CN103537652B - A kind of fine casting method preventing high-pressure turbine guide vane to be out of shape - Google Patents
A kind of fine casting method preventing high-pressure turbine guide vane to be out of shape Download PDFInfo
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- CN103537652B CN103537652B CN201310478881.3A CN201310478881A CN103537652B CN 103537652 B CN103537652 B CN 103537652B CN 201310478881 A CN201310478881 A CN 201310478881A CN 103537652 B CN103537652 B CN 103537652B
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- guide vane
- pressure turbine
- turbine guide
- process bar
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Abstract
The present invention proposes a kind of fine casting method preventing high-pressure turbine guide vane to be out of shape, process bar is added in high-pressure turbine guide vane Blank Design process, process bar is in the blade back side of high-pressure turbine guide vane, and is positioned at apart from blade leading edge apart from maximum blade listrium cantilever edge position; Process bar two ends are connected with blade supramarginal plate and blade inframarginal respectively; Process bar length is that the designed distance L of blade supramarginal plate and blade inframarginal deducts blade listrium deflection Δ X.The fine casting method preventing high-pressure turbine guide vane to be out of shape that the present invention proposes, just by increasing process bar in blade blank design process, Contrary compensation is carried out to the distortion of blade listrium, thus reduces the large listrium distortion of turbo blade from source, greatly improve product percent of pass.
Description
Technical field
The present invention relates to blade essence casting technical field, be specially a kind of fine casting method preventing high-pressure turbine guide vane to be out of shape.
Background technology
Novel aero-engine core component high-pressure turbine guide vane mainly adopts the monoblock cast of investment pattern precision casting technique at present.This high-pressure turbine guide vane is large listrium structure, and diagonal-size reaches 170mm, and cantilever reaches 55mm, is very easily out of shape after essence casting.Therefore in order to ensure the designing requirement of guide vane size conforms, need to take the measure of listrium anti-deformation in process of production.Prevent listrium to be out of shape and also become the key whether this guide vane can successfully develop.
For meeting the requirement of this blade design figure paper size, traditional way is the distortion that the thin rod wax of artificial weld diameter 3mm after wax-pattern injection-compression molding prevents from melting casting process, after cast, blade listrium is corrected, although the method can solve part guide vane listrium problem on deformation, but the uniformity of every batch is poor, and correction is easy to leave blemish at blade surface and correct stress, blade fatigue intensity is caused to reduce, the performance of so actual blade is just far below design performance, and this is also one of reason causing blade " life-span short, poor reliability ".Traditional bearing calibration cannot be applied in the large listrium structure of novel aero-engine high-pressure turbine guide vane.
Summary of the invention
The technical problem solved
In order to suppress the distortion of high-pressure turbine guide vane listrium in cast cooling procedure from source, the present invention proposes a kind of fine casting method preventing high-pressure turbine guide vane to be out of shape, the just design technology muscle between inframarginal on blade essence casting blank when carrying out Blank Design, in blade essence casting process, suppress the distortion of listrium, obtain the qualified blade that size is accurate, free of surface defects, nothing correct stress.
Technical scheme
Technical scheme of the present invention is:
Described a kind of fine casting method preventing high-pressure turbine guide vane to be out of shape, is characterized in that: adopt following steps:
Step 1: according to high-pressure turbine guide vane to be processed design high-pressure turbine guide vane blank, wherein in blank, be designed with process bar, described process bar is in the blade back side of high-pressure turbine guide vane, and is positioned at apart from blade leading edge apart from maximum blade listrium cantilever edge position; Process bar two ends are connected with blade supramarginal plate and blade inframarginal respectively; Process bar length is that the designed distance L of blade supramarginal plate and blade inframarginal deducts blade listrium deflection Δ X, wherein Δ X=L (σ h-1) (ε z-ε e), σ h are blade material casts comprehensive shrinkage factor, ε z is blade material directional solidificating alloy elastic elongation amount, ε e is the equiax crystal alloy elastic elongation of blade material;
Step 2: according to the high-pressure turbine guide vane Blank Design result processing high-pressure turbine guide vane blank of step 1;
Step 3: high-pressure turbine guide vane blank essence is cast shape, then by process bar difference vertically listrium skin cut.
Described a kind of fine casting method preventing high-pressure turbine guide vane to be out of shape, is characterized in that: the cross section of described process bar is the isosceles trapezoidal structure of foursquare arc transition.
Beneficial effect
The fine casting method preventing high-pressure turbine guide vane to be out of shape that the present invention proposes, just by increasing process bar in blade blank design process, Contrary compensation is carried out to the distortion of blade listrium, thus reduces the large listrium distortion of turbo blade from source, greatly improve product percent of pass.
Accompanying drawing explanation
Fig. 1: certain high-pressure turbine guide vane essence casting blank schematic diagram;
Fig. 2: process bar cross sectional representation;
Wherein: 1. turborotor; 2. blade back; 3. leading edge; 4. supramarginal plate; 5. inframarginal; 6. inside process bar 7. process bar; 8. outside process bar.
Detailed description of the invention
Below in conjunction with specific embodiment, the present invention is described:
The present embodiment is processed certain machine high-pressure turbine directional solidification guide vane, adopts following steps:
Step 1: according to high-pressure turbine guide vane to be processed design high-pressure turbine guide vane blank, wherein in blank, be designed with process bar 6, prevent the distortion of listrium, described process bar is in blade back 2 side of high-pressure turbine guide vane 1, and is positioned at apart from blade leading edge 3 apart from maximum blade listrium cantilever edge position; Process bar two ends are connected with blade supramarginal plate and blade inframarginal respectively; Process bar length is that the designed distance L of blade supramarginal plate and blade inframarginal deducts blade listrium deflection Δ X, wherein Δ X=L (σ h-1) (ε z-ε e), σ h are blade material casts comprehensive shrinkage factor, ε z is blade material directional solidificating alloy elastic elongation amount, ε e is the equiax crystal alloy elastic elongation of blade material; The present embodiment Leaf listrium deflection Δ X is 0.76 ε e.
With reference to accompanying drawing 2, the cross section of process bar is the isosceles trapezoidal structure of foursquare arc transition, (upper base 7) long 6mm, outside (going to the bottom 8) long 9mm, high 3mm inside it, process bar lateral surface 8 and supramarginal plate 4 and inframarginal 5 surface co-planar, process bar corner is with R1(mm) circular arc switching.
Step 2: according to the high-pressure turbine guide vane Blank Design result processing high-pressure turbine guide vane blank of step 1;
Step 3: high-pressure turbine guide vane blank essence is cast shape, then by process bar difference vertically listrium skin cut.
Adopt anti-deformation process muscle that the deflection of the large listrium of blade is reduced greatly in the present embodiment.Pass through contrast test: two pieces does not add anti-deformation process muscle, and wherein a blade 12 measurement points are all overproof, the minimum 0.32mm of overproof amount, maximum 0.68mm, the minimum 0.37mm of overproof amount of an other blade 12 measurement points, maximum 0.72mm; And wherein one 2 all the other points overproof are all qualified to use two of anti-deformation process muscle blades, 1 overproof 0.01mm, 1 overproof 0.03mm.Other one only 1 overproof, overproof 0.03mm.
Claims (2)
1. the fine casting method preventing high-pressure turbine guide vane to be out of shape, is characterized in that: adopt following steps:
Step 1: according to high-pressure turbine guide vane to be processed design high-pressure turbine guide vane blank, wherein in blank, be designed with process bar, described process bar is in the blade back side of high-pressure turbine guide vane, and is positioned at apart from blade leading edge apart from maximum blade listrium cantilever edge position; Process bar two ends are connected with blade supramarginal plate and blade inframarginal respectively; Process bar length is that the designed distance L of blade supramarginal plate and blade inframarginal deducts blade listrium deflection Δ X, wherein Δ X=L (σ h-1) (ε z-ε e), σ h are blade material casts comprehensive shrinkage factor, ε z is blade material directional solidificating alloy elastic elongation amount, ε e is the equiax crystal alloy elastic elongation of blade material;
Step 2: according to the high-pressure turbine guide vane Blank Design result processing high-pressure turbine guide vane blank of step 1;
Step 3: after high-pressure turbine guide vane blank essence is cast shape, by process bar difference vertically listrium skin cut.
2. the fine casting method preventing high-pressure turbine guide vane to be out of shape according to claim 1, is characterized in that: the cross section of described process bar is the isosceles trapezoidal structure of foursquare arc transition.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201310478881.3A CN103537652B (en) | 2013-10-14 | 2013-10-14 | A kind of fine casting method preventing high-pressure turbine guide vane to be out of shape |
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| CN201310478881.3A CN103537652B (en) | 2013-10-14 | 2013-10-14 | A kind of fine casting method preventing high-pressure turbine guide vane to be out of shape |
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| CN103537652A CN103537652A (en) | 2014-01-29 |
| CN103537652B true CN103537652B (en) | 2015-08-12 |
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104384449B (en) * | 2014-10-29 | 2016-07-20 | 西安航空动力股份有限公司 | A kind of method controlling essence casting turbo blade grain size |
| CN104923722B (en) * | 2015-06-24 | 2017-03-22 | 西安航空动力股份有限公司 | Method for controlling hollow guide blade upper edge plate cavity wall thickness |
| CN109226691A (en) * | 2018-10-10 | 2019-01-18 | 深圳市万泽中南研究院有限公司 | Manufacturing method, ceramic shell mould and the manufacturing equipment of guide vane |
| CN111496182B (en) * | 2020-05-15 | 2021-03-26 | 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 |
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| CN1683099A (en) * | 2005-02-02 | 2005-10-19 | 哈尔滨鑫润精铸工业有限公司 | Fine casting method for super long lower pressure partition guide blade of turbine in stainless steel investment mold |
| EP1980343A1 (en) * | 2007-04-11 | 2008-10-15 | Snecma | Tool for manufacturing foundry ceramic cores for turbomachine vanes |
| CN101530892A (en) * | 2009-03-31 | 2009-09-16 | 宁波通达精密铸造有限公司 | Investment casting thin-walled part casting method |
| CN101829776A (en) * | 2010-05-26 | 2010-09-15 | 中国科学院金属研究所 | Method for preparing high-temperature alloy thin wall cast with fine structure |
| CN102814464A (en) * | 2012-09-10 | 2012-12-12 | 上海宝钢铸造有限公司 | Deformation preventing device for flat plate type iron castings and implementing method of deformation preventing device |
| CN102873275A (en) * | 2012-09-28 | 2013-01-16 | 西安航空动力股份有限公司 | Fixing method of isometric crystal and columnar crystal ceramic mold core in mold shell |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US3965963A (en) * | 1973-11-16 | 1976-06-29 | United Technologies Corporation | Mold and process for casting high temperature alloys |
| CN1683099A (en) * | 2005-02-02 | 2005-10-19 | 哈尔滨鑫润精铸工业有限公司 | Fine casting method for super long lower pressure partition guide blade of turbine in stainless steel investment mold |
| EP1980343A1 (en) * | 2007-04-11 | 2008-10-15 | Snecma | Tool for manufacturing foundry ceramic cores for turbomachine vanes |
| CN101530892A (en) * | 2009-03-31 | 2009-09-16 | 宁波通达精密铸造有限公司 | Investment casting thin-walled part casting method |
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Address after: 710021 Xu Jia Bay, Xi'an, Shaanxi, Beijiao Patentee after: AECC AVIATION POWER CO,LTD. Address before: 710021 Xu Jia Bay, Xi'an, Shaanxi, Beijiao Patentee before: AVIC AVIATION ENGINE Corp.,PLC Address after: 710021 Xu Jia Bay, Xi'an, Shaanxi, Beijiao Patentee after: AVIC AVIATION ENGINE Corp.,PLC Address before: 710021 Xu Jia Bay, Xi'an, Shaanxi, Beijiao Patentee before: XI'AN AVIATION POWER Co.,Ltd. |