A quick tooling method for manufacturing a single-crystal blade of an aircraft engine by precise electrolytic machining

Abstract

A kind of manufacturing airplane engine single crystal blade precision electrolytic machining quick tooling method, including system touch screen, precision electrolytic machining system, electrolytic power supply;The precision electrolytic machining system includes electrolytic machining system rack, main shaft quick fixture system, main shaft drag plate assembly, left die electrode, electrolytic reaction box, right die electrode, main shaft machining reference quick positioning device A;It is characterized by: the main shaft quick fixture system includes workpiece clamping shaft, top spring bolt, top spring, insulating sleeve lock pin, clamping shaft seat, quick clamping device, top pin, parallel pad cover, parallel connecting bolt;The top spring bolt, top spring, top pin are used for active elastic top quick clamping device biasing in right side, to facilitate the quick loading and unloading of blade workpiece;Beneficial effect: due to the effect of quick clamping device, the prior art is replaced, and the blade workpiece is replaced after the insulating sleeve is disassembled, and the blade workpiece is replaced again by using tool wrench to disassemble bolt and clamp;Convenient and quick replacement blade workpiece;Improve blade processing efficiency.

Description

TECHNICAL FIELD

[0001] The application relates to a manufacturing method of a single-crystal blade of an aircraft engine, in particular to a quick tooling method for precision electrolytic machining of a single-crystal blade of an aircraft engine. BACKGROUND

[0002] As the heart of an aircraft, the development and production of an aircraft engine is a systematic project, which represents the scientific and technological level of a country to some extent. In recent years, the aviation and aerospace industry in China has made rapid progress, and a new generation of aircraft has been developed one after another. The development of aircraft engines has also made great progress, and the manufacturing technology of aircraft engines has played an important role. Among all the components of the engine, the blade is one of the most important parts. Due to its prominent role, special structure, twisted blade shape and other characteristics, it brings many difficulties to manufacturing, and has been the focus of research and development of production departments for many years. With the increasing demand for high thrust-to-weight ratio of the new generation of aircraft engines, especially the blades, most of the blades are currently made of difficult-to-machine materials such as titanium-aluminum alloy and high-temperature alloy. Due to the complex structure, high hardness, special curved shape, sharp and twisted leading and trailing edges, and strict precision requirements of the blade, the manufacturing of titanium-aluminum alloy blades is very difficult, and many new challenges are posed to machining and manufacturing.

[0003] Among many manufacturing technologies, electrolytic machining technology is one of the preferred solutions for the manufacturing of single-crystal blades of aircraft engines, because it has the special advantages of no tool wear, no limitation on the mechanical properties of the material itself, high machining efficiency, and is consistent with the characteristics of special materials, difficult machining and other characteristics in blade manufacturing.

[0004] Electrolytic machining is a processing method that removes materials by using the principle of electrochemical anodic dissolution, and belongs to the field of special processing. Electrolytic machining has the advantages of high machining efficiency, good surface quality, no electrode wear, wide machining range, etc. With the in-depth study of electrolytic machining technology, the precision and stability of electrolytic machining have been greatly improved, and the application has become more and more extensive, especially suitable for the needs of high-precision and difficult-to-machine aircraft engine blades. However, the anodic dissolution process of electrolytic machining is very complex, and the positioning tooling method of the main shaft machining reference has many varieties, and the structure is complex, which greatly limits the machining speed and efficiency.

[0005] There are still aspects to be improved in the electrolytic machining. In actual production, the structure of the workpiece clamp is complex, and the loading and unloading of the workpiece and the operation method are complicated, which are the main reasons for the low production efficiency and long production cycle of the electrolytic machining of aircraft engine blades. Therefore, the cost of batch production is high, and the cost is high, especially the smaller the batch, the higher the cost of single manufacturing.

[0006] The monocrystal blade of aircraft engine reduces density, improves structural strength and high temperature resistance coefficient from the characteristics of the material, but people hope to have a better breakthrough in the design of the structure. For many years, the lightweight of aircraft engine blade has been a high technology that people constantly pursue and challenge. For this reason, we have carried out research and development, design and test for many years, and will provide an optimal blade design scheme, hoping to play a prominent role in promoting the development of China's aviation industry.

[0007] Therefore, the research on the manufacturing and processing of aircraft engine monocrystal blades is a meaningful and good work. SUMMARY

[0008] The present application provides a kind of manufacturing aircraft engine monocrystal blade precision electrolytic processing fast tooling method, can solve the problems mentioned in the background art.

[0009] The key technical solution of the present application to solve its technical problems is: 1. According to the characteristics of electrolytic processing, the positioning tooling of main shaft machining reference and the mode structure of workpiece clamp are optimized, a fast positioning device of main shaft machining reference and a fast clamping device of workpiece are designed to improve the efficiency and quality of electrolytic processing of aircraft engine monocrystal blades; 2. Further, in order to improve the performance and quality of aircraft engine monocrystal blades, we have designed and tested the blade root part of aircraft engine monocrystal blades several times, optimized a kind of aircraft engine monocrystal blade with blade root gap structure, and then used precision electrolytic processing to form, in order to reduce the weight of aircraft engine monocrystal blades and solve the problem of lightweight of aircraft engine monocrystal blades; 3. Further, in order to realize the blade root gap structure, we start from the mold, design the cathode mold into two parts, and set multiple vacuum structures in the left and right molds. After electrolytic processing, the blade root of the aircraft engine monocrystal blade forms multiple root branch grooves and inner root branches, so that the blade root of the aircraft engine monocrystal blade has many gaps.

[0010] The application discloses a quick tooling method for precision electrolytic machining of single crystal blades of aircraft engine, which comprises a machine tool shell, a system touch screen, a precision electrolytic machining system, an operation panel, a control panel, an electrolyte output pipe, an electrolyte input pipe, a movable door, a right panel, a machine foot, a seat frame, a left panel, an electrolytic power supply and a control power supply.

[0011] The main shaft quick clamping system comprises an insulation sleeve, a workpiece clamping shaft, a sealing ring, a top spring bolt, a top spring, an insulation sleeve lock pin, a clamping shaft seat, a quick clamping device, a top pin and a parallel connection bolt.

[0012] The quick clamping device comprises a wire shaft, a wire sleeve stop ring, a wire sleeve flange seat, a wire sleeve, a trapezoidal seat piece, a trapezoidal seat piece adjusting bolt, a quick pull trapezoidal long piece, a connecting bolt pin and a flange seat bolt.

[0013] The workpiece clamping shaft comprises a shaft root, a shaft table, a lock pin hole, a top spring hole, a clamping shaft body, a workpiece seat hole, a trapezoidal seat piece adjusting hole and a quick pull channel.

[0014] The positioning tool of the spindle machining reference includes a spindle machining reference quick positioning device A and a spindle machining reference quick positioning device B. The spindle machining reference quick positioning device A includes a trapezoidal column, a push-away spring, a limiting top, a coil groove, an electric core, a coil, an indicator light, and a positioning button. The bottom surface of the trapezoidal column is long, the top is square, and the middle upper section is square. The middle upper section and the square top together form a square long column. The lower surface of the square long column and the bottom long surface of the trapezoidal column together form a trapezoidal long column with a small upper surface and a large lower surface. The trapezoidal column is provided with a coil groove at the square long column part, and the coil groove is provided with a coil. The middle part of the coil is an electric core. The coil and the electric core are combined to magnetically attract the spindle drag plate assembly. The trapezoidal column is provided with a push-away spring and a limiting top at the front wall surface below the coil. The limiting top is used to accurately limit the position of the spindle drag plate assembly. The limiting top is a convex column with a wear-resistant surface. The push-away spring is a compression spring used to push the spindle drag plate assembly back to the non-processing position after processing. The trapezoidal column is provided with an indicator light at the top. The indicator light is used to indicate the state of the spindle drag plate assembly during processing. When the spindle drag plate assembly is positioned and processed, the indicator light is on. When the spindle drag plate assembly is in the non-processing position, the indicator light is off.

[0015] The spindle machining reference quick positioning device A and the spindle machining reference quick positioning device B have the same structure, function, effect, and purpose. The difference lies in the position. The spindle machining reference quick positioning device A is arranged on the right side between the spindle drag plate assembly and the electrolytic reaction box. The spindle machining reference quick positioning device B is arranged on the left side between the spindle drag plate assembly and the electrolytic reaction box.

[0016] The spindle drag plate assembly includes a vertical seat, a terminal post, a positioning release button, a handle, a main drag plate, a connecting hole, an insulating partition, and a right-angle connecting plate. The handle is provided with a positioning release button. The positioning release button is used to turn on or off the power supply of the coil of the spindle machining reference quick positioning device A and the spindle machining reference quick positioning device B, thereby controlling the positioning release and reset of the spindle drag plate assembly.

[0017] The main shaft machining reference quick positioning device A and the main shaft machining reference quick positioning device B are arranged on both sides between the main shaft dragboard assembly and the electrolytic reaction box, the main shaft machining reference quick positioning device A is arranged on the right side, and the main shaft machining reference quick positioning device B is arranged on the left side; the coils of the main shaft machining reference quick positioning device A and the main shaft machining reference quick positioning device B are connected in parallel, when the single-crystal blade of the aircraft engine is electrolytically machined, the main shaft dragboard assembly is moved to the main shaft machining reference quick positioning device A and the main shaft machining reference quick positioning device B, the positioning button arranged on the main shaft machining reference quick positioning device A and the main shaft machining reference quick positioning device B is touched, so that the power supply of YA1, YA2 and the coil is turned on, the magnetic attraction force of the electric iron core is generated to tightly attract the main shaft dragboard assembly, and the positioning purpose of the main shaft dragboard assembly is achieved; when the electrolytic machining of the single-crystal blade of the aircraft engine is completed, the positioning release button on the handle is pressed to cut off the power supply of YA1, YA2 and the coil, the magnetic attraction force of the electric iron core is eliminated, meanwhile, the main shaft machining reference quick positioning device A and the main shaft machining reference quick positioning device B push the main shaft dragboard assembly away; the handle of the main shaft dragboard assembly is dragged to reset the main shaft dragboard assembly, and the next single-crystal blade of the aircraft engine is machined; the technical scheme can replace the existing technology, the dragboard and the workpiece are bolted and fixed during electrolytic machining, the bolt is disassembled after machining, the main shaft dragboard is reset, the next workpiece is installed, and the complicated work is avoided; the positioning of the main shaft dragboard assembly and the workpiece is convenient and fast, the advanced effect is achieved, the machining speed is improved, and the machining efficiency is improved.

[0018] The cathode mold comprises a left mold electrode and a right mold electrode.

[0019] The left mold electrode comprises a left mold body, a blade seat mold groove Z, an acute angle edge root branch mold groove Z, a root branch groove mold convex body Z, an inner root branch mold groove Z, an obtuse angle edge root branch groove mold convex body Z, an obtuse angle edge root branch mold groove Z, a blade seat flash B mold groove Z, a blade direction synchronous taper shaft mold hole Z, a workpiece groove Z and a left mold mounting buckle; the left mold mounting buckle is arranged at the left end of the left mold body and is used for being connected with a left feeding shaft.

[0020] The right mold electrode comprises a right mold body, a blade seat mold groove Y, an acute angle edge root branch mold groove Y, a root branch groove mold convex body Y, an inner root branch mold groove Y, an obtuse angle edge root branch groove mold convex body Y, an obtuse angle edge root branch mold groove Y, a blade seat flash B mold groove Y, a blade direction synchronous taper shaft mold hole Y, a workpiece groove Y and a right mold mounting buckle; the right mold mounting buckle is arranged at the right end of the right mold body and is used for being connected with a right feeding shaft.

[0021] The left mold electrode is arranged at the right end of the left feeding shaft of the electrolytic machining system, and the electrical connection connection mode of the left mold electrode is that the left mold electrode is connected with the left feeding shaft, the left feeding shaft is connected with the electrolytic machining system rack, and the electrolytic machining system rack is connected with an electrolytic power supply.

[0022] The right dielectric electrode device is arranged at the left end of the right feeding shaft of the electrolytic machining system, and the electrical connection of the right dielectric electrode is connected to the right feeding shaft, the right feeding shaft is connected to the electrolytic machining system rack, and the electrolytic machining system rack is connected to the electrolytic power supply;

[0023] Further, the single-crystal blade of the aircraft engine of the precise electrolytic machining comprises a blade root, a blade direction synchronous taper shaft, a blade seat, a blade body and a blade crown.

[0024] That is, the blade root is provided with a plurality of root branch grooves and a plurality of inner root branches, and the plurality of root branch grooves and the plurality of inner root branches are distributed at intervals to form a gap body in the blade root.

[0025] The width ratio of the root branch groove to the inner root branch is 1-1.5 to 1-1.5, and the preferred ratio is 1 to 1.

[0026] The beneficial effects of the present application are: 1. Due to the effect of the quick clamp device, the cumbersome work of disassembling the insulating sleeve, disassembling the bolt with a tool wrench, replacing the blade workpiece and clamping again in the prior art is replaced; the advanced effect of convenient and quick replacement of the blade workpiece is achieved; the purpose of improving the blade machining speed and improving the machining efficiency is achieved; 2. Due to the effect of the spindle machining reference quick positioning device A and the spindle machining reference quick positioning device B, the cumbersome work of the prior art of electrolytic machining, i.e. the spindle drag plate is bolted and fixed with the workpiece, the bolt is disassembled after machining to reset the spindle drag plate, and the next workpiece is installed for machining, is replaced; the advanced effect of convenient and quick positioning of the spindle drag plate assembly and the workpiece is achieved; the purpose of improving the machining speed and improving the machining efficiency is achieved; 3. Due to the reduction of the volume and mass of the blade root, the weight of the aircraft engine is reduced, the load of the aircraft engine is reduced, thereby promoting the improvement of the propulsion efficiency of the aircraft engine, reducing the failure rate of the aircraft engine and improving the service life of the aircraft engine; the fuel consumption of the aircraft engine is reduced, thereby saving energy, reducing pollution and protecting the environment. BRIEF DESCRIPTION OF DRAWINGS

[0027] Figure 1 is two perspective structural diagrams of the single-crystal blade of the aircraft engine of the present application.

[0028] Figure 2 is Figure 1 the A-A sectional view of

[0029] Figure 3 is three perspective structural diagrams of the blade root.

[0030] Figure 4 is Figure 3 the B-B sectional view of

[0031] Figure 5 is three perspective view of the leaf crown.

[0032] Figure 6 is a structure diagram of a precision electrolytic machine of the present application.

[0033] Figure 7 is a structure diagram of a precision electrolytic machining system of the present application.

[0034] Figure 8 is two perspective view of the precision electrolytic machining system of the present application in unprocessed reset state.

[0035] Figure 9 is a C-C sectional view of Figure 8

[0036] Figure 10 is a D-D sectional view of Figure 8

[0037] Figure 11 is an E-E sectional view of Figure 8

[0038] Figure 12 is two perspective view of the precision electrolytic machining system of the present application in positioning machining state.

[0039] Figure 13 is a F-F sectional view of Figure 12

[0040] Figure 14 is a G-G sectional view of Figure 12

[0041] Figure 15 is a H-H sectional view of Figure 12

[0042] Figure 16 is two perspective view of the main shaft quick fixture system.

[0043] Figure 17 is a K-K sectional view of Figure 16

[0044] Figure 18 is a structure diagram of the quick fixture device.

[0045] Figure 19 is a T-T sectional view of Figure 20

[0046] Figure 20 is two perspective view of the workpiece clamping shaft.

[0047] Figure 21 is​​​​​​​​Figure 21 L-L cross-sectional view of the

[0048] Figure 22 Figure 17 Enlarged view of I in

[0049] Figure 23 Figure 17 Enlarged view of II in

[0050] Figure 24 Structure diagram of main shaft machining reference quick positioning device A.

[0051] Figure 25 Structure diagram of main shaft drag board assembly.

[0052] Figure 26 Structure diagram of left mode electrode from two perspectives.

[0053] Figure 27 Structure diagram of right mode electrode from two perspectives.

[0054] Figure 28 Circuit diagram of coil control circuit.

[0055] Figure 1 In the figure, 1-A is a perspective view of the single-crystal blade of the aircraft engine; 1-B is an elevation view of the single-crystal blade of the aircraft engine.

[0056] Figure 3 In the figure, 3-A is a perspective view of the blade root; 3-B is a front view of the blade root; 3-C is a top view of the blade root.

[0057] Figure 5 In the figure, 5-A is a perspective view of the blade crown; 5-B is a front view of the blade crown; 5-C is a bottom view of the blade crown.

[0058] Figure 8 In the figure, 8-A is a top view of the precision electrolytic machining system in the unprocessed reset state; 8-B is a front view of the precision electrolytic machining system in the unprocessed reset state.

[0059] Figure 12 In the figure, 12-A is a top view of the precision electrolytic machining system in the positioning machining state; 12-B is a front view of the precision electrolytic machining system in the positioning machining state.

[0060] Figure 16 In the figure, 16-A is a perspective view of the main shaft quick fixture system; 16-B is a front view of the main shaft quick fixture system.

[0061] Figure 20 In the figure, 20-A is a perspective view of the workpiece clamping shaft; 20-B is a top view of the workpiece clamping shaft.

[0062] Figure 26 ​​In the figure, 26-A is the right view of the left mold electrode; 26-B is the front view of the left mold electrode.

[0063] Figure 27 In the figure, 27-A is the left view of the right mold electrode; 27-B is the front view of the right mold electrode.

[0064] In the figure, 1. Machine tool shell; 2. System touch screen; 3. Precision electrolytic machining system; 4. Operation panel; 5. Control panel; 6. Electrolyte output pipe; 7. Electrolyte input pipe; 8. Movable door; 9. Right panel; 10. Machine foot; 11. Seat frame; 12. Left panel; 13. Electrolysis power supply; 14. Control power supply.

[0065] In the figure, 31. Electrolytic machining system rack; 32. Main shaft quick clamp system; 33. Main shaft drag board assembly; 34. Blade workpiece; 35. Left shaft driving device; 36. Left feeding shaft; 37. Left mold electrode; 38. Electrolytic reaction box; 39. Right mold electrode; 310. Cathode wiring bridge assembly; 311. Right feeding shaft; 312. Right shaft driving device; 313. Main shaft machining reference quick positioning device A; 314. Main shaft machining reference quick positioning device B.

[0066] In the figure, 321. Insulating sleeve; 322. Workpiece clamping shaft; 323. Sealing ring; 324. Top spring bolt; 325. Top spring; 326. Insulating sleeve lock pin; 327. Clamping shaft seat; 328. Quick clamping device; 329. Top pin; 320. Parallel pad sleeve; 3211. Parallel connecting bolt; 3271. Middle through hole; 3272. Parallel connecting bolt hole.

[0067] In the figure, 3221. Shaft root; 3222. Shaft table; 3223. Lock pin hole; 3224. Top spring hole; 3225. Clamping shaft body; 3226. Workpiece seat hole; 3227. Trapezoidal seat piece adjusting hole; 3228. Quick pull channel.

[0068] In the figure, 3281. Wire shaft; 3282. Wire sleeve retainer; 3283 wire sleeve flange seat; 3284. Wire sleeve; 3285. Trapezoidal seat piece; 3286. Trapezoidal seat piece adjusting bolt; 3287. Quick pull trapezoidal long piece; 3288. Connecting bolt pin; 3289. Flange seat bolt.

[0069] In the figure, 331. Vertical seat; 332. Terminal post; 333. Positioning release button; 334. Handle; 335. Main drag board; 336. Connection hole; 337. Insulating partition; 338. Right angle connecting plate.

[0070] In the figure, 371. left mold specific; 372. leaf seat mold groove Z; 373. sharp edge root branch mold groove Z; 374. root branch groove mold convex Z; 375. inner root branch mold groove Z; 376. blunt edge root branch groove mold convex Z; 377. blunt edge root branch mold groove Z; 378. leaf seat flash B mold groove Z; 379. leaf direction synchronous taper shaft mold hole Z; 3710. workpiece groove Z; 3711. left mold mounting buckle.

[0071] In the figure, 391. right mold specific; 392. leaf seat mold groove Y; 393. sharp edge root branch mold groove Y; 394. root branch groove mold convex Y; 395. inner root branch mold groove Y; 396. blunt edge root branch groove mold convex Y; 397. blunt edge root branch mold groove Y; 398. leaf seat flash B mold groove Y; 399. leaf direction synchronous taper shaft mold hole Y; 3910. Workpiece groove Y; 3911. right mold mounting buckle.

[0072] In the figure, 3131. trapezoidal column; 3132. push away spring; 3133. limit top; 3134. coil groove; 3135. electric iron core; 3136. coil; 3137. indicator light; 3138. positioning button.

[0073] In the figure, 341. blade root; 342. leaf direction synchronous taper shaft; 343. leaf seat; 344. blade body; 345. blade crown;

[0074] In the figure, 3441. leaf body wall; 3442. leaf concave surface; 3443. leaf convex surface; 3444. shunt arc head; 3445. jet sharp tail.

[0075] In the figure, 3411. sharp edge root branch; 3412. root branch groove; 3413. inner root branch; 3414. blunt edge root branch groove; 3415. blunt edge root branch; 3416. vertical parallel plane; 3417. oblique transverse parallel corrugated surface; 3418. One wave trough; 3419. One wave peak; 3420. Two wave trough; 3421. Two wave peak; 3422. Root tip.

[0076] In the figure, 3431. leaf seat body; 3432. leaf seat flash A; 3433. leaf seat flash B; 3434. leaf seat inner flash A; 3435. Leaf seat inner flash B; 3436. Leaf seat inner flash B; 3437. Oblique transverse parallel corrugated surface; 3438. One wave trough; 3439. One wave peak; 3430. Two wave trough.

[0077] In the figure, 3451. crown seat; 3452. leaf direction synchronous lock groove A; 3453. leaf direction synchronous AB lock tip; 3454. Leaf direction synchronous lock groove B; 3455. Leaf direction synchronous lock groove C; 3456. Leaf direction synchronous CD lock tip; 3457. Leaf direction synchronous lock groove D; 3458. Crown sawtooth; 3459. Crown flash.

[0078] Figure 4 In the formula, DX is the total width of the blade root; d1 is the width of the acute-angle side root branch; d2 is the width of the root branch groove; d3 is the width of the inner root branch; d4 is the width of the obtuse-angle side root branch; d5 is the width of the obtuse-angle side root branch groove; DY is the maximum parallel distance of the two side oblique transverse parallel wave surfaces; dy1 is the distance between the centers of the two side root branch groove bottoms; dy2 is the depth of the root branch groove; and DA is the acute-angle of the blade root.

[0079] Figure 28 In the formula, SB1 represents the positioning button (3138); SB2 represents the positioning release button (333); YA1 and YA2 represent the coil (3136); LED represents the indicator light (3137); R1 represents the resistor; and C1 represents the capacitor.

[0080] DETAILED DESCRIPTION OF THE INVENTION

[0081] The application is further described below according to the drawings and examples.

[0082] Example 1.

[0083] In Figure 6 , Figure 7 , Figure 24 In the formula, a method for manufacturing a fast tooling jig for precision electrolytic machining of a single-crystal blade of an aircraft engine includes a machine tool shell (1), a system touch screen (2), a precision electrolytic machining system (3), an operation panel (4), a control panel (5), an electrolyte output pipe (6), an electrolyte input pipe (7), a movable door (8), a right panel (9), a machine foot (10), a seat frame (11), a left panel (12), an electrolytic power supply (13), and a control power supply (14). The precision electrolytic machining system (3) includes an electrolytic machining system frame (31), a main shaft fast clamping system (32), a main shaft drag plate assembly (33), a blade workpiece (34), a left shaft driving device (35), a left feeding shaft (36), a left mold electrode (37), an electrolytic reaction box (38), a right mold electrode (39), a cathode wiring bridge assembly (310), a right feeding shaft (311), a right shaft driving device (312), a main shaft machining reference fast positioning device A (313), and a main shaft machining reference fast positioning device B (314). The main shaft machining reference fast positioning device A (313) includes a trapezoidal column (3131), a push-away spring (3132), a limiting top (3133), a coil slot (3134), an electric iron core (3135), a coil (3136), an indicator light (3137), and a positioning button (3138).

[0084] The middle device of the electrolytic processing system frame (31) has an electrolytic reaction box (38), the front pair of the electrolytic reaction box (38) is provided with a main shaft drag plate assembly (33), and the two sides between the main shaft drag plate assembly (33) and the electrolytic reaction box (38) are respectively provided with a main shaft processing reference quick positioning device A (313) and a main shaft processing reference quick positioning device B (314);

[0085] The bottom surface of the trapezoidal column (3131) is a long side, the top is a square side, and the middle and upper sections are square; the middle and upper sections are equal to the top square side, and together form a square long column; the square long column is combined with the bottom long side of the trapezoidal column (3131) to form a trapezoidal long column with a small upper part and a large lower part; a coil groove (3134) is arranged in the square long column part of the trapezoidal column (3131), and a coil (3136) is arranged in the coil groove (3134); the middle part of the coil (3136) is an electric core (3135); the coil (3136) and the electric core (3135) are combined to magnetically attract and position the main shaft drag plate assembly (33); a push-away spring (3132) and a limiting top (3133) are arranged on the front wall surface of the trapezoidal column (3131) below the coil (3136);

[0086] The limiting top (3133) is used for accurate positioning of the main shaft drag plate assembly (33), and the limiting top (3133) is a convex column with a wear-resistant surface; the push-away spring (3132) is a compression spring, which is used to push the main shaft drag plate assembly (33) back to a non-processing position after processing; the top of the trapezoidal column (3131) is provided with an indicator light (3137), which is used for indicating the state of the main shaft drag plate assembly (33) during processing positioning; when the main shaft drag plate assembly (33) is positioned and processed, the indicator light (3137) is bright, and when the main shaft drag plate assembly (33) is in a non-processing position, the indicator light (3137) is not bright.

[0087] The main shaft processing reference quick positioning device A (313) and the main shaft processing reference quick positioning device B (314) have the same structure, function, effect and purpose; the difference is that the positions are different, the main shaft processing reference quick positioning device A (313) is arranged on the right side between the main shaft drag plate assembly (33) and the electrolytic reaction box (38), and the main shaft processing reference quick positioning device B (314) is arranged on the left side between the main shaft drag plate assembly (33) and the electrolytic reaction box (38);

[0088] In Figure 25The main shaft drag board assembly (33) comprises a vertical seat (331), a connecting column (332), a positioning release button (333), a handle (334), a main drag board (335), a connecting hole (336), an insulating partition (337), and a right-angle connecting plate (338). The handle (334) is provided with the positioning release button (333), the positioning release button (333) is used for turning on or off the coil (3136) power supply of the main shaft machining reference quick positioning device A (313) and the main shaft machining reference quick positioning device B (314), so as to control the positioning release and reset of the main shaft drag board assembly (33).

[0089] In Figure 8 、 Figure 10 、 Figure 12 、 Figure 24 、 Figure 9 、 Figure 13 、 Figure 11 、 Figure 14 、 Figure 15 、 Figure 25 、 Figure 28The main shaft machining reference quick positioning device A (313) and the main shaft machining reference quick positioning device B (314) are arranged on the two sides between the main shaft drag plate assembly (33) and the electrolytic reaction box (38), the main shaft machining reference quick positioning device A (313) is arranged on the right side, and the main shaft machining reference quick positioning device B (314) is arranged on the left side; the coils (3136) of the main shaft machining reference quick positioning device A (313) and the main shaft machining reference quick positioning device B (314) are connected in parallel, when the aircraft engine single crystal blade is electrolytically machined, the main shaft drag plate assembly (33) is moved to the main shaft machining reference quick positioning device A (313) and the main shaft machining reference quick positioning device B (314), the positioning button (3138) on the main shaft machining reference quick positioning device A (313) and the main shaft machining reference quick positioning device B (314) is touched, so that the power supply of YA1, YA2 and the coil (3136) is turned on, the magnetic attraction force of the electric iron core (3135) is generated to tightly attract the main shaft drag plate assembly (33), so that the main shaft drag plate assembly (33) achieves the positioning purpose; when the electrolytic machining of the aircraft engine single crystal blade is completed, the positioning release button (333) on the handle (334) is pressed to cut off the power supply of YA1, YA2 and the coil (3136), the magnetic attraction force of the electric iron core (3135) is eliminated, and at the same time, the push-off spring (3132) of the main shaft machining reference quick positioning device A (313) and the main shaft machining reference quick positioning device B (314) pushes away the main shaft drag plate assembly (33); the handle (334) of the main shaft drag plate assembly (33) is dragged to reset the main shaft drag plate assembly (33), and the next aircraft engine single crystal blade is machined; the technical scheme can replace the existing technology, that is, the main shaft drag plate and the workpiece are bolted and fixed during electrolytic machining, the bolt is disassembled after machining, the main shaft drag plate is reset, and the next workpiece is installed for machining, so that the main shaft drag plate assembly (33) and the workpiece (34) are conveniently and quickly positioned, the advanced effect is achieved, the machining speed is improved, and the machining efficiency is improved.

[0090] In Figure 16 、 Figure 17In the main shaft quick clamp system (32), the insulating sleeve (321), the workpiece clamping shaft (322), the sealing ring (323), the top spring bolt (324), the top spring (325), the insulating sleeve lock pin (326), the clamping shaft seat (327), the quick clamp device (328), the top pin (329), the parallel pad sleeve (320), and the parallel connecting bolt (3211) are arranged in the workpiece clamping shaft (322). The quick clamp device (328), the top spring bolt (324), the top spring (325), and the top pin (329) are arranged in the workpiece clamping shaft (322). The quick clamp device (328) is used for quickly clamping the blade workpiece (34). The top spring bolt (324), the top spring (325), and the top pin (329) are used for elastically biasing the quick clamp device (328) to the right side, so as to facilitate quick clamping and unclamping of the blade workpiece (34).

[0091] In Figure 18 、 Figure 19 The quick clamp device (328) includes a wire shaft (3281), a wire sleeve retainer ring (3282), a wire sleeve flange seat (3283), a wire sleeve (3284), a trapezoidal seat piece (3285), a trapezoidal seat piece adjusting bolt (3286), a quick pull trapezoidal long piece (3287), a connecting bolt pin (3288), and a flange seat bolt (3289). The trapezoidal seat piece (3285) is in contact with the right upper inclined plane of the quick pull trapezoidal long piece (3287). The quick pull trapezoidal long piece (3287) is movably connected with the wire shaft (3281) through the connecting bolt pin (3288). The wire shaft (3281) is screw-connected with the wire sleeve (3284). Rotating the wire sleeve (3284) can push the wire shaft (3281) and thus push the quick pull trapezoidal long piece (3287) to move up and down, so that the quick pull trapezoidal long piece (3287) is gradually biased to the left or right under the action of the trapezoidal seat piece (3285). When the quick pull trapezoidal long piece (3287) is pushed upward, the quick pull trapezoidal long piece (3287) is biased to the right. When the quick pull trapezoidal long piece (3287) is pushed downward, the quick pull trapezoidal long piece (3287) is biased to the left.

[0092] In Figure 20 、 Figure 21In the middle, the workpiece clamping shaft (322) includes shaft root (3221), shaft table (3222), lock pin hole (3223), top spring hole (3224), clamping shaft body (3225), workpiece seat hole (3226), trapezoidal seat piece adjusting hole (3227), quick pull channel (3228); characterized in that: the bottom surface of the workpiece seat hole (3226) is provided with a quick pull channel (3228) downward, the quick pull channel (3228) is a rectangular through hole perpendicular to the bottom surface of the workpiece seat hole (3226); the left side of the quick pull channel (3228) is provided with a top spring hole (3224), the top spring hole (3224) is used for device top spring bolt (324), top spring (325), top pin (329); the right side of the workpiece seat hole (3226) is provided with a trapezoidal seat piece adjusting hole (3227), the trapezoidal seat piece adjusting hole (3227) is used for device trapezoidal seat piece adjusting bolt (3286) of quick clamp device (328);

[0093] In Figure 17 、 Figure 19 、 Figure 22 In the middle, the clamping shaft seat (327) includes a middle through hole (3271) and a parallel connection bolt hole (3272); the wire sleeve flange seat (3283), the wire sleeve (3284), the wire sleeve retainer (3282) and the wire shaft (3281) of the quick clamp device (328) are arranged in the middle through hole (3271) of the clamping shaft seat (327), and the wire sleeve flange seat (3283) is fixedly connected with the clamping shaft seat (327) by the flange seat bolt (3289); the quick pull trapezoidal long piece (3287) is arranged in the quick pull channel (3228) of the workpiece clamping shaft (322), the quick pull trapezoidal long piece (3287) is movably connected with the wire shaft (3281), and the connecting bolt pin (3288) is inserted into the wire shaft (3281) and the quick pull trapezoidal long piece (3287);

[0094] In Figure 17 、 Figure 19 、 Figure 23In the middle, the fast pull trapezoidal long piece (3287), trapezoidal seat piece (3285) is in the right side of workpiece seat hole (3226); when the fast pull trapezoidal long piece (3287) moves downwards, because of the trapezoidal effect of fast pull trapezoidal long piece (3287), trapezoidal seat piece (3285), the fast pull trapezoidal long piece (3287) gradually deviates to the left side, and the left extrusion force is generated; therefore, when the vane workpiece (34) is arranged in the workpiece seat hole (3226), the wire sleeve (3284) of the rotating fast clamping device (328) is rotated, the fast pull trapezoidal long piece (3287) moves downwards and generates the left extrusion force, and the left extrusion force of the fast pull trapezoidal long piece (3287) extrudes the vane workpiece (34) in the workpiece seat hole (3226), so that the vane workpiece (34) is tightly fixed in the workpiece seat hole (3226); the outstanding effect of the technical scheme is that the cumbersome work of disassembling the insulating sleeve (321), disassembling the bolt with a tool spanner, replacing the vane workpiece (34) and clamping again in the prior art is replaced; the advanced effect of conveniently and quickly replacing the vane workpiece (34) is achieved; the purpose of improving the vane processing speed and improving the processing efficiency is achieved.

[0095] In Figure 25 In the middle, the main shaft drag board assembly (33) includes a vertical seat (331), a connecting post (332), a positioning release button (333), a handle (334), a main drag board (335), a connecting hole (336), an insulating partition (337), and a right-angle connecting plate (338); characterized in that: the handle (334) is provided with the positioning release button (333), and the positioning release button (333) is used for turning on or turning off the power supply of the coil (3136) of the main shaft machining reference quick positioning device A (313) and the main shaft machining reference quick positioning device B (314), so as to control the positioning release and reset of the main shaft drag board assembly (33).

[0096] In Figure 26 In the middle, the left mold electrode (37) includes a left mold body (371), a blade seat mold groove Z (372), an acute angle edge root branch mold groove Z (373), a root branch groove mold convex Z (374), an inner root branch mold groove Z (375), a blunt angle edge root branch groove mold convex Z (376), a blunt angle edge root branch mold groove Z (377), a blade seat flash B mold groove Z (378), a blade direction synchronous taper shaft mold hole Z (379), a workpiece groove Z (3710), and a left mold mounting buckle (3711); the left mold mounting buckle (3711) is arranged at the left end of the left mold body (371) and is used for being connected with the left feeding shaft (36).

[0097] In Figure 27In the right die electrode (39), the right die body (391), the leaf seat die groove Y (392), the acute edge root branch die groove Y (393), the root branch die convex Y (394), the inner root branch die groove Y (395), the obtuse edge root branch die convex Y (396), the obtuse edge root branch die groove Y (397), the leaf seat flash B die groove Y (398), the workpiece groove Y (3910), and the right die mounting buckle (3911) are arranged.

[0098] In the left die electrode (37), the left die body (371), the leaf seat die groove Y (372), the acute edge root branch die groove Y (373), the root branch die convex Y (374), the inner root branch die groove Y (375), the obtuse edge root branch die convex Y (376), the obtuse edge root branch die groove Y (377), the leaf seat flash B die groove Y (378), the workpiece groove Y (3710), and the left die mounting buckle (3711) are arranged. Figure 6 Figure 9 Figure 26 In the left die electrode (37), the left die body (371), the leaf seat die groove Y (372), the acute edge root branch die groove Y (373), the root branch die convex Y (374), the inner root branch die groove Y (375), the obtuse edge root branch die convex Y (376), the obtuse edge root branch die groove Y (377), the leaf seat flash B die groove Y (378), the workpiece groove Y (3710), and the left die mounting buckle (3711) are arranged.

[0099] In the right die electrode (39), the right die body (391), the leaf seat die groove Y (392), the acute edge root branch die groove Y (393), the root branch die convex Y (394), the inner root branch die groove Y (395), the obtuse edge root branch die convex Y (396), the obtuse edge root branch die groove Y (397), the leaf seat flash B die groove Y (398), the workpiece groove Y (3910), and the right die mounting buckle (3911) are arranged. Figure 6 Figure 9 Figure 27 In the right die electrode (39), the right die body (391), the leaf seat die groove Y (392), the acute edge root branch die groove Y (393), the root branch die convex Y (394), the inner root branch die groove Y (395), the obtuse edge root branch die convex Y (396), the obtuse edge root branch die groove Y (397), the leaf seat flash B die groove Y (398), the workpiece groove Y (3910), and the right die mounting buckle (3911) are arranged.

[0100] In the right die electrode (39), the right die body (391), the leaf seat die groove Y (392), the acute edge root branch die groove Y (393), the root branch die convex Y (394), the inner root branch die groove Y (395), the obtuse edge root branch die convex Y (396), the obtuse edge root branch die groove Y (397), the leaf seat flash B die groove Y (398), the workpiece groove Y (3910), and the right die mounting buckle (3911) are arranged. Figure 28 Figure 24 In the coil control circuit, DC, SB1, SB2, C1, LED, R1, YA1, and YA2 are included, YA1 and YA2 represent the coil (3136); the coil (3136) is used to control the spindle machining reference quick positioning device A and the spindle machining reference quick positioning device B; DC is a 12-36V DC power supply, which is input from the control power supply (14); SB1 is a normally open button switch for large current; SB2 is a normally closed button switch for large current; C1 is an electrolytic capacitor; LED is an indicator light (3137); R1 is a resistor; YA1 and YA2 are coils (3136); when normally working, SB1 is pressed to make C1 supply power to YA1 and YA2, i.e., the coil (3136) works; after the coil (3136) is powered, the electromagnet core (3135) generates magnetic attraction, and the LED is lit; SB2 is pressed to cut off the power supply of YA1, YA2, C1, and LED, so that YA1 and YA2 lose power, the LED is turned off, and the electromagnetic attraction disappears after YA1 and YA2 lose power. ​​​​

[0101] In Figure 1 , Figure 2 , Figure 3 , Figure 4 The single crystal blade of the aircraft engine produced by the precise electrolytic machining of the application comprises a blade root (341), a blade direction synchronous taper shaft (342), a blade seat (343), a blade body (344), and a blade crown (345). The blade root (341) comprises an acute angle edge root branch (3411), a root branch groove (3412), an inner root branch (3413), an obtuse angle edge root branch groove (3414), an obtuse angle edge root branch (3415), a vertical parallel plane (3416), and an inclined transverse parallel corrugated surface (3417).

[0102] In Figure 2 The blade body (344) comprises a blade body wall (3441), a blade concave surface (3442), a blade convex surface (3443), a shunt arc head (3444), and a jet sharp tail (3445).

[0103] In Figure 3 , Figure 4 The blade root (341) comprises an acute angle edge root branch (3411), a root branch groove (3412), an inner root branch (3413), an obtuse angle edge root branch groove (3414), an obtuse angle edge root branch (3415), a vertical parallel plane (3416), an inclined transverse parallel corrugated surface (3417), a wave trough (3418), a wave peak (3419), a second wave trough (3420), a second wave peak (3421), and a root tip (3422).

[0104] In Figure 3 The blade seat (343) comprises a blade seat body (3431), a blade seat flash A (3432), a blade seat flash B (3433), a blade seat inner flash A (3434), a blade seat inner flash B (3435), a blade seat inner flash B (3436), an inclined transverse parallel corrugated surface (3437), a wave trough (3438), a wave peak (3439), and a second wave trough (3430).

[0105] In Figure 4In the formula, DX is the total width of the blade root, d1 is the width of the acute angle root branch, the ratio of DX to d1 is 1 to 8-12; d2 is the width of the root branch groove, the ratio of DX to d2 is 1 to 10-14; d3 is the width of the inner root branch; the ratio of DX to d3 is 1 to 10-14; d4 is the width of the obtuse angle root branch; the ratio of DX to d4 is 1 to 18-22; d5 is the width of the obtuse angle root branch groove, the ratio of DX to d5 is 1 to 18-22; DY is the maximum parallel distance of the two side inclined transverse parallel wave surfaces; dy1 is the distance between the centers of the two root branch groove bottoms, the ratio of dy1 to DY is 2-2.5 to 1; dy2 is the depth of the root branch groove, the ratio of dy2 to DY is 6-6.5 to 1; DA is the acute angle of the blade root, the angle of DA is 65-75 degrees.

[0106] In Figure 5 the formula, the blade crown (345) includes a crown seat (3451), a blade direction synchronization lock groove A (3452), a blade direction synchronization AB lock tip (3453), a blade direction synchronization lock groove B (3454), a blade direction synchronization lock groove C (3455), a blade direction synchronization CD lock tip (3456), a blade direction synchronization lock groove D (3457), a crown sawtooth (3458), and a crown flash (3459);

[0107] Further, the blade root (341) is provided with a plurality of root branch grooves (3412) and a plurality of inner root branches (3413), and the plurality of root branch grooves (3412) and the plurality of inner root branches (3413) are distributed at intervals to form a void body of the blade root (341);

[0108] Further, the width ratio of the root branch groove (3412) to the inner root branch (3413) is 1-1.5 to 1-1.5, and the preferred ratio is 1 to 1;

[0109] Further, in Figure 4 the formula, the root branch groove (3412) is arranged in the upper half body and the lower half body of the blade root (341);

[0110] Further, in Figure 4 the formula, the root branch groove (3412) of the upper half body and the root branch groove (3412) of the lower half body do not intersect on the same straight line;

[0111] Further, in Figure 4 the formula, the root branch groove (3412) of the upper half body and the root branch groove (3412) of the lower half body are arranged in parallel in a staggered manner;

[0112] Further, in Figure 4In the embodiment, the root branch groove (3412) of the upper half body has a certain wall thickness distance from the groove bottom of the root branch groove (3412) of the lower half body, and the distance is greater than or equal to 0.5 times the wall thickness width size of the inner root branch (3413).

[0113] The above technical solution can reduce the volume and mass of the blade root (341) by a large margin due to the multiple root branch grooves (3412) and multiple inner root branches (3413).

[0114] In addition, the volume and mass of the blade root (341) account for a large part of the aircraft engine single crystal blade.

[0115] Furthermore, there are hundreds or thousands of blades in the aircraft engine, and if all of them use the aircraft engine single crystal blade of the present application, the total weight of the aircraft engine can be reduced by a large margin.

[0116] Therefore, the aircraft engine single crystal blade of the present application can reduce the dead weight of the aircraft engine and improve the propulsion efficiency of the aircraft engine.

[0117] Furthermore, the aircraft engine has a reduced load due to the light dead weight of the present application, thereby reducing the failure rate and prolonging the service life of the aircraft engine.

[0118] Furthermore, the fuel consumption of the aircraft engine can be reduced due to the light dead weight of the present application, thereby saving energy, reducing pollution, and protecting the environment.

[0119] The present application is the first in the field of domestic and foreign aviation technology, and has certain creativity and novelty.

[0120] Embodiment Two.

[0121] In Figure 6 , Figure 7The application discloses a quick tooling method for manufacturing aero-engine single-crystal blade precision electrolytic machining, which comprises a machine tool shell (1), a system touch screen (2), a precision electrolytic machining system (3), an operation panel (4), a control panel (5), an electrolyte output pipe (6), an electrolyte input pipe (7), a movable door (8), a right panel (9), a machine foot (10), a seat frame (11), a left panel (12), an electrolytic power supply (13) and a control power supply (14). The precision electrolytic machining system (3) comprises an electrolytic machining system frame (31), a main shaft quick clamp system (32), a main shaft drag plate assembly (33), a blade workpiece (34), a left shaft driving device (35), a left feeding shaft (36), a left mold electrode (37), an electrolytic reaction box (38), a right mold electrode (39), a cathode wiring bridge assembly (310), a right feeding shaft (311), a right shaft driving device (312), a main shaft machining reference quick positioning device A (313) and a main shaft machining reference quick positioning device B (314). The middle part of the electrolytic machining system frame (31) is provided with the electrolytic reaction box (38), the front opposite surface of the electrolytic reaction box (38) is provided with the main shaft drag plate assembly (33), and the main shaft machining reference quick positioning device A (313) and the main shaft machining reference quick positioning device B (314) are arranged on the two sides between the main shaft drag plate assembly (33) and the electrolytic reaction box (38).

[0122] In Figure 24In the main shaft processing reference quick positioning device A (313), the trapezoidal column (3131), the push-off spring (3132), the limiting top (3133), the coil groove (3134), the electric iron core (3135), the coil (3136), the indicator light (3137), and the positioning button (3138) are included. The bottom surface of the trapezoidal column (3131) is a long side, the top is a square side, and the middle upper section is a square. The middle upper section and the top square side are equal, which together form a square long column. The lower surface of the square long column and the bottom long side of the trapezoidal column (3131) together form a trapezoidal long column with a small upper surface and a large lower surface. The trapezoidal column (3131) is provided with a coil groove (3134) in the square long column part. The coil groove (3134) is provided with a coil (3136) inside. The middle part of the coil (3136) is an electric iron core (3135). The coil (3136) and the electric iron core (3135) are combined to magnetically attract the main shaft drag plate assembly (33). The front wall surface of the trapezoidal column (3131) below the coil (3136) is provided with a push-off spring (3132) and a limiting top (3133). The limiting top (3133) is used to accurately limit the position of the main shaft drag plate assembly (33). The limiting top (3133) is a convex column with a wear-resistant surface. The push-off spring (3132) is a compression spring, which is used to push the main shaft drag plate assembly (33) back to the non-processing position after processing. The top of the trapezoidal column (3131) is provided with an indicator light (3137). The indicator light (3137) is used to indicate the state of the main shaft drag plate assembly (33) during processing positioning. When the main shaft drag plate assembly (33) is positioned and processed, the indicator light (3137) is on. When the main shaft drag plate assembly (33) is in the non-processing position, the indicator light (3137) is off.

[0123] The main shaft processing reference quick positioning device A (313) and the main shaft processing reference quick positioning device B (314) have the same structure, function, effect, and purpose. The difference is the position. The main shaft processing reference quick positioning device A (313) is installed on the right side between the main shaft drag plate assembly (33) and the electrolytic reaction box (38). The main shaft processing reference quick positioning device B (314) is installed on the left side between the main shaft drag plate assembly (33) and the electrolytic reaction box (38).

[0124] In Figure 25The main shaft drag board assembly (33) comprises a vertical seat (331), a connecting column (332), a positioning release button (333), a handle (334), a main drag board (335), a connecting hole (336), an insulating partition (337), and a right-angle connecting plate (338). The handle (334) is provided with the positioning release button (333), the positioning release button (333) is used for turning on or off the coil (3136) power supply of the main shaft machining reference quick positioning device A (313) and the main shaft machining reference quick positioning device B (314), so as to control the positioning release and reset of the main shaft drag board assembly (33).

[0125] In Figure 8 、 Figure 10 、 Figure 12 、 Figure 24 、 Figure 9 、 Figure 13 、 Figure 11 、 Figure 14 、 Figure 15 、 Figure 25 、 Figure 28The main shaft machining reference quick positioning device A (313) and the main shaft machining reference quick positioning device B (314) are arranged on the two sides between the main shaft drag plate assembly (33) and the electrolytic reaction box (38), the main shaft machining reference quick positioning device A (313) is arranged on the right side, and the main shaft machining reference quick positioning device B (314) is arranged on the left side; the coils (3136) of the main shaft machining reference quick positioning device A (313) and the main shaft machining reference quick positioning device B (314) are connected in parallel, when the aircraft engine single crystal blade is electrolytically machined, the main shaft drag plate assembly (33) is moved to the main shaft machining reference quick positioning device A (313) and the main shaft machining reference quick positioning device B (314), the positioning button (3138) on the main shaft machining reference quick positioning device A (313) and the main shaft machining reference quick positioning device B (314) is touched, so that the power supply of YA1, YA2 and the coil (3136) is turned on, the magnetic attraction force of the electric iron core (3135) is generated to tightly attract the main shaft drag plate assembly (33), so that the main shaft drag plate assembly (33) achieves the positioning purpose; when the electrolytic machining of the aircraft engine single crystal blade is completed, the positioning release button (333) on the handle (334) is pressed to cut off the power supply of YA1, YA2 and the coil (3136), the magnetic attraction force of the electric iron core (3135) is eliminated, and at the same time, the push-off spring (3132) of the main shaft machining reference quick positioning device A (313) and the main shaft machining reference quick positioning device B (314) pushes away the main shaft drag plate assembly (33); the handle (334) of the main shaft drag plate assembly (33) is dragged to reset the main shaft drag plate assembly (33), and the next aircraft engine single crystal blade is machined; the technical scheme can replace the existing technology, that is, the main shaft drag plate and the workpiece are bolted and fixed during electrolytic machining, the bolt is disassembled after machining, the main shaft drag plate is reset, and the next workpiece is installed for machining, so that the main shaft drag plate assembly (33) and the workpiece (34) are conveniently and quickly positioned, the advanced effect is achieved, the machining speed is improved, and the machining efficiency is improved.

[0126] In Figure 16 、 Figure 17In the main shaft quick clamp system (32), the insulating sleeve (321), the workpiece clamping shaft (322), the sealing ring (323), the top spring bolt (324), the top spring (325), the insulating sleeve lock pin (326), the clamping shaft seat (327), the quick clamp device (328), the top pin (329), the parallel pad sleeve (320), and the parallel connecting bolt (3211) are arranged in the workpiece clamping shaft (322). The quick clamp device (328), the top spring bolt (324), the top spring (325), and the top pin (329) are arranged in the workpiece clamping shaft (322). The quick clamp device (328) is used for quickly clamping the blade workpiece (34). The top spring bolt (324), the top spring (325), and the top pin (329) are used for elastically biasing the quick clamp device (328) to the right side, so as to facilitate quick clamping and unclamping of the blade workpiece (34).

[0127] In Figure 18 、 Figure 19 In the quick clamp device (328), the wire shaft (3281), the wire sleeve retainer ring (3282), the wire sleeve flange seat (3283), the wire sleeve (3284), the trapezoidal seat piece (3285), the trapezoidal seat piece adjusting bolt (3286), the quick pull trapezoidal long piece (3287), the connecting bolt pin (3288), and the flange seat bolt (3289) are arranged. The trapezoidal seat piece (3285) is in contact with the right upper inclined plane of the quick pull trapezoidal long piece (3287). The quick pull trapezoidal long piece (3287) is movably connected with the wire shaft (3281) through the connecting bolt pin (3288). The wire shaft (3281) is screw-connected with the wire sleeve (3284). Rotation of the wire sleeve (3284) can push the wire shaft (3281) to push the quick pull trapezoidal long piece (3287) to move up and down, so that the quick pull trapezoidal long piece (3287) is gradually biased to the left or right under the action of the trapezoidal seat piece (3285). When the quick pull trapezoidal long piece (3287) is pushed upward, the quick pull trapezoidal long piece (3287) is biased to the right. When the quick pull trapezoidal long piece (3287) is pushed downward, the quick pull trapezoidal long piece (3287) is biased to the left.

[0128] In Figure 20 、 Figure 21In the middle, the workpiece clamping shaft (322) includes shaft root (3221), shaft table (3222), lock pin hole (3223), top spring hole (3224), clamping shaft body (3225), workpiece seat hole (3226), trapezoidal seat piece adjusting hole (3227), fast pull channel (3228); characterized in that: the bottom surface of the workpiece seat hole (3226) is provided with a fast pull channel (3228) downward, the fast pull channel (3228) is a rectangular through hole perpendicular to the bottom surface of the workpiece seat hole (3226); the left side of the fast pull channel (3228) is provided with a top spring hole (3224), the top spring hole (3224) is used for device top spring bolt (324), top spring (325), top pin (329); the right side of the workpiece seat hole (3226) is provided with a trapezoidal seat piece adjusting hole (3227), the trapezoidal seat piece adjusting hole (3227) is used for device trapezoidal seat piece adjusting bolt (3286) of fast clamping device (328);

[0129] In Figure 17 、 Figure 22 In the middle, the clamping shaft seat (327) includes a middle through hole (3271) and a parallel connection bolt hole (3272); the wire sleeve flange seat (3283), the wire sleeve (3284), the wire sleeve retainer (3282) and the wire shaft (3281) of the fast clamping device (328) are arranged in the middle through hole (3271) of the clamping shaft seat (327), and the wire sleeve flange seat (3283) is fixedly connected with the clamping shaft seat (327) by the flange seat bolt (3289); the fast pull trapezoidal long piece (3287) is arranged in the fast pull channel (3228) of the workpiece clamping shaft (322), the fast pull trapezoidal long piece (3287) is movably connected with the wire shaft (3281), and the connecting bolt pin (3288) is inserted into the wire shaft (3281) and the fast pull trapezoidal long piece (3287);

[0130] In Figure 17 、 Figure 19 、 Figure 23In the middle, the fast pull trapezoidal long piece (3287), trapezoidal seat piece (3285) is in the right side of workpiece seat hole (3226); when the fast pull trapezoidal long piece (3287) moves downwards, because of the trapezoidal effect of fast pull trapezoidal long piece (3287), trapezoidal seat piece (3285), the fast pull trapezoidal long piece (3287) gradually offsets to the left side, and generates left extrusion force; therefore, when the vane workpiece (34) is arranged in the workpiece seat hole (3226), the wire sleeve (3284) of the rotating fast clamping device (328) is rotated, the fast pull trapezoidal long piece (3287) moves downwards and generates left extrusion force, and the left extrusion force of the fast pull trapezoidal long piece (3287) will extrude the vane workpiece (34) in the workpiece seat hole (3226), so that the vane workpiece (34) is tightly fixed in the workpiece seat hole (3226); the outstanding effect of the technical scheme is that the cumbersome work of disassembling the insulating sleeve (321), disassembling the bolt with a tool spanner, replacing the vane workpiece (34) and clamping again in the prior art is replaced; the advanced effect of conveniently and quickly replacing the vane workpiece (34) is achieved; the purpose of improving the vane processing speed and improving the processing efficiency is achieved.

[0131] In Figure 25 The main shaft drag board assembly (33) includes a vertical seat (331), a connecting post (332), a positioning release button (333), a handle (334), a main drag board (335), a connecting hole (336), an insulating partition (337), and a right-angle connecting plate (338). The handle (334) is provided with the positioning release button (333), which is used to turn on or turn off the power supply of the coil (3136) of the main shaft machining reference quick positioning device A (313) and the main shaft machining reference quick positioning device B (314), so as to control the positioning release and reset of the main shaft drag board assembly (33).

[0132] In Figure 26 The left die electrode (37) includes a left die body (371), a blade seat die groove Z (372), an acute angle edge root branch die groove Z (373), a root branch groove die convex Z (374), an inner root branch die groove Z (375), a blunt angle edge root branch groove die convex Z (376), a blunt angle edge root branch die groove Z (377), a blade seat flash B die groove Z (378), a blade direction synchronous taper shaft die hole Z (379), a workpiece groove Z (3710), and a left die mounting buckle (3711). The left die mounting buckle (3711) is arranged at the left end of the left die body (371) and is used to be connected with the left feeding shaft (36).

[0133] In Figure 27In the right die electrode (39), the right die body (391), the leaf seat die groove Y (392), the acute edge root branch die groove Y (393), the root branch die convex Y (394), the inner root branch die groove Y (395), the obtuse edge root branch die convex Y (396), the obtuse edge root branch die groove Y (397), the leaf seat flash B die groove Y (398), the workpiece groove Y (3910), and the right die mounting buckle (3911) are arranged.

[0134] In the right die electrode (39), the right die body (391), the leaf seat die groove Y (392), the acute edge root branch die groove Y (393), the root branch die convex Y (394), the inner root branch die groove Y (395), the obtuse edge root branch die convex Y (396), the obtuse edge root branch die groove Y (397), the leaf seat flash B die groove Y (398), the workpiece groove Y (3910), and the right die mounting buckle (3911) are arranged. Figure 6 Figure 9 Figure 26 In the left die electrode (37), the left die electrode (37) is arranged at the right end of the left feed shaft (36), and the electrical connection of the left die electrode (37) is connected in the following manner: the left die electrode (37) is connected to the left feed shaft (36), the left feed shaft (36) is connected to the electrolytic machining system rack (31), and the electrolytic machining system rack (31) is connected to the electrolytic power supply (13).

[0135] In the right die electrode (39), the right die electrode (39) is arranged at the left end of the right feed shaft (311), and the electrical connection of the right die electrode (39) is connected in the following manner: the right die electrode (37) is connected to the right feed shaft (311), the right feed shaft (311) is connected to the electrolytic machining system rack (31), and the electrolytic machining system rack (31) is connected to the electrolytic power supply (13). Figure 6 Figure 9 Figure 27 In the right die electrode (39), the right die electrode (39) is arranged at the left end of the right feed shaft (311), and the electrical connection of the right die electrode (39) is connected in the following manner: the right die electrode (37) is connected to the right feed shaft (311), the right feed shaft (311) is connected to the electrolytic machining system rack (31), and the electrolytic machining system rack (31) is connected to the electrolytic power supply (13).

[0136] In the right die electrode (39), the right die electrode (39) is arranged at the left end of the right feed shaft (311), and the electrical connection of the right die electrode (39) is connected in the following manner: the right die electrode (37) is connected to the right feed shaft (311), the right feed shaft (311) is connected to the electrolytic machining system rack (31), and the electrolytic machining system rack (31) is connected to the electrolytic power supply (13). Figure 28 Figure 24 In the coil control circuit, DC, SB1, SB2, C1, LED, R1, YA1, and YA2 are included, YA1 and YA2 represent the coil (3136), and the coil (3136) is used to control the spindle machining reference quick positioning device A and the spindle machining reference quick positioning device B. DC is a 12-36V DC power supply input from the control power supply (14), SB1 is a normally open button switch for large current, SB2 is a normally closed button switch for large current, C1 is an electrolytic capacitor, LED is an indicator light (3137), R1 is a resistor, YA1 and YA2 are coils (3136), and when normally working, SB1 is pressed to make C1 supply power to YA1 and YA2, i.e., the coil (3136) works. After the coil (3136) is powered, the electromagnet core (3135) generates magnetic attraction, and the LED is lit. SB2 is pressed to cut off the power supply of YA1, YA2, C1, and LED, so that YA1 and YA2 lose power, the LED is turned off, and YA1 and YA2 lose power after losing power, and the electromagnetic attraction is lost. ​​​​

[0137] In Figure 1 , Figure 2 , Figure 3 , Figure 4 The single crystal blade of the aircraft engine produced by the precise electrolytic machining of the application comprises a blade root (341), a blade direction synchronous taper shaft (342), a blade seat (343), a blade body (344), and a blade crown (345). The blade root (341) comprises an acute angle edge root branch (3411), a root branch groove (3412), an inner root branch (3413), an obtuse angle edge root branch groove (3414), an obtuse angle edge root branch (3415), a vertical parallel plane (3416), and an inclined transverse parallel corrugated surface (3417). The number of root branch grooves (3412) is 12, and the number of inner root branches (3413) is 10.

[0138] In Figure 2 The blade body (344) comprises a blade body wall (3441), a blade concave surface (3442), a blade convex surface (3443), a shunt arc head (3444), and a jet sharp tail (3445).

[0139] In Figure 3 , Figure 4 The blade root (341) comprises an acute angle edge root branch (3411), a root branch groove (3412), an inner root branch (3413), an obtuse angle edge root branch groove (3414), an obtuse angle edge root branch (3415), a vertical parallel plane (3416), an inclined transverse parallel corrugated surface (3417), a wave valley (3418), a wave peak (3419), a second wave valley (3420), a second wave peak (3421), and a root tip (3422).

[0140] In Figure 3 The blade seat (343) comprises a blade seat body (3431), a blade seat flash A (3432), a blade seat flash B (3433), a blade seat inner flash A (3434), a blade seat inner flash B (3435), a blade seat inner flash B (3436), an inclined transverse parallel corrugated surface (3437), a wave valley (3438), a wave peak (3439), and a second wave valley (3430).

[0141] In Figure 4In the formula, DX is the total width of the blade root, d1 is the width of the acute angle root branch, the ratio of DX to d1 is 1 to 10; d2 is the width of the root branch groove, the ratio of DX to d2 is 1 to 12; d3 is the width of the inner root branch; the ratio of DX to d3 is 1 to 12; d4 is the width of the obtuse angle root branch; the ratio of DX to d4 is 1 to 20; d5 is the width of the obtuse angle root branch groove, the ratio of DX to d5 is 1 to 20; DY is the maximum parallel distance of the two side inclined transverse parallel corrugated surfaces; dy1 is the distance between the centers of the two root branch groove bottoms, the ratio of dy1 to DY is 2.3 to 1; dy2 is the depth of the root branch groove, the ratio of dy2 to DY is 6.25 to 1; DA is the acute angle of the blade root, the angle of DA is 70 degrees.

[0142] In Figure 5 , the blade crown (345) comprises a crown seat (3451), a blade direction synchronization lock groove A (3452), a blade direction synchronization AB lock tip (3453), a blade direction synchronization lock groove B (3454), a blade direction synchronization lock groove C (3455), a blade direction synchronization CD lock tip (3456), a blade direction synchronization lock groove D (3457), a crown sawtooth (3458), and a crown flash (3459);

[0143] Further, the blade root (341) is provided with 10 root branch grooves (3412) and 10 inner root branches (3413), and the 10 root branch grooves (3412) and the 10 inner root branches (3413) are distributed at intervals to form a clearance body in the blade root (341);

[0144] Further, the width ratio of the root branch groove (3412) to the inner root branch (3413) is 1 to 1;

[0145] Further, in Figure 4 , the root branch groove (3412) is arranged in the upper half body and the lower half body of the blade root (341);

[0146] Further, in Figure 4 , the root branch groove (3412) of the upper half body and the root branch groove (3412) of the lower half body do not intersect on the same straight line;

[0147] Further, in Figure 4 , the root branch groove (3412) of the upper half body and the root branch groove (3412) of the lower half body are arranged in parallel in a staggered manner;

[0148] Further, in Figure 4 Figure 6 Figure 7 Figure 24 Figure 25 Figure 8 Figure 10 Figure 12 Figure 24 Figure 9 Figure 13 Figure 11 Figure 14 Figure 15 Figure 25 Figure 28 Figure 16 Figure 17 Figure 18 Figure 19 Figure 20 Figure 21 Figure 17 Figure 22 Figure 17 Figure 19 Figure 23 Figure 25 Figure 26 Figure 27 Figure 6 Figure 9 Figure 26 Figure 6 Figure 9 Figure 27 Figure 28 Figure 24 Figure 1 Figure 2 Figure 3 Figure 4 Figure 2 Figure 3 Figure 4 Figure 3 Figure 4 Figure 5 Figure 4 Figure 4 Figure 4 Figure 4 Figure 6 Figure 7 Figure 24 Figure 25 Figure 8 Figure 10 Figure 12 Figure 24 Figure 9 Figure 13 Figure 11 Figure 14 Figure 15 Figure 25 Figure 28 Figure 16 Figure 17 Figure 18 Figure 19 Figure 20 Figure 21 Figure 17 Figure 22 Figure 17 Figure 19 Figure 23 Figure 25 , the groove bottom of the root branch groove (3412) of the upper half body and the groove bottom of the root branch groove (3412) of the lower half body have a certain wall thickness distance, and the distance wall thickness size is equal to 0.5 times the wall thickness width size of the inner root branch (3413);

[0149] The technical scheme has 10 root branch grooves (3412) and 10 inner root branches (3413), so that the volume and mass ratio of the blade root (341) is reduced compared with the prior art;

[0150] The volume and mass ratio of the blade root (341) accounts for a large proportion of the aircraft engine single crystal blade;

[0151] Furthermore, there are hundreds or thousands of blades in the aircraft engine, and if all the aircraft engine single crystal blades are used, the total weight of the aircraft engine can be greatly reduced;

[0152] Therefore, the aircraft engine single crystal blade can reduce the self-weight of the aircraft engine and improve the propulsion efficiency of the aircraft engine;

[0153] Further, the self-weight of the aircraft engine is reduced, thereby reducing the load of the aircraft engine, and further reducing the failure rate and improving the service life of the aircraft engine;

[0154] Further, the self-weight of the aircraft engine is reduced, thereby reducing the fuel consumption of the aircraft engine, saving energy, and protecting the environment.

[0155] The present application is the first in the field of domestic and foreign aviation technology, and has certain creativity, novelty and practicality.

Claims

1. A kind of manufacturing airplane engine single crystal blade precision electrolytic machining quick tooling method, including machine tool shell (1), system touch screen (2), precision electrolytic machining system (3), operating panel (4), electrolytic power (13), control power (14);The precision electrolytic machining system (3) includes electrolytic machining system frame (31), main shaft quick fixture system (32), main shaft drag plate assembly (33), left feed shaft (36), left die electrode (37), electrolytic reaction box (38), right die electrode (39), right feed shaft (311), main shaft machining datum quick positioning device A (313), main shaft machining datum quick positioning device B (314);Its characterized in that: The main shaft quick fixture system (32) comprises a workpiece clamping shaft (322), a top spring bolt (324), a top spring (325), an insulating sleeve lock pin (326), a clamping shaft seat (327), a quick clamping device (328), a top pin (329), a parallel pad sleeve (320), and a parallel connecting bolt (3211); the quick clamping device (328), the top spring bolt (324), the top spring (325), and the top pin (329) are arranged in the workpiece clamping shaft (322); the quick clamping device (328) is used for quickly clamping a blade workpiece (34); the top spring bolt (324), the top spring (325), and the top pin (329) are used for elastically biasing the quick clamping device (328) to the right side, so as to facilitate quick mounting and dismounting of the blade workpiece (34); The main shaft machining reference quick positioning device A (313) and the main shaft machining reference quick positioning device B (314) are arranged on both sides between the main shaft drag board assembly (33) and the electrolytic reaction box (38); The main shaft machining reference quick positioning device A (313) comprises a trapezoidal column (3131), a push-away spring (3132), a limiting top (3133), a coil groove (3134), an electric iron core (3135), a coil (3136), and a positioning button (3138). The trapezoidal column (3131) is provided with the coil groove (3134) in the square column part, and the coil (3136) is arranged in the coil groove (3134); the middle part of the coil (3136) is the electric iron core (3135); the coil (3136) and the electric iron core (3135) are combined to be used for magnetically attracting and positioning the main shaft drag board assembly (33); the front wall surface of the trapezoidal column (3131) below the coil (3136) is provided with the push-away spring (3132) and the limiting top (3133). The main shaft drag board assembly (33) comprises a vertical seat (331), a wiring column (332), a positioning release button (333), a handle (334), a main drag board (335), a connecting hole (336), an insulating partition plate (337), and a right-angle connecting plate (338). The handle (334) is provided with the positioning release button (333), the positioning release button (333) is used for turning on or off the power supply of the coil (3136) of the main shaft machining reference quick positioning device A (313) and the main shaft machining reference quick positioning device B (314), so as to control the positioning release and reset of the main shaft drag board assembly (33).

2. The method of claim 1, wherein the method further comprises: The quick clamping device (328) comprises a wire shaft (3281), a wire sleeve check ring (3282), a wire sleeve flange seat (3283), a wire sleeve (3284), a trapezoidal seat piece (3285), a trapezoidal seat piece adjusting bolt (3286), a quick pull trapezoidal long piece (3287), a connecting bolt pin (3288), and a flange seat bolt (3289). ​ 3. The method of claim 2, wherein the method further comprises: providing a jig having a plurality of holes, each hole having a diameter that is smaller than the diameter of the single crystal blade; and positioning the single crystal blade in the jig such that the single crystal blade is aligned with the plurality of holes. The trapezoidal seat piece (3285) is in contact with the upper right inclined plane of the fast pull trapezoidal long piece (3287); the fast pull trapezoidal long piece (3287) is movably connected with the silk shaft (3281) by a connecting bolt pin (3288); the silk shaft (3281) is screw-connected with the silk sleeve (3284), and rotating the silk sleeve (3284) can push the silk shaft (3281) to push the fast pull trapezoidal long piece (3287) to move up and down, so that the fast pull trapezoidal long piece (3287) is gradually biased to the left or to the right under the action of the trapezoidal seat piece (3285); when the fast pull trapezoidal long piece (3287) is pushed upward, the fast pull trapezoidal long piece (3287) is biased to the right, and when the fast pull trapezoidal long piece (3287) is pushed downward, the fast pull trapezoidal long piece (3287) is biased to the left.

4. The method of claim 1, wherein the method further comprises: providing a jig having a plurality of holes; and positioning the jig on the single crystal blade such that the plurality of holes align with the plurality of holes in the single crystal blade. The workpiece clamping shaft (322) comprises a shaft root (3221), a shaft table (3222), a lock pin hole (3223), a top spring hole (3224), a clamping shaft body (3225), a workpiece seat hole (3226), a trapezoidal seat piece adjusting hole (3227), and a fast pull channel (3228).

5. The method of claim 4, wherein the method further comprises: A fast pull channel (3228) is arranged downward on the bottom surface of the workpiece seat hole (3226), the fast pull channel (3228) is a long rectangular through hole perpendicular to the bottom surface of the workpiece seat hole (3226); a top spring hole (3224) is arranged on the left side of the fast pull channel (3228), and the top spring hole (3224) is used for arranging a top spring bolt (324), a top spring (325), and a top pin (329); a trapezoidal seat piece adjusting hole (3227) is arranged on the right side of the workpiece seat hole (3226), and the trapezoidal seat piece adjusting hole (3227) is used for arranging a trapezoidal seat piece adjusting bolt (3286) of a fast clamping device (328). ​ 6. The method of claim 2, wherein the method further comprises: The clamping shaft seat (327) comprises a middle through hole (3271) and a parallel connecting bolt hole (3272); the silk sleeve flange seat (3283), the silk sleeve (3284), the silk sleeve retainer ring (3282), and the silk shaft (3281) of the fast clamping device (328) are arranged in the middle through hole (3271) of the clamping shaft seat (327), and the silk sleeve flange seat (3283) is fixedly connected with the clamping shaft seat (327) by a flange seat bolt (3289); the fast pull trapezoidal long piece (3287) is arranged in the fast pull channel (3228) of the workpiece clamping shaft (322), and the fast pull trapezoidal long piece (3287) is movably connected with the silk shaft (3281) by a connecting bolt pin (3288).

7. The method of claim 2, wherein the method further comprises: providing a jig having a plurality of holes; and positioning the jig on the single crystal blade such that the plurality of holes align with the plurality of holes in the single crystal blade. The fast pull trapezoidal long piece (3287) and the trapezoidal seat piece (3285) are arranged on the right side of the workpiece seat hole (3226).

8. The method of claim 2, wherein the method further comprises: providing a jig having a plurality of holes; and positioning the jig on the single crystal blade such that the plurality of holes align with the plurality of holes in the single crystal blade. When the fast pull trapezoidal long piece (3287) moves downward, due to the trapezoidal effect of the fast pull trapezoidal long piece (3287) and the trapezoidal seat piece (3285), the fast pull trapezoidal long piece (3287) gradually deviates to the left side, generating a leftward extrusion force; therefore, when the blade workpiece (34) is arranged in the workpiece seat hole (3226), the wire sleeve (3284) of the rotating fast clamping device (328) is rotated to make the fast pull trapezoidal long piece (3287) move downward to generate a leftward extrusion force, and the leftward extrusion force of the fast pull trapezoidal long piece (3287) will extrude the blade workpiece (34) in the workpiece seat hole (3226), so that the blade workpiece (34) is tightly fixed in the workpiece seat hole (3226).

Images