CN107013367B - Turbine base double combustion chamber's punching press combined cycle engine - Google Patents
Turbine base double combustion chamber's punching press combined cycle engine Download PDFInfo
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- CN107013367B CN107013367B CN201710086643.6A CN201710086643A CN107013367B CN 107013367 B CN107013367 B CN 107013367B CN 201710086643 A CN201710086643 A CN 201710086643A CN 107013367 B CN107013367 B CN 107013367B
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 146
- 238000004080 punching Methods 0.000 title claims abstract description 55
- 238000000034 method Methods 0.000 claims description 9
- 102100040255 Tubulin-specific chaperone C Human genes 0.000 claims description 6
- 108010093459 tubulin-specific chaperone C Proteins 0.000 claims description 6
- 238000011084 recovery Methods 0.000 claims description 5
- 230000008569 process Effects 0.000 claims description 4
- 239000007787 solid Substances 0.000 claims description 2
- 238000004513 sizing Methods 0.000 claims 1
- 230000006835 compression Effects 0.000 abstract description 9
- 238000007906 compression Methods 0.000 abstract description 9
- 238000005516 engineering process Methods 0.000 description 9
- CNKHSLKYRMDDNQ-UHFFFAOYSA-N halofenozide Chemical compound C=1C=CC=CC=1C(=O)N(C(C)(C)C)NC(=O)C1=CC=C(Cl)C=C1 CNKHSLKYRMDDNQ-UHFFFAOYSA-N 0.000 description 7
- 230000001154 acute effect Effects 0.000 description 6
- 238000010586 diagram Methods 0.000 description 6
- 230000008901 benefit Effects 0.000 description 4
- 230000001276 controlling effect Effects 0.000 description 4
- 230000008450 motivation Effects 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 230000006870 function Effects 0.000 description 3
- 210000000867 larynx Anatomy 0.000 description 3
- 239000000243 solution Substances 0.000 description 3
- 230000008859 change Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000003134 recirculating effect Effects 0.000 description 2
- 230000009466 transformation Effects 0.000 description 2
- 230000002902 bimodal effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010304 firing Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 230000035800 maturation Effects 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 230000000116 mitigating effect Effects 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
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- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Classifications
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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
- F02K7/16—Composite ram-jet/turbo-jet engines
-
- 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
- F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/042—Air intakes for gas-turbine plants or jet-propulsion plants having variable geometry
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/057—Control or regulation
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/06—Varying effective area of jet pipe or nozzle
- F02K1/15—Control or regulation
- F02K1/16—Control or regulation conjointly with another control
- F02K1/165—Control or regulation conjointly with another control with air intake control
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Geometry (AREA)
- Supercharger (AREA)
Abstract
It is an object of the invention to overcome the shortage of prior art, a kind of turbine base double combustion chamber's punching press combined cycle engine is provided, solving existing turbo ramjet engine cannot be compared with low mach relay the problems such as.The present invention is improved first against double combustion chamber's punching engine, combustion chamber uses rectangle parallel configuration, and it is improved for its air intake duct, the air intake duct uses two dimensional inlet configuration, and sub- combustion runner and super burn runner are divided by support plate along flow direction, the sub- combustion channel 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, realize needs of each combustion chamber to different compression degree air, widen engine work range of Mach numbers, improve engine performance.
Description
Technical field
The invention belongs to aerospace technical field of engines, and in particular to turbine base double combustion chamber punching press combination cycle hair
Motivation.
Background technology
Near space hypersonic flight task, empty day aerial mission etc. are to having wide spatial domain, wide fast domain ability to work
High-performance novel power proposes urgent demand, and the rocket engine of technology maturation, turbogenerator and punching engine are each
It is advantageous, but all can not individually complete above-mentioned task.It, at present can be with above-mentioned three kinds of engine technologies to adapt to the mission requirements
Based on form new thermodynamic cycle scheme, to widen working range, then develop out turboram combination (TBCC, Turbo
Based Combined Cycle), the combined engines scheme such as TRIJET.
There are still following defects for above-mentioned TBCC, TRIJET combined engine：TBCC, can not by high speed turbine limitation of the technology
Realize the fine relay with dual-mode scramjet.It is domestic in the recent period to propose to intend building parallel connection TBCC schemes using active service turbine,
It is quasi- that relay is solved the problems, such as by Rocket ejector pushing or water spray precooling etc., but system complexity and quality cost can be increased in this way.
TRIJET is used by introducing injection punching engine, realizes pushing away between active service turbogenerator and dual-mode scramjet
Power is connected, but due to using triple channel structure, faces system complex, the problems such as architecture quality is big.
Double combustion chamber's punching engine is lower than Dual-mode Scramjet work Mach number lower limit, is Ma3.3 left
The right side, by adjustable air intake technology, work Mach number lower limit can be opened up further down to Ma2.5 or so, thus turbogenerator with
The assembled scheme of double combustion chamber's punching engine is more conducive to solve " thrust wide gap " problem, the group based on shelf turbogenerator
It is more feasible to close power scheme.However existing double combustion chamber's punching engine is axial symmetry configuration, using axialsymmetrical inlet, more
It is laid out suitable for axial symmetry, is difficult to realize be arranged in parallel with turbine channel in terms of runner and structure design and shares air inlet system
System, and the prior art is using fixed geometry air intake duct, it is difficult to adapt to wider work range of Mach numbers.
Invention content
It is an object of the invention to overcome the shortage of prior art, a kind of turbine base double combustion chamber punching press combination cycle hair is provided
Motivation, solving existing turbo ramjet engine cannot be compared with low mach relay the problems such as.
Technical solution of the invention：
Turbine base double combustion chamber's punching press combined cycle engine, including high-speed channel and slow channels, the high-speed channel
It is arranged in parallel with slow channels, and it includes double combustion chamber's punching engine, institute to share air intake duct and jet pipe, the high-speed channel
It includes turbine core engine to state slow channels, and double combustion chamber's punching engine includes double combustion chamber's ram air duct, subsonic speed
Combustion chamber and supersonic speed combustion chamber, and the subsonic combustion room and supersonic speed combustion chamber use rectangle parallel configuration；
The ram air duct uses two dimensional inlet configuration, and is divided into sub- combustion runner and super burn stream by support plate along flow direction
Road, the sub- combustion runner are at least one and are connected with subsonic combustion room, the super burn runner at least two and respectively exist
Asia combustion runner both sides, the super burn runner are separately connected supersonic speed combustion chamber；
The sub- combustion is consistent with super burn flow passage structure：It is made of fixed face, adjustable type face and connects hinge, wherein institute
State fixed face include 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, and the contract section is adjusted
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 include hinge a and b, and the hinge a and b is located at contract section starting point and expansion segment endpoint, and institute
Contract section adjustment type face and expansion segment adjustment type face is stated to be revolved by design rotation angle respectively around the hinge a and b
Turn.
Further, in rotating adjustment process, 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 is adjusted
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
Pneumatic venturi type face at vortex as runner, after the corresponding venturi height in the pneumatic venturi type face is defined as the rotation of adjustable type face
The venturi height H of runnerth, obtained by formula (1)：
Wherein, HthRunner venturi height after being rotated for adjustable type face, HcHeight is captured for air intake duct runner, q (Ma) is stream
Flow function, Ma0And MathRespectively free stream Mach number and air intake duct runner venturi Mach number,For discharge coefficient, σthFor runner larynx
Road total pressure recovery coefficient.
Further, the rotation angle includes the rotation angle θ in contract section adjustment type face7With expansion segment adjustment type face
Rotation angle 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, HthRunner venturi height after being rotated for adjustable type face, L7For contract section adjustment type face two
Distance between endpoint, L8The distance between the two-end-point of expansion segment adjustment type face, θ2For 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 rotation angle θ7And θ8When being 0 °, the contract section adjustment type face and expansion segment adjustment type face respectively with it is interior
It shrinks segment type face and expansion segment type face paste is closed；
The rotation angle θ7And θ8For maximum value when, the contract section adjustment type face and expansion segment adjustment type face are complete
Close the runner.
Further, the slow channels and high-speed channel also share air intake duct, are equipped in the air intake duct for controlling
The air inlet flow distribution plate of the turbine core engine and double combustion chamber's punching engine charge air flow distribution.
Further, in the high-speed channel and the slow channels intersection institute is controlled equipped with hinge c, the hinge c
It states air inlet flow distribution plate to rotate between the slow channels and high-speed channel, rotation angle range is can completely close high-speed channel
Or the principles of slow channels determines.
Further, the slow channels and high-speed channel also common nozzle, the jet pipe is interior to be equipped with for controlling
State the exhaust controllable register of turbogenerator and double combustion chamber's punching engine gas discharge.
Further, the slow channels end is equipped with hinge d, the hinge adjacent to a line position of air stream outlet
Chain d controls the exhaust controllable register and is rotated between the slow channels and high-speed channel.
Further, the flow distribution plate and the exhaust controllable register coordinative role close institute in the air inlet flow distribution plate
While stating turbine core engine, the exhaust controllable register, which is gone to, closes the slow channels side.
Further, the turbine core engine can be turbogenerator or series connection TBCC engines.
Further, it is as follows to fix quasi spline for the runner：Set double combustion chamber's ram air duct work Mach number model
It encloses for Mamin~Mamax, runner fixed face is according to MamaxThe performance indicators such as discharge coefficient, total pressure recovery require and
MaminStarting performance Demand Design and obtain, this technology being known in the art.
Further, when free stream Mach number is more than MaminWhen, according to the adjusting of engine performance demand and runner design
Rule, hinge control adjustable type face rotation is adjusted, until free stream Mach number is Mamax。
The present invention compared with the existing technology the characteristics of and advantage：
Turbine base provided by the invention double combustion chamber's punching press combined cycle engine, first to double combustion chamber's punching engine
It is improved, including the change of chamber structure and the change of combustion chamber charge runner, a kind of nonaxisymmetrical double combustions is provided
Room engine and matched runner configuration are burnt, and then is realized turbogenerator and double combustion chamber's punching engine very
The characteristics of good integration, fast domain wide using double combustion chamber's punching engine, and further widen work range of Mach numbers, can compared with
Under the conditions of low mach steady operation and have high thrust performance, realize itself and the steady relay of turbogenerator.
To sum up：
1, a kind of nonaxisymmetrical double combustion chamber's punching engine is provided, by the way of two dimensional inlet runner, solution
The air inlet problem of the double combustion chambers Jue Liao punching engine non-axis symmetry configuration, and can preferably be applied to parallel turbine base combination hair
Motivation scheme.
2, it adjusts using geometry and pneumatically adjusts the regulation measure being combined and preferably resolve double combustion chamber's punching press and start
Machine width range work problem helps to widen engine work Mach number lower limit, while the regulation scheme has mitigation adjusting attached
Add quality, reduce many advantages, such as high temperature dynamic sealing demand.
3, subsonic combustion room runner and supersonic speed combustion chamber runner are separately adjustable, and to entering subsonic combustion room
The compression degree of air-flow is more than the air-flow into supersonic speed combustion chamber, is conducive to the respective demand for matching combustion chamber, convenient for burning
Tissue improves engine performance.
4, it realizes intake valve deposit using the existing air inlet adjustment function of combined engine, widens double combustion chamber's punching press and start
The work range of Mach numbers of machine increases regulating mechanism without additional.
5, engine quality can effectively be mitigated by sharing inlet and exhaust system, and engine is averagely had an high regard for relatively high.
Description of the drawings
Included attached drawing is used for providing being further understood from the embodiment of the present invention, and which constitute one of specification
Point, for illustrating the embodiment of the present invention, and come together with verbal description to illustrate the principle of the present invention.It should be evident that below
Attached drawing in description is only some embodiments of the present invention, for those of ordinary skill in the art, is not paying creation
Property labour under the premise of, other drawings may also be obtained based on these drawings.
Fig. 1 is that the cross-section structure of turbine base provided in an embodiment of the present invention double combustion chamber's punching press combined cycle engine is illustrated
Figure；
Fig. 2 is punching engine structural schematic diagram in double combustion chamber's provided in an embodiment of the present invention；
Fig. 3 is double combustion chamber's ram air duct runner schematic layout pattern in the embodiment of the present invention；
Fig. 4 is double combustion chamber's punching engine flow path adjustment scheme schematic diagram in the embodiment of the present invention；
Fig. 5 is double combustion chamber's punching engine flow path adjustment parameter declaration schematic diagram in the embodiment of the present invention；
Fig. 6 is inlet structure schematic diagram in the embodiment of the present invention；
Fig. 7 is jet pipe structural schematic diagram in the embodiment of the present invention.
In figure, 1, air intake duct；2, turbogenerator；3, double combustion chamber's punching engine；4, jet pipe；5, double combustion chamber rushes
It is pressed into air flue；6, subsonic combustion room；7, supersonic speed combustion chamber；6' subsonic combustions room cavity；7', supersonic speed combustion chamber are recessed
Chamber；8, air inlet flow distribution plate；9, it is vented controllable register；A, super burn runner；B, sub- combustion runner；C, super burn runner；11, external pressure miniature
Face；12, contract segment type face；13, venturi type face；14, expansion segment type face；15, lip type face；16, with combustion chamber connecting-type face；
17, contract section adjustment type face；18, expansion segment adjustment type face；21, hinge a；22, hinge b；23, hinge c；24, hinge d；H7
For 17 fixing end of contract section adjustment type face and 15 vertical height of lip type face；H8For 18 fixing end of expansion segment adjustment type face and lip
15 vertical height of shape of the mouth as one speaks face；HthFor the required venturi height adjusted；HcHeight is captured for air intake duct runner；θ2For contract section
Angle (taking acute angle) between 12 two end point connecting line of type face and venturi type face 13；θ4For 14 two end point connecting line of expansion segment type face and larynx
Angle (taking acute angle) between channel type face 13.
Specific implementation mode
Specific embodiments of the present invention are described in detail below in conjunction with attached drawing.In the following description, for solution
Purpose and not restrictive is released, elaborates 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.
It should be noted that in order to avoid having obscured the present invention because of unnecessary details, only show in the accompanying drawings
The device structure closely related with scheme according to the present invention and/or processing step are gone out, and have been omitted with relationship of the present invention not
Big other details.
Embodiment 1
The present embodiment provides a kind of turbine base double combustion chamber's punching press combined cycle engines.Fig. 1 shows its cross-section structure,
Its structure includes air intake duct 1, turbogenerator 2, double combustion chamber's punching engine 3 and jet pipe 4, wherein in 1 He of air intake duct
Channel between jet pipe 4 where turbogenerator 2 constitutes slow channels, double burnings between air intake duct 1 and the jet pipe 4
Channel where room punching engine 3 constitutes high-speed channel.
Slow channels and high-speed channel are connected in parallel, and this parallel relationship can be in parallel up and down, can also be left and right
Parallel connection, Fig. 1 show a kind of parallel way of slow channels in upper, high-speed channel under.
Further, Fig. 2 shows the structural schematic diagrams of double combustion chamber's punching engine, including double combustion chamber's punching press air inlet
Road 5, subsonic combustion room 6 and supersonic speed combustion chamber 7, and the subsonic combustion room 6 and supersonic speed combustion chamber 7 use rectangle simultaneously
Connection layout, Fig. 3 show the concrete structure of above-mentioned double combustion chamber's ram air duct 5：
Double combustion chamber's ram air duct 5 uses two dimensional inlet configuration, and is divided into sub- combustion stream by support plate along flow direction
Road B and super burn runner A and C, the B runners are intermediate flow channel, connect subsonic combustion room, and A, C runner is distributed in B streams
Road both sides are simultaneously separately connected supersonic speed combustion chamber.
Further, it is arranged by engine blockization, above-mentioned runner layout can also be that AABAA, ABABC, ABBC etc. are more
Kind combining form.
Preferably, the middle and back of the subsonic combustion room 6 is provided with subsonic combustion room cavity 6', the ultrasound quick burning
The inlet for burning room 7 is provided with supersonic speed combustion chamber cavity 7'；
Low speed recirculating zone is formed inside the subsonic combustion room cavity 6', for stablizing flame, and the infrasound quick burning
Burn the Fuel-rich gas and feed the low speed that the fuel oil of supersonic speed combustion chamber 7 is formed in supersonic speed combustion chamber cavity 7' that room 6 is formed
The second-time burning of recirculating zone inner tissue.
The arbitrary runner design of A, B, C is as follows, referring specifically to Fig. 4：
The runner is made of fixed face, adjustable type face and connects hinge, wherein the fixed face includes external compression
Type face 11, contract segment type face 12, venturi type face 13, expansion segment type face 14, lip type face 15 and with combustion chamber connecting-type face
16；The adjustable type face includes contract section adjustment type face 17 and expansion segment adjustment type face 18, the contract section adjustment type face
17 and expansion segment adjustment type face 18 one end be individually fixed in contract section starting point and expansion segment endpoint, the other end be respectively activity
End, the connects hinge includes hinge a21 and b22, and the hinge a21 and b22 is located at contract section starting point and expansion segment
Segment endpoint, and the contract section adjustment type face 17 and expansion segment adjustment type face 18 can be pressed respectively around the hinge a21 and b22
Design rotation angle is rotated.
Further, it is as follows to fix quasi spline for the runner：Set double combustion chamber's ram air duct work Mach number model
It encloses for Mamin~Mamax, runner fixed face is according to MamaxThe performance indicators such as discharge coefficient, total pressure recovery require and
MaminStarting performance Demand Design and obtain, 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
Rule is saved, hinge control adjustable type face rotation is adjusted, until free stream Mach number is Mamax。
Pass through the above-mentioned course of work so that double combustion chamber's ramjet engine air inlet is in Mamin~MamaxEnergy can in range
By efficient operation, the compressed air stream for meeting the requirements such as speed, pressure is provided for combustion chamber, it is ensured that engine is in Mamin~MamaxModel
Enclosing interior equal can work normally and generate thrust performance.
Further, in rotating adjustment process, the contract section adjustment type face 17 and expansion segment adjustment type face 18
Vertical range of the movable end apart from lip type face 15 remains equal.
Further, referring to Figure 4 and 5, after the contract section adjustment type face 17 and expansion segment adjustment type face 18 rotate, institute
State contract section adjustment type face 17, contract segment type face 12, venturi type face 13, expansion segment type face 14 and expansion segment adjustment type face 18
A cavity is surrounded, forms pneumatic venturi type face of the vortex as runner in cavity, to reduce inlet throat area, is increased
Air intake duct shrinkage ratio, and then increase the compression to incoming air, the corresponding venturi height in the pneumatic venturi type face is defined as adjustable
Runner venturi height H after the rotation of type faceth, obtained by formula (1)：
Wherein, HthRunner venturi height after being rotated for adjustable type face, HcHeight 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, the contract section adjustment type face 17 and expansion segment
Contract segment type face 12 and expansion segment type face 14 are close in adjustment type face 18 respectively, with the increase of free stream Mach number, then need root
According to parameters such as free stream Mach number, the required inlet throat Mach numbers of Flow coefficient of inlet and combustion chamber, by above-mentioned formula (1)
The inlet throat height adjusted needed for being calculated, then be converted to contract section adjustment type face 17 and expansion segment by geometrical relationship
The angle rotated needed for adjustment type face 18, and free stream Mach number is bigger, contract section adjustment type face 17 and expansion segment adjustment type face
18 rotation angles are bigger, and after forming pneumatic venturi, inlet throat circulation area is smaller, stronger to incoming compression, for combustion
It burns room and the compressed air met the requirements is provided, be conducive to stablize burning and engine performance improves.In addition, increase can be passed through when necessary
The rotation angle in contract section adjustment type face 17 and expansion segment adjustment type face 18, completely closes runner.
Above-mentioned rotation angle includes the rotation angle θ in contract section adjustment type face 177With the rotation in expansion segment adjustment type face 18
Gyration θ8, obtained by formula (2)；
Wherein, H7For 17 fixing end of contract section adjustment type face and 15 vertical height of lip type face, H8For expansion segment adjustment type
18 fixing end of face and 15 vertical height of lip type face, HthRunner venturi height after being rotated for adjustable type face, L7For contract section tune
Distance between 17 two-end-point of nodal pattern face, L8The distance between 18 two-end-point of expansion segment adjustment type face, θ2For 12 two-end-point of contract segment type face
Angle (taking acute angle) between line and venturi type face 13, θ4Between 14 two end point connecting line of expansion segment type face and venturi type face 13
Angle (taking acute angle).
The rotation angle θ7And θ8When being 0 °, the contract section adjustment type face 17 and expansion segment adjustment type face 18 are distinguished
It is bonded with contract segment type face 12 and expansion segment type face 14；
The rotation angle rotation angle θ7And θ8For maximum value when, the contract section adjustment type face 17 and expansion segment tune
Nodal pattern face 18 completely closes the runner, and the state is depending on special duty demand.
Further, slow channels and high-speed channel also share air intake duct 1, are equipped in air intake duct 1 for controlling turbine hair
The air inlet flow distribution plate 8 of motivation 2 and the distribution of 3 charge air flow of double combustion chamber's punching engine, shared air intake duct are conducive to reduce entire
The quality and volume of engine.
As shown in fig. 6, being equipped with hinge c23 in high-speed channel and slow channels intersection, hinge c23 controls air inlet flow distribution plate
8 rotate between double combustion chamber's punching engine 3 and turbogenerator 2, and rotation angle range is can completely close high speed
The principles of channel or slow channels determines.Shape, the size of air inlet flow distribution plate 8 are big according to high-speed channel or slow channels entrance
Small, shape determines.
Further, slow channels and high-speed channel also common nozzle 4,4 are equipped with for controlling propeller for turboprop in jet pipe
The exhaust controllable register 9 of machine 2 and the discharge of 3 gas of double combustion chamber's punching engine.
As shown in fig. 7, slow channels end is equipped with hinge d24, hinge d24 adjacent to a line position of air stream outlet
Control exhaust controllable register 9 rotates between the slow channels and high-speed channel.
Further, air inlet flow distribution plate 8 and exhaust 9 coordinative role of controllable register, the turbine is closed in air inlet flow distribution plate 8
While engine 2, the exhaust controllable register 9, which is gone to, closes the slow channels side.
Further, the initial position of air inlet flow distribution plate 8 is in while opening the state of high-speed channel and slow channels, this
When slow channels and high-speed channel open simultaneously, large quantity of air enters slow channels, and a small amount of air enters high-speed channel, to drop
The resistance of low high-speed channel near exit.Air inlet flow distribution plate 8 simultaneously can at the uniform velocity rotate upwards, downwards using hinge as rotation center,
Final position, which is in, closes slow channels state.
Above-mentioned turbine base double combustion chamber's punching press combined cycle engine control method includes：
When aircraft takes off from ground, the air inlet flow distribution plate is in while opening the position of slow channels and high-speed channel
It sets, air respectively enters slow channels and high-speed channel after air intake duct compresses, and is distributed to by the location determination of air inlet flow distribution plate
The air mass flow of slow channels and high-speed channel, the turbogenerator start work, and high-speed channel keeps open position, reduces
Air intake duct and aircraft tail portion resistance, exhaust controllable register is located at jet pipe centre position, in each runner of ram air duct
Contract section adjustment type face and expansion segment adjustment type face respectively with contract segment type face and expansion segment type face paste close；
When flight Mach number reaches the first Mach number, air inlet flow distribution plate moves up, and closes slow channels, the sub- combustion
Contract segment type face and expansion segment are close in the contract section adjustment type face and expansion segment adjustment type face of runner and super burn runner respectively
Type face, subsonic combustion room and supersonic speed combustion chamber start to light a fire, and gross thrust is maintained to meet aircraft demand, the infrasound quick burning
It is sub- combustion mode to burn room and supersonic speed combustion chamber；When air inlet flow distribution plate goes to the position of closing slow channels, turbogenerator
It is stopped, exhaust controllable register, which is rotated upwardly into, closes slow channels outlet, and mode relay is completed；
When flight Mach number reaches the second Mach number, the contract section adjustment type face of the sub- combustion runner and super burn runner and
Expansion segment adjustment type face proceeds by rotation, with the increase of flight Mach number, controls the interior receipts of sub- combustion runner 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 third Mach number, the contract section adjustment type face and expansion segment adjustment type face of super burn runner
It stops rotating adjusting, with the increase of flight Mach number, supersonic speed combustion chamber gradually changes 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 and expansion segment adjustment type face of super burn runner still stop, and do not rotate adjusting；
When flight Mach number reaches the 5th Mach number, the contract section adjustment type face and expansion segment adjustment type face of super burn runner
Start rotation to adjust, with the increase of flight Mach number so that the supersonic speed combustion chamber is in super burn mode always；
When flight Mach number reaches the 6th Mach number, this is engine maximum functional Mach number, and the Asia is fired runner and surpassed
The contract section adjustment type face and expansion segment adjustment type face for firing runner are stopped rotating adjusting, and shown subsonic combustion room is located always
Mode is fired in Asia, supersonic speed combustion chamber is in super burn mode always；
Between second Mach number and the 6th Mach number, contract section adjustment type face and the expansion segment of sub- combustion runner are controlled
Adjustment type face rotates so that the subsonic combustion room is in sub- combustion mode always.
It is described so that it refers to so that the Asia that the subsonic combustion room and supersonic speed combustion chamber are in sub- combustion mode always
Runner and the corresponding postrotational venturi Mach number of super burn runner is fired to be in 1.2~1.5 ranges always；
It is described so that the supersonic speed combustion chamber refers to so that the corresponding rotation of the super burn runner in super burn mode always
Venturi Mach number after turning is in 9/20~11/20 range of flight Mach number always；
The first Mach 2 ship Mamin；For punching engine start-up operation Mach number and relay Mach number, correspond to
Runner venturi Mach 2 ship Ma-th1；
The second Mach 2 ship Ma-2 corresponds to venturi Mach number Ma-th2, the Ma-th2 and is more than threshold value MaΔ1, institute
State MaΔ1 preferred scope is 1.2~1.5；
The third Mach 2 ship Ma-3, the 4th Mach 2 ship Ma-4, Ma-3 and Ma-4 and between realize supersonic speed
Transformation of the combustion chamber from sub- combustion mode to super burn mode, and the third Mach number is according to its corresponding venturi Mach number Ma-
Th3, the 4th Mach number Ma-4 and its correspond to venturi Mach number Ma-th4 and determine；Specifically, according to the 4th Mach number Ma-4 and
Venturi Mach number Ma-th4 can obtain rotation angle by formula (1) and (2), and Ma- can be obtained by rotation angle and Ma-th3
3；
The 4th Mach number Ma-4 preferred scopes are 5.5-6, and corresponding venturi Mach number Ma-th4 is 9/20~11/
20Ma-4；
The 5th Mach 2 ship Ma-5 corresponds to venturi Mach number Ma-th5, the Ma-th5 and is more than threshold value MaΔ2, institute
State MaΔ2 be 11/20Ma-5；
The 6th Mach 2 ship Mamax, punching engine maximum functional Mach number.
Further, in the above method, when aircraft takes off from ground, air inlet flow distribution plate and exhaust controllable register are in and close
High-speed channel position is closed, when flight Mach number reaches the first Mach number, air inlet shunting moves up, and closes slow channels；
Further, task terminates, and when downslide that aircraft is unpowered, subsonic combustion room and supersonic speed combustion chamber stop work
Make, when flight Mach number drops to the first Mach number, air inlet flow distribution plate and exhaust controllable register rotate down, and reopen low
Fast channel, turbine engine ignition provide power for aircraft low cruise and horizontal landing；
Further, in the above method, slow channels also can be not fully closed, retains suitable air mass flow to drive whirlpool
Wheel power generation, electric energy is provided for aircraft, to meet or partly meet aircraft power demand.
The design principle of the present invention is：
In view of combined engine is arranged in parallel with double combustion chamber's punching engine and turbogenerator, intake and exhaust system is shared
System, while need to need to use non-axis symmetry structure with lifting body or Waverider aircraft integrated design, double combustion chamber's punching engine
Type, therefore be directed to nonaxisymmetrical double combustion chamber's configuration, the present invention separately designs corresponding air inlet runner, and for each runner into
Row design, increases contract section adjustment type face and expansion segment adjustment type face, and control its rotation by hinge, in the process of rotation
In, contract section adjustment type face, contract segment type face, venturi type face, expansion segment type face and expansion segment adjustment type face can surround one
A cavity, forms vortex by the pneumatic venturi type face as air inlet runner in cavity, by rationally design contract segment type face,
The length in segment type face and venturi type face is expanded, and makes contract section adjustment type face consistent with contract segment type face respectively, is expanded
It is consistent with expansion segment type face length to open section adjustment type face, so that contract section adjustment type face movable end and expansion segment adjustment type
Face is less than the characteristic dimension of vortex with movable end at a distance from flow direction, and the characteristic dimension is calculated by CFD and obtained, and then recessed
Intracavitary forms stable vortex；In addition, according to the size of rotation angle, different pneumatic venturi type faces will be obtained, and then pass through
This mode reduces inlet throat area, increases air intake duct shrinkage ratio, that is, increases the compression to incoming air, air intake duct larynx
Road circulation area is smaller, stronger to incoming compression, and the compressed air met the requirements is provided for combustion chamber, is conducive to stablize burning
And engine performance improves.Passing through above-mentioned adjusting so that air intake duct provides larger compression to the air-flow for entering subsonic combustion room,
After a series of wave systems with subsonic speed enter subsonic combustion room tissue burning, to enter supersonic speed combustion chamber air-flow provide compared with
Small compression, air-flow enter supersonic speed combustion chamber with supersonic speed and realize that wide scope bimodal is burnt, and engine work horse is widened with this
Conspicuous several ranges improve engine performance.
As above it is directed to that a kind of embodiment describes and/or the feature that shows can be in a manner of same or similar at one or more
It is used in a number of other embodiments, and/or the feature in other embodiments is combined or substitutes with the feature in other embodiments
It uses.
It should be emphasized that term "comprises/comprising" refers to the presence of feature, one integral piece, step or component when being used herein, but simultaneously
It is not excluded for the presence or additional of one or more other features, one integral piece, step, component or combinations thereof.
The combined engine more than present invention is by combination of hardware software realization.The present invention relates to such computer-readable journeys
Sequence can make the logical block realize devices described above or component parts when the program is performed by logical block, or
The logical block is set to realize various method or steps described above.The invention further relates to storage Jie for storing procedure above
Matter, such as hard disk, disk, CD, DVD, flash memory.
The many features and advantage of these embodiments are clear according to the detailed description, therefore appended claims are intended to
Cover all these feature and advantage of these embodiments fallen into its true spirit and range.Further, since this field
Technical staff is readily apparent that many modifications and changes, therefore is not meant to the embodiment of the present invention being limited to illustrated and description essence
Really structurally and operationally, but all suitable modifications and the equivalent fallen within the scope of its can be covered.
Unspecified part of the present invention is known to the skilled person technology.
Claims (9)
1. turbine base double combustion chamber's punching press combined cycle engine, which is characterized in that described including high-speed channel and slow channels
Slow channels and high-speed channel are arranged in parallel, and it includes turbine core engine, institute to share air intake duct and jet pipe, the slow channels
It includes double combustion chamber's punching engine to state high-speed channel；
Double combustion chamber's punching engine includes double combustion chamber's ram air duct, subsonic combustion room and supersonic speed combustion chamber,
And the subsonic combustion room and supersonic speed combustion chamber use rectangle parallel configuration；
The ram air duct uses two dimensional inlet configuration, by being divided into sub- combustion runner and super burn runner by support plate along flow direction,
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 of fixed face, adjustable type face and connects hinge, wherein described solid
Sizing face includes external pressure miniature face, contract segment type face, venturi type face, expansion segment type face, lip type face and connects 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
It is individually fixed in contract section starting point and expansion segment endpoint with 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, and described
Contract section adjustment type face and expansion segment adjustment type face can be rotated respectively around the hinge a and b by design rotation angle.
2. turbine base according to claim 1 double combustion chamber's punching press combined cycle engine, which is characterized 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 pneumatic venturi of the vortex as runner is formed in cavity
Type face, the corresponding venturi height in the pneumatic venturi type face are defined as the venturi height H of runner after the rotation of adjustable type faceth, pass through public affairs
Formula (1) obtains：
Wherein, HthRunner venturi height after being rotated for adjustable type face, HcHeight is captured for air intake duct runner, q (Ma) is flow letter
Number, Ma0And MathRespectively free stream Mach number and air intake duct runner venturi Mach number,For discharge coefficient, σthIt is total for runner venturi
Press recovery coefficient.
3. turbine base according to claim 2 double combustion chamber's punching press combined cycle engine, which is characterized in that in the hinge
Chain rotates in adjustment process, 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. turbine base according to claim 3 double combustion chamber's punching press combined cycle engine, which is characterized in that the rotation
Angle includes the rotation angle θ in contract section adjustment type face7With the rotation angle θ in expansion segment adjustment type face8, obtained by formula (2)
It arrives；
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, HthRunner venturi height after being rotated for adjustable type face, L7For contract section adjustment type face two-end-point
Between distance, L8The distance between the two-end-point of expansion segment adjustment type face, θ2Between 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. turbine base according to claim 4 double combustion chamber's punching press combined cycle engine, which is characterized in that the rotation
Angle, θ7And θ8When being 0 °, the contract section adjustment type face and expansion segment adjustment type face respectively with contract segment type face and expansion
Segment type face paste is closed；The rotation angle θ7And θ8For maximum value when, the contract section adjustment type face and expansion segment adjustment type face with
It closes subject to the runner.
6. according to claim 1-5 any one of them turbine base double combustion chamber's punching press combined cycle engines, which is characterized in that
The sub- combustion runner is B runners, and the super burn runner is respectively A, C runner, runner layout for selected from ABC, AABAA,
Any one of ABABC, ABBC combining form, wherein A runners are identical with C runners.
7. turbine base according to claim 1 double combustion chamber's punching press combined cycle engine, it is characterised in that：The air inlet
The air inlet shunting for controlling the turbine core engine and double combustion chamber's punching engine charge air flow distribution is equipped in road
Plate.
8. turbine base according to claim 1 double combustion chamber's punching press combined cycle engine, it is characterised in that：The jet pipe
The interior exhaust controllable register being equipped with for controlling the turbine core engine and double combustion chamber's punching engine gas discharge.
9. turbine base according to claim 1 double combustion chamber's punching press combined cycle engine, it is characterised in that：The turbine
Core engine is turbogenerator or series connection TBCC engines.
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| CN107448296B (en) * | 2017-08-07 | 2018-08-31 | 南京航空航天大学 | 0-7 grades of combined engine air intake ducts of Mach number that pneumatic type/mechanical combination is adjusted |
| CN107575309B (en) * | 2017-08-07 | 2018-12-14 | 南京航空航天大学 | A kind of high-performance dual rectangular channels loong shunt TBCC air intake duct and design method |
| CN108194224B (en) * | 2017-12-31 | 2019-08-27 | 厦门大学 | It is embedded to the TBCC parallel connection jet pipe regulating mechanism design method of diaphragm internal |
| CN109630271B (en) * | 2018-11-14 | 2021-01-01 | 中国航发沈阳黎明航空发动机有限责任公司 | Multifunctional aircraft engine air inlet channel and operation method thereof |
| CN109538377B (en) * | 2018-11-15 | 2020-03-27 | 厦门大学 | Design method of three-power combined engine sharing sub-combustion chamber |
| CN109670269B (en) * | 2019-01-07 | 2021-03-05 | 厦门大学 | Design method of multi-channel parallel three-power combined engine |
| CN113623086B (en) * | 2021-07-19 | 2022-08-02 | 南京航空航天大学 | Shock wave/boundary layer interference controller |
| CN114932019B (en) * | 2022-07-25 | 2022-11-01 | 中国空气动力研究与发展中心低速空气动力研究所 | Method for controlling expansion angle of rectangular jet flow |
| CN116902210B (en) * | 2023-09-13 | 2023-12-05 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Energy supply method and device for aircraft onboard system |
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