CN208669461U - Combined type combustion chamber - Google Patents
Combined type combustion chamber Download PDFInfo
- Publication number
- CN208669461U CN208669461U CN201821433420.9U CN201821433420U CN208669461U CN 208669461 U CN208669461 U CN 208669461U CN 201821433420 U CN201821433420 U CN 201821433420U CN 208669461 U CN208669461 U CN 208669461U
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- Prior art keywords
- combustion chamber
- fuel
- oxidant
- cylinder
- shell
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Abstract
The utility model discloses a kind of combined type combustion chambers, shell is fixedly connected with one end of cylinder, the other end of cylinder is connect with supersonic speed spout, centrum is equipped in shell, centrum includes front and rear, the first combustion chamber is formed between front and the inner wall of shell, fuel nozzle ports are connected to the closed end of the first combustion chamber；The side of oxidant set chamber towards the first combustion chamber is uniformly provided with multiple oxidant spouts；The conical surface at rear portion enters cylinder after shell stretching, fuel supporting plate there are two vertically being set in cylinder, two fuel supporting plates are connect with barrel body rotation respectively, return passage is constituted between two fuel supporting plates and rear portion, return passage is connected to the outlet end of the first combustion chamber, the second combustion chamber is constituted between two fuel supporting plates and supersonic speed spout, annular fuel column is equipped in the second combustion chamber, and the second combustion chamber is equipped with intake valve.The utility model overall dimensions are small, and the bags is big, high combustion efficiency, and the economy of system is high.
Description
Technical field
The utility model belongs to rocket engine technical field, is related to a kind of combined type combustion chamber.
Background technique
Knocking combustion mode has many advantages, such as that energy rate of release is fast, and efficiency of thermal cycle is high, in propulsion field always
It is concerned, in aerospace field, is had using the engine of knocking combustion mode: pulse-knocking engine, oblique detonation wave hair
Motivation and rotation detonation wave engine；Currently, liquid, solid, punching engine are had in order to improve the efficiency of engine
Effect combination, plays respective maximum performance advantage, but the assembly power superior performance of solid, liquid engine, but gas generator
Liquid, solid propellant rocket performance can not be improved further, and well known turbo ramjet engine is by whirlpool spray/turbofan
Engine disposes the series arrangement before punching engine, this makes engine whole partially long；Needing one kind makes full use of combination to send out
The space of motivation improves efficiency of combustion, improves the combined type combustion chamber of the economy of system.
Summary of the invention
To solve the above-mentioned problems, the utility model provides a kind of combined type combustion chamber, and overall dimensions are small, the bags
Greatly, the economy of high combustion efficiency, system is high, solves problems of the prior art.
The utility model is the technical scheme adopted is that a kind of fixed company in one end of combined type combustion chamber, shell and cylinder
It connects, the other end of cylinder is connect with supersonic speed spout, centrum is equipped in shell, centrum includes front and rear, preceding
The first combustion chamber is formed between portion and the inner wall of shell, rotates detonation wave circumferentially rotatable propagation, center in the first combustion chamber
The front end of centrum is built-in with discoidal fuel reservoir, and the side of fuel reservoir is circumferentially uniformly provided with multiple fuel nozzle ports, combustion
Material spout is connected to the closed end of the first combustion chamber；The periphery of front is equipped with the oxidant set chamber of annular, oxidant set chamber
Multiple oxidant spouts are uniformly provided with towards the side of the first combustion chamber, oxidant set chamber passes through oxidant delivery pipe and oxidation
The connection of agent storage tank, oxidant storage tank are set in front；The end face at rear portion is the conical surface, and the conical surface at rear portion enters cylinder after shell stretching
Body is vertically set in cylinder there are two fuel supporting plate, and two fuel supporting plates are connect with barrel body rotation respectively, the free end of fuel supporting plate
For arc, return passage is constituted between two fuel supporting plates and rear portion, return passage is connected to the outlet end of the first combustion chamber, two combustions
The second combustion chamber is constituted between material supporting plate and supersonic speed spout, equipped with annular fuel column in the second combustion chamber, on the second combustion chamber
Equipped with intake valve.
The sign of the utility model also resides in, and further, the distance between described two fuel supporting plates are 1-2cm.
Further, the front and rear is integrally formed.
The beneficial effects of the utility model are: the oxidant in oxidant storage tank enters through oxidant delivery pipe when starting
Oxidant set chamber, oxidant spray into the first combustion chamber from oxidant spout, since oxidant set chamber is annular, oxidant
Axial depth of the penetrating face along the first combustion chamber is easy to adjust；The fuel in fuel reservoir burns through fuel nozzle ports from first simultaneously
The closed end of room enters the first combustion chamber, and fuel comes into full contact with oxidant, improves efficiency of combustion, in the effect of rotation detonation wave
Under, it is only necessary to once detonation, propellant can continuous detonating combustion, reduce detonation frequency；Oxidant storage tank and fuel reservoir
It is inside arranged inside centrum, under the premise of not increasing overall dimensions, increases and burn room space.
Intake valve is opened, air enters the second combustion chamber, outlet end of the high-temperature fuel gas through the first combustion chamber, into return passage
The free end of aggregation reflux, fuel supporting plate is arc, is passed through convenient for high-temperature fuel gas between two fuel supporting plates, into second
Combustion chamber, lights annular fuel column, and the air reaction of annular fuel column and inflow burns and generates high-temperature fuel gas, fuel supporting plate from
Vertical state becomes consistent with the trend of cylinder, expands the combustion zone of the second combustion chamber so that most of combustion process again this
It carries out, so that full combustion of fuel, avoids waste of fuel, improves the economy of system, high-temperature fuel gas is quick from supersonic speed spout
Discharge, to generate thrust.
Detailed description of the invention
In order to illustrate the embodiment of the utility model or the technical proposal in the existing technology more clearly, below will be to embodiment
Or attached drawing needed to be used in the description of the prior art is briefly described, it should be apparent that, the accompanying drawings in the following description is only
It is some embodiments of the utility model, for those of ordinary skill in the art, in the premise not made the creative labor
Under, it is also possible to obtain other drawings based on these drawings.
Fig. 1 is the structural schematic diagram of the utility model embodiment.
Fig. 2 is the structural schematic diagram of fuel reservoir in the utility model embodiment.
In figure, 1. centrums, 2. shells, 3. first combustion chambers, 4. second combustion chambers, 5. fuel reservoirs, the spray of 6. fuel
Mouthful, 7. oxidant storage tanks, 8. oxidant delivery pipes, 9. oxidant set chambers, 10. oxidant spouts, 11. rotation detonation waves, 12.
Outlet end, 13. rear portions, 14. fronts, 15. annular fuel columns, 16. cylinders, 17. fuel supporting plates, 18. supersonic speed spouts, 19. times
Flow chamber, 20. intake valves.
Specific embodiment
Below in conjunction with the utility model embodiment, the technical scheme in the embodiment of the utility model is carried out clear, complete
Site preparation description, it is clear that the described embodiments are only a part of the embodiments of the utility model, instead of all the embodiments.
Based on the embodiments of the present invention, obtained by those of ordinary skill in the art without making creative efforts
Every other embodiment, fall within the protection scope of the utility model.
The structure of the utility model embodiment, as shown in Figs. 1-2, shell 2 are fixedly connected with one end of cylinder 16, cylinder 16
The other end connect with supersonic speed spout 18, be equipped with centrum 1 in shell 2, centrum 1 includes front 14 and rear portion 13,
Front 14 and rear portion 13 are integrally formed, and the first combustion chamber 3 is formed between front 14 and the inner wall of shell 2, and rotation detonation wave 11 exists
Circumferentially rotatable propagation in first combustion chamber 3, the front end of centrum 1 are built-in with discoidal fuel reservoir 5, fuel reservoir 5
Side be circumferentially uniformly provided with multiple fuel nozzle ports 6, fuel nozzle ports 6 are connected to the closed end of the first combustion chamber 3；Front 14
Periphery is equipped with the oxidant set chamber 9 of annular, and the side of oxidant set chamber 9 towards the first combustion chamber 3 is uniformly provided with multiple oxygen
Agent spout 10, oxidant set chamber 9 is connect by oxidant delivery pipe 8 with oxidant storage tank 7, before oxidant storage tank 7 is set to
In portion 14；The end face at rear portion 13 is the conical surface, and the conical surface at rear portion 13 enters cylinder 16 after the stretching of shell 2, vertically sets in cylinder 16
There are two fuel supporting plate 17, two fuel supporting plates 17 are rotatablely connected with cylinder 16 respectively, two fuel supporting plates 17 and rear portion 13 it
Between constitute return passage 19, return passage 19 is connected to the outlet end 12 of the first combustion chamber 3, two fuel supporting plates 17 and supersonic speed spout
The second combustion chamber 4 is constituted between 18, annular fuel column 15 is equipped in the second combustion chamber 4, and the second combustion chamber 4 is equipped with intake valve
20。
The distance between two fuel supporting plates 17 are 1-2cm, and the free end of fuel supporting plate 17 is arc.
The working principle of the utility model embodiment: when starting, the oxidant in oxidant storage tank 7 is through oxidant delivery pipe
8 enter oxidant set chamber 9, and oxidant sprays into the first combustion chamber 3 from oxidant spout 10, since oxidant set chamber 9 is ring
Axial depth of the face along the first combustion chamber 3 that spray into of shape, oxidant is easy to adjust；The fuel in fuel reservoir 5 is through fuel simultaneously
Spout 6 enters the first combustion chamber 3 from the closed end of the first combustion chamber 3, and fuel comes into full contact with oxidant, improves efficiency of combustion,
Under the action of rotating detonation wave 11, it is only necessary to once detonation, propellant can continuous detonating combustion, reduce detonation frequency；
Fuel sufficiently reacts in the first combustion chamber 3 with oxidant, completes the starting of rocket engine；Open intake valve 20, air into
Enter the second combustion chamber 4, outlet end 12 of the high-temperature fuel gas through the first combustion chamber 3 assembles into return passage 19 and flow back, fuel supporting plate 17
Free end be arc, pass through convenient for high-temperature fuel gas between two fuel supporting plates 17, into the second combustion chamber 4, light ring
Shape fuel column 15, annular fuel column 15 and the air reaction flowed into burn and generate high-temperature fuel gas, and fuel supporting plate 17 is from vertical shape
State becomes consistent with the trend of cylinder 16, expands the combustion zone of the second combustion chamber 4 so that most of combustion process again this into
Row improves efficiency of combustion, and high-temperature fuel gas is quickly discharged from supersonic speed spout 18, to generate thrust.
It should be noted that, in this document, relational terms such as first and second and the like are used merely to a reality
Body or operation are distinguished with another entity or operation, are deposited without necessarily requiring or implying between these entities or operation
In any actual relationship or order or sequence.Moreover, the terms "include", "comprise" or its any other variant are intended to
Non-exclusive inclusion, so that the process, method, article or equipment including a series of elements is not only wanted including those
Element, but also including other elements that are not explicitly listed, or further include for this process, method, article or equipment
Intrinsic element.In the absence of more restrictions, the element limited by sentence "including a ...", it is not excluded that
There is also other identical elements in process, method, article or equipment including the element.
Each embodiment in this specification is all made of relevant mode and describes, same and similar portion between each embodiment
Dividing may refer to each other, and each embodiment focuses on the differences from other embodiments.
The above is only the preferred embodiment of the utility model only, is not intended to limit the protection model of the utility model
It encloses.Any modification, equivalent substitution, improvement and etc. made within the spirit and principle of the present invention, are all contained in this reality
With in novel protection scope.
Claims (3)
1. a kind of combined type combustion chamber, which is characterized in that shell (2) is fixedly connected with one end of cylinder (16), cylinder (16)
The other end is connect with supersonic speed spout (18), is equipped with centrum (1) in shell (2), centrum (1) include front (14) and
Rear portion (13) is formed the first combustion chamber (3) between front (14) and the inner wall of shell (2), and rotation detonation wave (11) is in the first combustion
Circumferentially rotatable propagation in room (3) is burnt, the front end of centrum (1) is built-in with discoidal fuel reservoir (5), fuel reservoir
(5) side is circumferentially uniformly provided with multiple fuel nozzle ports (6), and the closed end of fuel nozzle ports (6) and the first combustion chamber (3) connects
It is logical；The periphery of front (14) is equipped with the oxidant set chamber (9) of annular, oxidant set chamber (9) direction the first combustion chamber (3)
Side is uniformly provided with multiple oxidant spouts (10), and oxidant set chamber (9) passes through oxidant delivery pipe (8) and oxidant storage tank
(7) it connects, oxidant storage tank (7) is set in front (14)；The end face at rear portion (13) is the conical surface, and the conical surface of rear portion (13) is from shell
(2) enter cylinder (16) after stretching out, vertically set in cylinder (16) there are two fuel supporting plate (17), two fuel supporting plates (17) are distinguished
It is rotatablely connected with cylinder (16), the free end of fuel supporting plate (17) is arc, between two fuel supporting plates (17) and rear portion (13)
Constitute return passage (19), return passage (19) be connected to the outlet end (12) of the first combustion chamber (3), two fuel supporting plates (17) with surpass
It is constituted between velocity of sound spout (18) the second combustion chamber (4), is equipped with annular fuel column (15) in the second combustion chamber (4), the second burning
Room (4) is equipped with intake valve (20).
2. a kind of combined type combustion chamber according to claim 1, which is characterized in that between described two fuel supporting plates (17)
Distance be 1-2cm.
3. a kind of combined type combustion chamber according to claim 1, which is characterized in that the front (14) and rear portion (13) one
It is body formed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821433420.9U CN208669461U (en) | 2018-09-03 | 2018-09-03 | Combined type combustion chamber |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821433420.9U CN208669461U (en) | 2018-09-03 | 2018-09-03 | Combined type combustion chamber |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208669461U true CN208669461U (en) | 2019-03-29 |
Family
ID=65841464
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201821433420.9U Expired - Fee Related CN208669461U (en) | 2018-09-03 | 2018-09-03 | Combined type combustion chamber |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN208669461U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114165361A (en) * | 2021-12-10 | 2022-03-11 | 厦门大学 | Injection rocket ramjet engine combustion chamber and self-adaptive fuel injection method |
-
2018
- 2018-09-03 CN CN201821433420.9U patent/CN208669461U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114165361A (en) * | 2021-12-10 | 2022-03-11 | 厦门大学 | Injection rocket ramjet engine combustion chamber and self-adaptive fuel injection method |
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| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20190329 |