CN105736184B - High thrust is than, the micro-ablation that works long hours larynx lining and the laryngeal structure of diffuser - Google Patents
High thrust is than, the micro-ablation that works long hours larynx lining and the laryngeal structure of diffuser Download PDFInfo
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- CN105736184B CN105736184B CN201410743386.5A CN201410743386A CN105736184B CN 105736184 B CN105736184 B CN 105736184B CN 201410743386 A CN201410743386 A CN 201410743386A CN 105736184 B CN105736184 B CN 105736184B
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- diffuser
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- heat insulation
- ablation
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Abstract
The invention discloses a kind of high thrust than, the micro-ablation that works long hours larynx lining and the laryngeal structure of diffuser.Including larynx lining, backing, end liner and diffuser heat insulation layer;The First terrace that the outer surface of the larynx lining matches with the backing, the bottom surface of the backing is attached to second step surface of the end liner；3rd step surface of the diffuser heat insulation layer and the end liner；The second step face flushes with the 3rd step surface, while is bonded in the backing and diffuser heat insulation layer in circumferencial direction.Compared with prior art, its advantage and beneficial effect are：It disclosure satisfy that high thrust ratio and work long hours；Throat's component has the characteristics of micro-ablation；It disclosure satisfy that there is good effect of heat insulation under the conditions of working long hours, ensure the intensity of jet pipe housing；It can prevent that ablation amount in larynx footpath is excessive, the phenomenon for causing secondary work pressure to be decreased obviously；This structure can prevent that shock wave flows back, and avoid causing the energy loss of engine.
Description
Technical field
The present invention relates to nozzle technology, more particularly to a kind of high thrust ratio, the micro-ablation that works long hours larynx lining
And the laryngeal structure of diffuser.
Background technology
Jet pipe is one of important component in engine structure, and as the energy conversion device of engine, it makes high temperature
The heat energy of combustion gas is converted to the kinetic energy of combustion gas, so as to produce thrust.Meanwhile it is the control device of gas flow again, can make combustion
Burn the certain operating pressure of indoor foundation.
At present, for conventional jet pipe under conditions of ultra-long time work, larynx lining has obvious ablation, the change pair of larynx footpath
Engine inner trajectory has obvious influence, i.e. secondary work drop of pressure is obvious, while easily forms shock wave backflow and cause thrust
Total punching loss, therefore conventional jet pipe can not meet the design requirement of high thrust when long-time micro-ablation.
Therefore, in order to meet the requirement of low ablating rate for a long time, while need to avoid the ablation of larynx footpath larger, cause shock wave to return
Stream is, it is necessary to design throat's modular construction of a kind of new larynx lining, backing and diffuser.
The content of the invention
Present invention solves the technical problem that it is to provide a kind of high thrust than, the micro-ablation that works long hours larynx lining and diffuser
Laryngeal structure, solve the problems, such as that high thrust ratio works long hours micro-ablation, meet the design requirement totally proposed, it is ensured that engine long
Time effectively works.
In order to solve design requirement of the high thrust than the micro-ablation that works long hours, the present invention is real by the following technical programs
It is existing.A kind of high thrust is than, the micro-ablation that works long hours larynx lining and the laryngeal structure of diffuser, including larynx lining, backing, end liner and expansion
Dissipate section heat insulation layer;The First terrace that the outer surface of larynx lining matches with the backing, described in the bottom surface of the backing is attached to
Second step surface of end liner；3rd step surface of the diffuser heat insulation layer and the end liner；The second step face with
3rd step surface flushes, while is bonded in the backing and diffuser heat insulation layer in circumferencial direction.
Prior art is compared, and its advantage and beneficial effect are：
A, high thrust ratio can be expired and the requirement that works long hours（80~120s）；
B, throat's component has the characteristics of resistance to ablation；
C, meet that there is good effect of heat insulation under the conditions of working long hours, ensure the intensity of jet pipe housing；
D, ablation amount in larynx footpath can be avoided excessive, cause secondary work pressure to be decreased obviously；
E, avoid nozzle from producing shock wave backflow, cause energy loss.
Brief description of the drawings
Fig. 1 is a kind of high thrust of the present invention than, the micro-ablation that works long hours larynx lining and the laryngeal structure schematic diagram of diffuser.
Fig. 2 is a kind of high thrust of the specific embodiment of the invention than, the micro-ablation that works long hours larynx lining and the larynx of diffuser
The schematic diagram of portion's structure.
Fig. 3 is the heat examination trial curve figure of the specific embodiment of the invention.
Embodiment
A kind of high thrust of the present invention is now described in detail than, the micro-ablation that works long hours larynx lining and throat's knot of diffuser
Structure.
A kind of high thrust of the present invention is than, the micro-ablation that works long hours larynx lining and the parts of the laryngeal structure of diffuser
In, larynx lining 1, backing 2, end liner 3 and diffuser heat insulation layer 4 are using machining in corresponding metal or nonmetallic materials.Institute
The material for stating larynx lining 1 is W-cu.The material of backing 2 is felt carbon/carbon compound material.The material of end liner 3 is the high silica of phenolic aldehyde
Glass-cloth board.The diffuser heat insulation layer 4 is felt carbon/carbon compound material.Diffuser heat insulation layer and tail ring are first gluing using SW-2
Connect, then it is circumferentially fixed using 8 M4 soket head cap screw progress.
Its erection sequence is：Diffuser heat insulation layer 4 and backing 2 are sequentially loaded on end liner 3, is finally assembled to larynx lining 1
On backing 2 and diffuser heat insulation layer 4.The gap high-temp glue at each position（E-7 glue）Bonding, is specifically shown in Fig. 1 ~ Fig. 2.The present invention by
In the throat's modular construction mode for employing four part bondings, design method and principle：Diffuser is nonmetallic using resistance to erosion
Material, larynx shirt portion position use four-layer structure, wherein 1. larynx lining uses resistance to ablation metal structure, ensure engine long time work
Making larynx footpath does not have significant change；2. backing uses nonmetallic resistance to ablation and heat-barrier material；3. end liner uses non-metal heat-insulating material,
Jet pipe external temperature is set to be less than limit value, it is ensured that jet pipe casing rigidity is unaffected.4. diffuser uses non-metal heat-insulating material,
Ensure that the engine long time effectively works.
Jet pipe throat component has passed through the examination of multiple engine high and low temperature experiment.To nozzle throat after experiment
Component is decomposed, the results showed that the structure disclosure satisfy that the design requirement for the resistance to ablation that works long hours.Trial curve such as Fig. 3 institutes
Show.
The structure is applied in the model, and Product Process has been verified with productibility, and has been passed through in multiple times
Interview is tested, and structure is reliable, meets general requirement.
It is obvious to a person skilled in the art that the invention is not restricted to the details of above-mentioned one exemplary embodiment, Er Qie
In the case of without departing substantially from spirit or essential attributes of the invention, the present invention can be realized in other specific forms.
Claims (1)
1. a kind of high thrust is than, the micro-ablation that works long hours larynx lining and the laryngeal structure of diffuser, it is characterised in that including larynx
Lining, backing, end liner and diffuser heat insulation layer；The First terrace that the outer surface of the larynx lining matches with the backing, the back of the body
The bottom surface of lining is attached to the second step face of the end liner；3rd step surface of the diffuser heat insulation layer and the end liner；It is described
Second step face is flushed with the 3rd step surface, while the backing and diffuser heat insulation layer are bonded in circumferencial direction；The bottom of at
Lining is sequentially loaded into diffuser heat insulation layer and backing, and finally larynx lining is assembled on backing and diffuser heat insulation layer；The larynx lining
Heat-insulated nonmetallic materials are used using resistance to ablation nonmetallic materials, end liner using the metal material of resistance to ablation, backing；Diffuser is adiabatic
Layer uses resistance to ablation nonmetallic materials；The material of the end liner is phenolic aldehyde vagcor fabric swatch；The material of the larynx lining is W-
cu；The material of the backing is felt carbon/carbon compound material；The diffuser heat insulation layer is felt carbon/carbon compound material；The larynx lining
Formed with backing, backing and end liner, end liner and diffuser heat insulation layer by E-7 glue stickings；The diffuser heat insulation layer and tail ring
SW-2 glue stickings are first used, then it is circumferentially fixed using 8 M4 soket head cap screw progress.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410743386.5A CN105736184B (en) | 2014-12-09 | 2014-12-09 | High thrust is than, the micro-ablation that works long hours larynx lining and the laryngeal structure of diffuser |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410743386.5A CN105736184B (en) | 2014-12-09 | 2014-12-09 | High thrust is than, the micro-ablation that works long hours larynx lining and the laryngeal structure of diffuser |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105736184A CN105736184A (en) | 2016-07-06 |
| CN105736184B true CN105736184B (en) | 2018-04-03 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201410743386.5A Active CN105736184B (en) | 2014-12-09 | 2014-12-09 | High thrust is than, the micro-ablation that works long hours larynx lining and the laryngeal structure of diffuser |
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Families Citing this family (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106979095B (en) * | 2017-05-08 | 2019-10-08 | 湖北航天技术研究院总体设计所 | A kind of integrally formed integrated jet pipe and its manufacturing method |
| CN107091169A (en) * | 2017-06-29 | 2017-08-25 | 湖北三江航天江河化工科技有限公司 | A kind of rocket engine |
| CN107956597A (en) * | 2017-12-06 | 2018-04-24 | 内蒙动力机械研究所 | A kind of small-sized jet pipe to work long hours |
| CN108982747B (en) * | 2018-08-28 | 2021-06-15 | 西安近代化学研究所 | Superspeed ammunition throat liner ablation performance test kettle |
| CN110107429B (en) * | 2018-11-01 | 2023-07-21 | 内蒙古工业大学 | Design of double-flexible spray pipe joint of solid rocket engine |
| CN110608109B (en) * | 2019-10-09 | 2021-10-01 | 上海新力动力设备研究所 | Spray pipe structure |
| CN112780448A (en) * | 2021-01-26 | 2021-05-11 | 北京灵动飞天动力科技有限公司 | Thrust adjusting mechanism of solid rocket engine |
| CN113217229B (en) * | 2021-05-11 | 2022-02-18 | 中北大学 | Method and system for testing instantaneous nozzle throat diameter |
| CN115450798A (en) * | 2022-10-31 | 2022-12-09 | 北京中科宇航技术有限公司 | Long-time working solid rocket engine and long tail jet pipe thereof |
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| US3545679A (en) * | 1964-11-17 | 1970-12-08 | Thiokol Chemical Corp | Refractory article |
| US4180211A (en) * | 1974-05-30 | 1979-12-25 | Versar, Inc. | High temperature compressible support and gasket material |
| CN202360245U (en) * | 2011-11-21 | 2012-08-01 | 湖北航天技术研究院总体设计所 | Simplified combined nozzle structure of engine |
| CN103867339A (en) * | 2012-12-14 | 2014-06-18 | 上海新力动力设备研究所 | Ablation-proof structure of solid rocket engine |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS6194268U (en) * | 1984-11-28 | 1986-06-18 |
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Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3545679A (en) * | 1964-11-17 | 1970-12-08 | Thiokol Chemical Corp | Refractory article |
| US4180211A (en) * | 1974-05-30 | 1979-12-25 | Versar, Inc. | High temperature compressible support and gasket material |
| CN202360245U (en) * | 2011-11-21 | 2012-08-01 | 湖北航天技术研究院总体设计所 | Simplified combined nozzle structure of engine |
| CN103867339A (en) * | 2012-12-14 | 2014-06-18 | 上海新力动力设备研究所 | Ablation-proof structure of solid rocket engine |
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| 《碳毡/碳喷管喉衬的烧蚀形貌观察》;蒋谦逊;《航空材料工艺》;19900829(第4期);第1页 * |
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| CN105736184A (en) | 2016-07-06 |
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