CN209083430U - The turbofan punching press combined engine of rocket built in a kind of outer culvert - Google Patents
The turbofan punching press combined engine of rocket built in a kind of outer culvert Download PDFInfo
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- CN209083430U CN209083430U CN201821805166.0U CN201821805166U CN209083430U CN 209083430 U CN209083430 U CN 209083430U CN 201821805166 U CN201821805166 U CN 201821805166U CN 209083430 U CN209083430 U CN 209083430U
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Abstract
The turbofan punching press combined engine of rocket, belongs to combined engine field built in a kind of outer culvert, including air flue, turbofan-Asia combustion combination channel, ultra-combustion ramjet channel and jet pipe are rotated into three-dimensional；Air flue is rotated into three-dimensional equipped with first outlet and second outlet；Jet pipe is equipped with first entrance and second entrance；Turbofan-Asia combustion combination channel entrance connects with first outlet, and the outlet of turbofan-Asia combustion combination channel connects with the first entrance of jet pipe；It is sequentially installed with fanjet and sub- combustion combustion chamber from the inlet to the outlet in turbofan-Asia combustion combination channel；The entrance in ultra-combustion ramjet channel connects with second outlet, and the outlet in ultra-combustion ramjet channel connects with the second entrance of jet pipe；It is equipped with super burn combustion chamber in ultra-combustion ramjet channel, while wide fast domain flight and high specific impulse advantage can be kept, realizes coexisting for both modalities which combustion chamber, improves the overall performance of propulsion system, have many advantages, such as that simple and reliable for structure, technical difficulty is moderate.
Description
Technical field
The utility model relates to combined engine fields, more particularly to a kind of outer turbofan punching press for containing built-in rocket to combine hair
Motivation.
Background technique
Hypersonic flight is considered as the third time revolution after propeller and jet-propulsion, the generation headed by the U.S.
Major military power, boundary all attaches great importance to the research of hypersonic aircraft technology.Currently, the science of hypersonic aircraft is ground
Study carefully forward position focus turned to from the development of scramjet engine can be realized horizontal take-off, independently accelerate to it is hypersonic
The research of combined moving Force system, and wherein attached most importance to the development of turbine base combined cyclic engine.The combination of turbine base
Formula cycle engine (TBCC) refers to combined by turbogenerator with other types engine made of power device, be Gao Chaosheng
Fast aircraft realizes one of autonomous acceleration, drive horizontal landing and crucial dynamical system of reuse, has flexible
Launch and landing place, durability is high, specific thrust is big, can use conventional fuel and lubricant, and operating cost is lower and pacifies
The advantages that property is higher entirely is one of following up-and-coming hypersonic power.
The work Mach number of turbogenerator is mainly Mach 0~2, punching engine work Mach 2 ship Ma3 at this stage
~6+, in 2~3 range of Mach number, there are turbogenerator work Mach numbers not to increase for TBCC dynamical system, punching engine
Work Mach number the problem of being unable to come down, combined engine thrust is difficult to meet aircraft thrust demand in mode conversion process, falls into
Enter " the thrust wide gap " for being difficult to go beyond；In addition, existing turbogenerator mainly uses fanjet structure type, and turbofan is sent out
Motivation after-burner is in the nature sub- combustion combustion chamber.
Summary of the invention
Utility model aims to solve the above problem in the prior art, the whirlpool for containing built-in rocket outside one kind is provided
Punching press combined engine is fanned, while wide fast domain flight and high specific impulse advantage can be kept, realizes coexisting for both modalities which combustion chamber,
The overall performance for improving propulsion system, has many advantages, such as that simple and reliable for structure, technical difficulty is moderate.
In order to achieve the above objectives, the utility model adopts the following technical solution:
The turbofan punching press combined engine of rocket built in a kind of outer culvert, including air flue, turbofan-Asia combustion combination are rotated into three-dimensional
Channel, ultra-combustion ramjet channel and jet pipe；
Air flue is rotated into the three-dimensional equipped with first outlet and second outlet；
The jet pipe is equipped with first entrance and second entrance；
The turbofan-Asia combustion combination channel entrance connects with first outlet, the outlet of turbofan-Asia combustion combination channel and tail
The first entrance of jet pipe connects；Turbofan-Asia is sequentially installed with fanjet and sub- combustion in combustion combination channel from the inlet to the outlet
Combustion chamber；The fanjet is installed on turbofan-Asia combustion combination feeder connection one end, and the sub- combustion combustion chamber is installed on whirlpool
Fan-Asia combustion combination channel outlet one end；
The entrance in the ultra-combustion ramjet channel connects with second outlet, and the second of the outlet in ultra-combustion ramjet channel and jet pipe
Entrance connects；Super burn combustion chamber is equipped in ultra-combustion ramjet channel.
The fanjet is equipped with outer culvert channel and intension channel, and rocket engine is arranged in outer culvert using plate form
In channel.
The utility model further includes air intake duct flow distribution plate, adjustable throat, adjustable plate under adjustable plate and jet pipe on jet pipe；It is described
Air intake duct flow distribution plate is articulated at the first outlet for rotating into air flue in three-dimensional, to open or close turbofan-Asia combustion combination channel
Entrance；The adjustable throat is installed on the first access point of jet pipe；The outlet end of adjustable throat is hinged with the jet pipe up-regulation
Plate is saved, adjustable plate rotatable movement is on jet pipe to open or close the outlet of turbofan-Asia combustion combination channel；It is adjusted under the jet pipe
Plate is installed at the second entrance of jet pipe, and adjustable plate can move up and down to adjust the area of jet pipe under jet pipe.
The working principle of the utility model is as follows:
1, air flue is rotated into three-dimensional there are two outlet, first outlet connects turbofan-Asia combustion combination channel, and second outlet connects super burn
Punching press channel, Asia combustion combination channel is connected with ultra-combustion ramjet channel by two entrances and common nozzle for turbofan-.
2, when flight Mach number 0~2, turbofan-Asia combustion combination channel is opened, fanjet and as its afterbunring
The sub- combustion combustion chamber ignition work of room, turbofan-Asia combustion combination channel are in fanjet operating mode, and ultra-combustion ramjet channel is not
Point is fought in bleed state.
3, when flight Mach number 2~3, fanjet is closed and in windmill condition, and rocket motor ignition works,
Asia combustion combustion chamber keeps burning, and turbofan-Asia combustion combination channel is in Rocket ejector Asia burning ramjet operating mode, super burn punching
Pressure passageway plays aerial drainage.
4, when flight Mach number 3~4.5, rocket engine stops working, and Asia combustion combustion chamber keeps burning, turbofan-Asia
Combustion combination channel is in sub- burning ramjet operating mode, the super burn combustion chamber ignition work in ultra-combustion ramjet channel.
5, when flight Mach number 4.5~6+When, turbofan-Asia combustion is combined in adjustable plate rotation on air intake duct flow distribution plate and jet pipe
Channel is closed, and the super burn combustion chamber in ultra-combustion ramjet channel keeps burning.
Compared with the existing technology, the beneficial effect that technical solutions of the utility model obtain is:
1, the utility model forms power in such a way that rocket engine is placed in fanjet by-pass air duct and uses with
(turbine/punching press/rocket) merges fanjet after-burner and sub- burning ramjet combustion chamber, rocket hair
When motivation and sub- burning ramjet are worked together in same pipeline, due to ejector action, both gross thrust is greater than independent work
The sum of make, it can be effectively across thrust wide gap and the complexity of three power combination systems of reduction.
2, the utility model collection fanjet high specific impulse, punching engine High Mach number and rocket engine All Speed Range
Advantage, realizes coexisting for both modalities which combustion chamber, improves the overall performance of propulsion system.
3, the utility model shares a set of sub- combustion combustion chamber by fanjet and Rocket ejector Asia burning ramjet
And jet pipe, make it that can reduce a set of sub- combustion combustion chamber and jet pipe compared to conventional triple channel, three power combination engines
Structure has the advantages that simple and reliable for structure, technical difficulty is moderate.
4, the rocket engine solves fanjet and punching engine in Ma2~3 and can not generate enough
The problem of thrust, plays the role of guaranteeing thrust continuously；Ultra-combustion ramjet channel and super burn combustion chamber ensure that combined engine
Ma4.5~6 under High Mach number+Aircraft/the dynamical system of (i.e. entry of combustion chamber is under the conditions of supersonic speed) pushes away resistance balance.
Detailed description of the invention
Fig. 1 is the overall structure diagram of the utility model；
Fig. 2 is the schematic diagram of internal structure of the utility model；
Fig. 3 is the schematic cross-sectional view that turbofan-Asia combustion combination channel is opened；
Fig. 4 is the schematic cross-sectional view that turbofan-Asia combustion combination channel is closed；
Fig. 5 is the operation principle schematic diagram of the utility model；
Fig. 6 is turbofan-Asia combustion combination channel plane partial enlargement diagram.
Appended drawing reference: rotating into air flue in 1 three-dimensional, outside 2 culvert channel, 3 intension channels, 4 ultra-combustion ramjet channels, 5 jet pipes, and 6
Rocket engine, 7 fanjet core engines, 8 fanjet fans, adjustable plate under 9 jet pipes, adjustable plate on 10 jet pipes, 11
Asia combustion combustion chamber, 12 turbofans-Asia combustion combination channel, 13 air intake duct flow distribution plates, 14 super burn combustion chambers, 15 adjustable throats, first goes out
1. and 2. mouth 16, second outlet 17, first entrance 18, second entrance 19 indicate air intake duct point when engine different working condition
3. and 4. the position of flowing plate indicates the position of super burn combustion chamber adjustable plate under jet pipe in different working condition, 5. and 6. indicates
7. and 8. the position of super burn combustion chamber adjustable plate on jet pipe in different working condition indicates sub- combustion combustion chamber in different operating shape
The position that adjustable throat is adjusted when state.
Specific embodiment
In order to keep technical problem to be solved in the utility model, technical solution and beneficial effect clearer, tie below
Drawings and examples are closed, the utility model is described in further details.
As shown in Fig. 1~5, the utility model includes that air flue 1, turbofan-Asia combustion combination channel 12, super burn punching are rotated into three-dimensional
Pressure is logical 4, adjustable plate 9 and rocket under adjustable plate 10, jet pipe on jet pipe 5, air intake duct flow distribution plate 13, adjustable throat 15, jet pipe
Engine 6.
Air flue 1 is rotated into the three-dimensional equipped with first outlet 16 and second outlet 17.
The jet pipe 5 is equipped with first entrance 18 and second entrance 19.
The turbofan-Asia combustion combination channel 12 entrance connects with first outlet 16, and turbofan-Asia combustion combination channel 12 goes out
Mouth connects with the first entrance 18 of jet pipe 5；Turbofan-Asia is sequentially installed with turbofan hair in combustion combination channel 12 from the inlet to the outlet
Motivation and sub- combustion combustion chamber 11, fanjet includes the fanjet fan 8 of front end and the fanjet core of rear end
Machine 7, the fanjet are installed on one end that logical 12 entrances are combined in turbofan-Asia combustion, and the sub- combustion combustion chamber 11 is installed on whirlpool
One end that fan-Asia combustion combination channel 12 exports.
The entrance in the ultra-combustion ramjet channel 4 connects with second outlet 17, the outlet in ultra-combustion ramjet channel 4 and jet pipe 5
Second entrance 19 connect；Super burn combustion chamber 14 is equipped in ultra-combustion ramjet channel 4.
As figures 2-6, the fanjet is equipped with outer culvert channel 2 and intension channel 3, and rocket engine 6 is using slotting
Plate form is arranged in outer culvert channel 2.
The air intake duct flow distribution plate 13 is articulated at the first outlet 16 for rotating into air flue 1 in three-dimensional, to open or close whirlpool
Fan-Asia combustion combination channel 12 entrance.
The adjustable throat 15 is installed at the first entrance 18 of jet pipe 5；The outlet end of adjustable throat 15 is hingedly
Adjustable plate 10 on jet pipe are stated, 10 rotatable movement of adjustable plate goes out on jet pipe to open or close turbofan-Asia combustion combination channel 12
Mouthful；
Adjustable plate 9 is installed at the second entrance 19 of jet pipe 5 under the jet pipe, and adjustable plate 9 can move up and down under jet pipe
To adjust the area of jet pipe 5.
As shown in figure 5, the working process and principle of the utility model are as follows:
1, when flight Mach number is 0~2, as shown in Figures 3 and 5, the air intake duct flow distribution plate 13 in air flue 1 is rotated into three-dimensional
1., adjustable plate 10 is rotated down in the open state on jet pipe for the top in first outlet 16, i.e. state, i.e., state 5.,
At this point, turbofan-Asia combustion combination channel 12 is in the open state, turbofan-Asia combustion combination channel 12 is caused air flow through, turbofan is sent out at this time
Motivation and sub- combustion 11 ignition operation of combustion chamber as its after-burner, ultra-combustion ramjet channel 4 misfires and in aerial drainage shape
State；
2, when flight Mach number is 2~3, the position of adjustable plate 10 is constant on air intake duct flow distribution plate 13 and jet pipe, turbofan
Engine is in windmill condition, 6 ignition of rocket engine, and Asia combustion combustion chamber 11 works on, and the air-flow of generation passes through can
It adjusts venturi 15 to accelerate and generates thrust；
3, when flight Mach number is 3~4.5, rocket engine 6 stops working, and Asia combustion combustion chamber 11 works independently, and surpasses
It fires combustion chamber 14 to light a fire, ultra-combustion ramjet channel 4 is in igniter chamber state；It, can when turbofan-Asia combustion combination channel 12 works
It adjusts venturi 15 by state 7. to state 8. electrodeless variation, guarantees that flow can be normal through；
4, when flight Mach number is 4.5~6+When, as shown in Figures 4 and 5, air intake duct flow distribution plate 13 rotates down to state
2. on jet pipe 6. adjustable plate 10 is rotated upwardly to state, so that turbofan-Asia combustion combination channel 12 is closed, rocket 6, turbofan hair
Motivation and sub- combustion combustion chamber 11 stop working, and super burn combustion chamber 14 keeps combustion state at this time, and air-flow is expanded by jet pipe 5
Acting generates thrust；Under different free stream Mach number states, the area of jet pipe is controlled by adjustable plate 9 under adjustable jet tube, into
And guarantee thrust requirements；With the raising of free stream Mach number, adjustable plate 9 is by state 3. to state 4. electrodeless adjustment under jet pipe.
The utility model, which not only solves the punching engine under low mach operating condition, can not start and cannot generate enough
The problem of thrust, and the individually designed of super burn combustion chamber ensure that assembly power has enough push away under High Mach number operating condition
Power.
Claims (7)
1. a kind of outer turbofan punching press combined engine for containing built-in rocket, it is characterised in that: including rotating into air flue, whirlpool in three-dimensional
Fan-Asia combustion combination channel, ultra-combustion ramjet channel and jet pipe；Air flue is rotated into three-dimensional equipped with first outlet and second outlet；Tail
Jet pipe is equipped with first entrance and second entrance；Turbofan-Asia combustion combination channel entrance connects with first outlet, turbofan-Asia combustion group
The outlet for closing channel connects with the first entrance of jet pipe；Turbofan-Asia is sequentially installed with from the inlet to the outlet in combustion combination channel
Fanjet and sub- combustion combustion chamber；The entrance in ultra-combustion ramjet channel connects with second outlet, the outlet in ultra-combustion ramjet channel with
The second entrance of jet pipe connects；Super burn combustion chamber is equipped in ultra-combustion ramjet channel.
2. a kind of outer turbofan punching press combined engine for containing built-in rocket as described in claim 1, it is characterised in that: the whirlpool
Fan engine is equipped with outer culvert channel and intension channel, and rocket engine is arranged in outer culvert channel using plate form.
3. a kind of outer turbofan punching press combined engine for containing built-in rocket as described in claim 1, it is characterised in that: further include
Air intake duct flow distribution plate, the air intake duct flow distribution plate are articulated at the first outlet for rotating into air flue in three-dimensional, to open or close whirlpool
Fan-Asia combustion combination channel entrance.
4. a kind of outer turbofan punching press combined engine for containing built-in rocket as described in claim 1, it is characterised in that: the tail
The first access point of jet pipe is equipped with adjustable throat.
5. the as claimed in claim 4 a kind of outer turbofan punching press combined engine for containing built-in rocket, it is characterised in that: it is described can
The outlet end of venturi is adjusted to be hinged with adjustable plate on jet pipe, adjustable plate rotatable movement is on the jet pipe to open or close turbofan-
The outlet in Asia combustion combination channel.
6. a kind of outer turbofan punching press combined engine for containing built-in rocket as described in claim 1, it is characterised in that: further include
Adjustable plate under jet pipe, adjustable plate is installed at the second entrance of jet pipe under the jet pipe, and adjustable plate can move up and down under jet pipe
To adjust the area of jet pipe.
7. a kind of outer turbofan punching press combined engine for containing built-in rocket as described in claim 1, it is characterised in that: the whirlpool
Fan engine is installed on turbofan-Asia combustion combination feeder connection one end, and it is logical that the sub- combustion combustion chamber is installed on turbofan-Asia combustion combination
One end of road outlet.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821805166.0U CN209083430U (en) | 2018-11-02 | 2018-11-02 | The turbofan punching press combined engine of rocket built in a kind of outer culvert |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821805166.0U CN209083430U (en) | 2018-11-02 | 2018-11-02 | The turbofan punching press combined engine of rocket built in a kind of outer culvert |
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| Publication Number | Publication Date |
|---|---|
| CN209083430U true CN209083430U (en) | 2019-07-09 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201821805166.0U Active CN209083430U (en) | 2018-11-02 | 2018-11-02 | The turbofan punching press combined engine of rocket built in a kind of outer culvert |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109408993A (en) * | 2018-11-02 | 2019-03-01 | 厦门大学 | The design method of the turbofan punching press combined engine of rocket built in a kind of outer culvert |
| CN111594348A (en) * | 2020-05-01 | 2020-08-28 | 西北工业大学 | Starting control method for rocket-based combined cycle engine air inlet |
-
2018
- 2018-11-02 CN CN201821805166.0U patent/CN209083430U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109408993A (en) * | 2018-11-02 | 2019-03-01 | 厦门大学 | The design method of the turbofan punching press combined engine of rocket built in a kind of outer culvert |
| CN111594348A (en) * | 2020-05-01 | 2020-08-28 | 西北工业大学 | Starting control method for rocket-based combined cycle engine air inlet |
| CN111594348B (en) * | 2020-05-01 | 2023-03-10 | 西北工业大学 | Starting control method for rocket-based combined cycle engine air inlet |
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