CN103722789A - Multilayer molybdenum-based heat-proof material and structure thereof - Google Patents
Multilayer molybdenum-based heat-proof material and structure thereof Download PDFInfo
- Publication number
- CN103722789A CN103722789A CN201310412088.3A CN201310412088A CN103722789A CN 103722789 A CN103722789 A CN 103722789A CN 201310412088 A CN201310412088 A CN 201310412088A CN 103722789 A CN103722789 A CN 103722789A
- Authority
- CN
- China
- Prior art keywords
- molybdenum
- coating
- layer
- tubular structure
- 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.)
- Granted
Links
Images
Landscapes
- Laminated Bodies (AREA)
- Other Surface Treatments For Metallic Materials (AREA)
Abstract
The invention discloses a multilayer molybdenum-based heat-proof material and a structure thereof. The material adopts a multilayer structure and sequentially comprises a nickel coating with a thickness ranging from 0.5 mm to 3 mm, a molybdenum foam layer with a thickness ranging from 1 mm to 5 mm, a metal molybdenum layer with a thickness ranging from 0.1 mm to 0.5 mm and a MoSi2 coating with a thickness ranging from 0.1 mm to 0.5 mm from outside to inside. The nickel coating, the molybdenum foam layer, the metal molybdenum layer and the MoSi2 coating are mutually bonded through acting force among atoms to form a tubular structure. The material can stably work in the high temperature environment, can resist oxidation and corrosion and can be used as a strictly required high-temperature structural part such as an aerospace vehicle spray pipe and the like.
Description
Technical field
The present invention relates to a kind of heat insulation material and structure thereof, particularly relate to a kind of molybdenum Quito layer heat insulation material and structure thereof.
Background technology
Jet pipe is the important component part of engine, and it is in high-temperature high-pressure air flow environment.Owing to being subject to the restriction of total arrangement, cube little, lightweight, intensity is high, high temperature resistant.Therefore it can not use high-strength alloy steel making completely, but combined by multiple material.Conventional jet pipe material has Nb alloy, C/C composite etc. at present.
C-103 (Nb-10Hf-1Ti-0.5Zr) and two kinds of Nb alloys of Nb521 (Nb-5W-2Mo-1Zr) are critical materials that Liquid Rocket Engine Combustion Chambers body portion and thrust chamber, jet pipe extension are used.Its serviceability temperature of C-103 alloy, between 1200-1400 ℃, is the common used material of current China liquid-propellant rocket engine, 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/cm
3, a little less than C-103 alloy (8.9kg/cm
3), serviceability temperature is between 1400-1650 ℃, can meet rail, attitude control engine that KKV (KKV) and corresponding guided missile delivery system are used, 300N, 200N, 25N niobium alloy jet pipe and following New Type Military satellite, spacelab requirement to material with attitude control engine as Df-31A, No. JL-2 three grades of attitude control engines use, be designed to the multiple chamber structure parts such as 490N, 150N.But with respect to ceramic and other composite material, large quality and the high price of alloy jet pipe have limited its range of application to a certain extent.
Song Yun etc. have introduced the application of carbon/carbon compound material in the propulsion systems such as solid engines, liquid engine and turbojet in document " application of carbon/carbon compound material in propulsion system ".Cosmic space variations in temperature is violent, requires heat-resisting, the resistance to low and dimensionally stable of material, to cosmic space transmitting object, needs great thrust, and alleviating of weight will bring great benefit.The performance of C/C uniqueness makes it in aerospace system, have promising future, but is also subject to the restriction of manufacture method and means of testing at present.
Liquid propellant engine also can be referred to as liquid-propellant rocket engine or liquid engine.It is different from the maximum of solid propellant rocket be exactly propellant used be liquid condition.Liquid engine is generally comprised of thrust chamber, turbine pump, gas generator or precombustion chamber, valve and automation.Current liquid engine chamber pressure is all at 30 more than atmospheric pressure, and during liquid propellant burning temperature up to 3830 ℃.C/C discharge duct is so easily being oxidized under high temperature, and carbonaceous surface is easy to corrosion, and the C/C of coating only can not used in a short time.Although coating C/C has larger attraction, their price can not be compared with traditional material conventionally.
Summary of the invention
The present invention, mainly for the thermal structure pipe fitting of burner, proposes a kind of molybdenum Quito layer heat insulation material and structure thereof.This material is comprised of four layers of different materials, is nickel coating, molybdenum froth bed, metal molybdenum layer and MoSi from outside to inside successively
2coating.They mutually combine by active force between atom, form a kind of tubular structure, can be at steady operation under hot environment, and anti-oxidant, anticorrosion, can be used as and require the harsh high temperature structural members such as aerospace vehicle jet pipe.
Described molybdenum foam and metal molybdenum layer form the main body of tubular structure, are the intermediate layers of structure, and molybdenum foam is positioned at the outer surface of molybdenum pipe, and 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 good anti-oxidant and decay resistance.Described MoSi
2coating is positioned at the inner surface of molybdenum pipe, is the innermost layer of tubular structure, and thickness is 0.1mm～0.5mm, has very high intensity, hardness and high-temperature stability, and excellent anti-oxidant, abrasion resistance properties.
Major advantage of the present invention is: 1. this exothermic material has sandwich construction, and quality is light, and intensity is high, has excellent high-temperature behavior, can anti-oxidant and anticorrosion; 2. this material comprises multiple refractory metal and coating, keeps stable duty under hot environment; 3. this tubular structure inside is foamed material, can fill the materials such as cooling, phase transformation, realizes the temperature with high efficiency of thermal structure; 4. this tubular structure surface attachment has anti-oxidant, erosion shield, has long service life, the advantage of good stability.
Accompanying drawing explanation
Be illustrated as the schematic diagram of the anti-heat pipe of a kind of molybdenum Quito layer.
Diagram 10 is nickel coating; 20 is molybdenum foam; 30 is molybdenum pipe; 40 is MoSi
2coating.
The specific embodiment
Below in conjunction with specific embodiment, further illustrate the present invention, should understand these embodiment is only not used in and limits the scope of the invention for the present invention is described, after having read the present invention, those skilled in the art all fall within the application's claims to the modification of the various equivalent form of values of the present invention and limit.
Embodiment 1
Molybdenum Quito layer heat insulation material and a structure thereof, this material is comprised of four layers of different materials, is respectively nickel coating, molybdenum foam, metal molybdenum pipe and MoSi
2coating.They mutually combine by active force between atom, 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 and molybdenum pipe form the main body of tubular structure, and thickness is respectively 3mm and 0.2mm.MoSi
2coating is positioned at the inner surface of molybdenum pipe, is the innermost layer of tubular structure, and thickness is 0.2mm.
Embodiment 2
Molybdenum Quito layer heat insulation material and a structure thereof, this material is comprised of four layers of different materials, is respectively nickel coating, molybdenum foam, metal molybdenum pipe and MoSi
2coating.They mutually combine by active force between atom, 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 and molybdenum pipe form the main body of tubular structure, and thickness is respectively 5mm and 0.5mm.MoSi
2coating is positioned at the inner surface of molybdenum pipe, is the innermost layer of tubular structure, and thickness is 0.3mm.
Above are only two specific embodiment of the present invention, but design concept of the present invention is not limited to this, allly utilizes this design to carry out the change of unsubstantiality to the present invention, all should belong to the behavior of invading the scope of protection of the invention.In every case be the content that does not depart from technical solution of the present invention, any type of simple modification, equivalent variations and the remodeling above embodiment done according to technical spirit of the present invention, still belong to the protection domain of technical solution of the present invention.
Claims (9)
1. molybdenum Quito layer heat insulation material, is characterized in that by nickel coating, molybdenum froth bed, metal molybdenum layer and MoSi
2coating forms.
2. heat insulation material according to claim 1, is characterized in that the thickness of described nickel coating is 0.5～3mm.
3. heat insulation material according to claim 1, is characterized in that the thickness of described molybdenum froth bed is 1～5mm.
4. heat insulation material according to claim 1, is characterized in that the thickness of described metal molybdenum layer is 0.1～0.5mm.
5. heat insulation material according to claim 1, is characterized in that described MoSi
2the thickness of coating is 0.1～0.5mm.
6. molybdenum Quito layer thermal protection struc ture, is characterized in that being followed successively by from outside to inside nickel coating, molybdenum froth bed, metal molybdenum layer and MoSi
2coating, combines by active force between atom between layers, forms a kind of tubular structure.
7. thermal protection struc ture according to claim 6, is characterized in that described nickel coating is positioned at the outermost layer of tubular structure, is attached to the surface of molybdenum foam.
8. thermal protection struc ture according to claim 6, is characterized in that described molybdenum froth bed and metal molybdenum layer form the main body of tubular structure, is the intermediate layer of structure.
9. thermal protection struc ture according to claim 6, is characterized in that described MoSi
2coating is positioned at the inner surface of molybdenum pipe, forms the innermost layer of tubular structure.
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 true CN103722789A (en) | 2014-04-16 |
| CN103722789B 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 (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2000094574A (en) * | 1998-08-12 | 2000-04-04 | Siemens Westinghouse Power Corp | Multi-layer heat insulation coating system and method for forming the same |
| 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 |
-
2013
- 2013-09-11 CN CN201310412088.3A patent/CN103722789B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2000094574A (en) * | 1998-08-12 | 2000-04-04 | Siemens Westinghouse Power Corp | Multi-layer heat insulation coating system and method for forming the same |
| 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 |
|---|
| 孙悦等: "泡沫钼材料的吸能特性研究", 《四川大学学报（工程科学版）》 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103722789B (en) | 2016-08-10 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Padture | Advanced structural ceramics in aerospace propulsion | |
| US8127555B2 (en) | Flowpath heat exchanger for thermal management and power generation within a hypersonic vehicle | |
| Spriet | CMC applications to gas turbines | |
| EP2233727B1 (en) | Fuel-cooled flexible heat exchanger with thermoelectric device compression | |
| WO2010042095A2 (en) | Systems, methods and apparatus for propulsion | |
| CN111878238A (en) | Double-layer cooling channel for reducing temperature of aircraft component | |
| US9222438B2 (en) | Rocket engine with cryogenic propellants | |
| CN104948302A (en) | Fuel supply system of aircraft engine taking LNG (Liquefied Natural Gas) as fuel and working mode thereof | |
| Herbertz et al. | Transpiration Cooled Ceramic Thrust Chamber Applicability for High-Thrust Rocket Engines | |
| Ha et al. | Development trend of liquid hydrogen-fueled rocket engines (part 1: performance and operation) | |
| Wagner et al. | Advanced regenerative-cooling techniques for future space transportation systems | |
| Shelley et al. | Metal-matrix composites for liquid rocket engines | |
| CN103722789A (en) | Multilayer molybdenum-based heat-proof material and structure thereof | |
| CN103722806B (en) | The preparation method of a kind of molybdenum Quito layer heat insulation material | |
| Boyanapalli et al. | Analysis of composite De-Laval nozzle suitable for rocket applications | |
| RU2686815C1 (en) | Nuclear turbojet | |
| Zhang | Research on Ceramic Matrix Composites (CMC) for Aerospace Aplications | |
| Lacombe | 3D Novoltex and Naxeco Caron-Carbon Nozzle Extensions; matured, industrial and available technologies to reduce programmatic and technical risks and to increase performance of launcher upper stage engines | |
| Lacombe et al. | 3D carbon-carbon composites are revolutionizing upper stage liquid rocket engine performance by allowing introduction of large nozzle extension | |
| CN103722782B (en) | A kind of ceramic matrix hybrid composite material and structure thereof | |
| RU160797U1 (en) | TURBINE HOUSING OF A TURBO PUMP UNIT OF A LIQUID ROCKET ENGINE | |
| Kozlov et al. | Development liquid rocket engine of small thrust with combustion chamber from carbon-ceramic composite material | |
| 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 | |
| Ha et al. | Development Trend of Liquid Hydrogen-Fueled Rocket Engines (Part 2: Core Technologies) |
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 |
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. |
|
| CP02 | Change in the address of a patent holder |