CN204099074U - A kind of rocket punching press combined engine with ring-like ejection structure - Google Patents
A kind of rocket punching press combined engine with ring-like ejection structure Download PDFInfo
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- CN204099074U CN204099074U CN201420272376.3U CN201420272376U CN204099074U CN 204099074 U CN204099074 U CN 204099074U CN 201420272376 U CN201420272376 U CN 201420272376U CN 204099074 U CN204099074 U CN 204099074U
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- combined engine
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Abstract
The utility model relates to a kind of rocket punching press combined engine with ring-like ejection structure, belongs to space equipment technical field.Engine housing is relative with rectification head fixing by fixed guide post, and be provided with oxidant inlet and fuel inlet in fixed guide post, the front end of shell is air inlet.Rectification head precursor stretches out the front end of engine housing, and body is step type thereafter, and insert in shell, the rear end of shell is tubaeform ultrasound velocity spout.Inner casing is fixed on the middle part of rectification head by retaining ring, is wherein provided with fuel oxidizer mixing spray mouth, forms annular combustion chamber, form hybrid combustor between shell and rectification head between inner casing and rectification head.Rocket punching press combined engine of the present utility model, reduces the size of engine chamber, alleviates the weight of combined engine, improve the economic performance of power system.Annular combustion chamber wherein impels combustion gas circumferentially evenly to spray, and the combustion gas being conducive to spraying is carried out secondary with air and mixed, and improves combustion efficiency.
Description
Technical field
The utility model relates to a kind of rocket punching press combined engine with ring-like ejection structure, belongs to space equipment technical field.
Background technique
One of key technology of rocket punching press combined engine is exactly adopt effective Rocket ejector structural type, better guarantee motor is under low speed start state, realize the abundant mixing of fuel and air as early as possible, burning is realized in the bags short as far as possible, make combined engine can produce enough large thrust at low speeds, thus ensure the power take-off of combined engine low-speed stage.This for realize combined engine structure-integrated, alleviate structure weight and have great importance.In the last few years, near space as the spatial domain between satellite and aircraft, more and more pay attention to by concerned countries.Main because in this space air and thin, and cannot meet the job requirement of airbreathing motor.But in order to this space can better be utilized, the concept of combined engine appearing in one's mind in face of people gradually.Because in this space, only have combined engine can meet hypersonic near space vehicle technical need completely.Wherein with rocket punching press combined engine and turbo ramjet engine particularly outstanding.But in actual use, the constituent elements of turbo ramjet engine is very complicated, simultaneously also too harsh to turbogenerator technical requirements; The structure of rocket punching press combined engine is then relatively simple, and Rocket ejector technology is also more ripe simultaneously.Rocket compound propulsion system is formed primarily of flow channel and the rocket motor be embedded in passage, and rocket motor can be placed in flowing center or sidewall.Flow channel can be divided into intake duct, distance piece, firing chamber and jet pipe according to the function played separately.Combined engine utilizes the oxygen in air to realize autonomous take-off and landing in an atmosphere, and self-contained propellant agent makes it can fly at air outward.For typical rocket punching press combined engine, it mainly experiences four operation modes: Ejector Mode, punching press mode, ultra-combustion ramjet mode and pure rocket mode.Ejector Mode operates mainly in 0-3 Mach number, and rocket, with maximum rating work, by high-temperature fuel gas injection secondary air, improves engine/motor specific impulse and thrust.At low speeds, ejector action accounts for leading role, compared with the punching press effect then utilizing incoming flow under High Mach number.The operating rate scope of sub-combustion punching press mode is 3-6 Mach number.Now rocket motor cuts out or with the low operating mode work of mode on duty, mainly utilizes incoming flow punching press to organize subsonic combustion.Further, in ultra-combustion ramjet mode, work Mach number, within the scope of 6-8, realizes supersonic combustion in runner.Wherein injection operation mode decides combined engine and can accelerate flight from static starting to.So injection operation mode plays a part tool foot weight concerning combined engine.But the performance characteristic of Rocket ejector is directly connected to the performance index of combined engine injection operation mode, if the performance of rocket ramjet injection operation mode better will be played, so just need to design better Rocket ejector structure and spout structure.And this is also one of key issue in these research fields.
From current research conditions, the pipe rocket motor that relatively more conventional Rocket ejector structure is mainly common, is mainly placed in flowing center or sidewall.Wherein single pipe rocket motor is substantially all arranged on combined engine flowing center, and multibarrel rocket motor mainly round flowing center uniform ring around distribution, each rocket motor works alone simultaneously.In addition, can by determining that the thrust performance of combined engine determines the number of rocket motor.But as technically realizing or the trial of useful exploration, and technology realizes the reasons such as the restriction of difficulty aspect, and these schemes all exist certain defect.
Summary of the invention
The purpose of this utility model proposes a kind of rocket punching press combined engine with ring-like ejection structure, the structure of existing rocket punching press combined engine is improved, to realize higher space availability ratio and shorter combustion chamber dimensions, improve the induction efficiency of Rocket ejector simultaneously, promote the overall performance of combined engine further.
The rocket punching press combined engine with ring-like ejection structure that the utility model proposes, comprises engine housing, inner casing, rectification head, fixed guide post and retaining ring; Described engine housing is relative with rectification head fixing by fixed guide post, and be provided with oxidant inlet and fuel inlet in fixed guide post, the front end of engine housing is air inlet; Described rectification head precursor stretches out the front end of engine housing, and after rectification head, body is step type, and after step type rectification head, body inserts in engine housing, and the rear end of engine housing is tubaeform ultrasound velocity spout; Described inner casing is fixed on the middle part of rectification head by retaining ring, is provided with fuel oxidizer mixing spray mouth in retaining ring, and described air inlet and oxidant inlet are connected with fuel oxidizer mixing spray mouth respectively; Form annular combustion chamber between described inner casing and rectification head, between described engine housing and rectification head, form hybrid combustor.
The rocket punching press combined engine with ring-like ejection structure that the utility model proposes, its advantage is, rocket punching press combined engine of the present utility model, greatly enhance the space availability ratio of Rocket ejector firing chamber, therefore can reduce the size of engine chamber, alleviate the weight of combined engine, reduce the size of the component of being correlated with simultaneously, increase the mobility of final power system product, improve the economic performance of its power system.Annular combustion chamber simultaneously in combined engine can impel combustion gas circumferentially evenly to spray, and the combustion gas being conducive to spraying is carried out secondary with air and mixed in mixing mixed combustion room, carries out the combustion efficiency after secondary afterburning to improve combined engine through annular mixing chamber.
Accompanying drawing explanation
Fig. 1 is the structural representation with the rocket punching press combined engine of ring-like ejection structure that the utility model proposes.
Fig. 2 is that the A-A of the motor shown in Fig. 1 is to sectional view.
Fig. 3 is the partial enlarged drawing at oxidant inlet and fuel inlet place in the motor shown in Fig. 1.
Fig. 4 is in the motor shown in Fig. 1, the structural representation of fixed guide post.
In Fig. 1-Fig. 4,1 is rectification head precursor, and 2 is air inlets, 3 is oxidant inlets, and 4 is fuel inlets, and 5 is fixed guide posts, 6 is retaining rings, 7 is fuel oxidizer mixing spray mouths, and 8 is annular combustion chambers, and 9 is engine housings, 10 is bodies after rectification head, 11 is hybrid combustors, and 12 is ultrasound velocity spouts, and 13 is inner casings.
Embodiment
The rocket punching press combined engine with ring-like ejection structure that the utility model proposes, its structure as shown in Figure 1, comprises engine housing 9, inner casing 13, rectification head, fixed guide post 5 and retaining ring 6.Engine housing 9 is relative with rectification head fixing by fixed guide post 5, and be provided with oxidant inlet 3 and fuel inlet 4 in fixed guide post 5, the front end of engine housing is air inlet 2, as shown in Figure 2.The precursor 1 of rectification head stretches out the front end of engine housing 9, and the rear body 10 of rectification head is in step type, and after step type rectification head, body 10 inserts in engine housing 9, and the rear end of engine housing 9 is tubaeform ultrasound velocity spout 12.Inner casing 13 is fixed on the middle part of rectification head by retaining ring 6, is provided with fuel oxidizer mixing spray mouth 7, as shown in Figure 3 in retaining ring 6.Air inlet 2 and oxidant inlet 3 are connected with fuel oxidizer mixing spray mouth 7 respectively.Form annular combustion chamber 8 between inner casing 13 and rectification head, between engine housing 9 and rectification head, form hybrid combustor 11.
In combined engine of the present utility model, the cross section of fixed guide post 5 is fusiformis, and as shown in Figure 4, the major axis of fusiformis and the axis of engine housing are parallel to each other.
The rocket punching press combined engine with ring-like ejection structure that the utility model proposes, two kinds of conventional Rocket ejector structures are effectively attached in the structure of rocket punching press combined engine, wherein use the Rocket ejector structure of annular combustion chamber, to a certain extent, improve bags utilization ratio, decrease pitot loss.The length of firing chamber can be shortened simultaneously to a great extent, thus reduce the length of combined engine.Annular combustion chamber is used for Rocket ejector, the performance of hybrid combustor is greatly improved.Simultaneously, in the physical dimension of firing chamber, also greatly can reduce the physical dimension of firing chamber, the combined engine higher for design performance provides technological reserve, finally can improve mobility and the overall performance of the aircraft using these power systems.
The rocket punching press combined engine with ring-like ejection structure that the utility model proposes, after step type rectification head wherein, body 10 reduces the airspeed after entering step, thus form low speeds flow region, a local, this region not only ensure that stable incendiary source, simultaneously the also effective effective mixing improving fuel and air.Therefore, compared with the single rocket structure design proposal of existing use, the rocket punching press combined engine of ring-like Rocket ejector structure that what the utility model proposed have, improves bags utilization ratio; Combustion gas is circumferentially evenly sprayed, impels the fuel of hybrid combustor and air fully to mix; The pitot loss that fuel injection, mixing, burning bring is less; Plug ledge structure ensures to provide stable burning things which may cause a fire disaster for hybrid combustor; The physical dimension of firing chamber and combined engine greatly reduces; Higher performance and potentiality are brought to using the hypersonic vehicle of this power system.
Below in conjunction with accompanying drawing, introduce working principle and the working procedure of the rocket punching press combined engine that the utility model proposes:
The working principle of the rocket punching press combined engine that the utility model proposes: rocket motor of the present utility model and airbreathing motor are combined, the propulsion system of composition integration.Wherein rocket punching press combined engine possesses altogether four operation modes in flight course: Ejector Mode, sub-combustion punching press mode, ultra-combustion ramjet mode and pure rocket mode.Wherein can injection operation mode normally start under being related to combined engine ground low speed.Under injection operation mode, the air that the high-temperature fuel gas discharged by Rocket ejector is come to external world carries out injection suction.And the high-temperature fuel gas that the air be inhaled into and Rocket ejector are discharged carries out blending, and the oxygen in mixed gas in unburned fuel and air carries out aftercombustion again.Due in whole injection operation mode, Rocket ejector and combined engine diffuser all create thrust, so improve the thrust of combined engine on the whole.
The working procedure of the utility model rocket punching press combined engine: fuel and oxygenant are injected in the mixing spray chamber of annular combustion chamber by pipeline, and spray into annular combustion chamber 8 by fuel oxidizer mixing spray mouth 7 high speed and burn.By the high-temperature high-pressure fuel gas Accelerating Removal that burning produces in annular combustion chamber 8, produce thrust.The high-temperature high-pressure fuel gas of simultaneously discharging produces injection pumping action, constantly from combined engine, suck air by air inlet 2, the high-temperature fuel gas that the air sucked and annular combustion chamber 8 are discharged again carries out blending burning in hybrid combustor 11, the high-temperature fuel gas produced is discharged by the ultrasound velocity spout at combined engine shell rear portion, produces thrust.
Claims (2)
1. there is a rocket punching press combined engine for ring-like ejection structure, it is characterized in that this combined engine comprises engine housing, inner casing, rectification head, fixed guide post and retaining ring; Described engine housing is relative with rectification head fixing by fixed guide post, and be provided with oxidant inlet and fuel inlet in fixed guide post, the front end of engine housing is air inlet; Described rectification head precursor stretches out the front end of engine housing, and after rectification head, body is step type, and after step type rectification head, body inserts in engine housing, and the rear end of engine housing is tubaeform ultrasound velocity spout; Described inner casing is fixed on the middle part of rectification head by retaining ring, is provided with fuel oxidizer mixing spray mouth in retaining ring, and described air inlet and oxidant inlet are connected with fuel oxidizer mixing spray mouth respectively; Form annular combustion chamber between described inner casing and rectification head, between described engine housing and rectification head, form hybrid combustor.
2. combined engine as claimed in claim 1, it is characterized in that the cross section of wherein said fixed guide post is fusiformis, the major axis of fusiformis and the axis of engine housing are parallel to each other.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420272376.3U CN204099074U (en) | 2014-05-26 | 2014-05-26 | A kind of rocket punching press combined engine with ring-like ejection structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420272376.3U CN204099074U (en) | 2014-05-26 | 2014-05-26 | A kind of rocket punching press combined engine with ring-like ejection structure |
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| Publication Number | Publication Date |
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| CN204099074U true CN204099074U (en) | 2015-01-14 |
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| CN201420272376.3U Withdrawn - After Issue CN204099074U (en) | 2014-05-26 | 2014-05-26 | A kind of rocket punching press combined engine with ring-like ejection structure |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104295406A (en) * | 2014-05-26 | 2015-01-21 | 清华大学 | Rocket stamping combination engine with annular injection structure |
| RU2744528C2 (en) * | 2019-06-14 | 2021-03-11 | Акционерное общество "НПО Энергомаш имени академика В.П. Глушко" | Method of atmospheric air ejection to increase thrust of cruise propulsion system of carrier rocket and layout of pin nozzle unit for implementation thereof |
| CN112555051A (en) * | 2020-12-04 | 2021-03-26 | 华中科技大学 | Scramjet engine based on lightning arc discharge ignition technology |
| CN115680936A (en) * | 2022-12-30 | 2023-02-03 | 北京航天动力研究所 | Cooperative air-breathing rocket-based combined cycle engine and working method thereof |
-
2014
- 2014-05-26 CN CN201420272376.3U patent/CN204099074U/en not_active Withdrawn - After Issue
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104295406A (en) * | 2014-05-26 | 2015-01-21 | 清华大学 | Rocket stamping combination engine with annular injection structure |
| CN104295406B (en) * | 2014-05-26 | 2016-08-24 | 清华大学 | A kind of rocket punching press combined engine with ring-like ejection structure |
| RU2744528C2 (en) * | 2019-06-14 | 2021-03-11 | Акционерное общество "НПО Энергомаш имени академика В.П. Глушко" | Method of atmospheric air ejection to increase thrust of cruise propulsion system of carrier rocket and layout of pin nozzle unit for implementation thereof |
| CN112555051A (en) * | 2020-12-04 | 2021-03-26 | 华中科技大学 | Scramjet engine based on lightning arc discharge ignition technology |
| CN112555051B (en) * | 2020-12-04 | 2021-11-02 | 华中科技大学 | Scramjet engine based on lightning arc discharge ignition technology |
| CN115680936A (en) * | 2022-12-30 | 2023-02-03 | 北京航天动力研究所 | Cooperative air-breathing rocket-based combined cycle engine and working method thereof |
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| Date | Code | Title | Description |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20150114 Effective date of abandoning: 20160824 |
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| C25 | Abandonment of patent right or utility model to avoid double patenting |