CN103240574A - Processing method of journal guide vane of aero-engine - Google Patents
Processing method of journal guide vane of aero-engine Download PDFInfo
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- CN103240574A CN103240574A CN2013101706347A CN201310170634A CN103240574A CN 103240574 A CN103240574 A CN 103240574A CN 2013101706347 A CN2013101706347 A CN 2013101706347A CN 201310170634 A CN201310170634 A CN 201310170634A CN 103240574 A CN103240574 A CN 103240574A
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- blade
- center hole
- axle journal
- guide vane
- installing plate
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Abstract
The invention belongs to the aero-engine vane processing technology and relates to an improvement of a processing method of a journal guide vane of an aero-engine. The blank of the guide vane is a rectangular blank, and the processing method is characterized by comprising the following steps of punching a center hole; milling the vane shape and the inner surface of a mounting plate; sealing the guide vane with tin-bismuth alloy; subjecting the journal to fine finishing; and melting the tin-bismuth alloy sealing. The processing method of the journal guide vane of the aero-engine can guarantee the coaxiality of the journal, reduce the number of tools and shorten the processing cycle.
Description
Technical field
The invention belongs to the blade of aviation engine process technology, relate to the improvement to aero-engine axle journal class guide vane processing method.
Background technology
The structure of a kind of guide vane of certain type aero-engine is referring to Fig. 1, and it is made up of blade root screw rod 1, blade root axle journal 2, blade root installing plate 8, blade 4, blade tip installing plate 7 and blade tip axle journal 6.The right-hand member of blade root screw rod 1 is connected with the left end of blade root axle journal 2 is coaxial, the right-hand member of blade root axle journal 2 is connected with the outer surface of blade root installing plate 8, the inner surface of blade root installing plate 8 is connected with the root of blade 4, the tip of blade 4 is connected with the inner surface of blade tip installing plate 7, the outer surface of blade tip installing plate 7 is connected with the left end of blade tip axle journal 6, and blade tip axle journal 6 is coaxial with blade root axle journal 2.At present, domestic processing the type blade, key step is: blank is milled into six sides, and with the rough turn axle journal in six sides location, mill the processing blade with the axle journal location again, at last with top location, axle journal two ends finish turning axle journal.Its shortcoming is: the first, cause the axle journal bending easily owing to the blade insufficient strength in finish turning axle journal process, axiality can't guarantee.The second, the axle journal position can not time processing put in place, has increased frock quantity, has prolonged the process-cycle.
Summary of the invention
The objective of the invention is: propose a kind of improvement processing method of aero-engine axle journal class guide vane, to guarantee the axiality of axle journal, reduce frock quantity, shorten the process-cycle.
Technical scheme of the present invention is: a kind of aero-engine axle journal class guide vane processing method, processed guide vane is by blade root screw rod 1, blade root axle journal 2, blade root installing plate 8, blade 4, blade tip installing plate 7 and blade tip axle journal 6 are formed, the right-hand member of blade root screw rod 1 is connected with the left end of blade root axle journal 2 is coaxial, the right-hand member of blade root axle journal 2 is connected with the outer surface of blade root installing plate 8, the inner surface of blade root installing plate 8 is connected with the root of blade 4, the tip of blade 4 is connected with the inner surface of blade tip installing plate 7, the outer surface of blade tip installing plate 7 is connected with the left end of blade tip axle journal 6, blade tip axle journal 6 is coaxial with blade root axle journal 2, and the blank of this guide vane is the cuboid blank; It is characterized in that processing steps is as follows:
1, beat center hole: an end face in cuboid charge length direction is made a call to first center hole, and this first center hole is positioned at the blade tip direction of guide vane; Make a call to second center hole and the 3rd center hole at another end face of cuboid charge length direction, the center hole method for determining position is: the position of determining first center hole earlier, concrete grammar is: the perspective view of guide vane along axle journal (6) axis direction is placed on the end face of cuboid charge length direction, by translation or revolved projection make its profile be completely contained in this end face and on all directions with end face around minimum range be not less than 2mm, at this moment, the guide vane axis is the position of first center hole at the intersection point of this end face; The position of second center hole is: the some position corresponding with first center hole on another end face of cuboid charge length direction, the method of determining the 3rd center hole position is: do mistake second center hole and the straight line parallel with this end face broadside at another end face of cuboid charge length direction, second center hole is divided into two sections line segments with this straight line, wherein one section length is greater than another section, the 3rd center hole is positioned on the above-mentioned long line segment, and the 3rd center hole is not less than 5mm to the distance of this line segment and cuboid blank side intersection point; The straight line of crossing first center hole and second center hole is the axis of guide vane;
2, mill processing blade profile and installing plate inner surface: with cuboid blank clamping in the anchor clamps that have three top detent mechanisms, process leaf basin and the blade back profile of blade 4 with CNC milling machine, and process the inner surface 3 of blade root installing plate 8 and the inner surface 5 of blade tip installing plate 7;
3, sn-bi alloy package: with cuboid blank clamping in having the package anchor clamps of three top detent mechanisms, the position consistency of three center holes on above-mentioned three top detent mechanisms and the cuboid blank; Use sn-bi alloy that blade 4 is cast into cylinder, this cylindrical axis overlaps with the straight line of crossing first center hole and second center hole;
4, finish turning axle journal: with the cylinder of cuboid blank behind the sn-bi alloy package as the location benchmark, go out blade root screw rod 1, blade root axle journal 2, blade root installing plate 8, blade tip installing plate 7 and blade tip axle journal 6 with lathe in machining, form the guide vane that has the sn-bi alloy package;
5, melted alloy package: the guide vane of sn-bi alloy package is placed in the melting furnace, is heated to 160 ℃～180 ℃, treat after sn-bi alloy melts guide vane to be taken out.
Advantage of the present invention is: proposed a kind of improvement processing method of aero-engine axle journal class guide vane, guaranteed the axiality of axle journal, reduced frock quantity, shortened the process-cycle.Evidence, the process-cycle of the inventive method has shortened more than 40% than existing method.
Description of drawings
Fig. 1 is the structural representation of a kind of guide vane of certain type aero-engine.
The specific embodiment
Below the present invention is described in further details.Referring to Fig. 1, a kind of aero-engine axle journal class guide vane processing method, processed guide vane is by blade root screw rod 1, blade root axle journal 2, blade root installing plate 8, blade 4, blade tip installing plate 7 and blade tip axle journal 6 are formed, the right-hand member of blade root screw rod 1 is connected with the left end of blade root axle journal 2 is coaxial, the right-hand member of blade root axle journal 2 is connected with the outer surface of blade root installing plate 8, the inner surface of blade root installing plate 8 is connected with the root of blade 4, the tip of blade 4 is connected with the inner surface of blade tip installing plate 7, the outer surface of blade tip installing plate 7 is connected with the left end of blade tip axle journal 6, blade tip axle journal 6 is coaxial with blade root axle journal 2, and the blank of this guide vane is the cuboid blank; It is characterized in that processing steps is as follows:
1, beat center hole: an end face in cuboid charge length direction is made a call to first center hole, and this first center hole is positioned at the blade tip direction of guide vane; Make a call to second center hole and the 3rd center hole at another end face of cuboid charge length direction, the center hole method for determining position is: the position of determining first center hole earlier, concrete grammar is: the perspective view of guide vane along axle journal (6) axis direction is placed on the end face of cuboid charge length direction, by translation or revolved projection make its profile be completely contained in this end face and on all directions with end face around minimum range be not less than 2mm, at this moment, the guide vane axis is the position of first center hole at the intersection point of this end face; The position of second center hole is: the some position corresponding with first center hole on another end face of cuboid charge length direction, the method of determining the 3rd center hole position is: do mistake second center hole and the straight line parallel with this end face broadside at another end face of cuboid charge length direction, second center hole is divided into two sections line segments with this straight line, wherein one section length is greater than another section, the 3rd center hole is positioned on the above-mentioned long line segment, and the 3rd center hole is not less than 5mm to the distance of this line segment and cuboid blank side intersection point; The straight line of crossing first center hole and second center hole is the axis of guide vane;
2, mill processing blade profile and installing plate inner surface: with cuboid blank clamping in the anchor clamps that have three top detent mechanisms, process leaf basin and the blade back profile of blade 4 with CNC milling machine, and process the inner surface 3 of blade root installing plate 8 and the inner surface 5 of blade tip installing plate 7;
3, sn-bi alloy package: with cuboid blank clamping in having the package anchor clamps of three top detent mechanisms, the position consistency of three center holes on above-mentioned three top detent mechanisms and the cuboid blank; Use sn-bi alloy that blade 4 is cast into cylinder, this cylindrical axis overlaps with the straight line of crossing first center hole and second center hole;
4, finish turning axle journal: with the cylinder of cuboid blank behind the sn-bi alloy package as the location benchmark, go out blade root screw rod 1, blade root axle journal 2, blade root installing plate 8, blade tip installing plate 7 and blade tip axle journal 6 with lathe in machining, form the guide vane that has the sn-bi alloy package;
5, melted alloy package: the guide vane of sn-bi alloy package is placed in the melting furnace, is heated to 160 ℃～180 ℃, treat after sn-bi alloy melts guide vane to be taken out.
Embodiment
Certain type aero-engine compressor zero level guide vane, blank dimension is 145 * 45 * 21, processing method is as follows:
1, beats center hole: the first center hole position: the long limit 10.5 of an end face middle distance in the longitudinal direction, apart from the minor face 17.5. second center hole position: the position corresponding with ground one center hole on another end face in the longitudinal direction, the 3rd center hole and second center hole are on same end face, and the distance of distance second center hole is 22 in the direction parallel with this end face broadside.
2, mill processing: blank is had the Double Tops tip surface be connected on the machining center ring flange by frock, another end face is processed blade blade and installing plate inner surface by top clamping.
3, sn-bi alloy package: pour into a mould in the package anchor clamps with three top location, cast back cylinder dimensions is Φ 85 * 95.
4, finish turning axle journal: with the cylinder of cuboid blank behind the sn-bi alloy package as the location benchmark, with numerically controlled lathe finish turning axle journal, installing plate and screw thread.
5, the melted alloy package is finished blade processing.
In this grade blade processing, only use anchor clamps two covers, a cover is milling machine ring flange and Double Tops point adapter, and a cover has been saved a large amount of frocks for the package anchor clamps.Simultaneously, adopt packaging technique effectively to strengthen blade place intensity, avoided the distortion of finish turning operation axis.
Claims (1)
1. aero-engine axle journal class guide vane processing method, processed guide vane is by blade root screw rod (1), blade root axle journal (2), blade root installing plate (8), blade (4), blade tip installing plate (7) and blade tip axle journal (6) are formed, the coaxial connection of left end of the right-hand member of blade root screw rod (1) and blade root axle journal (2), the right-hand member of blade root axle journal (2) is connected with the outer surface of blade root installing plate (8), the inner surface of blade root installing plate (8) is connected with the root of blade (4), the tip of blade (4) is connected with the inner surface of blade tip installing plate (7), the outer surface of blade tip installing plate (7) is connected with the left end of blade tip axle journal (6), blade tip axle journal (6) is coaxial with blade root axle journal (2), and the blank of this guide vane is the cuboid blank; It is characterized in that processing steps is as follows:
1.1, beat center hole: an end face in cuboid charge length direction is made a call to first center hole, and this first center hole is positioned at the blade tip direction of guide vane; Make a call to second center hole and the 3rd center hole at another end face of cuboid charge length direction, the center hole method for determining position is: the position of determining first center hole earlier, concrete grammar is: the perspective view of guide vane along axle journal (6) axis direction is placed on the end face of cuboid charge length direction, by translation or revolved projection make its profile be completely contained in this end face and on all directions with end face around minimum range be not less than 2mm, at this moment, the guide vane axis is the position of first center hole at the intersection point of this end face; The position of second center hole is: the some position corresponding with first center hole on another end face of cuboid charge length direction, the method of determining the 3rd center hole position is: do mistake second center hole and the straight line parallel with this end face broadside at another end face of cuboid charge length direction, second center hole is divided into two sections line segments with this straight line, wherein one section length is greater than another section, the 3rd center hole is positioned on the above-mentioned long line segment, and the 3rd center hole is not less than 5mm to the distance of this line segment and cuboid blank side intersection point; The straight line of crossing first center hole and second center hole is the axis of guide vane;
1.2, mill processing blade profile and installing plate inner surface: with cuboid blank clamping in the anchor clamps that have three top detent mechanisms, process leaf basin and the blade back profile of blade (4) with CNC milling machine, and process the inner surface (3) of blade root installing plate (8) and the inner surface (5) of blade tip installing plate (7);
1.3, the sn-bi alloy package: with cuboid blank clamping in having the package anchor clamps of three top detent mechanisms, the position consistency of three center holes on above-mentioned three top detent mechanisms and the cuboid blank; Use sn-bi alloy that blade (4) is cast into cylinder, this cylindrical axis overlaps with the straight line of crossing first center hole and second center hole;
1.4, the finish turning axle journal: with the cylinder of cuboid blank behind the sn-bi alloy package as the location benchmark, go out blade root screw rod (1), blade root axle journal (2), blade root installing plate (8), blade tip installing plate (7) and blade tip axle journal (6) with lathe in machining, form the guide vane that has the sn-bi alloy package;
1.5, the melted alloy package: the guide vane of sn-bi alloy package is placed in the melting furnace, is heated to 160 ℃～180 ℃, treat after sn-bi alloy melts guide vane to be taken out.
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103586392A (en) * | 2013-11-15 | 2014-02-19 | 西安航空动力股份有限公司 | Method for manufacturing large titanium alloy fan damping platform blade blank |
| CN103737266A (en) * | 2013-12-31 | 2014-04-23 | 贵州遵义驰宇精密机电制造有限公司 | Machining method for rear shaft neck of aerial turbofan engine |
| CN105345057A (en) * | 2015-11-22 | 2016-02-24 | 沈阳黎明航空发动机(集团)有限责任公司 | Center hole benchmark correcting method reducing cutting torque |
| CN108714771A (en) * | 2018-05-30 | 2018-10-30 | 中国航发动力股份有限公司 | A kind of aero-engine compressor stator blade processing method and products thereof |
| CN108714770A (en) * | 2018-05-30 | 2018-10-30 | 中国航发动力股份有限公司 | A kind of method of engine rectification guide vane processing |
| CN108747232A (en) * | 2018-05-30 | 2018-11-06 | 中国航发动力股份有限公司 | A kind of finish forge stator blade automatization processing method |
| CN109623294A (en) * | 2019-02-22 | 2019-04-16 | 宁国市华成金研科技有限公司 | A kind of processing method of aircraft turbine blades |
| CN112388260A (en) * | 2020-11-20 | 2021-02-23 | 无锡航亚科技股份有限公司 | Machining method for journal of double-journal rectifying blade of aircraft engine |
| CN114643456A (en) * | 2021-06-30 | 2022-06-21 | 无锡航亚科技股份有限公司 | Anti-deformation processing method for adjustable guide vane shaft neck of aero-engine |
| CN114918632A (en) * | 2022-06-22 | 2022-08-19 | 中国航发贵州黎阳航空动力有限公司 | Device and method for machining blade arc mounting plate |
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| CN102962654A (en) * | 2012-11-22 | 2013-03-13 | 哈尔滨汽轮机厂有限责任公司 | Processing method for no-crown guide blade of steam turbine |
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| US5711068A (en) * | 1995-10-28 | 1998-01-27 | Rolls-Royce Plc | Method of manufacturing a blade |
| WO2002030619A1 (en) * | 2000-10-12 | 2002-04-18 | Sonats - Societe Des Nouvelles Applications Des Techniques De Surfaces | Peening method and machine therefor |
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Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103586392A (en) * | 2013-11-15 | 2014-02-19 | 西安航空动力股份有限公司 | Method for manufacturing large titanium alloy fan damping platform blade blank |
| CN103586392B (en) * | 2013-11-15 | 2015-05-27 | 西安航空动力股份有限公司 | Method for manufacturing large titanium alloy fan damping platform blade blank |
| CN103737266A (en) * | 2013-12-31 | 2014-04-23 | 贵州遵义驰宇精密机电制造有限公司 | Machining method for rear shaft neck of aerial turbofan engine |
| CN103737266B (en) * | 2013-12-31 | 2016-08-31 | 贵州遵义驰宇精密机电制造有限公司 | A kind of processing method of aviation turbofan engine rear shaft neck |
| CN105345057A (en) * | 2015-11-22 | 2016-02-24 | 沈阳黎明航空发动机(集团)有限责任公司 | Center hole benchmark correcting method reducing cutting torque |
| CN105345057B (en) * | 2015-11-22 | 2017-10-10 | 沈阳黎明航空发动机(集团)有限责任公司 | A kind of centre bore benchmark modification method for reducing the cutting moment of torque |
| CN108714771A (en) * | 2018-05-30 | 2018-10-30 | 中国航发动力股份有限公司 | A kind of aero-engine compressor stator blade processing method and products thereof |
| CN108714770A (en) * | 2018-05-30 | 2018-10-30 | 中国航发动力股份有限公司 | A kind of method of engine rectification guide vane processing |
| CN108747232A (en) * | 2018-05-30 | 2018-11-06 | 中国航发动力股份有限公司 | A kind of finish forge stator blade automatization processing method |
| CN108747232B (en) * | 2018-05-30 | 2020-02-11 | 中国航发动力股份有限公司 | Automatic machining method for precisely forged stator blade |
| CN109623294A (en) * | 2019-02-22 | 2019-04-16 | 宁国市华成金研科技有限公司 | A kind of processing method of aircraft turbine blades |
| CN112388260A (en) * | 2020-11-20 | 2021-02-23 | 无锡航亚科技股份有限公司 | Machining method for journal of double-journal rectifying blade of aircraft engine |
| CN114643456A (en) * | 2021-06-30 | 2022-06-21 | 无锡航亚科技股份有限公司 | Anti-deformation processing method for adjustable guide vane shaft neck of aero-engine |
| CN114918632A (en) * | 2022-06-22 | 2022-08-19 | 中国航发贵州黎阳航空动力有限公司 | Device and method for machining blade arc mounting plate |
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Address after: Fengcheng Weiyang District ten road 710021 Shaanxi city of Xi'an Province Patentee after: AECC AVIATION POWER CO,LTD. Address before: Fengcheng Weiyang District ten road 710021 Shaanxi city of Xi'an Province Patentee before: AVIC AVIATION ENGINE Corp.,PLC Address after: Fengcheng Weiyang District ten road 710021 Shaanxi city of Xi'an Province Patentee after: AVIC AVIATION ENGINE Corp.,PLC Address before: Fengcheng Weiyang District ten road 710021 Shaanxi city of Xi'an Province Patentee before: XI'AN AVIATION POWER Co.,Ltd. |