CN104289674B - Gas turbine cylindrulite guide vane casting method - Google Patents
Gas turbine cylindrulite guide vane casting method Download PDFInfo
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- CN104289674B CN104289674B CN201410574070.8A CN201410574070A CN104289674B CN 104289674 B CN104289674 B CN 104289674B CN 201410574070 A CN201410574070 A CN 201410574070A CN 104289674 B CN104289674 B CN 104289674B
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- blade
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- guide vane
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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
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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
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Abstract
The invention provides a kind of gas turbine cylindrulite guide vane casting method, manufacture a set of finish cast die group, including the formwork that from top to bottom order is arranged and chassis, described wax-pattern includes blade wax shell and upper and lower wax tire, two groups of seeding bars vertically arranged it are embedded with in blade wax shell, one of which upper end correspondence inner arc shroud, lower end correspondence outer arc shroud, another group upper end correspondence outer arc shroud, lower end flush with blade wax shell bottom surface；Being embedded with one group of seeding bar in lower wax tire, the cross section molded line around blade is vertically arranged；Under lacing wire boss C and D, it is lined with seeding section；Material molten is poured into finish cast die group；The formwork of pull finish cast die group, makes melt solidify along the reverse sequence in blade pull direction, forms cylindrulite.The gas turbine cylindrulite guide vane blade crystal grain that the present invention prepares is without brilliant and equiax crystal situation the most brilliant, disconnected, and blade interior is without loose, shrinkage cavity, and surface flawless, quality is good, efficiency is high, low cost, can large-scale use and popularization.
Description
Technical field
The present invention relates to the manufacture method of turbine guide blades, specifically, be the casting method of a kind of gas turbine cylindrulite guide vane.
Background technology
Along with government is to the energy and environmental problem pay attention to day by day, development heavy duty gas turbine energy source and power turbine technology efficient, cleaning occupies critical positions in national energy development strategy.Improving constantly of industrial gas turbine power, realizes by improving turbine initial temperature, needs the blade material using temperature capability the highest.The at present level of combustion gas initial temperature, nickel base superalloy selected the most without exception by the material of the high-temperature component such as turbine is dynamic, stator.Since the forties in 20th century, nickel base superalloy develops into directionally solidified superalloy, DS superalloy from wrought superalloy, cast superalloy, along with the development of precision casting process, the dynamic and static blade of turbine is developed to directional solidification cylindrulite blade from equiax crystal high-temperature alloy blades.
By high temperature alloy melt, by strictly controlling process of setting so that it is crystal grain, along blade principal direction of stress Parallel Growth, eliminates transverse grain boundaries, and this guide vane with bunchy columnar structure is referred to as cylindrulite blade, and its casting technique is referred to as directional solidification processes.Compared with common equiax crystal blade, cylindrulite blade has the following characteristics that (1) essentially eliminates crystal boundary on the direction be perpendicular to the principal axes of stress, and creep rupture strength is high；(2) casting is loose easily controllable；(3) vibration damping is effective；(4) there is not the low-cycle fatigue damage in physical significance；(5) thin-wall effect is little.
The direction of the column crystal of cylindrulite blade, size, average departure degree directly affect the performance of blade, are several the key technical indexes of directional solidification processes, comparatively speaking, the contour shape of moving vane is fairly simple, cylindrulite direction is single, and technology difficulty is less, has mature experience both at home and abroad；And heavy combustion engine guide vane size (see figure 1) big, complex-shaped, this guide vane is fan-shaped arc segment structure, there is integrally-built blade, inner arc shroud, outer arc shroud, the intrados of inner arc shroud has lacing wire boss A, B, having lacing wire boss C, D on the extrados of outer arc shroud, lacing wire boss A, B, C, D radially distribute；The cylindrulite direction of directional solidification is parallel with blade principal direction of stress.
How to control the direction of growth and the size of crystal grain, the average departure degree of columnar grain, technology difficulty is very big, there is no successfully precedent so far.
Summary of the invention
The purpose of the present invention, is to provide the casting method of a kind of heavy combustion engine cylindrulite guide vane, and the method uses near-net-shape directional solidification processes, can successfully cast out heavy combustion engine cylindrulite guide vane, and technique effect is excellent.
The technical solution adopted in the present invention is:
Gas turbine cylindrulite guide vane casting method, described guide vane is fan-shaped arc segment structure, there is integrally-built blade, inner arc shroud, outer arc shroud, the intrados of inner arc shroud has lacing wire boss A and B, having lacing wire boss C and D on the extrados of outer arc shroud, lacing wire boss A, B, C and D radially distribute；Its casting method is, manufacture a set of finish cast die group, this finish cast die group includes formwork and the chassis that from top to bottom order is arranged, described formwork includes blade wax shell and upper and lower wax tire, the inner space of described blade wax shell is divided into upper, middle, and lower part, upper part space is cup-like structure, as the cast gate of melt material；Tire of waxing is arranged in middle segment space, between lacing wire boss A and B, forms horizontal running channel；Lower part space profiles is consistent with the contour shape of guide vane, as the cast sizing space of guide vane；The orientation in this space is: on inner arc shroud occupies, and under outer arc shroud occupies, blade is placed in the middle and vertical；The lower wax fetus position is under lacing wire boss C and D；Two groups of seeding bars vertically arranged it are embedded with in blade wax shell, one of which is distributed in two circumferencial direction end faces of shroud, upper end correspondence inner arc shroud, lower end correspondence outer arc shroud, another component cloth flushes with blade wax shell bottom surface in two width end faces of outer arc shroud, upper end correspondence outer arc shroud, lower end；Being embedded with one group of seeding bar in lower wax tire, the cross section molded line around blade is vertically arranged；Under lacing wire boss C and D, it is lined with seeding section；
Cast guide vane as follows:
(1), by after prefabricated formwork roasting, it is combined into finish cast die group with chassis；
(2), material molten is poured into finish cast die group；
(3), the formwork of pull finish cast die group, make melt along blade pull direction reverse sequence solidify, formed cylindrulite.
In described step (1), the sintering temperature of formwork is 1450 DEG C,
In described step (2), melt cast temperature is 1550 DEG C, and the time of casting complete is 5～10 s.
In described step (3), pull formwork is divided into three sections, first with 15mm/min drawing velocity pull formwork, in order to fully select crystalline substance；Reducing drawing velocity subsequently is 12mm/min；Last drawing velocity is 8mm/min.
Have the beneficial effect that produced by the present invention
1. the present invention uses end wall seeding section, seeding bar and change drawing velocity to prepare directional solidification guide vane, the large scale produced, complex-shaped, near-net-shape orientation guide vane blade crystal grain is without brilliant and equiax crystal situation the most brilliant, disconnected, blade interior is without loose, shrinkage cavity, surface flawless；
2. directional solidification cylindrulite divergence is not more than 20 °, string position at least 5 column crystals in blade profile, and the average departure degree of column crystal is not more than 10 °；
3. use the method to further increase the qualification rate of near-net-shape directional solidification guide vane, be applied in the production process of other model heavy combustion engines and blade of aviation engine, produce bigger economic benefit.
Accompanying drawing explanation
Fig. 1 is heavy combustion engine stator schematic diagram
Fig. 2 is the enforcement schematic diagram of the present invention
Fig. 3 is guide vane outer end wall top view
Fig. 4 is for becoming drawing velocity crystal pulling schematic diagram
In figure, label represents: 1-cup, the horizontal running channel of 2-, the cast sizing space of 3-inner arc shroud, the cast sizing space of 4-blade, the cast sizing space of 5-outer arc shroud, 6-seeding section, 7.1-seeding bar, 7.2-seeding bar, 8-seeding bar, 9-water-cooled copper dish, 10-wax shell.
Detailed description of the invention
As shown in figures 1-4, the present invention is a kind of gas turbine cylindrulite guide vane casting method, this guide vane is fan-shaped arc segment structure, there is integrally-built blade, inner arc shroud, outer arc shroud, the intrados of inner arc shroud has lacing wire boss A and B, the extrados of outer arc shroud has lacing wire boss C and D.
Its casting method is, manufactures a set of finish cast die group, and this finish cast die group includes formwork and chassis (i.e. the water-cooled copper dish 9) that from top to bottom order is arranged.Formwork includes blade wax shell 10 and upper and lower wax tire, and the inner space of blade wax shell 10 is divided into upper, middle, and lower part, concrete:
The upper part space of blade wax shell 10 is cup-like structure, as the cup 1 of melt material.Tire of waxing is arranged in the middle segment space of wax shell 10, is arranged between lacing wire boss A and B, forms horizontal running channel 2；In this detailed description of the invention, tire of waxing is arranged between the top being arranged on lacing wire boss A and B.The lower part space profiles of wax shell 10 is consistent with the contour shape of guide vane, as the cast sizing space of guide vane.The orientation in the cast sizing space of this guide vane is: on the residence, cast sizing space 3 of inner arc shroud, and under the cast sizing space 5 of outer arc shroud occupies, the cast sizing space 4 of blade is placed in the middle and vertical.Lower wax tire is arranged in the lower part space of wax shell 10, is positioned under lacing wire boss C and D.
The topmost innovation of the present invention is, two groups of seeding bars 7 vertically arranged it are embedded with in wax shell 10, wherein: one group of seeding bar 7.1 is distributed in two circumferencial direction end faces of shroud, the cast sizing space 5 of the cast sizing space 3 of upper end correspondence inner arc shroud, lower end correspondence outer arc shroud；Another group seeding bar 7.2 is distributed in two width end faces of outer arc shroud, and the cast sizing space 5 of upper end correspondence outer arc shroud, lower end flush with the bottom surface of wax shell 10.Meanwhile, being embedded with one group of seeding bar 8 in lower wax tire, the cross section molded line around the cast sizing space 4 of blade is vertically arranged.It addition, under lacing wire boss C and D, be lined with seeding section 6 along the length direction of lacing wire boss C and D；
Cast guide vane as follows:
(1), by after prefabricated formwork roasting, it is combined into finish cast die group with chassis；Wherein, the sintering temperature of formwork is 1450 DEG C.
(2), material molten is poured into finish cast die group；Wherein, melt cast temperature is 1550 DEG C, and the time of casting complete is 5～10 s.
(3), the above-mentioned finish cast die group being cast with melt is placed on water-cooled copper dish 9, pull formwork 10, makes melt solidify along the reverse sequence in blade pull direction, form cylindrulite.Wherein, pull formwork 10 is divided into three sections, first with 15mm/min drawing velocity pull formwork 10, in order to fully select crystalline substance；Reducing drawing velocity subsequently is 12mm/min；Last drawing velocity is 8mm/min.
Embodiment 1
A kind of large scale, complex-shaped, the preparation method of near-net-shape orientation guide vane.This guide vane total length 170mm, blade length 100mm, design finish cast die group according to Fig. 4, crystal pulling is highly 220mm.Using EC95 to prepare formwork, the sintering temperature of formwork is 1450 DEG C, and pouring temperature is 1550 DEG C, and the casting complete time is 5～10 s.After casting complete, from the bottom to top, first with the drawing velocity pull formwork 1020mm of 15mm/min, in order to fully select crystalline substance；Subsequently with the drawing velocity pull formwork 40mm of 12mm/min；Finally with the drawing velocity pull formwork 160mm of 8mm/min, formwork is stretched complete.
Embodiment 2
The preparation method of certain 1 grade of directional columnargrain guide vane of combustion engine near-net-shape.This guide vane total length 181mm, blade length 77mm, design finish cast die group according to Fig. 4, crystal pulling is highly 230mm.Using EC95 to prepare formwork, the sintering temperature of formwork is 1500 DEG C, and pouring temperature is 1550 DEG C, and the casting complete time is 5～10 s.After casting complete, from the bottom to top, first with 20mm/min drawing velocity pull shell, in order to fully select crystalline substance；Reducing drawing velocity subsequently is 10mm/min；Last drawing velocity is 8mm/min.
Embodiment 3
The preparation method of certain 1 grade of directional columnargrain guide vane of combustion engine near-net-shape.This guide vane total length 290mm, blade length 180mm, design finish cast die group according to Fig. 4, crystal pulling is highly 330mm.Using EC95 to prepare formwork, the sintering temperature of formwork is 1500 DEG C, and pouring temperature is 1500 DEG C, and the casting complete time is 5～10 s.After casting complete, from the bottom to top, first with 20mm/min drawing velocity pull shell, in order to fully select crystalline substance；Reducing drawing velocity subsequently is 10mm/min；Last drawing velocity is 8mm/min.
Claims (1)
1. gas turbine cylindrulite guide vane casting method, described guide vane is fan-shaped arc segment structure, have integrally-built blade,
Inner arc shroud, outer arc shroud,
Having lacing wire boss A and B on the intrados of inner arc shroud, have lacing wire boss C and D on the extrados of outer arc shroud, lacing wire boss A, B, C and D radially distribute；Its casting method is, manufacture a set of finish cast die group, this finish cast die group includes formwork and the chassis that from top to bottom order is arranged, described formwork includes blade wax shell and upper and lower wax tire, it is characterized in that, the inner space of described blade wax shell is divided into upper, middle, and lower part, upper part space to be cup-like structure, as the cast gate of melt material；Tire of waxing is arranged in middle segment space, between lacing wire boss A and B, forms horizontal running channel；Lower part space profiles is consistent with the contour shape of guide vane, as the cast sizing space of guide vane；The orientation in this space is:
On inner arc shroud occupies, under outer arc shroud occupies, blade is placed in the middle and vertical；The lower wax fetus position is under lacing wire boss C and D；Being embedded with two groups of seeding bars vertically arranged in blade wax shell, one of which is distributed in two circumferencial direction end faces of shroud, and upper end is corresponding
Inner arc shroud, lower end correspondence outer arc shroud, another component cloth flushes with blade wax shell bottom surface in two width end faces of outer arc shroud, upper end correspondence outer arc shroud, lower end；Being embedded with one group of seeding bar in lower wax tire, the cross section molded line around blade is vertically arranged；Under lacing wire boss C and D, it is lined with seeding section；
Cast guide vane as follows:
(1), by after prefabricated formwork roasting, it is combined into finish cast die group with chassis；Wherein, the sintering temperature of formwork is 1450 DEG C；
(2), material molten is poured into finish cast die group；Wherein, melt cast temperature is 1550 DEG C, and the time of casting complete is 5～10s；
(3), the formwork of pull finish cast die group, make melt along blade pull direction reverse sequence solidify, formed cylindrulite, pull formwork is divided into three sections；Wherein, first with 15mm/min drawing velocity pull formwork, in order to fully select crystalline substance；Reducing drawing velocity subsequently is 12mm/min；Last drawing velocity is 8mm/min.
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN106270392A (en) * | 2015-05-25 | 2017-01-04 | 西安航空动力股份有限公司 | A kind of manufacture method of single crystal super alloy working-blade |
| CN105108061A (en) * | 2015-09-30 | 2015-12-02 | 东方电气集团东方汽轮机有限公司 | Method of eliminating stray grain defect in single crystal blade |
| CN105855468A (en) * | 2016-04-13 | 2016-08-17 | 东方电气集团东方汽轮机有限公司 | Ceramic shell manufacturing method and method for manufacturing ceramic shell of turbine blade |
| CN105798230A (en) * | 2016-04-26 | 2016-07-27 | 东方电气集团东方汽轮机有限公司 | Wax mould module for casting gas turbine blades and assembling method thereof |
| CN108097909B (en) * | 2016-11-25 | 2020-06-16 | 中国科学院金属研究所 | Process method for eliminating recrystallization of single crystal high-temperature alloy casting |
| CN107745093B (en) * | 2017-12-06 | 2023-06-06 | 安徽应流航源动力科技有限公司 | Fine casting module and casting method for preparing nickel-based single crystal guide vane with precisely controllable crystal orientation by utilizing fine casting module |
| CN109513881B (en) * | 2018-11-27 | 2020-10-27 | 安徽应流航源动力科技有限公司 | Casting method of monocrystalline high-temperature alloy blade capable of precisely controlling three-dimensional crystal orientation |
| 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 |
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| US3690368A (en) * | 1970-08-14 | 1972-09-12 | United Aircraft Corp | Casting single crystal articles |
| JP3004451B2 (en) * | 1992-02-06 | 2000-01-31 | 三菱重工業株式会社 | Manufacturing method of precision casting blade |
| CN1317095C (en) * | 2004-02-25 | 2007-05-23 | 中国科学院金属研究所 | Crystalloid laminae composited from single crystal and directional column crystal and preparing method |
| CN103143678B (en) * | 2013-04-01 | 2015-02-18 | 东方电气集团东方汽轮机有限公司 | Formwork for optimizing directional columnar crystal structure of high-temperature alloy blade |
| CN103192063B (en) * | 2013-04-01 | 2015-03-11 | 东方电气集团东方汽轮机有限公司 | Casting mold for producing high-temperature alloy single crystal blades and directional solidification device thereof |
| CN103861999B (en) * | 2014-03-26 | 2015-11-25 | 东方电气集团东方汽轮机有限公司 | Improve the method for cavity ceramic shell mould deformation of bottom in directional solidification processes |
| CN103894546B (en) * | 2014-03-26 | 2016-03-23 | 东方电气集团东方汽轮机有限公司 | The casting method of the concavo-convex intricate casting in end |
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