CN202360245U - Simplified combined nozzle structure of engine - Google Patents
Simplified combined nozzle structure of engine Download PDFInfo
- Publication number
- CN202360245U CN202360245U CN 201120463477 CN201120463477U CN202360245U CN 202360245 U CN202360245 U CN 202360245U CN 201120463477 CN201120463477 CN 201120463477 CN 201120463477 U CN201120463477 U CN 201120463477U CN 202360245 U CN202360245 U CN 202360245U
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- section
- nozzle
- heat insulation
- insulation layer
- jet pipe
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Abstract
The utility model discloses a simplified combined nozzle structure of an engine, which comprises a nozzle casing, a nozzle heat-insulating layer, a contraction section and a throat liner, wherein the nozzle heat-insulating layer is embedded in the casing and is positioned by the downstream end step of the casing; the nozzle heat-insulating layer comprises an upstream section, an intermediate section and a downstream section; the contraction section is embedded in the range from the upstream section to the first step of the heat-insulating layer; the intermediate section has a cone angle of 5-10 degrees and ranges from the first step of the heat-insulating layer to a conical step, and the throat liner is embedded in the intermediate section; the downstream section is used as a nozzle expansion section and ranges from the conical step to a nozzle outlet; the contraction section and the throat liner, and the contraction section and the downstream section of the heat-insulating layer are tightly jointed; and the taper of the conical step is 70-80 degrees. The utility model solves the existing problems of too many nozzle spare parts, complicated structure and time-consuming and labor-consuming machining and assembly, and is applicable to a (ram) engine nozzle structure of a solid rocket.
Description
Technical field
The utility model belongs to Space Dynamic's technical field, and a kind of motor that is specifically related to solid-rocket (punching press) motor is simplified the combination spray pipe structure.
Background technique
Solid rocket motor nozzle generally is installed in the motor afterbody, is made of a variety of materials, and adopt of structure taken piece formula or cordwood structure more.How the internal channel material is with high temperature resistant, anti-material of ablating, and medium material is used the low anti-thermal-protective material of heat conductivity always, and the outside is a metal shell, plays the load effect.
Existing solid-rocket (punching press) engine jet pipe structure comprises converging portion, larynx lining, back of the body wall heat insulation layer, diffuser heat insulation layer and jet pipe housing.Converging portion and larynx lining adopt high temperature resistant, anti-material of ablating, and back of the body wall heat insulation layer adopts high silica phenolic resin moulding material usually, is mainly used in anti-heat effect, prevents that heat from reaching the jet pipe housing; The diffuser heat insulation layer is used for main extending section, is made up of carbon cloth/phenolic aldehyde-compound winding material of Gao silica cloth/phenolic aldehyde, and high temperature resistant, the anti-ablation also has effect of heat insulation; The jet pipe housing adopts metallic material usually, mainly plays the load effect.Have following shortcoming: component are more, complex structure, and consumption power increases product cost when processing and assembly fee.
Summary of the invention
The purpose of the utility model is to provide a kind of component to reduce, and is simple and compact for structure, and processing and assembly process process are good, and the motor of reliable performance is simplified the combination spray pipe structure.
The technological scheme of the utility model: the motor of the utility model is simplified the combination spray pipe structure and is comprised jet pipe housing, jet pipe heat insulation layer, converging portion, larynx lining, and its jet pipe heat insulation layer is embedded in the housing, is located by housing downstream step; The jet pipe heat insulation layer comprises Upstream section, intermediate section and tract; Setting-in converging portion in Upstream section to the heat insulation layer first step; The cone angle of intermediate section is 5 °～10 °, and to type conical bench, intermediate section section setting-in larynx serves as a contrast by the heat insulation layer first step; Tract is as the jet pipe diffuser, by type conical bench to nozzle exit; Combine closely between converging portion and larynx lining and the heat insulation layer tract.
The tapering of said type conical bench is 70 °～80 °.
The advantage of the utility model: the utility model has solved more, the complex structure of existing jet pipe component, and the problem of consumption power is applicable to solid-rocket (punching press) engine jet pipe structure when processing and assembly fee.
Description of drawings
Fig. 1 is the structural representation of the utility model.
Embodiment
Below in conjunction with accompanying drawing and instance the utility model is done explanation in further detail.
Fig. 1 is the structural representation of the utility model, is half sectional view of jet pipe among the figure, and whole jet pipe should be the solid of rotation like Fig. 1.As shown in Figure 1, the utility model motor is simplified the combination spray pipe structure and is comprised jet pipe housing 1, jet pipe heat insulation layer 2, converging portion 3, larynx lining 4, jet pipe heat insulation layer, and jet pipe heat insulation layer 2 is embedded in the housing 1, is located by housing downstream step 1a; Jet pipe heat insulation layer 2 comprises Upstream section 2a, intermediate section 2b and tract 2c; Setting-in converging portion 3 in Upstream section to the heat insulation layer first step 2a1; The cone angle of intermediate section 2b is 5 °～10 °, and to type conical bench 2b1, intermediate section 2b section setting-in larynx serves as a contrast 4 by heat insulation layer first step 2a1; Tract 2c is as the jet pipe diffuser, by type conical bench 2b1 to nozzle exit; Combine closely between converging portion 3 and larynx lining 4 and the heat insulation layer tract 2c.
The tapering of said type conical bench 2b1 is 70 °～80 °.
Converging portion 3, larynx lining 4 adopt high temperature resistant, anti-material of ablating, and are processed by graphite; Larynx lining 4 docks assembling with jet pipe heat insulation layer 2 through two conical surfaces (intermediate section 2b, type conical bench 2b1), plays location, passing shaft to stress.
Jet pipe heat insulation layer 2 is positioned at one section 2c behind the larynx lining 4 also as the part of jet pipe extending section; Can adopt high silica cloth/phenolic resin to be entwined, promptly play anti-heat effect, prevent that the heat of hot high-temperature fuel gas from reaching jet pipe housing 1; Prevent that jet pipe housing 1 lost efficacy because of thermal structure; As the part of spray extending section, improve nozzle efficiency simultaneously, simplified nozzle structure.
The above is the preferred embodiment of the utility model, but the utility model should not be confined to the disclosed content of this embodiment and accompanying drawing.So everyly do not break away from the equivalence of accomplishing under the spirit disclosed in the utility model or revise, all fall into the scope of the utility model protection.
Claims (2)
1. a motor is simplified the combination spray pipe structure, comprises jet pipe housing (1), jet pipe heat insulation layer (2), converging portion (3), larynx lining (4), and it is characterized in that: jet pipe heat insulation layer (2) is embedded in the housing (1), is located by housing downstream step (1a); Jet pipe heat insulation layer (2) comprises Upstream section (2a), intermediate section (2b) and tract (2c); The interior setting-in converging portion of Upstream section to heat insulation layer first step (2a1) (3); The cone angle of intermediate section (2b) is 5 °～10 °, and to type conical bench (2b1), intermediate section (2b) section setting-in larynx serves as a contrast (4) by heat insulation layer first step (2a1); Tract (2c) is as the jet pipe diffuser, by type conical bench (2b1) to nozzle exit; Combine closely between converging portion (3) and larynx lining (4) and the heat insulation layer tract (2c).
2. motor according to claim 1 is simplified the combination spray pipe structure, and it is characterized in that: the tapering of said type conical bench (2b1) is 70 °～80 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201120463477 CN202360245U (en) | 2011-11-21 | 2011-11-21 | Simplified combined nozzle structure of engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201120463477 CN202360245U (en) | 2011-11-21 | 2011-11-21 | Simplified combined nozzle structure of engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202360245U true CN202360245U (en) | 2012-08-01 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201120463477 Expired - Fee Related CN202360245U (en) | 2011-11-21 | 2011-11-21 | Simplified combined nozzle structure of engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202360245U (en) |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104564424A (en) * | 2013-10-23 | 2015-04-29 | 上海新力动力设备研究所 | Material for back-wall insulating layer of throat liner of solid rocket engine |
| CN104696109A (en) * | 2013-12-10 | 2015-06-10 | 上海新力动力设备研究所 | Sealing structure of exhaust nozzle outlet of solid rocket engine |
| CN105736184A (en) * | 2014-12-09 | 2016-07-06 | 上海新力动力设备研究所 | Large thrust ratio, long-working micro-ablation throat insert and throat structure of expansion section |
| CN105736177A (en) * | 2014-12-09 | 2016-07-06 | 上海新力动力设备研究所 | Tailpipe nozzle heat insulation structure for double-layer composite material formed integrally |
| CN106050477A (en) * | 2016-07-28 | 2016-10-26 | 湖北航天技术研究院总体设计所 | Combined throat liner spraying pipe of solid rocket engine and manufacturing method |
| CN107084074A (en) * | 2017-05-23 | 2017-08-22 | 湖北航天技术研究院总体设计所 | A kind of high-performance side jet pipe solid propellant rocket |
| 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 |
| CN109047512A (en) * | 2018-10-12 | 2018-12-21 | 福建兵工装备有限公司 | SRM Nozzle blank component and its production method and the mold used |
| CN109139301A (en) * | 2018-09-07 | 2019-01-04 | 西安航天化学动力厂 | A kind of integrated solid rocket motor nozzle of thermal protection structure |
| CN109763916A (en) * | 2018-05-15 | 2019-05-17 | 湖北航天化学技术研究所 | A kind of solid rocket motor nozzle component connection sealing structure |
-
2011
- 2011-11-21 CN CN 201120463477 patent/CN202360245U/en not_active Expired - Fee Related
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104564424A (en) * | 2013-10-23 | 2015-04-29 | 上海新力动力设备研究所 | Material for back-wall insulating layer of throat liner of solid rocket engine |
| CN104696109A (en) * | 2013-12-10 | 2015-06-10 | 上海新力动力设备研究所 | Sealing structure of exhaust nozzle outlet of solid rocket engine |
| CN105736184A (en) * | 2014-12-09 | 2016-07-06 | 上海新力动力设备研究所 | Large thrust ratio, long-working micro-ablation throat insert and throat structure of expansion section |
| CN105736177A (en) * | 2014-12-09 | 2016-07-06 | 上海新力动力设备研究所 | Tailpipe nozzle heat insulation structure for double-layer composite material formed integrally |
| CN105736184B (en) * | 2014-12-09 | 2018-04-03 | 上海新力动力设备研究所 | High thrust is than, the micro-ablation that works long hours larynx lining and the laryngeal structure of diffuser |
| CN106050477A (en) * | 2016-07-28 | 2016-10-26 | 湖北航天技术研究院总体设计所 | Combined throat liner spraying pipe of solid rocket engine and manufacturing method |
| CN107084074B (en) * | 2017-05-23 | 2019-11-12 | 湖北航天技术研究院总体设计所 | A kind of high-performance side jet pipe solid propellant rocket |
| CN107084074A (en) * | 2017-05-23 | 2017-08-22 | 湖北航天技术研究院总体设计所 | A kind of high-performance side jet pipe solid propellant rocket |
| 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 |
| CN109763916A (en) * | 2018-05-15 | 2019-05-17 | 湖北航天化学技术研究所 | A kind of solid rocket motor nozzle component connection sealing structure |
| CN109139301A (en) * | 2018-09-07 | 2019-01-04 | 西安航天化学动力厂 | A kind of integrated solid rocket motor nozzle of thermal protection structure |
| CN109047512A (en) * | 2018-10-12 | 2018-12-21 | 福建兵工装备有限公司 | SRM Nozzle blank component and its production method and the mold used |
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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: 20120801 Termination date: 20141121 |
|
| EXPY | Termination of patent right or utility model |