CN206352838U - A kind of annular burner - Google Patents
A kind of annular burner Download PDFInfo
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- CN206352838U CN206352838U CN201621492760.XU CN201621492760U CN206352838U CN 206352838 U CN206352838 U CN 206352838U CN 201621492760 U CN201621492760 U CN 201621492760U CN 206352838 U CN206352838 U CN 206352838U
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- air admission
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- annular
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Abstract
The utility model belongs to miniature turbine jet engines technical field, more particularly to a kind of annular burner, including outer barrel, inner cylinder, ceiling and shirt rim；Ceiling includes annular disc, is arranged on the outer connection edge of outer edge, the interior connection edge at centrally disposed bore edges, and outer cylinder front end is fixedly connected with outer connection edge, inner cylinder front end with the interior edge that connects；First annular connecting portion that shirt rim includes being fixedly connected with outer tube rear end, the second annular connecting portion and it is connected reducing transition part between the two；Enter hole provided with multiple fuel oils in annular disc, the each fuel oil of correspondence enters provided with an evaporation tube at hole in combustion chamber, and evaporation tube includes entering straight sections that hole connect with fuel oil, connected with straight sections and perpendicular bending pipe portion and connected and perpendicular extension pipe portion with bending pipe portion.Front face area can be increased, fuel atomization effect is improved, the combustion efficiency of annular burner is improved, enhance the thrust performance of miniature turbine jet engines.
Description
Technical field
The utility model belongs to miniature turbine jet engines technical field, more particularly to a kind of annular burner.
Background technology
Turbojet is a kind of turbogenerator, is characterized in that being completely dependent on combustion gas body produces thrust, generally uses
Make the power of high-speed aircraft.Turbojet is divided into centrifugal and two kinds of axial-flow type.Turbojet is according to " work
The pattern of circulation " is operated, its inspiration air from air, air is compressed and heating process after obtain energy and momentum,
The air for obtaining energy and momentum afterwards is discharged from propelling nozzle, when high-speed gas spray engine, while with action pneumatic
Machine and turbine continue to rotate, and maintain working cycles.
The later stage nineties in last century, along with reaching its maturity and consummate for large-scale turbojet technology, abroad
Occur in that dozens of thrust with the product of the miniature turbine jet engines of subordinate successively.Miniature turbine jet engines product quilt
It is widely used in military, civilian different field, is played an important role in future war, for example, applies in micro-unmanned war
In bucket machine.The subject that miniature turbine jet engines design is related to includes：Aerodynamics, Combustion, engine structure intensity
, mechanics, autonetics etc..
Burner is the important component in turbojet, and the effect of burner is：Enter from by compressor
Fuel oil mixed combustion in air-flow and burner into burner, produces high-temperature high-pressure air flow in burner, and the high temperature is high
Pressure gas stream becomes high velocity air by guider and turbine rotor, is sprayed from jet pipe.The final thrust of turbojet
Performance is largely decided by the combustion efficiency in burner.
Utility model content
The purpose of this utility model is to provide a kind of annular burner, it is possible to increase front face area, raising fuel-oil atmozation effect
Really, combustion efficiency is improved, it is possible to increase the thrust performance of miniature turbine jet engines.
The utility model is achieved in that a kind of annular burner, and the annular burner includes outer barrel and inner cylinder,
Ceiling is connected between the outer cylinder front end and the inner cylinder front end, shirt rim, the outer barrel, institute are provided with the inner cylinder rear end
State and surround combustion chamber between inner cylinder, the ceiling and the shirt rim；The ceiling includes annular disc, in the annular disc
Outer edge be provided with outer connection edge, at the central aperture edge of the annular disc be provided with interior connection edge, the outer cylinder front end with
The outer connection edge is fixedly connected, and the inner cylinder front end is fixedly connected with the interior connection edge；The shirt rim include with it is described outer
First annular connecting portion that tube rear end is fixedly connected, with the annular connecting portion of the first annular connecting portion spaced second,
And the reducing transition part of connection therebetween；Enter hole provided with multiple fuel oils in the annular disc, in the combustion chamber
The each fuel oil of interior correspondence enters Kong Chu and is respectively equipped with an evaporation tube, and the every evaporation tube includes entering with the fuel oil respectively
The straight sections of hole connection, connect with the straight sections and perpendicular bending pipe portion and with it is described bend pipe portion connect and
Perpendicular extension pipe portion.
As an improvement, multiple fuel gas being evenly distributed along same circumference are additionally provided with the annular disc and are entered
Stomata；Multiple fuel oils enter hole and are evenly distributed along same circumference, and the centre-to-centre spacing that the fuel oil enters hole is less than the fuel gas
The centre-to-centre spacing of air admission hole.
As an improvement, the aperture of the fuel gas air admission hole is 4 millimeters, the center of the fuel gas air admission hole
Away from for 85 millimeters.
As an improvement, the fuel oil enters hole provided with 10, and the corresponding evaporation tube also is provided with 10, each described
The internal diameter of evaporation tube is 10 millimeters.
As an improvement, multiple rows of outer barrel air admission hole of axially spaced setting is provided with the outer barrel, often arranges described
Outer barrel air admission hole includes multiple outer barrel air admission holes of circumferentially spaced setting；It is provided with the first annular connecting portion of the shirt rim
One row shirt rim air admission hole, the row shirt rim air admission hole includes circumferentially arranged multiple shirt rim air admission holes；By the ceiling extremely
The aperture of shirt rim air admission hole increases successively described in multiple rows of outer barrel air admission hole of the shirt rim, a row, often arranges the outer barrel air admission hole
Aperture it is identical, the aperture of shirt rim air admission hole is identical described in a row.
As an improvement, to be respectively equipped with a row circumferentially distributed for the sidepiece of outer barrel air admission hole described in some rows wherein
Auxiliary inlet port.
As an improvement, the outer barrel air admission hole is provided with four rows in the axial direction, and the from the ceiling to the shirt rim
One row, second row, the 3rd row and the 4th row, the sum of outer barrel air admission hole described in first row are 40, and aperture is 3 millimeters, the
The sum of outer barrel air admission hole described in two rows is 40, and aperture is 3.5 millimeters, and the sum of outer barrel air admission hole described in the 3rd row is 40
Individual, aperture is 4 millimeters, and the sum of outer barrel air admission hole described in the 4th row is 40, and aperture is 6 millimeters；Shirt rim described in one row
The sum of air admission hole is 40, and aperture is 7 millimeters.
As an improvement, it is respectively equipped with described in a row and aids in the sidepiece of outer barrel air admission hole described in the 3rd row, the 4th row
Air admission hole, often arranges the auxiliary inlet port provided with 48, aperture is 1.5 millimeters.
As an improvement, the external diameter of the outer barrel is 210 millimeters, and the internal diameter of the inner cylinder is 92 millimeters.
As an improvement, multiple rows of inner cylinder air admission hole of axially spaced setting is arranged at intervals with the inner cylinder,
Guide pipe is connected with the side side that multiple rows of inner cylinder air admission hole described in wherein some rows is located in combustion chamber.
As a result of said structure, the annular burner that the utility model is provided includes outer barrel and inner cylinder, before outer barrel
Ceiling is connected between end and inner cylinder front end, shirt rim is provided with interior tube rear end, is surrounded between outer barrel, inner cylinder, ceiling and shirt rim
Combustion chamber；Ceiling includes annular disc, outer connection edge is provided with the outer edge of annular disc, on the centre bore side of annular disc
Interior connection edge is provided with edge, outer cylinder front end is fixedly connected with outer connection edge, and inner cylinder front end is fixedly connected with interior connection edge；Wrap shirt rim
Include the first annular connecting portion being fixedly connected with outer tube rear end, be connected with the annular of first annular connecting portion spaced second
The reducing transition part of portion and connection therebetween；Enter hole provided with multiple fuel oils in annular disc, the correspondence in combustion chamber
Each fuel oil enters Kong Chu and is respectively equipped with an evaporation tube, every evaporation tube include respectively with fuel oil enter straight sections that hole connect and
Straight sections connect and perpendicular bending pipe portion and with bend pipe portion connect and perpendicular extension pipe portion.Using upper
The annular burner of ceiling, outer barrel, inner cylinder and the shirt rim composition stated can increase front face area, and evaporation tubular construction can improve combustion
Oil atomization effect, so as to improve the combustion efficiency of annular burner, enhances the thrust performance of miniature turbine jet engines.
Brief description of the drawings
Fig. 1 is the cross section structure diagram of annular burner of the present utility model；
Fig. 2 is the left view structural representation of annular burner of the present utility model；
Fig. 3 is the right side structural representation of annular burner of the present utility model；
Wherein, 10, outer barrel, 101, outer barrel air admission hole, 102, auxiliary inlet port, 11, shirt rim, 111, first annular connection
Portion, the 112, second annular connecting portion, 113, reducing transition part, 114, shirt rim air admission hole, 20, inner cylinder, 201, inner cylinder air admission hole,
21st, guide pipe, 30, ceiling, 31, annular disc, 311, fuel gas air admission hole, 312, fuel oil enter hole, 32, outer connection edge, 33,
Interior connection edge, 40, evaporation tube, 41, straight sections, 42, bending pipe portion, 43, extension pipe portion.
Embodiment
In order that the purpose of this utility model, technical scheme and advantage are more clearly understood, below in conjunction with accompanying drawing and implementation
Example, the utility model is further elaborated.It should be appreciated that specific embodiment described herein is only to explain
The utility model, is not used to limit the utility model.
Fig. 1 to Fig. 3 is the structural representation of annular burner of the present utility model, wherein, Fig. 1 shows the utility model
Annular burner cross section structure diagram, Fig. 2 shows the left view structural representation of annular burner of the present utility model,
Fig. 3 shows the right side structural representation of annular burner of the present utility model, for convenience of description, is only gived in figure and this
The related part of utility model.
Before the one end for defining the air inlet of miniature turbine jet engines first is, after one end of jet is, miniature turbine spray
Gas engine include shell, be arranged on the front end of shell and be fixedly connected with its end impeller cover, be arranged on after shell
The jet pipe held and be fixedly connected with its end, sets successively vertically in the cavity that impeller cover, shell and jet pipe are surrounded
There are compressor impeller, diffuser, annular burner, guider, turbine rotor and bearing block, compressor impeller is arranged on impeller
In the cavity that case is surrounded and the cavity that the leading section of shell is surrounded, bearing block is arranged in the cavity that shell is surrounded simultaneously
Axially arranged along its, diffuser, which is arranged on the front end of bearing block and is secured to connection, annular burner, is set in bearing
On seat, guider is arranged at the rearward end of bearing block, and the turbine of turbine rotor is arranged in the cavity of guider formation, is located at
In the cavity that the rearward end and jet pipe of shell are surrounded.
From Fig. 1, Fig. 2 and Fig. 3, annular burner includes outer barrel 10, is arranged on the inside of outer barrel 10 and coaxial line
Inner cylinder 20 and the ceiling 30 that is connected between the front end of outer barrel 10 and the front end of inner cylinder 20, be provided with the rear end of inner cylinder 20
Shirt rim 11, surrounds a combustion chamber between outer barrel 10, inner cylinder 20, ceiling 30 and shirt rim 11；The ceiling 30 is justified including ring-type
Disk 31, is provided with outer connection edge 32 in the outer edge of annular disc 31, interior company is provided with the central aperture edge of annular disc 31
Edge 33 is connect, the front end of outer barrel 10 is fixedly connected with outer connection edge 32, and the front end of inner cylinder 20 is fixedly connected with interior connection edge 33；Shirt rim
11 include the reducing transition part 113 of the annular connecting portion 112 of first annular connecting portion 111, second and connection therebetween, the
One annular connecting portion 111 is fixedly connected with the rear end of inner cylinder 20, is typically to use laser welding.
Multiple fuel gas air admission holes 311 are provided with annular disc 31, multiple fuel gas air admission holes 311 are along same
Circumference is evenly distributed, and fuel gas is sent in combustion chamber by fuel gas air admission hole 311, in the present embodiment, and this is flammable
Gas inlet hole 311 is preferably provided with three, and the aperture of fuel gas air admission hole 311 is 4 millimeters, fuel gas air admission hole 311 away from
Centre-to-centre spacing from the center of ceiling 30 is preferably 85 millimeters；Multiple fuel oils are additionally provided with annular disc 31 and enter hole 312, in combustion chamber
The interior each fuel oil of correspondence enters to be respectively equipped with an evaporation tube 40 at hole 312, and every evaporation tube 40 includes entering hole 312 with fuel oil respectively
The straight sections 41 of connection, connect with straight sections 41 and perpendicular bending pipe portion 42 and connected with bending pipe portion 42 and with
Its vertical extension pipe portion 43, in order to further improve combustion efficiency, multiple fuel oils enter hole 312 along same circumference average mark
Cloth, and fuel oil enters hole 312 with the centre-to-centre spacing at the center of annular disc 31 less than in fuel gas air admission hole 311 and annular disc 31
The centre-to-centre spacing of the heart, specifically, fuel oil enter hole 312 provided with 10, and corresponding evaporation tube 40 also is provided with 10, each evaporation tube 40
Internal diameter be preferably 10 millimeters, be atomized in the fuel oil evaporation tube 40 after preheat projected from spray bar, the fuel oil after atomization from
Evaporation tube 40 enters together to burn in combustion chamber with air, produces high temperature and high pressure gas.It can be increased using above-mentioned structure and met
Wind area, it is possible to increase the combustion efficiency of annular burner, so as to improve the thrust performance of miniature turbine jet engines.
In order to further improve the front face area of annular burner, axially spaced setting is provided with outer barrel 10
Multiple rows of outer barrel air admission hole 101, includes multiple outer barrel air admission holes 101 of circumferentially spaced setting per exclusive cylinder air admission hole 101；In skirt
The first annular connecting portion 111 on side 11 is provided with a row shirt rim air admission hole 114, and the row shirt rim air admission hole 114 includes circumferentially setting
The multiple shirt rim air admission holes 114 put；By multiple rows of outer barrel air admission hole 101 of ceiling 30 to shirt rim 11, a row shirt rim air admission hole 114
Aperture increases successively, and the aperture per exclusive cylinder air admission hole 101 is identical, and the aperture of a row shirt rim air admission hole 114 is identical；Because gas
During ceiling 30 flows vertically, speed, amount are gradually reduced, and the aperture of outer barrel air admission hole 101 gradually increases, and can make
Air inlet is more uniform in the axial direction of combustion chamber, can improve combustion efficiency.
In the present embodiment, in order to the side of further strengthen burning effect, wherein some exclusive cylinder air admission holes 101
Portion, which has, is respectively equipped with the circumferentially distributed auxiliary inlet port 102 of a row, can increase air inflow, strengthen burning effect.
In the present embodiment, the arrangement of the outer barrel air admission hole 101 on outer barrel 10 and size use following preferred scheme,
Outer barrel air admission hole 101 is provided with four rows in the axial direction, from ceiling 30 to the first row of shirt rim 11, second row, the 3rd row and the 4th row,
The sum of first row outer barrel air admission hole 101 is 40, and aperture is 3 millimeters, and the sum of second row outer barrel air admission hole 101 is 40
Individual, aperture is 3.5 millimeters, and the sum of the three exclusive air admission holes 101 is 40, and aperture is 4 millimeters, and the 4th exclusive cylinder enters
The sum of stomata 101 is 40, and aperture is 6 millimeters；It is arranged on the row shirt rim on the first annular connecting portion 111 of shirt rim 11
The sum of air admission hole 114 is 40, and aperture is 7 millimeters.Set respectively in the sidepiece of the 3rd row, the four exclusive air admission holes 101
There is row's auxiliary inlet port 102, often arrange auxiliary inlet port 102 and be provided with 48, the aperture of each auxiliary inlet port 102 is 1.5
Millimeter.
The overall dimension of annular burner is preferably：The external diameter of outer barrel 10 is 210 millimeters, and the internal diameter of inner cylinder 20 is 92 millis
Rice；The second the circumferentially-spaced of annular connecting portion 112 in shirt rim 11 is provided with multiple guider mounting holes, in the present embodiment, leads
Four are provided with to device mounting hole, aperture is 5.5 millimeters.
In the present embodiment, multiple rows of inner cylinder air admission hole 201 of axially spaced setting is arranged at intervals with inner cylinder 20,
Guide pipe 21 is connected with the side side that wherein some multiple rows of inner cylinder air admission holes 201 of row are located in combustion chamber, gas can be adjusted
Into the direction of combustion chamber, prevent the flow direction of gas from excessively dissipating.
The annular burner that the utility model is provided includes outer barrel and inner cylinder, is connected between outer cylinder front end and inner cylinder front end
There is ceiling, shirt rim is provided with interior tube rear end, combustion chamber is surrounded between outer barrel, inner cylinder, ceiling and shirt rim；Ceiling is justified including ring-type
Disk, is provided with outer connection edge in the outer edge of annular disc, interior connection edge, outer barrel is provided with the central aperture edge of annular disc
Front end is fixedly connected with outer connection edge, and inner cylinder front end is fixedly connected with interior connection edge；Shirt rim includes being fixedly connected with outer tube rear end
First annular connecting portion, with the annular connecting portion of first annular connecting portion spaced second and being connected therebetween
Reducing transition part；Enter hole provided with multiple fuel oils in annular disc, each fuel oil of correspondence enters at hole in combustion chamber sets respectively
There is an evaporation tube, every evaporation tube includes entering straight sections that hole connects with fuel oil respectively, connected and perpendicular with straight sections
Bending pipe portion and with bending pipe portion connect and perpendicular extension pipe portion.Using above-mentioned ceiling, outer barrel, inner cylinder and
The annular burner of shirt rim composition can increase front face area, and evaporation tubular construction can improve fuel atomization effect, so as to improve
The combustion efficiency of annular burner, enhances the thrust performance of miniature turbine jet engines.
Preferred embodiment of the present utility model is the foregoing is only, it is all at this not to limit the utility model
Any modifications, equivalent substitutions and improvements made within the spirit and principle of utility model etc., should be included in the utility model
Protection domain within.
Claims (10)
1. a kind of annular burner, including outer barrel and inner cylinder, it is characterised in that the outer cylinder front end and the inner cylinder front end it
Between be connected with ceiling, the inner cylinder rear end be provided with shirt rim, the outer barrel, the inner cylinder, the ceiling and the shirt rim it
Between surround combustion chamber；The ceiling includes annular disc, outer connection edge is provided with the outer edge of the annular disc, described
Interior connection edge is provided with the central aperture edge of annular disc, the outer cylinder front end is fixedly connected with the outer connection edge, described interior
Cylinder front end is fixedly connected with the interior connection edge；The shirt rim includes the first annular connection being fixedly connected with the outer tube rear end
Portion, with the annular connecting portion of the first annular connecting portion spaced second and being connected reducing transition therebetween
Portion；Enter hole provided with multiple fuel oils in the annular disc, each fuel oil of correspondence, which enters at hole, in the combustion chamber distinguishes
Provided with an evaporation tube, the every evaporation tube includes entering straight sections and the straight sections that hole is connected with the fuel oil respectively
Connection and perpendicular bending pipe portion and with it is described bend pipe portion connect and perpendicular extension pipe portion.
2. annular burner according to claim 1, it is characterised in that be additionally provided with the annular disc multiple along same
The fuel gas air admission hole that one circumference is evenly distributed；Multiple fuel oils enter hole and are evenly distributed along same circumference, and the fuel oil enters
The centre-to-centre spacing in hole is less than the centre-to-centre spacing of the fuel gas air admission hole.
3. annular burner according to claim 2, it is characterised in that the aperture of the fuel gas air admission hole is 4 millis
Rice, the centre-to-centre spacing of the fuel gas air admission hole is 85 millimeters.
4. annular burner according to claim 1, it is characterised in that the fuel oil enters hole provided with 10, corresponding institute
State evaporation tube and also be provided with 10, the internal diameter of each evaporation tube is 10 millimeters.
5. the annular burner according to any one of Claims 1-4, it is characterised in that be provided with the outer barrel along axle
To spaced multiple rows of outer barrel air admission hole, often arranging the outer barrel air admission hole includes multiple outer barrel air inlets of circumferentially spaced setting
Hole；A row shirt rim air admission hole is provided with the first annular connecting portion of the shirt rim, the row shirt rim air admission hole was included along week
To multiple shirt rim air admission holes of setting；Shirt rim air inlet described in multiple rows of outer barrel air admission hole, a row as the ceiling to the shirt rim
The aperture in hole increases successively, and the aperture for often arranging the outer barrel air admission hole is identical, and the aperture of shirt rim air admission hole is identical described in a row.
6. annular burner according to claim 5, it is characterised in that the side of outer barrel air admission hole described in some rows wherein
Portion, which has, is respectively equipped with the circumferentially distributed auxiliary inlet port of a row.
7. annular burner according to claim 6, it is characterised in that the outer barrel air admission hole is provided with four in the axial direction
Row, from the ceiling to the first row of the shirt rim, second row, the 3rd row and the 4th row, outer barrel air admission hole described in first row
Sum is 40, and aperture is 3 millimeters, and the sum of outer barrel air admission hole described in second row is 40, and aperture is 3.5 millimeters, the
The sum of outer barrel air admission hole described in three rows is 40, and aperture is 4 millimeters, and the sum of outer barrel air admission hole described in the 4th row is 40
Individual, aperture is 6 millimeters；The sum of shirt rim air admission hole described in one row is 40, and aperture is 7 millimeters.
8. annular burner according to claim 7, it is characterised in that in outer barrel air admission hole described in the 3rd row, the 4th row
Sidepiece be respectively equipped with auxiliary inlet port described in a row, often arrange the auxiliary inlet port provided with 48, aperture is 1.5 millimeters.
9. annular burner according to claim 8, it is characterised in that the external diameter of the outer barrel is 210 millimeters, described interior
The internal diameter of cylinder is 92 millimeters.
10. annular burner according to claim 1, it is characterised in that be arranged at intervals with vertically on the inner cylinder
Spaced multiple rows of inner cylinder air admission hole, is located on the side side in combustion chamber in multiple rows of inner cylinder air admission hole described in wherein some rows
It is connected with guide pipe.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621492760.XU CN206352838U (en) | 2016-12-30 | 2016-12-30 | A kind of annular burner |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621492760.XU CN206352838U (en) | 2016-12-30 | 2016-12-30 | A kind of annular burner |
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| Publication Number | Publication Date |
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| CN206352838U true CN206352838U (en) | 2017-07-25 |
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ID=59349267
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621492760.XU Active CN206352838U (en) | 2016-12-30 | 2016-12-30 | A kind of annular burner |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107763668A (en) * | 2017-11-01 | 2018-03-06 | 中国科学院工程热物理研究所 | A kind of subregion burning high stability vaporizer tube combustor |
| CN108534180A (en) * | 2018-05-02 | 2018-09-14 | 中国科学院工程热物理研究所 | Engine combustion chamber |
| CN108758689A (en) * | 2018-07-09 | 2018-11-06 | 西安空天能源动力智能制造研究院有限公司 | A kind of micro turbine engine combustion chamber |
| CN108954387A (en) * | 2018-08-08 | 2018-12-07 | 北京航空航天大学 | A kind of micro gas turbine engine and its chamber assembly that burns |
| CN110043922A (en) * | 2019-04-24 | 2019-07-23 | 北京航空航天大学 | A kind of micro gas turbine engine and its reverse-flow can type combustor assembly |
| CN114234237A (en) * | 2021-12-20 | 2022-03-25 | 中国人民解放军总参谋部第六十研究所 | Head preparation method for wide-envelope starting of evaporating tube combustion chamber |
-
2016
- 2016-12-30 CN CN201621492760.XU patent/CN206352838U/en active Active
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107763668A (en) * | 2017-11-01 | 2018-03-06 | 中国科学院工程热物理研究所 | A kind of subregion burning high stability vaporizer tube combustor |
| CN108534180A (en) * | 2018-05-02 | 2018-09-14 | 中国科学院工程热物理研究所 | Engine combustion chamber |
| CN108534180B (en) * | 2018-05-02 | 2023-08-15 | 中国科学院工程热物理研究所 | Combustion chamber for engine |
| CN108758689A (en) * | 2018-07-09 | 2018-11-06 | 西安空天能源动力智能制造研究院有限公司 | A kind of micro turbine engine combustion chamber |
| CN108758689B (en) * | 2018-07-09 | 2024-04-09 | 西安空天能源动力智能制造研究院有限公司 | Combustion chamber of miniature turbine engine |
| CN108954387A (en) * | 2018-08-08 | 2018-12-07 | 北京航空航天大学 | A kind of micro gas turbine engine and its chamber assembly that burns |
| CN110043922A (en) * | 2019-04-24 | 2019-07-23 | 北京航空航天大学 | A kind of micro gas turbine engine and its reverse-flow can type combustor assembly |
| CN114234237A (en) * | 2021-12-20 | 2022-03-25 | 中国人民解放军总参谋部第六十研究所 | Head preparation method for wide-envelope starting of evaporating tube combustion chamber |
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