CN108941459A - A method of it is loose to reduce combustion engine turbine blade - Google Patents
A method of it is loose to reduce combustion engine turbine blade Download PDFInfo
- Publication number
- CN108941459A CN108941459A CN201811032442.9A CN201811032442A CN108941459A CN 108941459 A CN108941459 A CN 108941459A CN 201811032442 A CN201811032442 A CN 201811032442A CN 108941459 A CN108941459 A CN 108941459A
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- combustion engine
- blade
- engine turbine
- turbine blade
- formwork
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Links
- 238000002485 combustion reaction Methods 0.000 title claims abstract description 62
- 238000000034 method Methods 0.000 title claims abstract description 25
- 239000000919 ceramic Substances 0.000 claims abstract description 66
- 238000009415 formwork Methods 0.000 claims abstract description 51
- 210000002268 wool Anatomy 0.000 claims abstract description 42
- 229910000831 Steel Inorganic materials 0.000 claims abstract description 41
- 239000010959 steel Substances 0.000 claims abstract description 41
- 238000009288 screen filtration Methods 0.000 claims abstract description 6
- 229910045601 alloy Inorganic materials 0.000 claims description 12
- 239000000956 alloy Substances 0.000 claims description 12
- 229910000838 Al alloy Inorganic materials 0.000 claims description 7
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 claims description 6
- 238000001354 calcination Methods 0.000 claims description 6
- 238000002844 melting Methods 0.000 claims description 6
- 230000008018 melting Effects 0.000 claims description 6
- 229910052710 silicon Inorganic materials 0.000 claims description 6
- 239000010703 silicon Substances 0.000 claims description 6
- 239000007788 liquid Substances 0.000 claims description 4
- 238000007670 refining Methods 0.000 claims 2
- 238000001914 filtration Methods 0.000 description 7
- 238000005495 investment casting Methods 0.000 description 3
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 2
- 238000005266 casting Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000007689 inspection Methods 0.000 description 2
- 238000007711 solidification Methods 0.000 description 2
- 230000008023 solidification Effects 0.000 description 2
- 229910000851 Alloy steel Inorganic materials 0.000 description 1
- 229920000742 Cotton Polymers 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000004615 ingredient Substances 0.000 description 1
- 230000005764 inhibitory process Effects 0.000 description 1
- 229910052759 nickel Inorganic materials 0.000 description 1
- 229910052573 porcelain Inorganic materials 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 229910000601 superalloy Inorganic materials 0.000 description 1
Classifications
-
- 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
-
- 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
- B22C9/088—Feeder heads
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
- B22D27/00—Treating the metal in the mould while it is molten or ductile ; Pressure or vacuum casting
- B22D27/04—Influencing the temperature of the metal, e.g. by heating or cooling the mould
- B22D27/045—Directionally solidified castings
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a kind of methods that reduction combustion engine turbine blade is loose, the following steps are included: 1) prepare combustion engine turbine blade wax mould, wherein, the riser height of combustion engine turbine blade wax mould is the 1/5~1/6 of combustion engine turbine vane overall length, then prepares turbo blade formwork by combustion engine turbine blade wax mould；2) three layers of ceramic wool are wrapped up around turbo blade formwork, wherein, first layer ceramic wool is between ceramic pouring cup lower end and riser, and between ceramic pouring cup lower end and 1/3 blade, third layer ceramic wool is located at ceramics and burns between cup lower end and 2/3 blade second layer ceramic wool；It 3) will treated that turbo blade formwork roasts through step 2)；4) molten steel is prepared, then molten steel is poured into after filter screen filtration in turbo blade formwork, turbo blade formwork is then removed, then is cut, obtains combustion engine turbine blade, is formed at this method can be avoided blade and listrium is transferred R loose.
Description
Technical field
The invention belongs to precision casting technology fields, are related to a kind of method that reduction combustion engine turbine blade is loose.
Background technique
Large scale turbo blade is the key core component of heavy duty gas turbine, mainly using nickel base superalloy without surplus
Hot investment casting is made.The power blade is the rotatable parts of high temperature, high speed, top load, and working environment is severe, thermic load and power
Load is big, and operating condition is very harsh.Cast nickel-base alloy ingredient complex, solidification temperature range is wider, solidifies branch
Crystalline substance has inhibition than more developed, to interdendritic feeding, and loose formability is high.
Such blade construction is complicated, is made of big tenon frame structure, blade and inframarginal.Blade size is big, and wall thickness is thin,
It is about 200mm~245mm, chord width is 75mm~85mm, maximum gauge about 13mm, and the wide about 50mm of listrium, and tenon thickness is about
40mm.Since the Feeding channel of blade is too long, and tenon and blade thickness great disparity are big, and blade is caused to close in process of setting high temperature
Golden liquid feeding is insufficient, is unfavorable for the timely feeding in each section of blade, so as to cause blade section microporosity, and in blade and edge
Plate switching R place easily formed it is loose, this become restriction the blade hot investment casting of high temperature alloy combustion engine turbine key technology.
Summary of the invention
It is an object of the invention to overcome the above-mentioned prior art, it is loose to provide a kind of reduction combustion engine turbine blade
Method, this method can be avoided blade and listrium switching R at formed it is loose.
In order to achieve the above objectives, it is of the present invention reduce the loose method of combustion engine turbine blade the following steps are included:
1) combustion engine turbine blade wax mould is prepared, wherein the riser height of combustion engine turbine blade wax mould is combustion engine turbine blade
The 1/5~1/6 of overall length, then turbo blade formwork is prepared by combustion engine turbine blade wax mould；
2) three layers of ceramic wool are wrapped up around turbo blade formwork, wherein first layer ceramic wool is located at ceramic pouring cup lower end
Between riser, between ceramic pouring cup lower end and 1/3 blade, third layer ceramic wool is located at ceramics and burns second layer ceramic wool
Between cup lower end and 2/3 blade；
It 3) will treated that turbo blade formwork roasts through step 2)；
4) molten steel is prepared, then molten steel is poured into after filter screen filtration in turbo blade formwork, then removes turbo blade
Formwork, then cut, obtain combustion engine turbine blade.
Turbo blade formwork is prepared using transfer matic total silicon colloidal sol by combustion engine turbine blade wax mould in step 1).
The thickness of each layer ceramic wool is 6mm.
The concrete operations of step 3) are as follows: will treated that turbo blade formwork is put into roaster roasts through step 2)
It burns, wherein maturing temperature is 1000 DEG C~1075 DEG C, and calcining time is more than or equal to 2h.
The concrete operations of molten steel are prepared in step 4) are as follows:
Alloy is subjected to melting, obtains molten steel, then the temperature of molten steel is adjusted to more than aluminium alloy liquidus temperature 230 DEG C, and
3min~5min is refined, its temperature is then reduced to 150 DEG C~170 DEG C of aluminium alloy liquidus temperature or more, obtains molten steel.
In the environment of vacuum degree is less than or equal to 1.33Pa, molten steel is poured into turbo blade formwork after filter screen filtration
In, wherein pour the angle of incidence less than or equal to 4s, and turbo blade formwork since taken out in roaster pour between molten steel when
Between interval be less than or equal to 3min.
The invention has the following advantages:
The combustion engine turbine blade loose method of the present invention that reduces surrounds turbo blade formwork packet when specific operation
Wrap up in three layers of ceramic wool, wherein for first layer ceramic wool between ceramic pouring cup lower end and riser, second layer ceramic wool is located at pottery
Between porcelain sprue cup lower end and 1/3 blade, third layer ceramic wool is located at ceramics and burns between cup lower end and 2/3 blade, i.e. turbine
Blade formwork sequentially forms three layers of ceramic wool, two-layer ceramic cotton, one layer of ceramic wool and zero layer ceramic wool from top to bottom, so as to improve
The type of cooling of turbo blade effectively eliminates turbo blade blade and listrium switching R to realize the consecutive solidification of turbo blade
That locates is loose, reduces the microporosity in turbo blade section, turbo blade casting is made to meet the requirement of design drawing.
Further, liquid steel temperature is reduced to 150 DEG C~170 DEG C of aluminium alloy liquidus temperature or more, molten steel is obtained, then by steel
Liquid is poured into after filtering in turbo blade formwork, thus avoid pouring temperature it is too high or too low caused by microporosity and loose
Excessively.
Detailed description of the invention
Fig. 1 a is the fluorescent inspection result figure of existing combustion engine turbine blade leaf dish side；
Fig. 1 b is the fluorescent inspection result figure of existing combustion engine turbine blade and blade back side；
Fig. 2 is the structural schematic diagram of turbo blade formwork in the present invention；
Fig. 3 is the location drawing of three layers of ceramic wool package in the present invention.
Specific embodiment
The invention will be described in further detail with reference to the accompanying drawing:
With reference to Fig. 2 and Fig. 3, it is of the present invention reduce the loose method of combustion engine turbine blade the following steps are included:
1) combustion engine turbine blade wax mould is prepared, wherein the riser height of combustion engine turbine blade wax mould is combustion engine turbine blade
The 1/5~1/6 of overall length, then turbo blade formwork is prepared using transfer matic total silicon colloidal sol by combustion engine turbine blade wax mould；
2) three layers of ceramic wool are wrapped up around turbo blade formwork, wherein the thickness of each layer ceramic wool is 6mm, first layer
Ceramic wool between ceramic pouring cup lower end and riser, second layer ceramic wool be located at ceramic pouring cup lower end and 1/3 blade it
Between, third layer ceramic wool is located at ceramics and burns between cup lower end and 2/3 blade；
It 3) will treated that turbo blade formwork is put into roaster roasts through step 2), wherein maturing temperature is
1000 DEG C~1075 DEG C, calcining time is more than or equal to 2h；
4) alloy is subjected to melting, obtains molten steel, then the temperature of molten steel is adjusted to more than aluminium alloy liquidus temperature 230 DEG C,
And 3min~5min is refined, its temperature is then reduced to 150 DEG C~170 DEG C of aluminium alloy liquidus temperature or more, obtains molten steel, then
Vacuum degree is less than or equal in the environment of 1.33Pa, and molten steel is poured into after filter screen filtration in turbo blade formwork, is then removed
Turbo blade formwork, then cut, obtain combustion engine turbine blade, wherein pour the angle of incidence and be less than or equal to 4s, and turbo blade formwork
It is less than or equal to 3min since taking out to the time interval poured between molten steel in roaster.
Embodiment one
The present embodiment is of the present invention to reduce the loose method of combustion engine turbine blade by taking Ч С 70- В И alloy as an example
The following steps are included:
1) combustion engine turbine blade wax mould is prepared, wherein the riser height of combustion engine turbine blade wax mould is combustion engine turbine blade
The 1/5~1/6 of overall length, then turbo blade formwork is prepared using transfer matic total silicon colloidal sol by combustion engine turbine blade wax mould；
2) three layers of ceramic wool are wrapped up around turbo blade formwork, wherein the thickness of each layer ceramic wool is 6mm, first layer
Ceramic wool between ceramic pouring cup lower end and riser, second layer ceramic wool be located at ceramic pouring cup lower end and 1/3 blade it
Between, third layer ceramic wool is located at ceramics and burns between cup lower end and 2/3 blade；
It 3) will treated that turbo blade formwork is put into roaster roasts through step 2), wherein maturing temperature is
1000 DEG C, calcining time is more than or equal to 2h；
4) alloy is subjected to melting, obtains molten steel, then the temperature of molten steel is adjusted to 1560 DEG C, and refine 3min~5min,
Then its temperature is reduced to 1500 DEG C, molten steel is obtained, then in the environment of vacuum degree is less than or equal to 1.33Pa, by molten steel through filtering
It is poured into after net filtration in turbo blade formwork, then removes turbo blade formwork, then cut, obtain combustion engine turbine blade,
In, the angle of incidence is poured less than or equal to 4s, and turbo blade formwork is between taking-up pours into the time between molten steel in roaster
Every less than or equal to 3min.
Embodiment two
The present embodiment is of the present invention to reduce the loose method of combustion engine turbine blade by taking Ч С 70- В И alloy as an example
The following steps are included:
1) combustion engine turbine blade wax mould is prepared, wherein the riser height of combustion engine turbine blade wax mould is combustion engine turbine blade
The 1/5~1/6 of overall length, then turbo blade formwork is prepared using transfer matic total silicon colloidal sol by combustion engine turbine blade wax mould；
2) three layers of ceramic wool are wrapped up around turbo blade formwork, wherein the thickness of each layer ceramic wool is 6mm, first layer
Ceramic wool between ceramic pouring cup lower end and riser, second layer ceramic wool be located at ceramic pouring cup lower end and 1/3 blade it
Between, third layer ceramic wool is located at ceramics and burns between cup lower end and 2/3 blade；
It 3) will treated that turbo blade formwork is put into roaster roasts through step 2), wherein maturing temperature is
1075 DEG C, calcining time is more than or equal to 2h；
4) alloy is subjected to melting, obtains molten steel, then the temperature of molten steel is adjusted to 1560 DEG C, and refine 3min~5min,
Then its temperature is reduced to 1480 DEG C, molten steel is obtained, then in the environment of vacuum degree is less than or equal to 1.33Pa, by molten steel through filtering
It is poured into after net filtration in turbo blade formwork, then removes turbo blade formwork, then cut, obtain combustion engine turbine blade,
In, the angle of incidence is poured less than or equal to 4s, and turbo blade formwork is between taking-up pours into the time between molten steel in roaster
Every less than or equal to 3min.
Embodiment three
The present embodiment is of the present invention to reduce the loose method of combustion engine turbine blade by taking Ч С 70- В И alloy as an example
The following steps are included:
1) combustion engine turbine blade wax mould is prepared, wherein the riser height of combustion engine turbine blade wax mould is combustion engine turbine blade
The 1/5~1/6 of overall length, then turbo blade formwork is prepared using transfer matic total silicon colloidal sol by combustion engine turbine blade wax mould；
2) three layers of ceramic wool are wrapped up around turbo blade formwork, wherein the thickness of each layer ceramic wool is 6mm, first layer
Ceramic wool between ceramic pouring cup lower end and riser, second layer ceramic wool be located at ceramic pouring cup lower end and 1/3 blade it
Between, third layer ceramic wool is located at ceramics and burns between cup lower end and 2/3 blade；
It 3) will treated that turbo blade formwork is put into roaster roasts through step 2), wherein maturing temperature is
1100 DEG C, calcining time is more than or equal to 2h；
4) alloy is subjected to melting, obtains molten steel, then the temperature of molten steel is adjusted to 1560 DEG C, and refine 3min~5min,
Then its temperature is reduced to 1490 DEG C, molten steel is obtained, then in the environment of vacuum degree is less than or equal to 1.33Pa, by molten steel through filtering
It is poured into after net filtration in turbo blade formwork, then removes turbo blade formwork, then cut, obtain combustion engine turbine blade,
In, the angle of incidence is poured less than or equal to 4s, and turbo blade formwork is between taking-up pours into the time between molten steel in roaster
Every less than or equal to 3min.
Table 1 is the Ч С 70- В И of the obtained Ч С 70- В И alloy combustion engine turbine blade of each embodiment and the prior art
The comparison of alloy-steel casting section microporosity number.
Table 1
Claims (10)
1. a kind of reduce the loose method of combustion engine turbine blade, which comprises the following steps:
1) combustion engine turbine blade wax mould is prepared, wherein the riser height of combustion engine turbine blade wax mould is combustion engine turbine vane overall length
1/5~1/6, then turbo blade formwork is prepared by combustion engine turbine blade wax mould；
2) three layers of ceramic wool are wrapped up around turbo blade formwork, wherein first layer ceramic wool is located at ceramic pouring cup lower end and emits
Between mouthful, between ceramic pouring cup lower end and 1/3 blade, third layer ceramic wool is located at ceramics and burns cup second layer ceramic wool
Between lower end and 2/3 blade；
It 3) will treated that turbo blade formwork roasts through step 2)；
4) molten steel is prepared, then molten steel is poured into after filter screen filtration in turbo blade formwork, then removes turbo blade formwork,
It is cut again, obtains combustion engine turbine blade.
2. according to claim 1 reduce the loose method of combustion engine turbine blade, which is characterized in that pass through combustion in step 1)
Machine turbo blade wax-pattern prepares turbo blade formwork using transfer matic total silicon colloidal sol.
3. according to claim 1 reduce the loose method of combustion engine turbine blade, which is characterized in that the thickness of each layer ceramic wool
Degree is 6mm.
4. according to claim 1 reduce the loose method of combustion engine turbine blade, which is characterized in that the specific behaviour of step 3)
As: it will treated that turbo blade formwork is put into roaster roasts through step 2).
5. according to claim 4 reduce the loose method of combustion engine turbine blade, which is characterized in that maturing temperature 1000
DEG C~1075 DEG C, calcining time is more than or equal to 2h.
6. according to claim 1 reduce the loose method of combustion engine turbine blade, which is characterized in that prepare steel in step 4)
The concrete operations of liquid are as follows:
Alloy is subjected to melting, obtains molten steel, then the temperature of molten steel is adjusted to more than aluminium alloy liquidus temperature 230 DEG C, and is carried out
Refining, is then reduced to 150 DEG C~170 DEG C of aluminium alloy liquidus temperature or more for its temperature, obtains molten steel.
7. according to claim 6 reduce the loose method of combustion engine turbine blade, which is characterized in that refining time 3min
~5min.
8. according to claim 4 reduce the loose method of combustion engine turbine blade, which is characterized in that be less than in vacuum degree etc.
In the environment of 1.33Pa, molten steel is poured into after filter screen filtration in turbo blade formwork.
9. according to claim 7 reduce the loose method of combustion engine turbine blade, which is characterized in that pour the angle of incidence and be less than etc.
In 4s.
10. according to claim 7 reduce the loose method of combustion engine turbine blade, which is characterized in that turbo blade formwork
It is less than or equal to 3min since taking out to the time interval poured between molten steel in roaster.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811032442.9A CN108941459B (en) | 2018-09-05 | 2018-09-05 | Method for reducing turbine blade looseness of combustion engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811032442.9A CN108941459B (en) | 2018-09-05 | 2018-09-05 | Method for reducing turbine blade looseness of combustion engine |
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| Publication Number | Publication Date |
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| CN108941459A true CN108941459A (en) | 2018-12-07 |
| CN108941459B CN108941459B (en) | 2020-10-09 |
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| Application Number | Title | Priority Date | Filing Date |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109622888A (en) * | 2018-12-20 | 2019-04-16 | 航天海鹰(哈尔滨)钛业有限公司 | A kind of cast shaping process of the multi-joint guide vane casting of complexity high temperature alloy |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS5815743A (en) * | 1981-07-22 | 1983-01-29 | Izumi Jidosha Kogyo Kk | Piston and its manufacture for internal-combustion engine |
| FR2985925A1 (en) * | 2012-01-24 | 2013-07-26 | Snecma | Shell, useful for manufacturing bladed elements of turboshaft engine of aircraft by lost-wax casting, comprises thermal isolation coating carried out using set of thermal isolation strips for recovering part of external surface of shell |
| CN104308076A (en) * | 2014-10-29 | 2015-01-28 | 西安航空动力股份有限公司 | Wax mold combination of four-connection hollow turbine guide vane and precision casting method of wax mold combination |
| CN104308082A (en) * | 2014-10-29 | 2015-01-28 | 西安航空动力股份有限公司 | Pouring method of hollow turbine guide vane |
| CN104325081A (en) * | 2014-10-30 | 2015-02-04 | 西安航空动力股份有限公司 | Preparation method of combined type shell with heat insulating materials implanted therein |
| CN107755635A (en) * | 2017-09-12 | 2018-03-06 | 东方电气集团东方汽轮机有限公司 | A kind of method for solving combustion engine shrouded blade leaf top R angles fire check |
| CN108176817A (en) * | 2018-01-10 | 2018-06-19 | 中国航发北京航空材料研究院 | A kind of loose control method of elongated thin-walled band hat equiax crystal casting turbo blade |
-
2018
- 2018-09-05 CN CN201811032442.9A patent/CN108941459B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS5815743A (en) * | 1981-07-22 | 1983-01-29 | Izumi Jidosha Kogyo Kk | Piston and its manufacture for internal-combustion engine |
| FR2985925A1 (en) * | 2012-01-24 | 2013-07-26 | Snecma | Shell, useful for manufacturing bladed elements of turboshaft engine of aircraft by lost-wax casting, comprises thermal isolation coating carried out using set of thermal isolation strips for recovering part of external surface of shell |
| CN104308076A (en) * | 2014-10-29 | 2015-01-28 | 西安航空动力股份有限公司 | Wax mold combination of four-connection hollow turbine guide vane and precision casting method of wax mold combination |
| CN104308082A (en) * | 2014-10-29 | 2015-01-28 | 西安航空动力股份有限公司 | Pouring method of hollow turbine guide vane |
| CN104325081A (en) * | 2014-10-30 | 2015-02-04 | 西安航空动力股份有限公司 | Preparation method of combined type shell with heat insulating materials implanted therein |
| CN107755635A (en) * | 2017-09-12 | 2018-03-06 | 东方电气集团东方汽轮机有限公司 | A kind of method for solving combustion engine shrouded blade leaf top R angles fire check |
| CN108176817A (en) * | 2018-01-10 | 2018-06-19 | 中国航发北京航空材料研究院 | A kind of loose control method of elongated thin-walled band hat equiax crystal casting turbo blade |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109622888A (en) * | 2018-12-20 | 2019-04-16 | 航天海鹰(哈尔滨)钛业有限公司 | A kind of cast shaping process of the multi-joint guide vane casting of complexity high temperature alloy |
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| CN108941459B (en) | 2020-10-09 |
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