CN115138842A - Preparation method of high-temperature-oxidation-resistant high-temperature air direct-ignition combustion stabilizer shell - Google Patents
Preparation method of high-temperature-oxidation-resistant high-temperature air direct-ignition combustion stabilizer shell Download PDFInfo
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Abstract
The invention discloses a preparation method of a high-temperature oxidation resistant high-temperature air direct ignition combustion stabilizer shell, which mainly comprises the following steps: preparing a composite material shell blank by twice cold isostatic pressing; placing the composite material shell blank in a hydrogen furnace, heating to 1400-2000 ℃, and preserving heat for 12-72 hours to obtain a sintered composite material shell; machining, cleaning, drying and sandblasting the sintered composite material shell; respectively coating paint on the inner surface and the outer surface of the sintered composite material shell by adopting a normal-temperature gas atomization coating method to prepare ceramic protective layers, then sintering at high temperature, slowly cooling to room temperature and taking out to obtain the high-temperature air direct-ignition combustion stabilizer shell resistant to high-temperature oxidation. The flame stabilizer shell prepared by the preparation method has good high-temperature oxidation resistance.
Description
Technical Field
The invention relates to the technical field of molybdenum materials, in particular to a preparation method of a high-temperature-oxidation-resistant high-temperature air direct-ignition combustion stabilizer shell.
Background
The refractory alloy has excellent mechanical and physical properties such as high-temperature strength, high-temperature hardness, good heat conductivity and electrical conductivity, low thermal expansion coefficient and the like, and is widely applied to the fields of metallurgy, machinery, energy, chemical industry, national defense, electronics and the like. Meanwhile, due to its good high temperature resistance, it is also widely used in high temperature furnaces and vacuum furnaces in the form of heating furnace chambers.
The temperature of an inner cavity of the high-temperature air direct-ignition combustion stabilizer can reach about 1600 ℃ instantly when the high-temperature air direct-ignition combustion stabilizer works, the tolerance temperature of high-temperature steel and special steel which are commonly used in the current domestic and foreign markets is about 1200 ℃, and the basic requirement of the high-temperature air direct-ignition combustion stabilizer is far from being met. Therefore, it is necessary to use refractory metals and their alloys as the casing of the high temperature air direct ignition burner. However, refractory metals and their alloys are easily reacted with oxygen in an aerobic environment at temperatures higher than 400 ℃, and thus, the problems of material loss, reduced thermodynamic properties, etc. are likely to occur.
Therefore, how to solve the problems of service performance and service life of refractory metals and refractory metal alloys in an aerobic environment becomes a breakthrough point for solving the development and application of a high-temperature air direct-ignition combustion stabilizer.
Disclosure of Invention
In order to overcome the defects in the prior art, the invention provides a preparation method of a high-temperature air direct-ignition combustion stabilizer shell with high-temperature oxidation resistance.
In order to achieve the purpose, the invention adopts the specific scheme that:
a preparation method of a high-temperature oxidation resistant high-temperature air direct ignition combustion stabilizer shell mainly comprises the following steps:
(1) The alloy powder is pressed into an alloy shell blank through cold isostatic pressing;
(2) Turning the alloy shell blank obtained in the step (1) to obtain an alloy shell blank, wherein the shape of the alloy shell blank is basically consistent with that of a finished shell, and a corresponding allowance is reserved in the aspect of size;
(3) According to the weight percentage, 40 to 80 percent of Mo powder, 10 to 40 percent of Si powder, 5 to 20 percent of Hf powder and 1 to 5 percent of CeO powder are taken 2 Powder and 1% -5% of La 2 O 3 Mixing the powders to obtain mixed powder;
(4) Placing the alloy shell blank obtained in the step (2) in a rubber mould with a mandrel, ensuring that gaps of 5-40mm are reserved between the inner surface of the alloy shell blank and the outer surface of the mandrel and between the outer surface of the alloy shell blank and the inner wall of the rubber mould, uniformly pouring the mixed powder prepared in the step (3) into the gaps, and then placing the rubber mould in a cold isostatic press for cold isostatic pressing to obtain a composite material shell blank;
(5) Placing the composite material shell blank in a hydrogen furnace, heating to 1400-2000 ℃, and preserving heat for 12-72 hours to obtain a sintered composite material shell;
(6) Machining, cleaning, drying and sand blasting the sintered composite material shell;
(7) Respectively coating the inner surface and the outer surface of the sintered composite material shell treated in the step (6) with paint by adopting a normal-temperature gas atomization coating method to prepare ceramic protective layers to obtain a prefabricated combustion stabilizer shell;
(8) And sintering the prefabricated flame stabilizer shell at a high temperature by using a vacuum furnace, slowly cooling to room temperature, and taking out to obtain the flame stabilizer shell resistant to high-temperature oxidation.
Further, in the step (1), the alloy powder has any one of the following components:
the first method comprises the following steps: a refractory metal powder;
and the second method comprises the following steps: an alloy powder composed of at least two refractory metals;
and the third is that: multi-component alloy powders composed of one or more refractory metals with other metallic and/or non-metallic elements;
and fourthly: multi-component alloy powders composed of one or more refractory metals and other metal or metalloid oxides.
Further, in the step (1), the alloy powder has a Fisher-size of 4 μm or more and a specific surface area of 0.2 to 0.3m 2 /g。
Further, in the step (1), the pressure during cold isostatic pressing is 160-200Mpa, and the pressure maintaining time is 5-30 min.
Further, in the step (3), mo powder, si powder, hf powder, ceO powder are used 2 Powder and La 2 O 3 The purity of the powder is not less than 99.95 percent, and the granularity is 3.5-4.2um.
Further, in the step (4), the pressure of the cold isostatic pressing is 160-180Mpa, and the pressure maintaining time is 5-30 min.
Further, in the step (4), the alloy shell blank, the core rod and the rubber die should keep coaxiality higher than 0.03mm.
Further, in the step (7), the coating used for preparing the ceramic protective layer is a suspension of an oxide and a high-temperature binder, wherein the used oxide comprises the following components in percentage by weight: 20% -40% CrO 2 、10%-40% TiO 2 、1%-10% ReO 2 、10%-20% Si 3 N 4 、5%-10% SiC、0.1%-5% Lu 2 O 3 、0.1%-5% Yb 2 O 3 、0.1%-5% Tm 2 O 3 、0.1%-5% Y 2 O 3 、0.1%-5% Er 2 O 3 The high-temperature binder is hydroxyl or carboxyl.
Further, in the step (7), the coating material is applied in small quantities in multiple times, and the single application quantity is 25 um/time to 75 um/time.
Further, in the step (8), the parameters of the high-temperature sintering are as follows: heating to 1200-1700 ℃ at the heating rate of 10-40 ℃/min and keeping the temperature for 2-8 h.
Has the advantages that:
(1) According to the invention, the sintered composite material shell is prepared in a mode of cold isostatic pressing and hydrogen sintering twice, then the ceramic protective layers are prepared on the inner surface and the outer surface of the sintered composite material shell, and high-temperature sintering is carried out, so that the composite material shell with the protective layer with the standard thickness on the surface can be obtained, and the high-temperature oxidation resistant flame stabilizer shell is obtained, wherein the surface protective layer and the sintered composite material shell belong to metallurgical bonding, and the problems of coating falling, poor thermal shock resistance and the like in the preparation of the surface protective layer in the prior art are avoided.
(2) According to the invention, the inner surface and the outer surface of the composite material shell are coated by a gas atomization method, the aim is to close a pore path on the surface of the sintered composite material shell prepared by sintering through a powder metallurgy method, and a compact ceramic protection layer is formed after vacuum high-temperature sintering, so that the sintered composite material shell is effectively protected, and finally the high-temperature oxidation resistance and thermal shock loss resistance of the flame stabilizer shell are improved.
Drawings
Fig. 1 is a schematic structural diagram of the alloy case blank of the present invention after being pressed and formed in a rubber mold.
The graphic symbols are: 1. the method comprises the following steps of (1) a core rod, 2, a rubber mold, 3, a composite material shell blank, 31 and an alloy shell blank.
Detailed Description
The technical solutions of the present invention will be described clearly and completely with reference to specific embodiments, and it should be understood that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be obtained by a person skilled in the art without any inventive step based on the embodiments of the present invention, belong to the scope of the present invention.
A preparation method of a high-temperature air direct ignition combustion stabilizer shell resistant to high-temperature oxidation mainly comprises the following steps:
(1) The alloy powder is pressed into an alloy shell blank by cold isostatic pressing, the Fisher particle size of the selected alloy powder is more than 4 mu m, and the specific surface area is 0.2-0.3m 2 (ii) in terms of/g. The pressure during cold isostatic pressing is 160-200Mpa, and the pressure maintaining time is 5-30 min.
(2) Turning the alloy shell blank obtained in the step (1) to obtain an alloy shell blank, wherein the shape of the alloy shell blank is basically consistent with that of a finished shell, and a corresponding allowance is reserved in the aspect of size; it should be noted that the "corresponding allowance" herein includes the thickness of the mixed powder press molding, the subsequent sintering shrinkage allowance and the processing allowance;
(3) According to the weight percentage, 40 to 80 percent of Mo powder, 10 to 40 percent of Si powder, 5 to 20 percent of Hf powder and 1 to 5 percent of CeO powder are taken 2 Powder and 1% -5% of La 2 O 3 Mixing the powders to obtain mixed powder; wherein Mo powder, si powder, hf powder, ceO powder are used 2 Powder and La 2 O 3 The purity of the powder is not less than 99.95 percent, and the granularity is 3.5-4.2um;
(4) Placing the alloy shell blank obtained in the step (2) into a rubber mold with a core rod, ensuring that gaps of 5-40mm are reserved between the inner surface of the alloy shell blank and the outer surface of the core rod and between the outer surface of the alloy shell blank and the inner wall of the rubber mold, uniformly pouring the mixed powder prepared in the step (3) into the gaps, wherein the mixed powder needs to be uniformly spread, and shaping the mold after closing the rubber mold to ensure that no powder eccentricity exists in all parts; keeping the coaxiality of the powder shell, the core rod and the rubber mold to be higher than 0.03mm, and then placing the rubber mold into a cold isostatic press for cold isostatic pressing, wherein the pressure of the cold isostatic press is 160-180Mpa, and the pressure maintaining time is 5-30 min, so that a composite material shell blank is obtained;
(5) Placing the composite material shell blank in a hydrogen furnace, heating to 1400-2000 ℃, and preserving heat for 12-72 hours to obtain a sintered composite material shell;
(6) Machining, cleaning and sandblasting the sintered composite material shell;
(7) Respectively coating the inner surface and the outer surface of the sintered composite material shell treated in the step (6) with paint by adopting a normal-temperature gas atomization coating method to prepare ceramic protective layers to obtain a prefabricated combustion stabilizer shell; in detail, the coating used for preparing the ceramic protective layer is a suspension consisting of an oxide and a high-temperature binder, wherein the oxide is 20-40 percent CrO by weight 2 、10%-40% TiO 2 、10%-20% ReO 2 、10%-30% Si 3 N 4 、5%-10% SiC、0.1%-5% Lu 2 O 3 、0.1%-5% Yb 2 O 3 、0.1%-5% Tm 2 O 3 、0.1%-5% Y 2 O 3 、0.1%-5% Er 2 O 3 The high-temperature binder is hydroxyl and carboxyl high-temperature binder, and the hydroxyl and carboxyl high-temperature binder contains at least one of acetone, silane coupling agent, xylene, n-butyl alcohol and other hydrocarbons which can be used as the high-temperature binder; when the ceramic protective layer is prepared, a small amount of paint is coated for multiple times, and the single coating amount is 25-75 um/time;
(8) And (3) performing high-temperature sintering on the prefabricated combustion stabilizer shell by using a vacuum furnace (the high-temperature sintering parameter is that the temperature is increased to 1200-1700 ℃ at the heating rate of 10-40 ℃/min and is kept for 2-8 h), slowly cooling to the room temperature, and taking out to obtain the high-temperature oxidation resistant combustion stabilizer shell.
The alloy powder has any one of the following components:
a refractory metal powder;
and the second method comprises the following steps: an alloy powder composed of at least two refractory metals;
and the third is that: multi-component alloy powders composed of one or more refractory metals with other metallic and/or non-metallic elements;
and fourthly: multi-component alloy powders composed of one or more refractory metals and other metal or metalloid oxides.
Referring to fig. 1, T1 represents the thickness of the alloy shell blank, T2 represents the thickness of the alloy powder between the core rod and the inner surface of the alloy shell blank after pressing, and T3 represents the thickness of the alloy powder between the inner wall of the rubber grinding tool and the outer surface of the alloy shell blank after pressing, wherein (1) the thicknesses of T1, T2 and T3 need to comprehensively consider the load of the direct-ignition flame stabilizer during operation, the effective thickness of the protective layer, and the cold isostatic pressing and sintering shrinkage; (2) T2= T3; (3) The core mold is made of solid materials with certain yield strength, such as stainless steel, and the like, so that the core mold is prevented from being damaged due to stress bending in the cold isostatic pressing process; (4) The rubber grinding tool is a rubber product, has good elasticity, is complete and has no damage.
Example 1
A preparation method of a high-temperature air direct-ignition combustion stabilizer shell resistant to high-temperature oxidation comprises the following steps:
(1) Taking pure molybdenum powder with the purity of 99.95 percent, selecting alloy powder with the Fisher particle size of more than 4um and the specific surface area of 0.2-0.3m 2 The powder of the/g is subjected to cold isostatic pressing and crushing, and then the Fisher grain size is 4.2um and the specific surface area is 0.2m 2 Performing cold isostatic pressing on molybdenum powder per gram at 160Mpa for 15min to obtain an alloy shell blank;
(2) Turning the alloy shell blank to ensure that the shape of the alloy shell blank is basically consistent with that of a finished shell, and reserving the thickness of mixed powder compression molding, the subsequent sintering shrinkage allowance and the machining allowance in the aspect of size;
(3) Taking 40 percent of Mo powder, 40 percent of Si powder, 10 percent of Hf powder, 5 percent of CeO2 powder and 5 percent of La powder according to weight percentage 2 O 3 Mixing the powders to obtain mixed powder, wherein the purity of the selected powder is more than or equal to 99.95%, and the granularity of the selected powder is controlled to be about 3.5-4.2um;
(4) And (3) placing the alloy shell blank obtained in the step (2) in a rubber mold with a core rod, ensuring that the inner surface and the outer surface of the alloy shell blank are spaced from the inner surface of the rubber mold and the outer surface of the core rod properly, keeping the coaxiality of the alloy shell blank, the core rod and the rubber mold to be 0.02mm, uniformly pouring the mixed powder into the mold, and placing the mold in a cold isostatic press for secondary pressing. Forming the composite shell blank under the pressure of 180MPa for 5min, wherein T2= T3=15mm;
(5) Sintering the composite material shell blank in a hydrogen furnace to obtain a sintered composite material shell, wherein the temperature of the hydrogen furnace is 1400 ℃, and the heating time is 42 hours;
(6) Machining the sintered composite material shell, cleaning, sandblasting, wherein the sandblasting grade is Sa3.0 grade, cleaning by using acetone or deionized water, and drying for later use;
(7) Respectively coating the inner surface and the outer surface of the sintered composite material shell treated in the step (6) with paint by adopting a normal-temperature gas atomization coating method to prepare the ceramic waterproof coatingA sheath layer to obtain a prefabricated flame stabilizer shell; the coating used is a suspension consisting of an oxide and a high-temperature binder, wherein the oxide comprises the following components in percentage by mass: 25% of CrO 2 、40%TiO 2 、5%ReO 2 、15%Si 3 N 4 10% SiC and 2.6% Lu 2 O 3 And 2.4% Yb 2 O 3 (ii) a The adopted high-temperature binder is acetone and n-butanol, the mass ratio of the acetone to the n-butanol is respectively 40% and 60%, the single coating amount is 25 um/time, and the film thickness is 250um;
(8) And sintering the prefabricated flame stabilizer shell at high temperature by using a vacuum furnace, wherein the sintering temperature is 1200 ℃, the heating rate is 10 ℃/min, the heat preservation time is 2h after the design temperature is reached, and then slowly cooling to room temperature and taking out to obtain the flame stabilizer shell resistant to high-temperature oxidation.
Example 2
A preparation method of a high-temperature air direct-ignition combustion stabilizer shell resistant to high-temperature oxidation comprises the following steps:
(1) And taking pure tungsten powder with the purity of 99.95% and pure nickel powder with the purity of 99.95%, wherein the Fisher particle size is 4.02um and 4.1um respectively, mixing according to the weight ratio of 2 2 Performing cold isostatic pressing on the powder per gram, wherein the pressure is 170Mpa, and the pressure maintaining time is 10min to prepare an alloy shell blank;
(2) Turning the alloy shell blank to ensure that the shape of the alloy shell blank is basically consistent with that of a finished product, and reserving the thickness of mixed powder compression molding, the subsequent sintering shrinkage allowance and the machining allowance in the aspect of size;
(3) According to the weight percentage, 60 percent of Mo powder, 25 percent of Si powder, 5 percent of Hf powder and 6 percent of CeO are taken 2 Powder and 4% La 2 O 3 Mixing the powders to obtain mixed powder, wherein the purity of the selected powder is more than or equal to 99.95%, and the granularity of the selected powder is controlled to be about 3.5-4.2um;
(4) And (3) placing the alloy shell blank obtained in the step (2) in a rubber mold with a core rod, ensuring that the inner surface and the outer surface of the alloy shell blank are spaced from the inner surface of the mold and the outer surface of the core rod properly, keeping the coaxiality of the alloy shell blank, the core rod and the rubber mold to be 0.01mm, uniformly pouring the mixed powder into the mold, and placing the mold in a cold isostatic press for secondary pressing. Forming the composite shell blank under the pressure of 175MPa for 8min, wherein T2= T3=10mm;
(5) Sintering the composite material shell blank in a hydrogen furnace to obtain a sintered composite material shell, wherein the temperature of the hydrogen furnace is 1600 ℃, and the heating time is 48 hours;
(6) Machining a sintered composite material shell, cleaning, sandblasting, wherein the sandblasting grade is Sa3.0 grade, cleaning by using acetone or deionized water, and drying for later use;
(7) Respectively coating the inner surface and the outer surface of the sintered composite material shell treated in the step (6) with paint by adopting a normal-temperature gas atomization coating method to prepare ceramic protective layers to obtain a prefabricated combustion stabilizer shell; the coating used is a suspension consisting of an oxide and a high-temperature binder, wherein the oxide comprises the following components in percentage by mass: 40% CrO 2 、34% TiO 2 、1% ReO 2 、15% Si 3 N 4 8% SiC and 0.05% Lu 2 O 3 、1.1% Y 2 O 3 And 0.85% Yb 2 O 3 The selected high-temperature binder is acetone, the single coating amount is 35 um/time, and the film thickness is 300um;
(8) And sintering the prefabricated combustion stabilizer shell at high temperature by using a vacuum furnace, wherein the sintering temperature is 1500 ℃, the heating speed is 20 ℃/min, the heat preservation time is 4h after the design temperature is reached, and then slowly cooling to the room temperature and taking out to obtain the combustion stabilizer shell resistant to high-temperature oxidation.
Example 3
A preparation method of a high-temperature air direct-ignition combustion stabilizer shell resistant to high-temperature oxidation comprises the following steps:
(1) Taking pure tungsten powder with the purity of 99.95%, pure molybdenum powder with the purity of 99.95% and pure nickel powder with the purity of 99.95%, wherein the Fisher particle size is 4.0um, 4.2um and 4.24um respectively, and the weight ratio is 10%:75%:15% of the mixture was mixed and the specific surface area was 0.2m 2 Performing cold isostatic pressing on the powder per gram, wherein the pressure is 200Mpa, and the pressure maintaining time is 30min to prepare an alloy shell blank;
(2) Turning the alloy shell blank to make its shape basically identical to that of the finished shell, reserving the thickness of the mixed powder in the aspect of size, the subsequent sintering shrinkage allowance and the machining allowance for compression molding;
(3) Mixing 80% of Mo powder, 10% of Si powder, 3% of Hf powder, 5% of CeO2 powder and 2% of La2O3 powder according to the weight percentage to prepare mixed powder, wherein the purity of the selected powder is more than or equal to 99.95%, and the granularity of the selected powder is controlled to be about 3.5-4.2um;
(4) And (3) placing the alloy shell blank obtained in the step (2) in a rubber mould with a core rod, ensuring that the inner surface and the outer surface of the alloy shell blank are spaced from the inner surface of the rubber mould and the outer surface of the core rod properly, keeping the coaxiality of the alloy shell blank, the core rod and the rubber mould to be 0.01mm, uniformly pouring the mixed powder into the mould, and placing the mould in a cold isostatic press for secondary pressing. Wherein the pressure is 180Mpa, the dwell time is 10min, and the composite material shell blank is formed, wherein T2= T3=8mm;
(5) Sintering the composite material shell blank in a hydrogen furnace to obtain a sintered composite material shell, wherein the temperature of the hydrogen furnace is 1600 ℃, and the heating time is 48 hours;
(6) Machining, cleaning and sandblasting the sintered composite material shell, wherein the sandblasting grade is Sa3.0 grade, and the sintered composite material shell is cleaned by using acetone or deionized water and dried for later use;
(7) Respectively coating paint on the inner surface and the outer surface of the sintered composite material shell treated in the step (6) by adopting a normal-temperature gas atomization coating method to prepare ceramic protective layers so as to obtain a prefabricated combustion stabilizer shell; the coating used is a suspension composed of an oxide and a high-temperature binder, wherein the oxide comprises the following components in percentage by mass: 35% CrO 2 、27% TiO 2 、6.6% ReO 2 、12% Si 3 N 4 、6% SiC、0.1% Lu 2 O 3 、0.6% Er 2 O 3 、0.46% Yb 2 O 3 And 0.24% La 2 O 3 (ii) a The adopted high-temperature adhesive comprises a silane coupling agent, dimethylbenzene and acetone, the mass ratios of the silane coupling agent, the dimethylbenzene and the acetone are respectively 20%, 40% and 60%, and the single-time coating amount is 70 mu mPer time, the film thickness is 350um;
(8) And sintering the prefabricated flame stabilizer shell at a high temperature by using a vacuum furnace, wherein the sintering temperature is 1600 ℃, the heating rate is 25 ℃/min, the heat preservation time is 6h after the design temperature is reached, and then slowly cooling to the room temperature and taking out to obtain the flame stabilizer shell resistant to high-temperature oxidation.
The medium-frequency induction heating test and the high-temperature aerobic test under the same conditions were respectively carried out on the high-temperature oxidation resistant flame stabilizer casings prepared in examples 1 to 3, and the medium-frequency induction heating test and the high-temperature aerobic test both showed good heating rate and good high-temperature oxidation resistance and thermal shock resistance.
The foregoing is merely a preferred embodiment of the invention and is not to be construed as limiting the invention in any way. All equivalent changes or modifications made according to the spirit of the present invention should be covered within the protection scope of the present invention.
Claims (10)
1. A preparation method of a high-temperature oxidation resistant high-temperature air direct ignition combustion stabilizer shell is characterized by mainly comprising the following steps:
(1) The alloy powder is pressed into an alloy shell blank through cold isostatic pressing;
(2) Turning the alloy shell blank obtained in the step (1) to obtain an alloy shell blank, wherein the shape of the alloy shell blank is basically consistent with that of a finished shell, and a corresponding allowance is reserved in the aspect of size;
(3) According to the weight percentage, 40 to 80 percent of Mo powder, 10 to 40 percent of Si powder, 5 to 20 percent of Hf powder and 1 to 5 percent of CeO powder are taken 2 Powder and 1% -5% of La 2 O 3 Mixing the powders to obtain mixed powder;
(4) Placing the alloy shell blank obtained in the step (2) in a rubber mould with a mandrel, ensuring that gaps of 5-40mm are reserved between the inner surface of the alloy shell blank and the outer surface of the mandrel and between the outer surface of the alloy shell blank and the inner wall of the rubber mould, uniformly pouring the mixed powder prepared in the step (3) into the gaps, and then placing the rubber mould in a cold isostatic press for cold isostatic pressing to obtain a composite material shell blank;
(5) Heating the composite material shell blank in a hydrogen furnace to 1400-2000 ℃ and preserving the heat for 12-72 h to prepare a sintered composite material shell;
(6) Machining, cleaning and sandblasting the sintered composite material shell;
(7) Respectively coating the inner surface and the outer surface of the sintered composite material shell treated in the step (6) with paint by adopting a normal-temperature gas atomization coating method to prepare ceramic protective layers to obtain a prefabricated combustion stabilizer shell;
(8) And sintering the prefabricated combustion stabilizer shell at high temperature by using a vacuum furnace, slowly cooling to room temperature, and taking out to obtain the combustion stabilizer shell resistant to high-temperature oxidation.
2. The method for preparing the high-temperature air direct-ignition combustion stabilizer casing resistant to high-temperature oxidation according to claim 1, wherein in the step (1), the alloy powder comprises any one of the following components:
the first method comprises the following steps: a refractory metal powder;
and the second method comprises the following steps: an alloy powder composed of at least two refractory metals;
and the third is that: multi-component alloy powders composed of one or more refractory metals with other metallic and/or non-metallic elements;
and a fourth step of: multi-component alloy powders composed of one or more refractory metals and other metal or metalloid oxides.
3. The method for preparing a high temperature air direct ignition combustion stabilizer casing with high temperature oxidation resistance as claimed in claim 1, wherein in the step (1), the Fisher size of the alloy powder is more than 4um, and the specific surface area is 0.2-0.3m 2 /g。
4. The method for preparing a high temperature air direct ignition combustion stabilizer casing with high temperature oxidation resistance as claimed in claim 1, wherein in the step (1), the pressure during cold isostatic pressing is 160-200Mpa, and the dwell time is 5-30 min.
5. The method for preparing a high temperature air direct ignition combustion stabilizer casing resistant to high temperature oxidation as claimed in claim 1, wherein in step (3), mo powder, si powder, hf powder, ceO powder are used 2 Powder and La 2 O 3 The purity of the powder is not less than 99.95 percent, and the granularity is 3.5-4.2um.
6. The method for preparing a high temperature air direct ignition combustion stabilizer casing resistant to high temperature oxidation according to claim 1, wherein in the step (4), the pressure of the cold isostatic pressing is 160-180Mpa, and the pressure holding time is 5-30 min.
7. The method for preparing the high-temperature air direct-ignition combustion stabilizer shell resistant to high-temperature oxidation as claimed in claim 1, wherein in the step (4), the coaxiality of the alloy shell blank, the core rod and the rubber mold is kept to be higher than 0.03mm.
8. The method for preparing a high-temperature air direct-ignition combustion stabilizer casing resistant to high-temperature oxidation according to claim 1, wherein in the step (7), the coating used for preparing the ceramic protective layer is a suspension of an oxide and a high-temperature binder, wherein the oxide comprises the following components in percentage by weight: 20% -40% CrO 2 、10%-40% TiO 2 、1%-10% ReO 2 、10%-20% Si 3 N 4 、5%-10% SiC、0.1%-5% Lu 2 O 3 、0.1%-5% Yb 2 O 3 、0.1%-5% Tm 2 O 3 、0.1%-5% Y 2 O 3 、0.1%-5% Er 2 O 3 The high-temperature binder is hydroxyl or carboxyl.
9. The method for preparing the high temperature oxidation resistant high temperature air direct ignition combustion stabilizer casing according to the claim 1, characterized in that in the step (7), the coating is applied in small amount in multiple times, and the single coating amount is 25 um/time to 75 um/time.
10. The method for preparing the high-temperature air direct-ignition combustion stabilizer casing resistant to high-temperature oxidation according to claim 1, wherein in the step (8), the parameters of high-temperature sintering are as follows: heating to 1200-1700 ℃ at the heating rate of 10-40 ℃/min and preserving the heat for 2-8 h.
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