CN105562717A - Numerical control turning method for large deep cavity structure of aircraft engine disc part - Google Patents
Numerical control turning method for large deep cavity structure of aircraft engine disc part Download PDFInfo
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- CN105562717A CN105562717A CN201410538049.2A CN201410538049A CN105562717A CN 105562717 A CN105562717 A CN 105562717A CN 201410538049 A CN201410538049 A CN 201410538049A CN 105562717 A CN105562717 A CN 105562717A
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Abstract
The invention discloses a numerical control turning method for a large deep cavity structure of an aircraft engine disc part. The method comprises the following specific steps that a numerical control vertical lathe with cooling water pressure of 40-90 bar is adopted to machine a part; an inner cooling turning tool of high-pressure cooling water with pressure of 40-90 bar is used for machining a deep cavity structure of the part in rough machining of the part, and in the machining process, cutting chips can be broken to fragments; the main machining route is as follows: rough turning of a front end, rough turning of a back end, vacuum stress relief heat treatment, finish turning of a front end profile surface and finish turning of a back end profile surface; and the rough machining and the finish machining both adopt the numerical control vertical lathe to machine. The method has the following advantages that the geometric size and the surface quality of the machined part satisfy the design requirements; as the high-pressure cooling cutter is adopted, the turning blade durability is increased by 50% or above compared with traditional cooling, and single cutter consumption is reduced; and as the surface quality of the part satisfies the design requirement, the labor-hour and the cost are saved.
Description
Technical field
The present invention relates to field of machining, particularly the numerical control turning method of the large dark cavity configuration of a kind of disc part of aero-engine.
Background technology
Produce when developing a kind of large dark cavity configuration disc part of aero-engine, because Element Design structure is special-shaped dark cavity configuration, the dark about 160mm in chamber, inlet diameter are about Φ 260mm, entrance width is about 100mm, in semiclosed angle 40 degree of V-structures, by R14mm round-corner transition bottom enclosed cavity, the engine plate web pattern of to be long cantilever thickness be in side 6mm, opposite side is the scalene cone structure of thickness 3mm, weak rigidity.
Large dark cavity configuration part shape is complicated, and processing dimension and positional precision are all higher, and disc bore area is beated and is not more than 0.02mm, and end face run-out is 0.02mm, and part minimum wall thickness (MINI W.) is 3mm, and belong to thin-walled, large dark cavity configuration, rigidity is poor, and clamping is yielding.Part material is difficult-to-machine material titanium alloy, and part blank is forging part, and allowance is larger.The processing difficulties of part mainly concentrates on profile and disc surfaces in dark chamber, how to ensure accessory size, positional precision, brings very large difficulty to processing.
Conventional needle is to the processing of such constitutional detail, the common machine folder numerical control nonstandard side's knife bar of usual employing is processed, process tool is caused to overhang extremely long, processing chatter is serious, surface quality of workpieces after processing and geometric accuracy cannot meet design requirement, and the surface after processing needs to be met design requirement by follow-up manual polishing.
Summary of the invention
The object of the invention is to improve part geometry precision and surface quality in the large dark cavity configuration disk-like accessory process of aero-engine, spy provides the numerical control turning method of the large dark cavity configuration of a kind of disc part of aero-engine.
The invention provides the numerical control turning method of the large dark cavity configuration of a kind of disc part of aero-engine, it is characterized in that: the numerical control turning method of the large dark cavity configuration of described disc part of aero-engine, concrete steps are as follows:
The first step, adopts the NC vertical lathe processing parts with 40-90bar cooling water pressure.
Second step, process for cold lathe tool in the dark cavity configuration of the part high-pressure cooling water that uses pressure to be 40-90bar during part roughing, chip can be interrupted in process and become chip, working (machining) efficiency can be improved, improve tool life, reduce the cost of charp tool and ensure surface quality.
3rd step, main processing route is: rough turn front end → rough turn rear end → vacuum hidden lino removal → finish turning front end profile → finish turning rear end profile, roughing and fine finishining all adopt NC vertical lathe to process.
4th step, it is that the spherical blade of 4-6mm carries out layering processing to part profile that part dark chamber finish turning adds utilization of hour diameter, and every layer of working depth controls between 0.3-0.5mm;
Vehicle Processing cutting speed VC=40-60m/min, amount of feeding F=0.1-0.15mm/r, to control the deflection of part, avoid causing part deformation because cutting force is excessive, and spherical blade is conducive to improving surface quality of workpieces and working (machining) efficiency simultaneously.
5th step, finish turning adds and adopts man-hour machine tool on-line measurement function to carry out part dimension measurement, first Vehicle Processing 0.3 ~ 0.5mm part material when programming, utilize the actual value processing of machine tool on-line measurement functional measurement, automatically calculating cutter according to programmed values by Digit Control Machine Tool remedies defects in difference input machine tool wearing valve, carry out auto-compensation to cutter deviation, the 0.3 ~ 0.5mm material performing lower one deck according to program cuts, and completes the processing of part final size.
Described rough turn front end and rough turn rear end, after roughing, piece surface evenly stays 1mm ~ 2mm surplus.
After described part roughing, carry out hidden lino removal with vacuum drying oven, remove part roughing residual stress.
Advantage of the present invention:
The numerical control turning method of the large dark cavity configuration of disc part of aero-engine of the present invention, the part geometry size processed and surface quality meet design requirement, owing to adopting high pressure cooling cutter, raising more than 50% compared with Vehicle Processing blade durability cools with tradition, separate unit reduces cutter consumption and reduces, and because surface quality of workpieces meets design requirement, separate unit reduces the follow-up polishing amount of part, save work time cost, and lay a good foundation for processing homogeneous structure part.
Accompanying drawing explanation
Below in conjunction with drawings and the embodiments, the present invention is further detailed explanation:
Fig. 1 is design of part schematic diagram.
Detailed description of the invention
Embodiment 1
The numerical control turning method that the invention provides the large dark cavity configuration of a kind of disc part of aero-engine described in the present embodiment, is characterized in that: the numerical control turning method of the large dark cavity configuration of described disc part of aero-engine, and concrete steps are as follows:
The first step, adopts the NC vertical lathe processing parts with 40bar cooling water pressure.
Second step, process for cold lathe tool in the dark cavity configuration of the part high-pressure cooling water that uses pressure to be 40bar during part roughing, chip can be interrupted in process and become chip, working (machining) efficiency can be improved, improve tool life, reduce the cost of charp tool and ensure surface quality.
3rd step, main processing route is: rough turn front end → rough turn rear end → vacuum hidden lino removal → finish turning front end profile → finish turning rear end profile, roughing and fine finishining all adopt NC vertical lathe to process.
4th step, it is that the spherical blade of 4mm carries out layering processing to part profile that part dark chamber finish turning adds utilization of hour diameter, and every layer of working depth controls between 0.3mm;
Vehicle Processing cutting speed VC=40m/min, amount of feeding F=0.1mm/r, to control the deflection of part, avoid causing part deformation because cutting force is excessive, and spherical blade is conducive to improving surface quality of workpieces and working (machining) efficiency simultaneously.
5th step, finish turning adds and adopts man-hour machine tool on-line measurement function to carry out part dimension measurement, first Vehicle Processing 0.3mm part material when programming, utilize the actual value processing of machine tool on-line measurement functional measurement, automatically calculating cutter according to programmed values by Digit Control Machine Tool remedies defects in difference input machine tool wearing valve, carry out auto-compensation to cutter deviation, the 0.3mm material performing lower one deck according to program cuts, and completes the processing of part final size.
Described rough turn front end and rough turn rear end, after roughing, piece surface evenly stays 1mm surplus.
After described part roughing, carry out hidden lino removal with vacuum drying oven, remove part roughing residual stress.
Embodiment 2
The numerical control turning method that the invention provides the large dark cavity configuration of a kind of disc part of aero-engine described in the present embodiment, is characterized in that: the numerical control turning method of the large dark cavity configuration of described disc part of aero-engine, and concrete steps are as follows:
The first step, adopts the NC vertical lathe processing parts with 60bar cooling water pressure.
Second step, process for cold lathe tool in the dark cavity configuration of the part high-pressure cooling water that uses pressure to be 60bar during part roughing, chip can be interrupted in process and become chip, working (machining) efficiency can be improved, improve tool life, reduce the cost of charp tool and ensure surface quality.
3rd step, main processing route is: rough turn front end → rough turn rear end → vacuum hidden lino removal → finish turning front end profile → finish turning rear end profile, roughing and fine finishining all adopt NC vertical lathe to process.
4th step, it is that the spherical blade of 5mm carries out layering processing to part profile that part dark chamber finish turning adds utilization of hour diameter, and every layer of working depth controls between 0.4mm;
Vehicle Processing cutting speed VC=50m/min, amount of feeding F=0.12mm/r, to control the deflection of part, avoid causing part deformation because cutting force is excessive, and spherical blade is conducive to improving surface quality of workpieces and working (machining) efficiency simultaneously.
5th step, finish turning adds and adopts man-hour machine tool on-line measurement function to carry out part dimension measurement, first Vehicle Processing 0.4mm part material when programming, utilize the actual value processing of machine tool on-line measurement functional measurement, automatically calculating cutter according to programmed values by Digit Control Machine Tool remedies defects in difference input machine tool wearing valve, carry out auto-compensation to cutter deviation, the 0.4mm material performing lower one deck according to program cuts, and completes the processing of part final size.
Described rough turn front end and rough turn rear end, after roughing, piece surface evenly stays 1.5mm surplus.
After described part roughing, carry out hidden lino removal with vacuum drying oven, remove part roughing residual stress.
Embodiment 3
Present embodiments provide the numerical control turning method of the large dark cavity configuration of a kind of disc part of aero-engine, it is characterized in that: the numerical control turning method of the large dark cavity configuration of described disc part of aero-engine, concrete steps are as follows:
The first step, adopts the NC vertical lathe processing parts with 90bar cooling water pressure.
Second step, process for cold lathe tool in the dark cavity configuration of the part high-pressure cooling water that uses pressure to be 90bar during part roughing, chip can be interrupted in process and become chip, working (machining) efficiency can be improved, improve tool life, reduce the cost of charp tool and ensure surface quality.
3rd step, main processing route is: rough turn front end → rough turn rear end → vacuum hidden lino removal → finish turning front end profile → finish turning rear end profile, roughing and fine finishining all adopt NC vertical lathe to process.
4th step, it is that the spherical blade of 6mm carries out layering processing to part profile that part dark chamber finish turning adds utilization of hour diameter, and every layer of working depth controls at 0.5mm;
Vehicle Processing cutting speed VC=60m/min, amount of feeding F=0.15mm/r, to control the deflection of part, avoid causing part deformation because cutting force is excessive, and spherical blade is conducive to improving surface quality of workpieces and working (machining) efficiency simultaneously.
5th step, finish turning adds and adopts man-hour machine tool on-line measurement function to carry out part dimension measurement, first Vehicle Processing 0.5mm part material when programming, utilize the actual value processing of machine tool on-line measurement functional measurement, automatically calculating cutter according to programmed values by Digit Control Machine Tool remedies defects in difference input machine tool wearing valve, carry out auto-compensation to cutter deviation, the 0.5mm material performing lower one deck according to program cuts, and completes the processing of part final size.
Described rough turn front end and rough turn rear end, after roughing, piece surface evenly stays 2mm surplus.
After described part roughing, carry out hidden lino removal with vacuum drying oven, remove part roughing residual stress.
Claims (3)
1. a numerical control turning method for the large dark cavity configuration of disc part of aero-engine, is characterized in that: the numerical control turning method of the large dark cavity configuration of described disc part of aero-engine, and concrete steps are as follows:
The first step, adopts the NC vertical lathe processing parts with 40-90bar cooling water pressure;
Second step, processes for cold lathe tool in the dark cavity configuration of the part high-pressure cooling water that uses pressure to be 40-90bar during part roughing, chip can be interrupted and become chip in process;
3rd step, main processing route is: rough turn front end → rough turn rear end → vacuum hidden lino removal → finish turning front end profile → finish turning rear end profile, and roughing and fine finishining all adopt NC vertical lathe to process;
4th step, it is that the spherical blade of 4-6mm carries out layering processing to part profile that part dark chamber finish turning adds utilization of hour diameter, and every layer of working depth controls between 0.3-0.5mm;
Vehicle Processing cutting speed VC=40-60m/min, amount of feeding F=0.1-0.15mm/r, to control the deflection of part, avoid causing part deformation because cutting force is excessive, and spherical blade is conducive to improving surface quality of workpieces and working (machining) efficiency simultaneously;
5th step, finish turning adds and adopts man-hour machine tool on-line measurement function to carry out part dimension measurement, first Vehicle Processing 0.3 ~ 0.5mm part material when programming, utilize the actual value processing of machine tool on-line measurement functional measurement, automatically calculating cutter according to programmed values by Digit Control Machine Tool remedies defects in difference input machine tool wearing valve, carry out auto-compensation to cutter deviation, the 0.3 ~ 0.5mm material performing lower one deck according to program cuts, and completes the processing of part final size.
2., according to the numerical control turning method of the large dark cavity configuration of disc part of aero-engine according to claim 1, it is characterized in that: described rough turn front end and rough turn rear end, after roughing, piece surface evenly stays 1mm ~ 2mm surplus.
3. according to the numerical control turning method of the large dark cavity configuration of disc part of aero-engine according to claim 1, it is characterized in that: after described part roughing, carry out hidden lino removal with vacuum drying oven, remove part roughing residual stress.
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107214477A (en) * | 2017-06-12 | 2017-09-29 | 中国航发哈尔滨东安发动机有限公司 | A kind of compressor disc processing method |
| CN109277585A (en) * | 2018-11-30 | 2019-01-29 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of Ti3Al alloy guide vane inner ring method for turning |
| CN109746685A (en) * | 2018-11-29 | 2019-05-14 | 中国航发沈阳黎明航空发动机有限责任公司 | The processing method that high-precision high temperature alloy thin-walled double-vane installs the control deformation of side diskware |
| CN110539005A (en) * | 2019-09-17 | 2019-12-06 | 山东大学 | Workpiece cutting method for obtaining high-integrity surface |
| CN110976913A (en) * | 2019-11-22 | 2020-04-10 | 中国航发沈阳黎明航空发动机有限责任公司 | Turning and cutting method of high-temperature alloy ring-shaped piece |
| CN112570999A (en) * | 2020-12-15 | 2021-03-30 | 苏州市跃宇精密机械有限公司 | High-precision aerospace part ultra-precision machining process |
| CN112719311A (en) * | 2020-12-29 | 2021-04-30 | 沈阳黎明航空零部件制造有限公司 | Process method for precisely machining piston rod part of actuator cylinder of aero-engine |
| CN113579640A (en) * | 2021-07-19 | 2021-11-02 | 山西平阳重工机械有限责任公司 | Method for processing semi-closed inner cavity of high-temperature alloy material |
| CN113857498A (en) * | 2021-10-26 | 2021-12-31 | 中国航发沈阳黎明航空发动机有限责任公司 | Machining method of high-pressure compressor disc of aircraft engine |
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| CN112570999A (en) * | 2020-12-15 | 2021-03-30 | 苏州市跃宇精密机械有限公司 | High-precision aerospace part ultra-precision machining process |
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| CN112719311A (en) * | 2020-12-29 | 2021-04-30 | 沈阳黎明航空零部件制造有限公司 | Process method for precisely machining piston rod part of actuator cylinder of aero-engine |
| CN113579640A (en) * | 2021-07-19 | 2021-11-02 | 山西平阳重工机械有限责任公司 | Method for processing semi-closed inner cavity of high-temperature alloy material |
| CN113857498A (en) * | 2021-10-26 | 2021-12-31 | 中国航发沈阳黎明航空发动机有限责任公司 | Machining method of high-pressure compressor disc of aircraft engine |
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Application publication date: 20160511 |