CN105736177A - Tailpipe nozzle heat insulation structure for double-layer composite material formed integrally - Google Patents
Tailpipe nozzle heat insulation structure for double-layer composite material formed integrally Download PDFInfo
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- CN105736177A CN105736177A CN201410744417.9A CN201410744417A CN105736177A CN 105736177 A CN105736177 A CN 105736177A CN 201410744417 A CN201410744417 A CN 201410744417A CN 105736177 A CN105736177 A CN 105736177A
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Abstract
The invention discloses a tailpipe nozzle heat insulation structure for a double-layer composite material formed integrally. A convergence ring, a front section lining and a back section lining of the tailpipe nozzle heat insulation structure are located on the inner surface of a tailpipe nozzle, and a tailpipe back lining is located on the inner surface of a tailpipe nozzle shell body. After the convergence ring, the front section lining and the back section lining are bonded through SW-2 glue, the tailpipe back lining is pressurized, cured and formed by being integrally wound. According to the tailpipe nozzle heat insulation structure for the double-layer composite material formed integrally, by means of the novel structural mode type and the forming method, the thickness of a tailpipe heat insulation layer is increased, and the working reliability of the tailpipe nozzle is improved; and for the tailpipe nozzle which works reliably for a long time and is resistant to ablation, the structure with a die pressing layer and a winding layer is provided and is resistant to scouring and good in heat insulation effect, and the effect that an engine works reliably for a long time is ensured.
Description
Technical field
The present invention relates to nozzle technology, particularly to the jet pipe heat insulating construction of a kind of double-deck global formation composite.
Background technology
Jet pipe is one of vitals in engine structure, and as the energy conversion device of electromotor, it makes the heat energy of high-temperature fuel gas be converted to the kinetic energy of combustion gas, thus producing thrust.Meanwhile, it is again the control device of gas flow, can make to set up in combustor certain operating pressure.
At present, conventional jet pipe is when working long hours, and tail pipe heat insulation layer adopts one layer of carbon fiber/phenolic aldehyde pressing molding, this structure resistance to erosion, but the thermal protection scarce capacity worked long hours, and causes nozzle thermal protection to lose efficacy.Therefore conventional jet pipe can not meet the thermo-lag designing requirement that works long hours.In order to meet long-time thermo-lag requirement, it is necessary to design the adiabatic novel structure of jet pipe of a kind of double-deck global formation composite.
Summary of the invention
The present invention is the jet pipe heat insulating construction solving the technical problem that and being to provide a kind of double-deck global formation composite, improves the reliability that jet pipe works long hours, it is prevented that fire phenomenon that what resistance to ablation layer and thermal insulation layer two interlayer excesssive gap caused leap up.
Technical scheme: the jet pipe heat insulating construction of a kind of double-deck global formation composite, including: ring of convergence, leading portion lining, back segment lining, tail pipe backing；Described ring of convergence, leading portion lining, back segment lining are positioned at jet pipe inner surface, tail pipe backing is positioned at jet pipe shell inner surface；Described ring of convergence, leading portion lining, back segment lining adopt SW-2 is gluing connect after by tail pipe backing by entirety be wound around cure under pressure molding.
Further, the First terrace that the ring of convergence of described tail pipe heat insulation layer, leading portion lining, back segment lining mate with described tail pipe backing, with second step surface that the bottom surface of described tail pipe backing is attached to described end liner；Fit at circumferencial direction at described ring of convergence, leading portion lining simultaneously；Leading portion lining and the laminating of back segment lining circumferencial direction.
Further, described ring of convergence adopts resistance to ablation nonmetallic materials, leading portion lining to adopt resistance to ablation nonmetallic materials, back segment lining to adopt resistance to ablation nonmetallic materials, tail pipe backing to adopt heat insulation nonmetallic materials.
Due to the fact that to have employed four parts bonding and be wound around the frame modes of combination, compared with prior art, its advantage and providing the benefit that:
A, disclosure satisfy that the requirement (80 ~ 120s) that works long hours；
B, tail pipe heat insulation layer have the feature of resistance to ablation；
C, tail pipe heat insulation layer disclosure satisfy that have good effect of heat insulation under the condition of working long hours, it is ensured that the intensity of jet pipe housing；
D, prevent the fire phenomenon that leaps up that resistance to ablation layer and thermal insulation layer two interlayer excesssive gap cause；
The reliability that e, raising jet pipe work long hours.
Accompanying drawing explanation
Fig. 1 is the jet pipe heat insulating construction schematic diagram of a kind of two-layered, formed composite of the present invention.
Fig. 2 is the schematic diagram of each part of jet pipe heat insulation layer, in figure: ring of convergence 1, leading portion lining 2, back segment lining 3, tail pipe backing 4.
Fig. 3 is that the heat of the specific embodiment of the invention is had a try and tested curve chart.
Detailed description of the invention
Now describe the long-time reliably working of the present invention in detail, the jet pipe heat insulating construction of a kind of two-layered, formed composite of resistance to ablation.
In order to solve to work long hours anti-yaw damper and the good designing requirement of heat-proof quality, the present invention is achieved through the following technical solutions.The jet pipe heat insulating construction of a kind of double-deck global formation composite is made up of totally ring of convergence 1, leading portion lining 2, back segment lining 3, tail pipe backing 44 parts, ring of convergence 1, leading portion lining 2, back segment lining 3 radial gap room temperature gluing connect.Its erection sequence is: bonding leading portion lining 2 successively on ring of convergence 1, more bonding back segment lining 3.After bonding using ring of convergence 1, leading portion lining 2, back segment lining 3 as winding mandrel by wound on it for tail pipe backing 4.It is specifically shown in Fig. 1 ~ Fig. 2.
In the present embodiment, the material of described ring of convergence 1 is carbon fiber/phenolic aldehyde pressing, the material of described leading portion lining 2 is carbon fiber/phenolic aldehyde pressing, and the material of described back segment lining 3 is carbon fiber/phenolic aldehyde pressing, and the material of described tail pipe backing 4 is shell of column heat insulation layer winding product.This jet pipe insulating structure has passed through the examination of multiple electromotor high and low temperature test.After test, jet pipe heat insulation layer being decomposed, result shows that this structure disclosure satisfy that long-time reliably working, resistance to ablation and heat insulation good designing requirement.Trial curve is as shown in Figure 3.This structure is applied in this model, and Product Process and productibility are verified, and have passed through repeatedly ground experiment, 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, and when without departing substantially from the spirit of the present invention or basic feature, it is possible to realize the present invention in other specific forms.
Claims (7)
1. the jet pipe heat insulating construction of a double-deck global formation composite, it is characterised in that including: ring of convergence, leading portion lining, back segment lining, tail pipe backing；Described ring of convergence, leading portion lining, back segment lining are positioned at jet pipe inner surface, tail pipe backing is positioned at jet pipe shell inner surface；Described ring of convergence, leading portion lining, back segment lining adopt SW-2 is gluing connect after by tail pipe backing by entirety be wound around cure under pressure molding.
2. according to the jet pipe heat insulating construction of the double-deck global formation composite described in claim 1, it is characterized in that, the First terrace that the ring of convergence of described tail pipe heat insulation layer, leading portion lining, back segment lining mate with described tail pipe backing, with second step surface that the bottom surface of described tail pipe backing is attached to described end liner；Fit at circumferencial direction at described ring of convergence, leading portion lining simultaneously；Leading portion lining and the laminating of back segment lining circumferencial direction.
3. according to the jet pipe heat insulating construction of the double-deck global formation composite described in claim 1, it is characterized in that, described ring of convergence adopts resistance to ablation nonmetallic materials, leading portion lining to adopt resistance to ablation nonmetallic materials, back segment lining to adopt resistance to ablation nonmetallic materials, tail pipe backing to adopt heat insulation nonmetallic materials.
4. according to the jet pipe heat insulating construction of the double-deck global formation composite described in claim 1, it is characterised in that the material of described ring of convergence is carbon fiber/phenolic aldehyde pressing.
5. according to the jet pipe heat insulating construction of the double-deck global formation composite described in claim 1, it is characterised in that the material of described leading portion lining is carbon fiber/phenolic aldehyde pressing.
6. according to the jet pipe heat insulating construction of the double-deck global formation composite described in claim 1, it is characterised in that the material of described back segment lining is carbon fiber/phenolic aldehyde pressing.
7. according to the jet pipe heat insulating construction of the double-deck global formation composite described in claim 1, it is characterised in that the material of described tail pipe backing is shell of column heat insulation layer winding product.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410744417.9A CN105736177A (en) | 2014-12-09 | 2014-12-09 | Tailpipe nozzle heat insulation structure for double-layer composite material formed integrally |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410744417.9A CN105736177A (en) | 2014-12-09 | 2014-12-09 | Tailpipe nozzle heat insulation structure for double-layer composite material formed integrally |
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| CN105736177A true CN105736177A (en) | 2016-07-06 |
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| CN201410744417.9A Pending CN105736177A (en) | 2014-12-09 | 2014-12-09 | Tailpipe nozzle heat insulation structure for double-layer composite material formed integrally |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106628110A (en) * | 2016-11-28 | 2017-05-10 | 北京航天长征飞行器研究所 | Novel integral special-shaped heatproof structure with ablation and heat insulation function division |
| CN112035933A (en) * | 2020-09-03 | 2020-12-04 | 西北工业大学 | Solid rocket engine jet pipe thermal structure coupling analysis method considering structural clearance |
| CN112122889A (en) * | 2020-09-27 | 2020-12-25 | 西安远航真空钎焊技术有限公司 | Preparation method of thermal insulation board for power vectoring nozzle |
| CN113719380A (en) * | 2021-08-28 | 2021-11-30 | 福建兵工装备有限公司 | Endurance engine tail pipe lining blank and pressing die and manufacturing method thereof |
| CN114486552A (en) * | 2022-01-25 | 2022-05-13 | 长春长光宇航复合材料有限公司 | Method and device for representing performance of high-temperature environment interface of integrated spray pipe |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106628110A (en) * | 2016-11-28 | 2017-05-10 | 北京航天长征飞行器研究所 | Novel integral special-shaped heatproof structure with ablation and heat insulation function division |
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| CN112035933A (en) * | 2020-09-03 | 2020-12-04 | 西北工业大学 | Solid rocket engine jet pipe thermal structure coupling analysis method considering structural clearance |
| CN112035933B (en) * | 2020-09-03 | 2022-02-22 | 西北工业大学 | Solid rocket engine jet pipe thermal structure coupling analysis method considering structural clearance |
| CN112122889A (en) * | 2020-09-27 | 2020-12-25 | 西安远航真空钎焊技术有限公司 | Preparation method of thermal insulation board for power vectoring nozzle |
| CN112122889B (en) * | 2020-09-27 | 2021-11-19 | 西安远航真空钎焊技术有限公司 | Preparation method of thermal insulation board for power vectoring nozzle |
| CN113719380A (en) * | 2021-08-28 | 2021-11-30 | 福建兵工装备有限公司 | Endurance engine tail pipe lining blank and pressing die and manufacturing method thereof |
| CN114486552A (en) * | 2022-01-25 | 2022-05-13 | 长春长光宇航复合材料有限公司 | Method and device for representing performance of high-temperature environment interface of integrated spray pipe |
| CN114486552B (en) * | 2022-01-25 | 2024-03-26 | 长春长光宇航复合材料有限公司 | Method and device for representing interface performance of high-temperature environment of integrated spray pipe |
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Application publication date: 20160706 |
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