CN107894010A - A kind of laminated board type scramjet engine combustion chamber - Google Patents
A kind of laminated board type scramjet engine combustion chamber Download PDFInfo
- Publication number
- CN107894010A CN107894010A CN201710831675.4A CN201710831675A CN107894010A CN 107894010 A CN107894010 A CN 107894010A CN 201710831675 A CN201710831675 A CN 201710831675A CN 107894010 A CN107894010 A CN 107894010A
- Authority
- CN
- China
- Prior art keywords
- combustion chamber
- laminate
- laminated board
- board type
- scramjet engine
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
Abstract
The invention belongs to engine chamber technology, more particularly to a kind of laminated board type scramjet engine combustion chamber.Laminated board type scramjet engine combustion chamber of the present invention includes combustion chamber (1), combustion chamber import (5), combustor exit (7), laminate (2).Wherein, combustion chamber import (5) air-flow is supersonic flow, combustion chamber (1) indoor design has some laminates (2), combustion chamber (1) is divided into some small combustion chambers, after supersonic flow enters combustion chamber import (5), in the presence of laminate (2), air-flow is divided into multiple passages into combustion chamber (1) inside, is flowed out again from combustor exit (7) after burning.Fuel oil of the present invention injection and laminate and combustion chamber are using integrated, and overall structure is simple, and thermal protection requires low, effectively increases air-flow in combustion chamber residence time, and fuel oil projected area is big, and overlay area is wide, can fully burn, guarantee efficiency of combustion.
Description
Technical field
The invention belongs to engine chamber technology, more particularly to a kind of laminated board type scramjet engine combustion chamber.
Background technology
Scramjet engine be mainly characterized by realizing fuel flowed in supersonic speed in stable burning.Due to supersonic speed
The residence time that air flows through engine chamber is very short, wants to carry out efficiently mixing and burning with fuel within the extremely short time
It is extremely difficult thing.Super burn is mainly realized in scramjet engine combustion chamber using central burner or hollow technical at present
The supersonic combustion and flame stabilization of scramjet combustor.
United States Patent (USP) US2008/0092519A1, USPat7797943B2 proposes the mechanism of central burner super burn engine
And superiority, cavity combustion technology are applied on Russian Kholod scramjet engines.But central burner
Super burn engine structure is complicated, and the ratio of core air-flow is less than normal, can increase the cross-sectional area of combustion chamber.Cavity burning can increase combustion
The pressure loss during burning, and cause Inner Wall of Combustion Chamber thermal protection heavy load.In view of supersonic combustion performance boost pair
The significance of scramjet engine, therefore, the invention provides a kind of brand-new scramjet engine Combustion chamber design
Thinking.
The content of the invention
The purpose of the present invention is：One kind is provided while improving combustion efficiency, simplifies chamber structure, effectively reduces hair
The laminated board type scramjet engine combustion chamber of motivation thermal protection difficulty.
The technical scheme is that：
The solution have the advantages that：During laminated board type scramjet engine of the present invention work, combustion chamber inlet air flow with
Supersonic speed enters engine chamber, and in the presence of laminate, air-flow is divided into multiple passages and enters combustion chamber, simultaneously because laminate
The influence of leading edge, air-flow are opened up to a series of oblique shock wave strings are formed along laminate, effectively reduce the shock loss in combustion chamber.By
Boundary-layer is thicker in laminate, oblique shock wave Boundary Layer Interaction, is easier to form low speed recirculating zone, adds air-flow and is firing
Room residence time is burnt, is advantageous to fully burn.In addition, fuel oil injection uses integrated, entirety with laminate and combustion chamber
Simple in construction, projected area is big, and overlay area is wide, while chamber temperature is higher, and atomizing effect is better, is more advantageous to burn,
It is similar with the vaporizer tube combustor of aero-engine.
Brief description of the drawings
Fig. 1 is a kind of front view of laminated board type scramjet engine combustion chamber；
Fig. 2 is a kind of positive direction view of laminated board type scramjet engine combustion chamber,
Wherein, 1 combustion chamber, 2 laminates, 3 oblique shock wave strings, 4 fuel injection apertures, 5 combustion chamber imports, 6 fuel pump deliver lines,
7 combustor exits, 8 Inner Wall of Combustion Chamber, 9 fuel manifolds, 10 laminate heads, 11 boundary-layers, 12 outer wall of combustion chamber, 13 laminates lead to
Road.
Embodiment
The present invention will be further described with reference to the accompanying drawings and examples：
Refering to shown in Fig. 1, Fig. 2, the invention discloses a kind of laminated board type scramjet engine combustion chamber.In this embodiment party
In formula, the laminated board type scramjet engine combustion chamber is applied in scramjet engine.
Laminated board type burning scramjet engine combustion chamber of the present invention goes out including combustion chamber 1, combustion chamber import 5, combustion chamber
Mouth 7, laminate 2.Wherein, the combustion chamber is scramjet combustor, and the air-flow of combustion chamber import 5 is supersonic flow.It is described
Some laminates 2 be arrangeding in parallel are designed with along airflow direction inside combustion chamber 1, the interval of combustion chamber 1 is divided into some small burnings
Room.After supersonic flow enters combustion chamber import 5, in the presence of laminate 2, air-flow is divided into multiple passages and entered in combustion chamber 1
Portion.
The laminate leading edge 10 is wedge shape, and most leading edge sharp corner will be suitably passivated, and wedge angle depends on combustion chamber import 5
Gasflow mach number and the height of 1 laminate passage of combustion chamber 13, wedge angle is no more than 30 °.Supersonic flow enters into combustion chamber
After mouth 5, in the presence of laminate leading edge 10, oblique shock wave is formed, in laminate under the reflex of laminate 2 and Inner Wall of Combustion Chamber 8
A series of oblique shock wave strings 3 are formd in passage 13.
After supersonic flow enters combustion chamber import 5 simultaneously, thicker boundary-layer 11, laminate passage 13 can be formed on laminate
Oblique shock wave string 3 interfered with boundary-layer 11, form recirculating zone, be advantageous to stable burn.
The laminate 2 is hollow structure, and is connected as one with Inner Wall of Combustion Chamber 8, therefore simple in construction.Inside laminate 2
Comprising fuel pump deliver line 6, the surface face airflow direction of laminate 2 offers some fuel injection apertures 4, for fuel atomizing
Injection.
In addition, it is equipped with fuel manifold 9, fuel between the Inner Wall of Combustion Chamber 8 and outer wall of combustion chamber 12 of combustion chamber of the present invention
House steward 9 communicates with the fuel pump deliver line 6 inside laminate 2, the fuel pump deliver line 6 inside laminate 2 and the phase of fuel injection aperture 4
Even, so as to realize that fuel oil injection is integrated with laminate 2, structure, therefore overall structure are connected as one plus with combustion chamber
Simply, core air-flow ratio is big, effectively reduces engine thermal protection difficulty.
Referring again to Fig. 1, Fig. 2, when scramjet engine works, the air-flow of combustion chamber import 5 is entered with supersonic speed to be started
Machine combustion chamber 1, in the presence of laminate 2, air-flow is divided into multiple passages and enters combustion chamber 1, simultaneously because the shadow of laminate leading edge 10
Ring, air-flow is opened up to a series of oblique shock wave strings 3 are formed along laminate 2, effectively reduces the shock loss of air-flow.Due to attached in laminate
Surface layer 11 is thicker, and oblique shock wave string 3 interacts with boundary-layer 11, is relatively easy to form low speed recirculating zone, adds air-flow and is burning
Room residence time, be advantageous to fully burn.Fuel oil injection is integrated with laminate 2, and projected area is big, and overlay area is wide,
Simultaneously similar with the vaporizer tube combustor of aero-engine, the temperature of laminate 2 is higher, and atomizing effect is better, is more advantageous to burn, from
And the efficiency of combustion of combustion chamber is effectively ensured.
In summary, before laminated board type scramjet engine combustion chamber of the present invention has high engineer applied
Scape.
The method and approach that the present invention implements are more, and described above is only the preferred embodiments of the invention, right
For those skilled in the art, under the premise without departing from the principles of the invention, some improvement can also be made,
These improvement should also be considered as protection scope of the present invention.The available prior art of each part being not known in the present embodiment
Realized.
Claims (7)
- A kind of 1. laminated board type scramjet engine combustion chamber, it is characterised in that including combustion chamber (1), combustion chamber import (5), Combustor exit (7), laminate (2), wherein, combustion chamber import (5) air-flow is supersonic flow, is set inside combustion chamber (1) In respect of some laminates (2), combustion chamber (1) is divided into some small combustion chambers, after supersonic flow enters combustion chamber import (5), In the presence of laminate (2), air-flow is divided into multiple passages into combustion chamber (1) inside, goes out again from combustor exit (7) after burning Go.
- 2. laminated board type scramjet engine combustion chamber according to claim 1, it is characterised in that laminate (2) and burning Chamber interior walls (8) are connected, and are the part of combustion chamber (1) structure, and laminate leading edge (10) is wedge shape.
- 3. laminated board type scramjet engine combustion chamber according to claim 2, it is characterised in that laminate (2) is hollow Structure, laminate (2) is internal to include fuel pump deliver line (6).
- 4. laminated board type scramjet engine combustion chamber according to claim 3, it is characterised in that laminate (2) surface is just Some fuel injection apertures (4), fuel injection aperture (4) fuel -supply pipe internal with laminate (2) are offered to airflow direction Road (6) is connected.
- 5. laminated board type scramjet engine combustion chamber according to claim 4, it is characterised in that the combustion chamber of combustion chamber Fuel manifold (9) is equipped between inwall (8) and outer wall of combustion chamber (12), fuel manifold (9) fuel internal with laminate (2) is defeated Pipeline (6) is sent to communicate.
- 6. laminated board type scramjet engine combustion chamber according to claim 5, it is characterised in that supersonic flow enters After combustion chamber import (5), in the presence of laminate leading edge (10), a series of oblique shock wave strings are formd in laminate passage (13) (3)。
- 7. laminated board type scramjet engine combustion chamber according to claim 6, it is characterised in that supersonic flow enters Can form thicker boundary-layer (11) after combustion chamber import (5), on laminate, the oblique shock wave string (3) in laminate passage (13) with it is attached Surface layer (11) interferes, and forms recirculating zone.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710831675.4A CN107894010B (en) | 2017-09-15 | 2017-09-15 | Laminated super-combustion ramjet combustion chamber |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710831675.4A CN107894010B (en) | 2017-09-15 | 2017-09-15 | Laminated super-combustion ramjet combustion chamber |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107894010A true CN107894010A (en) | 2018-04-10 |
| CN107894010B CN107894010B (en) | 2020-10-16 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710831675.4A Active CN107894010B (en) | 2017-09-15 | 2017-09-15 | Laminated super-combustion ramjet combustion chamber |
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| CN (1) | CN107894010B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112668201A (en) * | 2021-01-11 | 2021-04-16 | 中国人民解放军国防科技大学 | Supersonic combustion chamber fuel injection design method based on non-uniform air flow of air inlet |
| CN113251440A (en) * | 2021-06-01 | 2021-08-13 | 成都中科翼能科技有限公司 | Multi-stage partition type combustion structure for gas turbine |
| CN115628464A (en) * | 2022-10-12 | 2023-01-20 | 哈尔滨工业大学 | Three-channel scramjet engine combustion chamber |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH05180074A (en) * | 1991-12-27 | 1993-07-20 | Nissan Motor Co Ltd | Scram jet engine |
| CN102980206A (en) * | 2012-12-18 | 2013-03-20 | 中国人民解放军国防科学技术大学 | Flame stabilizer and engine combustion chamber comprising same |
| CN106247407A (en) * | 2016-08-15 | 2016-12-21 | 西北工业大学 | A kind of fuel support plate ejector filler |
-
2017
- 2017-09-15 CN CN201710831675.4A patent/CN107894010B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH05180074A (en) * | 1991-12-27 | 1993-07-20 | Nissan Motor Co Ltd | Scram jet engine |
| CN102980206A (en) * | 2012-12-18 | 2013-03-20 | 中国人民解放军国防科学技术大学 | Flame stabilizer and engine combustion chamber comprising same |
| CN106247407A (en) * | 2016-08-15 | 2016-12-21 | 西北工业大学 | A kind of fuel support plate ejector filler |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112668201A (en) * | 2021-01-11 | 2021-04-16 | 中国人民解放军国防科技大学 | Supersonic combustion chamber fuel injection design method based on non-uniform air flow of air inlet |
| CN113251440A (en) * | 2021-06-01 | 2021-08-13 | 成都中科翼能科技有限公司 | Multi-stage partition type combustion structure for gas turbine |
| CN115628464A (en) * | 2022-10-12 | 2023-01-20 | 哈尔滨工业大学 | Three-channel scramjet engine combustion chamber |
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| Publication number | Publication date |
|---|---|
| CN107894010B (en) | 2020-10-16 |
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