CN110076292B - Investment casting method for duplex block casting directional solidification turbine guide blade - Google Patents
Investment casting method for duplex block casting directional solidification turbine guide blade Download PDFInfo
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- CN110076292B CN110076292B CN201910448470.7A CN201910448470A CN110076292B CN 110076292 B CN110076292 B CN 110076292B CN 201910448470 A CN201910448470 A CN 201910448470A CN 110076292 B CN110076292 B CN 110076292B
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- core
- directional solidification
- turbine guide
- blade
- guide vane
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C7/00—Patterns; Manufacture thereof so far as not provided for in other classes
- B22C7/02—Lost patterns
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C9/00—Moulds or cores; Moulding processes
- B22C9/02—Sand moulds or like moulds for shaped castings
- B22C9/04—Use of lost patterns
- B22C9/043—Removing the consumable pattern
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C9/00—Moulds or cores; Moulding processes
- B22C9/08—Features with respect to supply of molten metal, e.g. ingates, circular gates, skim gates
- B22C9/082—Sprues, pouring cups
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C9/00—Moulds or cores; Moulding processes
- B22C9/10—Cores; Manufacture or installation of cores
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C9/00—Moulds or cores; Moulding processes
- B22C9/22—Moulds for peculiarly-shaped castings
Abstract
The invention relates to a investment casting method of a duplex block casting directional solidification turbine guide vane, which comprises the steps of preparing a ceramic core, putting the ceramic core into an appearance mould to press a vane wax mould, coating a mould shell after mould assembly, dewaxing and roasting, then smelting, casting, shelling, depoling and cutting off the redundant part of a runner.
Description
Technical Field
The invention discloses an investment casting method of a duplex block casting directional solidification turbine guide vane, and belongs to the technical field of investment precision casting of high-temperature alloy.
Background
The increase of the temperature before the turbine is very important for the increase of the thrust-weight ratio of the engine, and the guide blade of the high-pressure turbine directly bears the impact of high-temperature gas, thereby putting high requirements on the temperature bearing capacity and the reliability of the guide blade. On one hand, the improvement of the temperature bearing capacity comes from the optimization of alloy components and microscopic structures, and compared with the traditional isometric crystal blade, the columnar crystal eliminates a transverse crystal boundary which is easy to generate cracks, so that the fatigue performance of the blade is greatly improved; on the other hand, the method is derived from the optimization of structural design, and comprises a gas film cooling mode of a hollow inner cavity and a multi-cast structure for realizing the accurate control of the areas of a channel point and a throat.
A high-pressure turbine guide vane belongs to a directional solidification columnar crystal vane with a duplex integral casting structure, and the appearance of the high-pressure turbine guide vane consists of a vane body (duplex), an inner edge plate and an outer edge plate. The traditional preparation process mainly adopts a flange plate seeding mode, has limited control capacity on the growth of blade grains, and is easy to generate metallurgical defects such as air inlet edge transverse grain boundary, air outlet edge outcrop crystal, mixed crystal, crystal orientation deviation and the like when the solidification process is influenced by external factor fluctuation. In addition, the seeding strips of the traditional edge plate seeding mode are large in number and too close in distance, so that the local drying condition of the shell is poor, and impurity rejection of the blade is easily caused. Therefore, the research on the preparation process of the duplex integral casting hollow guide blade to improve the qualified rate of the blade casting is a problem to be solved in the technical field of precision investment casting at present.
Disclosure of Invention
The invention aims to provide a investment casting method of a duplex integral casting directional solidification turbine guide vane aiming at the problems of metallurgical defects of inclusion, looseness, mixed crystals, transverse grain boundaries, outcrop crystals, crystal orientation deviation and the like, size problems of wall thickness ultra-difference and the like existing in the existing preparation process of the duplex integral casting hollow turbine guide vane, and aims to improve the qualification rate and the production efficiency of the vane and shorten the development and production period of the vane.
The technical solution of the invention is as follows:
the investment casting method of the duplex block casting directional solidification turbine guide vane comprises the steps of preparing a ceramic core, putting the ceramic core into an outline mold to press a vane wax mold, coating a shell after mold assembly, dewaxing, roasting, smelting, pouring, unshelling, depoling and cutting off the redundant part of a pouring channel, and is characterized in that:
a. when the ceramic core is prepared, firstly pressing and sintering a cold core which has the same shape with the ceramic core and the circumferential dimension which is smaller than the design dimension of the ceramic core, and then covering and sintering a layer of shell outside the cold core to form a complete ceramic core;
b. the combined mould comprises a sprue cup 1, a cross pouring channel 2, a blade wax mould, a seeding section 3, a disc 4, a feeding rectangular strip 5, a feeding bent sheet 6, a feeding sheet connecting pouring channel 7 and an exhaust edge wax sheet 8, wherein the blade wax mould comprises a blade body 9, an inner edge plate 10 and an outer edge plate 11; the sprue cup is characterized in that a horizontal runner 2 is connected to the lower plane of the sprue cup 1, the horizontal runner 2 is communicated with a blade wax mold inner edge plate 10 mounting edge through a feeding rectangular strip 5, a disc 4 located at the bottom wraps a core head of a core through a crystal guiding section 3 and then is connected with a blade wax mold outer edge plate 11, then a square positioning end with the side length of 2-5 mm or a circular positioning end with the diameter of 2-5 mm is dug at the basin side and the back side of the core head of the core respectively, a feeding bent piece 6 is identical to the bending shape of a blade body 9 and is arranged between two blade bodies 9 and connected with an outer edge plate 11 below the feeding bent piece, the two ends of the feeding bent piece 6 are connected with the runner 7 through the feeding piece and communicated with the inner edge plate 10 mounting edge, and an exhaust edge wax piece 8 is connected with the inner edge plate 10 and the outer edge plate 11 mounting edge at the corresponding position of each exhaust.
Furthermore, the circumferential size of the cold core is 0.5-2 mm smaller than the design size of the ceramic core.
Further, the material of the cold core is the same as the ceramic slurry used for preparing the ceramic core shell.
Further, the thickness of the seeding section 3 wrapping the core head of the core is 0.5-2 mm.
Further, the thickness of the feeding bent sheet 6 is 1-5 mm, the height is 5-20 mm, and the length is 10-50 mm.
Furthermore, the width of the exhaust edge wax sheet 8 is 3-20 mm, and the thickness is 1-5 mm.
Further, the blade body 9, the inner edge plate 10 and the outer edge plate 11 in the blade wax mold are integrally injection molded, the injection temperature is 63-70 ℃, the injection pressure is 6-10 bar, the injection time is 10-30 s, and the pressure maintaining time is 20-60 s.
Further, the material for preparing the shell is Al2O3-SiO2Is a ceramic shell material, and the number of coating layers is controlled to be 5-8.
Further, the master alloy adopted in the investment casting of the double-block casting turbine guide blade is a directional solidification high-temperature alloy.
Further, in the smelting and pouring process, a high-temperature gradient vacuum directional solidification furnace is adopted, the temperature of an upper heater is 1480-1510 ℃, the temperature of a lower heater is 1490-1520 ℃, the heat preservation time of the shell is 10-30 min, the pouring temperature is 1480-1520 ℃, and the drawing speed is 3-8 mm/min.
The invention has the beneficial effects that:
aiming at the turbine guide blade with the maximum size of the inner cavity in the thickness direction being larger than 8mm, in order to realize the accurate control of the size of the inner cavity, a cold core needs to be firstly pressed in the preparation process of the core, the size of the cold core is 0.5-2 mm smaller than the single side of the core, and then the cold core is placed into a core mould to press a ceramic core so as to control the size shrinkage of the core, so that a foundation is provided for the accurate control of the wall thickness size.
The blade wax mold adopts a wax pressing machine injection molding mode, the injection temperature is controlled to be 63-70 ℃ in the pressing process, the injection pressure is 6-10 bar, the injection time is 10-30 s, and the pressure maintaining time is 20-60 s, so that the wall thickness and the dimensional accuracy of the wax mold can be effectively guaranteed while the ceramic core is prevented from being broken. According to the grain size control requirement of the oriented columnar crystals, a module combination mode in the vertical direction is adopted, a feeding sheet and a pouring channel are connected in a channel region between two blades, and loosening, impurities and the like in the channel region are led to a feeding structure, so that the generation of metallurgical defects can be effectively avoided, and the casting qualification rate of the blades is greatly improved. The seeding mode is 'outer edge plate side core head seeding', the seeding distance of the blade body is shorter and more direct by adopting a wrapping type seeding structure design, so that the seeding efficiency is higher, the occurrence probability of abnormal grains such as transverse grain boundaries, outcrop crystals, large-angle grain boundaries and the like of the blade body can be obviously reduced, and meanwhile, compared with the traditional edge plate seeding mode, the seeding structure in a local space has a simple shape and a smaller number, so that the relative distance of the seeding structure is larger, the drying consistency and uniformity of a ceramic shell are facilitated, and the steel leakage rate of the shell is reduced by 30%. In conclusion, the application of the technology in the invention provides powerful guarantee for scientific research and production and provides technical support for multi-connection integral casting of large-size hollow blades.
Drawings
FIG. 1 is a schematic view of a turbine guide vane wax mold module with a duplex block casting structure. In the figure:
detailed description of the preferred embodiments
The technical solution of the present invention will be further described in detail with reference to the accompanying drawings and examples:
example 1
When the ceramic core is prepared, firstly pressing and sintering a ceramic core which has the same appearance with the ceramic core and the circumferential dimension which is 0.5mm smaller than the design dimension of the ceramic core, then presetting the ceramic core in a core mould, pressing a shell outside a cold core, and forming the complete ceramic core after sintering; the material of the cold core is the same as the ceramic slurry used for preparing the ceramic core shell;
pressing a blade wax mold after the ceramic core is subjected to the manufacturing strive, wherein the feeding bent sheet 6 is a wedge-shaped block which is 30mm long, 10mm high and has the thickness of being transited from 1mm to 3 mm;
the thickness of the crystal-leading section 3 wrapping the core head of the core is 0.5-2 mm;
the width of the exhaust edge wax sheet 8 is 5mm, and the thickness is 3 mm;
the blade body 9, the inner edge plate 10 and the outer edge plate 11 in the blade wax mold are integrally formed by injection, the injection temperature is 63-70 ℃, the injection pressure is 6-10 bar, the injection time is 10-30 s, and the pressure maintaining time is 20-60 s.
The wax pattern combination mode used by the invention is shown in figure 1, the lower plane of a sprue cup 1 is connected with a horizontal runner 2, the horizontal runner 2 is communicated with the mounting edge of an inner edge plate 10 of a blade wax pattern through a feeding rectangular strip 5, a disc 4 positioned at the bottom wraps a core head of a core through a crystal leading section 3 and then is connected with an outer edge plate 11 of the blade wax pattern, then a square positioning end with the side length of 2 mm-5 mm or a round positioning end with the diameter of 2 mm-5 mm is dug at the basin side and the back side of the core head of the core, a feeding bent plate 6 and a blade body 9 are in the same bending shape and are arranged between two blade bodies 9 and connected with the outer edge plate 11 below, the two ends of the feeding bent plate 6 are communicated with the mounting edge of the inner edge plate 10 through feeding plate connecting runners 7, and an exhaust edge wax plate 8 is connected with the mounting edge of the inner edge plate 10 and the outer edge plate 11 at the corresponding position of.
The material for preparing the shell is Al2O3-SiO2Is made of ceramic shell material, the number of the shell coating layers is 5, and finallyAnd sealing slurry adopts surface layer slurry, and the shell is cleaned after dewaxing roasting to prepare pouring.
The smelting and casting equipment is a vacuum induction directional solidification furnace, the shell is kept warm for 10min after reaching the temperature, IC10 alloy is selected for refining at 1545 ℃, and then the temperature of an upper heater is controlled to 1510 ℃, the temperature of a lower heater is controlled to 1520 ℃, the casting temperature is controlled to 1520 ℃, and the drawing speed is controlled to 3 mm/min.
And (3) cleaning the shell of the cast by adopting high-pressure water after the cast is taken out of the furnace, cutting off a pouring gate, corroding the cast in a ferric trichloride hydrochloric acid aqueous solution, and checking that the grain size of the blade body meets the design requirement. Through surface visual inspection, fluorescent inspection and X-ray inspection, the blade has no metallurgical defects such as sand holes, inclusion, looseness and the like. The wall thickness of the casting is measured by an ultrasonic method, and the requirement of design size is met.
Example 2
Compared with embodiment 1, the difference of this embodiment is:
the size of the cold core is 2mm smaller than that of the single side of the core;
the feeding bent sheet (6) is a wedge-shaped block with the length of 20mm, the height of 15mm and the thickness of 2mm to 4 mm;
the width of the exhaust edge wax sheet (8) is 3mm, and the thickness is 2 mm;
the number of the shell coating layers is 8;
the smelting and casting equipment is a vacuum induction directional solidification furnace, the shell is kept warm for 30min after reaching the temperature, IC10 alloy is selected for refining at 1535 ℃, then the temperature of an upper heater is controlled to be 1480 ℃, the temperature of a lower heater is controlled to be 1490 ℃, the casting temperature is controlled to be 1480 ℃, and the drawing speed is controlled to be 8 mm/min.
And (3) cleaning the shell of the cast by adopting high-pressure water after the cast is taken out of the furnace, cutting off a pouring gate, corroding the cast in a ferric trichloride hydrochloric acid aqueous solution, and checking that the grain size of the blade body meets the design requirement. Through surface visual inspection, fluorescent inspection and X-ray inspection, the blade has no metallurgical defects such as sand holes, inclusion, looseness and the like. The wall thickness of the casting is measured by an ultrasonic method, and the requirement of design size is met.
Claims (10)
1. A method for investment casting of double integral casting directional solidification turbine guide vane comprises the steps of preparing a ceramic core, putting the ceramic core into a shape mould to press a vane wax mould, coating a shell after mould assembly, dewaxing, roasting, smelting, pouring, unshelling, depoling and cutting off the redundant part of a pouring channel, and is characterized in that:
a. when the ceramic core is prepared, firstly pressing and sintering a cold core which has the same appearance with the ceramic core and the circumferential dimension of which is smaller than the design dimension of the ceramic core, then placing the cold core in a core mould to press the wet ceramic core, and forming the complete ceramic core after sintering;
b. the die set comprises a sprue cup (1), a cross gate (2), a blade wax die, a crystal guiding section (3), a disc (4), a feeding rectangular strip (5), a feeding bent sheet (6), a feeding sheet connecting gate (7) and an exhaust edge wax sheet (8), wherein the blade wax die comprises a blade body (9), an inner edge plate (10) and an outer edge plate (11); the lower plane of the sprue cup (1) is connected with a horizontal runner (2), the horizontal runner (2) is communicated with the mounting edge of the inner edge plate (10) of the blade wax mould through a feeding rectangular strip (5), a disc (4) positioned at the bottom wraps the core head of the core through a crystal leading section (3) and then is connected with the outer edge plate (11) of the blade wax mould, then a square positioning end with the side length of 2 mm-5 mm or a round positioning end with the diameter of 2 mm-5 mm is dug at the basin side and the back side of the core head of the core, the feeding bent sheet (6) and the blade body (9) are in the same bending shape, and is arranged between the two blade bodies (9) and is connected with the outer edge plate (11) at the lower part, the two ends of the feeding bent sheet (6) are communicated with the mounting edge of the inner edge plate (10) through the feeding sheet connecting pouring gate (7), the exhaust edge wax sheet (8) is connected with the mounting edges of the inner edge plate (10) and the outer edge plate (11) at the corresponding positions of the respective exhaust edges of the duplex blades.
2. The investment casting method of a twin block casting directional solidification turbine guide vane according to claim 1, wherein: the circumferential size of the cold core is 0.5-2 mm smaller than the design size of the ceramic core.
3. The investment casting method of a twin block casting directional solidification turbine guide vane according to claim 1, wherein: the material of the cold core is the same as the ceramic slurry used for preparing the ceramic core shell.
4. The investment casting method of a twin block casting directional solidification turbine guide vane according to claim 1, wherein: the thickness of the crystal-leading section (3) wrapping the core head of the core is 0.5-2 mm.
5. The investment casting method of a twin block casting directional solidification turbine guide vane according to claim 1, wherein: the feeding bent sheet (6) has a thickness of 1-5 mm, a height of 5-20 mm and a length of 10-50 mm.
6. The investment casting method of a twin block casting directional solidification turbine guide vane according to claim 1, wherein: the width of the exhaust edge wax sheet (8) is 3-20 mm, and the thickness is 1-5 mm.
7. The investment casting method of a twin block casting directional solidification turbine guide vane according to claim 1, wherein: the blade body (9), the inner edge plate (10) and the outer edge plate (11) in the blade wax mold are integrally injection molded, the injection temperature is 63-70 ℃, the injection pressure is 6-10 bar, the injection time is 10-30 s, and the pressure maintaining time is 20-60 s.
8. The investment casting method of a twin block casting directional solidification turbine guide vane according to claim 1, wherein: the material for preparing the shell is Al2O3-SiO2Is a ceramic shell material, and the number of coating layers is controlled to be 5-8.
9. The investment casting method of a twin block casting directional solidification turbine guide vane according to claim 1, wherein: the master alloy adopted in the investment casting of the double-block casting turbine guide blade is a directional solidification high-temperature alloy.
10. The investment casting method of a twin block casting directional solidification turbine guide vane according to claim 1, wherein: in the smelting and pouring process, a high-temperature gradient vacuum directional solidification furnace is adopted, the temperature of an upper heater is 1480-1510 ℃, the temperature of a lower heater is 1490-1520 ℃, the heat preservation time of a shell is 10-30 min, the pouring temperature is 1480-1520 ℃, and the drawing speed is 3-8 mm/min.
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Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN111496190B (en) * | 2020-05-11 | 2021-10-15 | 中国航发北京航空材料研究院 | Module structure of pouring triple-block-casting directional solidification hollow guide vane |
| CN111618279B (en) * | 2020-06-24 | 2021-08-03 | 中国航发北京航空材料研究院 | Precision casting method for quintuplet directional columnar crystal blade |
| CN111940679B (en) * | 2020-09-17 | 2021-10-22 | 中国航发沈阳黎明航空发动机有限责任公司 | Design method of double-linkage directional hollow blade gating system |
| CN113070454A (en) * | 2021-03-16 | 2021-07-06 | 贵阳航发精密铸造有限公司 | Casting device and method for non-preferred orientation single crystal guide hollow blade |
| CN115283650B (en) * | 2022-07-14 | 2024-03-22 | 中国科学院金属研究所 | Method for preventing blade body of single crystal twin cast turbine guide blade from being mixed |
| CN115106482A (en) * | 2022-07-28 | 2022-09-27 | 中国科学院金属研究所 | Inner cavity forming and wall thickness size control process method for large-size hollow guide blade |
| CN115570105B (en) * | 2022-11-21 | 2023-05-05 | 中国航发四川燃气涡轮研究院 | Manufacturing method of double-wall turbine blade |
| CN116174649B (en) * | 2023-02-28 | 2024-04-16 | 中国航发北京航空材料研究院 | Preparation method of air inlet side precision casting for maintaining high-temperature alloy turbine guide vane |
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| CN105170909B (en) * | 2015-10-10 | 2017-11-14 | 贵阳中航动力精密铸造有限公司 | A kind of running gate system for hollow single crystal blade |
| CN105290337B (en) * | 2015-11-16 | 2017-07-25 | 沈阳黎明航空发动机(集团)有限责任公司 | A kind of concatermer blade casting method |
| CN106734907B (en) * | 2016-11-25 | 2018-11-30 | 中航动力股份有限公司 | A kind of directional solidification cylindrulite and single crystal blade casting method |
| CN107598097B (en) * | 2017-11-10 | 2020-04-10 | 东方电气集团东方汽轮机有限公司 | Wax mold combination of turbine guide blade and precision casting method thereof |
| CN108941455B (en) * | 2018-07-27 | 2020-08-14 | 沈阳中科三耐新材料股份有限公司 | Casting method of duplex turbine guide vane for gas turbine |
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