CN114293121A - Thin-wall blade regional ultrasonic impact strengthening method - Google Patents
Thin-wall blade regional ultrasonic impact strengthening method Download PDFInfo
- Publication number
- CN114293121A CN114293121A CN202111647722.2A CN202111647722A CN114293121A CN 114293121 A CN114293121 A CN 114293121A CN 202111647722 A CN202111647722 A CN 202111647722A CN 114293121 A CN114293121 A CN 114293121A
- Authority
- CN
- China
- Prior art keywords
- ultrasonic impact
- blade
- thin
- strengthening
- region
- 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
Landscapes
- Milling Processes (AREA)
Abstract
The invention discloses a regional ultrasonic impact strengthening method for a thin-wall blade, which comprises the following steps of dividing the thin-wall blade into a blade root region, an air inlet and outlet edge region and a profile region according to a theoretical model and an actually measured three-dimensional model of the thin-wall blade; carrying out ultrasonic impact strengthening on the profile area by adopting a symmetrical ultrasonic impact tool; carrying out ultrasonic impact strengthening on a blade root area by adopting a single-head ultrasonic impact tool; carrying out ultrasonic impact strengthening on the air inlet and outlet edge area by adopting a single-head ultrasonic impact tool to complete the ultrasonic impact strengthening of the thin-wall blade; wherein the ultrasonic impact strengthening processing mode is one-way feed; according to the structural characteristics of the blade of the aero-engine, the blade is divided into three regions, the different regions adopt proper ultrasonic impact processing schemes, the purpose of ultrasonic impact strengthening on the thin-wall blade under the condition of avoiding processing deformation is achieved by adjusting the feed direction and the line spacing, and the surface roughness of the blade is improved.
Description
Technical Field
The invention belongs to the technical field of thin-wall blade surface strengthening in metal machining, and particularly relates to a regional ultrasonic impact strengthening method for a thin-wall blade.
Background
The blade is one of the most important core rotating components in the aircraft engine, belongs to a safety sensitive product, and needs to stably work under severe environments of high temperature, high pressure, high-speed rotation and the like. Once the system fails, the system can be shut down, the safety is endangered, and even the system can be damaged and even people can die.
In order to improve fatigue properties and reliability, it is common to perform surface strengthening treatment after cutting and forming to improve surface mechanical properties and the like. The common surface strengthening process is shot peening, but the surface roughness of the blade after shot peening is large, and the processing controllability is poor.
Disclosure of Invention
The invention aims to provide a regional ultrasonic impact strengthening method for a thin-wall blade, which adopts different ultrasonic impact strengthening cutters and paths according to different structural characteristics of regions and provides a reliable technical scheme for the surface ultrasonic impact strengthening of thin-wall blade parts.
The invention adopts the following technical scheme: a thin-wall blade regional ultrasonic impact strengthening method comprises the following steps:
dividing the thin-wall blade into a blade root area, an air inlet and outlet edge area and a profile area according to a theoretical model and an actually measured three-dimensional model of the thin-wall blade;
carrying out ultrasonic impact strengthening on the profile area by adopting a symmetrical ultrasonic impact tool;
carrying out ultrasonic impact strengthening on a blade root area by adopting a single-head ultrasonic impact tool;
carrying out ultrasonic impact strengthening on the air inlet and outlet edge area by adopting a single-head ultrasonic impact tool to complete the ultrasonic impact strengthening of the thin-wall blade;
wherein, the ultrasonic impact strengthening processing mode is one-way feed.
Further, dividing the thin-walled blade into a blade root area, an air inlet and outlet edge area and a profile area comprises:
determining an interference region according to the interference condition of the tenon part of the thin-wall blade and the symmetrical ultrasonic impact tool, dividing the interference region into a blade root region, and taking other parts of the thin-wall blade as non-blade root regions; wherein, the ultrasonic impact tool is interfered when the distance between the ultrasonic impact tool and the tenon is less than the interference threshold value.
Further, divide into not blade root district into advance exhaust edge area and profile area, specifically include:
and taking an intersection curve of the arc part of the air inlet and outlet edge of the thin-wall blade and the free curved surface of the blade profile as a boundary, and dividing the non-blade root region into an air inlet and outlet edge region and a profile region.
Further, the ultrasonic impact strengthening of the profile area by using a symmetrical ultrasonic impact tool comprises the following steps:
adopting a symmetrical ultrasonic impact tool to simultaneously carry out transverse/longitudinal ultrasonic impact strengthening along the blade basin part and the blade back part of the profile area;
the transverse direction is the length direction of the thin-wall blade, and the longitudinal direction is the width direction of the thin-wall blade.
Further ultrasonic impact strengthening of the profile area also comprises the following steps:
the processing line spacing in ultrasonic impact strengthening is less than 0.05 mm.
Further, the ultrasonic impact strengthening of the blade root area by the single-head ultrasonic impact tool comprises the following steps:
selecting a single-head ultrasonic impact tool with a spherical impact head according to the curvature of the leaf root area;
and carrying out ultrasonic impact strengthening on the blade root area by adopting a single-head ultrasonic impact tool with a spherical impact head.
Further, the ultrasonic impact strengthening of the blade root area by adopting the single-head ultrasonic impact tool with the spherical impact head comprises the following steps:
carrying out ultrasonic impact strengthening by taking parallel lines of edge lines of the tenon part as a cutter track; wherein the processing line spacing is less than 0.04 mm.
Further, when ultrasonic impact strengthening is carried out on the blade root area, the cutter shaft of the single-head ultrasonic impact tool is perpendicular to the processing surface.
Further, the ultrasonic impact strengthening of the air inlet and outlet side area by adopting a single-head ultrasonic impact tool comprises the following steps:
and carrying out ultrasonic impact strengthening on the air inlet and outlet side areas by adopting a single-head ultrasonic impact tool with a cylindrical impact head.
Further, the ultrasonic impact strengthening of the air inlet and outlet edge area further comprises the following steps:
carrying out ultrasonic impact strengthening on the air inlet and outlet edge area according to the cutter track of the thin-wall blade in the length direction; wherein the processing line spacing is less than 0.05 mm.
The invention has the beneficial effects that: according to the structural characteristics of the blade of the aero-engine, the blade is divided into three regions, the different regions adopt proper ultrasonic impact processing schemes, the purpose of ultrasonic impact strengthening on the thin-wall blade under the condition of avoiding processing deformation is achieved by adjusting the feed direction and the line spacing, and the surface roughness of the blade is improved.
Drawings
FIG. 1 is a schematic view of an ultrasonic impact system used in an embodiment of the present invention;
FIG. 2 is a schematic structural view of a single-headed ultrasonic impact tool used in an embodiment of the invention;
FIG. 3 is a schematic view of a symmetric ultrasonic impact actuator used in embodiments of the present invention;
FIG. 4 is a schematic view of a blade root zone being ultrasonically impact-strengthened according to an embodiment of the present invention;
FIG. 5 is a schematic view of the blade area division in an embodiment of the present invention;
FIG. 6 is a schematic view of a symmetrical ultrasonic impact feed path of a profile zone in an embodiment of the present invention;
FIG. 7 is a schematic illustration of an ultrasonic impact feed path in the root region of an embodiment of the present invention;
FIG. 8 is a schematic diagram of the ultrasonic impact feed path of the air inlet and outlet edge regions in the embodiment of the invention.
10. An ultrasonic signal power supply; 20. an intake valve; 30. a piezoelectric crystal; 40. an amplitude transformer; 50. ultrasonic rolling head; 60. a workpiece; 70. a profiled region; 80. a leaf root region; 90. and an air inlet and outlet side area.
Detailed Description
The present invention will be described in detail below with reference to the accompanying drawings and specific embodiments.
Compared with other processes, the ultrasonic impact strengthening process has the advantages of controllable processing path, convenient operation and capability of generating a considerable surface strengthening layer with smaller force. However, ultrasonic impact strengthening is commonly used for strengthening plane and shaft workpieces, because deformation caused by ultrasonic impact strengthening processing is a problem which must be considered for thin-wall curved parts such as blades of aero-engines.
According to the regional ultrasonic impact strengthening method, the ultrasonic impact tool is combined with a five-axis numerical control machine tool, the application range of the ultrasonic impact strengthening process is expanded to the thin-wall parts such as blades of the aircraft engine, and a feasible option is provided for the surface strengthening method of the complex thin-wall parts. Specifically, as shown in fig. 1, an ultrasonic signal power supply 10 converts a common 50Hz alternating current into an electrical signal with a frequency of 20KHz, and transmits the electrical signal to a piezoelectric crystal 30, the electrical signal is converted into a tiny mechanical vibration by the piezoelectric crystal 30, and the amplitude of the mechanical vibration is amplified by an amplitude transformer 40 to drive an ultrasonic rolling head 50 to strengthen the surface of a workpiece 60. During machining, static pressure is provided to the ultrasonic impact tool through the air inlet valve 20.
In the embodiment of the invention, the cutter is processed by adopting the combination of a double-head symmetrical ultrasonic rolling cutter and a single-head ultrasonic rolling cutter, wherein the single-head cutter adopts rolling heads in a spherical form and a cylindrical form. The static pressure of the ultrasonic rolling cutter is provided by compressed air generated by an air compression station, and the magnitude of the static pressure is determined according to the mechanical property of the material. The ultrasonic power supply converts 220V and 50Hz alternating current into 20kHz ultrasonic electric signals, transmits the ultrasonic electric signals to the piezoelectric crystal 30 in the ultrasonic rolling cutter, converts the ultrasonic electric signals into mechanical vibration, and transmits the mechanical vibration to the surface of a workpiece 60 after the mechanical vibration is amplified by the amplitude transformer 40.
The symmetrical ultrasonic rolling tool comprises two ultrasonic rolling tool units, the two units generate ultrasonic vibration with the same phase, frequency and amplitude during processing, and the static pressure acting on the two sides of the workpiece is also the same. The distance between the impact heads in the two ultrasonic impact units of the symmetrical ultrasonic impact tool can be adjusted within the range of 0-17mm so as to adapt to the change of the thickness of the thin-wall curved surface.
The invention discloses a thin-wall blade regional ultrasonic impact strengthening method, which comprises the following steps:
dividing the thin-wall blade into a blade root area 80, an air inlet and outlet edge area 90 and a molded surface area 70 according to a theoretical model and an actually measured three-dimensional model of the thin-wall blade; ultrasonic impact strengthening is performed on the profile area 70 by using a symmetrical ultrasonic impact tool (shown in fig. 3); carrying out ultrasonic impact strengthening on the leaf root region 80 by adopting a single-head ultrasonic impact tool; carrying out ultrasonic impact strengthening on the air inlet and outlet side area 90 by adopting a single-head ultrasonic impact tool (shown in figure 2) to finish the ultrasonic impact strengthening of the thin-wall blade; wherein, the ultrasonic impact strengthening processing mode is one-way feed.
According to the structural characteristics of the blade of the aero-engine, the blade is divided into three regions, the different regions adopt proper ultrasonic impact processing schemes, the purpose of ultrasonic impact strengthening on the thin-wall blade under the condition of avoiding processing deformation is achieved by adjusting the feed direction and the line spacing, and the surface roughness of the blade is improved.
As shown in fig. 4, determining an interference region according to an interference condition between a tenon portion of the thin-wall blade and the symmetric ultrasonic impact tool, dividing the interference region into a blade root region, and setting other portions of the thin-wall blade as non-blade root regions; wherein, the ultrasonic impact tool is interfered when the distance from the tenon is less than the interference threshold, and the interference threshold is designed to be 5mm in the embodiment.
The intersection curve of the arc part of the air inlet and outlet edge of the thin-wall blade and the free curved surface of the blade profile is used as a boundary, and the non-blade root area is divided into an air inlet and outlet edge area 90 and a profile area 70. In this way, the divided regions shown in fig. 5 can be obtained.
When the blade is subjected to strengthening processing, specifically, a symmetrical ultrasonic impact tool is adopted, and meanwhile, transverse/longitudinal ultrasonic impact strengthening is carried out along the blade basin part and the blade back part of the profile area. In order to improve the stability of the processing process, the path can adopt a transverse direction or a longitudinal direction according to the working load condition of the blade (wherein, the transverse direction is the length direction of the thin-walled blade, and the longitudinal direction is the width direction of the thin-walled blade), and the unidirectional feed is required to be maintained, as shown in FIG. 6
Taking TC17 material blade and impact head with diameter of 4mm as example, the line distance should be less than 0.05mm, the linear velocity should be more than 1000mm/min, and the static pressure is about 40N.
When the blade root area is subjected to strengthening processing, a single-head ultrasonic impact tool with a spherical impact head is selected according to the curvature of the blade root area, and the blade root area is subjected to ultrasonic impact strengthening by adopting the single-head ultrasonic impact tool with the spherical impact head. During machining, as shown in fig. 7, unidirectional feed machining is performed along the length direction of the region (i.e., ultrasonic impact is performed by using parallel lines of edge lines of the tenon portion as tool paths), and the tool shaft is kept as perpendicular as possible to the machining surface during machining.
Taking TC17 material blade and impact head with diameter of 4mm as example, the line spacing should be less than 0.04mm during processing, the linear velocity is about 500mm/min, and the static pressure is not more than 20N.
When the air inlet and outlet side areas are subjected to ultrasonic impact strengthening, a single-head ultrasonic impact tool with a cylindrical impact head is adopted to perform ultrasonic impact strengthening on the air inlet and outlet side areas. Specifically, as shown in fig. 8, the air inlet and outlet edge regions are subjected to unidirectional feed ultrasonic impact strengthening by using a tool path in the longitudinal direction of the thin-walled blade.
Taking TC17 material blade and impact head with diameter of 4mm as example, the line spacing should be less than 0.05mm, the linear velocity should be greater than 1000mm/min, and the static pressure should not exceed 20N.
Taking the TC17 titanium alloy as an example in the embodiment of the present invention: the surface roughness Ra of the workpiece after milling and shot blasting is more than 0.3 mu m, the individual workpiece even reaches 2.9 mu m, and the surface residual compressive stress is within the range of 600-800 MPa. After the milling and ultrasonic rolling strengthening of the embodiment of the invention are adopted, the surface roughness Ra of all workpieces is within 0.2 mu m, the surface residual compressive stress is within the range of 900-1300 MPa, and the microhardness and the grain refinement degree of the surface layer of the material are also remarkably improved, which are very beneficial to the fatigue performance of the engine blade.
Claims (10)
1. A thin-wall blade regional ultrasonic impact strengthening method is characterized by comprising the following steps:
dividing the thin-wall blade into a blade root area, an air inlet and outlet edge area and a profile area according to a theoretical model and an actually measured three-dimensional model of the thin-wall blade;
carrying out ultrasonic impact strengthening on the profile area by adopting a symmetrical ultrasonic impact tool;
carrying out ultrasonic impact strengthening on the leaf root area by adopting a single-head ultrasonic impact tool;
carrying out ultrasonic impact strengthening on the air inlet and outlet side area by adopting a single-head ultrasonic impact tool to finish the ultrasonic impact strengthening of the thin-wall blade;
wherein the ultrasonic impact strengthening processing mode is one-way feed.
2. The method of claim 1, wherein the dividing of the thin-walled blade into a blade root region, an air inlet and outlet edge region and a profile region comprises:
determining an interference region according to the interference condition of the tenon part of the thin-wall blade and the symmetrical ultrasonic impact tool, dividing the interference region into a blade root region, and taking other parts of the thin-wall blade as non-blade root regions; wherein, the ultrasonic impact tool is interfered when the distance between the ultrasonic impact tool and the tenon is less than the interference threshold value.
3. The thin-wall blade subregion ultrasonic impact strengthening method of claim 2, characterized in that, divide the non-blade root region into an air inlet and outlet edge region and a profile region, specifically comprising:
and dividing the non-blade root region into an air inlet and outlet edge region and a profile region by taking an intersection curve of the air inlet and outlet edge arc part of the thin-wall blade and the free curved surface of the profile of the blade as a boundary.
4. The method for ultrasonic impact strengthening of the thin-wall blade subarea according to claim 1, wherein the ultrasonic impact strengthening of the profile area by using a symmetrical ultrasonic impact tool comprises the following steps:
adopting a symmetrical ultrasonic impact tool to simultaneously carry out transverse/longitudinal ultrasonic impact strengthening along the blade basin part and the blade back part of the profile area;
the transverse direction is the length direction of the thin-wall blade, and the longitudinal direction is the width direction of the thin-wall blade.
5. The method of claim 4, wherein the ultrasonic impact strengthening of the profiled surface area further comprises:
the processing line spacing in the ultrasonic impact strengthening is less than 0.05 mm.
6. The method for ultrasonic impact strengthening of the thin-wall blade sub-region according to any one of claims 2 to 5, wherein the ultrasonic impact strengthening of the blade root region by using a single-head ultrasonic impact tool comprises the following steps:
selecting a single-head ultrasonic impact tool with a spherical impact head according to the curvature of the root zone;
and carrying out ultrasonic impact strengthening on the leaf root region by adopting the single-head ultrasonic impact tool with the spherical impact head.
7. The method for ultrasonic impact strengthening of the thin-walled blade sub-region according to claim 6, wherein the ultrasonic impact strengthening of the blade root region by the single-head ultrasonic impact tool with the spherical impact head comprises:
taking parallel lines of edge lines of the tenon part as cutter tracks for carrying out ultrasonic impact strengthening; wherein the processing line spacing is less than 0.04 mm.
8. The method for ultrasonic impact strengthening of the thin-walled blade in the sub-region according to claim 7, wherein when the blade root region is subjected to ultrasonic impact strengthening, a cutter shaft of the single-head ultrasonic impact tool is perpendicular to a processing surface.
9. The method for ultrasonic impact strengthening of the thin-wall blade sub-region according to claim 8, wherein the ultrasonic impact strengthening of the air inlet and outlet edge region by using a single-head ultrasonic impact tool comprises the following steps:
and carrying out ultrasonic impact strengthening on the air inlet and outlet side area by adopting a single-head ultrasonic impact tool with a cylindrical impact head.
10. The method for ultrasonic impact strengthening of the thin-walled blade sub-region according to claim 9, wherein the ultrasonic impact strengthening of the air inlet and outlet edge region further comprises:
carrying out ultrasonic impact strengthening on the air inlet and outlet edge area according to the cutter track of the thin-wall blade in the length direction; wherein the processing line spacing is less than 0.05 mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111647722.2A CN114293121B (en) | 2021-12-30 | 2021-12-30 | Thin-wall blade regional ultrasonic impact strengthening method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111647722.2A CN114293121B (en) | 2021-12-30 | 2021-12-30 | Thin-wall blade regional ultrasonic impact strengthening method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114293121A true CN114293121A (en) | 2022-04-08 |
| CN114293121B CN114293121B (en) | 2022-06-24 |
Family
ID=80972738
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111647722.2A Active CN114293121B (en) | 2021-12-30 | 2021-12-30 | Thin-wall blade regional ultrasonic impact strengthening method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114293121B (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4151012A (en) * | 1977-04-11 | 1979-04-24 | Latrobe Steel Company | High strength, corrosion resistant tubular products and methods of making the same |
| US20060147311A1 (en) * | 2004-11-30 | 2006-07-06 | General Electric Company | Fatigue-resistant components and method therefor |
| CN101558174A (en) * | 2005-09-23 | 2009-10-14 | Uit有限责任公司 | Method of metal performance improvement and protection against degradation and suppression thereof by ultrasonic impact |
| CN105734233A (en) * | 2016-03-08 | 2016-07-06 | 山东华云机电科技有限公司 | Ultrasound enhancing method for prolonging fatigue life of metal workpiece and application of method |
| DE102015204942A1 (en) * | 2015-03-19 | 2016-09-22 | Robert Bosch Gmbh | Blower fan for a blower module and blower module, in particular HVAC blower module |
| CN109465680A (en) * | 2018-12-17 | 2019-03-15 | 中国航发动力股份有限公司 | A method of it is ultrasound-enhanced for integral blade disk or blade profile |
-
2021
- 2021-12-30 CN CN202111647722.2A patent/CN114293121B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4151012A (en) * | 1977-04-11 | 1979-04-24 | Latrobe Steel Company | High strength, corrosion resistant tubular products and methods of making the same |
| US20060147311A1 (en) * | 2004-11-30 | 2006-07-06 | General Electric Company | Fatigue-resistant components and method therefor |
| CN101558174A (en) * | 2005-09-23 | 2009-10-14 | Uit有限责任公司 | Method of metal performance improvement and protection against degradation and suppression thereof by ultrasonic impact |
| DE102015204942A1 (en) * | 2015-03-19 | 2016-09-22 | Robert Bosch Gmbh | Blower fan for a blower module and blower module, in particular HVAC blower module |
| CN105734233A (en) * | 2016-03-08 | 2016-07-06 | 山东华云机电科技有限公司 | Ultrasound enhancing method for prolonging fatigue life of metal workpiece and application of method |
| CN109465680A (en) * | 2018-12-17 | 2019-03-15 | 中国航发动力股份有限公司 | A method of it is ultrasound-enhanced for integral blade disk or blade profile |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114293121B (en) | 2022-06-24 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Klocke et al. | Abrasive machining of advanced aerospace alloys and composites | |
| CN103255420B (en) | Titanium aluminide product with improved surface smoothness | |
| US11292147B2 (en) | Methods of cutting fiber reinforced polymer composite workpieces with a pure waterjet | |
| CN110076350B (en) | Ultrasonic stamping type cutting and extruding integrated processing method | |
| Liu et al. | Chipping minimization in drilling ceramic materials with rotary ultrasonic machining | |
| WO2017152683A1 (en) | Ultrasound enhancing method for prolonging fatigue life of metal workpiece and use thereof | |
| Zeng et al. | Research on dynamic characteristic of softness consolidation abrasives in machining process | |
| US20020174528A1 (en) | Apparatus for providing a residual stress distribution in the surface of a part | |
| Xiao et al. | An integrated polishing method for compressor blade surfaces | |
| CN102528077A (en) | Processing method of ferrous metal super-finishing surface | |
| US10228669B2 (en) | Machine tool monitoring | |
| US20160297044A1 (en) | Machining parameter control based on acoustic monitoring | |
| Hou et al. | Research on belt grinding for marine propeller blade based on the second-order osculation | |
| Gdula | Adaptive method of 5-axis milling of sculptured surfaces elements with a curved line contour | |
| CN114293121B (en) | Thin-wall blade regional ultrasonic impact strengthening method | |
| WO2001064397A2 (en) | Method for reducing tensile stress zones in the surface of a part | |
| CN114908224B (en) | Material surface composite strengthening device and method | |
| CN200995352Y (en) | Pneumatic controlling system of self-adaptive five-coordinate blade polisher | |
| CN109465680A (en) | A method of it is ultrasound-enhanced for integral blade disk or blade profile | |
| CN102632371A (en) | Processing technology of engine valve | |
| CN105195975A (en) | Method for machining inner surface of cylinder barrel of AGC (automatic gain control) servo cylinder | |
| Choi et al. | NC code generation for laser assisted turn-mill of various type of clovers and square section members | |
| Tawakoli et al. | Effects of ultrasonic assisted grinding on CBN grinding wheels performance | |
| Li et al. | Experimental research on the belt grinding technology for the real-R edge of the aero-engine precision-forging blade | |
| Zhang et al. | Control of ultrasonic surface rolling process machine tool for aero-engine blades |
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 | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |