CN115138842B - Preparation method of high-temperature air direct ignition flame stabilizer shell resistant to high-temperature oxidation - Google Patents
Preparation method of high-temperature air direct ignition flame stabilizer shell resistant to high-temperature oxidation Download PDFInfo
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
- B22F3/02—Compacting only
- B22F3/04—Compacting only by applying fluid pressure, e.g. by cold isostatic pressing [CIP]
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
- B22F3/12—Both compacting and sintering
- B22F3/16—Both compacting and sintering in successive or repeated steps
- B22F3/162—Machining, working after consolidation
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
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- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
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- C22C27/00—Alloys based on rhenium or a refractory metal not mentioned in groups C22C14/00 or C22C16/00
- C22C27/04—Alloys based on tungsten or molybdenum
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
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- C22C32/00—Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ
- C22C32/001—Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ with only oxides
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Abstract
The invention discloses a preparation method of a high-temperature oxidation resistant high-temperature air direct ignition flame stabilizer shell, which mainly comprises the following steps: preparing a composite material shell blank by two cold isostatic pressing; heating the composite material shell blank in a hydrogen furnace to 1400-2000 ℃ and preserving heat for 12-72 h to obtain a sintered composite material shell; machining, cleaning, drying and sand blasting the sintered composite material shell; and (3) respectively coating the inner surface and the outer surface of the sintered composite material shell with a coating by adopting a normal-temperature gas atomization coating method to prepare a ceramic protective layer, then carrying out high-temperature sintering, slowly cooling to room temperature, and taking out to obtain the high-temperature air direct-ignition flame stabilizer shell resistant to high-temperature oxidation. The burner housing 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 air direct ignition flame stabilizer shell resistant to high-temperature oxidation.
Background
Refractory alloy is widely used in the fields of metallurgy, machinery, energy, chemical industry, national defense, electronics and the like because of excellent mechanical properties and physical properties such as high-temperature strength and high-temperature hardness, good heat and electric conductivity, low thermal expansion coefficient and the like. Meanwhile, due to the good high temperature resistance, the material is widely applied to high temperature furnaces and vacuum furnaces in a heating furnace chamber mode.
When the high-temperature air direct-ignition flame stabilizer works, the temperature of an inner cavity can reach about 1600 ℃ instantly, and the tolerance temperature of high-temperature steel and special steel commonly used in the markets at home and abroad at present is about 1200 ℃, so that the basic requirement of the high-temperature air direct-ignition flame stabilizer is far not met. Therefore, the use of refractory metals and their alloys as housings for high temperature air direct-fired burners has become necessary. However, refractory metals and their alloys react with oxygen easily in an aerobic environment at temperatures above 400 ℃, and problems such as material loss and reduced thermodynamic properties are likely to occur.
Therefore, how to solve the problems of the service performance and the service life of refractory metals and alloys thereof in an aerobic environment becomes a breakthrough point for solving the development and the application of the high-temperature air direct-ignition flame 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 steady burner shell resistant to high-temperature oxidation, and the high-temperature air direct-ignition steady burner shell prepared by the preparation method overcomes the problems of easiness in oxidation and serious reduction of service performance in an aerobic environment at high temperature.
In order to achieve the above purpose, the invention adopts the following specific scheme:
a preparation method of a high-temperature air direct ignition flame stabilizer shell resistant to high-temperature oxidation mainly comprises the following steps:
(1) Pressing the alloy powder into an alloy shell blank by 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 corresponding allowance is reserved in the aspect of size;
(3) Taking 40-80% of Mo powder, 10-40% of Si powder, 5-20% of Hf powder and 1-5% of CeO according to weight percentage 2 Powder and 1% -5% La 2 O 3 Mixing the powder to obtain mixed powder;
(4) Placing the alloy shell blank obtained in the step (2) in a rubber mold with a core rod, ensuring that gaps of 5-40 mm 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, and then placing the rubber mold in a cold isostatic pressing machine for cold isostatic pressing to obtain the composite material shell blank;
(5) Heating the composite material shell blank in a hydrogen furnace to 1400-2000 ℃ and preserving heat for 12-72 h to obtain a sintered composite material shell;
(6) Machining, cleaning, drying and sand blasting the sintered composite material shell;
(7) Coating the inner surface and the outer surface of the sintered composite material shell treated in the step (6) with paint respectively by adopting a normal-temperature gas atomization coating method to prepare a ceramic protective layer, so as to obtain a prefabricated flame stabilizer shell;
(8) And (3) sintering the prefabricated flame stabilizer shell at 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 components of the alloy powder are any one of the following:
first kind: a refractory metal powder;
second kind: alloy powders of at least two refractory metals;
third kind: a multi-component alloy powder comprised of one or more refractory metals and other metallic and/or non-metallic elements;
fourth kind: a multi-component alloy powder comprised of one or more refractory metals and other metal or non-metal 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 dwell 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%, and the granularity is 3.5-4.2 μm.
Further, in the step (4), the pressure of the cold isostatic pressing is 160-180Mpa, and the dwell time is 5-30 min.
Further, in the step (4), the coaxiality of the alloy shell blank, the core rod and the rubber mold is kept higher than 0.03mm.
Further, in the step (7), the coating used for preparing the ceramic protective layer is a suspension formed by oxides and a high-temperature binder, wherein the oxides comprise 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 used is hydroxyl or carboxyl high-temperature binder.
Further, in the step (7), the coating is applied in small amounts in a plurality of times, the single application amount being 25 μm/time to 75 μm/time.
Further, in the step (8), parameters of the high-temperature sintering are as follows: heating to 1200-1700 ℃ at a heating rate of 10-40 ℃/min and preserving heat for 2-8 h.
The beneficial effects are that:
(1) According to the invention, the sintered composite material shell is prepared in a mode of twice cold isostatic pressing and hydrogen sintering, and then the ceramic protective layer is prepared on the inner surface and the outer surface of the sintered composite material shell and is sintered at high temperature, so that the composite material shell with the standard thickness protective layer 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 common coating falling and poor thermal shock resistance and the like in the preparation of the surface protective layer in the prior art are avoided.
(2) The invention coats the inner and outer surfaces of the composite material shell by an air atomization method, and aims to seal pore paths on the surfaces of the sintered composite material shell prepared by sintering by a powder metallurgy method, and a compact ceramic protective 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 view of the structure of the alloy shell blank after being pressed in a rubber mold.
The graphic indicia: 1. the core rod, 2, the rubber mould, 3, the composite material shell blank, 31, the alloy shell blank.
Detailed Description
The technical solutions of the present invention will be clearly and completely described below in connection with specific embodiments, and it is obvious that the described embodiments are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to fall within the scope of the invention.
A preparation method of a high-temperature air direct ignition flame stabilizer shell resistant to high-temperature oxidation mainly comprises the following steps:
(1) The alloy powder is pressed into alloy shell blank by cold isostatic pressing, the Fisher size of the selected alloy powder is above 4 mu m, and the specific surface area is 0.2-0.3m 2 And/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 corresponding allowance is reserved in the aspect of size; the "corresponding allowance" herein includes the thickness of the mixed powder pressed molding, the subsequent sintering shrinkage allowance, and the processing allowance;
(3) Taking 40-80% of Mo powder, 10-40% of Si powder, 5-20% of Hf powder and 1-5% of CeO according to weight percentage 2 Powder and 1% -5% La 2 O 3 Mixing the powder to obtain mixed powder; wherein Mo powder, si powder, hf powder and 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 3.5-4.2 mu m;
(4) Placing the alloy shell blank obtained in the step (2) in a rubber mold with a core rod, ensuring that gaps of 5-40 mm 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 distributed, and after the rubber mold is closed, shaping the mold, so as to ensure that no powder eccentricity exists in all parts; the coaxiality of the powder shell, the core rod and the rubber mold is kept higher than 0.03mm, then the rubber mold is placed in a cold isostatic pressing machine for cold isostatic pressing, the pressure of the cold isostatic pressing is 160-180Mpa, and the pressure maintaining time is 5-30 min, so that a composite material shell blank is obtained;
(5) Heating the composite material shell blank in a hydrogen furnace to 1400-2000 ℃ and preserving heat for 12-72 h to obtain a sintered composite material shell;
(6) Machining, cleaning and sand blasting the sintered composite material shell;
(7) Coating the inner surface and the outer surface of the sintered composite material shell treated in the step (6) with paint respectively by adopting a normal-temperature gas atomization coating method to prepare a ceramic protective layer, so as to obtain a prefabricated flame stabilizer shell; in detail, the coating used for preparing the ceramic protective layer is a suspension formed by oxide and high-temperature binder, wherein the oxide is used for preparing the ceramic protective layer, and the oxide is used for preparing the ceramic protective layer, wherein the oxide is used for preparing the ceramic protective layer, the ceramic protective layer comprises the following components in percentage by weight of 20% -40% CrO 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 comprises at least one of acetone, silane coupling agent, xylene, n-butanol and other hydrocarbon which can be used as the high-temperature binder; coating the ceramic protective layer by a small amount for multiple times in preparation of the ceramic protective layer, wherein the single coating amount is 25 mu m/time-75 mu m/time;
(8) And (3) performing high-temperature sintering (high-temperature sintering parameters: heating to 1200-1700 ℃ at a heating rate of 10-40 ℃/min) on the prefabricated flame stabilizer shell by using a vacuum furnace, preserving heat for 2-8 h), slowly cooling to room temperature, and taking out to obtain the flame stabilizer shell resistant to high-temperature oxidation.
The components of the alloy powder are any one of the following components:
a refractory metal powder;
second kind: alloy powders of at least two refractory metals;
third kind: a multi-component alloy powder comprised of one or more refractory metals and other metallic and/or non-metallic elements;
fourth kind: a multi-component alloy powder comprised of one or more refractory metals and other metal or non-metal oxides.
Referring to fig. 1, T1 represents the thickness of the alloy shell blank, T2 represents the thickness of the alloy powder between the mandrel 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 burner, 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 such as stainless steel with certain yield strength, 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 and is complete and free of damage.
Example 1
A preparation method of a high-temperature air direct ignition flame stabilizer shell resistant to high-temperature oxidation comprises the following steps:
(1) Taking pure molybdenum powder with purity of 99.95%, selecting alloy powder with Fisher particle size of more than 4 μm and specific surface area of 0.2-0.3m 2 After cold isostatic pressing and crushing, powder of/g is selected to have a Fisher size of 4.2 μm and a specific surface area of 0.2m by a size classifying device 2 Performing cold isostatic pressing on/g molybdenum powder, wherein the pressure is 160Mpa, and the pressure maintaining time is 15min to prepare an alloy shell blank;
(2) Turning the alloy shell blank to make the shape of the alloy shell blank basically consistent with that of the finished shell, and reserving the thickness of the mixed powder for compression molding, the subsequent sintering shrinkage allowance and the machining allowance in terms of size;
(3) Taking 40% of Mo powder, 40% of Si powder, 10% of Hf powder, 5% of CeO2 powder and 5% of La according to the weight percentage 2 O 3 Mixing the powder to obtain mixed powder, wherein the purity of the selected powder is more than or equal to 99.95%, and the granularity is controlled to be about 3.5-4.2 μm;
(4) And (3) placing the alloy shell blank obtained in the step (2) in a rubber mold with a core rod, ensuring proper spacing between the inner surface and the outer surface of the rubber mold and between the inner surface and the outer surface of the core rod, 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. Wherein, the pressure is 180Mpa, the dwell time is 5min, and the composite material shell blank is formed, wherein T2=T3=15mm;
(5) Sintering the composite material shell blank in a hydrogen furnace at 1400 ℃ for 42h to obtain a sintered composite material shell;
(6) Machining the sintered composite material shell, cleaning, sandblasting, cleaning with acetone or deionized water, and drying for later use, wherein the sandblasting grade is Sa3.0;
(7) Coating the inner surface and the outer surface of the sintered composite material shell treated in the step (6) with paint respectively by adopting a normal-temperature gas atomization coating method to prepare a ceramic protective layer, so as to obtain a prefabricated flame stabilizer shell; the coating is a suspension formed by oxide and high-temperature binder, wherein the oxide comprises the following components in percentage by mass: 25% 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 The method comprises the steps of carrying out a first treatment on the surface of the The adopted high-temperature binder is acetone and n-butanol, the mass ratio of the acetone to the n-butanol is 40% and 60%, the single coating amount is 25 mu m/time, and the film thickness is 250 mu m;
(8) And (3) sintering the prefabricated flame stabilizer shell at a 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 temperature reaches the design temperature, and then the flame stabilizer shell resistant to high temperature oxidation is obtained after the temperature is slowly reduced to room temperature.
Example 2
A preparation method of a high-temperature air direct ignition flame stabilizer shell resistant to high-temperature oxidation comprises the following steps:
(1) Mixing pure tungsten powder with purity of 99.95% and pure nickel powder with purity of 99.95%, fisher particle size of 4.02 μm and 4.1 μm respectively, and weight ratio of 2:1, and specific surface area of 0.2m 2 Carrying out cold isostatic pressing on the powder of/g, wherein the pressure is 170Mpa, and the pressure maintaining time is 10min to obtain an alloy shell blank;
(2) Turning the alloy shell blank to make the shape of the alloy shell blank basically consistent with that of a finished product, and reserving the thickness of the mixed powder for compression molding, the subsequent sintering shrinkage allowance and the machining allowance in terms of size;
(3) Taking 60% of Mo powder, 25% of Si powder, 5% of Hf powder and 6% of CeO according to weight percentage 2 Powder and 4% La 2 O 3 Mixing the powder to obtain mixed powder, wherein the purity of the selected powder is more than or equal to 99.95%, and the granularity is controlled to be about 3.5-4.2 μm;
(4) And (3) placing the alloy shell blank obtained in the step (2) in a rubber mold with a core rod, ensuring proper spacing between the inner surface and the outer surface of the mold and between the inner surface of the mold and the outer surface of the core rod, 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. Wherein, the pressure is 175Mpa, the dwell time is 8min, and the composite material shell blank is formed, wherein, T2=T3=10mm;
(5) Sintering the composite material shell blank in a hydrogen furnace at 1600 ℃ for 48h to obtain a sintered composite material shell;
(6) Machining the sintered composite material shell, cleaning, sandblasting, cleaning with acetone or deionized water, and drying for later use, wherein the sandblasting grade is Sa3.0;
(7) Adopting normal temperature gasThe atomization coating method is to respectively coat the coating on the inner surface and the outer surface of the sintered composite material shell treated in the step (6) to prepare a ceramic protective layer so as to obtain a prefabricated flame stabilizer shell; the coating is a suspension formed by oxide and 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 high-temperature adhesive is acetone, the single coating amount is 35 mu m/time, and the film thickness is 300 mu m;
(8) And (3) sintering the prefabricated flame stabilizer shell at a high temperature by using a vacuum furnace, wherein the sintering temperature is 1500 ℃, the heating rate is 20 ℃/min, the heat preservation time is 4 hours after the temperature reaches the design temperature, and then the flame stabilizer shell resistant to high temperature oxidation is obtained after the temperature is slowly reduced to room temperature.
Example 3
A preparation method of a high-temperature air direct ignition flame stabilizer shell resistant to high-temperature oxidation comprises the following steps:
(1) Pure tungsten powder with purity of 99.95%, pure molybdenum powder with purity of 99.95% and pure nickel powder with purity of 99.95% are taken, the Fisher particle sizes are respectively 4.0 mu m, 4.2 mu m and 4.24 mu m, and the weight ratio is 10%:75%:15% and a specific surface area of 0.2m 2 Carrying out cold isostatic pressing on the powder of/g, wherein the pressure is 200Mpa, and the pressure maintaining time is 30min to obtain an alloy shell blank;
(2) Turning the alloy shell blank to make the shape of the alloy shell blank basically consistent with that of the finished shell, and reserving the thickness of the mixed powder for compression molding, the subsequent sintering shrinkage allowance and the machining allowance in terms of size;
(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 weight percentage to prepare mixed powder, wherein the purity of the selected powder is more than or equal to 99.95%, and the granularity is controlled to be about 3.5-4.2 mu m;
(4) And (3) placing the alloy shell blank obtained in the step (2) in a rubber mold with a core rod, ensuring proper spacing between the inner surface and the outer surface of the rubber mold and between the inner surface and the outer surface of the core rod, 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. 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 at 1600 ℃ for 48h to obtain a sintered composite material shell;
(6) Machining, cleaning and sandblasting the sintered composite material shell, wherein the sandblasting grade is Sa3.0, cleaning by using acetone or deionized water, and drying for later use;
(7) Coating the inner surface and the outer surface of the sintered composite material shell treated in the step (6) with paint respectively by adopting a normal-temperature gas atomization coating method to prepare a ceramic protective layer, so as to obtain a prefabricated flame stabilizer shell; wherein the coating used is a suspension composed of oxides and a high-temperature binder, wherein the oxides comprise 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 The method comprises the steps of carrying out a first treatment on the surface of the The adopted high-temperature binder is silane coupling agent, dimethylbenzene and acetone, the mass ratio of the silane coupling agent to the dimethylbenzene to the acetone is 20%, 40% and 60%, the single coating amount is 70 mu m/time, and the film thickness is 350 mu m;
(8) And (3) 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 temperature reaches the design temperature, and then the flame stabilizer shell resistant to high temperature oxidation is prepared after the temperature is slowly reduced to room temperature.
The intermediate frequency induction heating test and the high temperature aerobic test under the same conditions are respectively carried out on the high temperature oxidation resistant burner housings prepared in the examples 1-3, and the high temperature oxidation resistant burner housings have good temperature rising rate and good high temperature oxidation resistance and thermal shock resistance.
The above description is only of the preferred embodiment of the present invention, and is not intended to limit the present invention in any way. All equivalent changes or modifications made according to the essence of the present invention should be included in the scope of the present invention.
Claims (9)
1. The preparation method of the high-temperature air direct ignition flame stabilizer shell resistant to high-temperature oxidation is characterized by mainly comprising the following steps of:
(1) Pressing the alloy powder into an alloy shell blank by 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 corresponding allowance is reserved in the aspect of size;
(3) Taking 40-80% of Mo powder, 10-40% of Si powder, 5-20% of Hf powder and 1-5% of CeO according to weight percentage 2 Powder and 1% -5% La 2 O 3 Mixing the powder to obtain mixed powder;
(4) Placing the alloy shell blank obtained in the step (2) in a rubber mold with a core rod, ensuring that gaps of 5-40 mm 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, and then placing the rubber mold in a cold isostatic pressing machine for cold isostatic pressing to obtain the composite material shell blank;
(5) Heating the composite material shell blank in a hydrogen furnace to 1400-2000 ℃ and preserving heat for 12-72 h to obtain a sintered composite material shell;
(6) Machining, cleaning and sand blasting the sintered composite material shell;
(7) Coating the inner surface and the outer surface of the sintered composite material shell treated in the step (6) with paint respectively by adopting a normal-temperature gas atomization coating method to prepare a ceramic protective layer, so as to obtain a prefabricated flame stabilizer shell;
(8) Sintering the prefabricated flame stabilizer shell at 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;
in the step (8), parameters of high-temperature sintering are as follows: heating to 1200-1700 ℃ at a heating rate of 10-40 ℃/min and preserving heat for 2-8 h.
2. The method for preparing a high-temperature oxidation resistant high-temperature air direct-ignition burner housing according to claim 1, wherein in the step (1), the alloy powder comprises any one of the following components:
first kind: a refractory metal powder;
second kind: alloy powders of at least two refractory metals;
third kind: a multi-component alloy powder comprised of one or more refractory metals and other metallic and/or non-metallic elements;
fourth kind: a multi-component alloy powder comprised of one or more refractory metals and other metal or non-metal oxides.
3. The method for preparing a high-temperature oxidation resistant high-temperature air direct-ignition burner housing according to claim 1, wherein in the step (1), the Fisher size of the alloy powder is more than 4 μm, and the specific surface area is 0.2-0.3m 2 /g。
4. The method for preparing a high-temperature oxidation resistant high-temperature air direct-ignition flame stabilizer shell according to 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 flame stabilizer housing resistant to high-temperature oxidation according to claim 1, wherein in the step (3), mo powder, si powder, hf powder and CeO are used 2 Powder and La 2 O 3 The purity of the powder is not less than 99.95%, and the granularity is 3.5-4.2 μm.
6. The method for preparing a high-temperature oxidation resistant high-temperature air direct-ignition flame stabilizer shell according to claim 1, wherein in the step (4), the pressure of cold isostatic pressing is 160-180Mpa, and the dwell time is 5-30 min.
7. The method for preparing a high-temperature air direct-ignition stabilizer housing resistant to high-temperature oxidation according to claim 1, wherein in the step (4), the coaxiality of the alloy housing blank, the core rod and the rubber mold is kept higher than 0.03mm.
8. The method for preparing a high-temperature oxidation resistant high-temperature air direct-ignition flame stabilizer shell according to claim 1, wherein in the step (7), the coating used for preparing the ceramic protective layer is a suspension formed by oxides and a high-temperature binder, and the oxides comprise 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 and/or carboxyl high-temperature binder.
9. The method for producing a high-temperature oxidation-resistant high-temperature air direct-ignition burner housing according to claim 1, wherein in the step (7), the coating is applied in a small number of times, the single application amount being 25 μm/time to 75 μm/time.
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