CN1350959A - Method and equipment for high-speed gas-phase carbon deposition of braking carbon disk for aircraft - Google Patents
Method and equipment for high-speed gas-phase carbon deposition of braking carbon disk for aircraft Download PDFInfo
- Publication number
- CN1350959A CN1350959A CN 00113952 CN00113952A CN1350959A CN 1350959 A CN1350959 A CN 1350959A CN 00113952 CN00113952 CN 00113952 CN 00113952 A CN00113952 A CN 00113952A CN 1350959 A CN1350959 A CN 1350959A
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- China
- Prior art keywords
- heater
- gas
- charcoal
- brake disc
- carbon
- Prior art date
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- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 title claims abstract description 59
- 229910052799 carbon Inorganic materials 0.000 title claims abstract description 53
- 238000000034 method Methods 0.000 title abstract description 14
- 230000008021 deposition Effects 0.000 title description 6
- 238000000151 deposition Methods 0.000 claims abstract description 14
- 238000001816 cooling Methods 0.000 claims abstract description 4
- 238000010438 heat treatment Methods 0.000 claims abstract description 4
- 239000003610 charcoal Substances 0.000 claims description 36
- 239000007789 gas Substances 0.000 claims description 26
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 claims description 16
- 239000012071 phase Substances 0.000 claims description 13
- 229910002804 graphite Inorganic materials 0.000 claims description 8
- 239000010439 graphite Substances 0.000 claims description 8
- 229910052757 nitrogen Inorganic materials 0.000 claims description 8
- ATUOYWHBWRKTHZ-UHFFFAOYSA-N Propane Chemical compound CCC ATUOYWHBWRKTHZ-UHFFFAOYSA-N 0.000 claims description 6
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 6
- 239000000498 cooling water Substances 0.000 claims description 5
- 239000000126 substance Substances 0.000 claims description 5
- QQONPFPTGQHPMA-UHFFFAOYSA-N propylene Natural products CC=C QQONPFPTGQHPMA-UHFFFAOYSA-N 0.000 claims description 4
- 125000004805 propylene group Chemical group [H]C([H])([H])C([H])([*:1])C([H])([H])[*:2] 0.000 claims description 4
- 230000015572 biosynthetic process Effects 0.000 claims description 3
- 239000000835 fiber Substances 0.000 claims description 3
- 239000007792 gaseous phase Substances 0.000 claims description 3
- 239000001294 propane Substances 0.000 claims description 3
- 238000007789 sealing Methods 0.000 claims description 3
- 230000000740 bleeding effect Effects 0.000 claims description 2
- 239000012159 carrier gas Substances 0.000 claims description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 abstract description 4
- 238000005516 engineering process Methods 0.000 abstract description 3
- 238000004519 manufacturing process Methods 0.000 description 4
- 239000002131 composite material Substances 0.000 description 2
- 229910052802 copper Inorganic materials 0.000 description 2
- 239000010949 copper Substances 0.000 description 2
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 1
- 208000032843 Hemorrhage Diseases 0.000 description 1
- 238000011021 bench scale process Methods 0.000 description 1
- 208000034158 bleeding Diseases 0.000 description 1
- 231100000319 bleeding Toxicity 0.000 description 1
- 239000003245 coal Substances 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 238000005087 graphitization Methods 0.000 description 1
- 238000009776 industrial production Methods 0.000 description 1
- 238000001764 infiltration Methods 0.000 description 1
- 230000008595 infiltration Effects 0.000 description 1
- 238000003475 lamination Methods 0.000 description 1
- 238000007740 vapor deposition Methods 0.000 description 1
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Abstract
A technology and equipment for preparing carbon braking disk of airplane by high-speed gas-phase carbon deposit includes such steps as stacking carbon disks in furnace, enclosing furnace, vacuumizing, heating the heat-generating body, introducing working gas to furnace, cooling furnace wall by water, and depositing carbon for 200-400 hr. Its advantages include high carbon density up to 1.7-1.75 g/cu.cm, and high productivity (10-50 carbon disks for one process).
Description
The present invention relates to be equipped with the process and the equipment of carbon/carbon composite aeroplane brake discs, refer in particular to the speed gas-phase carbon deposition method and the equipment thereof of aircraft buggies dish with heat gradient windstream legal system.
In background technology, the appearance of carbon/carbon composite aeroplane brake discs has 30 years history, and China began to study in 1973.The carbon/carbon brake disc of domestic development of nineteen ninety is being destroyed first to install to take a flight test on----7E type aircraft and is being achieved success, its process is a charcoal cloth lamination, the isothermal method gas-phase carbon deposition, though this technology has certain advantage, but its fatal inferior position is that process cycle is long, needs 1000～1500 hours, and the degree of utilization of unstripped gas is low, less than 5%, charcoal dish cost is high.Domestic in recent years though the densified time of speed gas-phase carbon deposition shortens about several hours to 300 hours, all is to use smallclothes at bench-scale experiment with thermal gradient method development C/C brake disc, still lacks the suitability for industrialized production pattern.
The objective of the invention is to develop a kind of speed gas-phase carbon deposition method and equipment thereof of airplane carbon brake disc, adapt to the industrialization speed gas-phase carbon deposition that is used for various airplane carbon brake discs, charcoal efficient is sunk in raising work, shorten process cycle, further improve the effective rate of utilization of charcoal source gas, reduce the consumed power of electricity consumption of equipment amount, reduce its manufacturing cost greatly.
Technical solution of the present invention is as follows:
A kind of speed gas-phase carbon deposition method of airplane carbon brake disc, it is characterized in that: predecessor's charcoal fiber multihole skeleton dish of airplane carbon brake disc (4) is folded to fall to putting on body of heater (8) the charcoal carriage (11), sealing body of heater (8), after body of heater 8 vacuumized, heating graphite heater (5), furnace pressure is controlled at＜10Kpa, the furnace wall is a water-cooled, make charcoal dish (4) formation temperature gradient, its charcoal dish 4 internal diameters reach 1000～1200 ℃, and the external diameter temperature is 750～950 ℃, feed propylene gas and nitrogen in body of heater 8, or propane flammable gas and nitrogen, or methane gas and nitrogen constitutes working gas as carrier gas, and by 2 gas bleedings of body of heater 8 top aspirating holes, the working air current that forms directed flow thus is equably by charcoal dish 4, through 200～400 hours industrialization chemical gaseous phase carbon deposit, charcoal dish 4 density reached 1.70～1.75 gram per centimeters
3, through natural cooling, the check of coming out of the stove, airplane carbon brake disc (4).
Implement said method and custom-designed equipment, it is characterized in that: body of heater (8) assembling furnace bottom 10 and furnace top cover (1), the interior bottom assembling of body of heater (8) charcoal carriage (11), graphite heater (5) is positioned at the middle part, there are cooling water inlet (7) and outlet (12) in body of heater (8) side, and the work gas that distributes inlet (6), aspirating hole (2) is arranged on the furnace top cover (1), the overplate (3) of placement is arranged on the interior charcoal dish of body of heater (8) (4).
Described airplane carbon brake disc (4) external diameter is 300～540 millimeters, and internal diameter is 160～300 millimeters, and thickness is 15～30 millimeters, and the amount of folding is 10～50, and initial density is 0.55 gram per centimeter
3
Advantage of the present invention and effect are as follows:
1) by the specialized equipment of this process and implementing process, can large-scale industrial production realize the speed gas-phase carbon deposition airplane carbon brake disc.
2) through trial-production, by the deposit carbon that the vapor deposition of heat gradient windstream method rapid chemical obtains, easy graphitization, the heat efficiency height, frictional behavior is good.
3) equipment investment of this method is low, and electric power energy consumption is few, and is with short production cycle, and cost of product is low, is easy to industry and promotes.
4) the effective rate of utilization height of work gas reaches 20～27% usually as the effective rate of utilization of propylene gas, almost exceeds 10 times than isothermal method.
5) the present invention is suitable for the carbon/carbon brake disc that uses in the various aircraft models, and as 160～300 millimeters of 300～540 millimeters/internal diameters of external diameter, thickness is 15～30 millimeters carbon/carbon brake disc.
6) fixable coal disc of the present invention is 10～50, and initial density is 0.55 gram per centimeter
3, through 200～400 hours thermal gradient chemical vapor infiltration (CVD) of accumulative total, the density of the charcoal dish of finally coming out of the stove reaches 1.70～1.75 gram per centimeters
3, the global density difference is less than 3%.
Accompanying drawing of the present invention is whole furnace binding and work scheme drawing.Label declaration: 1-furnace top cover, 2-aspirating hole, 3-overplate, 4-airplane carbon brake disc (being called for short the charcoal dish), 5-graphite heater, 6-work gas inlet, 7-cooling water inlet, 8-body of heater, 9-copper electrode, 10-furnace bottom, 11-charcoal carriage, 12-water outlet.
Be embodiments of the invention below, see shown in the accompanying drawing: assembling furnace bottom 10 below the body of heater 8, furnace bottom 10 interior middle parts are graphite heater 5 fixedly, the charcoal carriage 11 of body of heater 8 bottoms assembling band through hole, bottom, the furnace wall outside has at least one cooling water inlet 7 in the body of heater 8, and upper outside has at least one cooling water outlet 12, forms circulating water and is used for cooled furnace wall, the outside, body of heater 8 furnace walls has several uniform work gas inlets 6, and the assembling of body of heater 8 tops has the furnace top cover 1 of aspirating hole.Speed gas-phase carbon deposition method of the present invention is as follows: predecessor's charcoal fiber multihole skeleton dish of getting airplane carbon brake disc 4, external diameter is 300～540 millimeters, and internal diameter is 160～300 millimeters, and thickness is 15～30 millimeters, the amount of folding is 10～50, and initial density is 0.55 gram per centimeter
3, be inserted on the body of heater 8 interior cylindrical graphite heaters 5 folded dropping on the charcoal carriage 11 successively, build furnace top cover 1, sealing body of heater 8, the aspirating hole 2 from furnace top cover 1 vacuumizes, degree of vacuum is-0.1MPa, by copper electrode 9 energisings, graphite heater 5 heating, its charcoal dish 4 internal diameter temperature reach 1000～1200 ℃, the furnace wall forms water-cooled, the continuous cooled furnace wall of water that flows, charcoal dish 4 external diameter temperature reach 750～950 ℃, make charcoal dish 4 formation temperature gradients.Feed earlier nitrogen in the stove of stove lateral, the back feeds propylene gas, or propane flammable gas or methane gas, and nitrogen uses as protection gas, ratio of both amounts and flow velocity all according to the size of charcoal dish 4, fold amount, temperature and pressure, and the aircraft machine is set and is adjusted.The aspirating hole 2 of furnace top cover 1 is extracted work gas out, form the working air current of directed flow thus, work gas comes in from the furnace wall to adopt radially directly to supply gas, perhaps admission port inclination certain angle, form the rotary work air-flow around place, charcoal dish 4 external diameter spaces, its charcoal dish 4 inner diameter volume also form the rotary work air-flow.Work gas flows to internal diameter by the external diameter of charcoal dish 4 equably, carries out gas-phase carbon deposition by charcoal dish 4, and body of heater 8 internal pressures are controlled at＜10Kpa, and through 200～400 hours industrialization chemical gaseous phase carbon deposit, charcoal dish 4 density reached 1.70～1.75 gram per centimeters
3, charcoal dish 4 global density differences are ± 3%, through naturally cooling to room temperature, come out of the stove through check, airplane carbon brake disc.
Claims (3)
1, a kind of speed gas-phase carbon deposition method of airplane carbon brake disc, it is characterized in that: predecessor's charcoal fiber multihole skeleton dish of airplane carbon brake disc (4) is folded to fall to putting on body of heater (8) the charcoal carriage (11), sealing body of heater (8), after body of heater (8) vacuumized, heating graphite heater (5), furnace pressure is controlled at＜10Kpa, the furnace wall is a water-cooled, make charcoal dish (4) formation temperature gradient, its charcoal dish 4 internal diameters reach 1000～1200 ℃, the external diameter temperature is 750～950 ℃, in body of heater (8), feed nitrogen and propylene gas, or nitrogen and propane flammable gas, or nitrogen and methane gas constitute working gas as carrier gas, and by aspirating hole (2) gas bleeding of body of heater (8) top, the working air current that forms directed flow thus is equably by charcoal dish (4), through 200～400 hours industrialization chemical gaseous phase carbon deposit, charcoal dish (4) density reached 1.70～1.75 gram per centimeters
3, through natural cooling, the check of coming out of the stove, airplane carbon brake disc (4).
2, implement the speed gas-phase carbon deposition method of the described airplane carbon brake disc of claim 1 and custom-designed equipment, it is characterized in that: body of heater (8) assembling furnace bottom (10) and furnace top cover (1), the interior bottom assembling of body of heater (8) charcoal carriage (11), graphite heater (5) is positioned at the middle part, there are cooling water inlet (7) and outlet (12) in body of heater (8) side, and the work gas that distributes inlet (6), aspirating hole (2) is arranged on the furnace top cover (1), the overplate (3) of placement is arranged on the interior charcoal dish of body of heater (8) (4).
3, the speed gas-phase carbon deposition method of airplane carbon brake disc according to claim 1, it is characterized in that: described airplane carbon brake disc (4) external diameter is 300～540 millimeters, and internal diameter is 160～300 millimeters, and thickness is 15～30 millimeters, the amount of folding is 10～50, and initial density is 0.55 gram per centimeter
3
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB001139525A CN1144958C (en) | 2000-10-27 | 2000-10-27 | Method and equipment for high-speed gas-phase carbon deposition of braking carbon disk for aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB001139525A CN1144958C (en) | 2000-10-27 | 2000-10-27 | Method and equipment for high-speed gas-phase carbon deposition of braking carbon disk for aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1350959A true CN1350959A (en) | 2002-05-29 |
| CN1144958C CN1144958C (en) | 2004-04-07 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNB001139525A Expired - Fee Related CN1144958C (en) | 2000-10-27 | 2000-10-27 | Method and equipment for high-speed gas-phase carbon deposition of braking carbon disk for aircraft |
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| CN (1) | CN1144958C (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN100394060C (en) * | 2006-07-20 | 2008-06-11 | 西安超码科技有限公司 | Airplane carbon brake disc integral adhesive maintenance method |
| CN102020482A (en) * | 2010-11-13 | 2011-04-20 | 西安超码科技有限公司 | Large resistive double-vacuum gas-phase carbon deposition device |
| CN101671189B (en) * | 2009-09-23 | 2012-07-18 | 北京航空航天大学 | Method for using domestic carbon fiber to prepare high-performance carbon-based composite material through rapid directional infiltration |
| CN104831347A (en) * | 2015-04-30 | 2015-08-12 | 西安超码科技有限公司 | Tool and method for densification of C/C crucible through internal-heat type chemical vapor infiltration |
| CN111072397A (en) * | 2019-12-03 | 2020-04-28 | 北京优材百慕航空器材有限公司 | Carbon/carbon composite material brake disc and preparation method thereof |
| CN113293356A (en) * | 2021-04-09 | 2021-08-24 | 郭李梁 | Device for preparing carbon-carbon composite material |
| CN115536419A (en) * | 2022-10-14 | 2022-12-30 | 湖南博云新材料股份有限公司 | Aviation carbon-ceramic brake material and preparation method thereof |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1587515A (en) * | 1976-11-03 | 1981-04-08 | Courtaulds Ltd | Composite structure |
| US4297307A (en) * | 1979-06-29 | 1981-10-27 | Union Carbide Corporation | Process for producing carbon-carbon fiber composites suitable for use as aircraft brake discs |
| US5398784A (en) * | 1991-10-29 | 1995-03-21 | Nissin Kogyo Co., Ltd. | Brake friction composite with reinforcing pyrolytic carbon and thermosetting resin |
| US5962135A (en) * | 1997-04-09 | 1999-10-05 | Alliedsignal Inc. | Carbon/carbon friction material |
-
2000
- 2000-10-27 CN CNB001139525A patent/CN1144958C/en not_active Expired - Fee Related
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN100394060C (en) * | 2006-07-20 | 2008-06-11 | 西安超码科技有限公司 | Airplane carbon brake disc integral adhesive maintenance method |
| CN101671189B (en) * | 2009-09-23 | 2012-07-18 | 北京航空航天大学 | Method for using domestic carbon fiber to prepare high-performance carbon-based composite material through rapid directional infiltration |
| CN102020482A (en) * | 2010-11-13 | 2011-04-20 | 西安超码科技有限公司 | Large resistive double-vacuum gas-phase carbon deposition device |
| CN102020482B (en) * | 2010-11-13 | 2013-10-16 | 西安超码科技有限公司 | Large resistive double-vacuum gas-phase carbon deposition device |
| CN104831347A (en) * | 2015-04-30 | 2015-08-12 | 西安超码科技有限公司 | Tool and method for densification of C/C crucible through internal-heat type chemical vapor infiltration |
| CN104831347B (en) * | 2015-04-30 | 2017-07-14 | 西安超码科技有限公司 | A kind of frock and method of internal heat type chemical gas-phase permeation compaction C/C crucibles |
| CN111072397A (en) * | 2019-12-03 | 2020-04-28 | 北京优材百慕航空器材有限公司 | Carbon/carbon composite material brake disc and preparation method thereof |
| CN113293356A (en) * | 2021-04-09 | 2021-08-24 | 郭李梁 | Device for preparing carbon-carbon composite material |
| CN115536419A (en) * | 2022-10-14 | 2022-12-30 | 湖南博云新材料股份有限公司 | Aviation carbon-ceramic brake material and preparation method thereof |
| CN115536419B (en) * | 2022-10-14 | 2023-09-29 | 湖南博云新材料股份有限公司 | Aviation carbon ceramic brake material and preparation method thereof |
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| Publication number | Publication date |
|---|---|
| CN1144958C (en) | 2004-04-07 |
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| C14 | Grant of patent or utility model | ||
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Owner name: XI'AN LANKONG AVIATION EQUIPMENT LIMITED LIABILITY Free format text: FORMER NAME OR ADDRESS: LANKANG AVIATION EQUIPMENT CO, XI'AN CITY |
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| CP03 | Change of name, title or address |
Address after: 710077 Shaanxi province Xi'an Fengdeng Nan Lu Lan stem No. 163 hospital Patentee after: Xi'an LAN Aviation Equipment Co., Ltd. Address before: 710077 Shaanxi province Xi'an Fengdeng Nan Lu Lan stem No. 163 hospital Patentee before: Lankang Aviation Equipment Co, Xi'an City |
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Owner name: SHAANXI LANTAI AVIATION EQUIPMENT CO., LTD. Free format text: FORMER OWNER: XI'AN LANKONG AVIATION EQUIPMENT LIMITED LIABILITY COMPANY Effective date: 20080104 |
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| TR01 | Transfer of patent right |
Effective date of registration: 20080104 Address after: No. 552, Feng Jia Jiayuan, two hi tech Road, Xi'an, Shaanxi Patentee after: Shaanxi Lantai Aerospace Co., Ltd. Address before: Shaanxi province Xi'an Fengdeng Nan Lu Lan Hospital No. 163 dry Patentee before: Xi'an LAN Aviation Equipment Co., Ltd. |
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| DD01 | Delivery of document by public notice |
Addressee: Shaanxi Lantai Aerospace Co., Ltd. Document name: Notification to Pay the Fees |
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| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20040407 Termination date: 20161027 |
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| CF01 | Termination of patent right due to non-payment of annual fee |