CN203892065U - Cooling structure of lining of combustion chamber - Google Patents
Cooling structure of lining of combustion chamber Download PDFInfo
- Publication number
- CN203892065U CN203892065U CN201420229822.2U CN201420229822U CN203892065U CN 203892065 U CN203892065 U CN 203892065U CN 201420229822 U CN201420229822 U CN 201420229822U CN 203892065 U CN203892065 U CN 203892065U
- Authority
- CN
- China
- Prior art keywords
- liner
- liquid collecting
- collecting cavity
- cooling
- firing chamber
- 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.)
- Expired - Lifetime
Links
- 238000001816 cooling Methods 0.000 title claims abstract description 96
- 238000002485 combustion reaction Methods 0.000 title abstract description 12
- 239000002826 coolant Substances 0.000 claims abstract description 41
- 239000007788 liquid Substances 0.000 claims description 44
- 238000010304 firing Methods 0.000 claims description 27
- 239000000659 freezing mixture Substances 0.000 claims description 20
- 238000000034 method Methods 0.000 description 5
- 238000010586 diagram Methods 0.000 description 3
- 239000003380 propellant Substances 0.000 description 3
- 239000007921 spray Substances 0.000 description 2
- 238000005728 strengthening Methods 0.000 description 2
- 238000002679 ablation Methods 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000002955 isolation Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 239000013589 supplement Substances 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
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- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The utility model provides a cooling structure of a lining of a combustion chamber. The cooling structure comprises a body part; the body part comprises a column section, a constriction section, a throat section and an expanding section which are connected in sequence; a cooling agent inlet is formed in the front end of the column section. The cooling structure further comprises the lining that sleeves the inner surface of the body part; a cooling channel is arranged between the lining and the inner surface of the body part; the upper end of the cooling channel is communicated with the cooling agent inlet, and while the lower end of the cooling channel is positioned at the column section or the constriction section and used for enabling a cooling agent to flow out from the cooling channel. With the adoption of the cooling structure of the lining of the combustion chamber, the body part of the combustion chamber and the throat part of the body part can be cooled; high utilization rate of the cooling agent is realized.
Description
Technical field
The utility model relates to liquid propellant rocket engine field, is specifically related to a kind of firing chamber liner cooling structure.
Background technique
Firing chamber is as one of liquid engine significant components, bearing and organizing propellant combustion, producing the Main Functions such as thrust, in working procedure, propellant combustion high temperature bears in body portion in firing chamber, concerning Combustion chamber design, how to realize body portion reliable cooling be one of important prerequisite of ensureing engine reliable work.
At present the conventional firing chamber body portion type of cooling has that liquid film is cooling, radiation is cooling, it is cooling to regenerate, ablation is cooling etc., and wherein the liquid film type of cooling realizes owing to being simple and easy to, and is widely used in firing chamber body portion cooling.
The conventional liquid film type of cooling is mainly at head of combustion chamber spray location arrangements Cooling Holes, gives certain coolant flow and spray speed to realize reliably cooling to firing chamber body portion.Under this type of cooling, body portion border area freezing mixture can be entrainmented, consume by central combustion zone gradually, in special construction firing chamber, when as higher in constant pressure, firing chamber is longer, there is high temperature risk in body portion, very difficult realization is reliably cooling to throat, and Cooling Design difficulty is larger.
Model utility content
The utility model proposes and a kind ofly can carry out cooling a kind of firing chamber liner cooling structure to the throat of firing chamber body portion and body portion, this firing chamber liner cooling structure is high to freezing mixture utilization ratio.
Technical solution of the present utility model is:
A kind of firing chamber liner cooling structure, comprises body portion, and body portion comprises connected successively cylindrical section, converging portion, throat and extending section, and cylindrical section front end arranges coolant entrance, and its special way is:
Also comprise liner, neck bush, at body portion internal surface, is provided with cooling channel between liner and body portion internal surface;
Described coolant entrance is connected with the upper end of cooling channel; The lower end of cooling channel is positioned at cylindrical section or converging portion place, and the lower end of cooling channel is for flowing out the freezing mixture that enters into cooling channel.
Based on technique scheme, the utility model is also made following optimization and restriction
Above-mentioned liner is cylindric;
Described coolant entrance has one or more; If multiple, coolant entrance is distributed on cylindrical section front end;
Also comprise the ring-type liquid collecting cavity that is arranged on cylindrical section front end, described coolant entrance is connected with cooling channel by ring-type liquid collecting cavity;
Inner lining surface between liner and body portion is liner outer surface, and liner outer surface is provided with straight trough and/or circular groove.
Above-mentioned liner is round table-like, comprises small end head and large termination, and small end head is arranged on cylindrical section front end.
The periphery cover of above-mentioned small end head has air ring, and the periphery cover of air ring has side plate, and coolant entrance is arranged on side plate;
Air ring is provided with outer liquid collecting cavity, radial passage, interior liquid collecting cavity and aperture; Outer liquid collecting cavity is arranged between side plate and air ring, and interior liquid collecting cavity is arranged on the top of cooling channel, and interior liquid collecting cavity is provided with cover plate;
Described coolant entrance, outer liquid collecting cavity, radial passage, interior liquid collecting cavity, aperture and cooling channel are communicated with successively.
Inner lining surface between liner and body portion is liner outer surface, and liner outer surface is provided with straight trough and/or circular groove.
Above-mentioned outer liquid collecting cavity and/or interior liquid collecting cavity are ring-type.
Above-mentioned coolant entrance has one or more, if multiple, coolant entrance is distributed on side plate.
Above-mentioned radial passage has one or more, if multiple, radial passage is distributed on air ring.
If foraminate air ring part is bumped in cooling channel.
Above-mentioned side plate is bumped in air ring.
The utlity model has following technique effect:
1, neck bush of the present utility model, at body portion internal surface, is provided with cooling channel between liner and body portion internal surface; Can at utmost avoid loss of coolant, strengthen cooling effect;
2, the lower end of the utility model cooling channel is positioned at cylindrical section or converging portion place, can effectively protect converging portion and throat's high heat load region.
3, coolant entrance is connected with the upper end of cooling channel; The lower end of cooling channel is positioned at cylindrical section or converging portion place, and the lower end of cooling channel is for flowing out the freezing mixture that enters into cooling channel, has realized reliably cooling, simple in structure to downstream throat, easily realizes.
Brief description of the drawings
Fig. 1 is the first example structure schematic diagram of the present utility model;
Fig. 2 is the second example structure schematic diagram of the present utility model;
Reference character:
1-side plate, 2-air ring, 3-cover plate, liquid collecting cavity in 4-, the outer liquid collecting cavity of 5-, 6-aperture, 7-liner, 8-body portion, 9-cooling channel, 10-coolant entrance, 11-coolant outlet, 12-cylindrical section, 13-converging portion, 14-throat, 15-extending section, 16-ring-type liquid collecting cavity, 17-radial passage.
Embodiment
The utility model provides a kind of firing chamber liner cooling structure, comprise body portion 8, as Fig. 1, body portion comprises connected successively cylindrical section 12, converging portion 13, throat 14 and extending section 15, cylindrical section 12, converging portion 13, throat 14 and the extending section 15 of body portion are integrated, cylindrical section has two ends, one end is connected with converging portion, the other end is cylindrical section front end, cylindrical section front end arranges coolant entrance, also comprise liner 7, liner 7 is enclosed within body portion 8 internal surfaces, between liner and body portion internal surface, is provided with cooling channel 9; Coolant entrance 10 is connected with the upper end of cooling channel 9; The lower end of cooling channel is positioned at cylindrical section or converging portion place, and the lower end of cooling channel is coolant outlet 11, for flowing out the freezing mixture that enters into cooling channel.
As Fig. 1, liner can adopt and be cylindric liner, and coolant entrance has one or more, if multiple, coolant entrance is distributed on cylindrical section front end; The utility model also comprises the ring-type liquid collecting cavity 16 that is arranged on cylindrical section front end, and coolant entrance is connected with cooling channel by ring-type liquid collecting cavity; Inner lining surface between liner and body portion is liner outer surface, and liner outer surface is provided with straight trough and/or circular groove.Thereby further ensure cooling effect of the present utility model.
In addition, liner can adopt extended pattern, and its upper end is less, specifically can adopt the liner that is round table-like, and as Fig. 2, in the time that liner is round table-like, liner comprises small end head and large termination, and small end head is arranged on cylindrical section front end.The periphery cover of small end head has air ring 2, and the periphery cover of air ring has side plate 1, and now, coolant entrance 10 is arranged on side plate 1, and coolant entrance also can arrange one or more, if multiple, coolant entrance is distributed on side plate.
Air ring is provided with outer liquid collecting cavity 5, radial passage 17, interior liquid collecting cavity 4 and aperture 6; Outer liquid collecting cavity is arranged between side plate and air ring, and interior liquid collecting cavity is arranged on the top of cooling channel, and interior liquid collecting cavity is provided with cover plate; Coolant entrance, outer liquid collecting cavity, radial passage, interior liquid collecting cavity, aperture and cooling channel are communicated with successively.Because small aperture is less, in the time that entrainment central combustion zone of the present utility model, make freezing mixture enter cooling channel with very high speed, thereby cylindrical section, converging portion and the throat of can be fast cooling the utility model body portion.
Inner lining surface between liner and body portion is liner outer surface, and liner outer surface is provided with straight trough and/or circular groove, thereby has also further ensured cooling effect of the present utility model.
Side plate can be bumped in air ring, outer liquid collecting cavity and/or interior liquid collecting cavity are set to ring-type, and radial passage has one or more, if multiple, radial passage is distributed on air ring.The air ring part of aperture is bumped in cooling channel, can make to position in when assembling and body portion internal surface, convenient for assembly, if it is darker to be bumped into part in cooling channel, cooling effect is better.
Fig. 1, Fig. 2 are firing chamber of the present utility model liner cooling structure schematic diagram, below in conjunction with accompanying drawing, the technical solution of the utility model are described further.
Embodiment one
As shown in Figure 1, liner 7 can be by the mode such as welding with together with body portion assembly connection.On liner 7, process coolant entrance 10, freezing mixture enters liquid collecting cavity by coolant entrance 10, flow into again the cooling channel 9 forming between liner 7 and body portion internal surface, freezing mixture in cooling channel can ensure the cooling reliability of liner 2, meanwhile, the freezing mixture that liner 7 exports can ensure the cooling reliability of body portion back segment high-temperature zone.For strengthening cooling effect, can be in structures such as liner outer surface processing straight trough, circular grooves.In Fig. 2 the direction indication of arrow the flow direction of freezing mixture.
Embodiment two
As shown in Figure 2, firing chamber liner cooling structure is mainly by air ring 2, side plate 1, cover plate 3 and liner composition, freezing mixture from coolant entrance enter formed by side plate and air ring liquid collecting cavity 5, enter by multiple circumferentially uniform radial flow path the interior liquid collecting cavity being formed by cover plate and air ring again, then enter cooling channel via multiple circumferentially uniform apertures, and flow downward vertically along cooling channel, finally enter firing chamber by coolant outlet, form cooling film protection body subordinate at converging portion and throat's wall and swim high load region wall, at body portion leading portion with discharge cooling protection liner and combustion chamber wall surface, protect inwall in high-temperature zone with the cooling form of film, can reach and make the circumferential equally distributed effect of freezing mixture.For strengthening cooling effect, can be in structures such as liner outer surface processing straight trough, circular grooves, it is more even that this structure circumferentially distributes freezing mixture.In Fig. 2 the direction indication of arrow the flow direction of freezing mixture.
Main purpose of the present utility model is by freezing mixture and center main zone of combustion physical isolation, avoids combustion gas that entrainmenting of freezing mixture caused and consumed excessively, thereby reaches reliably cooling to throat and high heat load area of freezing mixture.
The utility model can be avoided the loss of freezing mixture in body portion leading portion low temperature area, effectively freezing mixture is used for to high-temperature zone thermal protection, improves high-temperature zone thermal protection level.
Foregoing description of the present utility model and accompanying drawing have represented preferred version of the present utility model, those skilled in the art can carry out various supplements, improvement and replacing not departing from the scope that the utility model claim defines according to different designing requirements and design parameter, therefore, the utility model is widely.
Claims (10)
1. a firing chamber liner cooling structure, comprises body portion, and body portion comprises connected successively cylindrical section, converging portion, throat and extending section, and cylindrical section front end arranges coolant entrance, it is characterized in that:
Also comprise liner, neck bush, at body portion internal surface, is provided with cooling channel between liner and body portion internal surface;
Described coolant entrance is connected with the upper end of cooling channel; The lower end of cooling channel is positioned at cylindrical section or converging portion place, and the lower end of cooling channel is for flowing out the freezing mixture that enters into cooling channel.
2. firing chamber according to claim 1 liner cooling structure, is characterized in that:
Described liner is cylindric;
Described coolant entrance has one or more; If multiple, coolant entrance is distributed on cylindrical section front end;
Also comprise the ring-type liquid collecting cavity that is arranged on cylindrical section front end, described coolant entrance is connected with cooling channel by ring-type liquid collecting cavity;
Inner lining surface between liner and body portion is liner outer surface, and liner outer surface is provided with straight trough and/or circular groove.
3. firing chamber according to claim 1 liner cooling structure, is characterized in that: described liner is round table-like, comprises small end head and large termination, and small end head is arranged on cylindrical section front end.
4. firing chamber according to claim 3 liner cooling structure, is characterized in that:
The periphery cover of described small end head has air ring, and the periphery cover of air ring has side plate, and coolant entrance is arranged on side plate;
Air ring is provided with outer liquid collecting cavity, radial passage, interior liquid collecting cavity and aperture; Outer liquid collecting cavity is arranged between side plate and air ring, and interior liquid collecting cavity is arranged on the top of cooling channel, and interior liquid collecting cavity is provided with cover plate;
Described coolant entrance, outer liquid collecting cavity, radial passage, interior liquid collecting cavity, aperture and cooling channel are communicated with successively.
5. firing chamber according to claim 4 liner cooling structure, is characterized in that: the inner lining surface between liner and body portion is liner outer surface, and liner outer surface is provided with straight trough and/or circular groove.
6. firing chamber according to claim 5 liner cooling structure, is characterized in that: described outer liquid collecting cavity and/or interior liquid collecting cavity are ring-type.
7. firing chamber according to claim 6 liner cooling structure, is characterized in that: described coolant entrance has one or more, if multiple, coolant entrance is distributed on side plate.
8. firing chamber according to claim 7 liner cooling structure, is characterized in that: described radial passage has one or more, if multiple, radial passage is distributed on air ring.
9. firing chamber according to claim 8 liner cooling structure, is characterized in that: establish foraminate air ring part and be bumped in cooling channel.
10. firing chamber according to claim 9 liner cooling structure, is characterized in that: described side plate is bumped in air ring.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420229822.2U CN203892065U (en) | 2014-05-06 | 2014-05-06 | Cooling structure of lining of combustion chamber |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420229822.2U CN203892065U (en) | 2014-05-06 | 2014-05-06 | Cooling structure of lining of combustion chamber |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203892065U true CN203892065U (en) | 2014-10-22 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420229822.2U Expired - Lifetime CN203892065U (en) | 2014-05-06 | 2014-05-06 | Cooling structure of lining of combustion chamber |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203892065U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104832948A (en) * | 2015-04-23 | 2015-08-12 | 中国人民解放军空军工程大学 | Fingerprint mesh cooling device for concave cavity combustion chamber |
| CN105089852B (en) * | 2014-05-06 | 2017-02-15 | 中国航天科技集团公司第六研究院第十一研究所 | Combustion chamber inner liner cooling structure |
| CN109827191A (en) * | 2019-01-17 | 2019-05-31 | 上海空间推进研究所 | A kind of double cooling re-generatively cooled body portion structures of liquid-propellant rocket engine |
-
2014
- 2014-05-06 CN CN201420229822.2U patent/CN203892065U/en not_active Expired - Lifetime
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105089852B (en) * | 2014-05-06 | 2017-02-15 | 中国航天科技集团公司第六研究院第十一研究所 | Combustion chamber inner liner cooling structure |
| CN104832948A (en) * | 2015-04-23 | 2015-08-12 | 中国人民解放军空军工程大学 | Fingerprint mesh cooling device for concave cavity combustion chamber |
| CN109827191A (en) * | 2019-01-17 | 2019-05-31 | 上海空间推进研究所 | A kind of double cooling re-generatively cooled body portion structures of liquid-propellant rocket engine |
| CN109827191B (en) * | 2019-01-17 | 2020-11-10 | 上海空间推进研究所 | Double-cooling regenerative cooling body part structure of liquid rocket engine |
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| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |