CN101369292A - Method for confirming equilibrium angle of TC11 alloy macrotype fan blade forging piece - Google Patents
Method for confirming equilibrium angle of TC11 alloy macrotype fan blade forging piece Download PDFInfo
- Publication number
- CN101369292A CN101369292A CNA2008101560306A CN200810156030A CN101369292A CN 101369292 A CN101369292 A CN 101369292A CN A2008101560306 A CNA2008101560306 A CN A2008101560306A CN 200810156030 A CN200810156030 A CN 200810156030A CN 101369292 A CN101369292 A CN 101369292A
- Authority
- CN
- China
- Prior art keywords
- blade
- angle
- equilibrium angle
- forging
- equilibrium
- 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
Images
Abstract
The invention relates to a determination method of TC11 alloy large fan blade forge trim angle. After determining the trim angle through the method, framework and performance of ingot of the fan blade forge and the forge satisfy technological requirement after being processed, thereby successfully solving the problems of dependence on import and high acquisition cost, characterized by comprising: (1) selecting integrated type lines of three typical sections, namely an end section near a blade root, a middle section of a blade, a top section near top of the blade; (2) using overlapped origin of the three typical sections as a base point, elementally determining the trim angle; (3) performing forging shape technical analysis according to the trim angle which is determined elementally; (4) validating application of an angle beta when determining the trim angle alpha; (5) through the sections of the blade root, the blade crown and a boss, furthermore trimming and determining the trim angle.
Description
Technical field
The present invention relates to the equilibrium angle technical field of fan blade forged piece, be specially definite method of TC11 alloy large-size fan blade forged piece equilibrium angle.
Background technology
Engine TC11 alloy large-size fan blade is characterized in that wide string, thin-walled, distortion are big.The development of its forging is a difficult point, in the Forging Technology of twisted blade, at first, by base to blank, opening wide die-forging forming then forges, equilibrium angle determines it is the key of forging and molding in the industrial analysis, the precondition of considering when also being the design of blade forging die cavity, so, when blade being carried out the forging and molding analysis, be shaped according to metal material Plastic Forming rule is sufficient when the die forging in order to help each position shape of forging, and the distortion blade profile of blade forging is forged the choose reasonable of direction,, be that equilibrium angle reaches preferable angle promptly with the section type line coordinates direction of principal axis on the forging direction after changeing and institute's gyration of theory shaped wire change in coordinate axis direction by rotation to geometric pattern line coordinates center, blade cross section.And determining of equilibrium angle is key in the difficult point, the plastic force of determining effectively to lower forging of suitable equilibrium angle, and can reduce the suffered cross component force of die holder, improve sufficient shaping of forging of TC11 alloy large-size fan blade, be beneficial to the die forging of TC11 alloy large-size fan blade forged piece open type.
Summary of the invention
At the problems referred to above, the invention provides definite method of TC11 alloy large-size fan blade forged piece equilibrium angle, after determining equilibrium angle by this method, make the blank of fan blade forged piece and forging its tissue and performance after processing all satisfy technological requirement, successfully solved and relied on import, a difficult problem that acquisition cost is high.
Its technical scheme is such: it is characterized in that: it may further comprise the steps,
(1), based on the secondary development program of UG three-dimensional CAD design software, X according to each cross section of vane type line data, Y, the Z coordinate points calculates the theory shaped wire of CAD figure, therefrom select the complete molded lines of three typical sections, promptly be respectively near blade root end section, blade midsection, lean on the leaf top section;
(2), be basic point with the overlapping initial point of three typical sections, take into full account the Plastic Forming of forging, cross component force into and out of the vapour side when considering forging and molding can reach balance or enough little as far as possible as far as possible, forging stock makes things convenient for the accounting quick shaping on open die forging, just tentatively determine equilibrium angle for the angle that the TC11 alloy large-size fan blade turns clockwise;
(3) carry out the forging and forming technology analysis according to just deciding equilibrium angle;
(a), work was taken all factors into consideration when the blade profile torsion resistance was big, should take into account that the abundance of lagging edge peak is shaped, and considered that again surplus of leading edge back of the body arc " overhead kick " is unsuitable excessive;
(b), by leaf top section blade profile broad, when lagging edge is thin, should make leaf top steam output side smooth and strengthen equilibrium angle;
(c), when finish forge or few surplus blade forge, should suitably strengthen equilibrium angle α;
(d), when the blank blade adopts the slab form, should suitably equilibrium angle be changeed little, when the blank blade adopts circle base form, should suitably equilibrium angle be changeed big;
(4), the application of checking angle β during equilibrium angle α determines;
Make the symmetrical center line that trend is extended at steam output side by leaf top section molded lines, the checking angle β that this center line is considered in just determining as equilibrium angle α with the angle that forges azimuth axis, the checking angle is controlled between 48 °-52 °, less than 48 ° of employing location and leading edge damping slots in Forging Technology, but never allow less than 45 °;
(5), further carry out the finishing of equilibrium angle and determine that take into account blade root, integral shroud, boss and forge the Plastic Forming situation under just fixed equilibrium angle, Plastic Forming is further verified by the numbered analog simulation technology by the cross section of blade root, integral shroud, boss;
For TC11 alloy large-size fan blade forged piece blade root die cavity profundity, to guarantee the sufficient shaping of fan blade forged piece from TC11 alloy plasticity forming technology on the one hand; Also to consider on the other hand from the force analysis situation of advanced die cavity, big hitting power is totally unfavorable to the forging die stress raiser, therefore determine that forging equilibrium angle also will take into account the stressing influence that mold stresses is concentrated the place, further revise equilibrium angle α, when definite equilibrium angle α, will make blade root die cavity lowest part and blade profile lowest part be in sustained height as far as possible.
Formulate TC11 alloy large-size fan blade forged piece equilibrium angle α by said method, like this by on the air forging hammer under phase point temperature 30 ℃～50 ℃ employing four fire preparing bases; By on the SPKA11200 clutch type screw press, adopting two fiery die forgings; Anneal for the second time by annealing to add between thermal recalibration and 500 ℃～550 ℃ temperature 30 ℃～50 ℃ first time under phase point temperature, the tissue of blank and forging and performance all satisfy production engineering specifications.
(4) description of drawings
Fig. 1 is theoretical coordinate and the synoptic diagram that forges coordinate;
Fig. 2 is TC11 alloy large-size fan blade forged piece and equilibrium angle synoptic diagram.
Embodiment
Below in conjunction with accompanying drawing deterministic process of the present invention is described:
(1), based on the secondary development program of UG three-dimensional CAD design software, X according to each cross section of vane type line data, Y, the Z coordinate points calculates the theory shaped wire of CAD figure, therefrom select the complete molded lines of three typical sections, promptly being respectively close blade root end section 3, blade midsection 2, leaning on leaf top section 1, XY coordinate is theoretical coordinate system, and X ' Y ' coordinate is to forge coordinate system;
(2), be basic point with the overlapping initial point of three typical sections, take into full account the Plastic Forming of forging, cross component force into and out of the vapour side when considering forging and molding can reach balance or enough little as far as possible as far as possible, forging stock makes things convenient for the accounting quick shaping on open die forging, just tentatively determine equilibrium angle α for the angle that the TC11 alloy large-size fan blade turns clockwise;
(3) carry out the forging and forming technology analysis according to just deciding equilibrium angle;
(a), work was taken all factors into consideration when the blade profile torsion resistance was big, should take into account that the abundance of lagging edge peak is shaped, and considered that again surplus of leading edge back of the body arc " overhead kick " is unsuitable excessive;
(b), by leaf top section blade profile broad, when lagging edge is thin, should make leaf top steam output side smooth and strengthen equilibrium angle;
(c), when finish forge or few surplus blade forge, should suitably strengthen equilibrium angle α;
(d), when the blank blade adopts the slab form, should suitably equilibrium angle α be changeed little, when the blank blade adopts circle base form, should suitably equilibrium angle α be changeed big;
(4), the application of checking angle β during equilibrium angle α determines;
Make the symmetrical center line that trend is extended at steam output side by leaf top section molded lines, the checking angle β that this center line is considered in just determining as equilibrium angle α with the angle that forges azimuth axis, the checking angle is controlled between 48 °-52 °, less than 48 ° of employing location and leading edge damping slots in Forging Technology, but never allow less than 45 °;
(5), further carry out the finishing of equilibrium angle and determine that take into account blade root, integral shroud, boss and forge the Plastic Forming situation under just fixed equilibrium angle α, Plastic Forming is further verified by the numbered analog simulation technology by the cross section of blade root, integral shroud, boss; For TC11 alloy large-size fan blade forged piece blade root die cavity profundity, to guarantee the sufficient shaping of fan blade forged piece from TC11 alloy plasticity forming technology on the one hand; Also to consider on the other hand from the force analysis situation of advanced die cavity, big hitting power is totally unfavorable to the forging die stress raiser, therefore determine that forging equilibrium angle also will take into account the stressing influence that mold stresses is concentrated the place, further revise equilibrium angle, when determining equilibrium angle, will make blade root die cavity lowest part and blade profile lowest part be in sustained height as far as possible.
Can determine TC11 alloy large-size fan blade forged piece equilibrium angle α more accurately by said method, realize the difficult problem that the TC11 alloy large-size fan blade forges like this, realized and grasped the big specification 95 round bar metallurgical technologies of TC11 that the domestic GJB494-88 of satisfying requires; Grasped base gordian technique on air forging hammer; Grasped the finite element numerical simulation technology in TC11 alloy large-size fan blade die forging stage; Grasped TC11 alloy large-size fan blade thermal recalibration technology; The most key is that this forging is succeeded in developing the history that has solved the dependence import, saves a large amount of foreign exchanges, has grasped TC11 alloy large-size fan blade hot-working technology, and 4 for forging direction, and 5 is surplus.
Claims (1)
1.TC11 definite method of alloy large-size fan blade forged piece equilibrium angle, it is characterized in that: it may further comprise the steps,
(1), based on the secondary development program of UG three-dimensional CAD design software, X according to each cross section of vane type line data, Y, the Z coordinate points calculates the theory shaped wire of CAD figure, therefrom select the complete molded lines of three typical sections, promptly be respectively near blade root end section, blade midsection, lean on the leaf top section;
(2), be basic point with the overlapping initial point of three typical sections, take into full account the Plastic Forming of forging, cross component force into and out of the vapour side when considering forging and molding can reach balance or enough little as far as possible as far as possible, forging stock makes things convenient for the accounting quick shaping on open die forging, just tentatively determine equilibrium angle for the angle that the TC11 alloy large-size fan blade turns clockwise;
(3) carry out the forging and forming technology analysis according to just deciding equilibrium angle;
(a), work was taken all factors into consideration when the blade profile torsion resistance was big, should take into account that the abundance of lagging edge peak is shaped, and considered that again surplus of leading edge back of the body arc " overhead kick " is unsuitable excessive;
(b), by leaf top section blade profile broad, when lagging edge is thin, should make leaf top steam output side smooth and strengthen equilibrium angle;
(c), when finish forge or few surplus blade forge, should suitably strengthen equilibrium angle α;
(d), when the blank blade adopts the slab form, should suitably equilibrium angle be changeed little, when the blank blade adopts circle base form, should suitably equilibrium angle be changeed big;
(4), the application of checking angle β during equilibrium angle α determines;
Make the symmetrical center line that trend is extended at steam output side by leaf top section molded lines, the checking angle β that this center line is considered in just determining as equilibrium angle α with the angle that forges azimuth axis, the checking angle is controlled between 48 °-52 °, less than 48 ° of employing location and leading edge damping slots in Forging Technology, but never allow less than 45 °;
(5), further carry out the finishing of equilibrium angle and determine that take into account blade root, integral shroud, boss and forge the Plastic Forming situation under just fixed equilibrium angle, Plastic Forming is further verified by the numbered analog simulation technology by the cross section of blade root, integral shroud, boss;
For TC11 alloy large-size fan blade forged piece blade root die cavity profundity, to guarantee the sufficient shaping of fan blade forged piece from TC11 alloy plasticity forming technology on the one hand; Also to consider on the other hand from the force analysis situation of advanced die cavity, big hitting power is totally unfavorable to the forging die stress raiser, therefore determine that forging equilibrium angle also will take into account the stressing influence that mold stresses is concentrated the place, further revise equilibrium angle α, when definite equilibrium angle α, will make blade root die cavity lowest part and blade profile lowest part be in sustained height as far as possible.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200810156030A CN100585606C (en) | 2008-09-26 | 2008-09-26 | Determination method of TC 11 alloy large fan blade forging balanced angle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200810156030A CN100585606C (en) | 2008-09-26 | 2008-09-26 | Determination method of TC 11 alloy large fan blade forging balanced angle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101369292A true CN101369292A (en) | 2009-02-18 |
| CN100585606C CN100585606C (en) | 2010-01-27 |
Family
ID=40413105
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200810156030A Active CN100585606C (en) | 2008-09-26 | 2008-09-26 | Determination method of TC 11 alloy large fan blade forging balanced angle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN100585606C (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102145354A (en) * | 2010-11-20 | 2011-08-10 | 无锡透平叶片有限公司 | Unigraphics NX-based blade profile software reshaping method |
| CN105626163A (en) * | 2015-12-28 | 2016-06-01 | 无锡透平叶片有限公司 | Forging corner determination method of separation plate stationary blade |
| CN106563754A (en) * | 2016-11-11 | 2017-04-19 | 武汉理工大学 | Symmetrical forging formation method for double-body blades |
| CN106825356A (en) * | 2016-12-09 | 2017-06-13 | 无锡航亚科技股份有限公司 | A kind of method of finish forge vane type line finishing |
| CN106862450A (en) * | 2017-03-10 | 2017-06-20 | 江苏龙城精锻有限公司 | A kind of method for determining the pre- forging geomery of pawl pole Simulation Based On Multi-step hot forging |
| CN116026265A (en) * | 2023-03-28 | 2023-04-28 | 沈阳强航时代精密科技有限公司 | Method for detecting low-pressure turbine blade sawtooth type blade crowns on three-coordinate measuring machine |
-
2008
- 2008-09-26 CN CN200810156030A patent/CN100585606C/en active Active
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102145354A (en) * | 2010-11-20 | 2011-08-10 | 无锡透平叶片有限公司 | Unigraphics NX-based blade profile software reshaping method |
| CN102145354B (en) * | 2010-11-20 | 2012-11-14 | 无锡透平叶片有限公司 | Unigraphics NX-based blade profile software reshaping method |
| CN105626163A (en) * | 2015-12-28 | 2016-06-01 | 无锡透平叶片有限公司 | Forging corner determination method of separation plate stationary blade |
| CN105626163B (en) * | 2015-12-28 | 2017-09-26 | 无锡透平叶片有限公司 | A kind of diaphragm nozzle forges the determination method of corner |
| CN106563754A (en) * | 2016-11-11 | 2017-04-19 | 武汉理工大学 | Symmetrical forging formation method for double-body blades |
| CN106825356A (en) * | 2016-12-09 | 2017-06-13 | 无锡航亚科技股份有限公司 | A kind of method of finish forge vane type line finishing |
| CN106825356B (en) * | 2016-12-09 | 2018-09-21 | 无锡航亚科技股份有限公司 | A kind of method of precision forged blade molded line finishing |
| CN106862450A (en) * | 2017-03-10 | 2017-06-20 | 江苏龙城精锻有限公司 | A kind of method for determining the pre- forging geomery of pawl pole Simulation Based On Multi-step hot forging |
| CN106862450B (en) * | 2017-03-10 | 2018-09-18 | 江苏龙城精锻有限公司 | A kind of method of the pre- forging geomery of determining pawl pole Simulation Based On Multi-step hot forging |
| CN116026265A (en) * | 2023-03-28 | 2023-04-28 | 沈阳强航时代精密科技有限公司 | Method for detecting low-pressure turbine blade sawtooth type blade crowns on three-coordinate measuring machine |
Also Published As
| Publication number | Publication date |
|---|---|
| CN100585606C (en) | 2010-01-27 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN100585606C (en) | Determination method of TC 11 alloy large fan blade forging balanced angle | |
| CN104077442A (en) | Method for controlling machining accuracy of large integrated thin-walled parts based on finite element analysis | |
| CN105160059A (en) | BP and GA based blade machining cutting quantity optimization selection method | |
| US10047612B2 (en) | Method and device for manufacturing turbine blades | |
| CN103722108B (en) | A kind of titanium alloy blade forging method | |
| CN109317590B (en) | Forming method of complex aluminum alloy casing forging | |
| CN103987474B (en) | For the technique manufacturing forging and machined components | |
| CN109365731B (en) | Die forging method for high-temperature alloy precision-forged blade | |
| CN101545440B (en) | Method for manufacturing swivel of actuating lever for motorcycle | |
| CN102989983A (en) | Forging method of automobile engine crankshaft | |
| CN110961563B (en) | Mold design method for reducing lateral force of forge piece through curve mold splitting | |
| CN103042144A (en) | Method for forging automobile engine crankshaft | |
| CN106078252A (en) | A kind of with fiberglass cambered surface and the clamp for machining of ladder hole type parts and processing method | |
| CN102981456B (en) | Non-uniform rational B-spline (NURBS) interpolation feed speed planning method aiming at embedded system | |
| CN108131169A (en) | Root architecture is stretched suitable for the adjustment of feather joint rotor blade position of centre of gravity | |
| CN106040938A (en) | Combined die for forging gear shaft through moulding bed and forging technology | |
| CN105033134B (en) | A kind of precision forging forming method of cam bit | |
| CN103846635A (en) | Forging method for automotive engine crankshaft | |
| CN105512426B (en) | A kind of design method reducing spider cold-forging forming blank discharge quantity | |
| CN102989954A (en) | Forging method of excavator engine crankshaft | |
| CN108057838B (en) | A kind of Whole fiber mulit-turning crankshaft forging design method | |
| Sińczak et al. | The forging process of aircraft engines turbine blades | |
| CN103551480B (en) | A kind of finish forge mould for mount pad forging and finish forge method | |
| CN115828458A (en) | Design and optimization method of aeroengine precision small-allowance blade correction die | |
| CN201407963Y (en) | Ultra-thin gliding missile wing casting piece |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP02 | Change in the address of a patent holder | ||
| CP02 | Change in the address of a patent holder |
Address after: 214000 No. 1800, Huishan Avenue, Huishan Economic Development Zone, Wuxi City, Jiangsu Province Patentee after: WUXI TURBINE BLADE Co.,Ltd. Address before: 214023 No. 305 Yang Qing Road, Jiangsu, Wuxi Patentee before: WUXI TURBINE BLADE Co.,Ltd. |