CN101319308A - Chemical vapor deposition stove for manufacturing carbon brake disc of airplane - Google Patents
Chemical vapor deposition stove for manufacturing carbon brake disc of airplane Download PDFInfo
- Publication number
- CN101319308A CN101319308A CNA2008100220114A CN200810022011A CN101319308A CN 101319308 A CN101319308 A CN 101319308A CN A2008100220114 A CNA2008100220114 A CN A2008100220114A CN 200810022011 A CN200810022011 A CN 200810022011A CN 101319308 A CN101319308 A CN 101319308A
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- CN
- China
- Prior art keywords
- brake disc
- graphite
- vapor deposition
- chemical vapor
- carbon brake
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Abstract
The invention discloses a chemical vapor deposition furnace for preparing a carbon brake disc of an airplane relating to a method for preparing the carbon brake disc of the airplane, in particular to the method for preparing the carbon brake disc of the airplane through external-heat chemical vapor deposition (CVD) with directional flow. The furnace comprises an annular insulating layer provided with insulating cover at the upper end, an inner wall of the insulting layer is provided with a heating body having a heating chamber, the lower end of the insulting layer is provided with a lower supporting plate, the heating chamber above the lower supporting plate is provided with a graphite lower cover plate, the graphite upper cover plate is arranged on the graphite lower cover plate, centers of the graphite upper cover plate and the insulating cover have through holes respectively, and a graphite pipe is connected hermetically between the two through holes. With this invention, the airplane carbon brake disc with density above 1.80g/cm<3> can be manufactured.
Description
Technical field
The present invention relates to a kind of preparing technical field of airplane carbon brake disc.
Background technology
As requested, airplane carbon brake disc comparatively ideal density should be at 1.80g/cm
3More than, but to be density difficult again when arriving to a certain degree continues density for recurrent situation, and general bottleneck is 1.60g/cm in density
3About.In density from 0.60g/cm
3Reach 1.60g/cm
3The used time of density before only accounts for 1/3rd times of whole density process, in addition from density 1.60g/cm
3To density 1.80g/cm
3The used time accounts for 2/3rds of whole density process, even density can't arrive ideal 1.80g/cm under many circumstances
3More than.
The domestic present technology that adopts for the method for production density airplane carbon brake disc mainly contains two classes: the first kind is the recombining process of thermograde chemical Vapor deposition process+dipping carbonization, and second class is the isothermal chemical Vapor deposition process.Difference according to the design of the flow direction of unstripped gas is subdivided into many subclasses.The common feature of these methods is the even density that are difficult to realize precast body, in whole density process, the volume difference that causes owing to the difference of the interior outer radius of precast body makes the flow velocity of carbon raw material gas differ greatly, there is difference successively the time that arrives owing to gas simultaneously, bigger variation has also taken place in the temperature of gas, add in deposition process also inhomogeneous in variation that concentration takes place and flow field, make whole density process become restive.
Have and a kind ofly can continue density to density 1.80g/cm
3The method of above preparing airplane carbon brake disc by chemical vapor deposition; in chemical vapor deposition stove, insert the stock column of forming by each airplane carbon brake disc precast body and graphite gasket ring; after vacuumizing earlier; utilize heating element to form the high temperature of setting, feed carbon-source gas, diluent gas, carrier gas and protection adjustments of gas more successively.The path of flowing through of above process gas is: at first feed the stock column outside in the sediment chamber of body of heater, permeate to the inboard of stock column by the space in the precast body again, in the process of infiltration, be deposited in the precast body, reach the effect of density, realize the even density of precast body by the good direction of control flow velocity, thereby realize the purpose that the reduction of erection time reduces cost, improve product quality stability and corresponding friction and wear behavior simultaneously.
Summary of the invention
The object of the invention is to invent the above thickening technology of a kind of cooperation, and production can continue density to density 1.80g/cm
3The above chemical vapor deposition stove that is used to prepare airplane carbon brake disc.
The present invention includes a ring-type thermal insulation layer, upper end at thermal insulation layer is provided with insulation cover, the inwall setting of thermal insulation layer has the heating element in heating chamber, in the thermal insulation layer lower end bolster is set, in the heating chamber above bolster the graphite lower cover is set, arrange the graphite upper cover plate above the graphite lower cover, offer through hole respectively at the center of graphite upper cover plate and insulation cover, a carbon tube is tightly connected between two through holes.
During actual production, the airplane carbon brake disc precast body is packed in the heating chamber in the thermal insulation layer with the form of stock column, adopt the graphite gasket ring to separate between the adjacent precast body, add a cover the graphite upper cover plate on the stock column top by adjusting, also be lined with the graphite gasket ring between graphite upper cover plate and the stock column, also being supported in the cvd furnace bottom of stock column by graphite gasket ring and graphite lower cover.Pass through special technology again, promptly can be made into density at 1.80g/cm
3Above airplane carbon brake disc.
The present invention is simple in structure, convenient to be used, and can ensure the realization of production technique, guarantees that product is qualified.
Adjust for convenience, the two ends of described carbon tube are connected on graphite upper cover plate and the insulation cover by fitting nut respectively.
The aperture of the through hole of described graphite upper cover plate is 50～200mm.Because gas must be in order to guarantee the flow direction of gas from here by being drawn out of the sediment chamber.The aperture be can guarantee usually, the size less again to the furnace insulation performance impact.
The aperture of the through hole of described insulation cover is 50～200mm.Purpose is in order to mate the size of upper cover plate.
The through-hole aperture of graphite upper cover plate and insulation cover is identical, can keep air-flow unobstructed.
Description of drawings
Fig. 1 is a kind of use synoptic diagram of the present invention.
Embodiment
As shown in Figure 1,1 airplane carbon brake disc precast body, 2 graphite gasket rings, 3 graphite lower covers, 4 graphite upper cover plates, 5 bolsters, 6 heating elements, 7 insulation covers, 8 carbon tubes, 9 thermal insulation layers, 10 heating chambeies among the figure.
The upper end of ring-type thermal insulation layer 9 is provided with insulation cover 7, and the inwall setting of thermal insulation layer 1 has the heating element 6 in heating chamber 10.
In thermal insulation layer 9 lower ends bolster 5 is set, in the heating chamber 10 above bolster 5 graphite lower cover 3 is set, above graphite lower cover 3, arrange graphite upper cover plate 4, through hole is offered at center at graphite upper cover plate 4 and insulation cover 7 respectively, a carbon tube 8 is tightly connected between two through holes, the two ends of carbon tube 8 are provided with outside screw respectively, and the two ends of carbon tube 8 are connected on graphite upper cover plate 4 and the insulation cover 7 by fitting nut 12,11 respectively.Graphite upper cover plate 4 is identical with the through-hole aperture of insulation cover 7, can be between 50～200mm.
Claims (5)
1, a kind of chemical vapor deposition stove that is used to prepare airplane carbon brake disc, it is characterized in that comprising a ring-type thermal insulation layer, upper end at thermal insulation layer is provided with insulation cover, the inwall setting of thermal insulation layer has the heating element in heating chamber, in the thermal insulation layer lower end bolster is set, in the heating chamber above bolster the graphite lower cover is set, above the graphite lower cover, arrange the graphite upper cover plate, through hole is offered at center at graphite upper cover plate and insulation cover respectively, and a carbon tube is tightly connected between two through holes.
2,, it is characterized in that the two ends of described carbon tube are connected on graphite upper cover plate and the insulation cover by fitting nut respectively according to the described chemical vapor deposition stove that is used to prepare airplane carbon brake disc of claim 1.
3 according to the described chemical vapor deposition stove that is used to prepare airplane carbon brake disc of claim 1, and the aperture that it is characterized in that the through hole of described graphite upper cover plate is 50～200mm.
4, according to the described chemical vapor deposition stove that is used to prepare airplane carbon brake disc of claim 1, the aperture that it is characterized in that the through hole of described insulation cover is 50～200mm.
5, according to claim 1 or 2 or the 3 or 4 described chemical vapor deposition stoves that are used to prepare airplane carbon brake disc, it is characterized in that the through-hole aperture of graphite upper cover plate and insulation cover is identical.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNA2008100220114A CN101319308A (en) | 2008-07-17 | 2008-07-17 | Chemical vapor deposition stove for manufacturing carbon brake disc of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNA2008100220114A CN101319308A (en) | 2008-07-17 | 2008-07-17 | Chemical vapor deposition stove for manufacturing carbon brake disc of airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN101319308A true CN101319308A (en) | 2008-12-10 |
Family
ID=40179575
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNA2008100220114A Pending CN101319308A (en) | 2008-07-17 | 2008-07-17 | Chemical vapor deposition stove for manufacturing carbon brake disc of airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN101319308A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10458019B2 (en) | 2012-11-02 | 2019-10-29 | Industrial Technology Research Institute | Film deposition apparatus having a peripheral spiral gas curtain |
| CN111519162A (en) * | 2020-04-22 | 2020-08-11 | 西安航空制动科技有限公司 | Material column pressure adjusting device of chemical vapor deposition furnace |
-
2008
- 2008-07-17 CN CNA2008100220114A patent/CN101319308A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10458019B2 (en) | 2012-11-02 | 2019-10-29 | Industrial Technology Research Institute | Film deposition apparatus having a peripheral spiral gas curtain |
| CN111519162A (en) * | 2020-04-22 | 2020-08-11 | 西安航空制动科技有限公司 | Material column pressure adjusting device of chemical vapor deposition furnace |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Open date: 20081210 |