CN205168925U - Aircraft engine storehouse - Google Patents
Aircraft engine storehouse Download PDFInfo
- Publication number
- CN205168925U CN205168925U CN201520889238.4U CN201520889238U CN205168925U CN 205168925 U CN205168925 U CN 205168925U CN 201520889238 U CN201520889238 U CN 201520889238U CN 205168925 U CN205168925 U CN 205168925U
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- China
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- layer
- thickness
- aircraft engine
- utility
- cabin according
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- 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 - Fee Related
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Abstract
The utility model discloses an aircraft engine storehouse, include: start the machinery room casing to and connect in mobilizing machinery room shells inner wall and being used for stationary engine's engine mounting frame, start the machinery room casing to be equipped with and prevent hot wall, prevent that hot wall includes by an outer extremely interior wrap -around fibre layers in proper order, first resin rete, concatenation layer, second resin rete, the 2nd fibre layers, glass fiber layer, titanium alloy sheet layer, the concatenation layer is formed by same thickness's phenolic foam board and honeycomb panel concatenation. The utility model discloses aircraft engine storehouse, its casing are equipped with and prevent hot wall, prevent that hot wall comprises multilayer structure, and fire behavior is good.
Description
Technical field
The utility model relates to aircraft engine cabin.
Background technology
The driving engine of blimp is generally installed in engine bin, and the fire resistance of engine bin is the key factor ensureing that engine health is run.
Utility model content
The purpose of this utility model is to provide a kind of aircraft engine cabin, and its housing is provided with fireproof brickwork, and fireproof brickwork is made up of multiple-structure, and fire resistance is good.
For achieving the above object, the technical solution of the utility model is a kind of aircraft engine cabin of design, comprising: engine bin housing, and is connected to engine bin inner walls and for the motor mounts of stationary engine;
Described engine bin housing is provided with fireproof brickwork;
Described fireproof brickwork comprises the first coated successively from outside to inside carbon fiber layer, the first resin film layer, splicing layer, the second resin film layer, the second carbon fiber layer, glass layer, titanium alloy flaggy;
Described splicing layer is spliced by the phenolic board of same thickness and bending block.
Preferably, the thickness of described titanium alloy flaggy is 1mm.
Preferably, the thickness of described glass layer is 2mm.
Preferably, the thickness of described second carbon fiber layer is 3mm.
Preferably, the thickness of described second resin film layer is 1mm.
Preferably, the thickness of described splicing layer is 8mm.
Preferably, the thickness of described first resin film layer is 1mm.
Preferably, the thickness of described first carbon fiber layer is 2mm.
Advantage of the present utility model and beneficial effect are: provide a kind of aircraft engine cabin, its housing is provided with fireproof brickwork, and fireproof brickwork is made up of multiple-structure, and fire resistance is good.
Accompanying drawing explanation
Fig. 1 is schematic diagram of the present utility model;
Fig. 2 is the schematic diagram of fireproof brickwork.
Detailed description of the invention
Below in conjunction with drawings and Examples, detailed description of the invention of the present utility model is further described.Following examples only for clearly the technical solution of the utility model being described, and can not limit protection domain of the present utility model with this.
The technical scheme that the utility model is specifically implemented is:
As shown in Figure 1, a kind of aircraft engine cabin, comprising: engine bin housing 10, and is connected to engine bin housing 10 inwall and for the motor mounts 20 of stationary engine;
Described engine bin housing 10 is provided with fireproof brickwork;
Described fireproof brickwork comprises the first coated successively from outside to inside carbon fiber layer 1, first resin film layer 2, splicing layer 3, second resin film layer 4, second carbon fiber layer 5, glass layer 6, titanium alloy flaggy 7;
Described splicing layer 3 is spliced by the phenolic board 31 of same thickness and bending block 32.
The thickness of described titanium alloy flaggy 7 is 1mm.
The thickness of described glass layer 6 is 2mm.
The thickness of described second carbon fiber layer 5 is 3mm.
The thickness of described second resin film layer 4 is 1mm.
The thickness of described splicing layer 3 is 8mm.
The thickness of described first resin film layer 2 is 1mm.
The thickness of described first carbon fiber layer 1 is 2mm.
The above is only preferred implementation of the present utility model; should be understood that; for those skilled in the art; under the prerequisite not departing from the utility model know-why; can also make some improvements and modifications, these improvements and modifications also should be considered as protection domain of the present utility model.
Claims (8)
1. aircraft engine cabin, is characterized in that, comprising: engine bin housing, and is connected to engine bin inner walls and for the motor mounts of stationary engine;
Described engine bin housing is provided with fireproof brickwork;
Described fireproof brickwork comprises the first coated successively from outside to inside carbon fiber layer, the first resin film layer, splicing layer, the second resin film layer, the second carbon fiber layer, glass layer, titanium alloy flaggy;
Described splicing layer is spliced by the phenolic board of same thickness and bending block.
2. aircraft engine cabin according to claim 1, is characterized in that, the thickness of described titanium alloy flaggy is 1mm.
3. aircraft engine cabin according to claim 2, is characterized in that, the thickness of described glass layer is 2mm.
4. aircraft engine cabin according to claim 3, is characterized in that, the thickness of described second carbon fiber layer is 3mm.
5. aircraft engine cabin according to claim 4, is characterized in that, the thickness of described second resin film layer is 1mm.
6. aircraft engine cabin according to claim 5, is characterized in that, the thickness of described splicing layer is 8mm.
7. aircraft engine cabin according to claim 6, is characterized in that, the thickness of described first resin film layer is 1mm.
8. aircraft engine cabin according to claim 7, is characterized in that, the thickness of described first carbon fiber layer is 2mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520889238.4U CN205168925U (en) | 2015-11-10 | 2015-11-10 | Aircraft engine storehouse |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520889238.4U CN205168925U (en) | 2015-11-10 | 2015-11-10 | Aircraft engine storehouse |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205168925U true CN205168925U (en) | 2016-04-20 |
Family
ID=55732942
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520889238.4U Expired - Fee Related CN205168925U (en) | 2015-11-10 | 2015-11-10 | Aircraft engine storehouse |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205168925U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105253308A (en) * | 2015-11-10 | 2016-01-20 | 康福斯（苏州）航空工业有限公司 | Aircraft engine bin |
-
2015
- 2015-11-10 CN CN201520889238.4U patent/CN205168925U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105253308A (en) * | 2015-11-10 | 2016-01-20 | 康福斯（苏州）航空工业有限公司 | Aircraft engine bin |
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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: 20160420 Termination date: 20211110 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |