CN209369950U - A kind of three power combination engines of shared sub- combustion combustion chamber - Google Patents
A kind of three power combination engines of shared sub- combustion combustion chamber Download PDFInfo
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- CN209369950U CN209369950U CN201821881488.3U CN201821881488U CN209369950U CN 209369950 U CN209369950 U CN 209369950U CN 201821881488 U CN201821881488 U CN 201821881488U CN 209369950 U CN209369950 U CN 209369950U
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Abstract
A kind of three power combination engines of shared sub- combustion combustion chamber, are related to combined engine.Equipped with turbine channel, rocket channel and punching press channel；The turbine channel, rocket channel and punching press channel share in a three-dimensional and rotate into air flue and jet pipe；Turbine channel and rocket channel outlet are connected to a shared sub- combustion combustion chamber, and punching press channel is equipped with super burn combustion chamber.For the problem in turbine-punching press, sub- combustion-super burn mode conversion, a kind of three power combination engine designing techniques for introducing the rocket in parallel with turbogenerator and carrying out turbine-punching press thrust bridge joint, the serial-parallel mirror for sharing sub- combustion combustion chamber are proposed.It is mixed by forming power, while the runner form that rocket is in parallel with turbine, it can be effectively across the complexity of three power combination systems of thrust wide gap and reduction.The advantages of integrating turbogenerator high specific impulse, punching engine High Mach number and rocket engine All Speed Range.
Description
Technical field
The utility model designs combined engine, more particularly, to a kind of turbine shared sub- combustion combustion chamber in parallel with rocket
Three power combination engines.
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 all attaches great importance to the research of hypersonic aircraft technology in boundary.Currently, the academic research of re-entry space vehicle
Forward position focus turns to from the development of scramjet engine and can be realized horizontal take-off, accelerates to hypersonic combined type
The research of dynamical system, and wherein attached most importance to the development of turbine base combined cyclic engine.Turbine base combined cyclic
Engine (TBCC) refers to combined by turbogenerator with other types engine made of power device, be hypersonic flight
One of the crucial dynamical system of device realization autoacceleration, drive horizontal landing and reuse.It has flexible transmitting and
Land point, durability are high, specific thrust is big, can use conventional fuel and lubricant, and operating cost is very low and safety is very high,
It is one of following up-and-coming hypersonic power.
But in 2~3 range of Mach, TBCC dynamical system, which exists, to be difficult to be converted to punching press from turbogenerator working condition
The problem of engine behavior；And TBCC dynamical system 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, the Mach number of compression ignition punching engine work at this stage concentrates on Ma3~5, super burn punching
Hydraulic motor work Mach 2 ship Ma5~8.In order to work normally the punching engine in the range of Ma3~8 can, at this stage
Mainly use Dual-mode Scramjet, the state of Ma3~5 combustion chamber inflow Mach number be subsonic speed, Ma5 the above are
Supersonic speed.However the technical maturity is lower at present, farther out from realization engineering application.
Summary of the invention
The purpose of this utility model is to provide a kind of three power packages of the turbine shared sub- combustion combustion chamber in parallel with rocket
Close engine.
The utility model is equipped with turbine channel, rocket channel and punching press channel；The turbine channel, rocket channel and punching press
Channel shares in a three-dimensional and rotates into air flue and jet pipe；Turbine channel and rocket channel outlet are connected to a shared sub- combustion combustion
Room is burnt, punching press channel is equipped with super burn combustion chamber.
Bimodulus super burn combustion chamber can be used in the super burn combustion chamber.
The utility model for the problem in turbine-punching press, sub- combustion-super burn mode conversion, propose a kind of introducing with
The rocket of turbogenerator parallel connection carries out three power packages of turbine-punching press thrust bridge joint, the serial-parallel mirror for sharing sub- combustion combustion chamber
Close engine designing technique.The combined engine uses (turbine/punching press/rocket) with by forming power, while rocket and turbine
Runner form in parallel, can be effectively across the complexity of three power combination systems of thrust wide gap and reduction.The utility model collection whirlpool
The advantages of turbine high specific impulse, punching engine High Mach number and rocket engine All Speed Range, has technical difficulty
The advantages that moderate, reusable.
Compared with prior art, the utility model has the prominent advantages that:
Turbine described in the utility model is in parallel with rocket, shares the sub- three power combination engines for firing combustion chamber has taken into account width
Fast domain and high performance feature.In view of turbogenerator after-burner is in the nature sub- combustion combustion chamber, working principle and fire
The sub- combustion combustion chamber of arrow engine is consistent, therefore there is the possibility for being combined into one the two in working principle.The utility model
It only needs that turbogenerator can be realized and rocket engine shares a set of sub- combustion combustion chamber and spray by a fluid passage selection valve
Pipe, compared to conventional triple channel, three power combination engines, the utility model can reduce a set of sub- combustion combustion chamber and jet pipe
Structure has the advantages that simple and reliable for structure.
Detailed description of the invention
Fig. 1 is the utility model embodiment integral passage cross-sectional view.
Fig. 2 is the schematic diagram of the middle section Fig. 1 A.
Fig. 3 is the schematic diagram of the middle section Fig. 1 B.
Label in figure are as follows: 1 indicates that composite engine air intake duct, 2 indicate that rocket channel, 3 indicate turbine channel, 4 tables
Show that ultra-combustion ramjet channel, 5 indicate that jet pipe, 6 indicate that rocket engine, 7 indicate that turbogenerator, 8 indicate that turbine channel shunts
Plate, 9 indicate that rocket corridor diversion plate, 10 indicate that turbine/rocket Mode-switch device, 11 indicate that sub- combustion combustion chamber, 12 indicate fish
Flake type throat area tunable arrangement, 13 indicate that super burn combustion chamber, 14 indicate adjustable plate under super burn jet pipe, and 15 spray for super burn tail
Adjustable plate on pipe；1., 2. indicate engine different working condition when air intake duct flow distribution plate state, 3., 4. indicate engine exist
5., 6. turbine/rocket Mode-switch device state when different working condition indicates flap when engine different working condition
7. the state of formula throat area tunable arrangement indicates the state of flow distribution plate under subsonic combustion state, 8. indicates supersonic combustion
9., 10. the state of flow distribution plate under state indicates the state of adjustable plate on super burn jet pipe when engine different working condition.
Specific embodiment
Following embodiment will be further described the utility model in conjunction with attached drawing.
Referring to Fig. 1~3, the utility model embodiment is equipped with turbine channel 3, rocket channel 2 and punching press channel 4 and (can be used
Ultra-combustion ramjet channel)；Air flue is rotated into the shared three-dimensional in the turbine channel 3, rocket channel 2 and punching press channel 4 (to combine
Formula engine inlets) and jet pipe 5；The outlet in turbine channel 3 and rocket channel 2 is connected to a shared sub- combustion combustion chamber
11, punching press channel 4 is equipped with super burn combustion chamber 13 (bimodulus super burn combustion chamber can be used in super burn combustion chamber).
Air flue is rotated into the three-dimensional of the utility model there are three outlet, one connects turbine channel 3, an arrow channel 2 of starting to exchange fire,
There are one connect punching press channel 4.When flight Mach number 0~2, turbogenerator 7 and sub- combustion 11 ignition operation of combustion chamber, turbine
Corridor diversion plate 8 is opened, rocket corridor diversion plate 9 is closed, and punching press channel 4 misfires and in bleed state.When flight Mach
When number 2~3, turbine channel flow distribution plate 8 is closed, rocket corridor diversion plate 9 is opened, rocket engine 6 and sub- 11 points of combustion chamber of combustion
Firer makees, and aerial drainage is played in punching press channel 4.When flight Mach number 3~4.5, Asia combustion combustion chamber 11 stops working, rocket motor
Machine 6 works on, and aerial drainage is played in punching press channel 4.When flight Mach number 4.5~6, rocket corridor diversion plate 9 is closed, punching press
13 ignition operation of super burn combustion chamber in channel 4.The turbine that the utility model introduces is in parallel with rocket, shares the side of sub- combustion combustion chamber
Method, which not only solves the rocket engine 6 under low mach operating condition, can not start and cannot lead to the problem of enough thrust, and
Punching press channel 4 is connect with super burn combustion chamber 13, ensure that rocket engine 6 has enough thrust under High Mach number operating condition.
When flight Mach number 0~2,7 ignition operation of turbogenerator, turbine is logical in three-dimensional contract air intake duct 1 at this time
1. road flow distribution plate 8 is in the top, i.e. state；2. rocket corridor diversion plate 9 is in bottom, i.e. state；Turbine/rocket mode
3. switching device 10 is in state, allow air-flow by turbine channel 3 and punching press channel 4 but not by rocket channel 2；It is super
On combustion jet pipe 10. adjustable plate 15 is in state, but punching press channel 4 misfires and in bleed state；When flight Mach number 2~3
When, rocket engine 6 and sub- combustion combustion chamber 11 the shared sub- combustion combustion chamber of switching working mode (can) ignition operation is fiery at this time
Flow distribution plate 9 in arrow channel rotates upwards, 1. in state；Flow distribution plate 8 in turbine channel is rotated down, 2. in state；
4. turbine/rocket Mode-switch device 10 is rotated to state, so that turbine channel 3 is closed, on super burn jet pipe at adjustable plate 15
10. in state, and aerial drainage is played in 4, punching press channel, rocket channel 2 works, and 6 exit flow of rocket engine flows into sub- combustion combustion
It burns room 11 and fuel oil is mixed and burned, thrust is generated by 5 expansion work of jet pipe later.When flight Mach number is 3~4.5, fire
Arrow engine 6 stops working, and Asia combustion 11 ignition operation of combustion chamber, fish scale chip throat area tunable arrangement 12 is adjusted to state
6. on super burn jet pipe 10. adjustable plate 15 is in state, aerial drainage is played the role of in punching press channel 4.When flight Mach number is 4.5~6
When, rocket channel 2 stops working, 2. turbine channel flow distribution plate 8 and rocket corridor diversion plate 9 rotate down to state, leads to gas
Stream can not flow into 2 internal-combustion of turbine channel 3 and rocket channel, rocket engine 6, turbogenerator 7 and sub- combustion combustion chamber
11 stop working, and on super burn jet pipe 9. adjustable plate 15 is in state, and the super burn combustion chamber 13 in punching press channel 4 starts at this time
Ignition, wherein air-flow is supersonic speed in 13 inlet of super burn combustion chamber, is mixed with fuel oil, is burnt in super burn combustion chamber 13.
Later, air-flow generates thrust by 5 expansion work of jet pipe.Under different free stream Mach number states, by adjusting super burn jet pipe
Lower adjustable plate 14 controls the area of jet pipe 5, and then guarantees thrust requirements.Wherein, under sub- combustion state, super burn jet pipe is lowered
Save the upward rotation of plate 14, i.e. state 8.；Under super burn state, adjustable plate 14 is rotated down under super burn jet pipe, i.e., state is 7..Rocket
There are problems that solving punching engine under low mach and can not starting and cannot generate thrust for channel 2, plays thrust company
Continuous effect.And punching press channel 4 is connected with super burn combustion chamber 13, ensure that engine (Ma4.5~6) under High Mach number, i.e.,
Entry of combustion chamber generates thrust under the conditions of supersonic speed, to remain to work normally.
The turbine of the utility model is in parallel with rocket, shares three power combination engines of sub- combustion combustion chamber in the wide speed of holding
While domain flight and high thrust advantage, coexisting for both modalities which combustion chamber is realized, the overall performance of propulsion system is improved,
And structure is simple, is easily achieved.
Claims (2)
1. a kind of three power combination engines of shared sub- combustion combustion chamber, it is characterised in that be equipped with turbine channel, rocket channel and
Punching press channel；The turbine channel, rocket channel and punching press channel share in a three-dimensional and rotate into air flue and jet pipe；Turbine is logical
Road and rocket channel outlet are connected to a shared sub- combustion combustion chamber, and punching press channel is equipped with super burn combustion chamber.
2. a kind of three power combination engines of shared sub- combustion combustion chamber as described in claim 1, it is characterised in that the super burn
Combustion chamber uses bimodulus super burn combustion chamber.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821881488.3U CN209369950U (en) | 2018-11-15 | 2018-11-15 | A kind of three power combination engines of shared sub- combustion combustion chamber |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821881488.3U CN209369950U (en) | 2018-11-15 | 2018-11-15 | A kind of three power combination engines of shared sub- combustion combustion chamber |
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| CN209369950U true CN209369950U (en) | 2019-09-10 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115434823A (en) * | 2022-08-31 | 2022-12-06 | 西安航天动力研究所 | Rocket stamping combined engine with parallel compressor runners |
-
2018
- 2018-11-15 CN CN201821881488.3U patent/CN209369950U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115434823A (en) * | 2022-08-31 | 2022-12-06 | 西安航天动力研究所 | Rocket stamping combined engine with parallel compressor runners |
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