CN106150757A - A kind of dual pathways becomes geometry rocket based combined cycle electromotor - Google Patents
A kind of dual pathways becomes geometry rocket based combined cycle electromotor Download PDFInfo
- Publication number
- CN106150757A CN106150757A CN201610653196.3A CN201610653196A CN106150757A CN 106150757 A CN106150757 A CN 106150757A CN 201610653196 A CN201610653196 A CN 201610653196A CN 106150757 A CN106150757 A CN 106150757A
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- Prior art keywords
- rocket
- combined cycle
- pressing board
- speed
- top pressing
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
- F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
- F02K7/18—Composite ram-jet/rocket engines
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/042—Air intakes for gas-turbine plants or jet-propulsion plants having variable geometry
-
- 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
- F02K1/06—Varying effective area of jet pipe or nozzle
- F02K1/12—Varying effective area of jet pipe or nozzle by means of pivoted flaps
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Geometry (AREA)
- Testing Of Engines (AREA)
Abstract
The invention discloses a kind of dual pathways and become geometry rocket based combined cycle electromotor, use channel structure, the pattern burnt by subregion realizes the works fine of wide flight range；Under low-speed condition, the dual pathways works simultaneously, completes Ejector Mode and the work of sub-combustion mode low speed segment；Under high-speed flight state, be converted to high-speed channel and work independently, complete sub-combustion mode high regime and the work of super burn mode.Use the change geometric ways that top pressing board rotates around the shaft, it is achieved the little shrinkage ratio of low-speed condition, the regulation of the big shrinkage ratio of high-speed flight state, the air capture met in the range of starting machine width under different flight Mach numbers and air-flow compression requirements.Using binary mixed compression inlet, top pressing board is good with air intake duct side plate degree of adhesion, and mechanical dynamic seal easily realizes, and is suitable to engineer applied；Meet the power demand of aircraft different operating mode.Top pressing board and change-over panel connect the rotating shaft of double fulcrum structure respectively, and structural rigidity is good, and elevated-temperature seal easily realizes.
Description
Technical field
The present invention relates to air suction type combination punching engine field, specifically, relate to a kind of dual pathways and become geometry rocket
Base combined cycle engine.
Background technology
Rocket based combined cycle RBCC (Rocket-Based Combined Cycle) electromotor is by the rocket of high thrust-weight ratio
The air suction type punching engine organic integration of electromotor and high specific impulse in same runner, compatible injection, sub-combustion, super burn with
And pure rocket mode, it is achieved wide speed territory and the high performance operation in big spatial domain.How to ensure that same electromotor is the widest horse
Realize the works fine of each mode, and the smooth transition between different modalities in the range of conspicuous number, be to determine that the basis set conjunction of rocket follows
The key of ring engine success.And the configuration that rocket based combined cycle electromotor uses and working method play decisive
Effect.Specifically how ensure that rocket based combined cycle engine inlets meet the performance requirement under different flight state,
Ensure that air intake duct is the key technology in research with the matched well work of rocket simultaneously.
At present, conventional rocket based combined cycle engine structure scheme for " variable-geometry air intake duct+in put/side fire
Arrow+fixing geometry combustor+variable-geometry jet pipe ".Generally, for convenience of aircraft/engine integration, binary rocket is basis set
Close circulation air intake duct and realize the regulation of shrinkage ratio frequently with lifting throat height, coordinate flow control technique or boundary-layer to inhale simultaneously
Geometrical solution is become, such as " rocket based combined cycle of built-in center support plate becomes the design of geometry two dimensional inlet and numerical simulation " except waiting
(" solid-rocket technology ", the 2nd phase of volume 37,2014,184-191 page)；Side compression type rocket based combined cycle air intake duct is commonly used
Change geometrical solution then into lifting top pressing board to realize the regulation of shrinkage ratio, such as " The Strutjet Engine:The
Overlooked Option for Space Launch " (American Institute of Aeronautics and Astronautics AIAA, 95-3124, nineteen ninety-five).These are two years old
Plant air intake duct change geometric ways and all can realize the regulation of compression ratio under rocket based combined cycle air intake duct different conditions, but there is also
Certain not enough:
(1) two dimensional inlet use lifting throat change geometric ways, certainly exist between itself and combustor one section servo-actuated
Section, this both can bring serious high temperature movable sealing problem, and also can limit the layout of rocket engine, between air intake duct and rocket
Joining property is poor；
(2) flow control means using boundary-layer to absorb in air intake duct, necessarily configures additional auxiliary device, both can give
Aircraft brings redundancy quality, also brings along extra resistance；
(3) Sidewall-compression inlet uses the change geometric ways of lifting top pressing board, can cause top pressing board and side guide and prop up
Between plate, there is serious mechanical seal problem in geometric match difficulty.
Summary of the invention
The deficiency existed in order to avoid prior art, the present invention proposes a kind of dual pathways change geometry rocket based combined cycle and sends out
Motivation.
The technical solution adopted for the present invention to solve the technical problems is: include air intake duct, high-speed channel, slow channels,
Built-in rocket, combustor, jet pipe, burning intensifier, top pressing board, change-over panel, the first rotating shaft, the second rotating shaft, the first start
Mechanism, the second actuation mechanism, described air intake duct is the channel structure of high-speed channel and slow channels composition, and slow channels is positioned at
Above high-speed channel, air intake duct upper wall surface front portion is provided with top pressing board, and top pressing board one end is connected by the first rotating shaft with fuselage,
Other end top is connected with the first actuation mechanism, and the first actuation mechanism is arranged on fuselage；Air intake duct upper wall surface rear portion is provided with
Change-over panel, change-over panel one end is connected by the second rotating shaft with fuselage, and other end top is connected with the second actuation mechanism, the second start
Mechanism is arranged on fuselage；Slow channels rotates respectively with change-over panel at top pressing board and closes to when contacting with the lower wall surface of slow channels
Close；Before and after high-speed channel and slow channels upper wall surface, position is separately installed with built-in rocket, and the built-in rocket of its postmedian is positioned at tail
Jet pipe front end, combustor is positioned at high-speed channel, is provided with burning intensifier in combustor.
Described combustor is rectangle or circular configuration；Described jet pipe is unilateral expansion nozzle.
Described burning intensifier is the one of fuel support plate or cavity, or fuel support plate and cavity combination form.
Described built-in rocket is multiple.
Beneficial effect
A kind of dual pathways that the present invention proposes becomes geometry rocket based combined cycle electromotor, uses twin-channel structure, logical
The pattern crossing subregion burning realizes the works fine of wide flight range, and under low-speed condition, the dual pathways works simultaneously, completes to draw
Penetrate mode and the work of sub-combustion mode low speed segment；Under high-speed flight state, be converted to high-speed channel and work independently, complete sub-combustion mould
State high regime and the work of super burn mode；Use the change geometric ways that top pressing board rotates by a small margin around the first rotary shaft, it is achieved low
The speed little shrinkage ratio of state of flight, the regulation of the big shrinkage ratio of high-speed flight state, meet rocket based combined cycle and start machine width scope
Air capture under interior different flight Mach number and air-flow compression requirements；Become geometry air intake duct and use binary mixed pressure formula structure
Air intake duct, top pressing board and air intake duct side plate degree of adhesion are preferable, become in geometry course of action mechanical dynamic seal therebetween and are easier to
Realize, it is to avoid the use of the pneumatic control means such as extra boundary-layer absorption, be suitable for practical engineering application；By reasonably fire
The design of arrow configuration and running parameter distribution, form flexile combustion method, effectively meet aircraft difference work
Make the power demand of mode；Top pressing board and change-over panel connect the rotary shaft of double fulcrum structures respectively, and structural rigidity is good, high temperature
Sealing is easier to realize.
Accompanying drawing explanation
With embodiment, the one dual pathways of the present invention is become geometry rocket based combined cycle electromotor below in conjunction with the accompanying drawings to make
Further describe.
Fig. 1 is that the dual pathways becomes geometry rocket based combined cycle engine structure schematic diagram.
Fig. 2 is that the dual pathways becomes geometry rocket based combined cycle electromotor at 0～3 Mach of interval operating diagram.
Fig. 3 is that the dual pathways becomes geometry rocket based combined cycle electromotor at 3～4 Mach of interval operating diagram.
Fig. 4 is that the dual pathways becomes geometry rocket based combined cycle electromotor at 4～7 Mach of interval operating diagram.
Fig. 5 is the combined cycle engine of the present invention performance change curve under different Mach number.
In figure:
1. the burning of air intake duct 2. high-speed channel 3. slow channels 4. built-in rocket 5. combustor 6. jet pipe 7. strengthens
Device 8. top pressing board 9. change-over panel 10. first rotating shaft 11. second rotating shaft 12. first actuation mechanism 13. second actuation mechanism
Detailed description of the invention
The present embodiment is that a kind of dual pathways becomes geometry rocket based combined cycle electromotor.
Refering to Fig. 1～Fig. 5, it is bilateral that the present embodiment dual pathways becomes the air intake duct 1 of geometry rocket based combined cycle electromotor
Road structure, is made up of with slow channels 3 high-speed channel 2, and slow channels 3 is positioned at above high-speed channel 2.When electromotor flies at low speed
Time under row state, high-speed channel 2 and slow channels 3 work simultaneously, at the back-end region tissue high-pressure combustion of dual pathways meet；
When electromotor is under high-speed flight state, slow channels 3 closes, and high-speed channel 2 normally works, at the combustor of high-speed channel
5 inner tissue's high-pressure combustions.Wherein, jet pipe 6, as a part for high-speed channel 2, can play the effect that flow expansion is accelerated.Enter
Air flue upper wall surface front portion is provided with top pressing board 8, and top pressing board 8 one end is connected by the first rotating shaft 10 with fuselage, top pressing board 8 other end
Top is connected with the first actuation mechanism 12, and the first actuation mechanism 12 is arranged on fuselage.Air intake duct upper wall surface rear portion is provided with and turns
Changing plate 9, change-over panel 9 one end is connected by the second rotating shaft 11 with fuselage, and change-over panel 9 other end top is with the second actuation mechanism 13 even
Connecing, the second actuation mechanism 13 is arranged on fuselage.Top pressing board 8 and change-over panel 9 are all attached to low speed under low-speed condition and lead to
The upper wall surface in road 3, now, slow channels 3 is fully on；When the compressing surface of top pressing board 8 rotates an angle around the first rotating shaft 10, turn
Change plate 9 when the second rotating shaft 11 rotates an angle, top pressing board 8 with change-over panel 9 the most not lower wall surface with slow channels 3 contact, this
Time, slow channels is partially ON；Rotate when the compressing surface of top pressing board 8 continues around the first rotating shaft 10, and change-over panel 9 is around the second rotating shaft
During rotation, all lower wall surfaces with slow channels 3 contact top pressing board 8 with change-over panel 9, and now, slow channels 3 closes.Top pressing board 8 He
The rotary power of change-over panel 9 derives from actuation mechanism, and top pressing board realizes rotating clockwise under the action of the first actuation mechanism 12,
Change-over panel realizes rotating counterclockwise under the action of the second actuation mechanism 13.First actuation mechanism 12 and the second actuation mechanism 13 points
Cai Yong hydraulic means or motor be not driving force.
In high-speed channel 2 and slow channels 3, before and after upper wall surface, position is separately installed with built-in rocket 4, and wherein, rear portion is built-in
Rocket 4 is arranged on jet pipe 6 front end；The quantity of built-in rocket 4 or be one, or be multiple；Built-in rocket is at electromotor runner
The interior multistage layout of diverse location, the mounting means of built-in rocket is put in being, or is side.
Burning intensifier be laid in combustor according to the demand that subregion burn, burn intensifier be fuel support plate,
Or the one in cavity or step.Combustor be shaped as rectangle or circle.Jet pipe is unilateral expansion nozzle.
Embodiment
In the present embodiment, air intake duct 1 is arranged on the front portion of rocket based combined cycle electromotor, wherein, Design of Inlet point
Being chosen as 5 Mach, flying height is 21km.Jet pipe 6 is unilateral expansion nozzle, is arranged on rocket based combined cycle electromotor
Afterbody.Slow channels 3 is positioned at the top of high-speed channel 2, and it is 7 ° that two passages flow to angle, and converges in the front portion of jet pipe 6, gas
It is 10 ° that stream converges angle.Wherein, the two-stage external compression angle of high-speed channel 2 is respectively 6.8 ° and 11.3 °, outside the two-stage of slow channels 3
Compression angle is respectively 6.8 ° and 4 °.Top pressing board 8 is connected with the first actuation mechanism and the first rotating shaft, and change-over panel 9 and second makees motivation
Structure and the second rotating shaft connect, and slow channels 3 rotates to contacting with the lower wall surface of slow channels 3 with change-over panel 9 respectively at top pressing board 8
Time Guan Bi.Built-in rocket 4 is liquid oxygen/coal liquid rocket engine, and in rocket based combined cycle electromotor, two-stage is installed, and adopts
Porch and the rear portion of combustor 5 it is arranged in by the mode of side.Wherein, the dutycycle of built-in rocket is less than 30%,
Specified chamber pressure 10MPa, mixing ratio is 2.5, and nozzle expansion ratio is 10.Combustor 5 selects rectangular configuration, and draw ratio is 10, uses
Unilateral expanded configuration, divergence ratio is 2.Burning intensifier 7 selects two modes combining fuel support plate and one group of cavity.Its
In, two pairs of fuel support plates are laid in middle part and the rear portion of combustor 5 respectively, and one group of cavity is positioned close to first group of fuel support plate
Region, to form the burning of different modalities subregion efficient stable.The aerofluxus of rocket basis set conjunction cycle engine in the present embodiment/
Air inlet area ratio is 2.
In the present embodiment, drive the first actuation mechanism by hydraulic means or motor, make top pressing board around the first rotating shaft up time
Pin rotates；Drive the second actuation mechanism by hydraulic means or motor, make change-over panel rotate counterclockwise around the second rotating shaft.When top pressure
Plate 8 turns clockwise 7.3 ° around the first rotating shaft 10, it is achieved electromotor by the dual pathways to single pass conversion.For realizing slow channels
3 of completely closed, change-over panel 9 need to coordinate and rotates 12 ° counterclockwise around the second rotating shaft 11.
In this example, choosing rocket based combined cycle electromotor work range of Mach numbers is 0～7 Mach, its specific works
Mode is: 0～3 Mach of interval intrinsic motivation dual pathways works simultaneously；In 3～4 Mach of intervals, top pressing board 8 makees motivation by first
Structure drives, and turns clockwise by a small margin around the first rotating shaft 10, and change-over panel 9 is under the second actuation mechanism drives simultaneously, around the
Two rotating shafts 11 rotate counterclockwise, progressively close off slow channels 3, switch to high-speed channel 2 and work independently state, complete passage
Conversion；In 4～7 Mach of intervals, high-speed channel 2 works independently.
In the present embodiment, rocket based combined cycle electromotor capture discharge coefficient change song at the air of flight point
Line can be seen that, becomes geometry adjustment structure by the simple dual pathways, and rocket based combined cycle electromotor is at 0～7 Mach
In wide flight range, it is thus achieved that comprehensive preferably air capture characteristic and engine performance, there is preferably actual application valency
Value.
In the present embodiment, rocket based combined cycle electromotor uses twin-channel structure, and the pattern burnt by subregion is real
The works fine of existing wide flight range, under low-speed condition, the dual pathways works simultaneously, completes Ejector Mode and sub-combustion mode is low
The work of speed section；Under high-speed flight state, be converted to high-speed channel and work independently, complete sub-combustion mode high regime and super burn mode
Work.Rocket based combined cycle electromotor uses the change geometric ways that top pressing board rotates by a small margin around the first rotating shaft, it is achieved low
The speed little shrinkage ratio of state of flight, the regulation of the big shrinkage ratio of high-speed flight state.
Claims (4)
1. the dual pathways becomes geometry rocket based combined cycle electromotor, it is characterised in that: include air intake duct, high-speed channel, low
Speed passage, built-in rocket, combustor, jet pipe, burning intensifier, top pressing board, change-over panel, the first rotating shaft, the second rotating shaft, the
One actuation mechanism, the second actuation mechanism, described air intake duct is the channel structure of high-speed channel and slow channels composition, and low speed leads to
Road is positioned at above high-speed channel, and air intake duct upper wall surface front portion is provided with top pressing board, and top pressing board one end and fuselage are by first turn
Axle connects, and other end top is connected with the first actuation mechanism, and the first actuation mechanism is arranged on fuselage；Air intake duct upper wall surface rear portion
Being provided with change-over panel, change-over panel one end is connected by the second rotating shaft with fuselage, and other end top is connected with the second actuation mechanism, the
Two actuation mechanism are arranged on fuselage；Slow channels rotates respectively with change-over panel to the lower wall surface with slow channels at top pressing board and connects
Guan Bi when touching；Before and after high-speed channel and slow channels upper wall surface, position is separately installed with built-in rocket, the built-in rocket of its postmedian
Being positioned at jet pipe front end, combustor is positioned at high-speed channel, is provided with burning intensifier in combustor.
The dual pathways the most according to claim 1 becomes geometry rocket based combined cycle electromotor, it is characterised in that: described burning
Room is rectangle or circular configuration；Described jet pipe is unilateral expansion nozzle.
The dual pathways the most according to claim 1 becomes geometry rocket based combined cycle electromotor, it is characterised in that: described burning
Intensifier is the one of fuel support plate or cavity, or fuel support plate and cavity combination form.
The dual pathways the most according to claim 1 becomes geometry rocket based combined cycle electromotor, it is characterised in that: described built-in
Rocket is multiple.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201610653196.3A CN106150757A (en) | 2016-08-10 | 2016-08-10 | A kind of dual pathways becomes geometry rocket based combined cycle electromotor |
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| CN201610653196.3A CN106150757A (en) | 2016-08-10 | 2016-08-10 | A kind of dual pathways becomes geometry rocket based combined cycle electromotor |
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Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107013334A (en) * | 2017-02-17 | 2017-08-04 | 北京动力机械研究所 | A kind of double combustion chamber's Scramjet Inlet and air intake control method |
| CN107013332A (en) * | 2017-02-17 | 2017-08-04 | 北京动力机械研究所 | A kind of variable geometry inlet |
| CN107013368A (en) * | 2017-02-17 | 2017-08-04 | 北京动力机械研究所 | Turbine base double combustion chamber's punching press combined cycle engine control method |
| CN107013327A (en) * | 2017-02-17 | 2017-08-04 | 北京动力机械研究所 | A kind of double combustion chamber's scramjet engine and its control method |
| CN107061010A (en) * | 2017-03-23 | 2017-08-18 | 西北工业大学 | A kind of rocket based combined cycle engine structure changes air intake duct |
| CN107448296A (en) * | 2017-08-07 | 2017-12-08 | 南京航空航天大学 | 07 grades of combined engine air intake ducts of Mach number of pneumatic type/mechanical combination regulation |
| CN106968835B (en) * | 2017-04-14 | 2018-07-06 | 西北工业大学 | Full runner is combined in a kind of rocket punching press of wide scope work |
| CN109101765A (en) * | 2018-09-19 | 2018-12-28 | 西北工业大学 | A kind of wide fast domain propulsion system modelling by mechanism method of big envelope curve of assembly power aircraft |
| CN109236472A (en) * | 2018-11-27 | 2019-01-18 | 北京航空航天大学 | A kind of axial symmetry change geometry bimodal air intake duct adapting to broad Mach number |
| CN109436347A (en) * | 2018-10-12 | 2019-03-08 | 北京动力机械研究所 | Engine binary channels list movable member air inlet regulating device |
| CN109436346A (en) * | 2018-10-12 | 2019-03-08 | 北京动力机械研究所 | Engine binary channels list movable member air inlet adjustment method |
| CN111255569A (en) * | 2020-01-13 | 2020-06-09 | 南京航空航天大学 | Mode conversion and variable geometry combined adjusting internal parallel type air inlet and control method |
| CN112627983A (en) * | 2020-12-25 | 2021-04-09 | 中国人民解放军国防科技大学 | RBCC engine inner flow channel and RBCC engine |
| CN112983675A (en) * | 2021-03-04 | 2021-06-18 | 中国人民解放军国防科技大学 | Rocket-based combined cycle engine with expandable air inlet |
| CN113323756A (en) * | 2021-06-22 | 2021-08-31 | 西安航天动力研究所 | Double-flow-passage graded adjustable wide-range air inlet passage, engine and air inlet adjusting method |
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| CN107013368A (en) * | 2017-02-17 | 2017-08-04 | 北京动力机械研究所 | Turbine base double combustion chamber's punching press combined cycle engine control method |
| CN107013327A (en) * | 2017-02-17 | 2017-08-04 | 北京动力机械研究所 | A kind of double combustion chamber's scramjet engine and its control method |
| CN107013368B (en) * | 2017-02-17 | 2018-06-12 | 北京动力机械研究所 | Turbine base double combustion chamber's punching press combined cycle engine control method |
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| CN107013327B (en) * | 2017-02-17 | 2018-07-20 | 北京动力机械研究所 | A kind of double combustion chamber's scramjet engine and its control method |
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| CN107061010A (en) * | 2017-03-23 | 2017-08-18 | 西北工业大学 | A kind of rocket based combined cycle engine structure changes air intake duct |
| CN107061010B (en) * | 2017-03-23 | 2019-01-01 | 西北工业大学 | A kind of rocket based combined cycle engine structure changes air intake duct |
| CN106968835B (en) * | 2017-04-14 | 2018-07-06 | 西北工业大学 | Full runner is combined in a kind of rocket punching press of wide scope work |
| CN107448296A (en) * | 2017-08-07 | 2017-12-08 | 南京航空航天大学 | 07 grades of combined engine air intake ducts of Mach number of pneumatic type/mechanical combination regulation |
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