CN115922234A - Deformation control method for titanium alloy ring segment class part forged by aero-engine - Google Patents
Deformation control method for titanium alloy ring segment class part forged by aero-engine Download PDFInfo
- Publication number
- CN115922234A CN115922234A CN202211355647.7A CN202211355647A CN115922234A CN 115922234 A CN115922234 A CN 115922234A CN 202211355647 A CN202211355647 A CN 202211355647A CN 115922234 A CN115922234 A CN 115922234A
- Authority
- CN
- China
- Prior art keywords
- ring segment
- parts
- finish turning
- titanium alloy
- semi
- 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.)
- Pending
Links
Images
Landscapes
- Forging (AREA)
Abstract
The invention discloses a deformation control method for forging titanium alloy ring segment parts of an aircraft engine, which comprises the following steps: step one, semi-finish turning, wherein the semi-finish turning is carried out on ring segment parts in an automatic layered numerical control mode, and cutting parameters of parts are solidified, and the semi-finish turning method comprises the following steps: the rotating speed is 40r/s to 60r/s, the feeding amount is F0.1mm/r to F0.2mm/r, and the semi-finish turning allowance is 1mm to 2mm; cutting off the section of the ring segment type part with the section not less than 80% in advance, and only keeping the inner wall of the ring segment type part connected; according to the deformation control method for the titanium alloy ring section class part forged by the aero-engine, stress is released in advance and stress generation is reduced by means of pre-cutting, low-stress cutting, multi-point limiting and the like, deformation of the titanium alloy ring section class part forged by the aero-engine is controlled, the production period is shortened, and repair cost of the part is reduced.
Description
Technical Field
The invention relates to the technical field of cutting deformation control of ring segment type parts, and particularly provides a deformation control method for titanium alloy ring segment type parts forged by an aero-engine.
Background
The titanium alloy ring segment class part is forged to a certain aeroengine, the part is cut after finishing the fine dimension processing, and the part is irregularly deformed due to rebalancing of internal stress after cutting, and the part is blocked when being assembled with a blade.
People hope urgently to obtain a deformation control method for titanium alloy ring segment class parts forged by an aircraft engine with excellent technical effect.
Disclosure of Invention
The invention aims to provide a deformation control method for a titanium alloy ring segment class part forged by an aircraft engine with excellent technical effect, which is used for controlling the deformation of the part and shortening the production period.
The invention provides a deformation control method for a titanium alloy ring segment class part forged by an aero-engine, which comprises the following steps:
the deformation control method of the titanium alloy ring segment class part forged by the aero-engine comprises the following steps:
step one, semi-finish turning, wherein the semi-finish turning is carried out on ring segment parts in an automatic layered numerical control mode, and cutting parameters of parts are solidified, and the semi-finish turning method comprises the following steps: the rotating speed is 40 r/s-60 r/s, the rotating speed of the part with the diameter larger than 500mm takes a small value, otherwise, the rotating speed takes a large value, the feeding amount is F0.1mm/r-F0.2mm/r, and the semi-finish turning allowance is 1 mm-2 mm;
step two, pre-cutting, namely cutting off more than or equal to 80% of the section of the ring segment type part, wherein the larger the section is, the better the section is, and only the inner wall of the ring segment type part is kept connected; not only releases most internal stress, but also avoids the problems of difficult circle returning and turning vibration caused by full cutting
Thirdly, limiting by using a clamp, limiting the ring segment parts by using a multi-point limiting clamp, wherein the inner circle is positioned by using a fine spigot, the end surface is compressed by using an annular gland, and the inner circle is supported by using an expansion block in an auxiliary manner; the common clamp is generally a pressure plate point contact compression mechanism without a tension mechanism, and the clamp increases the contact area of a ring segment part and the clamp, thereby avoiding clamping stress concentration, enhancing the rigidity of a process system, creating a stable clamping state for fine machining of the part and further reducing the elastic deformation of the part. The compression deformation is reduced from 0.01 mm-0.06 mm to 0.01mm.
Step four, finish machining, namely finish turning the ring segment parts in an automatic layering numerical control mode, and solidifying cutting parameters of the parts, wherein the finish turning method comprises the following steps: the rotating speed is 40 r/s-60 r/s, the diameter of the part is larger than 500mm, the rotating speed is small, otherwise, the rotating speed is large, the feed amount is F0.1mm/r-F0.2mm/r, low-stress cutting is realized, and the generation of stress is reduced.
And in the second step, the width of the precut joint is 0.18-0.2 mm, and two ends of the joint have no steps. The left end face and the right end face of the cutting slit are also connected because of incomplete cutting, so that steps of the left end face and the right end face of the cutting slit after clamping are prevented from being completely cut.
By adopting the deformation control method for forging the titanium alloy ring section parts by the aircraft engine, the planeness of the free end face of the inner ring part of the fan stator at a certain level is less than 0.025mm after being cut off, and the profile is less than 0.05mm. The assembly repair period of the delivered parts is reduced to 0 from 7 days, and the repair cost is saved.
According to the deformation control method for the titanium alloy ring section class part forged by the aero-engine, stress is released in advance and stress generation is reduced by means of pre-cutting, low-stress cutting, multi-point limiting and the like, deformation of the titanium alloy ring section class part forged by the aero-engine is controlled, the production period is shortened, and repair cost of the part is reduced.
Drawings
The invention is described in further detail below with reference to the following figures and embodiments:
FIG. 1 is a top view of a fixture for limiting and clamping;
FIG. 2 is a front view of a fixture for limiting and clamping;
FIG. 3 is a pre-cut front view;
FIG. 4 is a pre-cut top view;
FIG. 5 is a schematic view of a low stress layered machining tool path.
Detailed Description
Example 1
The deformation control method of the titanium alloy ring segment class part forged by the aero-engine comprises the following steps:
step one, semi-finish turning, namely semi-finish turning is carried out on the ring segment type part 1 in an automatic layered numerical control mode, and cutting parameters of parts are solidified, and the semi-finish turning method comprises the following steps: the rotating speed is 40 r/s-60 r/s, the rotating speed of the part with the diameter larger than 500mm takes a small value, otherwise, the rotating speed takes a large value, the feeding amount is F0.1mm/r-F0.2mm/r, and the semi-finish turning allowance is 1 mm-2 mm;
cutting off the section of the ring segment type part 1 by more than or equal to 80% in advance, wherein the larger the section is, the better the section is, and only the inner wall of the ring segment type part 1 is kept connected; not only releases most internal stress, but also avoids the problems of difficult rounding and turning vibration caused by full cutting
Thirdly, limiting by using a clamp, limiting the ring segment type part 1 by using a multi-point limiting clamp, wherein an inner circle is positioned by using a fine spigot, the end surface is compressed by using an annular gland, and the inner circle is supported by using an expansion block in an auxiliary manner; the common clamp is generally a pressure plate point contact compression mechanism without a tension mechanism, the contact area of the ring segment type part 1 and the clamp is increased by the clamp, the clamping stress concentration is avoided, the rigidity of a process system is enhanced, a stable clamping state is created for the finish machining of the part, and the elastic deformation of the part is further reduced. The compression deformation is reduced from 0.01 mm-0.06 mm to 0.01mm.
Step four, finish machining, namely finish turning the ring segment parts 1 in an automatic layering numerical control mode, and solidifying cutting parameters of the parts, and the method comprises the following steps: the rotating speed is 40 r/s-60 r/s, the diameter of the part is larger than 500mm, the rotating speed is small, otherwise, the rotating speed is large, the feeding amount is F0.1mm/r-F0.2mm/r, low stress cutting is realized, and stress generation is reduced.
And in the second step, the width of the precut joint is 0.18-0.2 mm, and two ends of the joint have no steps. Because the left end face and the right end face of the cutting seam are connected without being completely cut off, the steps of the left end face and the right end face of the cutting seam after clamping are avoided being completely cut off.
By adopting the deformation control method for forging the titanium alloy ring section parts by the aero-engine, the planeness of the free end surface of a certain level of fan stator inner ring part after being cut off is less than 0.025mm, and the profile degree is less than 0.05mm. The assembly repair period of the delivered parts is reduced to 0 from 7 days, and the repair cost is saved.
Claims (2)
1. A deformation control method for titanium alloy ring segment class parts forged by an aero-engine is characterized by comprising the following steps: the deformation control method of the titanium alloy ring segment class part forged by the aero-engine comprises the following steps:
step one, semi-finish turning, wherein the semi-finish turning is carried out on ring segment parts (1) in an automatic layering numerical control mode, and cutting parameters of parts are solidified, and the semi-finish turning method comprises the following steps: the rotating speed is 40 r/s-60 r/s, the feeding amount is F0.1mm/r-F0.2mm/r, and the semi-finish turning allowance is 1 mm-2 mm;
step two, pre-cutting, namely cutting off sections of more than or equal to 80% of the ring segment type parts (1), and only keeping the inner walls of the ring segment type parts (1) connected;
thirdly, limiting by a clamp, limiting the ring segment part (1) by a multi-point limiting clamp, wherein an inner circle is positioned by a fine spigot, the end surface is compressed by an annular gland, and the inner circle is supported by an expansion block in an auxiliary manner;
step four, finish machining, namely finish turning the ring segment parts (1) in an automatic layering numerical control mode, and solidifying cutting parameters of the parts, wherein the finish turning method comprises the following steps: the rotating speed is 40r/s to 60r/s, and the feed rate is F0.1mm/r to F0.2mm/r.
2. The deformation control method for the titanium alloy ring segment class part forged by the aero-engine as claimed in claim 1, wherein the deformation control method comprises the following steps: and in the second step, the width of the precut joint is 0.18-0.2 mm, and two ends of the joint have no steps.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211355647.7A CN115922234A (en) | 2022-11-01 | 2022-11-01 | Deformation control method for titanium alloy ring segment class part forged by aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211355647.7A CN115922234A (en) | 2022-11-01 | 2022-11-01 | Deformation control method for titanium alloy ring segment class part forged by aero-engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115922234A true CN115922234A (en) | 2023-04-07 |
Family
ID=86549622
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211355647.7A Pending CN115922234A (en) | 2022-11-01 | 2022-11-01 | Deformation control method for titanium alloy ring segment class part forged by aero-engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115922234A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117020239A (en) * | 2023-10-10 | 2023-11-10 | 中国航发沈阳黎明航空发动机有限责任公司 | Technological method for improving utilization rate of burrs of T-shaped plate part of aero-engine |
-
2022
- 2022-11-01 CN CN202211355647.7A patent/CN115922234A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117020239A (en) * | 2023-10-10 | 2023-11-10 | 中国航发沈阳黎明航空发动机有限责任公司 | Technological method for improving utilization rate of burrs of T-shaped plate part of aero-engine |
| CN117020239B (en) * | 2023-10-10 | 2023-12-08 | 中国航发沈阳黎明航空发动机有限责任公司 | Technological method for improving utilization rate of burrs of T-shaped plate part of aero-engine |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN115922234A (en) | Deformation control method for titanium alloy ring segment class part forged by aero-engine | |
| CN102717115B (en) | High-speed intermittent ultrasonic vibration cutting method for low-rigidity parts | |
| CN101596608B (en) | Grooving cutter device for machining circular grooves | |
| CN110802265B (en) | Vibration-damping slotting cutter and mounting method and control method thereof | |
| CN101347896A (en) | Technique for processing connecting rod bearing shell | |
| CN111673396A (en) | Machining method for large-diameter thin-wall diffuser of aero-engine | |
| CN105397425A (en) | Method for machining annular casing of aero-engine | |
| CN110900294B (en) | Method for preventing machine collision of numerical control machine tool | |
| CN111188790A (en) | Novel three-dimensional flow closed impeller structure and machining method | |
| CN201405076Y (en) | Slotting cutter used for processing ring-shaped slot | |
| JP4490881B2 (en) | Method for manufacturing variable wing in VGS type turbocharger | |
| CN209380018U (en) | A kind of 360 degree of Float principal axis deburring machines of air-cylinder type adjusting torque | |
| CN106001338A (en) | High-temperature alloy no-allowance blade rolling method | |
| EP0436733A1 (en) | Involute interpolation error correction system | |
| CN101992223A (en) | Processing method of porous round bar die | |
| RU2771884C1 (en) | Method for milling a diaphragm with guide vanes of a steam turbine | |
| CN204603335U (en) | A kind of gang tool of external splines nylon coated layer processing | |
| CN216705973U (en) | Novel cutter with constant roughness | |
| CN115647763A (en) | Method for controlling circumferential cutting deformation of annular part of aero-engine | |
| CN110976913A (en) | Turning and cutting method of high-temperature alloy ring-shaped piece | |
| CN214291034U (en) | Welding type PCD composite reamer | |
| CN216540900U (en) | Cutter body mounting seat and machine tool | |
| CN211276522U (en) | Multi-cutter turning device for main bearing cover of single cylinder machine | |
| CN217166528U (en) | Hydraulic tool apron for lathe | |
| CN110434670B (en) | Method for machining a starting component by means of a machining tool and machining tool |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |