CN111360399A - Laser welding forming method for titanium alloy control surface - Google Patents
Laser welding forming method for titanium alloy control surface Download PDFInfo
- Publication number
- CN111360399A CN111360399A CN201811601087.2A CN201811601087A CN111360399A CN 111360399 A CN111360399 A CN 111360399A CN 201811601087 A CN201811601087 A CN 201811601087A CN 111360399 A CN111360399 A CN 111360399A
- Authority
- CN
- China
- Prior art keywords
- welding
- control surface
- framework
- welded
- titanium alloy
- 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
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K26/00—Working by laser beam, e.g. welding, cutting or boring
- B23K26/20—Bonding
- B23K26/21—Bonding by welding
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K26/00—Working by laser beam, e.g. welding, cutting or boring
- B23K26/14—Working by laser beam, e.g. welding, cutting or boring using a fluid stream, e.g. a jet of gas, in conjunction with the laser beam; Nozzles therefor
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K37/00—Auxiliary devices or processes, not specially adapted to a procedure covered by only one of the preceding main groups
- B23K37/04—Auxiliary devices or processes, not specially adapted to a procedure covered by only one of the preceding main groups for holding or positioning work
- B23K37/0426—Fixtures for other work
- B23K37/0435—Clamps
- B23K37/0443—Jigs
Landscapes
- Physics & Mathematics (AREA)
- Optics & Photonics (AREA)
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Plasma & Fusion (AREA)
- Laser Beam Processing (AREA)
- Arc Welding In General (AREA)
Abstract
The invention provides a laser welding forming method for a titanium alloy control surface, belongs to the technical field of titanium alloy control surface forming, and particularly relates to the laser welding forming method for the titanium alloy control surface. The problem of current large thickness covering welding have the welding seam quality poor, welding deflection is big is solved. The method comprises the steps of manufacturing a welding tool and welding a control surface framework and a skin. The method is mainly used for forming the titanium alloy control surface.
Description
Technical Field
The invention belongs to the technical field of titanium alloy control surface forming, and particularly relates to a laser welding forming method of a titanium alloy control surface.
Background
The air rudder is a key component in the aircraft and plays a vital role in the flight trajectory and action of the aircraft. As an aerodynamic assembly, the aerodynamic assembly bears huge acting force, and in addition, in the process of high-speed movement of an aircraft, a control surface can bear severe working environments such as continuous high temperature and the like. In order to meet the above requirements, the structure and material of the control surface are required to have excellent performance. The welding process of the skin and the framework needs to meet the design index.
Titanium alloy shows excellent properties in most severe environments such as high temperature, low temperature and the like due to high strength and low density, and is widely applied to various structural members of aircrafts at present. Laser welding as a high-energy beam welding has the advantages of large depth-to-width ratio of welding seams, small heat affected zone, small welding deformation and the like, and in addition, compared with electron beam welding, laser welding does not need to complete welding in a vacuum environment, so that the laser welding has greater flexibility on the size and the structure of the welding seams. Therefore, laser welding is also increasingly used in the fields of automobiles, electronics, and aerospace.
At present, the improvement of the performance of aircraft structural parts by reducing the weight of the aircraft structural parts is a key direction of domestic and foreign research. For air rudder products, the framework structure is optimized in a mode of welding the framework and the skin, the purpose of reducing weight is achieved on the premise of meeting mechanical properties, and the welding of the skin with large thickness has the problems of poor welding seam quality, large welding deformation and the like.
Disclosure of Invention
The invention provides a laser welding forming method of a titanium alloy control surface, aiming at solving the problems in the prior art.
In order to achieve the purpose, the invention adopts the following technical scheme: a laser welding forming method for a titanium alloy control surface comprises the following steps:
the method comprises the following steps: manufacturing a welding tool, keeping a cavity in the welding tool consistent with the profile of the control surface, and ensuring that the welding surface is a horizontal plane through angle complementation;
step two: fixing a welding tool on the welding table top, and fixing the control surface framework on the welding tool;
step three: inputting welding parameters into a welding program according to the positions of the strengthening ribs in the framework;
step four: fixing the skin to one side of the control surface framework, and tack-welding the skin to the control surface framework according to a welding program from top to bottom and from left to right, wherein the tack-welding position is the center of the intersection of each rib;
step five: welding the skin to the other side of the skeleton in a tack welding manner according to the method in the fourth step;
step six: intermittently welding radial ribs in the middle of the control surface framework, wherein the welding sequence is that one side of the control surface framework is welded firstly and the other side of the control surface framework is welded secondly, and each side is welded from the middle reinforcing rib to the two side reinforcing ribs in sequence;
step seven: intermittently welding arc-shaped ribs in the middle of the control surface framework, wherein the welding sequence is that one side of the control surface framework is welded firstly and the other side of the control surface framework is welded secondly, and each side is welded from a middle reinforcing rib to two side reinforcing ribs in sequence;
step eight: and carrying out angle type continuous welding on the peripheral positions of the skins, wherein the welding sequence is that one side of the control surface framework is welded firstly and the other side of the control surface framework is welded secondly, and the skins on the two sides of the control surface framework are welded according to the same direction sequence.
Furthermore, the bottom of the welding tool is provided with a ring groove, and the top of the welding tool is provided with a threaded hole.
Furthermore, the deviation of the intermittent welding positions in the third step and the fourth step along the center line of the rib is less than 0.5mm, the intermittent welding length is 12mm, the pitch is 24mm, and the deviation is less than 1 mm.
Furthermore, the distance between the edge of the skin and the position of the sunken edge and the edge of the control surface skeleton is 2.5mm, and the deviation is less than 0.5 mm.
Furthermore, the laser welding process parameters are as follows: the welding power is 2800KW, the defocusing amount is-8, the welding speed is 1.5m/min, and the protective gas flow is 20L/min.
Compared with the prior art, the invention has the beneficial effects that: the laser welding forming method of the titanium alloy control surface ensures that the requirements of the internal and external quality of a welding line, the mechanical property of a joint, the planeness and the symmetry of the control surface after welding and the like all meet the design indexes, and the welding joint reaches the I-grade requirement; the product can achieve the effect that the air does not leak under the action of 1MPa of air pressure and internal pressure for 10min, and can meet the requirements of welding deformation such as flatness of a control surface, a rear edge and a bottom edge of a welded part being not more than 0.6, straightness of the front edge being not more than 0.2 and the like. The method also optimizes welding parameters, reduces the output of welding heat as much as possible while meeting the requirements of weld penetration, weld width, mechanical property and internal quality, and obtains proper welding line energy by matching parameters such as optimal welding power, welding rate, defocusing amount and the like so as to reduce welding deformation to the maximum extent. The problems of poor welding seam quality and overlarge welding deformation caused by welding of the large-thickness skin can be effectively solved.
Drawings
FIG. 1 is a schematic view of a control surface structure of the invention
FIG. 2 is a schematic view of a welding tool structure according to the present invention
FIG. 3 is a schematic view of the welding sequence of the reinforcing ribs of the control surface framework of the invention
Detailed Description
The technical solution in the embodiments of the present invention will be clearly and completely explained below with reference to the drawings in the embodiments of the present invention.
Referring to fig. 1 to 3, the embodiment is described, and a laser welding forming method of a titanium alloy control surface comprises the following steps:
the method comprises the following steps: manufacturing a welding tool, keeping a cavity in the welding tool consistent with the profile of the control surface, and ensuring that the welding surface is a horizontal plane through angle complementation;
step two: fixing a welding tool on the welding table top, and fixing the control surface framework on the welding tool;
step three: inputting welding parameters into a welding program according to the positions of the strengthening ribs in the framework;
step four: fixing the skin to one side of the control surface framework, and tack-welding the skin to the control surface framework according to a welding program from top to bottom and from left to right, wherein the tack-welding position is the center of the intersection of each rib;
step five: welding the skin to the other side of the skeleton in a tack welding manner according to the method in the fourth step;
step six: intermittently welding radial ribs in the middle of the control surface framework, wherein the welding sequence is that one side of the control surface framework is welded firstly and the other side of the control surface framework is welded secondly, and each side is welded from the middle reinforcing rib to the two side reinforcing ribs in sequence;
step seven: intermittently welding arc-shaped ribs in the middle of the control surface framework, wherein the welding sequence is that one side of the control surface framework is welded firstly and the other side of the control surface framework is welded secondly, and each side is welded from a middle reinforcing rib to two side reinforcing ribs in sequence;
step eight: and carrying out angle type continuous welding on the peripheral positions of the skins, wherein the welding sequence is that one side of the control surface framework is welded firstly and the other side of the control surface framework is welded secondly, and the skins on the two sides of the control surface framework are welded according to the same direction sequence.
The embodiment of the invention is suitable for laser welding of a skin control surface with the thickness of 3mm, the control surface is a multi-angle structural member, and skin welding parts on two sides are of a symmetrical structure. In order to ensure that the welding surface is positioned on a horizontal plane, a welding tool needs to be designed. Before welding, a welding tool is fixed on a workbench surface, a control surface framework is fixed on the tool, a welding program is edited, then a skin is fixed on the framework for welding, and the welding of the skin on the other side is completed by adopting the tool which has the same structural form and is symmetrical to the skin. The tool can fix the control surface framework and can also play a role in fixing the skin, and meanwhile, the tool plays a role in fixing and restraining the welding piece, so that the welding deformation can be effectively reduced. The method also explains the sequence of skin spot-fixing and welding, the reinforcing ribs of the control surface framework are in a radial structure, and the radial reinforcing ribs are connected by arc-shaped reinforcing ribs. The skin tack welding is finished from the center of the arc to the outside in sequence. The method can ensure that the gap between the skin and the framework is less than 0.1 mm. The welding sequence is that the middle rib is intermittently welded firstly, and the middle rib is continuously welded. In the intermittent welding process of the middle ribs, the radial ribs are welded at first, the arc-shaped ribs are welded, the welding sequence among the ribs is that the radial ribs are welded from the middle to two sides in sequence, skins at two sides are symmetrically welded, and finally the peripheral angle type continuous welding is completed. According to the method, the problem of overlarge welding deformation caused by welding of the large-thickness skin can be effectively solved, and various related design indexes of the control surface welding can be met according to the method.
Fig. 1 is a schematic view of a control surface structure, as shown in a, such a control surface mainly comprises a framework and a skin, wherein the skin of the control surface is a TA15 titanium plate with the thickness of 3mm, and is embedded into the framework of the control surface, and the distance from the edge of the skin to the sunken position of the framework is uniform and consistent with the distance from the edge of the framework. The control surface framework is a hollow structure with latticed reinforcing ribs as shown in b. The reinforcing ribs are divided into radial and circular arc. The dotted line is the welding position, the periphery adopts the angle type continuous welding, and the middle position adopts the lap intermittent welding. The control surface is a multi-angle structural member, the minimum thickness of the front edge of the framework of the control surface is less than 2mm, and deformation is easy to generate after welding. And c, welding skins on two sides of the control surface, wherein the welding surfaces on the two sides are of a symmetrical structure.
The deviation of the intermittent welding position in the third step and the fourth step of the method along the center line of the rib is less than 0.5mm, the intermittent welding length is 12mm, the pitch is 24mm, the deviation is less than 1m, the distance between the edge of the skin and the position of the sunken edge and the edge of the control surface framework is 2.5mm, and the deviation is less than 0.5 mm. And (5) performing lap-joint intermittent welding after the skin on the other side is tack-welded according to the same method.
The welding sequence of the reinforcing ribs of the control surface framework is shown in figure 3, the radial reinforcing ribs are welded firstly, the welding direction is from inside to outside, welding is carried out according to the sequence of 1-4, then the arc-shaped ribs are welded, and welding is carried out according to the sequence of a-c. And welding the skin on the other side after welding on one side. And finally, carrying out continuous welding of the angle type of the periphery of the skin, wherein the skins at two sides are required to be welded in the same direction.
The laser welding process parameters of the method are as follows: the welding power is 2800KW, the defocusing amount is-8, the welding speed is 1.5m/min, and the protective gas flow is 20L/min. According to the method, the shearing strength of the welding joint is more than 550 MPa; the welding joint meets the I-grade requirement; the product can achieve the effect of no air leakage within 10min under the action of the pressure of 1MPa in the air pressure. In addition, the requirements of welding deformation such as flatness of a control surface, a trailing edge and a bottom edge after welding is not more than 0.6, straightness of the leading edge is not more than 0.2 and the like can be met.
The method for laser welding and forming the titanium alloy control surface provided by the invention is described in detail, a specific example is applied in the method to explain the principle and the implementation mode of the invention, and the description of the example is only used for helping to understand the method and the core idea of the invention; meanwhile, for a person skilled in the art, according to the idea of the present invention, there may be variations in the specific embodiments and the application scope, and in summary, the content of the present specification should not be construed as a limitation to the present invention.
Claims (6)
1. A laser welding forming method of a titanium alloy control surface is characterized by comprising the following steps: it comprises the following steps:
the method comprises the following steps: manufacturing a welding tool, keeping a cavity in the welding tool consistent with the profile of the control surface, and ensuring that the welding surface is a horizontal plane through angle complementation;
step two: fixing a welding tool on the welding table top, and fixing the control surface framework on the welding tool;
step three: inputting welding parameters into a welding program according to the positions of the strengthening ribs in the framework;
step four: fixing the skin to one side of the control surface framework, and tack-welding the skin to the control surface framework according to a welding program from top to bottom and from left to right, wherein the tack-welding position is the center of the intersection of each rib;
step five: welding the skin to the other side of the skeleton in a tack welding manner according to the method in the fourth step;
step six: intermittently welding radial ribs in the middle of the control surface framework, wherein the welding sequence is that one side of the control surface framework is welded firstly and the other side of the control surface framework is welded secondly, and each side is welded from the middle reinforcing rib to the two side reinforcing ribs in sequence;
step seven: intermittently welding arc-shaped ribs in the middle of the control surface framework, wherein the welding sequence is that one side of the control surface framework is welded firstly and the other side of the control surface framework is welded secondly, and each side is welded from a middle reinforcing rib to two side reinforcing ribs in sequence;
step eight: and carrying out angle type continuous welding on the peripheral positions of the skins, wherein the welding sequence is that one side of the control surface framework is welded firstly and the other side of the control surface framework is welded secondly, and the skins on the two sides of the control surface framework are welded according to the same direction sequence.
2. The laser welding forming method of the titanium alloy control surface according to claim 1, characterized in that: the skin is a TA15 titanium plate with the thickness of 3 mm.
3. The laser welding forming method of the titanium alloy control surface according to claim 1, characterized in that: the welding tool is provided with a ring groove at the bottom and a threaded hole at the top.
4. The laser welding forming method of the titanium alloy control surface according to claim 1, characterized in that: and the deviation of the continuous welding positions in the sixth step and the seventh step along the center line of the rib is less than 0.5mm, the length of the continuous welding is 12mm, the pitch is 24mm, and the deviation is less than 1 mm.
5. The laser welding forming method of the titanium alloy control surface according to claim 1, characterized in that: the distance between the edge of the skin and the position of the sunken edge and the edge of the control surface skeleton is 2.5mm, and the deviation is less than 0.5 mm.
6. The laser welding forming method of the titanium alloy control surface according to claim 1, characterized in that: the laser welding process parameters are as follows: the welding power is 2800KW, the defocusing amount is-8, the welding speed is 1.5m/min, and the protective gas flow is 20L/min.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811601087.2A CN111360399B (en) | 2018-12-26 | 2018-12-26 | Laser welding forming method for titanium alloy control surface |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811601087.2A CN111360399B (en) | 2018-12-26 | 2018-12-26 | Laser welding forming method for titanium alloy control surface |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111360399A true CN111360399A (en) | 2020-07-03 |
| CN111360399B CN111360399B (en) | 2022-01-04 |
Family
ID=71200536
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811601087.2A Active CN111360399B (en) | 2018-12-26 | 2018-12-26 | Laser welding forming method for titanium alloy control surface |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111360399B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114180028A (en) * | 2021-12-09 | 2022-03-15 | 北京星航机电装备有限公司 | Assembly for preparing hollow grid structure wing rudder and preparation method of wing rudder |
| CN115889997A (en) * | 2022-12-30 | 2023-04-04 | 华钛空天(北京)技术有限责任公司 | Method for welding control surface by laser welding |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1990149A (en) * | 2005-12-30 | 2007-07-04 | 航天材料及工艺研究所 | Welding method of titanium alloy framework and covering variable cross-section element |
| JP2008272768A (en) * | 2007-04-26 | 2008-11-13 | Nippon Sharyo Seizo Kaisha Ltd | Welding joint and structure of double skin panel |
| CN102862021A (en) * | 2012-08-19 | 2013-01-09 | 什邡市明日宇航工业股份有限公司 | Method for manufacturing rudder assembly of aircraft by laser welding |
| CN104400283A (en) * | 2014-09-25 | 2015-03-11 | 北京航星机器制造有限公司 | Welding device for titanium alloy skin structural member for framework |
| CN105057990A (en) * | 2015-08-21 | 2015-11-18 | 北京星航机电装备有限公司 | Forming method of lightweight missile wing with integral diffusion bonding structure of envelope and framework |
| CN106425309A (en) * | 2016-11-14 | 2017-02-22 | 北京星航机电装备有限公司 | Method for machining and manufacturing titanium alloy folding airfoils |
| CN107717224A (en) * | 2017-09-26 | 2018-02-23 | 北京普惠三航科技有限公司 | The processing method of the hollow lightweight aerofoil of titanium alloy |
| CN108161205A (en) * | 2017-12-06 | 2018-06-15 | 北京星航机电装备有限公司 | A kind of wing rudder class part electron beam welding SPF Technology |
| CN108672935A (en) * | 2018-07-25 | 2018-10-19 | 北京航星机器制造有限公司 | A kind of large size, thin walled weak rigid titanium alloy rudder wing structure method for laser welding |
-
2018
- 2018-12-26 CN CN201811601087.2A patent/CN111360399B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1990149A (en) * | 2005-12-30 | 2007-07-04 | 航天材料及工艺研究所 | Welding method of titanium alloy framework and covering variable cross-section element |
| JP2008272768A (en) * | 2007-04-26 | 2008-11-13 | Nippon Sharyo Seizo Kaisha Ltd | Welding joint and structure of double skin panel |
| CN102862021A (en) * | 2012-08-19 | 2013-01-09 | 什邡市明日宇航工业股份有限公司 | Method for manufacturing rudder assembly of aircraft by laser welding |
| CN104400283A (en) * | 2014-09-25 | 2015-03-11 | 北京航星机器制造有限公司 | Welding device for titanium alloy skin structural member for framework |
| CN105057990A (en) * | 2015-08-21 | 2015-11-18 | 北京星航机电装备有限公司 | Forming method of lightweight missile wing with integral diffusion bonding structure of envelope and framework |
| CN106425309A (en) * | 2016-11-14 | 2017-02-22 | 北京星航机电装备有限公司 | Method for machining and manufacturing titanium alloy folding airfoils |
| CN107717224A (en) * | 2017-09-26 | 2018-02-23 | 北京普惠三航科技有限公司 | The processing method of the hollow lightweight aerofoil of titanium alloy |
| CN108161205A (en) * | 2017-12-06 | 2018-06-15 | 北京星航机电装备有限公司 | A kind of wing rudder class part electron beam welding SPF Technology |
| CN108672935A (en) * | 2018-07-25 | 2018-10-19 | 北京航星机器制造有限公司 | A kind of large size, thin walled weak rigid titanium alloy rudder wing structure method for laser welding |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114180028A (en) * | 2021-12-09 | 2022-03-15 | 北京星航机电装备有限公司 | Assembly for preparing hollow grid structure wing rudder and preparation method of wing rudder |
| CN115889997A (en) * | 2022-12-30 | 2023-04-04 | 华钛空天(北京)技术有限责任公司 | Method for welding control surface by laser welding |
| CN115889997B (en) * | 2022-12-30 | 2024-03-12 | 华钛空天(北京)技术有限责任公司 | Method for welding control surface by laser welding |
Also Published As
| Publication number | Publication date |
|---|---|
| CN111360399B (en) | 2022-01-04 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN111360399B (en) | Laser welding forming method for titanium alloy control surface | |
| CN107262713B (en) | Laser impact forging composite processing and forming device and method for coaxial powder feeding in light | |
| CN105108341A (en) | Laser-MAG welding method for steel plate of medium thickness and superhigh strength | |
| CN105436688A (en) | Vacuum electron beam welding method for variable-thickness ZL114A aluminum alloy | |
| CN109093270B (en) | Device and method for forming and manufacturing large-sized plate welding cabin body opening cover | |
| CN107511584A (en) | A kind of shape of a saddle aluminium alloy structure laser welding process method | |
| CN105328342A (en) | Method for removing laser welding pores of medium-thick D406A ultra-high-strength steel | |
| CN109158829A (en) | A kind of metal component optimization method and molding equipment based on increasing material technological forming | |
| CN110625335B (en) | Welding deformation control method for high-aspect-ratio framework skin wing type component | |
| CN102248298A (en) | Double laser beam welding method for reducing T-shaped joint welding deformation | |
| CN110539138B (en) | Preparation method of aluminum alloy lightweight active cooling structural skin | |
| WO2019080539A1 (en) | Method of manufacturing metal reinforced rim of composite material fan blade | |
| CN103537880A (en) | Method for welding high-strength steel through laser welding machine | |
| CN105817785A (en) | Laser welding method for variable-thickness variable-section thin-wall workpiece | |
| CN106670640A (en) | Electron beam welding method applicable to small-diameter flange plates on thin-wall top cover | |
| CN108941913A (en) | A kind of efficient laser-MAG compound welding method of slab marine high strength steel | |
| CN103737162A (en) | Compound welding method | |
| CN109604980A (en) | A kind of manufacturing method of long cylindrical mould structural member | |
| CN110439623B (en) | Metal edging for aircraft engine fan blade, machining tool and machining method | |
| CN104985326A (en) | Bilateral laser-InFocus electric arc composite welding method for T-type joint | |
| CN111085616A (en) | Forming die and manufacturing method of hollow complex structural member with support | |
| CN106738505A (en) | A kind of manufacture method of the composite material shaping mould with composite construction | |
| CN105382409A (en) | Laser shock processing method of thin plate welding structure | |
| CN105252118A (en) | Welding process for rear door of self-supporting van vehicle | |
| CN107283118A (en) | A kind of TC4 titanium alloys truss structure engine blade preparation method |
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 |