Ma-4 and between realize supersonic speed
Combustion chamber is from Asia combustion transformation of the mode to super burn mode, and the 3rd Mach number is according to its corresponding venturi Mach number Ma-
Th3, the 4th Mach number Ma-4 and its correspondence venturi Mach number Ma-th4 are determined；Specifically, according to the 4th Mach number Ma-4 and
Venturi Mach number Ma-th4 can draw the anglec of rotation by formula (1) and (2), and Ma- can be drawn by the anglec of rotation and Ma-th3
3；
The 4th Mach number Ma-4 preferred scopes are 5.5-6, and its corresponding venturi Mach number Ma-th4 is 9/20~11/
20Ma-4；
The 5th Mach 2 ship Ma-5, its correspondence venturi Mach number Ma-th5, the Ma-th5 are more than threshold value MaΔ2, institute
State MaΔ2 be 11/20Ma-5；
The 6th Mach 2 ship Mamax, punching engine maximum functional Mach number.
Unspecified part of the present invention is known to the skilled person technology.
Claims (10)
1. a kind of double combustion chamber's Scramjet Inlet, it is characterised in that：The air intake duct uses two dimensional inlet structure
Type, and sub- combustion runner and super burn runner are divided into by support plate along flow direction, the sub- combustion passage is at least one, the super burn runner
At least two and divide equally in Asia combustion runner both sides；
The sub- combustion is consistent with super burn flow passage structure, is made up of fixed face, adjustable type face and connects hinge, wherein, it is described solid
Sizing face includes external pressure miniature face, contract segment type face, venturi type face, expansion segment type face, lip type face and connected with combustion chamber
Direct type face；The adjustable type face includes contract section adjustment type face and expansion segment adjustment type face, the contract section adjustment type face
Contract section starting point and expansion segment endpoint are individually fixed in the one end in expansion segment adjustment type face, the other end is respectively movable end,
The connects hinge includes hinge a and b, and the hinge a and b is located at contract section starting point and expansion segment endpoint respectively, and described
Contract section adjustment type face and expansion segment adjustment type face can be rotated respectively around the hinge a and b by the design anglec of rotation.
2. a kind of double combustion chamber's Scramjet Inlet according to claim 1, it is characterised in that the interior receipts
Behind contracting section adjustment type face and the rotation of expansion segment adjustment type face, the contract section adjustment type face, contract segment type face, venturi type
Face, expansion segment type face and expansion segment adjustment type face surround a cavity, and vortex is formed in cavity as the gas of air intake duct runner
Dynamic venturi type face, the corresponding venturi in the pneumatic venturi type face is highly defined as runner venturi height H after the rotation of adjustable type faceth, lead to
Formula (1) is crossed to obtain：
Wherein, HthFor runner venturi height, H after the rotation of adjustable type facecHeight is captured for air intake duct runner, q (Ma) is flow letter
Number, Ma0And MathRespectively free stream Mach number and runner venturi Mach number,For discharge coefficient, σthFor runner venturi total pressure recovery
Coefficient.
3. a kind of double combustion chamber's Scramjet Inlet according to claim 2, it is characterised in that in the hinge
During chain rotation regulation, movable end the hanging down apart from lip type face in the contract section adjustment type face and expansion segment adjustment type face
Straight distance remains equal.
4. a kind of double combustion chamber's Scramjet Inlet according to claim 3, it is characterised in that the rotation
Angle includes the anglec of rotation θ in contract section adjustment type face7With the anglec of rotation θ in expansion segment adjustment type face8, obtained by formula (2)
Arrive；
Wherein, H7For contract section adjustment type face fixing end and lip type face vertical height, H8For expansion segment adjustment type face fixing end
With lip type face vertical height, HthFor runner venturi height, L after the rotation of adjustable type face7For contract section adjustment type face two-end-point
Between distance, L8For distance, θ between the two-end-point of expansion segment adjustment type face2For between contract segment type face two end point connecting line and venturi type face
Sharp angle, θ4For the sharp angle between expansion segment type face two end point connecting line and venturi type face.
5. a kind of double combustion chamber's Scramjet Inlet according to claim 4, it is characterised in that the rotation
Angle, θ7And θ8For 0 ° when, contract section adjustment type face and expansion segment adjustment type face respectively with contract segment type face and expansion
Fit in segment type face；The anglec of rotation θ7And θ8During for maximum, contract section adjustment type face and expansion segment adjustment type face with
The runner is closed to be defined.
6. a kind of double combustion chamber's Scramjet Inlet according to claim 5, it is characterised in that the sub- combustion
Runner is B runners, and the super burn runner is respectively A, C runner, and its runner layout is selected from ABC, AABAA, ABABC, ABBC group
Any of conjunction form, wherein A runners are identical with C runners.
7. a kind of double combustion chamber's Scramjet Inlet air inlet controlling party according to claim any one of 1-6
Method, it is characterised in that including procedure below：
When flight Mach number reaches the first Mach number, the contract section adjustment type face of sub- the combustion runner and super burn runner and expansion
Open section adjustment type face and be close to contract segment type face and expansion segment type face, subsonic combustion room and supersonic speed combustion chamber starting point respectively
Fire, the subsonic combustion room and supersonic speed combustion chamber are sub- combustion mode；
When flight Mach number reaches the second Mach number, the contract section adjustment type face of sub- the combustion runner and super burn runner and expansion
Section adjustment type face proceeds by rotation, with the increase of flight Mach number, the contract section of the sub- combustion runner of control and super burn runner
Adjustment type face and the rotation of expansion segment adjustment type face so that the subsonic combustion room and supersonic speed combustion chamber are in sub- combustion mould
State；
When flight Mach number reaches the 3rd Mach number, the contract section adjustment type face of super burn runner and expansion segment adjustment type face stop
Rotation regulation, with the increase of flight Mach number, supersonic speed combustion chamber is gradually changed from Asia combustion mode to super burn mode；
When flight Mach number reaches the 4th Mach number, supersonic speed combustion chamber is in super burn mode, mode transformation is completed, with flight
The increase of Mach number, the contract section adjustment type face of super burn runner and expansion segment adjustment type face still stop, and regulation is not rotated；
When flight Mach number reaches the 5th Mach number, the contract section adjustment type face of super burn runner and expansion segment adjustment type face start
Rotation regulation, with the increase of flight Mach number so that the supersonic speed combustion chamber is in super burn mode all the time；
When flight Mach number reaches the 6th Mach number, the contract section adjustment type face of sub- the combustion runner and super burn runner and expansion
Section adjustment type face is stopped the rotation regulation, and mode is fired in shown subsonic combustion room in sub- all the time, and supersonic speed combustion chamber is located all the time
In super burn mode；
Between second Mach number and the 6th Mach number, the contract section adjustment type face of the sub- combustion runner of control and expansion segment regulation
Type face rotates so that the subsonic combustion room is all the time in sub- combustion mode.
8. method according to claim 7, it is characterised in that also including at least one in following technical characteristic：
The first Mach 2 ship Mamin；The venturi Mach 2 ship Ma-th1 of its corresponding runner；
The second Mach 2 ship Ma-2, its correspondence venturi Mach number Ma-th2, the Ma-th2 are more than threshold value MaΔ1, it is described
MaΔ1 preferred scope is 1.2~1.5；
The 3rd Mach 2 ship Ma-3, the 4th Mach 2 ship Ma-4, Ma-3 and Ma-4 and between realize supersonic combustion
Room is from Asia combustion transformation of the mode to super burn mode, and the 3rd Mach number is according to its corresponding venturi Mach number Ma-th3, the
Four Mach number Ma-4 are determined with its correspondence venturi Mach number Ma-th4.
The 4th Mach number Ma-4 preferred scopes are 5.5-6, and its corresponding venturi Mach number Ma-th4 is 9/20~11/
20Ma-4；
The 5th Mach 2 ship Ma-5, its correspondence venturi Mach number Ma-th5, the Ma-th5 are more than threshold value MaΔ2, it is described
MaΔ2 be 11/20Ma-5；
The 6th Mach 2 ship Mamax, engine maximum functional Mach number.
9. method according to claim 8, it is characterised in that described so that the subsonic combustion room is all the time in sub- combustion
Mode refers to so that the corresponding postrotational venturi Mach number of the sub- combustion runner is in 1.1~1.5 scopes all the time.
10. method according to claim 9, it is characterised in that described so that the supersonic speed combustion chamber is all the time in super
Combustion mode refer to cause the corresponding postrotational venturi Mach number of the super burn runner all the time in flight Mach number 9/20~
In 11/20 scope.
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| CN107605601A (en) * | 2017-09-29 | 2018-01-19 | 南京航空航天大学 | A kind of Supersonic Inlet for capturing area and being adjusted in synchronism with throat area |
| CN108317541A (en) * | 2018-02-26 | 2018-07-24 | 中国科学院力学研究所 | A kind of punching engine |
| CN108592085A (en) * | 2018-03-09 | 2018-09-28 | 西北工业大学 | A kind of change geometry supersonic speed combustion chamber |
| CN108825381A (en) * | 2018-06-22 | 2018-11-16 | 西北工业大学 | A kind of rocket based combined cycle engine surface compression change geometry air intake duct |
| CN109098859A (en) * | 2018-08-13 | 2018-12-28 | 厦门大学 | A kind of hypersonic interior Parallet three-way valve road intake valve deposit mechanism design method |
| CN109667670A (en) * | 2019-01-24 | 2019-04-23 | 南京航空航天大学 | A kind of adjustable valve arrangement of whirlpool control that super/hypersonic two dimensional inlet of auxiliary starts |
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| CN109667670A (en) * | 2019-01-24 | 2019-04-23 | 南京航空航天大学 | A kind of adjustable valve arrangement of whirlpool control that super/hypersonic two dimensional inlet of auxiliary starts |
| CN114427496A (en) * | 2020-10-29 | 2022-05-03 | 南京理工大学 | Variable-geometry supersonic air inlet channel device with flow discharge channel |
| CN114427496B (en) * | 2020-10-29 | 2023-07-25 | 南京理工大学 | Variable-geometry supersonic air inlet device with leakage channel |
| CN113700560A (en) * | 2021-09-24 | 2021-11-26 | 西安航天动力研究所 | Half membrane upset supersonic speed adjustable intake duct |
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