CN109202017A - For producing the casting method for being used for the blade of gas turbine - Google Patents
For producing the casting method for being used for the blade of gas turbine Download PDFInfo
- Publication number
- CN109202017A CN109202017A CN201810698606.5A CN201810698606A CN109202017A CN 109202017 A CN109202017 A CN 109202017A CN 201810698606 A CN201810698606 A CN 201810698606A CN 109202017 A CN109202017 A CN 109202017A
- Authority
- CN
- China
- Prior art keywords
- shell
- blade
- casting method
- packing component
- molten metal
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
- B22D19/00—Casting in, on, or around objects which form part of the product
-
- 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
-
- 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
-
- 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
- B22C9/22—Moulds for peculiarly-shaped castings
- B22C9/28—Moulds for peculiarly-shaped castings for wheels, rolls, or rollers
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
- B22D19/00—Casting in, on, or around objects which form part of the product
- B22D19/0081—Casting in, on, or around objects which form part of the product pretreatment of the insert, e.g. for enhancing the bonding between insert and surrounding cast metal
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
- B22D23/00—Casting processes not provided for in groups B22D1/00 - B22D21/00
- B22D23/06—Melting-down metal, e.g. metal particles, in the mould
Abstract
The present invention is provided to produce the casting method of the blade of gas turbine, method includes the following steps: a) producing the model of the blade made of wax；B) with the shell overlay model made of slurry-mud；C) model covered by shell is heated, to separate wax with shell；D) molten metal is poured into the inside of shell；E) by shell from solidified inside metal removal.Wherein, between in step c) and d), method includes by the additional step of the inside of packing component insertion shell；Packing component is made of the material for being suitable for dissolving when the molten metal with the inside for being poured into shell contacts.
Description
Prioity claim
The application states the priority based on the European patent application 17179205.4 submitted on June 30th, 2017, passes through reference
And merging is disclosed.
Technical field
The present invention relates to for producing the method for being used for the blade of gas turbine.In particular it relates to for producing
The casting method of blade for gas turbine.More particularly, the present invention relate to produce the band shield for gas turbine
Blade casting method.
Background technique
Nowadays it is generally employed for the foundry engieering of the blade of production gas turbine.It practices according to prior art, in this way
The casting process of the blade for producing gas turbine include series of steps below:
A) blade made of wax (referred to as ' ' model ' ') is produced, there is shape identical with the metal blade that will be realized；
B) with slurry-mud material overlay model；
C) capped model is heated, to separate wax with the shell in slurry-mud；
D) molten metal is poured into the inside of shell；
E) by shell from solidified inside metal removal.
Generally, above-mentioned process is referred to as ' ' lost-wax casting ' ' process.
The step a) for producing leaf model is made of the process for generating the blade made of wax by injection.The model is also
Including the loader cast gate that will be used during decanting step or opening and as the casting member for the structure for being used to manipulate model
Part.The model structure made of wax may include more than one leaf model, which is connected to casting element, so as to reality
Existing tree-shaped component, wherein casting element forms channel, and molten metal will flow to all leaf models by the channel.
Process can also include manufacturing the preliminary step of the core of inside for the model that will be integrated in wax.
With the step b) of the model of slurry-mud material (that is, slurry-mud of fine ceramic particle) covering wax usually by soaking model
Stain executes in slurry-mud tank, just to generate shell around the model of wax once slurry-mud is made to dry out.The impregnation steps are repeated,
Until shell thickness is until being sufficient to resist molten metal.
The model of the wax covered by slurry-mud shell by being placed into the temperature for being suitable for making wax to melt by the step c) of heating
Under furnace box in and execute.Under this condition, the wax of melting leaves shell, which becomes hollow casing.By molten metal
It is poured into before the step d) of the inside of shell, such shell is preheating to until about 1000 °C.
Molten metal is poured into the step d) of the inside of shell usually by the way that molten metal is fed to loader cast gate
And it executes.Molten metal fills hollow casing from loader cast gate.In general, molten metal is fed into from the root portion of blade
The inside of slurry-mud shell, also, under the effect of gravity, molten metal reaches the opposite end (that is, tip portion) of blade.Once by
Filling, shell are just placed in the outside of furnace box, to allow molten metal cooling and be frozen into final metal blade.Cooling time
Depending on the thickness of part, and depend on used metal.
Shell can be executed from the step e) of solidified inside metal removal by using water jet.Once shell is gone
It removes, just by sawing or (using liquid nitrogen) or other methods can be broken, so that metal blade be made to separate with element is poured.Casting
The last one step of process is by finishing operations (such as, grinding or grit blasting operation) composition.
Currently, pneumatic Consideration requires to realize the turbo blade with long smooth form.However, the specific shape relates to
And some problems during the casting process of blade, wherein molten metal flow to tip portion from the root of blade.Specifically
There is casting problem when design has the blade at the tip with shield in ground.In fact, in the casting of the particular kind of blade
During making process, molten metal flow to biggish region (with shield from lesser region (airfoil portion of blade)
Tip).It fills metal volume required by shield and is higher than metal required in " feed " airfoil region.
This blade, which incurs, generates porous structure along airfoil portion.In fact, the filling at tip with shield
Period, the molten metal on airfoil portion excessively promptly cool down, also, such quick solidification generates porous structure.It changes
Sentence is talked about, and during for realizing the casting process of blade, the defect occurs, wherein as in bottleneck access, melting gold
Belong to by smaller size smaller and reaches in large volume.
Summary of the invention
Therefore, it is a principal object of the present invention to provide the casting method for producing the blade for being used for gas turbine, the party
Method is suitable for solving the problems, such as the aforementioned of the practice of the prior art.
It, should the present invention is provided to produce the casting method of the blade of gas turbine in order to reach target mentioned above
Method includes at least series of steps below:
A) model made of wax of blade is produced；
B) with the shell overlay model made of slurry-mud；
C) model covered by shell is heated, to separate wax with shell；
D) molten metal is poured into the inside of shell；
E) by shell from solidified inside metal removal.
The main aspect of casting method according to the present invention, in step c) and d) between, method includes the following steps, namely f):
By the inside of packing component insertion shell, wherein packing component is by being suitable in the molten metal with the inside for being poured into shell
The material dissolved when contact is made.
Advantageously, method according to the invention it is therefore possible to realize better smooth pneumatic paddle using foundry engieering
(that is, with the blade of lesser vesicularity at airfoil portion).In fact, in the inside that molten metal is poured into shell
Step d) during, such shell is positioned to configure vertically, to pour into molten metal from root, also, makees in gravity
Under, molten metal flowing to tip.The inside of shell is inserted into before decanting step according to the vertical configuration of shell
Packing component reach tip portion under the effect of gravity.When molten metal and packing component contact at tip portion, this
The packing component of sample liquefies, and therefore, helps the filling of vane tip.As a result, packing component allows to obtain the fast of tip portion
Speed filling, and therefore, obtain the rapid backfill being arranged at the airfoil portion of the shell of upstream at tip.Term upstream refer to from
The molten metal at root to tip flows direction.Such backfill subtracts the cooling of the molten metal at the airfoil portion of shell
Speed, and therefore, it eliminates and generates the excessively rapidly solidification for shrinking porous structure.Specifically, for smooth blades (that is, having
(10-20 cm) parallel surface of the length of tip upstream), or for the blade with the tip with shield, can be noted that this is advantageous
It influences.In fact, before backfilling airfoil portion, molten metal be must be filled with " greatly " for the blade of such type
Tip region.In the case where packing component of the invention is not present, which is delayed by, also, such delay caused
The generation of contraction porous structure at rapid solidification and airfoil portion.
Preferably, between in step f) and d), the method for the present invention includes following step g): to including packing component
Shell is heated.
Advantageously, according to the present embodiment, packing component reaches a high temperature, therefore, in the melting with the inside for being poured into shell
Under the contact of metal, packing component can promptly liquefy.
Preferably, packing component is sponge element (for example, wire mesh sponge).
Advantageously, according to the present embodiment, large volume is presented with a small amount of material in packing component.
Preferably, packing component is made of the identical material of molten metal.
Advantageously, according to the present embodiment, blade produced does not include any impurity about molten metal material.Example
Such as, packing component can be made of Ni, Co or Fe.Alternatively, packing component can be by Ni base, the alloy of Co base or Fe base or super
Grade alloy is made.
Preferably, the step of heating to the shell for including packing component executes in vacuum furnace box.
Advantageously, according to the present embodiment, filler material does not realize any oxide layer during heating stepses.
Alternatively, in order to avoid oxidation, this method, which comprises the following steps that, is being inserted into packing component the inside of shell
Before step, with inert material plating filler material.According to the present embodiment, plating material can be that Pt deposition, Au deposition or W are heavy
Product.Advantageously, W deposition avoids aoxidizing, also, any temperature during heating stepses is not required to limit.
Alternatively, in order to generate oxidation, during the step of heating, heating is executed in the furnace box under atmosphere.
Advantageously, according to the present embodiment, filler material realizes the oxide particle that can be cracked during decanting step.
These oxide particles can be used in guard function.In fact, the tip with shield becomes wear-resisting, and therefore, it is suitable in leaf
Sealing surface is realized during the use of piece.
Preferably, model (casting method and therefore, through the invention and the metal leaf that produces produced in the step a)
Piece) it include airfoil, which is provided with parallel surface in the upstream of vane tip.The length of parallel surface is at least 10 cm.Root
According to the present embodiment, packing component allows to realize the suitable backfill of molten metal at airfoil parallel surface.
Preferably, model (casting method and therefore, through the invention and the metal leaf that produces produced in the step a)
Piece) it include the tip with shield.
Finally, the invention further relates to the blades directly obtained by casting method above-mentioned.
It will be appreciated that both general introduction above and detailed description hereafter are exemplary, and, it is desirable to provide as required to protect
The of the invention of shield is explained further.By from the description below, the apparent further advantage of the invention of drawings and claims
And feature.
In the following claims, it specifically illustrates and is considered novel feature of the invention.
Brief description
After suitably reading over detailed description with reference to attached drawing, other benefit and advantage of the invention be will become obvious.
However, by joint attached drawing with reference to hereafter detailed of the invention for describing exemplary embodiment of the invention
It states, so as to be expressly understood the present invention itself, in which:
Fig. 1 is the perspective illustration of the blade with shield for gas turbine；
Fig. 2 be casting method during about gravity blade configure schematic diagram；
Fig. 3 is the schematic diagram of the flow chart of the embodiment of casting method according to the present invention.
Specific embodiment
Hereinafter, technology contents and detailed description of the invention are described according to preferred embodiment with attached drawing cooperation, wherein
These embodiments are not intended to limit its practical range.Present invention claim claimed covers whole according to appended by
Claim and any equivalent variants and modifications made.
Now, the present invention will be described in detail with reference to attached drawing.
It is the perspective illustration of the blade with shield for gas turbine with reference to Fig. 1, Fig. 1.Generally, with the leaf of shield
Piece (that is, blade with the tip with shield) flows leakage minimum between vane tip and the rotor frame of surrounding for making
Change.In general, the tip with shield includes the platform extended in the plane substantially parallel with opposite rotor frame, also,
Including one or more fins.
According to the example of Fig. 1, represented blade 1 includes airfoil 2, and airfoil 2 prolongs along longitudinal axis 3 from root 4
Reach 5 part of tip, wherein longitudinal axis 3 is the longitudinal axis relative to turbine rotor.Tip portion 5 includes platform-type band
The section 6 of shield.Once be installed in gas turbine, the blade that such section 6 with shield just abuts against it is similar
Sheath section, to realize ring type shield.Section 6 with shield is provided with multiple fins 7, and fin 7 limits parallel channel 8.
The configuration of the blade relative to gravity direction 10 during being casting method of the invention with reference to Fig. 2, Fig. 2 is shown
It is intended to.
According to fig. 2, at least during decanting step (will be described below), blade 1 is substantially vertically arranged, with
Just under the effect of gravity, the molten metal introduced at root portion 4 flow to tip portion 5 (that is, band by airfoil 2
The tip portion of shield).In Fig. 2, reference section 9 indicates a part of airfoil for being connected to tip 5, wherein part tool
There is parallel shape, to realize smooth blades.
It is the schematic diagram of the flow chart of the embodiment of casting method according to the present invention with reference to Fig. 3, Fig. 3.According to the example,
Casting method includes series of steps below:
A the model of the blade with shield) is produced by wax injection, which is provided with casting element and loader opening；
B) model is impregnated in slurry-mud solution, so as to the shell overlay model made of slurry-mud；
C) model covered by shell is heated, to separate wax with shell；
D) it is sintered hollow casing；
E) by the inside of sponge element insertion shell；
F) shell comprising sponge element is heated；
G) molten metal is poured into the inside of the shell comprising sponge element；
H) by shell from solidified inside metal removal；
I casting element and loader) are removed by blade；
L) blade is finished.
It will be described in detail casting method step above now.
During step A), the model of the blade with shield is generated by wax injection.Model is disclosed the gold of production
Belong to the identical outer shape of blade.According to fig. 2, which includes the tip with shield and is connected to point with parallel shape
The airfoil portion at end.As learnt during lost-wax casting, model further includes casting element and the loader with opening.
During step B), the model made of wax is impregnated in slurry-mud solution (for example, the slurry of fine ceramic particle
Mud) in, so as to shell overlay model.
During step C), the model of the wax covered by shell is heated to the melting temperature of wax.Once melting, wax is just
It is flowed out from shell, shell becomes hollow casing.
During step D), it is sintered hollow casing above, to realize solid structure.
During step E), sponge element is at least introduced to the inside of hollow casing.By sponge element from the root of shell
Portion introduces the tip with shield, also, is evenly distributed as much as possible.As presented in the flow chart of Fig. 3, can for example lead to
It crosses W to deposit and plating sponge element (step O), to avoid aoxidizing during the remaining step of method.
During step F), the shell comprising sponge element is heated.As represented in the flow chart of Fig. 3,
Step F can be executed in two different ways.In the first situation (F'), the heating stepses are executed in vacuum furnace box,
To avoid oxidation.Alternatively, at second situation (F''), heating stepses are executed in furnace box at ambient, to generate oxygen
Change, which would be beneficial for guard function.
During step G), molten metal is poured into the inside of the shell comprising sponge element.With molten metal
Contact under, sponge element dissolution.In this manner, the tip portion with shield is promptly filled, and as a result, molten metal exists
Its parallel part that airfoil is reached before solidifying.
During step H), and after the solidification of molten metal, by shell from solidified inside metal removal.
(step I) is removed from blade finally, element and loader will be poured, also, (step is finished to blade
L)。
According to the different embodiments indicated in Fig. 3 by hachure, method includes the preliminary step N for producing core) and it is right
Leach the penultimate step M of such core).
Although having explained the present invention about (multiple) preferred embodiment of the invention as mentioned above, it will be understood that
It arrives, without departing substantially from the scope of the present invention, many other possible modifications and variations can be made.Therefore, it is contemplated that institute
Attached (multiple) claims will cover the such modifications and variations belonged in essential scope of the invention.
Claims (14)
1. it is a kind of for producing the casting method of the blade of gas turbine, it the described method comprises the following steps:
A) model made of wax of the blade is produced；
B) model is covered with the shell made of slurry-mud；
C) model covered by the shell is heated, for separating the wax with the shell；
D) molten metal is poured into the inside of the shell；
E) by the shell from the solidified inside metal removal；
It is characterized in that, the method includes packing component is inserted into the inside of the shell between in the step c) and d)
Step f), wherein the packing component is contacted by being suitable for the molten metal for the inside for being poured into the shell
When the material that dissolves be made.
2. casting method according to claim 1, wherein between in the step f) and d), the method includes to packet
The step g) that the shell containing the packing component is heated.
3. casting method according to claim 2, wherein the packing component is sponge element.
4. the casting method according to claim 3 or 2, wherein the packing component is identical by the molten metal
Material is made.
5. the casting method according to any one of preceding claims 4-2, wherein the packing component by Ni or Co or
Fe is made, or is made of the alloy or superalloy of Ni base or Co base or Fe base.
6. casting method according to claim 5, wherein heated to the shell comprising the packing component
The step g) is executed in vacuum furnace box.
7. casting method according to claim 5, wherein heated to the shell comprising the packing component
The step g) is executed in the furnace box under atmosphere.
8. casting method according to claim 5, wherein before the step g), the method includes described in plating
The step of filler material.
9. casting method according to claim 8, wherein the coating step is deposited by W and executed.
10. casting method according to claim 3, wherein the packing component is made of inert material.
11. casting method according to any one of the preceding claims, wherein the molding production in the step a)
The blade includes the parallel surface of the upstream of the vane tip.
12. casting method according to claim 11, wherein the length of the parallel surface is at least 10 cm.
13. casting method according to any one of the preceding claims, wherein the molding production in the step a)
The blade is the blade with shield.
14. a kind of turbo blade for gas turbine, passes through casting side according to any one of the preceding claims
Method and realize.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EP17179205.4 | 2017-06-30 | ||
| EP17179205.4A EP3421156B1 (en) | 2017-06-30 | 2017-06-30 | Casting method for producing a blade for a gas turbine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109202017A true CN109202017A (en) | 2019-01-15 |
| CN109202017B CN109202017B (en) | 2022-05-13 |
Family
ID=59269966
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810698606.5A Active CN109202017B (en) | 2017-06-30 | 2018-06-29 | Casting method for producing a blade for a gas turbine |
Country Status (2)
| Country | Link |
|---|---|
| EP (1) | EP3421156B1 (en) |
| CN (1) | CN109202017B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112548076A (en) * | 2020-11-19 | 2021-03-26 | 东莞材料基因高等理工研究院 | Preparation method of double-structure high-temperature alloy integral material, test bar, blade disc and blade ring |
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| US1374509A (en) * | 1919-10-10 | 1921-04-12 | Harold A Lomax | Art of hardening metal |
| JPS55114452A (en) * | 1979-02-27 | 1980-09-03 | Hitachi Ltd | Casting method of gas turbine blade |
| CN1042490A (en) * | 1988-11-10 | 1990-05-30 | 兰克西敦技术公司 | Be used to prepare the fusible pattern casting of metal matrix composite and the product produced of method thus thereof |
| CN1148953A (en) * | 1995-07-28 | 1997-05-07 | 布里斯托尔-迈尔斯斯奎布公司 | Cast orthopaedic implant and method of making same |
| CN1684786A (en) * | 2002-08-20 | 2005-10-19 | 美国挤压研磨公司 | Casting process and articles for performing the same |
| CN1846899A (en) * | 2005-04-06 | 2006-10-18 | 通用汽车环球科技运作公司 | Method and apparatus for controlling dispersion of molten metal in a mold cavity |
| CN102913395A (en) * | 2011-08-05 | 2013-02-06 | 通用电气公司 | Wind turbine component having a lightweight structure |
| US20130330201A1 (en) * | 2012-06-11 | 2013-12-12 | Snecma | Casting method for obtaining a part including a tapering portion |
| CN103506574A (en) * | 2012-06-27 | 2014-01-15 | 嘉善鑫海精密铸件有限公司 | Casting method for pouring and molding thin-wall investment pattern steel casting |
| CN203679178U (en) * | 2013-12-26 | 2014-07-02 | 湖北航特装备制造股份有限公司 | Metal type gravity casting mould with fusion-splicing casting mechanism |
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|---|---|---|---|---|
| GB9601910D0 (en) * | 1996-01-31 | 1996-04-03 | Rolls Royce Plc | A method of investment casting and a method of making an investment casting mould |
| US9555471B2 (en) * | 2014-01-28 | 2017-01-31 | General Electric Company | Casting method and cast article |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US1374509A (en) * | 1919-10-10 | 1921-04-12 | Harold A Lomax | Art of hardening metal |
| JPS55114452A (en) * | 1979-02-27 | 1980-09-03 | Hitachi Ltd | Casting method of gas turbine blade |
| CN1042490A (en) * | 1988-11-10 | 1990-05-30 | 兰克西敦技术公司 | Be used to prepare the fusible pattern casting of metal matrix composite and the product produced of method thus thereof |
| CN1148953A (en) * | 1995-07-28 | 1997-05-07 | 布里斯托尔-迈尔斯斯奎布公司 | Cast orthopaedic implant and method of making same |
| CN1684786A (en) * | 2002-08-20 | 2005-10-19 | 美国挤压研磨公司 | Casting process and articles for performing the same |
| CN1846899A (en) * | 2005-04-06 | 2006-10-18 | 通用汽车环球科技运作公司 | Method and apparatus for controlling dispersion of molten metal in a mold cavity |
| CN102913395A (en) * | 2011-08-05 | 2013-02-06 | 通用电气公司 | Wind turbine component having a lightweight structure |
| US20130330201A1 (en) * | 2012-06-11 | 2013-12-12 | Snecma | Casting method for obtaining a part including a tapering portion |
| CN103506574A (en) * | 2012-06-27 | 2014-01-15 | 嘉善鑫海精密铸件有限公司 | Casting method for pouring and molding thin-wall investment pattern steel casting |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112548076A (en) * | 2020-11-19 | 2021-03-26 | 东莞材料基因高等理工研究院 | Preparation method of double-structure high-temperature alloy integral material, test bar, blade disc and blade ring |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109202017B (en) | 2022-05-13 |
| EP3421156B1 (en) | 2020-06-24 |
| EP3421156A1 (en) | 2019-01-02 |
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