CN103726954A - Rocket based combined cycle engine rocket ejector T-type layout - Google Patents
Rocket based combined cycle engine rocket ejector T-type layout Download PDFInfo
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- CN103726954A CN103726954A CN201310731215.6A CN201310731215A CN103726954A CN 103726954 A CN103726954 A CN 103726954A CN 201310731215 A CN201310731215 A CN 201310731215A CN 103726954 A CN103726954 A CN 103726954A
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- rocket
- ejector
- rocket ejector
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Abstract
The invention discloses a rocket based combined cycle engine rocket ejector T-type layout comprising a central supporting plate rocket ejector and a plurality of side-wall rocket ejectors. The side-wall rocket ejectors are located above the central supporting plate rocket ejector. The front portions of the side-wall rocket ejector are connected to rocket combustion chamber pipelines, the central supporting plate rocket ejector is connected to a combustion chamber through upper-side pipelines, and the section of two sets of rockets is the interface of an insulating segment and a mixing segment. By means of limitation on T-type rocket ejector layout size, and a layout manner with smaller duty ratio than a full throughout central supporting plate layout manner and larger wetted perimeter than a side-wall layout manner is provided; congestion effect on the insulating segment of a full throughout supporting plate type rocket ejector and flight drag of scramjet mode are reduced, and cutting area of a primary jet flow and secondary jet flow are increased; the scalability of the rocket ejector T-type layout is high, and the rocket ejector layout is designed according to different mixing segment inlet section sizes so as to acquire excellent engine performance.
Description
Technical field
The invention belongs to rocket ramjet field, specifically, relate to the T-shaped layout of a kind of Rocket based combined cycle motor Rocket ejector.
Background technique
Rocket based combined cycle (Rocket-Based-Combined-Cycle, RBCC) motor has reusable, low cost and higher reliability, is regarded as one of propulsion system being most possibly applied to following earth to orbit and return transportation system.Under different flight Mach numbers, this motor carries out work with different thermodynamic cycles in same runner, in same runner, realized wide range flight, ramp-up period is divided into Ejector Mode, sub-combustion mode, super combustion mode and four kinds of mode of operations of pure rocket mode.Rocket ejector in runner has played the effect of injection air, propellant spray, generation thrust and igniting in Ejector Mode, under Asia combustion mode, super combustion mode, mainly play igniting and flame holding, in pure rocket mode, provide thrust, therefore, the layout type of Rocket ejector produces considerable influence to motor power, thrust gain and specific impulse.Rocket based combined cycle motor is divided into axisymmetric configuration and diadactic structure configuration, wherein diadactic structure configuration can make full use of aircraft precursor and carries out precompression, and bring certain lift for aircraft, make the aircraft can horizontal take-off, current research work mainly concentrates on diadactic structure configuration.Diadactic structure motor is divided into again the lateral wall type Rocket ejector configuration that Rocket ejector is arranged on a board-like Rocket ejector configuration at motor distance piece center and is arranged on motor distance piece top, center is propped up board-like Rocket ejector and is proposed by U.S. Aerojet company, as document < < The Strutjet Engine:The Overlooked Option For Space Launch > > (AIAA95-3124, 1995:1～14), the advantage of this Rocket ejector layout method be once flow with the shearing area of Secondary Flow larger, be conducive to improve induction efficiency, but main support plate has the larger effect of being jammed to runner, in super combustion mode, can bring larger flight resistance.The A5 motor that Boeing proposes adopts lateral wall type Rocket ejector, as document < < Rocket-Based Combustion Cycle Activities In The Advanced Space Transportation Program Office > > (AIAA99-2352, 1999:1～9), the motor that Japan proposes subsequently has also adopted this configuration, as document < < Aerodynamic Experiment on an Ejector-Jet > > (JOURNAL OF PROPULSION AND POWER, Vol.21, No.3, May-June 2005:496～503), the advantage of this Rocket ejector layout method is that runner is unobstructed, Rocket ejector is combined preferably with flame holder, its shortcoming is that Rocket ejector performance loss is larger, once stream is less with Secondary Flow shearing area, be unfavorable for the raising of induction efficiency.
The distance piece height of existing board-like Rocket ejector layout equates with mixing section height, entirely runs through support plate and is through to distance piece lower wall surface completely from distance piece upper wall surface, and runner has been produced to the larger effect of being jammed.The Rocket ejector of existing lateral wall type Rocket ejector layout is arranged in distance piece top, and Rocket ejector wetted perimeter is long littlely to be caused once flowing with Secondary Flow area of contact less, and rocket performance loss is large, induction efficiency is lower.
Summary of the invention
For fear of entirely run through a board-like Rocket ejector compared with big space rate the effect of being jammed to runner, bring larger flight resistance to super combustion mode, make up the once stream deficiency lower with the less induction efficiency of Secondary Flow shearing area that lateral wall type Rocket ejector is less, the present invention proposes the T-shaped layout of a kind of Rocket based combined cycle motor Rocket ejector simultaneously.
Thinking of the present invention is: by sidewall Rocket ejector with partly run through center support plate Rocket ejector and combine, the dimension constraint proposing by the present invention, partly run through center support plate Rocket ejector and to firing chamber lower wall surface, be partly through to certain altitude from firing chamber upper wall surface, rather than prop up the same distance piece lower wall surface that is through to completely of board-like Rocket ejector layout with existing entirely running through, reduce dutycycle and reduced the effect of being jammed to runner, reduced the flight resistance of super combustion mode, the wetted perimeter that has simultaneously increased rocket and secondary gas flow runner is long, once stream and Secondary Flow area of contact have been increased, the induction efficiency that acquisition is higher than lateral wall type Rocket ejector.
The technical solution adopted for the present invention to solve the technical problems is: comprise center support plate Rocket ejector and multiple sidewall Rocket ejector, sidewall Rocket ejector is positioned at and partly runs through support plate Rocket ejector top, center, and distributes according to axial both sides horizontal symmetrical; Sidewall Rocket ejector is anterior to communicate with rocket chamber pipeline, and center support plate Rocket ejector is connected with rocket chamber by the pipeline on top, and two groups of rocket outlets are the separating surface of distance piece and mixing section; According to overall definite distance piece and mixing section entrance section size L
1, L
2and H, partly running through center support plate Rocket ejector width is L
2, mixing section and distance piece height difference are H
1, partly running through center support plate Rocket ejector height is H
2, by L
1, L
2retrain H with H
1and H
2span; Main support plate width is L
2the board-like Rocket ejector layout type dutycycle of entirely running through be L
2/ L
1, lateral wall type Rocket ejector layout type wetted perimeter is long is L
1;
For guaranteeing that T-shaped Rocket ejector layout type dutycycle is less than, entirely run through a board-like Rocket ejector layout type: (L
1h
1+ L
2h
2)/(L
1h) <L
2/ L
1, abbreviation obtains: H
2< (L
2h-L
1h
1)/L
2;
For guaranteeing T-shaped Rocket ejector layout type wetted perimeter, grow up in lateral wall type Rocket ejector layout type: L
1<L
1+ 2H
2; Meet above two dimension constraints simultaneously, obtain formula: 0<H
2< (L
2h-L
1h
1)/L
2,
For assurance formula: 0<H
2< (L
2h-L
1h
1)/L
2, must meet formula: (L
2h-L
1h
1)/L
2>0, that is: H
1<L
2h/L
1;
For given distance piece and mixing section sectional dimension L
1, L
2in H situation, as T-shaped Rocket ejector layout dimension H
1and H
2meet formula: 0<H simultaneously
2< (L
2h-L
1h
1)/L
2and formula: H
1<L
2h/L
1time, its dutycycle is less than and entirely runs through a board-like Rocket ejector layout type, and wetted perimeter is grown up in lateral wall type Rocket ejector layout type.
Beneficial effect
The T-shaped layout of a kind of Rocket based combined cycle motor Rocket ejector that the present invention proposes, the in the situation that of the overall given mixing section entrance section size of motor, the layout type proposing according to the present invention of mixing section entrance section dimension constraint, reduce entirely to run through the flight resistance of be jammed effect and the super combustion mode of a board-like Rocket ejector to distance piece 2, increased the shearing area of injection air-flow and Secondary Flow simultaneously.The T-shaped layout expansion of Rocket ejector of the present invention is strong, can to Rocket ejector layout, design according to different mixing section entrance section sizes, with acquisition dutycycle, be less than and entirely run through a board-like Rocket ejector layout type, once flow with Secondary Flow shearing area and be greater than the layout type of lateral wall type Rocket ejector, thereby obtain preferably engine performance.At given distance piece and mixing section sectional dimension L
1, L
2in H situation, as long as meet the formula that the present invention proposes: 0<H
2< (L
2h-L
1h
1)/L
2and formula: H
1<L
2h/L
1, can obtain dutycycle be less than entirely run through a board-like Rocket ejector layout, wetted perimeter is grown up in the Rocket ejector layout type of lateral wall type layout.Rocket layout dutycycle that the T-shaped layout design method of Rocket ejector that utilizes the present invention to propose in experiment obtains than entirely run through board-like little by 42%, wetted perimeter length is higher by 40% than lateral wall type.In dimensional range of the presently claimed invention, the T-shaped Rocket ejector layout dutycycle obtaining is less than and entirely runs through a board-like Rocket ejector layout, be jammed effect and flight resistance to runner have been reduced, acquisition, than the higher induction efficiency of lateral wall type Rocket ejector layout, is conducive to improve motor overall performance.
Accompanying drawing explanation
Below in conjunction with drawings and embodiments, the T-shaped layout of a kind of Rocket based combined cycle motor Rocket ejector of the present invention is described in further detail.
Fig. 1 is Rocket based combined cycle engine structure schematic diagram.
Fig. 2 is the T-shaped layout plan view of Rocket based combined cycle motor Rocket ejector of the present invention.
Fig. 3 is the T-shaped layout A-A cross-sectional view of Rocket based combined cycle motor Rocket ejector of the present invention.
Fig. 4 is sidewall Rocket ejector and center support plate Rocket ejector structural representation.
Fig. 5 is the axonometric drawings such as the T-shaped layout of Rocket ejector.
In figure:
1. intake duct 2. distance piece 3. mixing section 4. extending section 5. sidewall Rocket ejector 6. center support plate Rocket ejectors
Embodiment
The present embodiment is the T-shaped layout of a kind of Rocket based combined cycle motor Rocket ejector.
The T-shaped layout of Rocket based combined cycle motor Rocket ejector of the present invention, by the size to mixing section 3 and distance piece 2 height difference with partly run through the constraint of center support plate Rocket ejector 6 height dimensions, obtain dutycycle and be less than an existing board-like Rocket ejector layout type that entirely runs through, once stream and Secondary Flow shearing area are greater than the T-shaped Rocket ejector layout type of existing lateral wall type Rocket ejector layout type.Airflow direction is as being direction as shown in u in figure, air-flow enters distance piece 2 from intake duct 1 compression, the combustion gas of the High Temperature High Pressure that Rocket ejector firing chamber produces burning is passed to sidewall Rocket ejector 5 and is partly run through center support plate Rocket ejector 6 by pipeline, after jet pipe expands, entering mixing section 3 shears with secondary gas flow, secondary gas flow is accelerated and carries out blending combustion reaction with secondary gas flow, at extending section 4, the interior kinetic energy that can be converted into is produced to thrust acting.
Consult Fig. 1-Fig. 5, the T-shaped Rocket ejector layout of Rocket based combined cycle motor of the present invention, comprise and partly run through center support plate Rocket ejector and multiple sidewall Rocket ejector, sidewall Rocket ejector is positioned at and partly runs through support plate Rocket ejector top, center, and distributes according to axial both sides horizontal symmetrical; Two groups of rocket outlets are the separating surface of distance piece and mixing section; Lateral wall type Rocket ejector 5 is anterior to communicate with rocket chamber pipeline, the combustion gas of the High Temperature High Pressure that firing chamber produces is expanded to do work by jet pipe and is entered in mixing section 3, by shear action, secondary gas flow is accelerated, produce pumping action and introduce secondary air, fuel-rich combustion gas and secondary air air-flow carry out combustion reaction, transfer heat to secondary gas flow, further the interior of air-flow can be converted into kinetic energy, produce thrust acting.The center support plate Rocket ejector that partly runs through partly running through to lower wall surface from distance piece 2 upper wall surfaces is connected with rocket chamber by the pipeline on top, the fuel-rich combustion gas of High Temperature High Pressure is done work to secondary gas flow by shear action after expanding by jet pipe, produce pumping action and increase secondary air flow, and with the secondary air exothermic reaction of burning, the interior kinetic energy that can be converted into is produced to thrust.At mixing section entrance section, provided T-shaped Rocket ejector layout sectional dimension, mixing section 3 entrances are of a size of wide L
1, high H, by motor general requirement, determined, for different Rocket ejector layout type, reply mixing section 3 entrance sizes are optimized design, make Rocket ejector mate work with mixing section 3, to realize engine optimum performance.In practical application, consider the thermal protection problem of support plate, partly run through Rocket ejector support plate width L
2there is a minimum value L
2min, L
2minby Rocket ejector configuration, working state, material thermal resistance energy and active cooling ability integration, determined L
2consistent with existing the board-like injection support plate width of entirely running through.Mixing section 3 and distance piece 2 height difference H
1, the height that partly runs through center support plate Rocket ejector 6 is H
2.
The present invention is by overall definite size L
1, L
2retrain H with H
1and H
2span.Main support plate width is L
2entirely to run through support plate Rocket ejector layout type dutycycle be L
2/ L
1, lateral wall type Rocket ejector layout type wetted perimeter is long is L
1.
In order to guarantee that T-shaped Rocket ejector layout type dutycycle is less than, entirely run through a board-like Rocket ejector layout type, need to meet:
(L
1·H
1+L
2·H
2)/(L
1·H)<L
2/L
1 (1)
Draw:
H
2<(L
2·H-L
1·H
1)/L
2 (2)
In order to guarantee that T-shaped Rocket ejector layout type wetted perimeter grows up in lateral wall type Rocket ejector layout type, need to meet: L
1<L
1+ 2H
2(3)
Only need meet H
2>0;
Meet formula (2) and formula (3) simultaneously:
0<H
2<(L
2·H-L
1·H
1)/L
2 (4)
Meaningful for assurance formula (4), must meet:
(L
2·H-L
1·H
1)/L
2>0 (5)
That is: H
1<L
2h/L
1(6)
For given distance piece 2 and mixing section 3 sectional dimension L
1, L
2in H situation, as T-shaped Rocket ejector layout dimension H
1and H
2while meeting formula (4) and formula (6), its dutycycle is less than and entirely runs through a board-like layout type, wetted perimeter is grown up in lateral wall type layout type simultaneously.
The T-shaped layout design of Rocket ejector can reduce the effect of being jammed to distance piece 2 on the one hand, has avoided entirely running through the shortcoming of a board-like Rocket ejector to distance piece 2 flow choking effects and increase flight resistance; Increase on the other hand the shearing area of injection air-flow and secondary gas flow, strengthened the injection effect of an air-flow, avoided the drawback that jet of lateral wall type Rocket ejector and secondary gas flow shearing area are little.
For the aircraft of 500 tons of take off weights, aircraft adopts six module motors, the wide L of each module mixing section 3 entrance section
1=1.50m, high H=1.05m, partly runs through center support plate Rocket ejector 5 width L
2=0.50m.According to formula: H
1<L
2h/L
1, draw H
1span be H
1<0.35m, optional value H within the scope of this
1=0.10m, brings formula into: 0<H
2< (L
2h-L
1h
1)/L
2in, further obtain H
2span be 0m<H
2<0.75m chooses H within the scope of this
2=0.30m, now, T-shaped Rocket ejector layout dutycycle is 19%, than entirely running through board-like 33%, has reduced by 42%; T-shaped Rocket ejector layout wetted perimeter is long for 2.10m, than the 1.50m of lateral wall type, has improved 40%.
Prove that by experiment the T-shaped layout of Rocket ejector of the present invention has reduced dutycycle on the one hand, compared with entirely running through a board-like Rocket ejector layout, the T-shaped layout of Rocket ejector has reduced the effect of being jammed to distance piece 2, the flight resistance while having reduced super combustion mode; Increased on the other hand Rocket ejector wetted perimeter long, compared with lateral wall type Rocket ejector layout, the T-shaped layout of Rocket ejector has improved the shearing area of injection air-flow and secondary gas flow, has strengthened the injection effect of an air-flow, is conducive to improve engine performance.
Claims (1)
1. the T-shaped layout of Rocket based combined cycle motor Rocket ejector, it is characterized in that: comprise center support plate Rocket ejector and multiple sidewall Rocket ejector, sidewall Rocket ejector is positioned at and partly runs through support plate Rocket ejector top, center, and distributes according to axial both sides horizontal symmetrical; Sidewall Rocket ejector is anterior to communicate with rocket chamber pipeline, and center support plate Rocket ejector is connected with rocket chamber by the pipeline on top, and two groups of rocket outlets are the separating surface of distance piece and mixing section; According to overall definite distance piece and mixing section entrance section size L
1, L
2and H, partly running through center support plate Rocket ejector width is L
2, mixing section and distance piece height difference are H
1, partly running through center support plate Rocket ejector height is H
2, by L
1, L
2retrain H with H
1and H
2span; Main support plate width is L
2the board-like Rocket ejector layout type dutycycle of entirely running through be L
2/ L
1, lateral wall type Rocket ejector layout type wetted perimeter is long is L
1;
For guaranteeing that T-shaped Rocket ejector layout type dutycycle is less than, entirely run through a board-like Rocket ejector layout type: (L
1h
1+ L
2h
2)/(L
1h) <L
2/ L
1, abbreviation obtains: H
2< (L
2h-L
1h
1)/L
2;
For guaranteeing T-shaped Rocket ejector layout type wetted perimeter, grow up in lateral wall type Rocket ejector layout type: L
1<L
1+ 2H
2; Meet above two dimension constraints simultaneously, obtain formula: 0<H
2< (L
2h-L
1h
1)/L
2,
For assurance formula: 0<H
2< (L
2h-L
1h
1)/L
2, must meet formula: (L
2h-L
1h
1)/L
2>0, that is: H
1<L
2h/L
1; For given distance piece and mixing section sectional dimension L
1, L
2in H situation, as T-shaped Rocket ejector layout dimension H
1and H
2meet formula: 0<H simultaneously
2< (L
2h-L
1h
1)/L
2and formula: H
1<L
2h/L
1time, its dutycycle is less than and entirely runs through a board-like Rocket ejector layout type, and wetted perimeter is grown up in lateral wall type Rocket ejector layout type.
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|---|---|---|---|
| CN201310731215.6A CN103726954B (en) | 2013-12-23 | 2013-12-23 | The T-shaped layout of a kind of Rocket based combined cycle motor Rocket ejector |
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|---|---|---|---|
| CN201310731215.6A CN103726954B (en) | 2013-12-23 | 2013-12-23 | The T-shaped layout of a kind of Rocket based combined cycle motor Rocket ejector |
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| CN103726954A true CN103726954A (en) | 2014-04-16 |
| CN103726954B CN103726954B (en) | 2015-11-18 |
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|---|---|---|---|
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109882886A (en) * | 2018-12-21 | 2019-06-14 | 西安航天动力研究所 | A kind of the RBCC engine chamber and its design method of slope rocket layout type |
| CN116335852A (en) * | 2023-02-07 | 2023-06-27 | 中国空气动力研究与发展中心空天技术研究所 | Stamping engine tail nozzle of integrated enhanced rocket and design and working methods thereof |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109882886A (en) * | 2018-12-21 | 2019-06-14 | 西安航天动力研究所 | A kind of the RBCC engine chamber and its design method of slope rocket layout type |
| CN116335852A (en) * | 2023-02-07 | 2023-06-27 | 中国空气动力研究与发展中心空天技术研究所 | Stamping engine tail nozzle of integrated enhanced rocket and design and working methods thereof |
| CN116335852B (en) * | 2023-02-07 | 2023-09-01 | 中国空气动力研究与发展中心空天技术研究所 | Stamping engine tail nozzle of integrated enhanced rocket and design and working methods thereof |
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