CN110686080A - 一种由石英纤维与金属复合而成的耐高温密封件 - Google Patents
一种由石英纤维与金属复合而成的耐高温密封件 Download PDFInfo
- Publication number
- CN110686080A CN110686080A CN201911006028.5A CN201911006028A CN110686080A CN 110686080 A CN110686080 A CN 110686080A CN 201911006028 A CN201911006028 A CN 201911006028A CN 110686080 A CN110686080 A CN 110686080A
- Authority
- CN
- China
- Prior art keywords
- quartz
- quartz fiber
- braiding
- temperature
- braided layer
- Prior art date
- 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.)
- Pending
Links
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N silicon dioxide Inorganic materials O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 title claims abstract description 68
- 239000000835 fiber Substances 0.000 title claims abstract description 65
- 239000010453 quartz Substances 0.000 title claims abstract description 60
- 238000007789 sealing Methods 0.000 title claims abstract description 37
- 229910052751 metal Inorganic materials 0.000 title claims abstract description 9
- 239000002184 metal Substances 0.000 title claims abstract description 9
- 238000013329 compounding Methods 0.000 title abstract description 5
- 229910045601 alloy Inorganic materials 0.000 claims abstract description 33
- 239000000956 alloy Substances 0.000 claims abstract description 33
- 238000009954 braiding Methods 0.000 claims abstract description 22
- 239000006104 solid solution Substances 0.000 claims abstract description 12
- 238000005728 strengthening Methods 0.000 claims abstract description 12
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 claims abstract description 6
- 229910052804 chromium Inorganic materials 0.000 claims abstract description 6
- 239000011651 chromium Substances 0.000 claims abstract description 6
- 239000010941 cobalt Substances 0.000 claims abstract description 6
- 229910017052 cobalt Inorganic materials 0.000 claims abstract description 6
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 claims abstract description 6
- 229910052746 lanthanum Inorganic materials 0.000 claims abstract description 6
- FZLIPJUXYLNCLC-UHFFFAOYSA-N lanthanum atom Chemical compound [La] FZLIPJUXYLNCLC-UHFFFAOYSA-N 0.000 claims abstract description 6
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 claims abstract description 6
- 229910052721 tungsten Inorganic materials 0.000 claims abstract description 6
- 239000010937 tungsten Substances 0.000 claims abstract description 6
- 150000004696 coordination complex Chemical class 0.000 claims 1
- 239000000463 material Substances 0.000 abstract description 6
- 238000000034 method Methods 0.000 abstract description 5
- 238000005452 bending Methods 0.000 abstract description 2
- 235000012239 silicon dioxide Nutrition 0.000 description 42
- 239000010410 layer Substances 0.000 description 20
- 230000003647 oxidation Effects 0.000 description 6
- 238000007254 oxidation reaction Methods 0.000 description 6
- 230000007797 corrosion Effects 0.000 description 4
- 238000005260 corrosion Methods 0.000 description 4
- 238000004519 manufacturing process Methods 0.000 description 4
- 239000000377 silicon dioxide Substances 0.000 description 4
- 238000009941 weaving Methods 0.000 description 4
- 230000007547 defect Effects 0.000 description 3
- 238000013461 design Methods 0.000 description 3
- 230000004075 alteration Effects 0.000 description 2
- 229910052681 coesite Inorganic materials 0.000 description 2
- 239000002131 composite material Substances 0.000 description 2
- 229910052906 cristobalite Inorganic materials 0.000 description 2
- 239000013078 crystal Substances 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 239000004744 fabric Substances 0.000 description 2
- 239000012784 inorganic fiber Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000011160 research Methods 0.000 description 2
- 229910052682 stishovite Inorganic materials 0.000 description 2
- 238000006467 substitution reaction Methods 0.000 description 2
- 229910052905 tridymite Inorganic materials 0.000 description 2
- 238000003466 welding Methods 0.000 description 2
- 102100023904 Nuclear autoantigenic sperm protein Human genes 0.000 description 1
- 101710149564 Nuclear autoantigenic sperm protein Proteins 0.000 description 1
- 230000001133 acceleration Effects 0.000 description 1
- 230000003064 anti-oxidating effect Effects 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 239000000919 ceramic Substances 0.000 description 1
- 239000011248 coating agent Substances 0.000 description 1
- 238000000576 coating method Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000009413 insulation Methods 0.000 description 1
- 230000004807 localization Effects 0.000 description 1
- 229910052758 niobium Inorganic materials 0.000 description 1
- 239000010955 niobium Substances 0.000 description 1
- GUCVJGMIXFAOAE-UHFFFAOYSA-N niobium atom Chemical compound [Nb] GUCVJGMIXFAOAE-UHFFFAOYSA-N 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 239000004065 semiconductor Substances 0.000 description 1
- 229910021332 silicide Inorganic materials 0.000 description 1
- FVBUAEGBCNSCDD-UHFFFAOYSA-N silicide(4-) Chemical compound [Si-4] FVBUAEGBCNSCDD-UHFFFAOYSA-N 0.000 description 1
- 239000002356 single layer Substances 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J15/00—Sealings
- F16J15/02—Sealings between relatively-stationary surfaces
- F16J15/06—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces
- F16J15/10—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces with non-metallic packing
- F16J15/12—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces with non-metallic packing with metal reinforcement or covering
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B1/00—Layered products having a non-planar shape
- B32B1/08—Tubular products
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B15/00—Layered products comprising a layer of metal
- B32B15/02—Layer formed of wires, e.g. mesh
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B15/00—Layered products comprising a layer of metal
- B32B15/14—Layered products comprising a layer of metal next to a fibrous or filamentary layer
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
- B32B5/02—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
- B32B2262/10—Inorganic fibres
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
- B32B2262/10—Inorganic fibres
- B32B2262/101—Glass fibres
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2307/00—Properties of the layers or laminate
- B32B2307/30—Properties of the layers or laminate having particular thermal properties
- B32B2307/306—Resistant to heat
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2307/00—Properties of the layers or laminate
- B32B2307/50—Properties of the layers or laminate having particular mechanical properties
- B32B2307/51—Elastic
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2307/00—Properties of the layers or laminate
- B32B2307/70—Other properties
- B32B2307/724—Permeability to gases, adsorption
- B32B2307/7242—Non-permeable
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2605/00—Vehicles
- B32B2605/18—Aircraft
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Gasket Seals (AREA)
Abstract
本发明涉及密封件领域，尤其涉及一种由石英纤维与金属复合而成的耐高温密封件,由内往外依次为石英纤维内芯，石英纤维编织层和高温合金丝编织层，所述石英纤维内芯由4束石英纤维束绞合，所述石英纤维束由8根1040dtex的石英纤维成束组成，所述石英纤维编织层由多层石英纤维立体紧密编织而成，编织密度达97％以上，所述高温合金丝编织层由直径为0.04mm±0.005的合金丝编织而成，编织结构为48×11/0.04，编织密度不小于95％，所述合金丝为固溶强化型钴基高温合金，加入14％的钨固溶强化并且加入较高含量铬和微量镧。本发明具有高温回弹性良好，结构细密，良好的气密性能，并且纤维结构为主体，弯曲性能良好、重量轻，且其材料成本与工艺成本都在较低的范围。
Description
【技术领域】
本发明涉及密封件领域，尤其涉及一种由石英纤维与金属复合而成的耐高温密封件。
【背景技术】
热密封件就是在指能承受接缝位移，能在1050℃的高温条件中保持完好的密封效果，当航天飞行器处于极端热环境时，用于降低高温密封时气流的流动性，避免大量热气传到内部结构中，为了达到气密目的而嵌入部件中的材料。
高超音速飞行器的主要密封位置是在操纵截面、缝隙接口、发动机与机身的交界面等处，其中在操作面主要用在前缘、副翼、襟翼，除去以上位置还有用于部分起落架门、座舱罩、通道以及货舱门和有效载重舱门等。
NASA Glenn研究中心(GRC)的研究人员在20世纪80年代后期和90年代初开展了一项内部项目，即为NASP发动机开发密封件，推进系统密封件的开发研究，除此还包括X-38项目、NASA-ARC项目、轨道飞行器试验密封和热防护制造等项目。经过几十年的发展，各类高温密封组件已经广泛应用在航天飞机、X-37B、X-38、HTV-2、X-51等飞行器中。
密封件用于高速飞行器中，要承受其在加速过程中高热负荷及氧化，所以对其本身的性能要求很高，既要满足使用机件复杂的构型，又要有良好的隔热性能和柔韧性，可以使发动机的气体泄漏降到最低；此外还要承受一定的压力与摩擦，必须具备良好的弹性和耐磨性，这样才能在载荷和使用过程中保持本身的完整性。
但是目前，国内外密封件的研究多数还是基线密封或者二维织物密封，其存在高温回弹性丧失、结构单一、加工复杂等特点，并且还具有以下缺点：
1.陶瓷片密封件属于易碎性材料，不可适用于弯折处热密封，一般只用于特殊场合，如高冲压发动机内。因此，有必要针对弯曲的间隙密封研制具有柔性且气密性良好的热密封件。
2.编织绳状热密封件的纤维结构中倾斜方向与织物成型方向垂直，单层厚度较薄，很难保证在其使用过程中的是否对间隙进行了有效的密封。
3.基线密封条结构的弹簧表面需硅化铌涂层，并进行高温热处理，价格昂贵，质量与刚度问题无法大范围使用。此热密封件织造工艺复杂，需要进行多个织造环节最终成型，织造成本高。基线密封条主要由防热毡，阻隔热量传递，从而起到密封作用，但是因其结构不连续，芯子易被抽离，从而使密封件失效。
本发明即是针对现有技术的不足而研究提出的。
【发明内容】
本发明的目的是克服上述现有技术的缺点，提供了一种由石英纤维与金属复合而成的耐高温密封件，具有高温回弹性良好，结构细密，良好的气密性能，并且纤维结构为主体，弯曲性能良好、重量轻，且其材料成本与工艺成本都在较低的范围。
本发明可以通过以下技术方案来实现：
本发明公开了一种由石英纤维与金属复合而成的耐高温密封件,由内往外依次为石英纤维内芯，石英纤维编织层和高温合金丝编织层，所述石英纤维内芯由4束石英纤维束绞合，所述石英纤维束由8根1040dtex的石英纤维成束组成，所述石英纤维编织层由多层石英纤维立体紧密编织而成，编织密度达97％以上，所述高温合金丝编织层由直径为0.04mm±0.005的合金丝编织而成，编织结构为48×11/0.04，编织密度不小于95％，所述合金丝为固溶强化型钴基高温合金，加入14％的钨固溶强化并且加入较高含量铬和微量镧。石英纤维由高纯度二氧化硅和天然石英晶体制成的SiO2纯度高达99.99％的高性能无机纤维，直径一般为几微米～几十微米，质轻高强，具有强度高，介电常数和介电损耗小，耐高温一般在600～1500℃长期使用，膨胀系数小，耐腐蚀及可设计性好等一系列独特的优点，1040dtex石英纤维，密度：2.2g/cm3，断裂强度：1500-2400MPa，断裂伸长率：4.5％，在850℃下，纤维保留较高的强度和韧性，石英纤维编织层由石英纤维束作芯，再经过数层石英纤维立体紧密编织而成，编织密度达97％以上，各层空隙互相填补，经过多层的填补基本已无漏气风险，气密性能优异，合金丝是固溶强化型钴基高温合金，加入14％的钨固溶强化，使合金丝具有优良的高温热强性，添加较高含量铬和微量镧，使合金具有良好的高温抗氧化性能，同时具有满意的成形、焊接等工艺性能，适于制造航空发动机上在980℃以下要求高温和在1100℃以下要求抗氧化的零件，高温合金丝编织层在保证耐磨损防氧化防腐蚀的性能下，编织密度达97％以上具有良好的气密性能。
优选的，所述石英纤维内芯直径为0.8mm。
本发明与现有的技术相比有如下优点：
本方案设计的产品装配位置：排气装置与动力涡轮轴壳体组件之间，工作环境：燃气，工作环境温度：≤860℃，能达到1800小时的阶段使用寿命。
以往该产品都依赖进口，本方案的设计填补了国内复合材料密封件的空白，对先进装备国产化作出了比较突出的贡献。产品的纤维编织结构柔软性良好，可用于弯曲的间隙密封。纤维的耐热性良好，物理强度高，其回弹性能也比较良好；因其优异的编织结构设计，气密性能满足大部分密封件的要求；产品使用的石英纤维与高温合金丝均为国产产品，其价格比较有优势，在需求成本上有比较大的竞争力。
【附图说明】
下面结合附图对本发明的具体实施方式作进一步详细说明，其中：
图1为本发明的结构示意图；
图中：1、石英纤维内芯；2、石英纤维编织层；3、高温合金丝编织层；
【具体实施方式】
下面结合附图对本发明的实施方式作详细说明：
如图1所示，本发明公开了一种由石英纤维与金属复合而成的耐高温密封件,由内往外依次为石英纤维内芯1，石英纤维编织层2和高温合金丝编织层3，石英纤维内芯1由4束石英纤维束绞合，石英纤维束由8根1040dtex的石英纤维成束组成，石英纤维编织层2由多层石英纤维立体紧密编织而成，编织密度达97％以上，高温合金丝编织层3由直径为0.04mm±0.005的合金丝编织而成，编织结构为48×11/0.04，编织密度不小于95％，合金丝为固溶强化型钴基高温合金，加入14％的钨固溶强化并且加入较高含量铬和微量镧。石英纤维由高纯度二氧化硅和天然石英晶体制成的SiO2纯度高达99.99％的高性能无机纤维，直径一般为几微米～几十微米，质轻高强，具有强度高，介电常数和介电损耗小，耐高温一般在600～1500℃长期使用，膨胀系数小，耐腐蚀及可设计性好等一系列独特的优点，1040dtex石英纤维，密度：2.2g/cm3，断裂强度：1500-2400MPa，断裂伸长率：4.5％，在850℃下，纤维保留较高的强度和韧性，石英纤维编织层2由石英纤维束作芯，再经过数层石英纤维立体紧密编织而成，编织密度达97％以上，各层空隙互相填补，经过多层的填补基本已无漏气风险，气密性能优异，合金丝是固溶强化型钴基高温合金，加入14％的钨固溶强化，使合金丝具有优良的高温热强性，添加较高含量铬和微量镧，使合金具有良好的高温抗氧化性能，同时具有满意的成形、焊接等工艺性能，适于制造航空发动机上在980℃以下要求高温和在1100℃以下要求抗氧化的零件，高温合金丝编织层3在保证耐磨损防氧化防腐蚀的性能下，编织密度达97％以上具有良好的气密性能。
其中，石英纤维内芯1直径为0.8mm。
以上所述仅是本发明的优选实施方式，应当指出，对于本技术领域的普通技术人员来说，在不脱离本发明技术原理的前提下，可以对这些实施例进行多种变化、修改、替换和变型，这些变化、修改、替换和变型，也应视为本发明的保护范围。
Claims (3)
1.一种由石英纤维与金属复合而成的耐高温密封件，其特征在于：由内往外依次为石英纤维内芯，石英纤维编织层和高温合金丝编织层，所述石英纤维内芯由4束石英纤维束绞合，所述石英纤维束由8根1040dtex的石英纤维成束组成，所述石英纤维编织层由多层石英纤维立体紧密编织而成，编织密度达97％以上，所述高温合金丝编织层由直径为0.04mm±0.005的合金丝编织而成，编织结构为48×11/0.04，编织密度不小于95％。
2.根据权利1要求所述的由石英纤维与金属复合而成的耐高温密封件，其特征在于：所述石英纤维内芯直径为0.8mm。
3.根据权利1要求所述的由石英纤维与金属复合而成的耐高温密封件，其特征在于：所述合金丝为固溶强化型钴基高温合金，加入14％的钨固溶强化并且加入较高含量铬和微量镧。
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911006028.5A CN110686080A (zh) | 2019-10-22 | 2019-10-22 | 一种由石英纤维与金属复合而成的耐高温密封件 |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911006028.5A CN110686080A (zh) | 2019-10-22 | 2019-10-22 | 一种由石英纤维与金属复合而成的耐高温密封件 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110686080A true CN110686080A (zh) | 2020-01-14 |
Family
ID=69113560
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911006028.5A Pending CN110686080A (zh) | 2019-10-22 | 2019-10-22 | 一种由石英纤维与金属复合而成的耐高温密封件 |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110686080A (zh) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114056540A (zh) * | 2021-10-26 | 2022-02-18 | 航天特种材料及工艺技术研究所 | 一种舱门热密封材料构件及其制备方法 |
| CN115742351A (zh) * | 2022-11-04 | 2023-03-07 | 航天特种材料及工艺技术研究所 | 一种高弹性夹芯结构静密封材料构件及其制备方法 |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR1212515A (fr) * | 1958-10-24 | 1960-03-24 | Frankfurter Asbestwerke Paul K | Procédé pour la fabrication de bourrages de presse-étoupe et bourrages ainsi obtenus |
| US4119323A (en) * | 1976-05-18 | 1978-10-10 | Herbert Meister And Co. | Heat and solvent resistant flexible gasket means and process for production thereof |
| US4441726A (en) * | 1981-12-14 | 1984-04-10 | Shan-Rod, Inc. | Heat and vibration resistant seal |
| CN205424285U (zh) * | 2015-10-16 | 2016-08-03 | 天津工业大学 | 一种高温热密封件 |
| US20170260868A1 (en) * | 2016-03-11 | 2017-09-14 | General Electric Company | Method of treating a brush seal, treated brush seal, and brush seal assembly |
| CN110043665A (zh) * | 2019-04-30 | 2019-07-23 | 哈尔滨工业大学 | 一种适用于高温环境的热密封结构及其组装方法 |
| CN211175361U (zh) * | 2019-10-22 | 2020-08-04 | 江西瑞金金字电线电缆有限公司 | 一种由石英纤维与金属复合而成的耐高温密封件 |
-
2019
- 2019-10-22 CN CN201911006028.5A patent/CN110686080A/zh active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR1212515A (fr) * | 1958-10-24 | 1960-03-24 | Frankfurter Asbestwerke Paul K | Procédé pour la fabrication de bourrages de presse-étoupe et bourrages ainsi obtenus |
| US4119323A (en) * | 1976-05-18 | 1978-10-10 | Herbert Meister And Co. | Heat and solvent resistant flexible gasket means and process for production thereof |
| US4441726A (en) * | 1981-12-14 | 1984-04-10 | Shan-Rod, Inc. | Heat and vibration resistant seal |
| CN205424285U (zh) * | 2015-10-16 | 2016-08-03 | 天津工业大学 | 一种高温热密封件 |
| US20170260868A1 (en) * | 2016-03-11 | 2017-09-14 | General Electric Company | Method of treating a brush seal, treated brush seal, and brush seal assembly |
| CN110043665A (zh) * | 2019-04-30 | 2019-07-23 | 哈尔滨工业大学 | 一种适用于高温环境的热密封结构及其组装方法 |
| CN211175361U (zh) * | 2019-10-22 | 2020-08-04 | 江西瑞金金字电线电缆有限公司 | 一种由石英纤维与金属复合而成的耐高温密封件 |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114056540A (zh) * | 2021-10-26 | 2022-02-18 | 航天特种材料及工艺技术研究所 | 一种舱门热密封材料构件及其制备方法 |
| CN114056540B (zh) * | 2021-10-26 | 2023-05-05 | 航天特种材料及工艺技术研究所 | 一种舱门热密封材料构件及其制备方法 |
| CN115742351A (zh) * | 2022-11-04 | 2023-03-07 | 航天特种材料及工艺技术研究所 | 一种高弹性夹芯结构静密封材料构件及其制备方法 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110686080A (zh) | 一种由石英纤维与金属复合而成的耐高温密封件 | |
| CN211175361U (zh) | 一种由石英纤维与金属复合而成的耐高温密封件 | |
| US11148980B2 (en) | Protective coating for ceramic matrix composites | |
| EP2995779B1 (en) | Electrical panel and corresponding manufacturing method | |
| US9321537B2 (en) | Beam for suspending a turboshaft engine from an aircraft structure | |
| CN205282157U (zh) | 一种航空发动机区域用高温耐火电缆 | |
| CN112399744B (zh) | 一种复合耐高温阻热支撑结构 | |
| CN211893639U (zh) | 一种高超声速飞行器超高温端头热密封结构 | |
| US20140208770A1 (en) | Component having insert for receiving threaded fasteners | |
| CA2767319C (en) | A high temperature heat exchanger structure | |
| CN103500610A (zh) | 一种架空导线用纤维复合绳芯 | |
| CN110553554A (zh) | 一种用于高超声速导弹的轻质热防护结构 | |
| CN112109406B (zh) | 一种低导热高气阻热密封材料及其制备方法 | |
| CN111570804B (zh) | 基于梯度记忆合金驱动的航空发动机变形齿及加工工艺 | |
| CA2843765C (en) | Electrostatic bonding of coaxial tubing | |
| US20230100318A1 (en) | Ceramic matrix composite-based seal | |
| EP3913194B1 (en) | Variable vane assembly and method for operating a variable vane assembly | |
| EP3838868A1 (en) | Article with cooling holes and method of forming the same | |
| CN211150147U (zh) | 一种航空用耐高温高压导线 | |
| CN219891904U (zh) | 一种航空航天发动机舱用耐火电缆 | |
| CN111774512A (zh) | 一种基于体积成形的整体式重载承力结构拉杆制造方法 | |
| CN117963131A (zh) | 适用于变形翼飞行器的防热结构及变形翼飞行器 | |
| CN211087943U (zh) | 一种航空航天用组合绝缘电缆 | |
| US20240157183A1 (en) | Sacrificial fire shield for shielding an aircraft part | |
| CN219101465U (zh) | 一种新型密封耐热衬垫结构 |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |