CN106747524A - A kind of aviation propeller and its manufacture method - Google Patents
A kind of aviation propeller and its manufacture method Download PDFInfo
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- CN106747524A CN106747524A CN201710043293.5A CN201710043293A CN106747524A CN 106747524 A CN106747524 A CN 106747524A CN 201710043293 A CN201710043293 A CN 201710043293A CN 106747524 A CN106747524 A CN 106747524A
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- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
- C04B35/66—Monolithic refractories or refractory mortars, including those whether or not containing clay
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C15/00—Attitude, flight direction, or altitude control by jet reaction
- B64C15/02—Attitude, flight direction, or altitude control by jet reaction the jets being propulsion jets
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- C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
- C04B35/515—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxide ceramics
- C04B35/58—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxide ceramics based on borides, nitrides, i.e. nitrides, oxynitrides, carbonitrides or oxycarbonitrides or silicides
- C04B35/584—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxide ceramics based on borides, nitrides, i.e. nitrides, oxynitrides, carbonitrides or oxycarbonitrides or silicides based on silicon nitride
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- C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
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- C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
- C04B35/622—Forming processes; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
- C04B35/626—Preparing or treating the powders individually or as batches ; preparing or treating macroscopic reinforcing agents for ceramic products, e.g. fibres; mechanical aspects section B
- C04B35/63—Preparing or treating the powders individually or as batches ; preparing or treating macroscopic reinforcing agents for ceramic products, e.g. fibres; mechanical aspects section B using additives specially adapted for forming the products, e.g.. binder binders
- C04B35/632—Organic additives
- C04B35/634—Polymers
- C04B35/63404—Polymers obtained by reactions only involving carbon-to-carbon unsaturated bonds
- C04B35/63416—Polyvinylalcohols [PVA]; Polyvinylacetates
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- C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
- C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
- C04B2235/30—Constituents and secondary phases not being of a fibrous nature
- C04B2235/32—Metal oxides, mixed metal oxides, or oxide-forming salts thereof, e.g. carbonates, nitrates, (oxy)hydroxides, chlorides
- C04B2235/3217—Aluminum oxide or oxide forming salts thereof, e.g. bauxite, alpha-alumina
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- C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
- C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
- C04B2235/30—Constituents and secondary phases not being of a fibrous nature
- C04B2235/32—Metal oxides, mixed metal oxides, or oxide-forming salts thereof, e.g. carbonates, nitrates, (oxy)hydroxides, chlorides
- C04B2235/3224—Rare earth oxide or oxide forming salts thereof, e.g. scandium oxide
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- C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
- C04B2235/30—Constituents and secondary phases not being of a fibrous nature
- C04B2235/32—Metal oxides, mixed metal oxides, or oxide-forming salts thereof, e.g. carbonates, nitrates, (oxy)hydroxides, chlorides
- C04B2235/3224—Rare earth oxide or oxide forming salts thereof, e.g. scandium oxide
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- C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
- C04B2235/30—Constituents and secondary phases not being of a fibrous nature
- C04B2235/38—Non-oxide ceramic constituents or additives
- C04B2235/3817—Carbides
- C04B2235/3839—Refractory metal carbides
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- C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
- C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
- C04B2235/30—Constituents and secondary phases not being of a fibrous nature
- C04B2235/38—Non-oxide ceramic constituents or additives
- C04B2235/3852—Nitrides, e.g. oxynitrides, carbonitrides, oxycarbonitrides, lithium nitride, magnesium nitride
- C04B2235/3865—Aluminium nitrides
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- C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
- C04B2235/50—Constituents or additives of the starting mixture chosen for their shape or used because of their shape or their physical appearance
- C04B2235/52—Constituents or additives characterised by their shapes
- C04B2235/5208—Fibers
- C04B2235/5216—Inorganic
- C04B2235/524—Non-oxidic, e.g. borides, carbides, silicides or nitrides
- C04B2235/5248—Carbon, e.g. graphite
Abstract
The present invention proposes a kind of aviation propeller, and its raw material is respectively according to each composition proportion of mass fraction：75 90 parts of beta-silicon nitride powder, 2 10 parts of metal oxide, 3 10 parts of rare earth oxide mixture, 02 parts of transition metal carbide, 2.5 5 parts of carbon fiber, 2 parts of polyvinyl alcohol, 04 parts of aluminium nitride, are also added with 1.5 times of deionized waters of amount of beta-silicon nitride powder.The present invention also proposes the manufacture method of aviation propeller, its step：Its sample is dried into 48h 96h in vacuum drying chamber, drying temperature is 35 DEG C 70 DEG C；Sample is sintered under nitrogen protection in vacuum high temperature furnace after drying, and sintering temperature is 1720 DEG C 1800 DEG C, and heating rate is 0.5 DEG C/min, 2 DEG C/min, and the heat preservation sintering time is 1h 2h.The aviation is manufactured with propeller using silicon nitride ceramic material, its corrosion-and high-temp-resistant, with pyroconductivity higher, is capable of achieving repeatedly to utilize.
Description
Technical field
The present invention relates to a kind of propeller, more particularly to a kind of aviation propeller and its manufacture method.
Background technology
Propeller is the puopulsion equipment of the vehicles, is to be converted into pushing away by the power that power set on the vehicles are provided
Power, the propulsion vehicles move ahead, and it is widely used in the fields such as space flight and aviation, ship, automobile.It is by rotating vane or spray
Gas (water) produces thrust.Propeller the fields such as ship, aviation apply it is relatively broad, be primarily used to promote ship,
What ships and light boats advanced, the species of its pusher is various, screw propeller, electronic ship's propeller, aero propulsion device, hydraulic jet propulsion
Device etc., each has its special purposes and feature.Existing propeller is substantially senior carrying fuel and oxidant,
The fuel of the burning being easily carried during use is damaged, and causes it to be single use, it is impossible to reuse, and is had
Treat in improvement.
The content of the invention
The present invention proposes a kind of aviation propeller and its manufacture method, solves propeller in the prior art and is easily burned
The problem that fuel is damaged.
The technical proposal of the invention is realized in this way：
A kind of aviation propeller, its raw material is respectively according to each composition proportion of mass fraction：Beta-silicon nitride powder 75-90
Part, metal oxide 2-10 parts, 3-10 parts of rare earth oxide mixture, transition metal carbide 0-2 parts, carbon fiber 2.5-5 parts,
2 parts of polyvinyl alcohol, aluminium nitride 0-4 parts, be also added with the raw material of the aviation propeller 1.5 times of beta-silicon nitride powder amount go from
Sub- water.
Preferred scheme is that the metal oxide is aluminum oxide or magnesia, and the transition metal carbide is titanium carbide
Or tungsten carbide.
Preferred scheme is, the rare earth oxide mixture be yttria, neodymia, lanthanum sesquioxide, cerium oxide,
At least one in luteium oxide.
Preferred scheme is to be respectively according to each composition proportion of mass fraction in the raw material：75 parts of beta-silicon nitride powder, oxidation
4 parts of rare earth oxide mixture, 1 part of titanium carbide, 4 parts of carbon fiber, the polyethylene of 10 parts of aluminium, yttria and cerium oxide composition
2 parts of alcohol, 4 parts of aluminium nitride is also added with 1.5 times of deionized waters of amount of beta-silicon nitride powder in the raw material of aviation propeller.
Preferred scheme is to be respectively according to each composition proportion of mass fraction in the raw material：80 parts of beta-silicon nitride powder, oxidation
4 parts of rare earth oxide mixture, 1.5 parts of titanium carbide, 2.5 parts of carbon fiber, the polyvinyl alcohol 2 of 6 parts of aluminium, yttria composition
Part, 4 parts of aluminium nitride is also added with 1.5 times of deionized waters of amount of beta-silicon nitride powder in the raw material of aviation propeller.
Preferred scheme is to be respectively according to each composition proportion of mass fraction in the raw material：90 parts of beta-silicon nitride powder, oxidation
3 parts of rare earth oxide mixture, 0 part of titanium carbide, 3 parts of carbon fiber, 2 parts of the polyvinyl alcohol, nitrogen of 2 parts of aluminium, yttria composition
Change 0 part of aluminium, 1.5 times of deionized waters of amount of beta-silicon nitride powder are also added with the raw material of aviation propeller.
Preferred scheme is that with propeller manufacturing process, its sample drying time in vacuum drying chamber is 48h- for aviation
96h, drying temperature is 35 DEG C -70 DEG C.
Preferred scheme is that with propeller manufacturing process, its sample is under nitrogen protection in vacuum high temperature furnace for the aviation
Sintering, sintering temperature is 1720 DEG C -1800 DEG C, and heating rate is 0.5 DEG C/min-2 DEG C/min, and in-furnace temperature reaches sintering temperature
The heat preservation sintering time is 1h-2h afterwards.
Preferred scheme is, the vacuum high temperature furnace domestic demand is fitted into graphite frock carries out burying burning in nitrogen atmosphere, base substrate with
Separated by buried powder between graphite frock.
A kind of manufacture method of aviation propeller, it comprises the following steps：
The first step, 48h-96h is dried by the base substrate of aviation propeller sample in vacuum drying chamber, and drying temperature is 35
℃-70℃；
Second step, the sample after drying is sintered in the vacuum high temperature furnace under nitrogen protection, and sintering temperature is 1720 DEG C-
1800 DEG C, heating rate is 0.5 DEG C/min-2 DEG C/min, and the heat preservation sintering time is 1h-2h after in-furnace temperature reaches sintering temperature.
Beneficial effects of the present invention are：
Aviation of the invention is manufactured with propeller using silicon nitride ceramic material, its corrosion-and high-temp-resistant, with higher
Pyroconductivity, performance is more superior, is capable of achieving repeatedly to utilize, and greatly reduces launch cost.
Brief description of the drawings
In order to illustrate more clearly about the embodiment of the present invention or technical scheme of the prior art, below will be to embodiment or existing
The accompanying drawing to be used needed for having technology description is briefly described, it should be apparent that, drawings in the following description are only this
Some embodiments of invention, for those of ordinary skill in the art, on the premise of not paying creative work, can be with
Other accompanying drawings are obtained according to these accompanying drawings.
Fig. 1 is the structure chart of the upper shell of aviation propeller of the present invention；
Fig. 2 is the structure chart of the lower shell of aviation propeller of the present invention；
Fig. 3 is the structure chart of the nitridation silicone disc of aviation propeller of the present invention；
Fig. 4 is the flow chart of the manufacturing process of aviation propeller of the present invention.
In figure：
10th, upper shell；20th, lower shell；30th, silicone disc is nitrogenized；31st, circular hole.
Specific embodiment
Below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is carried out clear, complete
Site preparation is described, it is clear that described embodiment is only a part of embodiment of the invention, rather than whole embodiments.It is based on
Embodiment in the present invention, it is every other that those of ordinary skill in the art are obtained under the premise of creative work is not made
Embodiment, belongs to the scope of protection of the invention.
The aviation with propeller include upper shell 10 as shown in Figure 1, lower shell 20 as shown in Figure 2 and as shown in Figure 3
Nitridation silicone disc 30.The upper shell is highly 430 ㎜, and internal diameter is 350 ㎜, outer through being 362 ㎜.The side wall middle part shape of the lower shell
Into a stage portion, it is highly 183 ㎜, and internal diameter is 350 ㎜, and top external diameter is 364 millimeters, and bottom external diameter is 394 ㎜.The nitridation
The radius of silicone disc 30 is 180 ㎜, is circumferentially provided with circular hole 31 at equal intervals by the center of circle of its center thereon.
The raw material of the aviation propeller is respectively according to each composition proportion of mass fraction：Beta-silicon nitride powder 75-90 parts, gold
2-10 parts of oxide of category, 3-10 parts of rare earth oxide mixture, transition metal carbide 0-2 parts, carbon fiber 2.5-5 parts, poly- second
2 parts, aluminium nitride 0-4 parts of enol.1.5 times of deionizations of amount of beta-silicon nitride powder are also added with the raw material of the aviation propeller
Water.The metal oxide concretely aluminum oxide or magnesia.The rare earth oxide mixture concretely three oxidation two
At least one in yttrium, neodymia, lanthanum sesquioxide, cerium oxide, luteium oxide.The transition metal carbide is concretely carbonized
Titanium or tungsten carbide.
With in propeller manufacturing process, its sample drying time in vacuum drying chamber is 48h-96h, drying temperature for the aviation
Spend is 35 DEG C -70 DEG C.Sintered under nitrogen protection in vacuum high temperature furnace, sintering temperature is 1720 DEG C -1800 DEG C, and heating rate is
0.5 DEG C/min-2 DEG C/min, the heat preservation sintering time is 1h-2h after in-furnace temperature reaches sintering temperature.The vacuum high temperature furnace domestic demand
Be fitted into graphite frock carries out burying burning in nitrogen atmosphere, is separated by buried powder between base substrate and graphite frock.The buried powder is nitridation
Silicon powder and the mixture of boron nitride powder, make to be uniformly heated in its intensification or temperature-fall period, are not likely to produce crackle.
The aviation is manufactured with propeller using silicon nitride ceramic material, its corrosion-and high-temp-resistant, with heat transfer higher
Rate, performance is more superior, is capable of achieving repeatedly to utilize, and greatly reduces launch cost.
During specific implementation, aviation of the invention with the raw material of the better embodiment of propeller one according to mass fraction it is each into
Distribution ratio is respectively：The rare earth oxide that 75 parts of beta-silicon nitride powder, 10 parts of aluminum oxide, yttria are constituted with cerium oxide mixes
4 parts of body, 1 part of titanium carbide, 4 parts of carbon fiber, 2 parts of polyvinyl alcohol, 4 parts of aluminium nitride, additionally, being additionally added 1.5 times of amounts of beta-silicon nitride powder
Deionized water.
During specific implementation, aviation of the invention is each according to mass fraction in the raw material with the another better embodiment of propeller
Composition proportion can also be respectively：80 parts of beta-silicon nitride powder, 6 parts of aluminum oxide, the rare earth oxide mixture 4 of yttria composition
Part, 1.5 parts of titanium carbide, 2.5 parts of carbon fiber, 2 parts of polyvinyl alcohol, 4 parts of aluminium nitride, additionally, being additionally added 1.5 times of amounts of beta-silicon nitride powder
Deionized water.
During specific implementation, aviation of the invention is each according to mass fraction in the raw material with the another better embodiment of propeller
Composition proportion can also be respectively：90 parts of beta-silicon nitride powder, 2 parts of aluminum oxide, the rare earth oxide mixture 3 of yttria composition
Part, 0 part of titanium carbide, 3 parts of carbon fiber, 2 parts of polyvinyl alcohol, 0 part of aluminium nitride, additionally, being additionally added going for 1.5 times of amounts of beta-silicon nitride powder
Ionized water.
As shown in figure 4, the present invention also provides the manufacture method of aviation propeller, it comprises the following steps：
The first step, 48h-96h is dried by the base substrate of aviation propeller sample in vacuum drying chamber, and drying temperature is 35
DEG C -70 DEG C, the idiosome is made up of above-mentioned raw materials；
Second step, the sample after drying is sintered in the vacuum high temperature furnace under nitrogen protection, and sintering temperature is 1720 DEG C-
1800 DEG C, heating rate is 0.5 DEG C/min-2 DEG C/min, and the heat preservation sintering time is 1h-2h after in-furnace temperature reaches sintering temperature.
Vacuum high temperature furnace domestic demand in the sintering is fitted into graphite frock to be carried out burying burning in nitrogen atmosphere, is led between base substrate and graphite frock
Buried powder is crossed to separate.
The manufacturing process of the aviation propeller realizes the sintering of large-size ceramic product, it is ensured that it is in sintering process
Do not rupture.
Presently preferred embodiments of the present invention is the foregoing is only, is not intended to limit the invention, it is all in essence of the invention
Within god and principle, any modification, equivalent substitution and improvements made etc. should be included within the scope of the present invention.
Claims (10)
1. a kind of aviation propeller, it is characterised in that：The raw material of the aviation propeller is matched somebody with somebody according to each composition of mass fraction
Than being respectively：Beta-silicon nitride powder 75-90 parts, metal oxide 2-10 parts, 3-10 parts of rare earth oxide mixture, transition metal carbon
Compound 0-2 parts, carbon fiber 2.5-5 parts, 2 parts of polyvinyl alcohol, aluminium nitride 0-4 parts, also added in the raw material of the aviation propeller
There are 1.5 times of deionized waters of amount of beta-silicon nitride powder.
2. aviation propeller as claimed in claim 1, it is characterised in that：The metal oxide is aluminum oxide or oxidation
Magnesium, the transition metal carbide is titanium carbide or tungsten carbide.
3. aviation propeller as claimed in claim 1, it is characterised in that：The rare earth oxide mixture is three oxidations two
At least one in yttrium, neodymia, lanthanum sesquioxide, cerium oxide, luteium oxide.
4. aviation propeller as claimed in claim 1, it is characterised in that：Match somebody with somebody according to each composition of mass fraction in the raw material
Than being respectively：The rare earth oxide mixture 4 of 75 parts of beta-silicon nitride powder, 10 parts of aluminum oxide, yttria and cerium oxide composition
Part, 1 part of titanium carbide, 4 parts of carbon fiber, 2 parts of polyvinyl alcohol, 4 parts of aluminium nitride are also added with nitridation in the raw material of aviation propeller
1.5 times of deionized waters of amount of silicon powder.
5. aviation propeller as claimed in claim 1, it is characterised in that：Match somebody with somebody according to each composition of mass fraction in the raw material
Than being respectively：80 parts of beta-silicon nitride powder, 6 parts of aluminum oxide, 4 parts of rare earth oxide mixture, the titanium carbide of yttria composition
1.5 parts, 2.5 parts of carbon fiber, 2 parts of polyvinyl alcohol, 4 parts of aluminium nitride is also added with silicon nitride powder in the raw material of aviation propeller
1.5 times of deionized waters of amount of body.
6. aviation propeller as claimed in claim 1, it is characterised in that：Match somebody with somebody according to each composition of mass fraction in the raw material
Than being respectively：90 parts of beta-silicon nitride powder, 2 parts of aluminum oxide, 3 parts of rare earth oxide mixture, the titanium carbide 0 of yttria composition
Part, 3 parts of carbon fiber, 2 parts of polyvinyl alcohol, 0 part of aluminium nitride are also added with beta-silicon nitride powder 1.5 in the raw material of aviation propeller
The deionized water measured again.
7. aviation propeller according to any one of claims 1 to 6, it is characterised in that：The aviation propeller system
During making, its sample drying time in vacuum drying chamber is 48h-96h, and drying temperature is 35 DEG C -70 DEG C.
8. aviation propeller as claimed in claim 7, it is characterised in that：The aviation with propeller manufacturing process, its
Sample is sintered under nitrogen protection in vacuum high temperature furnace, and sintering temperature is 1720 DEG C -1800 DEG C, and heating rate is 0.5 DEG C/min-
2 DEG C/min, the heat preservation sintering time is 1h-2h after in-furnace temperature reaches sintering temperature.
9. aviation propeller as claimed in claim 8, it is characterised in that：The vacuum high temperature furnace domestic demand loads graphite frock
Carry out burying burning in nitrogen atmosphere, separated by buried powder between base substrate and graphite frock.
10. a kind of manufacture method of aviation propeller, it comprises the following steps：
The first step, 48h-96h is dried by the base substrate of aviation propeller sample in vacuum drying chamber, and drying temperature is 35 DEG C-
70 DEG C, the idiosome is made up of any one in claim 1 to 6；
Second step, the sample after drying is sintered under nitrogen protection in vacuum high temperature furnace, and sintering temperature is 1720 DEG C -1800
DEG C, heating rate is 0.5 DEG C/min-2 DEG C/min, and the heat preservation sintering time is 1h-2h after in-furnace temperature reaches sintering temperature.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710043293.5A CN106747524B (en) | 2017-01-19 | 2017-01-19 | Propeller for aviation and manufacturing method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710043293.5A CN106747524B (en) | 2017-01-19 | 2017-01-19 | Propeller for aviation and manufacturing method thereof |
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| CN106747524A true CN106747524A (en) | 2017-05-31 |
| CN106747524B CN106747524B (en) | 2020-06-30 |
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| CN201710043293.5A Active CN106747524B (en) | 2017-01-19 | 2017-01-19 | Propeller for aviation and manufacturing method thereof |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111393170A (en) * | 2020-03-19 | 2020-07-10 | 西安澳秦新材料有限公司 | Method for preparing high-density silicon nitride ceramic through multi-factor optimization and prepared silicon nitride ceramic |
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|---|---|---|---|---|
| US4596781A (en) * | 1985-08-30 | 1986-06-24 | Rockwell International Corporation | Tough Si3 N4 composite ceramics |
| CN1063744A (en) * | 1991-01-29 | 1992-08-19 | 王勤兴 | Ceramic rotary piston ingine |
-
2017
- 2017-01-19 CN CN201710043293.5A patent/CN106747524B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4596781A (en) * | 1985-08-30 | 1986-06-24 | Rockwell International Corporation | Tough Si3 N4 composite ceramics |
| CN1063744A (en) * | 1991-01-29 | 1992-08-19 | 王勤兴 | Ceramic rotary piston ingine |
Non-Patent Citations (2)
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| 杨亮亮等: "气压烧结氮化硅陶瓷的研究与应用进展", 《陶瓷学报》 * |
| 车剑飞等: "《复合材料及其工程应用》", 31 August 2006 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111393170A (en) * | 2020-03-19 | 2020-07-10 | 西安澳秦新材料有限公司 | Method for preparing high-density silicon nitride ceramic through multi-factor optimization and prepared silicon nitride ceramic |
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| CN106747524B (en) | 2020-06-30 |
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