CN103722789B - A kind of molybdenio multilamellar heat insulation material and structure thereof - Google Patents
A kind of molybdenio multilamellar heat insulation material and structure thereof Download PDFInfo
- Publication number
- CN103722789B CN103722789B CN201310412088.3A CN201310412088A CN103722789B CN 103722789 B CN103722789 B CN 103722789B CN 201310412088 A CN201310412088 A CN 201310412088A CN 103722789 B CN103722789 B CN 103722789B
- Authority
- CN
- China
- Prior art keywords
- molybdenum
- molybdenio
- coating
- heat insulation
- thickness
- 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.)
- Active
Links
Abstract
A kind of molybdenio multilamellar heat insulation material and structure thereof, this material presents multiple structure, is nickel coating, molybdenum froth bed, metal molybdenum layer and MoSi the most successively2Coating, thickness is respectively 0.5～3mm, 1～5mm, 0.1～0.5mm and 0.1～0.5mm.They are be combined with each other by interatomic force, form a kind of tubular structure, can steady operation in high temperature environments, and antioxidation, anticorrosion, can be as requiring the high temperature structural members such as harsh aerospace vehicle jet pipe.
Description
Technical field
The present invention relates to a kind of heat insulation material and structure thereof, particularly relate to a kind of molybdenio multilamellar heat insulation material and structure thereof.
Background technology
Jet pipe is the important component part of electromotor, and it is in high-temperature high-pressure air flow environment.Owing to being limited by total arrangement,
Wanting cube little, lightweight, intensity is high, high temperature resistant.Therefore it can not use high-strength alloy steel making completely, but by many
Plant what combination of materials got up.The most conventional jet pipe material has Nb alloy, C/C composite etc..
C-103 (Nb-10Hf-1Ti-0.5Zr) and two kinds of Nb alloys of Nb521 (Nb-5W-2Mo-1Zr) are liquid-rocket combustions
Chamber body portion and thrust chamber, the critical material of jet pipe extension.Its use temperature of C-103 alloy, between 1200-1400 DEG C, is
The common used material of China's liquid-propellant rocket engine at present, has been applied to YF-40 and Long March series, Dongfeng series rocket engine,
Nearly 4 tons of annual production.Nb521 alloy density is 8.87kg/cm3, slightly below C-103 alloy (8.9kg/cm3), use temperature to exist
Between 1400-1650 DEG C, it is possible to meet KKV (KKV) and the rail of corresponding guided missile delivery system use, appearance control are sent out
Motivation, as novel in Df-31A, 300N, 200N, 25N niobium alloy jet pipe of No. JL-2 three grades of attitude control engines use and future
Military satellite, the requirement to material of the spacelab attitude control engine, have been designed to the multiple combustor such as 490N, 150N knot
Component.But, relative to ceramic and other composite material, the big quality of alloy jet pipe and high price limit it to a certain extent should
Use scope.
Song Yun etc. describe carbon/carbon compound material in document " carbon/carbon compound material application in propulsion system " and send out at solid
Application in the propulsion systems such as motivation, liquid engine and turbojet.Cosmic space variations in temperature is violent, it is desirable to material
Expecting low and dimensionally stable heat-resisting, resistance to, need great thrust to cosmic space launching objects, alleviating of weight will bring greatly
Benefit.Performance unique for C/C makes it have promising future in aerospace system, but at present also by manufacture method and test
The restriction of means.
Liquid propellant engine may be also referred to simply as liquid-propellant rocket engine or liquid engine.It is with solid propellant rocket
Different propellant the most used is liquid condition.Liquid engine is typically by thrust chamber, turbine pump, gas generator or pre-
Combustion room, valve and automation composition.Current liquid engine chamber pressure is all more than 30 atmospheric pressure, and liquid pushes away
When entering agent burning, temperature is up to 3830 DEG C.C/C discharge duct the most easily aoxidizes, and carbonaceous surface is easy to corrosion, not
The C/C of coating is only capable of using in a short time.Although coating C/C has a bigger captivation, but their price be generally not capable of with
Traditional material is compared.
Summary of the invention
Present invention is generally directed to the thermal structure pipe fitting of burner, propose a kind of molybdenio multilamellar heat insulation material and structure thereof.This material
It is made up of four layers of different materials, is nickel coating, molybdenum froth bed, metal molybdenum layer and MoSi the most successively2Coating.They lead to
Cross interatomic force to be combined with each other, form a kind of tubular structure, can steady operation in high temperature environments, and antioxidation, anti-
Corrosion, can be as requiring the high temperature structural members such as harsh aerospace vehicle jet pipe.
Described molybdenum foam constitutes the main body of tubular structure with metal molybdenum layer, is the intermediate layer of structure, and molybdenum foam is positioned at molybdenum pipe
Outer surface, inside presents three-dimensional network shape, and thickness is 1～5mm.Molybdenum pipe is the metal molybdenum layer of tubulose, and thickness is
0.1～0.5mm.
Described nickel coating is positioned at the outermost layer of tubular structure, is attached to molybdenum foam surface, and thickness is 0.5～3mm, has excellent
Antioxidation and decay resistance.Described MoSi2Coating is positioned at the inner surface of molybdenum pipe, is the innermost layer of tubular structure,
Thickness is 0.1mm～0.5mm, has the highest intensity, hardness and high-temperature stability, and the antioxidation of excellence, mar proof
Energy.
Present invention have the main advantage that 1. this exothermic material has multiple structure, light weight, intensity is high, has the high temperature of excellence
Performance, it is possible to antioxidation and anticorrosion；2. this material comprises multiple refractory metal and coating, keeps stable in high temperature environments
Duty；3. it is foamed materials inside this tubular structure, the materials such as cooling, phase transformation can be filled, it is achieved the height of thermal structure
Effect cooling；4. this tubular structure surface attachment has antioxidation, erosion shield, has service life long, the advantage of good stability.
Accompanying drawing explanation
It is illustrated as the schematic diagram of a kind of anti-heat pipe of molybdenio multilamellar.
Diagram 10 is nickel coating；20 is molybdenum foam；30 is molybdenum pipe；40 is MoSi2Coating.
Detailed description of the invention
Below in conjunction with specific embodiment, it is further elucidated with the present invention, it should be understood that these embodiments are merely to illustrate the present invention and need not
In limiting the scope of the present invention, after having read the present invention, those skilled in the art repair the various equivalent form of values of the present invention
Change and all fall within the application claims and limited.
Embodiment 1
A kind of molybdenio multilamellar heat insulation material and structure thereof, this material is made up of four layers of different materials, be respectively nickel coating, molybdenum foam,
Metal molybdenum pipe and MoSi2Coating.They are be combined with each other by interatomic force, form a kind of tubular structure.Nickel coating is positioned at
The outermost layer of tubular structure, is attached to molybdenum foam surface, and thickness is 1mm.Molybdenum foam constitutes the master of tubular structure with molybdenum pipe
Body, thickness is respectively 3mm and 0.2mm.MoSi2Coating is positioned at the inner surface of molybdenum pipe, is the innermost layer of tubular structure,
Thickness is 0.2mm.
Embodiment 2
A kind of molybdenio multilamellar heat insulation material and structure thereof, this material is made up of four layers of different materials, be respectively nickel coating, molybdenum foam,
Metal molybdenum pipe and MoSi2Coating.They are be combined with each other by interatomic force, form a kind of tubular structure.Nickel coating is positioned at
The outermost layer of tubular structure, is attached to molybdenum foam surface, and thickness is 3mm.Molybdenum foam constitutes the master of tubular structure with molybdenum pipe
Body, thickness is respectively 5mm and 0.5mm.MoSi2Coating is positioned at the inner surface of molybdenum pipe, is the innermost layer of tubular structure,
Thickness is 0.3mm.
Above are only two detailed description of the invention of the present invention, but the design concept of the present invention is not limited thereto, all utilize this to conceive
The present invention is carried out the change of unsubstantiality, the behavior invading the scope of protection of the invention all should be belonged to.In every case it is without departing from this
The content of bright technical scheme, any type of simple modification above example made according to the technical spirit of the present invention, equivalent
Change and remodeling, still fall within the protection domain of technical solution of the present invention.
Claims (1)
1. a molybdenio multilamellar heat insulation material, is a kind of tubular structure, it is characterised in that this material is made up of four layers of different materials,
Be the most successively thickness be 0.5～3mm nickel coating, thickness be 1～5mm molybdenum froth bed, thickness be 0.1～0.5mm
Metal molybdenum layer and MoSi that thickness is 0.1mm～0.5mm2Coating.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310412088.3A CN103722789B (en) | 2013-09-11 | 2013-09-11 | A kind of molybdenio multilamellar heat insulation material and structure thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310412088.3A CN103722789B (en) | 2013-09-11 | 2013-09-11 | A kind of molybdenio multilamellar heat insulation material and structure thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103722789A CN103722789A (en) | 2014-04-16 |
| CN103722789B true CN103722789B (en) | 2016-08-10 |
Family
ID=50447203
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310412088.3A Active CN103722789B (en) | 2013-09-11 | 2013-09-11 | A kind of molybdenio multilamellar heat insulation material and structure thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103722789B (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1757787A (en) * | 2005-08-02 | 2006-04-12 | 哈尔滨工业大学 | Preparation method of intermetallic compound/metal multilayer plate |
| CN101117718A (en) * | 2007-09-12 | 2008-02-06 | 河北理工大学 | Fire-resistant oxidation resistant material and preparation method thereof |
| CN101200801A (en) * | 2007-12-18 | 2008-06-18 | 中南大学 | Niobic alloy high temperature antioxidation silicide coating and preparation method thereof |
| CN101660079A (en) * | 2009-10-14 | 2010-03-03 | 北京师范大学 | Macro mesh structural porous foamed molybdenum and preparation method thereof |
| CN102851635A (en) * | 2012-09-20 | 2013-01-02 | 河北联合大学 | Mo-C-N-Si-Nb gradient coating material and preparation method thereof |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6306515B1 (en) * | 1998-08-12 | 2001-10-23 | Siemens Westinghouse Power Corporation | Thermal barrier and overlay coating systems comprising composite metal/metal oxide bond coating layers |
-
2013
- 2013-09-11 CN CN201310412088.3A patent/CN103722789B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1757787A (en) * | 2005-08-02 | 2006-04-12 | 哈尔滨工业大学 | Preparation method of intermetallic compound/metal multilayer plate |
| CN101117718A (en) * | 2007-09-12 | 2008-02-06 | 河北理工大学 | Fire-resistant oxidation resistant material and preparation method thereof |
| CN101200801A (en) * | 2007-12-18 | 2008-06-18 | 中南大学 | Niobic alloy high temperature antioxidation silicide coating and preparation method thereof |
| CN101660079A (en) * | 2009-10-14 | 2010-03-03 | 北京师范大学 | Macro mesh structural porous foamed molybdenum and preparation method thereof |
| CN102851635A (en) * | 2012-09-20 | 2013-01-02 | 河北联合大学 | Mo-C-N-Si-Nb gradient coating material and preparation method thereof |
Non-Patent Citations (1)
| Title |
|---|
| 泡沫钼材料的吸能特性研究;孙悦等;《四川大学学报（工程科学版）》;20020131;第34卷(第1期);第124～126页 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103722789A (en) | 2014-04-16 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Spriet | CMC applications to gas turbines | |
| CN111878238A (en) | Double-layer cooling channel for reducing temperature of aircraft component | |
| Brown | Conceptual investigations for a methane-fueled expander rocket engine | |
| Herbertz et al. | Transpiration Cooled Ceramic Thrust Chamber Applicability for High-Thrust Rocket Engines | |
| Sengupta et al. | Advanced high-temperature structural materials in petrochemical, metallurgical, power, and aerospace sectors—An overview | |
| CN103722789B (en) | A kind of molybdenio multilamellar heat insulation material and structure thereof | |
| Shelley et al. | Metal-matrix composites for liquid rocket engines | |
| Purwar et al. | Design of thermal barrier coating system for scramjet using coupled thermo-structural analysis | |
| Preclik et al. | LOX/hydrocarbon propellant trade considerations for future reusable liquid booster engines | |
| Henderson et al. | Performance results for the advanced materials bipropellant rocket (ambr) engine | |
| Boyanapalli et al. | Analysis of composite De-Laval nozzle suitable for rocket applications | |
| Götz et al. | Application of non-toxic propellants for future launch vehicles | |
| CN103722806B (en) | The preparation method of a kind of molybdenum Quito layer heat insulation material | |
| Beyer et al. | Technology status of fuel cooled ceramic matrix composites for dual-mode ramjet (DMR) and liquid rocket engine (LRE) applications | |
| Valentine et al. | Extreme-temperature carbon-and ceramic-matrix composite nozzle extensions for liquid rocket engines | |
| Tomita et al. | A conceptual system design study for a linear aerospike engine applied to a future SSTO vehicle | |
| Henson et al. | Applications of Ceramic Matrix Composites in Liquid Rocket Propulsion | |
| Sverdrup et al. | A system dynamics assessment of the supply of superalloys using WORLD6; Sufficiency for civilian and military aviation needs | |
| Koc | The use of liquefied petroleum gas (lpg) and natural gas in gas turbine jet engines | |
| Kim et al. | Effects of temperature on the coking characteristics of kerosene | |
| Ha et al. | Development Trend of Liquid Hydrogen-Fueled Rocket Engines (Part 2: Core Technologies) | |
| CN103722782B (en) | A kind of ceramic matrix hybrid composite material and structure thereof | |
| Brockmeyer | Ceramic matrix composite applications in advanced liquid fuel rocket engine turbomachinery | |
| Liu et al. | Optimization selection of regulated pressurization system schemes for liquid attitude and divert propulsion systems | |
| Behrendt et al. | Development and test of oxide/oxide cmc combustor liner demonstrators for aero engines |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP02 | Change in the address of a patent holder | ||
| CP02 | Change in the address of a patent holder |
Address after: 215400 Chengxiang City, Taicang Province town of the People South Road, No. 162, No. Patentee after: TAICANG PAIOU TECHNOLOGY CONSULTATION SERVICE CO., LTD. Address before: 215400 people's road, Jiangsu, Taicang Hua Xu apartment C412 Patentee before: TAICANG PAIOU TECHNOLOGY CONSULTATION SERVICE CO., LTD. |