CN106762218A - A kind of method and jet pipe for improving pulse detonation engine thrust coefficient - Google Patents
A kind of method and jet pipe for improving pulse detonation engine thrust coefficient Download PDFInfo
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- CN106762218A CN106762218A CN201710006976.3A CN201710006976A CN106762218A CN 106762218 A CN106762218 A CN 106762218A CN 201710006976 A CN201710006976 A CN 201710006976A CN 106762218 A CN106762218 A CN 106762218A
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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
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/28—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto using fluid jets to influence the jet flow
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- Jet Pumps And Other Pumps (AREA)
Abstract
The present invention proposes a kind of method and jet pipe for improving pulse detonation engine thrust coefficient, in pulse detonation engine afterbody nozzle divergence cone wall, to jet pipe, axially inside direction is equidistantly introduced no less than two groups of annular jets, the one group jet nearest apart from nozzle throat needs to be arranged in before position occurs in swelling, every group of annular jet is circumferentially evenly arranged, and jet edge enters jet pipe with the radial direction of jet pipe central axis upright.The improvement in structure is carried out in traditional De Laval noz(zle) expansion segment wall according to the method for the present invention, the shallow bid annular subsonic jets differed greatly with center main flow Mach number are introduced in ad-hoc location, new chain of command is formed on the outside of main flow, make the actual expansion ratio of main flow closer to optimum value, effectively increase the thrust coefficient of engine.Simultaneously because the jet for introducing is annular jet, nozzle exit air-flow can be reached still into the effect of axial symmetry type, motor power is along nozzle axis direction.
Description
Technical field
The invention belongs to nozzle technical field, and in particular to one kind improves pulse detonation engine thrust coefficient
Method and be applicable the method unsteady annular jet control jet pipe.
Background technology
Relative maturity is studied based on aerodynamic permanent Nozzle Design, but for the Nozzle Design of nonstationary flow
So far there is not breakthrough.With pulse detonation engine (Pulse Detonation Engine, abbreviation PDE), pulsation hair
The research of the unsteady engine such as motivation and application, the Nozzle Design in nonstationary flow turn into the important skill that researcher needs to break through
Art, researcher need by jet pipe by unsteady engine combustion room produce heat energy be fully converted into increase engine push away
The kinetic force of power.And such engine is different from conventional engine, its combustion chamber and nozzle interior field are unstable, with unsteady
Property, periodicity, therefore the design concept of conventional permanent jet pipe is no longer applicable herein, and the jet pipe of fixed dimension cannot long-term work
Under optimum expansion state.
Based on pulsed detonation wave, detonation wave energy produces high gaseous-pressure and combustion gas temperature to pulse detonation engine
Degree, is propagated with the speed of several kms per second to non-burning mixt, and detonation combustion process is close to constant volume process.According to thermodynamic argument
Know that the engine Humphrey recycle ratios based on isochoric combustion are based on the engine Brayton circulations of isobaric combustion with higher
The efficiency of cycle.The advantage how advantage in pulse detonation engine Theory of Combustion is converted into propulsive performance still perplexs so far
Numerous scholars, it is exactly at it that the heat energy of HTHP detonation combustion gas is converted into one of the propulsive performance of engine, approach
Afterbody installs suitable jet pipe.And the temperature and pressure large span characteristic and unsteady characteristic of PDE to govern its always unsteady
The design of jet pipe, so far design of the scholar to the engine jet pipe does not draw consistent conclusion also, the optimum configuration of PDE jet pipes with
The running parameters such as fuel, filling rate, frequency, height, flight Mach number are closely related.According to correlative study, PDE is according to fixation
Structure jet pipe, or even the same class jet pipe complete phase of the influence to PDE propulsive performances under engine different working condition occurs
Anti- phenomenon.A kind of change jet pipe for adapting to pulse detonation engine is developed for this has important practical significance.
The content of the invention
Regarding to the issue above, jet pipe moving boundary is controlled to improve by annular jet it is an object of the invention to provide one kind
The method of pulse detonation engine thrust coefficient and the suitable pulse detonation engine working characteristics based on the method it is non-fixed
Normal annular jet control jet pipe.
The technical solution for realizing the object of the invention is：
A kind of method for improving pulse detonation engine thrust coefficient, specially in pulse detonation engine afterbody jet pipe
To inside jet pipe, along jet pipe axial direction, equidistantly introducing is no less than two groups with core flow Mach number difference very to expansion segment wall
Big shallow bid subsonic speed annular jet, the one group fluidic arrangement nearest apart from nozzle throat cross swelling occur position it
Before, i.e., the distance to nozzle throat should be less than 0.2 times of throat diameter, and every group of annular jet is arranged circumferentially along jet pipe, penetrates
Stream enters jet pipe along with the radial direction of jet pipe central axis upright, and the throat opening area of the jet pipe reaches velocity of sound for nozzle throat
When critical area 80%-90%.Annular jet is presented axial symmetry type to main flow control, and new control is formed on the outside of main flow
Face, jet pipe moving boundary is controlled by annular jet, so as to be sprayed according to the supersonic speed and subsonic speed status adjustment of nozzle entry air-flow
The actual type face of main flow and actual discharge area, can make the Resulting thrust force of main flow outlet be oriented parallel to engine center in pipe
Axle, makes the actual expansion ratio of main flow closer to optimum value, and the thrust coefficient of engine is improved with this.Jet total pressure is set to be needed to protect
Card：When there is expansion in PDE exhaust later stage jet pipes, jet initially enters nozzle divergence cone.
Further, nozzle structure is controlled present invention also offers a kind of unsteady annular jet based on the above method,
Including converging portion and expansion segment, between the expansion segment inside and outside wall along jet pipe it is axially arranged be no less than two groups by inside jet pipe with it is outer
The annular jet through hole of portion's connection.It is as follows in detail：
One, the jet pipe is installed at pulse detonation engine afterbody, and the type face of nozzle divergence cone may be designed as bell type face,
To reach by the smooth effect of the expansion segment Mainstream Packs surface current after jet vectoring.
Nozzle throat area takes the value more smaller than optimal throat opening area in engine filling process during minimum stagnation pressure, jet pipe
Optimal throat opening area is critical area value when nozzle throat reaches velocity of sound, and general nozzle throat area takes minimum stagnation pressure operating mode
When critical area 80%-90%, to ensure structure rocket type pulse detonation engine (PDRE) under minimum stagnation pressure operating mode
Nozzle throat is critical flow.
The calculation of general throat opening area is as follows：
(1) Mach number of nozzle entry when engine is filled is measured.Or air-flow stagnation pressure and static pressure calculate spray during by filling
Tube inlet Mach number, triadic relation's formula is：
γ is the specific heat ratio of air-flow in formula, and p is filling air-flow static pressure, p*It is filling air-flow stagnation pressure, M is nozzle entry
Mach number.
(2) critical throat opening area is calculated according to nozzle entry Mach number and nozzle entry area, triadic relation's formula is
A in formulacrAs throat throat opening area, A is nozzle entry area, and M is still nozzle entry Mach number.
Two, it is axially arranged along jet pipe between the expansion segment inside and outside wall to be no less than two groups by inside jet pipe and ft connection
Annular jet through hole, the jet via-hole be used for introduce annular jet, the jet via-hole is equidistant along nozzle axis direction
Set, annular jet is presented axial symmetry type to main flow control, control is uniform, and the Resulting thrust force direction of main flow outlet can be made parallel
In engine center axle.Specific jet needs to be arranged in before position occurs in expansion, and jet location can excessively cause spray rearward
Occurs subsonic flow zonule group on tube hub axis.Therefore the first strand jet nearest apart from nozzle throat is to nozzle throat
Distance should be less than 0.2 times of throat diameter.Jet total pressure is set to be needed to ensure：Occurred in PDE exhaust later stage jet pipes swollen
When swollen, jet initially enters nozzle divergence cone.Jet total pressure increases to jet incident pressure and tends towards stability, it is impossible to excessive,
Otherwise cause jet incidence Mach number excessive.
Annular jet through hole has following two set-up modes：
The first, every group of jet via-hole is by orifice, circular passage and goes out to flow annular distance and constitutes, and the circular passage is expansion
Annular cavity in Duan Guanbi, the orifice is the cylindrical hole by circular passage and jet pipe ft connection, described to go out to flow annular distance
It is the cylindrical hole for connecting circular passage and expansion segment inwall and be evenly distributed.
Further, the cross sectional shape of the circular passage is rectangle or circle, and the sectional area of each circular passage is should
Go out to flow the 85%-110% of the total sectional area of annular distance in group jet via-hole.
Further, the central axis upright of the orifice and jet pipe set and orifice extended line not with go out to flow ring
The cylindrical of hole intersects, and every group of jet via-hole includes being no less than three orifices being evenly distributed.
Further, it is described to go out to flow radial direction setting of the annular distance along jet pipe, so can guarantee that annular jet incident angle
Using 90 ° of incidence angles, effect is more preferable.Go out to flow the diameter range of annular distance for 0.001-0.002m, depth is 0.001-0.003m, often
Group jet via-hole in it is adjacent go out flow annular distance distance be 0.002-0.004m.
Further, in described each orifice correspondence insertion jet air supply pipe, the jet air supply pipe by with jet pipe in
Heart diameter parallel and the two sections of air inlet straight tubes composition with jet pipe central axis upright.
Second, every group of jet via-hole is made up of circumferential uniform cylindrical hole, and each cylindrical hole is along jet pipe
It is radially arranged, same to ensure that entrance angle of jet current degree uses 90 ° of incidence angles, each cylindrical hole diameter range is 0.001-
0.002m, the distance of adjacent column shape through hole is 0.002-0.004m in every group of jet via-hole.Each cylindrical hole correspondence is inserted
Incident flow air supply pipe, the jet air supply pipe is by two sections of parallel with nozzle axis and vertical with nozzle axis air inlet straight tube groups
Into.
Compared with prior art, its remarkable advantage is the present invention：
The present invention is differed by being introduced in traditional De Laval noz(zle) expansion segment wall ad-hoc location with center main flow Mach number
Very big shallow bid annular subsonic jets, form new chain of command on the outside of main flow, reach the actual type face of main flow and discharge area
Controllable effect.Simultaneously because the jet for introducing is annular jet, control is uniform, can reach nozzle exit air-flow still into axial symmetry
The effect of type, motor power direction makes the actual expansion ratio of main flow closer to optimum value along nozzle axis, effectively improves engine
Thrust coefficient, be easy to thrust control.
Brief description of the drawings
Fig. 1 is the structural representation of the jet pipe of the embodiment of the present invention one.
Fig. 2 is the left view of the nozzle divergence cone of the embodiment of the present invention one.
Fig. 3 is A-A faces sectional view in Fig. 1.
Fig. 4 is B-B faces sectional view in Fig. 1.
Fig. 5 is C-C faces sectional view in Fig. 3.
Fig. 6 is the structural representation of the jet pipe of the embodiment of the present invention two.
Fig. 7 is D-D faces sectional view in Fig. 6.
Fig. 8 is E-E faces sectional view in Fig. 7.
Fig. 9 is conventional De Laval noz(zle) Mach number flow field figure when there is swelling in the PDRE exhaust later stages.
Figure 10 is that jet pipe of the present invention improved the Mach number flow field figure after swelling.
In figure：1-converging portion；2-expansion segment；3-throat；4-orifice；5-circular passage；6-go out to flow annular distance；
7-cylindrical jet via-hole.
Specific embodiment
The present invention is described in further detail with reference to specific embodiment.
A kind of method for improving pulse detonation engine thrust coefficient, in pulse detonation engine afterbody nozzle divergence cone wall
Equidistantly introduced no less than two groups of annular jet along jet pipe axial direction inside towards jet pipe, apart from nozzle throat it is nearest one
Group jet needs to be arranged in before position occurs in swelling；Every group of annular jet is circumferentially evenly arranged, jet along and spray
The vertical radial direction of tube hub axis enters jet pipe, and annular jet is presented axial symmetry type, the shape on the outside of main flow to main flow control
The chain of command of Cheng Xin, can make the Resulting thrust force of main flow outlet be oriented parallel to engine center axle, make the actual expansion ratio of main flow
Closer to optimum value, the thrust coefficient of engine is improved with this.
Wherein, jet total pressure is set needs to ensure：When there is expansion in pulse detonation engine exhaust later stage jet pipe,
Jet initially enters nozzle divergence cone；The 80%- of the critical area when throat opening area of jet pipe reaches velocity of sound for nozzle throat
90%.
A kind of unsteady annular jet control jet pipe of the above method is applicable, the jet pipe is arranged on pulse detonation engine tail
Portion, as shown in figure 1, the jet pipe is convergence diverging nozzle, it is axial symmetry type, design easy to process, including converging portion 1 and expansion
Section 2 is opened, the type face of converging portion 1 is taper, and the type face of expansion segment 2 may be designed as bell type face, to reach by after jet vectoring
The smooth effect of the Mainstream Packs surface current of expansion segment 2.
Specifically, the unsteady annular jet of the two-phase rocket type pulse detonation engine design for a diameter of 0.06m
Control jet pipe, nozzle entry diameter (d1) it is 0.06m, the diameter of throat 3 and outlet diameter of jet pipe are critical data, it is necessary to pass through
Fluid calculation and analogue simulation are obtained, optimal throat diameter (d after calculating2) it is 0.039m, outlet diameter (d3) it is 0.086m.
Embodiment one
With reference to Fig. 1-5, three groups of annular jet through holes are set in above-mentioned nozzle divergence cone tube wall, every group of jet via-hole is by noting
Discharge orifice 4, circular passage 5, go out to flow annular distance 6 and constitute.Specific first group of jet via-hole is by orifice 41, circular passage 51 and goes out stream
Annular distance 61 is constituted, and second group of jet via-hole is by orifice 42, circular passage 52 and goes out to flow annular distance 62 and constitutes, the 3rd group of jet via-hole
By orifice 43, circular passage 53 and go out to flow annular distance 63 and constitute, the circular passage 5 is the annular cavity in expansion segment tube wall,
The orifice 4 be by the cylindrical hole of circular passage 5 and jet pipe ft connection, it is described go out flow annular distance 6 for connection circular passage 5 with
The cylindrical hole being evenly distributed of expansion segment inwall.
Drawn by simulation calculation, first group of axial distance between jet via-hole and nozzle throat is 0.006-
0.008m, the axial distance between second group of jet via-hole and first group of jet via-hole is 0.006-0.008m, and the 3rd group is same,
It is 0.006-0.008m with the axial distance between second group of jet via-hole.
Go out to flow annular distance 6 to be set along the radial direction of jet pipe, so can guarantee that annular jet incident angle uses 90 ° of incidences
Angle, effect is more preferable.Drawn by simulation calculation, go out to flow the preferred 0.001-0.002m of diameter range of annular distance 6, and every group of jet leads to
It is adjacent in hole to go out to flow between annular distance 6 at a distance of 0.002-0.004m.Certainly this distance is also not necessarily limited to, as long as can guarantee that the side spray of annular distance two
The stability of pipe connection, prevents jet pipe from disconnecting.Go out to flow the desirable 0.001-0.003m of the depth of annular distance 6, should not be too deep, to prevent
Flow losses are too big in aperture.
The annular distance 6 that goes out to flow in every group of jet via-hole is radially linked with circular passage 5 along jet pipe respectively.To ensure jet in ring
Shape passage 5 neutralizes out the medium velocity of stream annular distance 6 and approaches, the institute that the sectional area of each circular passage 5 should be close in this group of jet via-hole
There is the total sectional area sum of stream annular distance 6, be specifically as follows in this group of jet via-hole the 85%- of the total sectional area for going out to flow annular distance
110%.For the design size, circular passage 51 can design that 3mm is wide, 8mm deep rectangular channel；Circular passage 52 can be designed
3.5mm is wide, 9mm deep rectangular channel；Circular passage 53 can design that 4mm is wide, 9mm deep rectangular channel.Certain circular passage 5
Circular cross-section is may be designed as, as long as the sectional area for meeting circular passage goes out to flow the total cross section of annular distance 6 close to all of correspondence group
Product sum.
With reference to Fig. 5, three orifices 4 being evenly distributed are set, orifice 4 is used for annular is logical in every group of jet via-hole
Road 5 and jet pipe ft connection, the central axis upright of orifice 4 and jet pipe and with radially angled arrangement, angle requirement
Can guarantee that in can only directly reaching circular passage 5 by the jet of orifice 4, it is impossible to reach out in stream annular distance 6, that is, meet beam
The extended line in hole 4 not with go out to flow the cylindrical of annular distance 6 and intersect.The diameter of orifice 4 is identical with the width of circular passage 5,
In each orifice 4 correspondence insertion jet air supply pipe, the jet air supply pipe by with jet pipe centerline axis parallel and with jet pipe in
The vertical two sections of air inlet straight tubes composition of heart axis, three incoming positions of orifice 4 in preferably every group jet via-hole are in axial direction
On mutually stagger, be so easy to be staggeredly arranged the air supply pipe being connected with orifice.
Embodiment two
With reference to Fig. 6-8, three groups of annular jet through holes, every group of jet via-hole are set between above-mentioned nozzle divergence cone inside and outside wall
Constituted by along the circumferentially uniform cylindrical hole 7 of jet pipe, obtained by analogue simulation, penetrated apart from nearest first group of nozzle throat
Axial distance between opening 71 and nozzle throat is 0.006-0.008m, and second group of jet via-hole 72 and first group of jet lead to
Axial distance between hole 71 is 0.006-0.008m, and the 3rd group of jet via-hole 73 is same, between second group of jet via-hole 72
Axial distance be 0.006-0.008m.
Cylindrical hole 7 is radially arranged along jet pipe, the preferred 0.001-0.002m of the diameter of cylindrical hole 7, every group of jet
The distance of adjacent column shape through hole is 0.002-0.004m in through hole, this distance is also not necessarily limited to certainly, as long as can guarantee that annular distance two
The stability of lateral jet pipe connection, that is, the rear jet that punches should not be thrust by air-flow.
In each cylindrical hole 7 correspond to insertion jet air supply pipe, the jet air supply pipe by with jet pipe central axis
Two sections of air inlet straight tubes composition parallel and with jet pipe central axis upright, turns round by different level at more than nozzle entry section.
Certain jet via-hole of the invention is not limited to above two design, is not departing from the spirit and scope of the present invention
It is interior, various changes can be made.
The jet pipe course of work is as follows：
The pulse detonation engine course of work includes isolation, filling, detonation and exhaust four-stage,
Annular jet control jet pipe sets stagnation temperature stagnation pressure to be needed to reach following effect：(1) jet pipe rank is entered in detonation wave
Section jet pipe is operated at full capacity, and the jet total pressure and stagnation temperature of setting need to ensure that jet does not enter nozzle divergence cone in this stage；(2)
Jet pipe is operated at full capacity in the first stage of exhaust；(3) when engine exhaust entered the expansion stage, the jet total pressure of setting needs
Ensure that jet can be incident, now jet pipe sets moving boundary by jet, forms new jet boundary and expansion ratio；(4) hair is worked as
Motivation is in isolation and filling process, still has swelling to occur, and also needs jet to be controlled jet pipe border.Therefore
Need to initially enter nozzle divergence cone in exhaust later stage jet.
In order to reach the effect above, the incident stagnation pressure of each jet, first group of jet incidence stagnation pressure are set by simulation calculation
Preferable span is 0.181Mpa-0.207Mpa, and second group of jet is 0.136Mpa-0.155Mpa, and the 3rd group of jet is
0.104Mpa-0.116Mpa.Should be noted that three groups of jets need to set different jet total pressures because of position difference, from left to right by
It is small to big because the pressure of fluid is different during diverse location correspondence jet pipe flowing full.If each group jet incidence stagnation pressure is identical, it is close to
3rd group of jet of nozzle exit can be injected in advance, or even can be incident when jet pipe is not up to expansion, can not now be played
The effect of regulation supersonic speed main flow flowing, wastes the jet for preparing, and influence the bulk expansion effect of main flow.
As shown in Figure 10, Fig. 9 is that conventional De Laval noz(zle) is arranged in PDRE to the working effect of the jet vectoring moving boundary jet pipe
There is Mach number flow field during swelling in the gas later stage, and from supersonic speed moment be reduced to fluid by the shock wave for now occurring in jet pipe
Subsonic speed, reduces the thrust coefficient of engine；Figure 10 is then that, with the improvement phenomenon after the design jet pipe, streamline is no longer in figure
In divergence form, jet compressing central supersonic main flow direction central shaft is pressed close to, and jet is disturbed main flow flowing, is close in jet pipe
Subsonic flow region is formed at wall and replaces Supersonic Flow, form new jet boundary, reduce nozzle expansion ratio, improve
Motor power coefficient.
The above, preferably specific embodiment only of the invention, but this should not be interpreted as above-mentioned theme of the invention
Scope be only limitted to the embodiment of the above, all technologies realized based on present invention belong to the scope of the present invention.
Claims (10)
1. it is a kind of improve pulse detonation engine thrust coefficient method, it is characterised in that：
It is many to equidistantly being introduced along jet pipe axial direction inside jet pipe in pulse detonation engine afterbody nozzle divergence cone wall
In two groups of annular jet, the one group jet nearest apart from nozzle throat needs to be arranged in before position occurs in swelling；
Every group of annular jet is circumferentially evenly arranged, and jet edge enters jet pipe, ring with the radial direction of jet pipe central axis upright
Shape jet is presented axial symmetry type to main flow control, and new chain of command is formed on the outside of main flow, can close the thrust of main flow outlet
Force direction makes the actual expansion ratio of main flow closer to optimum value parallel to engine center axle, and the thrust of engine is improved with this
Coefficient.
Wherein, jet total pressure is set needs to ensure：When there is expansion in pulse detonation engine exhaust later stage jet pipe, jet
Initially enter nozzle divergence cone；The 80%-90% of the critical area when throat opening area of jet pipe reaches velocity of sound for nozzle throat.
2. a kind of unsteady annular jet based on claim 1 methods described controls jet pipe, it is characterised in that：Including converging portion
(1) and expansion segment (2), between expansion segment (2) inside and outside wall along jet pipe it is axially arranged be no less than two groups by inside jet pipe with it is outer
The annular jet through hole of portion's connection.
3. a kind of unsteady annular jet according to claim 2 controls jet pipe, it is characterised in that：The jet via-hole edge
The axial spaced set of jet pipe, the one group jet via-hole nearest apart from nozzle throat was arranged on swelling and position occurred
Before putting.
4. a kind of unsteady annular jet according to claim 2 controls jet pipe, it is characterised in that：The nozzle divergence cone
(2) type face for bell, the 80%-90% of the critical area when throat opening area of the jet pipe reaches velocity of sound for nozzle throat.
5. a kind of unsteady annular jet according to claim 2 controls jet pipe, it is characterised in that：Every group of jet via-hole by
Orifice (4), circular passage (5) and go out to flow annular distance (6) composition, the circular passage (5) be in expansion segment tube wall annular in
Chamber, the orifice (4) be by the cylindrical hole of circular passage (5) and jet pipe ft connection, it is described go out to flow annular distance (6) be connected ring
Shape passage (5) and expansion segment inwall and the cylindrical hole being evenly distributed.
6. a kind of unsteady annular jet according to claim 5 controls jet pipe, it is characterised in that：The circular passage
(5) cross sectional shape is rectangle or circle, and the sectional area of each circular passage (5) in this group of jet via-hole to go out to flow annular distance (6)
Total sectional area 85%-110%.
7. a kind of unsteady annular jet according to claim 5 controls jet pipe, it is characterised in that：The orifice (4)
Set with the central axis upright of jet pipe and orifice (4) extended line not with cylindrical the intersecting for going out to flow annular distance (6), every group of jet
Through hole includes being no less than three orifices being evenly distributed (4).
8. a kind of unsteady annular jet according to claim 5 controls jet pipe, it is characterised in that：It is described to go out to flow annular distance
(6) set along the radial direction of jet pipe, go out to flow the diameter range of annular distance (6) for 0.001-0.002m, depth is 0.001-
0.003m, in every group of jet via-hole it is adjacent go out flow annular distance distance be 0.002-0.004m.
9. a kind of unsteady annular jet according to claim 2 controls jet pipe, it is characterised in that：Every group of jet via-hole by
Circumferential uniform cylindrical hole (7) composition, each cylindrical hole is radially arranged along jet pipe, each cylindrical hole diameter
Scope is 0.001-0.002m, and the distance of adjacent column shape through hole is 0.002-0.004m in every group of jet via-hole.
10. a kind of unsteady annular jet according to claim 5 or 9 controls jet pipe, it is characterised in that：Described each note
Correspondence insertion is for introducing the air supply pipe of jet in discharge orifice (4) and cylindrical hole (7), the air supply pipe by with jet pipe central shaft
Parallel and with jet pipe central axis upright the two sections of air inlet straight tubes composition of line.
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| CN112628027A (en) * | 2020-12-15 | 2021-04-09 | 中国人民解放军国防科技大学 | Rocket nozzle applied to RBCC engine and RBCC engine |
| CN112610362A (en) * | 2020-12-18 | 2021-04-06 | 贵州航天朝阳科技有限责任公司 | Engine thrust control method and variable thrust engine |
| CN115434829A (en) * | 2022-10-17 | 2022-12-06 | 西安探火航天技术有限公司 | Reusable rocket engine nozzle assembly with variable expansion ratio |
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