CN104691038A - Structure of thermal protection coating used for steel structure surface and application thereof - Google Patents
Structure of thermal protection coating used for steel structure surface and application thereof Download PDFInfo
- Publication number
- CN104691038A CN104691038A CN201310661722.7A CN201310661722A CN104691038A CN 104691038 A CN104691038 A CN 104691038A CN 201310661722 A CN201310661722 A CN 201310661722A CN 104691038 A CN104691038 A CN 104691038A
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- thermal protection
- protection coating
- curing agent
- organic underlayer
- thickness
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- 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
- B32B9/00—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00
- B32B9/04—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00 comprising such particular substance as the main or only constituent of a layer, which is next to another layer of the same or of a different material
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- 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
- B32B27/00—Layered products comprising a layer of synthetic resin
-
- 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
- B32B2307/304—Insulating
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- 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
Abstract
The invention discloses a structure of a thermal protection coating material used for a steel structure surface and application thereof. The thermal protection coating material comprises an organic bottom layer material, refractory bricks and an inorganic surface layer material, wherein the organic bottom layer comprises epoxy resin, a curing agent polyamide and a toughening agent liquid rubber; clayey refractory bricks are selected; the inorganic surface layer comprises sodium silicate, a curing agent sodium fluosilicate, sand, cement and a refractory aggregate. The thermal protection coating material can bear scouring of a gas flow simulated by a rocket and ensures that the metal back temperature does not exceed 150 DEG C, and a coating has good thermal insulation property.
Description
Technical field
The present invention relates to a kind of thermal protection coating structure of steel structure surface; especially relate to a kind of for the reduction transmitting station back of the body temperature of rocket launching pad surface coating, the thermal protection coating structure of protection rocket launching pad steel structure surface and application thereof, belong to high temperature resistant adiabatic protection field.
Background technology
Along with the development of space flight, aerospace cause, thermal protection coating has opened up new application.Except the thermal protection of aircraft itself, domestic to ground installation as rocket launching pad too increases thermal protection measure.If transmitting station is coated with thermal protection coating, metal surface can be made heat insulation, reduce thermal ablation and thermal shock, and prevent transmitting station under the effect of repeatedly thermal shock load, producing heat fatigue, heat cracks and thermal destruction, thus guarantee the reliability of transmitting station work, extend the service life of transmitting station.Abroad, the Ariane rocket flat pad that European Space Agency is positioned at Guyana, South America is concrete flat pad, it is better than organic ablation surface that ablation property is swept in this kind of transmitting station fire-resistant air-blowing of being constructed by Inorganic Non-metallic Materials, but it is thick that shortcoming is thickness, Heavy Weight, and transmitting station cannot move.
Utilize special thermal protection coating materials and structures can carry out thermal protection to rocket launching pad, but at present, yet there are no relevant report about carrying out thermo-lag technology to transmitting station.
Summary of the invention
Technical problem to be solved by this invention increases thermal protection measure to ground installation rocket launching pad, and provide one can bear rocket wake flame and purge, back of the body temperature is no more than the structure of the thermal protection coating of 150 DEG C.
Technical problem to be solved by this invention is achieved through the following technical solutions:
Thermal protection coating structure of the present invention, is made up of trilaminate material, and bottom is organic material, and intermediate layer is clay refractory brick, and top layer is inorganic material.
Bottom is made up of organic material, epoxy resin (mass ratio, lower same) 65 ~ 80%, curing agent polyamide 10 ~ 20%, flexibilizer liquid rubber 5 ~ 20%.The thickness of primer is 2 ~ 6mm.
Intermediate layer is made up of clay refractory brick, and its refractoriness can reach 1730 DEG C, Al
2o
3content > 40%.
Top layer is made up of inorganic material, waterglass 20 ~ 40%, curing agent prodan 2 ~ 10%, filler sand 15 ~ 30%, filler cement 5 ~ 15%, refractory aggregate 20 ~ 40%.The thickness of skin-material is 6 ~ 14mm.
Thermal protection coating organic underlayer of the present invention, intermediate layer and inorganic top layer gross thickness are 12 ~ 35mm.
Raw material used by the present invention can be bought from market and obtain, and its specification meets professional standard.Cement: model is 425 portland cements, and manufacturer is Zhengzhou Dengfeng Smelting Materials Co., Ltd..Epoxy resin: model is SM828, curing agent polyamide: model is 650, manufacturer is the bright Chemical Co., Ltd. in Wuxi.Flexibilizer liquid rubber: model is number-average molecular weight 4000, manufacturer is Jinzhou Dalian Sheng Da product of rubber and plastic Co., Ltd.Waterglass: modulus is 3, manufacturer is Jing Hua chemical plant, Jiashan of Zhejiang county.Refractory aggregate: particle diameter is 3-5mm, manufacturer is Dalian Xing Gang kiln material factory.Refractory brick: model is (NZ)-2, and manufacturer is Zhonggang Group Refractory Material Co., Ltd..
Thermal protection coating material of the present invention can bear rocket simulation gas-flow and wash away, and metal backing surface temperature is no more than 150 DEG C, and coating has good heat-proof quality.
When the present invention applies, organic underlayer, intermediate layer and inorganic top layer are coated on rocket launching pad successively, because skin-material of the present invention has mobility, are therefore specially adapted to the planar structure of rocket launching pad.When rocket launching is gone up to the air, coating is subject to the high temperature of gas-flow and washing away at a high speed, and the skin-material of coating is owing to being inorganic refractory materials, and this inorganic material can resistance to ablation and resistance to erosion, therefore serves heat-blocking action.
As can be seen here, will greatly reduce thermal ablation and the thermal shock of metallic matrix through the present invention, the back of the body temperature of metal will reduce greatly, thus effectively plays thermal protection effect to rocket launching pad.
Accompanying drawing explanation
The back temperature of Fig. 1: 15mm coating sample and the relation curve of ablation time;
The back temperature of Fig. 2: 30mm coating sample and the relation curve of ablation time.
Detailed description of the invention
Further describe the present invention below in conjunction with specific embodiments and the drawings, advantage and disadvantage of the present invention will be more clear along with description.
The preparation of embodiment 1 thermal protection coating structure
1. the preparation of organic underlayer: by epoxy resin SM828, curing agent polyamide 6 50, flexibilizer liquid rubber according to after the mixing of 7:2:1 mass ratio, be coated in the steel plate side of 190 × 120 × 5mm after rust cleaning on the surface, coating thickness is 2mm.
2. the preparation in intermediate layer: be that the clay refractory brick (NZ)-2 of 5mm is pasted onto on organic underlayer by thickness.
3. the preparation on inorganic top layer: first filler sand and cement are mixed according to the mass ratio of 2:1, add in waterglass (M=3) and the mixed liquor of curing agent prodan according to 10:1 mass ratio again together with refractory aggregate, filler sand and cement: refractory aggregate: waterglass (containing curing agent) mass ratio=1:1:1.Be coated in by skin-material on refractory brick, coating thickness is 8mm, and preparation gross thickness is the thermal protection coating of 15mm.
The thermal protection effect heat insulation to thermal protection coating on metal foil is tested:
Adopt YA6804 type oxygen kerosene engine sample to be carried out to the test of testpieces back temperature, sample is that metal foil side scribbles thermal protection coating, and the metal covering without coating is the back side.Experimental condition: engine combustion chamber pressure: Pc=1.4 ± 0.05MPa; Engine excess oxidizer coefficient: α=0.7 ± 0.03; Engine nozzle diameter: 65mm; The ablation test time: 5s/ part.Wake flame when experimental condition is rocket launching analog purges situation, and flame purges the metal foil scribbling thermal protection coating side.The back temperature of test metal foil.The back temperature of 15mm thick coating and the relation of ablation time are as shown in Figure 1.As can be seen from the figure, the back of the body Wen Wei of the sample of 15mm thick coating is applied more than 100 DEG C.Result of the test shows, coating material of the present invention and structure have good heat-proof quality, and protects steel plate ground.
The preparation of embodiment 2 thermal protection coating structure
1. the preparation of organic underlayer: by epoxy resin SM828, curing agent polyamide 6 50, flexibilizer liquid rubber according to after the mixing of 7:2:1 mass ratio, be coated in the steel plate side of 190 × 120 × 5mm after rust cleaning on the surface, coating thickness is 4mm.
2. the preparation in intermediate layer: be that the clay refractory brick (NZ)-2 of 15mm is pasted onto on organic underlayer by thickness.
3. the preparation on inorganic top layer: first filler sand and cement are mixed according to the mass ratio of 2:1, add in waterglass (M=3) and the mixed liquor of curing agent prodan according to 10:1 mass ratio again together with refractory aggregate, filler sand and cement: refractory aggregate: waterglass (containing curing agent) mass ratio=1:1:1.Be coated in by skin-material on refractory brick, coating thickness is 11mm, and preparation gross thickness is the thermal protection coating of 30mm.
The thermal protection effect heat insulation to thermal protection coating on metal foil is tested:
Adopt YA6804 type oxygen kerosene engine sample to be carried out to the test of testpieces back temperature, sample is that metal foil side scribbles thermal protection coating, and the metal covering without coating is the back side.Experimental condition: engine combustion chamber pressure: Pc=1.4 ± 0.05MPa; Engine excess oxidizer coefficient: α=0.7 ± 0.03; Engine nozzle diameter: 65mm; The ablation test time: 5s/ part.Wake flame when experimental condition is rocket launching analog purges situation, and flame purges the metal foil scribbling thermal protection coating side.The back temperature of test metal foil.The back temperature of 30mm thick coating and the relation of ablation time are as shown in Figure 2.As can be seen from the figure, the back of the body Wen Wei of the sample of 30mm thick coating is applied more than 100 DEG C.Result of the test shows, coating material of the present invention and structure have good heat-proof quality, and protects steel plate ground.
Claims (10)
1. a thermal protection coating, is characterized in that: be provided with organic underlayer, clay refractory brick layer and inorganic top layer trilaminate material composition successively in substrate surface.
2. according to thermal protection coating according to claim 1, it is characterized in that: count in mass ratio, organic underlayer is made up of epoxy resin 65 ~ 80%, curing agent polyamide 10 ~ 20%, flexibilizer liquid rubber 5 ~ 20%.
3. according to thermal protection coating according to claim 1, it is characterized in that: clay refractory brick refractoriness can reach 1730 DEG C, Al
2o
3content > 40%; The thickness of refractory brick is 5 ~ 15mm.
4. according to thermal protection coating according to claim 1, it is characterized in that: count in mass ratio, inorganic top layer is made up of waterglass, curing agent prodan, filler sand and cement, refractory aggregate, wherein, waterglass 20 ~ 40%, curing agent prodan 2 ~ 10%, filler sand 15 ~ 30%, filler cement 5 ~ 15%, refractory aggregate 20 ~ 40%.
5. according to the thermal protection coating described in claim 1 or 2, it is characterized in that: organic underlayer thickness is 2 ~ 6mm.
6. according to the thermal protection coating described in claim 1 or 4, it is characterized in that: the thickness of inorganic skin-material is 6 ~ 14mm.
7. according to thermal protection coating structure according to claim 1, it is characterized in that: thermal protection coating organic underlayer, clay refractory brick layer and inorganic top layer gross thickness are 12 ~ 35mm.
8. according to thermal protection coating structure according to claim 1, it is characterized in that: described substrate is metal steel structure substrate.
9. according to thermal protection coating structure according to claim 4, it is characterized in that: described sand was component under the sieve after 35 mesh sieves.
10. the thermal protection coating of claim 1-9 described in any one is as a thermal protection coating on rocket launching pad outer surface, is provided with organic underlayer, fire brick layer, inorganic top layer successively in transmitting station outer surface.
Priority Applications (1)
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| CN201310661722.7A CN104691038B (en) | 2013-12-06 | 2013-12-06 | Structure of thermal protection coating used for steel structure surface and application thereof |
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| CN104691038A true CN104691038A (en) | 2015-06-10 |
| CN104691038B CN104691038B (en) | 2017-01-11 |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106808768A (en) * | 2015-12-01 | 2017-06-09 | 周依宁 | A kind of fire resisting packaging material |
| CN106808772A (en) * | 2015-12-01 | 2017-06-09 | 周依宁 | A kind of wear-resisting, waterproof barrier material |
| CN106808769A (en) * | 2015-12-01 | 2017-06-09 | 周依宁 | A kind of wear-resisting packaging material |
| CN107081940A (en) * | 2016-02-16 | 2017-08-22 | 中国科学院大连化学物理研究所 | A kind of structure of ship deck thermal protection coating and its application |
| CN107081941A (en) * | 2016-02-16 | 2017-08-22 | 中国科学院大连化学物理研究所 | Structure and its application of a kind of metal surface with thermal protection coating material |
| CN107081939A (en) * | 2016-02-16 | 2017-08-22 | 中国科学院大连化学物理研究所 | A kind of rocket launching pad high-temperature resistant coating structure and its application |
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| US7648605B2 (en) * | 2007-05-17 | 2010-01-19 | Siemens Energy, Inc. | Process for applying a thermal barrier coating to a ceramic matrix composite |
| CN102180639A (en) * | 2011-02-24 | 2011-09-14 | 卢清友 | Environment-friendly light heat-insulating material and manufacturing method thereof |
| CN203004461U (en) * | 2012-12-04 | 2013-06-19 | 中国科学院大连化学物理研究所 | Thermal protection coating structure for transmitting platform |
| CN203255972U (en) * | 2013-04-18 | 2013-10-30 | 河北海丽特种石墨制造有限公司 | Annular roasting oven |
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Patent Citations (4)
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|---|---|---|---|---|
| US7648605B2 (en) * | 2007-05-17 | 2010-01-19 | Siemens Energy, Inc. | Process for applying a thermal barrier coating to a ceramic matrix composite |
| CN102180639A (en) * | 2011-02-24 | 2011-09-14 | 卢清友 | Environment-friendly light heat-insulating material and manufacturing method thereof |
| CN203004461U (en) * | 2012-12-04 | 2013-06-19 | 中国科学院大连化学物理研究所 | Thermal protection coating structure for transmitting platform |
| CN203255972U (en) * | 2013-04-18 | 2013-10-30 | 河北海丽特种石墨制造有限公司 | Annular roasting oven |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106808768A (en) * | 2015-12-01 | 2017-06-09 | 周依宁 | A kind of fire resisting packaging material |
| CN106808772A (en) * | 2015-12-01 | 2017-06-09 | 周依宁 | A kind of wear-resisting, waterproof barrier material |
| CN106808769A (en) * | 2015-12-01 | 2017-06-09 | 周依宁 | A kind of wear-resisting packaging material |
| CN107081940A (en) * | 2016-02-16 | 2017-08-22 | 中国科学院大连化学物理研究所 | A kind of structure of ship deck thermal protection coating and its application |
| CN107081941A (en) * | 2016-02-16 | 2017-08-22 | 中国科学院大连化学物理研究所 | Structure and its application of a kind of metal surface with thermal protection coating material |
| CN107081939A (en) * | 2016-02-16 | 2017-08-22 | 中国科学院大连化学物理研究所 | A kind of rocket launching pad high-temperature resistant coating structure and its application |
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| CN104691038B (en) | 2017-01-11 |
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