阅读说明：本技术 一种航空发动机作动筒活塞杆部精密加工的工艺方法 (Process method for precisely machining piston rod part of actuator cylinder of aero-engine ) 是由 王长阁 马仑 金亚洲 杨帆 马晓薇 于 2020-12-29 设计创作，主要内容包括：一种航空发动机作动筒活塞杆部精密加工的工艺方法,属于航空发动机作动筒技术领域。所述航空发动机作动筒活塞杆部精密加工的工艺方法包括：S1、粗车活塞杆部,采用车刀刀片车加工活塞杆部外圆,车床主轴转速为1200r/min,进给量为0.1mm/r,背吃刀量为0.2mm；S2、精车活塞杆部,采用车刀刀片车加工活塞杆部外圆,车床主轴转速为2000r/min,进给量为0.5mm/r,背吃刀量为0mm；S3、采用豪克能加工活塞杆部,采用斜线走刀的方式,车床主轴转速为800r/min～1000r/min,进给量为0.2mm/r～0.25mm/r,背吃刀量为0.4mm。所述航空发动机作动筒活塞杆部精密加工的工艺方法能够实现活塞杆部的镜面加工,提高活塞及组件的使用可靠性和寿命。(A process method for precisely machining a piston rod part of an aircraft engine actuator cylinder belongs to the technical field of aircraft engine actuator cylinders. The process method for precisely machining the piston rod part of the actuator cylinder of the aero-engine comprises the following steps: s1, roughly turning the piston rod part, and turning the excircle of the piston rod part by adopting a turning tool blade, wherein the rotating speed of a lathe spindle is 1200r/min, the feed amount is 0.1mm/r, and the back bite amount is 0.2 mm; s2, finely turning the piston rod part, and turning the excircle of the piston rod part by adopting a turning tool blade, wherein the rotating speed of a lathe spindle is 2000r/min, the feed amount is 0.5mm/r, and the back bite amount is 0 mm; s3, adopting Haokay energy to process the piston rod part, adopting a diagonal feed mode, and enabling the rotation speed of a lathe spindle to be 800 r/min-1000 r/min, the feed amount to be 0.2 mm/r-0.25 mm/r and the back draft to be 0.4 mm. The process method for precisely machining the piston rod part of the aircraft engine actuator cylinder can realize mirror surface machining of the piston rod part, improve the service reliability and prolong the service life of the piston and the component.)

1. A process method for precisely machining a piston rod part of an aircraft engine actuator cylinder is used for a lathe with Hockey energy machining equipment, and is characterized by comprising the following steps of:

s1, roughly turning the piston rod part, turning the excircle of the piston rod part by using a turning tool blade, and setting the machining parameters of the lathe as follows: the rotating speed of a lathe spindle is 1200r/min, the feed amount is 0.1mm/r, and the back cutting amount is 0.2 mm;

s2, finish turning the piston rod part, turning the excircle of the piston rod part by using a turning tool blade, and setting the machining parameters of the lathe as follows: the rotating speed of a lathe spindle is 2000r/min, the feeding amount is 0.5mm/r, and the back cutting amount is 0 mm;

s3, adopting Haoke energy to process the piston rod part, adopting an oblique line feed mode, and adjusting the equipment parameters of the Haoke energy processing equipment as follows: the no-load current is 2A, and the resonance voltage is more than 15V; the machining parameters of the lathe are set as follows: the rotating speed of the lathe spindle is 800 r/min-1000 r/min, the feed rate is 0.2 mm/r-0.25 mm/r, and the back cutting depth is 0.4 mm.

2. The process of precision machining of piston rods for aircraft engines as claimed in claim 1, wherein the oblique line feed in step S3 is specifically: when the lathe is fed along the Z direction, the lathe needs to be inwardly shifted by 0.02mm along the X direction every 45 mm.

3. The process method for precisely machining the piston rod part of the aircraft engine ram of claim 1, wherein the technical parameters of the turning tool blade are as follows: a triangular blade; the double-sided chip breaker groove is formed; the blade relief angle is 0 degree; the radius of the rounded corner of the tool nose is R0.4mm; the blade thickness was 4.8 mm.

4. The process of precision machining of the piston rod of the aircraft engine ram of claim 1, wherein a rough machining step of a blank is provided before step S1, and specifically comprises: and (3) roughly processing the piston rod part blank on a lathe, and reserving 0.2-0.5 mm of allowance according to the designed size of the piston rod part on one side.

Technical Field

The invention relates to the technical field of aircraft engine actuating cylinders, in particular to a process method for precisely machining piston rods of aircraft engine actuating cylinders.

Background

The actuating cylinder assembly of a certain type of aeroengine is arranged in a high-pressure compressor assembly of the engine and is connected with an adjustable blade through an operating support assembly, as shown in figure 1, the position and dimensional tolerance of the part are strict, the steering of the blade is controlled by the transmission action of the actuating cylinder, and therefore the surface quality of a piston in the actuating cylinder is guaranteed to be very important.

The main processing procedures of the piston rod part of the actuating cylinder are as follows: rough turning of the end face of the outer circle, finish turning of the end face of the outer circle, grinding machining, polishing of the outer circle, wherein the rough turning and the finish turning are machined on a numerically controlled lathe, the grinding is machined on an outer circle grinding machine, and the polishing of the outer circle is carried out on a polishing machine. The surface after turning and grinding has ring-shaped processing lines, and the lines cannot be completely removed by traditional processing methods such as polishing, namely, although the processing method can ensure the dimensional accuracy of the part, the processing lines remain on the surface of the part, and the limit of the surface roughness which can be achieved by the method is Ra0.2 mu m, so that the surface quality cannot be economically further improved. The above-mentioned disadvantages of the piston during long-term use of the engine can lead to wear of the rubber ring and the cylinder in the component and even to the component being scrapped.

Disclosure of Invention

In order to solve the technical problems in the prior art, the invention provides a process method for precisely machining the rod part of a piston of an aircraft engine actuator cylinder, which can realize mirror surface machining of the rod part of the piston, improve the use reliability and prolong the service life of the piston and a component.

In order to achieve the purpose, the technical scheme of the invention is as follows:

a process method for precisely machining a piston rod part of an aeroengine actuator cylinder is used for a lathe with Hockey energy machining equipment and comprises the following steps:

s1, roughly turning the piston rod part, turning the excircle of the piston rod part by using a turning tool blade, and setting the machining parameters of the lathe as follows: the rotating speed of a lathe spindle is 1200r/min, the feed amount is 0.1mm/r, and the back cutting amount is 0.2 mm;

s2, finish turning the piston rod part, turning the excircle of the piston rod part by using a turning tool blade, and setting the machining parameters of the lathe as follows: the rotating speed of a lathe spindle is 2000r/min, the feeding amount is 0.5mm/r, and the back cutting amount is 0 mm;

s3, adopting Haoke energy to process the piston rod part, adopting an oblique line feed mode, and adjusting the equipment parameters of the Haoke energy processing equipment as follows: the no-load current is 2A, and the resonance voltage is more than 15V; the machining parameters of the lathe are set as follows: the rotating speed of the lathe spindle is 800 r/min-1000 r/min, the feed rate is 0.2 mm/r-0.25 mm/r, and the back cutting depth is 0.4 mm.

Further, the oblique line feeding manner in step S3 specifically includes: when the lathe is fed along the Z direction, the lathe needs to be inwardly shifted by 0.02mm along the X direction every 45 mm.

Further, the technical parameters of the turning tool blade are as follows: a triangular blade; the double-sided chip breaker groove is formed; the blade relief angle is 0 degree; the radius of the rounded corner of the tool nose is R0.4mm; the blade thickness was 4.8 mm.

Further, a rough machining step of the wool is provided before the step S1, and specifically includes: and (3) roughly processing the piston rod part blank on a lathe, and reserving 0.2-0.5 mm of allowance according to the designed size of the piston rod part on one side.

The invention has the beneficial effects that:

1) the piston rod part of the actuator cylinder is processed by the process method, the piston rod part is processed into Haokang energy through the turning tool blade to be subjected to surface pretreatment, then the Haokang energy is used for processing and removing processing lines, the surface quality is improved, processing parameters and equipment parameters are solidified, all links are strictly controlled, the precision processing of the piston rod part is realized, the size requirement of a part is ensured, the surface quality is improved, the qualification rate of the part is greatly improved, the use reliability and the service life of the part are obviously improved, and the process method has wide application prospect in the high-precision piston processing;

2) the precision machining method of the piston rod part replaces the traditional piston rod part machining mode, the original machining equipment is a numerical control lathe, a cylindrical grinding machine and a polishing machine, and the main machining process route is rough turning, fine turning, grinding and polishing; the method is used for precisely machining the rod part of the piston by adopting a lathe with a Hooke energy machining device, successfully solves the problem of annular machining lines after the rod part of the piston is machined, improves the surface roughness of the rod part by 1-2 grades, and greatly improves the qualified rate, the use reliability and the service life of the piston;

3) the process method of the invention can ensure that the surface of the piston rod part has no any processing lines, the roughness reaches below Ra0.1 mu m, the service reliability of the piston and the component is improved, and the service life of the piston and the component is prolonged.

Additional features and advantages of the invention will be set forth in part in the detailed description which follows.

Drawings

FIG. 1 is a schematic illustration of the structure of a piston rod portion of an aircraft engine ram according to an embodiment of the present invention;

fig. 2 is a schematic structural diagram of a turning tool insert provided in an embodiment of the present invention, wherein (a) is a schematic front view of the turning tool insert; (b) a side cut-away view of the turning tool blade;

fig. 3 is a schematic view of a piston rod provided in accordance with an embodiment of the present invention clamped to a lathe with a hokken machine.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments.

In order to solve the problems in the prior art, as shown in fig. 1 to 3, the invention provides a process method for precisely machining a piston rod part of an aeroengine ram, which is used for a lathe with a Haokou machining device, and comprises the following steps:

s1, roughly turning the piston rod part, turning the excircle of the piston rod part by using a turning tool blade, and setting the machining parameters of the lathe as follows: the rotating speed of a lathe spindle is 1200r/min, the feed amount is 0.1mm/r, and the back cutting amount is 0.2 mm; in the structure of the piston rod part of the cylinder of the aircraft engine shown in fig. 1, the position of a thick solid line of the piston rod part in fig. 1 is a processing area, and the roughness of the rod part can be guaranteed to be less than Ra0.8 μm after rough turning.

The numerical control program of step S1 on the lathe (with siemens system) is as follows:

T0413

M3 S2000 M8

G99 G0 X100 Z55

X16

G1 X15.9 Z0.5 F0.2

G0 X32

Z0

G1 X16 F0.2

Z0.5

G0 X200 M5 M9

G28 U0

G0 Z150

M30

s2, finish turning the piston rod part, turning the piston rod part by using a turning tool blade, and setting the machining parameters of the lathe as follows: the rotating speed of a lathe spindle is 2000r/min, the feeding amount is 0.5mm/r, and the back cutting amount is 0 mm; the invention carries out fine machining on the surface of the part by the idle feed, can not only remove the cutter back-off generated in the rough machining process of the long rod and ensure the machining size of the part, but also can further improve the surface quality of the piston rod and ensure that the roughness of the rod part can reach less than Ra0.4 mu m after machining.

The numerical control program of step S2 on the lathe (with siemens system) is as follows:

T0404

M3 S2000 M8

G99 G0 X100 Z55

X16

G1 X16 Z0.5 F0.5

G0 X32

Z0

G1 X16 F0.2

Z0.2

G0 X200 M5 M9

G28 U0

G0 Z150

M01

s3, adopting Haoke energy to process the piston rod part, adopting an oblique line feed mode during processing, and adjusting the equipment parameters of the Haoke energy processing equipment as follows: the no-load current is 2A, and the resonance voltage is more than 15V; the machining parameters of the lathe are set as follows: the rotating speed of the lathe spindle is 800 r/min-1000 r/min, the feed rate is 0.2 mm/r-0.25 mm/r, and the back cutting depth is 0.4 mm. The processing is carried out according to the parameter setting, the removal amount of the radial unilateral material after the processing is within 0.001mm, the surface roughness can reach below Ra0.1 mu m, no processing grain exists on the surface, and the mirror surface effect is realized.

In step S3, the oblique line feeding is specifically performed by shifting 0.02mm inward along the X direction of the lathe every 45mm while feeding along the Z direction of the lathe. The invention adopts the Haokang energy to process the radial force is large, the long rod part can produce the cutter back off, so the oblique line feed is adopted when processing the piston rod part, when the lathe Z direction (namely the axial direction of the piston rod part) is fed, the lathe X direction (namely the radial direction of the piston rod part) is shifted inwards by 0.02mm when the lathe Z direction (namely the axial direction of the piston rod part) is fed with the cutter once the cutter moves 45 mm.

The numerical control program for machining on the lathe (adopting the siemens system) in the step S3 is as follows:

T0202

M3 S900

G99 G0 X50 Z45.3

X2

G1 X-0.2 F0.2

G1 X-0.22Z0 F0.25

G0 X50 M5

G28 U0

G0 Z80

M30

as shown in fig. 2, the technical parameters of the turning tool insert are as follows: a triangular blade; the double-sided chip breaker groove is formed; the blade relief angle is 0 degree; the radius of the rounded corner of the tool nose is R0.4mm; the blade thickness was 4.8 mm. The piston rod part is machined by a special turning tool blade, the surface roughness of the piston rod is machined to be less than Ra0.4 mu m, the surface pretreatment is carried out for machining the Haokang energy, and then machining lines can be removed by adopting the Haokang energy on the premise of ensuring the size requirement of the part, so that the surface quality is improved.

In the invention, a rough machining step of the wool is provided before the step S1, and the rough machining step specifically comprises the following steps: and (3) roughly processing the piston rod part blank on a lathe, and reserving 0.2-0.5 mm of allowance according to the designed size of the piston rod part on one side. After rough machining of the blank, the semi-finished product is clamped on a lathe with a machining device for machining the piston rod, as shown in fig. 3, the two ends of the piston rod are tightly pressed by the center of the lathe, rough turning, fine turning and machining for the solid line thickened part of the piston rod in fig. 1 are carried out according to the parameters and numerical control programs in the steps from S1 to S3, and after the machining is finished, the part is taken out.

While embodiments of the invention have been shown and described, it will be understood by those of ordinary skill in the art that: various changes, modifications, substitutions and alterations can be made to the embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the claims and their equivalents.