CN104525853A - A method of eliminating deformation of a wax mould for an ultrathin elongated working blade of a turbine - Google Patents

A method of eliminating deformation of a wax mould for an ultrathin elongated working blade of a turbine Download PDF

Info

Publication number
CN104525853A
CN104525853A CN201410631739.2A CN201410631739A CN104525853A CN 104525853 A CN104525853 A CN 104525853A CN 201410631739 A CN201410631739 A CN 201410631739A CN 104525853 A CN104525853 A CN 104525853A
Authority
CN
China
Prior art keywords
blade
wax
pattern mold
moving turbine
turbine blade
Prior art date
Application number
CN201410631739.2A
Other languages
Chinese (zh)
Other versions
CN104525853B (en
Inventor
韩宏
张民政
顾欣
朱洪斌
张贺
Original Assignee
沈阳黎明航空发动机(集团)有限责任公司
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by 沈阳黎明航空发动机(集团)有限责任公司 filed Critical 沈阳黎明航空发动机(集团)有限责任公司
Priority to CN201410631739.2A priority Critical patent/CN104525853B/en
Publication of CN104525853A publication Critical patent/CN104525853A/en
Application granted granted Critical
Publication of CN104525853B publication Critical patent/CN104525853B/en

Links

Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B22CASTING; POWDER METALLURGY
    • B22CFOUNDRY MOULDING
    • B22C7/00Patterns; Manufacture thereof so far as not provided for in other classes
    • B22C7/02Lost patterns
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B22CASTING; POWDER METALLURGY
    • B22CFOUNDRY MOULDING
    • B22C9/00Moulds or cores; Moulding processes
    • B22C9/02Sand moulds or like moulds for shaped castings
    • B22C9/04Use of lost patterns

Abstract

The invention relates to a method of eliminating deformation of a wax mould for an ultrathin elongated working blade of a turbine, and belongs to the technical field of manufacturing of blades of aviation engines. The method overcomes disadvantages in the prior art, provides a scheme of carrying and installing the blade wax mould by utilizing a wax mould clamping fixture, and discloses a design scheme of the wax mould clamping fixture. In an actual development and production process of a turbine working blade, because the wax mould clamping fixture is utilized to carry and install the blade wax mould, deformation of the blade wax mould is effectively controlled, and the deformation amount of the turbine working blade manufactured by utilization of the blade wax mould is reduced from original about 1 mm to now about 0.3 mm. Because the deformation amount is reduced, blade correction becomes relatively easy, thus avoiding generation of correction cracks, increasing the yield of precision casting of the turbine working blade by about 20%, largely reducing the rejection rate of the blade and largely saving the production cost.

Description

A kind of method eliminating ultra-thin elongated moving turbine blade wax-pattern distortion

Technical field

The invention belongs to blade of aviation engine manufacturing technology field, particularly relate to a kind of method eliminating ultra-thin elongated moving turbine blade wax-pattern distortion.

Background technology

As important one---the moving turbine blade of blade of aviation engine, it has the thin and elongated feature of blade, for a certain type moving turbine blade, the blade length of this moving turbine blade is 190mm, blade string is wide is 25mm, the inlet and outlet limit thickness of blade is only 0.5 ~ 0.6mm, and blade entirety has certain torsional angle.

In the development and production process of moving turbine blade, there is the excessive problem of deflection in frequent discovery blade, deflection is approximately about 1mm, now can only carry out correction process to this blade, because the deflection of blade is excessive, blade is corrected and becomes quite difficulty, and in blade correcting process, enter, arrange the weakness on limit at blade, often produce and correct crackle, and then cause scrapping of this blade, cause no small economic loss to the development and production of moving turbine blade.

Through the continuous tracing observation of staff, it is excessive that final discovery is that the blade wax mould used in blade development and production process is out of shape the deformable blade amount caused, because blade wax mould is combined into module from being pressed into, about 72 hours of whole cycle, if blade wax mould after pressing molding time undue force, molding just can be caused to be out of shape.Because the thick middle of blade wax mould blade part, both sides are thin, therefore amount of contraction is different, causes blade wax mould blade to twist.No matter how blade wax mould puts, and blade wax mould is all in cantilever position, and being conducted oneself with dignity by blade wax mould also to cause blade to bend.But also do not have effective way can solve the problem on deformation of blade wax mould at present.

Summary of the invention

For prior art Problems existing, the invention provides a kind of method eliminating ultra-thin elongated moving turbine blade wax-pattern distortion, propose a kind of scheme utilizing wax-pattern mold to take up blade wax mould, and disclose the design of wax-pattern mold, by the use of wax-pattern mold, effectively control the distortion of blade wax mould.

To achieve these goals, the present invention adopts following technical scheme: a kind of method eliminating ultra-thin elongated moving turbine blade wax-pattern distortion, comprises the steps:

Step one: according to the blade back shape face parameter designing wax-pattern mold of moving turbine blade;

Step 2: according to the blade back shape foliation opinion coordinate value of moving turbine blade, calculate the working surface coordinate value of wax-pattern mold, its computing formula is:

Xb′=Xb×k

Yb′=Yb×k

In formula, the working surface coordinate that Xb ', Yb ' they are wax-pattern mold, and Xb, Yb are the blade back shape face theoretical coordinate of moving turbine blade, and k is correction factor;

Step 3: the value calculating correction factor k, its computing formula is:

k=δ 12

In formula, δ 1for the shrinkage factor of wax-pattern mold, δ 2for the shrinkage factor of blade wax mould, and δ 1, δ 2be given value;

Step 4: the effective face length L ' and the effective face width degree M ' that calculate wax-pattern mold, its computing formula is:

L′=(L-R 1-R 2)×k-0.2

M′=M×k

In formula, L is moving turbine blade blade length, R 1for the switching radius of corner of moving turbine blade integral shroud, R 2for the switching radius of corner of moving turbine blade tenon bar, M is that moving turbine blade blade string is wide;

Step 5: according to the wax-pattern matrix design parameter calculated, manufactures processing wax-pattern mold;

Step 6; Blade wax mould after compacting is put on wax-pattern mold, the blade back position of blade wax mould is contacted with wax-pattern mold holotype face, and blade wax mould carries out depositing, having enough to meet the need and walk operation, until be combined into module on wax-pattern mold.

In order to ensure that wax-pattern mold has good processing characteristics, the material of described wax-pattern mold adopts LD8, and the working surface roughness of wax-pattern mold is Ra0.4.

Beneficial effect of the present invention:

Instant invention overcomes the deficiencies in the prior art, propose a kind of scheme utilizing wax-pattern mold to take up blade wax mould, and disclose the design of wax-pattern mold, in the actual development and production process of moving turbine blade, blade wax mould is taken up owing to employing wax-pattern mold, effectively control the distortion of blade wax mould, utilize the moving turbine blade that blade wax mould manufactures, make the deflection of moving turbine blade by original about 1mm, be reduced to present about 0.3mm, because deflection has diminished, blade is corrected and becomes relatively easy, thus avoid the generation of correcting crackle, make the essence of moving turbine blade cast qualification rate and improve about 20 percentage points, greatly reduce the scrappage of blade, save a large amount of production costs.

Accompanying drawing explanation

Fig. 1 is a kind of moving turbine blade schematic diagram;

Fig. 2 is the blade back shape face theoretical coordinate schematic diagram of moving turbine blade;

Fig. 3 is the working surface coordinate schematic diagram of wax-pattern mold;

Fig. 4 is blade length and the wide schematic diagram of blade string of moving turbine blade;

Fig. 5 is effective face length and the effective face width degree schematic diagram of wax-pattern mold;

In figure, the blade back shape face theoretical coordinate of Xb, Yb-moving turbine blade, the working surface coordinate of Xb ', Yb '-wax-pattern mold, L-moving turbine blade blade length, M-moving turbine blade blade string is wide, R 1the switching radius of corner of-moving turbine blade integral shroud, R 2the switching radius of corner of-moving turbine blade tenon bar, effective face length of L '-wax-pattern mold, the effective face width degree of M '-wax-pattern mold.

Detailed description of the invention

Below in conjunction with the drawings and specific embodiments, the present invention is described in further detail.

In the present embodiment, need the blade length of the moving turbine blade of development and production to be 190mm, blade string is wide is 25mm, and the inlet and outlet limit thickness of blade is 0.5 ~ 0.6mm, and wherein, the blade profile parameters of blade wax mould is identical with moving turbine blade.

The method of the ultra-thin elongated moving turbine blade wax-pattern distortion of described elimination, comprises the steps:

Step one: according to the blade back shape face parameter designing wax-pattern mold of moving turbine blade;

Step 2: according to the blade back shape foliation opinion coordinate value of moving turbine blade, calculate the working surface coordinate value of wax-pattern mold, its computing formula is:

Xb′=Xb×k

Yb′=Yb×k

In formula, the working surface coordinate that Xb ', Yb ' they are wax-pattern mold, and Xb, Yb are the blade back shape face theoretical coordinate of moving turbine blade, and k is correction factor;

Step 3: the value calculating correction factor k, its computing formula is:

k=δ 12

In formula, δ 1for the shrinkage factor of wax-pattern mold, δ 2for the shrinkage factor of blade wax mould, and δ 1, δ 2be given value;

Step 4: the effective face length L ' and the effective face width degree M ' that calculate wax-pattern mold, its computing formula is:

L′=(L-R 1-R 2)×k-0.2

M′=M×k

In formula, L is moving turbine blade blade length, R 1for the switching radius of corner of moving turbine blade integral shroud, R 2for the switching radius of corner of moving turbine blade tenon bar, M is that moving turbine blade blade string is wide;

Step 5: according to the wax-pattern matrix design parameter calculated, manufactures processing wax-pattern mold;

Step 6; Blade wax mould after compacting is put on wax-pattern mold, the blade back position of blade wax mould is contacted with wax-pattern mold holotype face, and blade wax mould carries out depositing, having enough to meet the need and walk operation, until be combined into module on wax-pattern mold.

In order to ensure that wax-pattern mold has good processing characteristics, the material of described wax-pattern mold adopts LD8, and the working surface roughness of wax-pattern mold is Ra0.4.

Scheme in embodiment is also not used to limit scope of patent protection of the present invention, and the equivalence that all the present invention of disengaging do is implemented or changed, and is all contained in the scope of the claims of this case.

Claims (2)

1. eliminate a method for ultra-thin elongated moving turbine blade wax-pattern distortion, it is characterized in that: comprise the steps:
Step one: according to the blade back shape face parameter designing wax-pattern mold of moving turbine blade;
Step 2: according to the blade back shape foliation opinion coordinate value of moving turbine blade, calculate the working surface coordinate value of wax-pattern mold, its computing formula is:
Xb′=Xb×k
Yb′=Yb×k
In formula, the working surface coordinate that Xb ', Yb ' they are wax-pattern mold, and Xb, Yb are the blade back shape face theoretical coordinate of moving turbine blade, and k is correction factor;
Step 3: the value calculating correction factor k, its computing formula is:
k=δ 12
In formula, δ 1for the shrinkage factor of wax-pattern mold, δ 2for the shrinkage factor of blade wax mould, and δ 1, δ 2be given value;
Step 4: the effective face length L ' and the effective face width degree M ' that calculate wax-pattern mold, its computing formula is:
L′=(L-R 1-R 2)×k-0.2
M′=M×k
In formula, L is moving turbine blade blade length, and R1 is the switching radius of corner of moving turbine blade integral shroud, and R2 is the switching radius of corner of moving turbine blade tenon bar, and M is that moving turbine blade blade string is wide;
Step 5: according to the wax-pattern matrix design parameter calculated, manufactures processing wax-pattern mold;
Step 6; Blade wax mould after compacting is put on wax-pattern mold, the blade back position of blade wax mould is contacted with wax-pattern mold holotype face, and blade wax mould carries out depositing, having enough to meet the need and walk operation, until be combined into module on wax-pattern mold.
2. a kind of method eliminating ultra-thin elongated moving turbine blade wax-pattern distortion according to claim 1, in order to ensure that wax-pattern mold has good processing characteristics, it is characterized in that: the material of described wax-pattern mold adopts LD8, and the working surface roughness of wax-pattern mold is Ra0.4.
CN201410631739.2A 2014-11-11 2014-11-11 A kind of method eliminating the deformation of ultra-thin elongated moving turbine blade wax-pattern CN104525853B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201410631739.2A CN104525853B (en) 2014-11-11 2014-11-11 A kind of method eliminating the deformation of ultra-thin elongated moving turbine blade wax-pattern

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201410631739.2A CN104525853B (en) 2014-11-11 2014-11-11 A kind of method eliminating the deformation of ultra-thin elongated moving turbine blade wax-pattern

Publications (2)

Publication Number Publication Date
CN104525853A true CN104525853A (en) 2015-04-22
CN104525853B CN104525853B (en) 2016-08-24

Family

ID=52841584

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201410631739.2A CN104525853B (en) 2014-11-11 2014-11-11 A kind of method eliminating the deformation of ultra-thin elongated moving turbine blade wax-pattern

Country Status (1)

Country Link
CN (1) CN104525853B (en)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105290327B (en) * 2015-11-11 2017-06-20 沈阳黎明航空发动机(集团)有限责任公司 A kind of method for controlling large complicated block cast casing wax-pattern deformation
FR3057187A1 (en) * 2016-10-12 2018-04-13 Safran Aircraft Engines METHOD FOR DETERMINING THE REMOVAL OF A FOUNDRY CORE DURING THERMAL TREATMENT OF THE CORE
CN108620539A (en) * 2017-12-21 2018-10-09 贵州安吉航空精密铸造有限责任公司 A kind of investment casting method with complex-curved shape casting
CN109465385A (en) * 2018-12-04 2019-03-15 沈阳航发精密铸造有限公司 A kind of no-residual length leaf wax-pattern state correction detecting tool
CN110842147A (en) * 2019-11-29 2020-02-28 西安航天发动机有限公司 Method for controlling size of closed impeller investment precision casting runner
CN110961574A (en) * 2019-12-30 2020-04-07 安徽应流航源动力科技有限公司 Placer of engine guide vane wax matrix
CN111390113A (en) * 2020-04-17 2020-07-10 中国航发北京航空材料研究院 Method for accurately controlling outline dimension of hollow single crystal turbine working blade
CN111496182A (en) * 2020-05-15 2020-08-07 中国航发北京航空材料研究院 Precision casting method for preventing deformation of single-crystal duplex block-cast turbine guide vane edge plate

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107790623B (en) * 2017-10-27 2019-03-22 中国航发南方工业有限公司 A kind of combined method of hot investment casting assembling wax pattern

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2004276109A (en) * 2003-03-19 2004-10-07 Daido Steel Co Ltd Lost wax pattern for lost wax casting method
CN101480696A (en) * 2008-01-11 2009-07-15 中国科学院金属研究所 Method for preparing high-temperature alloy thin-section casting
CN102019354A (en) * 2010-12-27 2011-04-20 沈阳黎明航空发动机(集团)有限责任公司 Directional solidification method of ultra-thin and long shrouded blade
CN102091757A (en) * 2010-12-30 2011-06-15 沈阳黎明航空发动机(集团)有限责任公司 Integral precision casting method for large thin-wall casing part
CN102228955A (en) * 2011-07-01 2011-11-02 李复旺 Treatment method for deformation of massive lost foam

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2004276109A (en) * 2003-03-19 2004-10-07 Daido Steel Co Ltd Lost wax pattern for lost wax casting method
CN101480696A (en) * 2008-01-11 2009-07-15 中国科学院金属研究所 Method for preparing high-temperature alloy thin-section casting
CN102019354A (en) * 2010-12-27 2011-04-20 沈阳黎明航空发动机(集团)有限责任公司 Directional solidification method of ultra-thin and long shrouded blade
CN102091757A (en) * 2010-12-30 2011-06-15 沈阳黎明航空发动机(集团)有限责任公司 Integral precision casting method for large thin-wall casing part
CN102228955A (en) * 2011-07-01 2011-11-02 李复旺 Treatment method for deformation of massive lost foam

Non-Patent Citations (3)

* Cited by examiner, † Cited by third party
Title
王永明等: "控制超薄细长无余量定向叶片变形的工艺措施", 《特种铸造及有色合金》 *
秦乐天等: "铝青铜高速螺旋桨熔模铸造工艺", 《特种铸造及有色合金》 *
韩伟等: "大型涡轮叶片精密铸造尺寸精度控制研究——反变形技术", 《铸造》 *

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105290327B (en) * 2015-11-11 2017-06-20 沈阳黎明航空发动机(集团)有限责任公司 A kind of method for controlling large complicated block cast casing wax-pattern deformation
FR3057187A1 (en) * 2016-10-12 2018-04-13 Safran Aircraft Engines METHOD FOR DETERMINING THE REMOVAL OF A FOUNDRY CORE DURING THERMAL TREATMENT OF THE CORE
CN108620539A (en) * 2017-12-21 2018-10-09 贵州安吉航空精密铸造有限责任公司 A kind of investment casting method with complex-curved shape casting
CN108620539B (en) * 2017-12-21 2020-06-23 贵州安吉航空精密铸造有限责任公司 Investment casting method for casting with complex curved surface shape
CN109465385A (en) * 2018-12-04 2019-03-15 沈阳航发精密铸造有限公司 A kind of no-residual length leaf wax-pattern state correction detecting tool
CN109465385B (en) * 2018-12-04 2020-09-04 中国航发沈阳黎明航空发动机有限责任公司 No-allowance blade wax mold state correction detection tool
CN110842147A (en) * 2019-11-29 2020-02-28 西安航天发动机有限公司 Method for controlling size of closed impeller investment precision casting runner
CN110961574A (en) * 2019-12-30 2020-04-07 安徽应流航源动力科技有限公司 Placer of engine guide vane wax matrix
CN111390113A (en) * 2020-04-17 2020-07-10 中国航发北京航空材料研究院 Method for accurately controlling outline dimension of hollow single crystal turbine working blade
CN111496182A (en) * 2020-05-15 2020-08-07 中国航发北京航空材料研究院 Precision casting method for preventing deformation of single-crystal duplex block-cast turbine guide vane edge plate

Also Published As

Publication number Publication date
CN104525853B (en) 2016-08-24

Similar Documents

Publication Publication Date Title
CN104028983B (en) A kind of fir-tree root class turbine blade manufacturing process
CN201239760Y (en) Sectional type bender tool bit
CN103291653B (en) A kind of low-specific speed impeller and blade design method thereof
CN103252451B (en) A kind of manufacture method of low pressure guiding triplet hollow blade
CN102207101A (en) CFD (Computational Fluid Dynamics)-based modeling design method for nuclear main pump and designed million-kilowatt-grade nuclear main pump impeller
FR2970668B1 (en) PROCESS FOR MAKING A METAL REINFORCEMENT
CN204220932U (en) A kind of six conjuncted guide vane casting moulding systems
CN102231170B (en) Parameterized sizing method for turbine blade mould cavity
CN101767286A (en) Finishing and machining locating process method of high- pressure turbine working blade
CN102717336A (en) Angular adjustment cushion block for angular forming machine
CN105587840A (en) Flexible gear delta-shaped tooth of harmonic reducer
CN103691866B (en) A kind of method improving blade blank position stability on mould
CN103551521B (en) A kind of casting method of guide vane foundry goods
CN103611881A (en) Mould for valve-manufacturing lost foam and casting technology for manufacturing valve by using lost foam
CN102962694B (en) For the accurately machined clamping and positioning device of aero engine turbine blades
CN105215321A (en) A kind of multimode cavity die casting
CN104400607A (en) Polishing method for precision mold
CN103111588A (en) Manufacturing method of precision casting of titanium alloy impeller
CN107931544A (en) A kind of conjuncted hollow guide vane investment casting process
CN202239496U (en) Metal gravity casting die
CN102606224A (en) Impulse steam turbine welding partition board with embedded fixed blades and assembling process of impulse steam turbine welding partition board
CN102163244A (en) Method for dolphin head-shaped processing of blade leading edge
CN102240928B (en) Numerical control (NC) polishing method for molded arc vane air inlet/outlet side
CN103537652B (en) A kind of fine casting method preventing high-pressure turbine guide vane to be out of shape
CN205201917U (en) High accuracy forming die

Legal Events

Date Code Title Description
PB01 Publication
C10 Entry into substantive examination
SE01 Entry into force of request for substantive examination
GR01 Patent grant
C14 Grant of patent or utility model
CP01 Change in the name or title of a patent holder
CP01 Change in the name or title of a patent holder

Address after: 110043 Liaoning Province, Shenyang City District East Street No. 6

Patentee after: Chinese Hangfa Shenyang Liming Aero engine limited liability company

Address before: 110043 Liaoning Province, Shenyang City District East Street No. 6

Patentee before: Liming Aeroplane Engine (Group) Co., Ltd., Shenyang City