A method for designing the blade root of an aircraft engine and its manufacturing apparatus

Abstract

An aircraft engine blade includes a blade root (341), a blade body (344), and a blade crown (345); characterized in that: the blade root (341) includes root branch grooves (3412) and inner root branches (3413); the blade root (341) is provided with multiple root branch grooves (3412) and multiple inner root branches (3413), and the multiple root branch grooves (3412) and multiple inner root branches (3413) are distributed at intervals to form a void body in the blade root (341); beneficial effects: 1. Due to the reduction in the volume and mass of the blade root, the self-weight of the aircraft engine can be reduced, which promotes the improvement of the propulsion efficiency of the aircraft engine; the failure rate of the aircraft engine is reduced and its service life is increased; energy is saved and pollution is reduced; 2. It is an advanced alternative to the existing electrolytic machining technology, where the spindle slide and the workpiece are fixed with bolts, and the bolts are removed and the spindle slide is reset after machining before the next workpiece is installed and machined; it has the advanced effect of convenient and quick positioning of the spindle slide assembly and the workpiece; and improves machining efficiency.

Description

Technical Field

[0001] This invention relates to an aircraft engine blade, and more particularly to an aircraft engine blade root design method and manufacturing apparatus. Background Technology

[0002] As the heart of an aircraft, the development and production of aircraft engines is a systematic project, representing, to some extent, a country's technological level. In recent years, my country's aerospace industry has made rapid progress, with new-generation aircraft being developed one after another, and aircraft engine development has also made significant progress. Among these, aircraft engine manufacturing technology has always played a crucial role. Among the various components of an aircraft engine, blades are one of the most important parts. Due to their prominent role, special structure, and twisted blade shape, they present many challenges to manufacturing and have been a key focus of research and development for many years. With the increasing demands for thrust-to-weight ratio in new-generation aircraft engines, the expectations and requirements for blades are even higher.

[0003] Currently, most aircraft engine blades use new materials such as titanium-aluminum alloys to reduce density, improve structural strength and high temperature resistance. However, people hope to make better breakthroughs in structural design. For many years, lightweighting of aircraft engine blades has been a high technology that people have been constantly pursuing and challenging. To this end, we have carried out many years of research, design and testing, and will select and provide a blade design scheme with the best structure, hoping to play a prominent role in promoting the development of my country's aviation industry.

[0004] Due to the difficulty in processing and manufacturing high-temperature alloy materials, and the complex structure, high hardness, special curved surface shape, sharp and twisted leading and trailing edges, and stringent precision requirements of the blades, the manufacturing of titanium-aluminum alloy blades is extremely difficult, posing many new challenges to processing and manufacturing.

[0005] Among numerous manufacturing technologies, electrolytic machining technology stands out as a preferred option for aircraft engine blade manufacturing due to its unique advantages, such as no tool wear, no limitation by the mechanical properties of the metal material itself, and high processing efficiency. These advantages perfectly match the special materials, difficult processing, and other characteristics of blade manufacturing.

[0006] Electrolytic machining is a processing method that removes materials using the principle of electrochemical anodic dissolution, belonging to the field of special machining. Electrolytic machining has advantages such as high processing efficiency, good surface quality, no electrode wear, and a wide processing range. With the in-depth research of electrolytic machining technology, the accuracy and stability of electrolytic machining have been greatly improved, and its application is becoming more and more widespread, especially suitable for the high-precision and difficult-to-machine requirements of aircraft engine blades. However, the anodic dissolution process in electrolytic machining is very complex, especially the various methods of positioning the spindle machining reference, which have complex structures and greatly limit the processing speed and efficiency.

[0007] In the actual production of blades, the main reasons for the low production efficiency and long production cycle of electrolytic machining of aircraft engine blades are the complex structure of the workpiece fixtures and the cumbersome loading, unloading and operation methods of the workpieces. As a result, the cost of mass production is high, especially the cost of manufacturing a single piece is even higher when the batch size is smaller.

[0008] Therefore, researching the precision electrolytic machining of aircraft engine blades is a highly anticipated and desired endeavor. Summary of the Invention

[0009] This invention provides a method for designing the blade root of an aircraft engine and a manufacturing apparatus thereof, which can solve the problems mentioned in the background art.

[0010] The key technical solutions of this invention to solve its technical problems are as follows: 1. Based on the lightweight requirements of aircraft engine blades, we conducted several designs and experiments on the root portion of the aircraft engine blades, and finally selected a root gap structure design scheme to further reduce the self-weight of the aircraft engine blades and solve the problem of lightweighting the aircraft engine blades; 2. In order to realize the root gap structure, we started with the mold, designing the cathode mold into two parts, left and right, with multiple vacuum structures in the left and right molds. After electrolytic machining, the root of the aircraft engine blade forms multiple root branch grooves and inner root branches, thus creating many gaps in the root of the aircraft engine blade; 3. Based on the characteristics of electrolytic machining, we optimized the positioning fixture and workpiece clamping method of the spindle machining reference, and designed a fast spindle machining reference quick positioning device and a workpiece quick clamping device to improve the efficiency and quality of electrolytic machining.

[0011] The design of the blade root of the present invention is as follows: the blade root of an aircraft engine blade includes an acute-angled side root branch, a root branch groove, an inner root branch, an obtuse-angled side root branch groove, an obtuse-angled side root branch, a vertical parallel plane, an oblique transverse parallel corrugated surface, a trough, a peak, two troughs, two peaks, and a root tip.

[0012] The leaf root is provided with multiple root branch grooves and multiple inner root branches, and the multiple root branch grooves and multiple inner root branches are distributed at intervals to make the leaf root form a void body.

[0013] The ratio of the root-branch groove to the width of the inner root branch is 1-1.5 to 1-1.5, with the preferred ratio being 1 to 1.

[0014] The blade, comprising an aircraft engine blade according to the present invention, includes a blade root, a blade direction synchronous cone shaft, a blade seat, a blade body, and a blade crown; characterized in that: the blade root is designed with a void structure.

[0015] A cathode mold, the cathode mold comprising a left mold electrode and a right mold electrode;

[0016] The left mold electrode includes a left mold body, a blade seat mold groove Z, an acute-angled root branch mold groove Z, a root branch groove mold protrusion Z, an inner root branch mold groove Z, an obtuse-angled root branch groove mold protrusion Z, an obtuse-angled root branch mold groove Z, a blade seat flash edge B mold groove Z, a blade direction synchronous cone shaft mold hole Z, a workpiece groove Z, and a left mold mounting buckle; the left mold mounting buckle is located at the left end of the left mold body and is used to connect with the left feed shaft;

[0017] The right mold electrode includes a right mold body, a blade seat mold groove Y, an acute-angled root branch mold groove Y, a root branch groove mold protrusion Y, an inner root branch mold groove Y, an obtuse-angled root branch groove mold protrusion Y, an obtuse-angled root branch mold groove Y, a blade seat flash edge B mold groove Y, a blade direction synchronous cone shaft mold hole Y, a workpiece groove Y, and a right mold mounting buckle; the right mold mounting buckle is located at the right end of the right mold body and is used to connect with the right feed shaft.

[0018] The left mold electrode device is located at the right end of the left feed shaft of the electrolytic machining system. The electrical connection of the left mold electrode is as follows: the left mold electrode is connected to the left feed shaft, the left feed shaft is connected to the electrolytic machining system frame, and the electrolytic machining system frame is connected to the electrolytic power supply.

[0019] The right mold electrode device is located at the left end of the right feed shaft of the electrolytic machining system. The electrical connection of the right mold electrode is as follows: the right mold electrode is connected to the right feed shaft, the right feed shaft is connected to the frame of the electrolytic machining system, and the frame of the electrolytic machining system is connected to the electrolytic power supply.

[0020] Precision electrolytic machining, a method for manufacturing the root of an aircraft engine blade according to the present invention, includes a machine tool housing, 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, machine feet, a base, a left panel, an electrolytic power supply, and a control power supply; characterized in that: the precision electrolytic machining system includes an electrolytic machining system frame, a spindle quick clamping system, a spindle slide assembly, a blade workpiece, a left axis drive device, a left feed axis, a left mold electrode, an electrolytic reaction chamber, a right mold electrode, a cathode wiring bridge assembly, a right feed axis, a right axis drive device, a spindle machining reference rapid positioning device A, and a spindle machining reference rapid positioning device B; the electrolytic reaction chamber is installed in the middle of the electrolytic machining system frame, the spindle slide assembly is installed opposite the front of the electrolytic reaction chamber, and the spindle machining reference rapid positioning device A and the spindle machining reference rapid positioning device B are respectively installed on both sides between the spindle slide assembly and the electrolytic reaction chamber;

[0021] Manufacturing related workpiece fixtures, the spindle quick clamping system includes an insulating sleeve, a workpiece clamping shaft, a sealing ring, a top spring bolt, a top spring, an insulating sleeve locking pin, a clamping shaft seat, a quick clamping device, a top pin, a parallel washer, and a parallel connecting bolt; characterized in that: a quick clamping device, a top spring bolt, a top spring, and a top pin are installed in the workpiece clamping shaft; the quick clamping device is used for quick clamping of blade workpieces; the top spring bolt, top spring, and top pin are used to flexibly and elastically push the quick clamping device to the right side, facilitating quick loading and unloading of blade workpieces;

[0022] The quick-clamping device includes a screw shaft, a screw sleeve retaining ring, a screw sleeve flange seat, a screw sleeve, a trapezoidal seat plate, a trapezoidal seat plate adjusting bolt, a quick-pull trapezoidal long plate, a connecting bolt pin, and a flange seat bolt. The trapezoidal seat plate contacts the upper right inclined plane of the quick-pull trapezoidal long plate. The quick-pull trapezoidal long plate is movably connected to the screw shaft by the connecting bolt pin. The screw shaft is helically connected to the screw sleeve. Rotating the screw sleeve can push the screw shaft, thereby pushing the quick-pull trapezoidal long plate to move up and down, so that the quick-pull trapezoidal long plate gradually deflects to the left or right under the action of the trapezoidal seat plate. When the quick-pull trapezoidal long plate moves upward, it deflects to the right; when it moves downward, it deflects to the left.

[0023] The workpiece clamping shaft includes a shaft root, a shaft platform, a locking pin hole, a top spring hole, a clamping shaft body, a workpiece seat hole, a trapezoidal seat adjustment hole, and a quick-pull channel; characterized in that: a quick-pull channel is provided with the bottom surface of the workpiece seat hole facing downwards, the quick-pull channel being a rectangular through hole perpendicular to the bottom surface of the workpiece seat hole; a top spring hole is provided on the left side of the quick-pull channel, the top spring hole being used to install a top spring bolt, a top spring, and a top pin; a trapezoidal seat adjustment hole is provided on the right side of the workpiece seat hole, the trapezoidal seat adjustment hole being used to install a trapezoidal seat adjustment bolt for the quick-clamping device.

[0024] Manufacturing related spindle machining reference positioning fixtures, the spindle machining reference positioning fixtures include spindle machining reference rapid positioning device A and spindle machining reference rapid positioning device B. Spindle machining reference rapid positioning device A includes a trapezoidal column, a push-off spring, a limit top, a coil slot, an electromagnet core, a coil, an indicator light, and a positioning button. The trapezoidal column has a long base, a square top, and a square upper-middle section. The upper-middle section and the square top section are equal in size, together forming a square elongated column. The bottom of the square elongated column and the long base of the trapezoidal column together form a trapezoidal elongated column that is smaller at the top and larger at the bottom. A coil slot is provided in the square elongated section of the trapezoidal column. A coil is installed inside the coil slot; the middle part of the coil is an electric core; the combination of the coil and the electric core is used for magnetic positioning of the spindle slide assembly; a push-away spring and a limiting top are installed on the front wall of the trapezoidal column below the coil; the limiting top is used to precisely define the position of the spindle slide assembly, and the limiting top is a protruding column with wear-resistant material on its surface; the push-away spring is a compression spring used to spring the spindle slide assembly back to the non-processing position after processing; an indicator light is installed on the top of the trapezoidal column, and the indicator light is used to indicate the status of the spindle slide assembly during processing and positioning. When the spindle slide assembly is positioned and processing, the indicator light is on; when the spindle slide assembly is in the non-processing position, the indicator light is off.

[0025] The spindle machining reference rapid positioning device A and the spindle machining reference rapid positioning device B have the same structure, function, purpose, and purpose; the difference lies in their positions. The spindle machining reference rapid positioning device A is installed on the right side between the spindle slide assembly and the electrolytic reaction tank, while the spindle machining reference rapid positioning device B is installed on the left side between the spindle slide assembly and the electrolytic reaction tank.

[0026] The spindle slide assembly includes a vertical base, a terminal block, a positioning release button, a handle, a main slide, a connecting hole, an insulating partition, and a right-angle connecting plate; characterized in that: a positioning release button is provided on the handle, which is used to connect or disconnect the coil power of the spindle machining reference rapid positioning device A and the spindle machining reference rapid positioning device B, thereby controlling the positioning release and reset of the spindle slide assembly;

[0027] The spindle machining reference rapid positioning device A and spindle machining reference rapid positioning device B are installed on both sides between the spindle slide assembly and the electrolytic reaction tank, with spindle machining reference rapid positioning device A on the right and spindle machining reference rapid positioning device B on the left. The coils of spindle machining reference rapid positioning devices A and B are connected in parallel. When electrolytically machining aircraft engine blades, when the spindle slide assembly moves to spindle machining reference rapid positioning devices A and B, the positioning buttons on spindle machining reference rapid positioning devices A and B are activated, thereby connecting the power supply to YA1, YA2 and the coils, causing the electromagnet core to generate a magnetic attraction force that tightly holds the spindle slide assembly. The spindle slide assembly is positioned to achieve the desired location. When the electrolytic machining of the aircraft engine blade is complete, pressing the positioning release button on the handle cuts off the power to YA1, YA2, and the coils, eliminating the magnetic attraction of the electromagnet core. Simultaneously, the push-away springs of the spindle machining reference quick positioning devices A and B push the spindle slide assembly away. Dragging the handle of the spindle slide assembly resets it, allowing for the machining of the next aircraft engine blade. This technical solution replaces the cumbersome process of bolting the slide to the workpiece during electrolytic machining, requiring subsequent disassembly, resetting, and reinstalling the spindle slide to install the next workpiece. It provides a convenient and quick way to position the spindle slide assembly and workpiece, thereby increasing machining speed and efficiency.

[0028] The beneficial effects of this invention are as follows: 1. Due to the reduction in the volume and mass of the blade root, the self-weight of the aircraft engine can be reduced, the load on the aircraft engine can be reduced, thereby promoting the improvement of the propulsion efficiency of the aircraft engine, reducing the failure rate and extending the service life of the aircraft engine; it can also reduce the fuel consumption of the aircraft engine, thereby saving energy, reducing pollution and protecting the environment; 2. Due to the function of the electrolytic machining spindle machining reference quick positioning device A and the spindle machining reference quick positioning device B, it can advancedly replace the cumbersome work of the existing electrolytic machining technology, where the spindle slide and the workpiece are fixed with bolts, and after machining, the bolts are removed and the spindle slide is reset, and then the next workpiece is installed for machining; it has the advanced effect of conveniently and quickly positioning the spindle slide assembly and the workpiece; achieving the purpose of improving machining speed and machining efficiency; 3. Due to the function of the quick clamping device, it replaces the cumbersome work of the existing technology, which requires removing the insulating sleeve, using a wrench to remove the bolts to replace the blade workpiece and then clamping it again; it has the advanced effect of conveniently and quickly replacing the blade workpiece; achieving the purpose of improving blade machining speed and machining efficiency. Attached Figure Description

[0029] Figure 1 These are structural diagrams of aircraft engine blades from two different perspectives.

[0030] Figure 2 yes Figure 1 A sectional view along the AA direction.

[0031] Figure 3 These are three perspective structural diagrams of the leaf root of this invention.

[0032] Figure 4 yes Figure 3 BB-direction sectional view.

[0033] Figure 5 This is a structural diagram of the leaf crown from three perspectives.

[0034] Figure 6 This is a structural diagram of a precision electrolysis machine tool.

[0035] Figure 7 This is a structural diagram of a precision electrolytic machining system.

[0036] Figure 8 These are two perspective structural diagrams of a precision electrolytic machining system in its unprocessed, reset state.

[0037] Figure 9 yes Figure 8 CC-direction sectional view.

[0038] Figure 10 yes Figure 8 DD section view.

[0039] Figure 11 yes Figure 8 EE-directed sectional view.

[0040] Figure 12 These are two perspective structural diagrams of the positioning and machining state of a precision electrolytic machining system.

[0041] Figure 13 yes Figure 12 FF section view.

[0042] Figure 14 yes Figure 12 GG section view.

[0043] Figure 15 yes Figure 12 HH sectional view.

[0044] Figure 16 These are two perspective structural diagrams of the spindle quick clamping system.

[0045] Figure 17 yes Figure 16 KK sectional view.

[0046] Figure 18 This is a structural diagram of the quick-clamp device.

[0047] Figure 19 yes Figure 20 TT sectional view.

[0048] Figure 20 These are structural diagrams of the workpiece clamping shaft from two different perspectives.

[0049] Figure 21 yes Figure 21 LL-direction sectional view.

[0050] Figure 22 yes Figure 17 Enlarged view of I in the middle.

[0051] Figure 23 yes Figure 17 Enlarged view of section II.

[0052] Figure 24 This is a structural diagram of the rapid positioning device A for the spindle machining reference.

[0053] Figure 25 This is a structural diagram of the spindle slide assembly.

[0054] Figure 26 These are structural diagrams of the left mode electrode from two different perspectives.

[0055] Figure 27 These are structural diagrams of the right-side mode electrode from two different perspectives.

[0056] Figure 28 This is a schematic diagram of a coil control circuit.

[0057] Figure 1 In the diagram, 1-A is a perspective view of an aircraft engine blade; 1-B is a front view of an aircraft engine blade.

[0058] Figure 3 In the diagram, 3-A is a three-dimensional view of the leaf root; 3-B is a front view of the leaf root; and 3-C is a top view of the leaf root.

[0059] Figure 5 In the diagram, 5-A is a three-dimensional view of the leaf crown; 5-B is a front view of the leaf crown; and 5-C is a bottom view of the leaf crown.

[0060] Figure 8 In the diagram, 8-A is a top view of the precision electrochemical machining system in its unprocessed and reset state; 8-B is a front view of the precision electrochemical machining system in its unprocessed and reset state.

[0061] Figure 12 In the diagram, 12-A is a top view of the precision electrochemical machining system in its positioning and machining state; 12-B is a front view of the precision electrochemical machining system in its positioning and machining state.

[0062] Figure 16In the diagram, 16-A is a perspective view of the spindle quick clamping system; 16-B is a front view of the spindle quick clamping system.

[0063] Figure 20 In the diagram, 20-A is a perspective view of the workpiece clamping shaft; 20-B is a top view of the workpiece clamping shaft.

[0064] Figure 26 In the diagram, 26-A is the right view of the left model electrode; 26-B is the front view of the left model electrode.

[0065] Figure 27 In the diagram, 27-A is the left view of the right-side electrode; 27-B is the front view of the right-side electrode.

[0066] In the diagram: 1. Machine tool housing; 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 feet; 11. Stand; 12. Left panel; 13. Electrolysis power supply; 14. Control power supply.

[0067] In the diagram, 31. Electrolytic machining system frame; 32. Spindle quick-clamp system; 33. Spindle slide assembly; 34. Blade workpiece; 35. Left axis drive; 36. Left feed axis; 37. Left die electrode; 38. Electrolytic reaction chamber; 39. Right die electrode; 310. Cathode wiring bridge assembly; 311. Right feed axis; 312. Right axis drive; 313. Spindle machining reference quick-positioning device A; 314. Spindle machining reference quick-positioning device B.

[0068] In the diagram, 321. Insulating sleeve; 322. Workpiece clamping shaft; 323. Sealing ring; 324. Top spring bolt; 325. Top spring; 326. Insulating sleeve locking pin; 327. Clamping shaft seat; 328. Quick clamping device; 329. Top pin; 320. Parallel washer; 3211. Parallel connecting bolt; 3271. Through hole; 3272. Parallel connecting bolt hole.

[0069] In the figure, 3221. Shaft root; 3222. Shaft platform; 3223. Locking pin hole; 3224. Top spring hole; 3225. Shaft clamping body; 3226. Workpiece seat hole; 3227. Trapezoidal seat adjustment hole; 3228. Quick pull channel.

[0070] In the diagram, 3281. Lead shaft; 3282. Threaded sleeve retaining ring; 3283. Threaded sleeve flange seat; 3284. Threaded sleeve; 3285. Trapezoidal seat plate; 3286. Trapezoidal seat plate adjusting bolt; 3287. Quick-release trapezoidal long plate; 3288. Connecting bolt pin; 3289. Flange seat bolt.

[0071] In the diagram, 331. Vertical seat; 332. Terminal block; 333. Position release button; 334. Handle; 335. Main slide plate; 336. Connection hole; 337. Insulating partition; 338. Right-angle connecting plate.

[0072] In the figure, 371. Left mold body; 372. Blade seat mold groove Z; 373. Acute angle side root branch mold groove Z; 374. Root branch groove mold protrusion Z; 375. Inner root branch mold groove Z; 376. Obtuse angle side root branch groove mold protrusion Z; 377. Obtuse angle side root branch mold groove Z; 378. Blade seat flash B mold groove Z; 379. Blade direction synchronous cone shaft mold hole Z; 3710. Workpiece groove Z; 3711. Left mold mounting buckle.

[0073] In the diagram, 391. Right mold body; 392. Blade seat mold groove Y; 393. Acute-angled edge root branch mold groove Y; 394. Root branch groove mold protrusion Y; 395. Inner root branch mold groove Y; 396. Obtuse-angled edge root branch groove mold protrusion Y; 397. Obtuse-angled edge root branch mold groove Y; 398. Blade seat flash B mold groove Y; 399. Blade direction synchronous cone shaft mold hole Y; 3910. Workpiece groove Y; 3911. Right mold mounting buckle.

[0074] In the diagram, 3131. Trapezoidal column; 3132. Push-off spring; 3133. Limiting top; 3134. Coil slot; 3135. Electromagnetic core; 3136. Coil; 3137. Indicator light; 3138. Positioning button.

[0075] In the diagram, 341. Leaf root; 342. Leaf-directional synchronous cone; 343. Leaf seat; 344. Leaf blade body; 345. Leaf crown;

[0076] In the figure, 3441. Blade wall; 3442. Blade concave surface; 3443. Blade convex surface; 3444. Flow splitting arc head; 3445. Jet tip.

[0077] In the diagram, 3411. Acute-angled side root branch; 3412. Root branch groove; 3413. Inner root branch; 3414. Obtuse-angled side root branch groove; 3415. Obtuse-angled side root branch; 3416. Vertical parallel plane; 3417. Oblique transverse parallel corrugated surface; 3418. First trough; 3419. First peak; 3420. Second trough; 3421. Second peak; 3422. Root tip.

[0078] In the diagram, 3431. Main body of the blade seat; 3432. Blade seat flash A; 3433. Blade seat flash B; 3434. Inner flash A of the blade seat; 3435. Inner flash B of the blade seat; 3436. Inner flash B of the blade seat; 3437. Oblique transverse parallel corrugated surface; 3438. First trough; 3439. First peak; 3430. Second trough.

[0079] In the diagram, 3451. Crown seat; 3452. Leaf-direction synchronous locking groove A; 3453. Leaf-direction synchronous AB locking tip; 3454. Leaf-direction synchronous locking groove B; 3455. Leaf-direction synchronous locking groove C; 3456. Leaf-direction synchronous CD locking tip; 3457. Leaf-direction synchronous locking groove D; 3458. Crown serration; 3459. Crown flash.

[0080] Figure 4 In the diagram, DX is the total width of the leaf root; d1 is the width of the root branch with acute angle; d2 is the width of the root branch groove; d3 is the width of the inner root branch; d4 is the width of the root branch with obtuse angle; d5 is the width of the root branch groove with obtuse angle; DY is the maximum parallel distance between the two oblique transverse parallel corrugated surfaces; dy1 is the distance between the centers of the bottom circles of the root branch grooves on both sides; dy2 is the depth of the root branch groove; and DA is the acute angle of the leaf root.

[0081] Figure 28 In the diagram, 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. Detailed Implementation

[0082] The present invention will be further described below with reference to the accompanying drawings and embodiments.

[0083] Example 1

[0084] exist Figure 3 , Figure 4 In a design of an aircraft engine blade root, the blade root (341) is characterized by comprising an acute-angled root branch (3411), a root branch groove (3412), an inner root branch (3413), an obtuse-angled root branch groove (3414), an obtuse-angled root branch (3415), a vertical parallel plane (3416), an oblique transverse parallel corrugated surface (3417), a trough (3418), a peak (3419), two troughs (3420), two peaks (3421), and a root tip (3422).

[0085] exist Figure 1 , Figure 2 , Figure 3 , Figure 4 The present invention provides an aircraft engine blade comprising a blade root (341), a blade-direction synchronous cone shaft (342), a blade seat (343), a blade body (344), and a blade crown (345); characterized in that: the blade root (341) has a void structure design;

[0086] exist Figure 2 In the process, the blade body (344) includes a blade wall (3441), a concave surface (3442), a convex surface (3443), a flow splitting arc head (3444), and a jet tip (3445).

[0087] exist Figure 3 In the middle, the blade seat (343) includes a blade seat body (3431), a blade seat flash A (3432), a blade seat flash B (3433), an inner blade seat flash A (3434), an inner blade seat flash B (3435), an inner blade seat flash B (3436), a diagonal parallel corrugated surface (3437), a trough (3438), a peak (3439), and two troughs (3430);

[0088] exist Figure 4 In this diagram, DX represents the total width of the leaf root; d1 represents the width of the root branch with acute angles, with the ratio of DX to d1 being 1:8-12; d2 represents the width of the root branch groove, with the ratio of DX to d2 being 1:10-14; d3 represents the width of the inner root branch, with the ratio of DX to d3 being 1:10-14; d4 represents the width of the root branch with obtuse angles, with the ratio of DX to d4 being 1:18-22; d5 represents the width of the root branch groove with obtuse angles, with the ratio of DX to d5 being 1:18-22; DY represents the maximum parallel distance between the two oblique transverse parallel corrugated surfaces; dy1 represents the distance between the centers of the bottom circles of the root branch grooves on both sides, with the ratio of dy1 to DY being 2-2.5:1; dy2 represents the depth of the root branch groove, with the ratio of dy2 to DY being 6-6.5:1; and DA represents the acute angle of the leaf root, with the angle of DA being 65-75 degrees.

[0089] exist Figure 5 In the above, the leaf crown (345) includes a crown seat (3451), a leaf direction synchronous locking groove A (3452), a leaf direction synchronous AB locking tip (3453), a leaf direction synchronous locking groove B (3454), a leaf direction synchronous locking groove C (3455), a leaf direction synchronous CD locking tip (3456), a leaf direction synchronous locking groove D (3457), a crown serration (3458), and a crown flash (3459);

[0090] Furthermore, the leaf root (341) is provided with multiple root branch grooves (3412) and multiple inner root branches (3413), and the multiple root branch grooves (3412) and multiple inner root branches (3413) are distributed at intervals to make the leaf root (341) form a void body;

[0091] Furthermore, 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;

[0092] Furthermore, in Figure 4 In this process, the root and branch groove (3412) is disposed in the upper and lower halves of the leaf root (341);

[0093] Furthermore, in Figure 4In the middle, the root and branch groove (3412) of the upper half and the root and branch groove (3412) of the lower half do not intersect on the same straight line;

[0094] Furthermore, in Figure 4 In the middle, the root and branch grooves (3412) of the upper half and the root and branch grooves (3412) of the lower half are arranged in parallel with each other in a staggered manner;

[0095] Furthermore, in Figure 4 In the middle, the bottom of the root and branch groove (3412) of the upper half and the bottom of the root and branch groove (3412) of the lower half are separated by a certain wall thickness, and the distance wall thickness dimension is greater than or equal to 0.5 times the wall thickness width dimension of the inner root and branch (3413).

[0096] The above-described technical solution, due to the presence of multiple root and branch grooves (3412) and multiple internal root branches (3413), can significantly reduce the volume and mass of the leaf roots (341) compared to existing technologies.

[0097] Furthermore, the volume and mass of the blade root (341) account for a large portion of the aircraft engine blades;

[0098] Furthermore, since there are hundreds or thousands of blades in an aircraft engine, if all the aircraft engine blades of this invention are used, the total weight of the aircraft engine can be reduced significantly.

[0099] Therefore, the aircraft engine blades of the present invention can reduce the weight of the aircraft engine and improve the propulsion efficiency of the aircraft engine.

[0100] Furthermore, because the present invention is lightweight, the load on the aircraft engine is reduced, which in turn reduces the failure rate and increases the service life of the aircraft engine.

[0101] Furthermore, because the present invention is lightweight, it can reduce the fuel consumption of aircraft engines, thereby saving energy and reducing pollution to protect the environment.

[0102] As this invention is the first of its kind in the field of aviation technology both domestically and internationally, it possesses a certain degree of creativity and novelty.

[0103] Example 2

[0104] exist Figure 6 , Figure 7In a precision electrolytic machining process for manufacturing the root of an aircraft engine blade, the following components are included: a machine tool housing (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), machine feet (10), a frame (11), a left panel (12), an electrolytic power supply (13), and a control power supply (14); characterized in that: the precision electrolytic machining system (3) includes an electrolytic machining system frame (31), a spindle quick clamping system (32), a spindle slide assembly (33), a blade workpiece (34), a left axis drive device (35), and a left feed axis (36). The system includes a left mold electrode (37), an electrolytic reaction chamber (38), a right mold electrode (39), a cathode wiring bridge assembly (310), a right feed axis (311), a right axis drive device (312), a spindle machining reference rapid positioning device A (313), and a spindle machining reference rapid positioning device B (314). The electrolytic machining system frame (31) is equipped with an electrolytic reaction chamber (38) in the middle. A spindle slide assembly (33) is installed opposite the front of the electrolytic reaction chamber (38). A spindle machining reference rapid positioning device A (313) and a spindle machining reference rapid positioning device B (314) are installed on both sides between the spindle slide assembly (33) and the electrolytic reaction chamber (38).

[0105] exist Figure 24The spindle machining reference rapid positioning device A (313) includes a trapezoidal column (3131), a push-off spring (3132), a limit top (3133), a coil slot (3134), an electric core (3135), a coil (3136), an indicator light (3137), and a positioning button (3138). The bottom surface of the trapezoidal column (3131) is rectangular, the top surface is square, and the upper middle section is square. The upper middle section is equal to the top square section, forming a rectangular rectangular column. The bottom of the rectangular column and the bottom rectangular section of the trapezoidal column (3131) together form a trapezoidal column that is smaller at the top and larger at the bottom. A coil slot (3134) is provided in the rectangular rectangular section of the trapezoidal column (3131), and a coil (3136) is installed in the coil slot (3134). The middle part of the coil (3136) is an electric core (3135). The coil (3136) The coil (3136) and the electric core (3135) are combined for magnetic positioning of the spindle slide assembly (33); a push-off spring (3132) and a limiting top (3133) are installed on the front wall of the trapezoidal column (3131) below the coil (3136); the limiting top (3133) is used to precisely limit the position of the spindle slide assembly (33), and the limiting top (3133) is a protruding column with wear-resistant material on its surface; the push-off spring (3132) is a compression spring, used to spring the spindle slide assembly (33) back to the non-processing position after the machining is completed; an indicator light (3137) is installed on the top of the trapezoidal column (3131), and the indicator light (3137) is used to indicate the status of the spindle slide assembly (33) during machining and positioning. When the spindle slide assembly (33) is positioned and machined, the indicator light (3137) is lit, and when the spindle slide assembly (33) is in the non-processing position, the indicator light (3137) is not lit.

[0106] The spindle machining reference rapid positioning device A (313) and the spindle machining reference rapid positioning device B (314) have the same structure, function, purpose and purpose; the difference is that the spindle machining reference rapid positioning device A (313) is installed on the right side between the spindle slide assembly (33) and the electrolytic reaction tank (38), and the spindle machining reference rapid positioning device B (314) is installed on the left side between the spindle slide assembly (33) and the electrolytic reaction tank (38).

[0107] exist Figure 25In the present invention, the spindle slide assembly (33) includes a vertical seat (331), a terminal block (332), a positioning release button (333), a handle (334), a main slide (335), a connecting hole (336), an insulating partition (337), and a right-angle connecting plate (338); characterized in that: a positioning release button (333) is provided on the handle (334), the positioning release button (333) is used to turn on or off the power supply of the coil (3136) of the spindle machining reference rapid positioning device A (313) and the spindle machining reference rapid positioning device B (314), thereby controlling the positioning release and reset of the spindle slide assembly (33).

[0108] exist Figure 8 , Figure 10 , Figure 12 , Figure 24 , Figure 9 , Figure 13 , Figure 11 , Figure 14 , Figure 15 , Figure 25 , Figure 28In the middle, the spindle machining reference rapid positioning device A (313) and the spindle machining reference rapid positioning device B (314) are installed on both sides between the spindle slide assembly (33) and the electrolytic reaction tank (38), with the spindle machining reference rapid positioning device A (313) installed on the right and the spindle machining reference rapid positioning device B (314) installed on the left; the coils (3136) of the spindle machining reference rapid positioning device A (313) and the spindle machining reference rapid positioning device B (314) are connected. When the spindle slide assembly (33) moves to the spindle machining reference rapid positioning device A (313) and spindle machining reference rapid positioning device B (314) during electrolytic machining of aircraft engine blades, the positioning button (3138) on the spindle machining reference rapid positioning device A (313) and spindle machining reference rapid positioning device B (314) is activated, thereby connecting the power supply of YA1, YA2 and coil (3136), causing the electromagnet core (3135) to generate magnetic attraction to move the spindle slide. The assembly (33) is firmly held in place, allowing the spindle slide assembly (33) to achieve its positioning purpose. When the electrolytic machining of the aircraft engine blades is completed, pressing the positioning release button (333) on the handle (334) cuts off the power to YA1, YA2 and the coil (3136), causing the magnetic attraction of the electromagnet core (3135) to be eliminated. At the same time, the push-away springs (3132) of the spindle machining reference rapid positioning device A (313) and the spindle machining reference rapid positioning device B (314) push the spindle slide assembly (33) away. The handle (334) of the moving spindle slide assembly (33) resets the spindle slide assembly (33) and allows for the reprocessing of the next aircraft engine blade. The effect of this technical solution is to replace the tedious work of fixing the spindle slide and the workpiece with bolts during electrolytic machining in the prior art, and then removing the bolts to reset the spindle slide after machining, and then installing the next workpiece for machining. It achieves the advanced effect of conveniently and quickly positioning the spindle slide assembly (33) and the workpiece (34), thereby increasing the machining speed and machining efficiency.

[0109] exist Figure 16 , Figure 17In the above, the spindle quick clamping system (32) includes an insulating sleeve (321), a workpiece clamping shaft (322), a sealing ring (323), a top spring bolt (324), a top spring (325), an insulating sleeve locking pin (326), a clamping shaft seat (327), a quick clamping device (328), a top pin (329), a parallel washer (320), and a parallel connecting bolt (3211); characterized in that: a quick clamping device (328), a top spring bolt (324), a top spring (325), and a top pin (329) are installed in the workpiece clamping shaft (322); the quick clamping device (328) is used for quick clamping of the blade workpiece (34); the top spring bolt (324), the top spring (325), and the top pin (329) are used to flexibly and elastically push the quick clamping device (328) to the right side, so as to facilitate quick loading and unloading of the blade workpiece (34).

[0110] exist Figure 18 , Figure 19 In this device, the quick-clamping device (328) includes a lead screw (3281), a lead sleeve retaining ring (3282), a lead sleeve flange seat (3283), a lead sleeve (3284), a trapezoidal seat plate (3285), a trapezoidal seat plate adjusting bolt (3286), a quick-pull trapezoidal long plate (3287), a connecting bolt pin (3288), and a flange seat bolt (3289). The trapezoidal seat plate (3285) contacts the upper right inclined plane of the quick-pull trapezoidal long plate (3287). The quick-pull trapezoidal long plate (3287) and the lead screw (3281) are connected by the connecting bolt pin (3288). The screw shaft (3281) is spirally connected to the screw sleeve (3284). Rotating the screw sleeve (3284) can push the screw shaft (3281) and thus push the quick-draw trapezoidal long piece (3287) to move up and down, so that the quick-draw trapezoidal long piece (3287) gradually deviates to the left or right under the action of the trapezoidal seat piece (3285). When the quick-draw trapezoidal long piece (3287) moves upward, the quick-draw trapezoidal long piece (3287) deviates to the right. When the quick-draw trapezoidal long piece (3287) moves downward, the quick-draw trapezoidal long piece (3287) deviates to the left.

[0111] exist Figure 20 , Figure 21The workpiece clamping shaft (322) includes a shaft root (3221), a shaft platform (3222), a locking pin hole (3223), a top spring hole (3224), a clamping shaft body (3225), a workpiece seat hole (3226), a trapezoidal seat adjustment hole (3227), and a quick-pull channel (3228); characterized in that: a quick-pull channel (3228) is provided on the bottom surface of the workpiece seat hole (3226), and the quick-pull channel (3228) is connected to the workpiece seat hole (3226). A rectangular through hole with a vertical bottom surface; a top spring hole (3224) is provided on the left side of the quick-pull channel (3228), the top spring hole (3224) is used to install the top spring bolt (324), the top spring (325), and the top pin (329); a trapezoidal seat plate adjustment hole (3227) is provided on the right side of the workpiece seat hole (3226), the trapezoidal seat plate adjustment hole (3227) is used to install the trapezoidal seat plate adjustment bolt (3286) of the quick clamping device (328).

[0112] exist Figure 17 , Figure 19 , Figure 22 In the above, the clamping shaft seat (327) includes a central through hole (3271) and a parallel connecting bolt hole (3272); the threaded sleeve flange seat (3283), threaded sleeve (3284), threaded sleeve retaining ring (3282), and threaded shaft (3281) of the quick clamping device (328) are installed in the central through hole (3271) of the clamping shaft seat (327), and the threaded sleeve flange seat (3283) and the clamping shaft seat (327) are fixedly connected by flange seat bolts (3289); the quick pull channel (3228) of the workpiece clamping shaft (322) is equipped with a quick pull trapezoidal long piece (3287), the quick pull trapezoidal long piece (3287) is movably connected to the threaded shaft (3281), and a connecting bolt pin (3288) is inserted in the threaded shaft (3281) and the quick pull trapezoidal long piece (3287).

[0113] exist Figure 17 , Figure 19 , Figure 23In this configuration, the quick-draw trapezoidal long piece (3287) and trapezoidal seat piece (3285) are located on the right side of the workpiece seat hole (3226). When the quick-draw trapezoidal long piece (3287) moves downward, due to the trapezoidal action of the quick-draw trapezoidal long piece (3287) and trapezoidal seat piece (3285), the quick-draw trapezoidal long piece (3287) gradually shifts to the left, generating a leftward squeezing force. Therefore, when a blade workpiece (34) is installed in the workpiece seat hole (3226), rotating the screw sleeve (3284) of the quick-clamping device (328) causes the quick-draw trapezoidal long piece (3287) to move downward, generating a leftward squeezing force. The leftward squeezing force of the quick-pull trapezoidal long piece (3287) will squeeze the blade workpiece (34) in the workpiece seat hole (3226), thereby tightening and fixing the blade workpiece (34) in the workpiece seat hole (3226). The outstanding feature of this technical solution is that it replaces the tedious work of removing the insulating sleeve (321) and using a wrench to remove the bolts to replace the blade workpiece (34) and then clamping it again, which is required by the prior art. It has the advanced effect of convenient and quick replacement of the blade workpiece (34) and achieves the purpose of improving the blade processing speed and processing efficiency.

[0114] exist Figure 25 In the present invention, the spindle slide assembly (33) includes a vertical seat (331), a terminal block (332), a positioning release button (333), a handle (334), a main slide (335), a connecting hole (336), an insulating partition (337), and a right-angle connecting plate (338); characterized in that: a positioning release button (333) is provided on the handle (334), the positioning release button (333) is used to turn on or off the power supply of the coil (3136) of the spindle machining reference rapid positioning device A (313) and the spindle machining reference rapid positioning device B (314), thereby controlling the positioning release and reset of the spindle slide assembly (33).

[0115] exist 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 side root branch mold groove Z (373), a root branch groove mold protrusion Z (374), an inner root branch mold groove Z (375), an obtuse angle side root branch groove mold protrusion Z (376), an obtuse angle side root branch mold groove Z (377), a blade seat flash edge B mold groove Z (378), a blade direction synchronous cone shaft mold hole Z (379), a workpiece groove Z (3710), and a left mold mounting buckle (3711); the left mold mounting buckle (3711) is located at the left end of the left mold body (371) and is used to connect with the left feed shaft (36).

[0116] exist Figure 27In the middle, the right mold electrode (39) includes a right mold body (391), a blade seat mold groove Y (392), an acute angle side root branch mold groove Y (393), a root branch groove mold protrusion Y (394), an inner root branch mold groove Y (395), an obtuse angle side root branch groove mold protrusion Y (396), an obtuse angle side root branch mold groove Y (397), a blade seat flash edge B mold groove Y (398), a blade direction synchronous cone shaft mold hole Y (399), a workpiece groove Y (3910), and a right mold mounting buckle (3911); the right mold mounting buckle (3911) is located at the right end of the right mold body (391) and is used to connect with the right feed shaft (311).

[0117] exist Figure 6 , Figure 9 , Figure 26 In the middle, the left mold electrode (37) is installed at the right end of the left feed shaft (36). The electrical connection of the left mold electrode (37) is as follows: the left mold electrode (37) is connected to the left feed shaft (36), the left feed shaft (36) is connected to the electrolytic machining system frame (31), and the electrolytic machining system frame (31) is connected to the electrolytic power supply (13).

[0118] exist Figure 6 , Figure 9 , Figure 27 In the middle, the right mold electrode (39) is installed at the left end of the right feed shaft (311). The electrical connection of the right mold electrode (39) is as follows: the right mold electrode (37) is connected to the right feed shaft (311), the right feed shaft (311) is connected to the electrolytic machining system frame (31), and the electrolytic machining system frame (31) is connected to the electrolytic power supply (13).

[0119] exist Figure 28 Figure 24 In the circuit, the coil control circuit includes DC, SB1, SB2, C1, LED, R1, YA1, and YA2, where YA1 and YA2 represent coils (3136); used to control the coils (3136) of the spindle machining reference rapid positioning device A and the spindle machining reference rapid positioning device B; DC is a 12-36V DC power supply, input from the control power supply (14); SB1 is a normally open push-button switch for high current, SB2 is a normally closed push-button switch for high current, and C1 is an electrolytic capacitor. The LED is an indicator light (3137), R1 is a resistor, and YA1 and YA2 are coils (3136). During normal operation, pressing SB1 energizes C1 to power YA1 and YA2, i.e., the coil (3136). After the coil (3136) is energized, the electric iron core (3135) generates a magnetic attraction force, and the LED lights up. Pressing SB2 cuts off the power supply to YA1, YA2, C1, and the LED, causing YA1 and YA2 to lose power and the LED to turn off. After YA1 and YA2 lose power, the electromagnetic attraction force disappears.

[0120] Example 3

[0121] exist Figure 3 , Figure 4 In a design of an aircraft engine blade root, the blade root (341) is characterized in that: the blade root (341) includes an acute-angled side root branch (3411), a root branch groove (3412), an inner root branch (3413), an obtuse-angled side root branch groove (3414), an obtuse-angled side root branch (3415), a vertical parallel plane (3416), an oblique transverse parallel corrugated surface (3417), a trough (3418), a peak (3419), a second trough (3420), a second peak (3421), and a root tip (3422).

[0122] exist Figure 1 , Figure 2 , Figure 3 , Figure 4 The aircraft engine blade of the present invention includes a blade root (341), a blade axial synchronous cone shaft (342), a blade seat (343), a blade body (344), and a blade crown (345); characterized in that: the blade root (341) includes an acute-angled root branch (3411), a root branch groove (3412), an inner root branch (3413), an obtuse-angled root branch groove (3414), an obtuse-angled root branch (3415), a vertical parallel plane (3416), and an oblique transverse parallel corrugated surface (3417); the number of root branch grooves (3412) is 12; the number of inner root branches (3413) is 10;

[0123] exist Figure 2 In the process, the blade body (344) includes a blade wall (3441), a concave surface (3442), a convex surface (3443), a flow splitter head (3444), and a jet tip (3445);

[0124] exist Figure 3 In the middle, the blade seat (343) includes a blade seat body (3431), a blade seat flash A (3432), a blade seat flash B (3433), an inner blade seat flash A (3434), an inner blade seat flash B (3435), an inner blade seat flash B (3436), a diagonal parallel corrugated surface (3437), a trough (3438), a peak (3439), and two troughs (3430);

[0125] exist Figure 4In this diagram, DX represents the total width of the leaf root; d1 represents the width of the root branch with acute angles, with a ratio of 1:10 between DX and d1; d2 represents the width of the root branch groove, with a ratio of 1:12 between DX and d2; d3 represents the width of the inner root branch, with a ratio of 1:12 between DX and d3; d4 represents the width of the root branch with obtuse angles, with a ratio of 1:20 between DX and d4; d5 represents the width of the root branch groove with obtuse angles, with a ratio of 1:20 between DX and d5; DY represents the maximum parallel distance between the two oblique transverse parallel corrugated surfaces; dy1 represents the distance between the centers of the bottom circles of the root branch grooves on both sides, with a ratio of 2.3:1 between dy1 and DY; dy2 represents the depth of the root branch groove, with a ratio of 6.25:1 between dy2 and DY; and DA represents the acute angle of the leaf root, with an angle of 70 degrees.

[0126] exist Figure 5 In the above, the leaf crown (345) includes a crown seat (3451), a leaf direction synchronous locking groove A (3452), a leaf direction synchronous AB locking tip (3453), a leaf direction synchronous locking groove B (3454), a leaf direction synchronous locking groove C (3455), a leaf direction synchronous CD locking tip (3456), a leaf direction synchronous locking groove D (3457), a crown serration (3458), and a crown flash (3459);

[0127] Furthermore, the leaf root (341) is provided with 10 root branch grooves (3412) and 10 inner root branches (3413), and the 10 root branch grooves (3412) and 10 inner root branches (3413) are distributed alternately to make the leaf root (341) form a void body;

[0128] Furthermore, the width ratio of the root branch groove (3412) to the inner root branch (3413) is 1:1;

[0129] Furthermore, in Figure 4 In this process, the root and branch groove (3412) is disposed in the upper and lower halves of the leaf root (341);

[0130] Furthermore, in Figure 4 In the middle, the root and branch groove (3412) of the upper half and the root and branch groove (3412) of the lower half do not intersect on the same straight line;

[0131] Furthermore, in Figure 4 In the middle, the root and branch grooves (3412) of the upper half and the root and branch grooves (3412) of the lower half are arranged in parallel with each other in a staggered manner;

[0132] Furthermore, in Figure 4 In the middle, the bottom of the root and branch groove (3412) of the upper half and the bottom of the root and branch groove (3412) of the lower half are separated by a certain wall thickness, and the distance wall thickness is equal to 0.5 times the width of the wall thickness of the inner root and branch (3413).

[0133] The above-described technical solution, with 10 root and branch grooves (3412) and 10 inner root branches (3413), can reduce the volume and mass of the leaf roots (341) by a lot compared with the prior art;

[0134] Furthermore, the volume and mass of the blade root (341) account for a large portion of the aircraft engine blades;

[0135] Furthermore, since there are hundreds or thousands of blades in an aircraft engine, if all the aircraft engine blades of this invention are used, the total weight of the aircraft engine can be reduced significantly.

[0136] Therefore, the aircraft engine blades of the present invention can reduce the weight of the aircraft engine and improve the propulsion efficiency of the aircraft engine.

[0137] Furthermore, because the present invention is lightweight, the load on the aircraft engine is reduced, which in turn reduces the failure rate and increases the service life of the aircraft engine.

[0138] Furthermore, because the present invention is lightweight, it can reduce the fuel consumption of aircraft engines, thereby saving energy and reducing pollution to protect the environment.

[0139] As this invention is the first of its kind in the field of aviation technology both domestically and internationally, it possesses a certain degree of creativity, novelty, and practicality.

[0140] Example 4

[0141] exist Figure 6 , Figure 7A precision electrolytic machining machine tool for manufacturing aircraft engine blade roots includes a machine tool housing (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), machine feet (10), a frame (11), a left panel (12), an electrolytic power supply (13), and a control power supply (14); characterized in that: the precision electrolytic machining system (3) includes an electrolytic machining system frame (31), a spindle quick clamping system (32), a spindle slide assembly (33), a blade workpiece (34), a left axis drive device (35), and a left feed axis (36). The electrolytic machining system frame (31) is equipped with an electrolytic reaction box (38), a right mold electrode (39), a cathode wiring bridge assembly (310), a right feed axis (311), a right axis drive device (312), a spindle machining reference rapid positioning device A (313), and a spindle machining reference rapid positioning device B (314). The electrolytic machining system frame (31) is equipped with an electrolytic reaction box (38) in the middle. The front of the electrolytic reaction box (38) is equipped with a spindle slide assembly (33). The spindle machining reference rapid positioning device A (313) and the spindle machining reference rapid positioning device B (314) are respectively installed on both sides between the spindle slide assembly (33) and the electrolytic reaction box (38).

[0142] exist Figure 24The spindle machining reference rapid positioning device A (313) includes a trapezoidal column (3131), a push-off spring (3132), a limit top (3133), a coil slot (3134), an electric core (3135), a coil (3136), an indicator light (3137), and a positioning button (3138). The bottom surface of the trapezoidal column (3131) is rectangular, the top surface is square, and the upper middle section is square. The upper middle section is equal to the top square section, forming a rectangular rectangular column. The bottom of the rectangular column and the bottom rectangular section of the trapezoidal column (3131) together form a trapezoidal column that is smaller at the top and larger at the bottom. A coil slot (3134) is provided in the rectangular rectangular section of the trapezoidal column (3131), and a coil (3136) is installed in the coil slot (3134). The middle part of the coil (3136) is an electric core (3135). The coil (3136) The coil (3136) and the electric core (3135) are combined for magnetic positioning of the spindle slide assembly (33); a push-off spring (3132) and a limiting top (3133) are installed on the front wall of the trapezoidal column (3131) below the coil (3136); the limiting top (3133) is used to precisely limit the position of the spindle slide assembly (33), and the limiting top (3133) is a protruding column with wear-resistant material on its surface; the push-off spring (3132) is a compression spring, used to spring the spindle slide assembly (33) back to the non-processing position after the machining is completed; an indicator light (3137) is installed on the top of the trapezoidal column (3131), and the indicator light (3137) is used to indicate the status of the spindle slide assembly (33) during machining and positioning. When the spindle slide assembly (33) is positioned and machined, the indicator light (3137) is lit, and when the spindle slide assembly (33) is in the non-processing position, the indicator light (3137) is not lit.

[0143] The spindle machining reference rapid positioning device A (313) and the spindle machining reference rapid positioning device B (314) have the same structure, function, purpose and purpose; the difference is that the spindle machining reference rapid positioning device A (313) is installed on the right side between the spindle slide assembly (33) and the electrolytic reaction tank (38), and the spindle machining reference rapid positioning device B (314) is installed on the left side between the spindle slide assembly (33) and the electrolytic reaction tank (38).

[0144] exist Figure 25In the present invention, the spindle slide assembly (33) includes a vertical seat (331), a terminal block (332), a positioning release button (333), a handle (334), a main slide (335), a connecting hole (336), an insulating partition (337), and a right-angle connecting plate (338); characterized in that: a positioning release button (333) is provided on the handle (334), the positioning release button (333) is used to turn on or off the power supply of the coil (3136) of the spindle machining reference rapid positioning device A (313) and the spindle machining reference rapid positioning device B (314), thereby controlling the positioning release and reset of the spindle slide assembly (33).

[0145] exist Figure 8 , Figure 10 , Figure 12 , Figure 24 , Figure 9 , Figure 13 , Figure 11 , Figure 14 , Figure 15 , Figure 25 , Figure 28In the middle, the spindle machining reference rapid positioning device A (313) and the spindle machining reference rapid positioning device B (314) are installed on both sides between the spindle slide assembly (33) and the electrolytic reaction tank (38), with the spindle machining reference rapid positioning device A (313) installed on the right and the spindle machining reference rapid positioning device B (314) installed on the left; the coils (3136) of the spindle machining reference rapid positioning device A (313) and the spindle machining reference rapid positioning device B (314) are connected. When the spindle slide assembly (33) moves to the spindle machining reference rapid positioning device A (313) and spindle machining reference rapid positioning device B (314) during electrolytic machining of aircraft engine blades, the positioning button (3138) on the spindle machining reference rapid positioning device A (313) and spindle machining reference rapid positioning device B (314) is activated, thereby connecting the power supply of YA1, YA2 and coil (3136), causing the electromagnet core (3135) to generate magnetic attraction to move the spindle slide. The assembly (33) is firmly held in place, allowing the spindle slide assembly (33) to achieve its positioning purpose. When the electrolytic machining of the aircraft engine blades is completed, pressing the positioning release button (333) on the handle (334) cuts off the power to YA1, YA2 and the coil (3136), causing the magnetic attraction of the electromagnet core (3135) to be eliminated. At the same time, the push-away springs (3132) of the spindle machining reference rapid positioning device A (313) and the spindle machining reference rapid positioning device B (314) push the spindle slide assembly (33) away. The handle (334) of the moving spindle slide assembly (33) resets the spindle slide assembly (33) and allows for the reprocessing of the next aircraft engine blade. The effect of this technical solution is to replace the tedious work of fixing the spindle slide and the workpiece with bolts during electrolytic machining in the prior art, and then removing the bolts to reset the spindle slide after machining, and then installing the next workpiece for machining. It achieves the advanced effect of conveniently and quickly positioning the spindle slide assembly (33) and the workpiece (34), thereby increasing the machining speed and machining efficiency.

[0146] exist Figure 16 , Figure 17In the above, the spindle quick clamping system (32) includes an insulating sleeve (321), a workpiece clamping shaft (322), a sealing ring (323), a top spring bolt (324), a top spring (325), an insulating sleeve locking pin (326), a clamping shaft seat (327), a quick clamping device (328), a top pin (329), a parallel washer (320), and a parallel connecting bolt (3211); characterized in that: a quick clamping device (328), a top spring bolt (324), a top spring (325), and a top pin (329) are installed in the workpiece clamping shaft (322); the quick clamping device (328) is used for quick clamping of the blade workpiece (34); the top spring bolt (324), the top spring (325), and the top pin (329) are used to flexibly and elastically push the quick clamping device (328) to the right side, so as to facilitate quick loading and unloading of the blade workpiece (34).

[0147] exist Figure 18 , Figure 19 In this device, the quick-clamping device (328) includes a lead screw (3281), a lead sleeve retaining ring (3282), a lead sleeve flange seat (3283), a lead sleeve (3284), a trapezoidal seat plate (3285), a trapezoidal seat plate adjusting bolt (3286), a quick-pull trapezoidal long plate (3287), a connecting bolt pin (3288), and a flange seat bolt (3289). The trapezoidal seat plate (3285) contacts the upper right inclined plane of the quick-pull trapezoidal long plate (3287). The quick-pull trapezoidal long plate (3287) and the lead screw (3281) are connected by the connecting bolt pin (3288). The screw shaft (3281) is spirally connected to the screw sleeve (3284). Rotating the screw sleeve (3284) can push the screw shaft (3281) and thus push the quick-draw trapezoidal long piece (3287) to move up and down, so that the quick-draw trapezoidal long piece (3287) gradually deviates to the left or right under the action of the trapezoidal seat piece (3285). When the quick-draw trapezoidal long piece (3287) moves upward, the quick-draw trapezoidal long piece (3287) deviates to the right. When the quick-draw trapezoidal long piece (3287) moves downward, the quick-draw trapezoidal long piece (3287) deviates to the left.

[0148] exist Figure 20 , Figure 21The workpiece clamping shaft (322) includes a shaft root (3221), a shaft platform (3222), a locking pin hole (3223), a top spring hole (3224), a clamping shaft body (3225), a workpiece seat hole (3226), a trapezoidal seat adjustment hole (3227), and a quick-pull channel (3228); characterized in that: a quick-pull channel (3228) is provided on the bottom surface of the workpiece seat hole (3226), and the quick-pull channel (3228) is connected to the workpiece seat hole (3226). A rectangular through hole with a vertical bottom surface; a top spring hole (3224) is provided on the left side of the quick-pull channel (3228), the top spring hole (3224) is used to install the top spring bolt (324), the top spring (325), and the top pin (329); a trapezoidal seat plate adjustment hole (3227) is provided on the right side of the workpiece seat hole (3226), the trapezoidal seat plate adjustment hole (3227) is used to install the trapezoidal seat plate adjustment bolt (3286) of the quick clamping device (328).

[0149] exist Figure 17 , Figure 22 In the above, the clamping shaft seat (327) includes a central through hole (3271) and a parallel connecting bolt hole (3272); the threaded sleeve flange seat (3283), threaded sleeve (3284), threaded sleeve retaining ring (3282), and threaded shaft (3281) of the quick clamping device (328) are installed in the central through hole (3271) of the clamping shaft seat (327), and the threaded sleeve flange seat (3283) and the clamping shaft seat (327) are fixedly connected by flange seat bolts (3289); the quick pull channel (3228) of the workpiece clamping shaft (322) is equipped with a quick pull trapezoidal long piece (3287), the quick pull trapezoidal long piece (3287) is movably connected to the threaded shaft (3281), and a connecting bolt pin (3288) is inserted in the threaded shaft (3281) and the quick pull trapezoidal long piece (3287).

[0150] exist Figure 17 , Figure 19 , Figure 23In this configuration, the quick-draw trapezoidal long piece (3287) and trapezoidal seat piece (3285) are located on the right side of the workpiece seat hole (3226). When the quick-draw trapezoidal long piece (3287) moves downward, due to the trapezoidal action of the quick-draw trapezoidal long piece (3287) and trapezoidal seat piece (3285), the quick-draw trapezoidal long piece (3287) gradually shifts to the left, generating a leftward squeezing force. Therefore, when a blade workpiece (34) is installed in the workpiece seat hole (3226), rotating the screw sleeve (3284) of the quick-clamping device (328) causes the quick-draw trapezoidal long piece (3287) to move downward, generating a leftward squeezing force. The leftward squeezing force of the quick-pull trapezoidal long piece (3287) will squeeze the blade workpiece (34) in the workpiece seat hole (3226), thereby tightening and fixing the blade workpiece (34) in the workpiece seat hole (3226). The outstanding feature of this technical solution is that it replaces the tedious work of removing the insulating sleeve (321) and using a wrench to remove the bolts to replace the blade workpiece (34) and then clamping it again, which is required by the prior art. It has the advanced effect of convenient and quick replacement of the blade workpiece (34) and achieves the purpose of improving the blade processing speed and processing efficiency.

[0151] exist Figure 25 In the present invention, the spindle slide assembly (33) includes a vertical seat (331), a terminal block (332), a positioning release button (333), a handle (334), a main slide (335), a connecting hole (336), an insulating partition (337), and a right-angle connecting plate (338); characterized in that: a positioning release button (333) is provided on the handle (334), the positioning release button (333) is used to turn on or off the power supply of the coil (3136) of the spindle machining reference rapid positioning device A (313) and the spindle machining reference rapid positioning device B (314), thereby controlling the positioning release and reset of the spindle slide assembly (33).

[0152] exist 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 side root branch mold groove Z (373), a root branch groove mold protrusion Z (374), an inner root branch mold groove Z (375), an obtuse angle side root branch groove mold protrusion Z (376), an obtuse angle side root branch mold groove Z (377), a blade seat flash edge B mold groove Z (378), a blade direction synchronous cone shaft mold hole Z (379), a workpiece groove Z (3710), and a left mold mounting buckle (3711); the left mold mounting buckle (3711) is located at the left end of the left mold body (371) and is used to connect with the left feed shaft (36).

[0153] exist Figure 27In the middle, the right mold electrode (39) includes a right mold body (391), a blade seat mold groove Y (392), an acute angle side root branch mold groove Y (393), a root branch groove mold protrusion Y (394), an inner root branch mold groove Y (395), an obtuse angle side root branch groove mold protrusion Y (396), an obtuse angle side root branch mold groove Y (397), a blade seat flash edge B mold groove Y (398), a blade direction synchronous cone shaft mold hole Y (399), a workpiece groove Y (3910), and a right mold mounting buckle (3911); the right mold mounting buckle (3911) is located at the right end of the right mold body (391) and is used to connect with the right feed shaft (311).

[0154] exist Figure 6 , Figure 9 , Figure 26 In the middle, the left mold electrode (37) is installed at the right end of the left feed shaft (36). The electrical connection of the left mold electrode (37) is as follows: the left mold electrode (37) is connected to the left feed shaft (36), the left feed shaft (36) is connected to the electrolytic machining system frame (31), and the electrolytic machining system frame (31) is connected to the electrolytic power supply (13).

[0155] exist Figure 6 , Figure 9 , Figure 27 In the middle, the right mold electrode (39) is installed at the left end of the right feed shaft (311). The electrical connection of the right mold electrode (39) is as follows: the right mold electrode (37) is connected to the right feed shaft (311), the right feed shaft (311) is connected to the electrolytic machining system frame (31), and the electrolytic machining system frame (31) is connected to the electrolytic power supply (13).

[0156] exist Figure 28 Figure 24 In the circuit, the coil control circuit includes DC, SB1, SB2, C1, LED, R1, YA1, and YA2, where YA1 and YA2 represent coils (3136); used to control the coils (3136) of the spindle machining reference rapid positioning device A and the spindle machining reference rapid positioning device B; DC is a 12-36V DC power supply, input from the control power supply (14); SB1 is a normally open push-button switch for high current, SB2 is a normally closed push-button switch for high current, and C1 is an electrolytic capacitor. The LED is an indicator light (3137), R1 is a resistor, and YA1 and YA2 are coils (3136). During normal operation, pressing SB1 energizes C1 to power YA1 and YA2, i.e., the coil (3136). After the coil (3136) is energized, the electric iron core (3135) generates a magnetic attraction force, and the LED lights up. Pressing SB2 cuts off the power supply to YA1, YA2, C1, and the LED, causing YA1 and YA2 to lose power and the LED to turn off. After YA1 and YA2 lose power, the electromagnetic attraction force disappears.

Claims

1. An aircraft engine blade, comprising a blade root (341), a blade body (344), and a blade crown (345); characterized in that: The leaf root (341) includes root branch grooves (3412) and inner root branches (3413); the leaf root (341) is provided with multiple root branch grooves (3412) and multiple inner root branches (3413), and the multiple root branch grooves (3412) and multiple inner root branches (3413) are distributed alternately to make the leaf root (341) form a void body; The width ratio of the root branch groove (3412) to the inner root branch (3413) is 1-1.5 to 1-1.5; The root and branch groove (3412) is set in the upper and lower halves of the leaf root (341); the root and branch groove (3412) of the upper half and the root and branch groove (3412) of the lower half are not on the same straight line; the root and branch groove (3412) of the upper half and the root and branch groove (3412) of the lower half are staggered and arranged in parallel; the bottom of the root and branch groove (3412) of the upper half and the bottom of the root and branch groove (3412) of the lower half have a certain wall thickness distance, and the distance wall thickness dimension is greater than or equal to 0.5 times the wall thickness width dimension of the inner root branch (3413).

2. An aircraft engine blade according to claim 1, characterized in that: DX is the total width of the leaf root; d1 is the width of the root branch with acute angles, and the ratio of DX to d1 is 1:8-12; d2 is the width of the root branch groove, and the ratio of DX to d2 is 1:10-14; d3 is the width of the inner root branch, and the ratio of DX to d3 is 1:10-14; d4 is the width of the root branch with obtuse angles, and the ratio of DX to d4 is 1:18-22; d5 is the width of the root branch groove with obtuse angles, and the ratio of DX to d5 is 1:18-22; DY is the maximum parallel distance between the two oblique transverse parallel corrugated surfaces; dy1 is the distance between the centers of the bottom circles of the root branch grooves on both sides, and the ratio of dy1 to DY is 2-2.5:1; dy2 is the depth of the root branch groove, and the ratio of dy2 to DY is 6-6.5:1; DA is the acute angle of the leaf root, and the angle of DA is 65-75 degrees.

3. A precision electrolytic manufacturing apparatus for producing aircraft engine blades as described in claim 1, comprising a machine tool housing (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), machine feet (10), a frame (11), a left panel (12), an electrolytic power supply (13), and a control power supply (14); characterized in that: The precision electrolytic machining system (3) includes an electrolytic machining system frame (31), a spindle quick clamping system (32), a spindle slide assembly (33), a blade workpiece (34), a left axis drive device (35), a left feed axis (36), a left mold electrode (37), an electrolytic reaction chamber (38), a right mold electrode (39), a cathode wiring bridge assembly (310), a right feed axis (311), a right axis drive device (312), a spindle machining reference quick positioning device A (313), and a spindle machining reference quick positioning device B (314). An electrolytic reaction box (38) is installed in the middle of the frame (31) of the electrolytic machining system. A spindle slide assembly (33) is installed on the front opposite of the electrolytic reaction box (38). A spindle machining reference rapid positioning device A (313) and a spindle machining reference rapid positioning device B (314) are respectively installed on both sides between the spindle slide assembly (33) and the electrolytic reaction box (38). The spindle machining reference rapid positioning device A (313) includes a trapezoidal column (3131), a push-off spring (3132), a limit top (3133), a coil slot (3134), an electric core (3135), a coil (3136), an indicator light (3137), and a positioning button (3138).

4. The precision electrolytic manufacturing apparatus according to claim 3, characterized in that: The trapezoidal column (3131) has a rectangular base, a square top, and a square upper-middle section. The upper-middle section and the square top section are equal in size, forming a cuboid. The bottom of the cuboid and the bottom length of the trapezoidal column (3131) together form a trapezoidal column that is smaller at the top and larger at the bottom. A coil groove (3134) is provided in the square section of the trapezoidal column (3131), and a coil (3136) is installed 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 for magnetically locating the spindle slide assembly (33). A push-off spring (3132) and a limit top (3133) are installed on the front wall of the trapezoidal column (3131) below the coil (3136).

5. The precision electrolytic manufacturing apparatus according to claim 3, characterized in that: The limiting top (3133) is used to precisely define the position of the spindle slide assembly (33). The limiting top (3133) is a protruding post with wear-resistant material on its surface. The push-away spring (3132) is a compression spring used to spring the spindle slide assembly (33) back to the non-processing position after the machining is completed. An indicator light (3137) is installed on the top of the trapezoidal column (3131). The indicator light (3137) is used to indicate the status of the spindle slide assembly (33) during machining and positioning. When the spindle slide assembly (33) is positioned and machining, the indicator light (3137) is lit. When the spindle slide assembly (33) is in the non-processing position, the indicator light (3137) is not lit.

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