CN1242090C - Carbon brake disc negative pressure directional flow outward thermal gradient chemical gas phase penetration process and apparatus - Google Patents
Carbon brake disc negative pressure directional flow outward thermal gradient chemical gas phase penetration process and apparatus Download PDFInfo
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- CN1242090C CN1242090C CN 200310115118 CN200310115118A CN1242090C CN 1242090 C CN1242090 C CN 1242090C CN 200310115118 CN200310115118 CN 200310115118 CN 200310115118 A CN200310115118 A CN 200310115118A CN 1242090 C CN1242090 C CN 1242090C
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- carbon
- precast body
- negative pressure
- thermal gradient
- bodies
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- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 title claims abstract description 67
- 229910052799 carbon Inorganic materials 0.000 title claims abstract description 43
- 238000000034 method Methods 0.000 title claims abstract description 28
- 239000000126 substance Substances 0.000 title abstract description 6
- 230000035515 penetration Effects 0.000 title 1
- 229910002804 graphite Inorganic materials 0.000 claims abstract description 24
- 239000010439 graphite Substances 0.000 claims abstract description 24
- 230000008021 deposition Effects 0.000 claims abstract description 5
- 238000005056 compaction Methods 0.000 claims abstract description 3
- 238000001816 cooling Methods 0.000 claims description 10
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 10
- 238000000151 deposition Methods 0.000 claims description 5
- 238000004519 manufacturing process Methods 0.000 abstract description 11
- 230000003068 static effect Effects 0.000 abstract 1
- 239000003610 charcoal Substances 0.000 description 16
- 239000007789 gas Substances 0.000 description 15
- 238000005516 engineering process Methods 0.000 description 9
- 238000009413 insulation Methods 0.000 description 9
- 239000007792 gaseous phase Substances 0.000 description 6
- 238000012856 packing Methods 0.000 description 5
- 239000000463 material Substances 0.000 description 4
- 230000006698 induction Effects 0.000 description 3
- 238000002791 soaking Methods 0.000 description 3
- 238000010438 heat treatment Methods 0.000 description 2
- 238000012546 transfer Methods 0.000 description 2
- 238000009423 ventilation Methods 0.000 description 2
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 1
- 230000006978 adaptation Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000006229 carbon black Substances 0.000 description 1
- 239000003245 coal Substances 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 239000002826 coolant Substances 0.000 description 1
- 229910052802 copper Inorganic materials 0.000 description 1
- 239000010949 copper Substances 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000003085 diluting agent Substances 0.000 description 1
- 239000006185 dispersion Substances 0.000 description 1
- 238000009422 external insulation Methods 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 239000012535 impurity Substances 0.000 description 1
- 238000003780 insertion Methods 0.000 description 1
- 230000037431 insertion Effects 0.000 description 1
- 210000000867 larynx Anatomy 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 239000012071 phase Substances 0.000 description 1
- 238000003672 processing method Methods 0.000 description 1
- 239000002296 pyrolytic carbon Substances 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 239000000758 substrate Substances 0.000 description 1
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Abstract
The present invention relates to a negative-pressure directional-flow external thermal gradient chemical gas-phase permeation method and equipment for aero carbon braking discs, which is characterized in that: prefab bodies of aero carbon braking discs are loaded in a furnace; isopachous graphite pads are padded between all the prefab bodies; under negative pressure, the outside of the prefab bodies is heated and the inside is cooled to form a thermal gradient in a radial direction; under the negative pressure, carbon source gas nearly completely flows across all the equidistant slits between the prefab bodies in a fixed direction; a temperature difference of 0.3 DEG C /cm to 25 DEG C /cm, or an inner and outer total temperature difference of 30 DEG C to 380 DEG C is adopted, so the carbon source gas is made to enter the inner sides of the prefab bodies to flow across all the equidistant slits between the prefab bodies in a fixed direction and be discharged out of the furnace from the outer side; the compaction process of the prefab bodies is gradually carried out from the outer high-temperature face to the inner low-temperature face; and aero carbon braking disc products can be made through gas-phase carbon deposition for 300 to 600 hours. The present invention effectively enhances the use ratio of carbon source gas, has the advantages of good frictional characteristic and high thermal efficiency, is suitable for the structural characteristics of a static disc and a tail disc of various aero carbon braking discs, shortens the production period, reduces the cost, and is also suitable for industrial mass production.
Description
Affiliated technical field
The present invention relates to a kind of manufacture method of airplane carbon brake disc, particularly adopt the method for cold heat gradient chemical gaseous phase permeation (CVI) technology manufacturing airplane carbon brake disc in the outer heat of negative pressure oriented flow.
Background technology
CVI technology is a kind of well-known method in order to dense char fiber preform manufacturing thermal structure carbon/carbon composite, and for example materials such as airplane carbon brake disc, solid rocket motor nozzle charcoal/charcoal larynx lining, expansion segment all adopt this method.Traditional CVI technology is divided into four kinds of soaking method, thermal gradient method, pressure differential method and impulse methods.Britain Dunlop company, French Carbon Industie company, U.S. Goodyear, Bendix company etc. all adopt soaking CVI technology to make the carbon/carbon brake disc material, this traditional technology has the commercial scale production of adaptation, product is not subjected to characteristics such as geometrical shape restriction, heavy charcoal efficient is low, the production cycle is long but exist, and the surface easily crust, need repeatedly in the middle of shortcomings such as greying perforate or machining.U.S. B.F.Goodrich company and China 514 factories adopt pressure reduction CVI technology to make the airplane carbon brake disc material, though can shorten the production cycle, but adopt when only being confined to the carbon/carbon brake disc low density, after its density raises, the ventilation property variation of product, still need adopt soaking CVI technology, the shortcoming of above-mentioned existence still can not overcome fully.And Thermal Gradient CVI Process is made the method for airplane carbon brake disc, mainly be interior hot external cooling Thermal Gradient CVI Process, precast body does not have the artificial gas passage when folding in stove, certainly will cause each position gas flow inhomogeneous, influence the homogeneity of its density, and easily produce carbon black at the gas hold-up position; In addition, interior hot external cooling Thermal Gradient CVI Process is only applicable to the suitability for industrialized production of all types of aircraft charcoal brake Moving plates, and the outside of its quiet dish and final quotaion surface of friction easily causes its microtexture inhomogeneous, and influenced rubbing characteristics because the deposit carbon temperature is on the low side.
Summary of the invention
Technology of the present invention is dealt with problems and is: in order to overcome the deficiencies in the prior art, a kind of aircraft charcoal brake quiet dish and final quotaion constructional feature and ventilation property and good outer hot heat gradient chemical gaseous phase permeation (CVI) method of carbon/carbon brake disc negative pressure oriented flow of rubbing characteristics of being adapted to is provided.
Technical solution of the present invention is: outer hot heat gradient chemical gaseous phase permeation (CVI) method of carbon/carbon brake disc negative pressure oriented flow comprises the following steps:
(1) the airplane carbon brake disc precast body is packed in the outer thermal gradient gaseous phase deposition stove, be encased inside the Graphite pad of uniform thickness between each precast body;
(2) under negative pressure, make outside the precast body in the heat coldly, radially set up thermal gradient;
(3) adopt 30 ℃～380 ℃ of the temperature head of 0.3 ℃/cm～25 ℃/cm or inside and outside total temperature difference;
(4) make carbon-source gas enter the precast body inboard, oriented flow is equidistant slit through between each precast body, and is discharged out of the furnace by the outside;
(5) compaction process of precast body by outside high temperature face to the inside the low temperature face pass gradually, constantly adjust the shove charge position according to charcoal dish density value, through 4～6 stoves,, promptly can be made into the airplane carbon brake disc goods through 300～600 hours gas-phase carbon depositions.
The thickness that is encased inside the uniform thickness Graphite pad in the described step (1) between each charcoal dish precast body is 0.5～4.0mm.
The built-in interior water cooling plant of cold employing in the outer heat in the described step (2), outer heat is graphite heater.
Carbon-source gas enters the precast body inner chamber by furnace bottom in the described step (4), and oriented flow equidistant slit through between precast body.
The temperature range of precast body outside high temperature face is 1000 ℃～1180 ℃ in the described step (2).
Charcoal dish density value is constantly adjusted the position up and down that the shove charge position is meant the stove of packing into that density is high, the middle part of the low density stove of packing in the described step (5).
The present invention's beneficial effect compared with prior art is:
(1) the present invention is by the Frequency Induction Heating graphite heater, and precast body is heated through radiative transfer, because of it is equipped with interior water cooling plant, radially set up thermal gradient at precast body, and the outer Thermal Gradient CVI Process method and apparatus of employing negative pressure oriented flow, realized commercial scale production airplane carbon brake disc material, 50～60 of fixable coal discs have characteristics with short production cycle, that product cost is low.
(2) have and adapt to the brake characteristic of quiet dish and final quotaion constructional feature of all types of aircraft charcoals, on the surface of friction of charcoal dish, obtained rough laminar microstructure pyrolytic carbon matrix, have easy greying, thermo-efficiency height, feature that rubbing characteristics is good.
(3) the gas oriented flow is crossed equidistant slit between each precast body under the negative pressure, makes carbon-source gas (C
3H
6) almost 100% by precast body, improved its effective rate of utilization, often reach 20%～40%; And the directed stream of gas is unobstructed, and no gas hold-up place can prevent that the objectionable impurities sooty from forming.
(4) adopt than conventional Thermal Gradient CVI Process (temperature head (0.3 ℃/cm～25 ℃/cm), can widen the deposit carbon compact zone are reduced the consumption of plant capacity significantly that 70 ℃/cm of temperature head～400 ℃/cm) is less.
(5) the present invention can respond on the gaseous phase deposition stove to do slightly to change and just can reach function of the present invention in traditional vacuum.
Description of drawings
Fig. 1 is outer thermal gradient CVI equipment of oriented flow and a principle of work synoptic diagram among the present invention.
Embodiment
As shown in Figure 1, the outer thermal gradient CVI equipment of the oriented flow of the present invention's design is by bell 1, graphite cover plate 3 and on insulation quilt 2, graphite heater 5 and be positioned at its outside insulation quilt 6, be positioned at the copper induction coil 4 of insulation quilt 6, charcoal dish precast body 7, Graphite pad 8, thermopair 9, thermal insulation layer 10, graphite supporting plate 11, graphite carriage 12, insulation quilt 13, furnace bottom 14, inlet pipe 15, insulation quilt 16, interior water cooling plant 17, external furnace body 18, aspirating hole 19 is formed, interior water cooling plant 17 is arranged on the furnace bottom 14, and be inserted in the internal diameter of charcoal dish precast body 7, be provided with certain interval with charcoal dish precast body 7, water cooling plant 17 is the water pipe of interior logical water coolant, and is regulated the temperature head in charcoal dish precast body 7 outsides by the thickness that is positioned at its external insulation layer 16; Also fixing and inlet pipe 15 and graphite carriage 12 on furnace bottom 14, graphite supporting plate 11 is contained on the graphite carriage 12, and thickness is the thermal insulation layer 10 of 30mm～60mm on it.The charcoal dish precast body 7 of on thermal insulation layer 10, packing into, and separate with uniform thickness Graphite pad 8, the thickness of Graphite pad is 0.5mm～4.0mm, constitutes carbon-source gas C
3H
6The directed flow passage; Fixing temperature thermocouple 9 also on furnace bottom 14, and enter in the stove from charcoal dish precast body 7 inboards, and at the middle part curved 90 ° of angles are extended down to outer ledge from the inboard of precast body 7, be used to measure the temperature outside value.
Specific embodiments of the invention negative pressure oriented flow outside gradient CVI processing method is:
(1) with the precast body 7 of airplane carbon brake disc, external diameter is 300mm～500mm, and internal diameter is 150mm～320mm, and thickness is 15mm～40mm, and initial density is 0.56g/cm
3, suit is gone into above the graphite supporting plate 11 between water cooling plant 17 and the graphite heater 5, and with the Graphite pad 8 of uniform thickness, its thickness is that 0.5mm～4.0mm separates between each precast body 7, forms carbon-source gas C
3H
6The path of directed flow from the inside to the outside.When precast body 8 is packed stove inner height 50% into, with the outer edge place of thermopair 9 insertion precast bodies 7.The precast body 7 of once can packing into is 50～60, and after the superiors' precast body 7 is encased inside Graphite pad 8, covers graphite cover plate 3, the insulation quilt 2 of packing into, and lifting bell 1.
(2) start the vacuum unit, vacuumize by 19 pairs of bodies of heater of aspirating hole, vacuum meter show negative pressure be-0.086MPa～-0.1MPa.
(3) by Frequency Induction Heating graphite heater 4, and through radiative transfer precast body 7 is heated, its precast body 7 temperature outside reach 1000 ℃～1180 ℃, and because of water cooling plant 17 in being equipped with, its precast body 7 inboard temperature are 800 ℃～1000 ℃, have formed thermograde.
(4) carbon-source gas (C
3H
6) and diluent gas (N
2) entering precast body 7 inner chambers by inlet pipe 15, all according to the size of precast body 7, the shove charge total mass is set and is adjusted for both ratios and flow.The gas oriented flow is discharged out of the furnace by aspirating hole 19 through the equidistant slit of 7 of precast bodies.
When (5) carbon-source gas is flowed through the plane of precast body 7, be diffused in the hole rapidly, and carry out the deposit carbon process, and fine and closely pass gradually by the inboard, lateral in the outside of precast body 6 high temperature face.
(6) by the shove charge position of density size adjustment carbon/carbon brake disc base substrate 7, through 4～6 stoves, accumulative total depositing time 300～600 hours makes the density of carbon/carbon brake disc 7 reach 1.60g/cm
3～1.75g/cm
3, the density coefficient of dispersion of every batch of charcoal dish is less than 2%.
Claims (4)
1, the outer thermal gradient CVI method of the negative pressure oriented flow of airplane carbon brake disc is characterized in that comprising the following steps:
(1) the airplane carbon brake disc precast body is packed in the stove, be encased inside the Graphite pad of uniform thickness between each precast body;
(2) under negative pressure, make outside the precast body in the heat coldly, radially set up thermal gradient;
(3) adopt 30 ℃～380 ℃ of the temperature head of 0.3 ℃/cm～25 ℃/cm or inside and outside total temperature difference;
(4) make carbon-source gas enter the precast body inboard, oriented flow is equidistant slit through between each precast body, and is discharged out of the furnace by the outside;
(5) compaction process of precast body by outside high temperature face to the inside the low temperature face pass gradually, through 300～600 hours gas-phase carbon depositions, promptly can be made into the airplane carbon brake disc goods.
2, the outer thermal gradient CVI method of negative pressure oriented flow according to claim 1, it is characterized in that: the thickness of uniform thickness Graphite pad is 0.5～4.0mm in the described step (1).
3, the outer thermal gradient CVI method of negative pressure oriented flow according to claim 1 is characterized in that: in the described step (2) make in the outer heat of precast body cold employing built-in in water cooling plant, outer heat is graphite heater.
4, according to the thermal gradient CVI method outside the 1 described negative pressure oriented flow that requires of right, it is characterized in that: the temperature of precast body outside high temperature face is 1000 ℃～1180 ℃ in the described step (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200310115118 CN1242090C (en) | 2003-11-24 | 2003-11-24 | Carbon brake disc negative pressure directional flow outward thermal gradient chemical gas phase penetration process and apparatus |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200310115118 CN1242090C (en) | 2003-11-24 | 2003-11-24 | Carbon brake disc negative pressure directional flow outward thermal gradient chemical gas phase penetration process and apparatus |
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| Publication Number | Publication Date |
|---|---|
| CN1544686A CN1544686A (en) | 2004-11-10 |
| CN1242090C true CN1242090C (en) | 2006-02-15 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN 200310115118 Expired - Lifetime CN1242090C (en) | 2003-11-24 | 2003-11-24 | Carbon brake disc negative pressure directional flow outward thermal gradient chemical gas phase penetration process and apparatus |
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Families Citing this family (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN100368592C (en) * | 2005-08-03 | 2008-02-13 | 西北工业大学 | Large power heat gradient chemical gas phase infiltration process system monitoring device and method |
| CN101831623B (en) * | 2010-05-28 | 2011-12-07 | 湖南金博复合材料科技有限公司 | Chemical vapor densification furnace hearth |
| CN101942232B (en) * | 2010-08-17 | 2013-03-27 | 南京钛威科技有限公司 | Method for modifying stuffing by carbon |
| CN102618851B (en) * | 2012-03-31 | 2014-02-12 | 西安航天复合材料研究所 | Tool for compacting thick-walled hollow carbon/carbon (C/C) composite product |
| CN103044056B (en) * | 2013-01-10 | 2014-08-13 | 湖南南方搏云新材料有限责任公司 | Technology and equipment for preparing C/C composite |
| CN103193498B (en) * | 2013-04-07 | 2014-06-18 | 山东国晶新材料有限公司 | Narrow flow induction coupling chemical vapor deposition (CVD) densification method for rapidly preparing carbon/carbon composite material crucible |
| US10107343B2 (en) * | 2015-01-22 | 2018-10-23 | Ford Global Technologies, Llc | Thermoelectric energy recovery from a brake system |
| CN111120548A (en) * | 2019-12-26 | 2020-05-08 | 贵州宏安制动器科技有限公司 | Automatic production line for disc brake pieces |
| CN112628326A (en) * | 2020-11-13 | 2021-04-09 | 甘肃新西北碳素科技有限公司 | Preparation method of aircraft brake disc made of carbon/carbon composite material |
| CN116283330B (en) * | 2022-10-19 | 2024-06-07 | 西北工业大学 | Preparation method of directional deposition heterogeneous CC composite material |
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2003
- 2003-11-24 CN CN 200310115118 patent/CN1242090C/en not_active Expired - Lifetime
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| CN1544686A (en) | 2004-11-10 |
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Owner name: XI'AN CHAOMA SCIENCE CO., LTD. Free format text: FORMER OWNER: XI'AN AEROSPACE COMPOSITE MATERIALS INSTITUTE Effective date: 20060303 |
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Effective date of registration: 20060303 Address after: 101 mailbox 710025, Shaanxi City, Xi'an Province Patentee after: Xi'an Chaoma Technology Co.,Ltd. Address before: 101 mailbox 710025, Shaanxi City, Xi'an Province Patentee before: XI'AN AEROSPACE COMPOSITE MATERIALS Research Institute |
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