An aerofoil blade machining apparatus with floating support

Abstract

The present application relates to the field of aero-engine blade machining, and specifically relates to an aero-engine blade machining device with floating supports, comprising a support base, a plurality of special-shaped floating support assemblies and two hinge pressing assemblies, the special-shaped floating support assembly comprising an adjusting structure, a support block body, a pressing plate, a first spring, a special-shaped block, a rotating pin and an adjusting screw, the base supports the support body, the support body is used for mounting other components, the support block body is fixed on the adjusting structure, the rotating pin and the special-shaped block are arranged on the support block body, the special-shaped block is in contact with the blade, the position of the special-shaped block is adjusted through the rotating pin, the pressing plate is fixed on the support body through the adjusting screw and is used for supporting the first spring, the support block body is elastically supported by the first spring, the special-shaped block is better attached to the blade, the position of the special-shaped block is more conveniently adjusted through the adjusting structure, the device is suitable for fixing different blades, better supports the blades and improves machining precision.

Description

Technical Field

[0001] This invention relates to the field of aerospace component machining, and more particularly to an aerospace blade machining device with floating support. Background Technology

[0002] Aircraft blades are one of the core components of aero engines. Engines rely on numerous blades to compress and expand gases to generate powerful thrust, propelling the aircraft forward. According to the aerodynamic characteristics of blades, their surface shape and manufacturing precision directly determine the engine's propulsion efficiency. However, due to the thin walls, large blade twist, complex profiles, wide size range, numerous dimensions, and strict tolerance requirements of blade components, deformation and vibration are easily generated during machining, severely affecting the blade's machining accuracy and surface quality. As major aircraft manufacturers demand increasingly higher machining accuracy for blades, and with the large quantity and variety of blades, strictly controlling machining errors and ensuring good surface accuracy has become a constant pursuit for manufacturers. Advanced technology lies in the improvement and innovation of blade machining methods, thereby enhancing blade machining levels and efficiency.

[0003] Existing clamping methods have low support strength and generate large torques, leading to blade deformation. Summary of the Invention

[0004] The purpose of this invention is to provide an aircraft blade processing device with floating support, which aims to enable more stable fixed processing of blades.

[0005] To achieve the above objectives, the present invention provides an aircraft blade processing device with floating supports, comprising a support base, multiple irregularly shaped floating support assemblies, and two hinge clamping assemblies. The support base includes a base and a support body, the support body being fixedly connected to the base and located on top of the base. Each irregularly shaped floating support assembly includes an adjustment structure, a support block body, a pressure plate, a first spring, an irregularly shaped block, a rotating pin, and an adjustment screw. The adjustment structure is slidably mounted on the support body. The support block body has a cavity and is mounted on the adjustment structure. The pressure plate is fixed to the support body by the adjustment screw and closes the cavity. A first spring is disposed within the cavity. Multiple irregularly shaped floating support assemblies are sequentially disposed on the support body. Two hinge clamping assemblies are disposed on the upper and lower sides of the support body. The rotating pin is rotatably connected to the support block body and is located on the side of the support block body away from the pressure plate. The irregularly shaped block is fixedly connected to the rotating pin and is located on one side of the support block body.

[0006] The base has multiple mounting holes distributed on the base.

[0007] The adjustment structure includes a first screw, a first slider, a second screw, and a second slider. The first screw is rotatably connected to the support body and is located on one side of the support body. The first slider is slidably connected to the support body and threadedly connected to the first screw. The second screw is rotatably connected to the first slider. The second slider is slidably connected to the first slider and threadedly connected to the second screw. The support block body is mounted on the second slider.

[0008] The hinge clamping assembly includes a hinge support, a movable pressure plate, a hinge nut, a clamping block, and a support column. The hinge support is fixed to the support body. The movable pressure plate is rotatably connected to the hinge support and is located on one side of the hinge support. The clamping block is disposed on the sliding pressure plate. The support column is fixed to the support body and is located at the end of the movable pressure plate away from the hinge support. The hinge nut is threaded onto the support column.

[0009] The clamping block includes a clamping block body and a fixing pin. The fixing pin is rotatably connected to the sliding pressure plate and passes through the movable pressure plate. The clamping block body is fixedly connected to the fixing pin and is located on one side of the fixing pin.

[0010] The aircraft blade processing device with floating support also includes a hinge opener / closer, which is located on one side of the hinge nut.

[0011] The aircraft blade processing device with floating support also includes a feeding structure, which is located on one side of the support body.

[0012] This invention discloses an aircraft blade processing device with floating support. A base supports a support body, which is used to mount other components. Due to the complex curved surface of aircraft blades, multiple irregularly shaped floating support components are used for support. Specifically, the support block body is fixed to an adjustment structure. The support block body is equipped with a rotating pin and an irregularly shaped block. The irregularly shaped block contacts the blade, and its position can be adjusted by the rotating pin. A pressure plate is fixed to the support body by adjusting screws, providing support for a first spring. This allows the first spring to elastically support the support block body, resulting in better contact with the blade. The adjustment structure allows for easier adjustment of the irregularly shaped block's position, making it suitable for fixing different blades and providing better support for the blade, thus improving processing accuracy. This invention optimizes the support method, adds multiple flexible support points, disperses the torque generated during processing, improves support strength, reduces vibration, and features a flexible structure, resulting in a smoother and more precise processing process.

[0013] This invention optimizes the clamping method, reduces the number of clamping operations, and enables the processing of multiple surfaces in a single clamping operation. This improves processing efficiency, ensures processing accuracy, shortens the manufacturing cycle, saves resources, and reduces production management and planning costs.

[0014] The floating support and hinge clamping mechanism designed in this invention has controllable clamping force, is simple to operate, and is easy to learn.

[0015] Based on the above three points, this invention greatly improves the processing efficiency and quality of aero-engine blades, bringing significant economic benefits to the production process. Attached Figure Description

[0016] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0017] Figure 1 This is a structural diagram of an aircraft blade processing device with floating support according to the first embodiment of the present invention.

[0018] Figure 2 This is a cross-sectional structural diagram of an aircraft blade processing device with floating support according to the first embodiment of the present invention.

[0019] Figure 3 This is a structural diagram of the hinge clamping assembly according to the first embodiment of the present invention.

[0020] Figure 4 This is a structural diagram of the irregular floating support component according to the first embodiment of the present invention.

[0021] Figure 5 This is a cross-sectional structural diagram of an aircraft blade processing device with floating support according to the second embodiment of the present invention.

[0022] Figure 6 This is a cross-sectional structural diagram of an aircraft blade processing device with floating support according to the third embodiment of the present invention.

[0023] 101-Support base, 102-Irregular floating support assembly, 103-Hinge clamping assembly, 104-Base, 105-Support body, 106-Adjustment structure, 107-Support block body, 108-Pressure plate, 109-First spring, 110-Irregular block, 111-Rotating pin, 112-Adjusting screw, 113-Mounting hole, 114-First screw, 115-First slider, 116-Second screw, 117-Second slider, 118-Hinge support, 119-Modible pressure plate, 120-Hinge nut 121-Clamping block, 122-Support column, 123-Clamping block body, 124-Fixing pin, 201-Hinge opener / closer, 202-Bracket, 203-Rotating cover, 204-Sliding rod, 205-Second spring, 206-Drive motor, 207-Transmission chain, 208-Limiting rod, 301-Feeding structure, 302-Sliding seat, 303-Moving slider, 304-Drive element, 305-Clamping device, 306-Universal ball, 307-Clamping screw, 308-Support, 309-Clamping component. Detailed Implementation

[0024] Embodiments of the present invention are described in detail below, examples of which are illustrated in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain the present invention, and should not be construed as limiting the present invention.

[0025] First Embodiment

[0026] Please see Figures 1-4 , Figure 1 This is a structural diagram of an aircraft blade processing device with floating support according to the first embodiment of the present invention. Figure 2 This is a cross-sectional structural diagram of an aircraft blade processing device with floating support according to the first embodiment of the present invention. Figure 3 This is a structural diagram of the hinge clamping assembly according to the first embodiment of the present invention. Figure 4 This is a structural diagram of the irregular floating support assembly according to the first embodiment of the present invention. The present invention provides an aerospace blade processing device with floating support:

[0027] The system includes a support base 101, multiple irregularly shaped floating support assemblies 102, and two hinge clamping assemblies 103. The support base 101 includes a base 104 and a support body 105. The support body 105 is fixedly connected to the base 104 and located on top of the base 104. Each irregularly shaped floating support assembly 102 includes an adjustment structure 106, a support block body 107, a pressure plate 108, a first spring 109, an irregularly shaped block 110, a rotating pin 111, and an adjustment screw 112. The adjustment structure 106 is slidably mounted on the support body 105. The support block body 107 has a cavity and is installed onto the... On the adjustment structure 106, the pressure plate 108 is fixed to the support body 105 by the adjustment screw 112 and the cavity is closed. A first spring 109 is provided in the cavity. Multiple irregular floating support components 102 are sequentially arranged on the support body 105. Two hinge clamping components 103 are arranged on the upper and lower sides of the support body 105. The rotating pin 111 is rotatably connected to the support block body 107 and is located on the side of the support block body 107 away from the pressure plate 108. The irregular block 110 is fixedly connected to the rotating pin 111 and is located on one side of the support block body 107.

[0028] In this embodiment, the base 104 supports the support body 105, which is used to install other components. Since the curved surface of the aircraft blade is complex, multiple irregularly shaped floating support assemblies 102 are used for support. Specifically, the support block body 107 is fixed to the adjustment structure 106. The support block body 107 is provided with a rotating pin 111 and an irregularly shaped block 110. The irregularly shaped block 110 contacts the blade, and its position can be adjusted using the rotating pin 111. The pressure plate 108 is fixed to the support body 105 by the adjusting screw 112, providing support for the first spring 109. This allows the first spring 109 to elastically support the support block body 107, enabling better contact with the blade. The adjustment structure 106 allows for easier adjustment of the position of the irregularly shaped block 110, making it suitable for fixing different blades and providing better support for the blade, thus improving machining accuracy.

[0029] The base 104 has multiple mounting holes 113 distributed on it. The base 104 is ultimately fixed to the machine tool via these mounting holes 113, allowing it to swing freely up and down, thus enabling the machining of multiple surfaces of the blade.

[0030] Secondly, the adjustment structure 106 includes a first screw 114, a first slider 115, a second screw 116, and a second slider 117. The first screw 114 is rotatably connected to the support body 105 and is located on one side of the support body 105. The first slider 115 is slidably connected to the support body 105 and threadedly connected to the first screw 114. The second screw 116 is rotatably connected to the first slider 115. The second slider 117 is slidably connected to the first slider 115 and threadedly connected to the second screw 116. The support block body 107 is mounted on the second slider 117. By rotating the first screw 114, the first slider 115 can be moved left and right. By rotating the second screw 116, the second slider 117 can be moved up and down, thereby allowing the position of the irregular block 110 to be adjusted in all directions, making it more convenient to use.

[0031] Secondly, the hinge clamping assembly 103 includes a hinge support 118, a movable pressure plate 119108, a hinge nut 120, a clamping block 121, and a support column 122. The hinge support 118 is fixed to the support body 105. The movable pressure plate 119108 is rotatably connected to the hinge support 118 and is located on one side of the hinge support 118. The clamping block 121 is disposed on the movable pressure plate 108. The support column 122 is fixed to the support body 105 and is located at the end of the movable pressure plate 119108 away from the hinge support 118. The hinge nut 120 is threaded onto the support column 122. By unscrewing the hinge nut 120, the movable pressure plate 108 can be rotated to open a certain space, allowing the aircraft blade to be inserted. Then, by rotating the movable pressure plate 108 and tightening the nut again, the clamping block 121 can clamp and fix the blade.

[0032] Finally, the clamping block 121 includes a clamping block body 123 and a fixing pin 124. The fixing pin 124 is rotatably connected to the sliding pressure plate 108 and passes through the movable pressure plate 119108. The clamping block body 123 is fixedly connected to the fixing pin 124 and is located on one side of the fixing pin 124. The clamping block body 123 can rotate under the action of the fixing pin 124, thereby allowing for flexible adjustment of its position to better fix the blades.

[0033] The overall working principle is:

[0034] Open the hinge nut 120 and hinge pressure plate 108, place the aero-engine blade into the device to fit against the floating irregular support plate, adjust the first screw 114 and the second screw 116 to make the blade's irregular surface tightly adhere to the support plate's profile, then press the hinge pressure plate 108 to tighten the blade, adjusting the clamping force to ensure that the profile support block and profile clamping block 121 always adhere to the blade profile. This minimizes profile deformation during blade machining. Multiple support and clamping mechanisms help to firmly fix blades with large size spans and reduce torque during blade machining, thereby reducing blade profile deformation and vibration. This results in blades with precise dimensions and shapes.

[0035] Second Embodiment

[0036] Please see Figure 5 , Figure 5 This is a cross-sectional structural diagram of an aircraft blade processing device with floating support according to a second embodiment of the present invention. The present invention also provides an aircraft blade processing device with floating support, which further includes a hinge opening / closing device 201, which is disposed on one side of the hinge nut 120. The hinge opener / closer 201 includes a bracket 202, two rotating covers 203, two sliding rods 204, two second springs 205, a drive motor 206, a transmission chain 207, and two limiting rods 208. The drive motor 206 is fixedly connected to the support body 105 and is located on one side of the support body 105. The bracket 202 is fixed to one side of the drive motor 206. The two rotating covers 203 are rotatably connected to the bracket 202 and are set corresponding to the hinge nut 120. The transmission chain 207 is connected to the output shaft of the drive motor 206 and is connected to the two rotating covers 203. The two sliding rods 204 are slidably connected to the two rotating covers 203 and are located on the side of the rotating covers 203 near the hinge nut 120. The sliding rods 204 have grooves that match the hinge nut 120. The second springs 205 are disposed between the sliding rods 204 and the rotating covers 203. The two limiting rods 208 are rotatably connected to the sliding rod 204 and are located on one side of the movable pressure plate 119108.

[0037] In this embodiment, the hinge opening / closing device 201 can automatically move the position of the hinge pressure plate 108, making it more convenient to use. Specifically, starting the drive motor 206 can drive the transmission chain 207 to rotate, which in turn drives the two rotating covers 203 to rotate, thereby driving the two sliding rods 204 to rotate. The grooves of the sliding rods 204 contact the hinge nut 120 to unscrew the hinge nut 120. While unscrewing, the sliding rods 204 slide backward relative to the rotating covers 203, and the limiting rod 208 drives the hinge pressure plate 108, making it more convenient to use. The second spring 205 can keep the hinge nut 120 in contact with the support column 122, making it easy to fix after the blade is installed.

[0038] Third Embodiment

[0039] Please see Figure 6 , Figure 6 This is a cross-sectional view of an aircraft blade processing device with floating support according to a third embodiment of the present invention. The present invention also provides an aircraft blade processing device with floating support, which further includes a loading structure 301 disposed on one side of the support body 105. The loading structure 301 includes a sliding seat 302, a movable slider 303, a driving element 304, and a clamp 305. The sliding seat 302 is disposed on one side of the base 104, the movable slider 303 is slidably connected to the sliding seat 302 and located on one side of the sliding seat 302, the driving element 304 is disposed on one side of the movable slider 303, and the clamp 305 is disposed on the movable slider 303. The movable slider 303 can slide on the sliding seat 302, so the movable slider 303 can be moved by the driving element 304. Then, the blade to be processed is initially clamped by the clamp 305 and moved to the position of the base 104. The hinge pressure plate 108 is opened, and then the blade can be put in. In order to perform the necessary actions, the driving element 304 includes two types: horizontal movement mechanism and vertical movement mechanism.

[0040] The clamp 305 includes a ball joint 306, a clamping screw 307, a support 308, and a clamping member 309. The support 308 is fixed to the movable slider 303. The ball joint 306 is disposed in the groove of the support 308. The clamping screw 307 is threadedly connected to the support 308 and contacts the ball joint 306. The clamping member 309 is fixedly connected to the ball joint 306. Because the blade has a complex shape, direct placement may be difficult due to the angle. Therefore, the ball joint 306 allows for adjustment of the position of the clamping member 309, and the clamping screw 307 fixes the position of the ball joint 306, making placement easier.

[0041] The above description discloses only one preferred embodiment of the present invention, and should not be construed as limiting the scope of the present invention. Those skilled in the art will understand that all or part of the processes of the above embodiments can be implemented, and equivalent changes made in accordance with the claims of the present invention are still within the scope of the invention.

Claims

1. An aircraft blade processing device with floating support, characterized in that, The system includes a support base, multiple irregularly shaped floating support assemblies, and two hinge clamping assemblies. The support base comprises a base and a support body, with the support body fixedly connected to the base and located on top of the base. Each irregularly shaped floating support assembly includes an adjustment structure, a support block body, a pressure plate, a first spring, an irregularly shaped block, a rotating pin, and an adjustment screw. The adjustment structure is slidably mounted on the support body. The support block body has a cavity and is mounted on the adjustment structure. The pressure plate is fixed to the support body by the adjustment screw and seals the cavity. A [missing information - likely a component or element] is disposed within the cavity. A first spring, multiple irregularly shaped floating support components are sequentially arranged on the support body, two hinge clamping components are arranged on the upper and lower sides of the support body, a rotating pin is rotatably connected to the support block body and located on the side of the support block body away from the pressure plate, and an irregularly shaped block is fixedly connected to the rotating pin and located on one side of the support block body; the hinge clamping component includes a hinge support, a movable pressure plate, a hinge nut, a clamping block, and a support column, the hinge support is fixed on the support body, and the movable pressure plate is rotatably connected to the hinge support and located on the hinge support. On one side, the clamping block is disposed on the movable pressure plate, the support column is fixed on the support body and located at the end of the movable pressure plate away from the hinge support, the hinge nut is threaded onto the support column, and the aircraft blade processing device with floating support also includes a hinge opener / closer, the hinge opener / closer is disposed on one side of the hinge nut; the hinge opener / closer includes a bracket, two rotating covers, two sliding rods, two second springs, a drive motor, a transmission chain and two limit rods, the drive motor is fixedly connected to the support body and is located on one side of the support body, The bracket is fixed to one side of the drive motor. The two rotating covers are rotatably connected to the bracket and are positioned corresponding to the hinge nuts. The transmission chain is connected to the output shaft of the drive motor and to the two rotating covers. The two sliding rods are slidably connected to the two rotating covers and are located on the side of the rotating covers near the hinge nuts. The sliding rods have grooves that match the hinge nuts. The second spring is positioned between the sliding rods and the rotating covers. The two limiting rods are rotatably connected to the sliding rods and are located on one side of the movable pressure plate.

2. The aircraft blade processing device with floating support as described in claim 1, characterized in that, The base has multiple mounting holes distributed on the base.

3. The aircraft blade processing device with floating support as described in claim 2, characterized in that, The adjustment structure includes a first screw, a first slider, a second screw, and a second slider. The first screw is rotatably connected to the support body and is located on one side of the support body. The first slider is slidably connected to the support body and threadedly connected to the first screw. The second screw is rotatably connected to the first slider. The second slider is slidably connected to the first slider and threadedly connected to the second screw. The support block body is mounted on the second slider.

4. The aircraft blade processing device with floating support as described in claim 3, characterized in that, The clamping block includes a clamping block body and a fixing pin. The fixing pin is rotatably connected to the movable pressure plate and passes through the movable pressure plate. The clamping block body is fixedly connected to the fixing pin and is located on one side of the fixing pin.

5. The aircraft blade processing device with floating support as described in claim 4, characterized in that, The aircraft blade processing device with floating support also includes a feeding structure, which is disposed on one side of the support body.

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