CN205505079U - Supersonic combustion chamber of accurate isothermal - Google Patents
Supersonic combustion chamber of accurate isothermal Download PDFInfo
- Publication number
- CN205505079U CN205505079U CN201620290601.5U CN201620290601U CN205505079U CN 205505079 U CN205505079 U CN 205505079U CN 201620290601 U CN201620290601 U CN 201620290601U CN 205505079 U CN205505079 U CN 205505079U
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- wall surface
- combustion chamber
- combustion
- combustion zone
- upper wall
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Abstract
The utility model provides a supersonic combustion chamber of accurate isothermal for solve the hot protection problem that present supersonic combustion chamber faces, include: keep apart section, fuel injector and a plurality of continuous echelonment combustion area, to stair structure after the combustion area is, the upper reaches bottom surface of combustion area and low reaches bottom surface are parallel, connect perpendicularly through the step basal portion of combustion area between upper reaches bottom surface and the low reaches bottom surface, fuel injector installs at the step basal portion, and fuel injector's central line is on a parallel with the low reaches bottom surface of combustion area, 10 are no less than to the quantity of combustion area. The burning of accurate isothermal can be realized in this combustion chamber, and the temperature of air current remains unchanged in combustion processes basically, and the chemical energy of fuel all changes the kinetic energy of air current into to reduce the heat protection pressure that supersonic combustion chamber faces, be favorable to surpassing the long -time and high mach number flight of firing the punching press engine.
Description
Technical field
This utility model relates to scramjet engine technical field, particularly relates to a kind of quasi-isothermal supersonic speed
Combustor.
Background technology
The design of supersonic speed combustion chamber geometric configuration needs to meet both sides requirement, and the first can accommodate
Abundant heat, determines electromotor and can be generated by the size of thrust, for SP,
Seek to meet chemistry of fuel appropriately than time release thermal requirement；It two is alap pitot loss,
It directly affects engine/motor specific impulse, determines the flying distance of electromotor.The heat release amount that combustor is accommodated
Restricted by electromotor work border, the air intake duct unstart boundary that mainly burning induction back pressure causes
With combustion chamber wall surface material overtemperature border, can they be related to electromotor and normally work.High flight horse
Conspicuous several under, the burning inoperative constraint that causes of back pressure has disappeared.But, thermal protection difficulty significantly increases
Add so that in air-flow, add heat face the biggest difficulty.Additionally, along with the increase of flight Mach number,
The Rayleigh heat loss that combustion process causes starts to occupy leading position.Freely flow stagnation temperature along with flight Mach number
Raising and increase sharply, active thermal guard technology has been difficult to solve the wall surface material overtemperature that faces of combustor
Problem.It is then desired to consider thermal protection pressure when combustor configuration designs, to reduce the gas of combustion field
Stream temperature.
From the perspective of thermodynamic cycle, current supersonic speed combustion chamber typically uses accurate isobaric Working mould
Formula, in combustion, the pressure approximation of air-flow is constant, but temperature can rise rapidly, even more than combustion
Burn the license operating temperature of room wall surface material, destroy chamber structure.Additionally, due to the limit on overtemperature border
System, it has been disclosed that the supersonic speed combustion chamber thermal efficiency the most relatively low, chamber performance is the highest, it is difficult to meet super
The requirement of burning ramjet width range of Mach numbers work.
Utility model content
This utility model provides a kind of quasi-isothermal supersonic speed combustion chamber, is used for solving supersonic speed in prior art
The thermal protection problem that combustor faces.
This utility model provides a kind of quasi-isothermal supersonic speed combustion chamber, including: distance piece, fuel nozzle
Combustion zone stepped with multiple continuous print；Combustion zone is backward facing step structure, the bottom surface, upstream of combustion zone and
Downstream bottom is parallel, is vertically connected by the step base portion of combustion zone between bottom surface, upstream and downstream bottom；
Fuel nozzle is arranged on step base portion, and the centerline parallel of fuel nozzle is in the downstream bottom of combustion zone；Combustion
Burn the quantity in district no less than 10.
Wherein, the upper wall surface of distance piece is parallel with lower wall surface；Combustion zone is arranged on the lower wall surface of combustor；
The upper wall surface of combustor is integrated, including upper wall surface and the upper wall surface of combustion zone of distance piece, every
It it is 180 degree from the angle between section upper wall surface and the upper wall surface of combustion zone.
Further, the internal face molded line of fuel nozzle is gradually-reducing shape；The upper wall surface of fuel nozzle and lower wall
Face is curved surface, and two side wall surfaces are plane.
It addition, the material of the housing of combustor and fuel nozzle is 0Cr18Ni9.
This utility model has the beneficial effect that:
The quasi-isothermal supersonic speed combustion chamber that this utility model provides has the stepped combustion zone of multiple continuous print,
Air-flow is behind each stepped combustion zone, and temperature is held essentially constant, and the heat of burning release all turns
Turn to the kinetic energy of air-flow, thus substantially reduce the thermal protection pressure of supersonic speed combustion chamber.Its thermal efficiency is higher,
The irreversible entropy loss that heating process is caused is less, thus effectively promotes the specific impulse of supersonic speed combustion chamber.
The design of its configuration is simple, it is easy to Project Realization.
Accompanying drawing explanation
Accompanying drawing described herein is used for providing being further appreciated by of the present utility model, constitutes the application's
A part, schematic description and description of the present utility model is used for explaining this utility model, not structure
Paired improper restriction of the present utility model.In the accompanying drawings:
Fig. 1 be this utility model provide quasi-isothermal supersonic speed combustion chamber upper wall surface and lower wall surface structure show
It is intended to；
Fig. 2 is the upward view of the quasi-isothermal supersonic speed combustion chamber that this utility model provides；
Fig. 3 is configuration and the flow field schematic diagram of first stepped combustion zone that this utility model provides；
Fig. 4 is that the gas flow temperature Axial changes of the quasi-isothermal supersonic speed combustion chamber that this utility model provides shows
It is intended to.
Detailed description of the invention
In order to solve the thermal protection problem that supersonic speed combustion chamber in prior art faces, this utility model provides
A kind of quasi-isothermal supersonic speed combustion chamber, below in conjunction with accompanying drawing and embodiment, is carried out this utility model
Further describe.Should be appreciated that specific embodiment described herein is only in order to explain this practicality
Novel, do not limit this utility model.
In order to realize the fuel quasi-constant-temperature combustion under stoichiometric ratio, the quantity of stepped combustion zone is many
In 10.Fig. 1 be the quasi-isothermal supersonic speed combustion chamber with 10 stepped combustion zones upper wall surface and
Lower wall surface structural representation, including: distance piece upper wall surface 1, combustion zone upper wall surface 2, distance piece lower wall
Face 3 and the stepped combustion zone of multiple continuous print 4～13.Wherein, the upper wall surface 1 of distance piece and lower wall surface 2
Parallel so that distance piece cross-sectional area keeps constant；Combustor upper wall surface uses integrated structure design,
Including distance piece upper wall surface 1 and combustion zone upper wall surface 3, angle is 180 degree therebetween.Multiple ladders
Shape combustion zone is linked in sequence and forms the lower wall surface of combustor.Fig. 2 is the upward view of supersonic speed combustion chamber, figure
Shown in 21 and 22 be respectively combustor forward and backward side wall surface, as in figure 2 it is shown, combustor is overall
Use symmetrical rectangular structure.
The operation principle of quasi-isothermal supersonic speed combustion chamber is described below in conjunction with Fig. 3 and Fig. 4.Fig. 3 is
The configuration of one stepped combustion zone and flow field schematic diagram.The structure of combustion zone includes: at the bottom of upstream, combustion zone
Face 17, fuel nozzle 18 and combustion zone downstream bottom surface 20.Combustor uses hydrogen as fuel, fuel
The internal face molded line of nozzle 18 is gradually-reducing shape, the hydrogen Mach 2 ship 1 of nozzle exit, thus improves
By the hydrogen quality flow of nozzle.
The main Field Characteristics of combustion zone includes: from origin stream 14, dilatational wave 15, shear layer 16, return
Stream district 19.At the trailing edge of bottom surface, upstream, combustion zone 17, owing to flow area is expanded suddenly, flow field goes out
Existing dilatational wave 15, from origin stream 14 after overexpansion shock 15, air velocity rises and kinetic energy increases,
But temperature declines, and defines recirculating zone in backward facing step.Shape between recirculating zone 19 and main flow
Becoming shear layer 16, fuel injects in recirculating zone 19 by nozzle 18, injects and is caused reducing fuel
Pitot loss, and fully burn in recirculating zone 19.In view of combustion zone downstream bottom surface 20 and burning
Chamber upper wall face 2 keeping parallelism so that cross-sectional area during combustion of hydrogen immobilizes, burning release
Heat gas flow temperature will be made to be compensated.It is found that the heat of combustion process release is wholly converted into
The kinetic energy of air-flow in expansion process, the temperature of air-flow then keeps constant.It addition, each stepped
In combustion zone, fuel equivalence ratio is all less than 0.1 so that fuel can be sufficiently mixed also in recirculating zone
Complete combustion process.Fig. 4 gives the gas flow temperature change schematic diagram that supersonic speed combustion chamber is axial, air-flow
Temperature is overall to be distributed in " zigzag ".Along with flow expansion is accelerated, declining occurs in temperature；In combustion zone
Downstream, fuel can fully burn, and gas flow temperature rises, and compensate for the temperature that expansion process declines, thus
At air-flow behind each stepped combustion zone, temperature keeps constant, is that a kind of " quasi-isothermal " is burned
Journey, thus effectively solve the thermal protection problem that supersonic speed combustion chamber faces.And chamber structure is simple,
It is prone to Project Realization.
The operating temperature of successive steps shape combustion zone can be set near material permissive temperature, supersonic speed
The working range of combustor will not restricted by material temperature border, can be in flight Mach number 5～10
Effectively work in the range of width.It addition, under high flight Mach number, it is possible to add more in combustor
Heat, thus improve the flight speed of scramjet engine further, widen the working range of electromotor.
According to Carnot's theorem, " quasi-isothermal " combustion process is maximally effective mode of heating, and its thermal efficiency is more
Height, the irreversible entropy loss that heating process is caused is less, thus effectively promotes the ratio of supersonic speed combustion chamber
Punching, makes scramjet engine produce bigger thrust.
The foregoing is only embodiment of the present utility model, be not limited to this utility model, right
For those skilled in the art, this utility model can have various modifications and variations.All in this practicality
Within novel spirit and principle, any modification, equivalent substitution and improvement etc. made, should be included in
Within right of the present utility model.
Claims (4)
1. a quasi-isothermal supersonic speed combustion chamber, it is characterised in that including:
Distance piece, fuel nozzle and the stepped combustion zone of multiple continuous print；
Described stepped combustion zone is backward facing step structure, the bottom surface, upstream of described combustion zone and downstream bottom
Parallel, vertically connected by the step base portion of described combustion zone between bottom surface, described upstream and described downstream bottom
Connect；Described fuel nozzle is arranged on described step base portion, and the centerline parallel of described fuel nozzle is in described
The downstream bottom of combustion zone；The quantity of described combustion zone is no less than 10.
Quasi-isothermal supersonic speed combustion chamber the most according to claim 1, it is characterised in that also include:
The upper wall surface of described distance piece is parallel with lower wall surface；Described combustion zone is arranged under described combustor
Wall；The upper wall surface of described combustor is integrated, including upper wall surface and the burning of described distance piece
The upper wall surface in district, the angle between described distance piece upper wall surface and the upper wall surface of described combustion zone is 180
Degree.
Quasi-isothermal supersonic speed combustion chamber the most according to claim 1, it is characterised in that described combustion
The internal face molded line of material nozzle is gradually-reducing shape；The upper wall surface of described fuel nozzle and lower wall surface are curved surface, two
Individual side wall surface is plane.
4. according to the quasi-isothermal supersonic speed combustion chamber described in claims 1 to 3 any one, its feature
Being, the housing of described combustor and the material of described fuel nozzle are 0Cr18Ni9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620290601.5U CN205505079U (en) | 2016-04-11 | 2016-04-11 | Supersonic combustion chamber of accurate isothermal |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620290601.5U CN205505079U (en) | 2016-04-11 | 2016-04-11 | Supersonic combustion chamber of accurate isothermal |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205505079U true CN205505079U (en) | 2016-08-24 |
Family
ID=56737279
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620290601.5U Expired - Fee Related CN205505079U (en) | 2016-04-11 | 2016-04-11 | Supersonic combustion chamber of accurate isothermal |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205505079U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110779042A (en) * | 2018-07-31 | 2020-02-11 | 中国人民解放军国防科技大学 | Rotary detonation combustion chamber and engine with same |
| CN111207415A (en) * | 2020-01-17 | 2020-05-29 | 西北工业大学 | Flame tube of combustion chamber of aircraft engine |
-
2016
- 2016-04-11 CN CN201620290601.5U patent/CN205505079U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110779042A (en) * | 2018-07-31 | 2020-02-11 | 中国人民解放军国防科技大学 | Rotary detonation combustion chamber and engine with same |
| CN110779042B (en) * | 2018-07-31 | 2021-02-26 | 中国人民解放军国防科技大学 | Rotary detonation combustion chamber and engine with same |
| CN111207415A (en) * | 2020-01-17 | 2020-05-29 | 西北工业大学 | Flame tube of combustion chamber of aircraft engine |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160824 Termination date: 20170411 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |