A real-time measuring device and grinding device for high-speed aircraft engine rotor blade tips

Abstract

The present invention relates to a real-time measurement device for high-speed aircraft engine rotor blade tip grinding, and relates to patented aircraft engine blade tip grinding technology. The device comprises a second track and two measuring mechanisms mounted to the second track; the measuring mechanisms comprise a base body slidably connected to the second track; an infrared emitter and an infrared sensor for receiving infrared signals emitted by the first infrared emitter, both sides of the two base bodies facing each other being mounted; a main grating scale arranged along the length of the second track, and two grating scale reading heads slidably connected to the main grating scale, the two grating scale reading heads corresponding to and connected to the two base bodies, respectively; and an adjustment mechanism for driving the base bodies to reciprocate along the second track. This application has the advantage of improving the production efficiency of aircraft rotor blades.

Description

Technical Field

[0001] The present application relates to a patented blade tip grinding technology for aircraft engines, and in particular to a real-time measuring device and a grinding device for high-speed aircraft engine rotor blade tips. Background Art

[0002] Aircraft engine rotors are one of the most important components in aircraft engines. During the rotor machining process, after the main rotor body is machined, the blade tips need to be polished. During this polishing process, workers are required to measure the rotor diameter. However, conventional techniques typically use manual labor, resulting in low rotor production efficiency. Summary of the Invention

[0003] The purpose of this application is to provide a high-speed aircraft engine rotor tip real-time measurement device and grinding device for improving the production efficiency of aircraft rotor blades.

[0004] In the first aspect, the present application provides a high-speed aircraft engine rotor tip real-time measurement device for improving the production efficiency of aircraft rotor blades, which adopts the following technical solutions:

[0005] A high-speed aircraft engine rotor blade tip grinding real-time measurement device comprises a track 2, two sets of measurement mechanisms and a displacement measurement mechanism mounted on the track 2;

[0006] The measuring mechanism includes a base body slidably connected to the track 2; an infrared emitter 1 and an infrared sensor 1 for receiving infrared signals emitted by the infrared emitter 1 are installed on the sides of the two base bodies facing each other;

[0007] The displacement measuring mechanism comprises a grating scale main scale arranged along the second longitudinal direction of the track, and two grating scale reading heads slidably connected to the grating scale main scale, wherein the two grating scale reading heads are respectively connected to the two base bodies in a one-to-one correspondence;

[0008] The seat body is provided with an adjusting mechanism for driving the seat body to perform reciprocating motion along the second track.

[0009] By adopting the above technical solution, during the polishing process of the aircraft rotor, infrared emitter 1 continuously emits infrared rays to infrared sensor 1. The power element on the base body drives the base body to move in the direction of the aircraft rotor. When the infrared rays emitted by infrared emitter 1 are blocked by the aircraft rotor, infrared sensor 1 senses the change in the infrared signal and feeds it back to the control system. The control system records and determines the position and displacement of the grating scale reading heads corresponding to the two base bodies on the grating scale main scale, then controls the base body to stop or reset. The system then calculates the size of the aircraft rotor using a formula. This allows for efficient and convenient real-time measurement of aircraft rotor size.

[0010] Optionally, the straight line where the infrared emitter 1 and the infrared sensor 1 on the same base are located is in a vertical state.

[0011] By adopting the above technical solution, compared to the horizontal arrangement of the straight line containing infrared emitter 1 and infrared sensor 1 (in this case, the distance between infrared emitter 1 and infrared sensor 1 must be greater than the length of the aircraft rotor, which occupies a large space), the straight line containing infrared emitter 1 and infrared sensor 1 is vertical (the distance between infrared emitter 1 and infrared sensor 1 only needs to be greater than the diameter of the aircraft rotor, which can minimize the space occupied by the real-time measurement device).

[0012] Optionally, the seat body is provided with two slideways 1, and the slideway 1 is slidably connected with a support;

[0013] The infrared emitter 1 and the infrared sensor 1 are respectively mounted on the two supports;

[0014] The seat body is provided with a driving mechanism for driving the two supports to move closer to or away from each other.

[0015] By adopting the above technical solution, the distance between infrared emitter 1 and infrared sensor 1 can be adjusted, thereby adapting to aircraft engine rotors with as many diameters as possible.

[0016] Optionally, the driving mechanism includes a bidirectional motor and two screws;

[0017] The two screw rods 2 are respectively threadedly connected to the two supports, and the rotation directions of the two screw rods 2 are opposite, and the two screw rods 2 are respectively connected to the two output shafts of the bidirectional motor.

[0018] By adopting the above technical solution, the bidirectional motor can synchronously drive the two screws to rotate, thereby achieving the two supports to move closer to or farther away from each other.

[0019] Optionally, a second elastic member is provided between the support and the seat body;

[0020] A connecting assembly is provided between the output shaft and the second screw;

[0021] The connection assembly includes component one, component two and an intermediate piece;

[0022] The first component and the second component are both tubular structures with polygonal cross sections; the middle piece is a rod-shaped structure adapted to the first component and the second component;

[0023] The component is connected to the second screw rod, and the second component is connected to the output shaft of the bidirectional motor;

[0024] The two ends of the middle piece are respectively slidably connected to the first component and the second component;

[0025] The intermediate component is fixed with an elastic component 1, and the elastic component 1 is connected to the component 2 or the output shaft of the driving mechanism;

[0026] Under the action of the elastic member 1, the intermediate member extends into the member 1.

[0027] By adopting the above technical solution, the disassembly and installation of the bidirectional motor is facilitated.

[0028] Optionally, a fixing seat is provided on one side of the middle piece, and the fixing seat is fixedly connected to the bidirectional motor;

[0029] A slideway 2 is vertically provided on the fixed seat, a connecting piece is slidably connected inside the slideway 2, a ring-shaped slideway 3 is fixed to the connecting piece and is sleeved on the outer periphery of the output shaft of the bidirectional motor, a toggle piece is slidably connected inside the slideway 3, and the toggle piece is fixed to the middle piece.

[0030] By adopting the above technical solution, it is convenient for people to remove the middle piece from component one, thereby making it convenient for people to disassemble and assemble the bidirectional motor.

[0031] Optionally, an adjustment rope is fixedly connected between the two slideways three on the same seat body.

[0032] By adopting the above technical solution, the two middle pieces can be retracted into the second component synchronously through the adjustment rope, thereby making it more convenient for people to disassemble and assemble the bidirectional motor.

[0033] Optionally, a distance measurement component is further included, the distance measurement component including a second infrared emitter and a second infrared sensor for receiving the infrared signal emitted by the second infrared emitter, the second infrared emitter and the second infrared sensor are respectively located on the top of the upper supports of the two bases;

[0034] When the second infrared sensor does not sense the infrared signal emitted by the second infrared transmitter, the bidirectional motor starts the two supports to move away from each other;

[0035] When the second infrared sensor senses the infrared signal emitted by the second infrared transmitter, the bidirectional motor stops working.

[0036] By adopting the above technical solution, the second infrared emitter and the second infrared sensor can sense whether the spacing between two supports on the same base body can adapt to the diameter of the aircraft rotor. The signal can be transmitted to the control system to achieve adaptive adjustment of the two supports to the diameter of the aircraft rotor.

[0037] In summary, this application includes at least one of the following beneficial technical effects:

[0038] 1. By setting up a real-time measuring device on the tooling table, the real-time measuring device can replace manual real-time measurement of the diameter of the aviation rotor, greatly improving the measurement efficiency of the aviation rotor and improving the grinding efficiency of the aviation rotor;

[0039] 2. By arranging the second infrared emitter and the second infrared sensor in the real-time measuring device, the real-time measuring device can be adjusted in real time according to the diameter of the aviation rotor, thereby improving the grinding efficiency of the aviation rotor. BRIEF DESCRIPTION OF THE DRAWINGS

[0040] Figure 1 It is a schematic diagram of the external structure of the grinding device in this application.

[0041] Figure 2 Schematic diagram of the external structure of the supporting mechanism in the embodiment of the present application;

[0042] Figure 3 This is a schematic diagram of the appearance structure of the real-time measurement device in an embodiment of the present application;

[0043] Figure 4 is a schematic diagram of the connection structure between the bidirectional motor and the support in an embodiment of the present application;

[0044] Figure 5 is a cross-sectional view of the connection structure between the bidirectional motor and the support in an embodiment of the present application;

[0045] Figure 6 It is a structural diagram of the real-time measurement device in this application.

[0046] In the figure, 1. tooling table; 11. length direction; 12. width direction; 13. arrangement slot; 2. bearing mechanism; 21. main seat; 212. driving member; 22. support seat; 221. sub-seat; 2211. clamping plate; 23. track mechanism; 231. track 1; 232. power assembly; 2321. motor 1; 2322. screw 1; 3. grinding mechanism; 31. base; 311. horizontal part; 3111. guide hole; 312. vertical part; 32. lifting assembly; 321. lifting seat; 3211. guide member; 322. lifting member; 33. grinding assembly; 331. grinding member; 332. motor 2; 4. control system; 5. track 2; 51. steel; 6. displacement measuring mechanism; 61. grating ruler main scale; 6 2. Grating scale reading head; 7. Measuring mechanism; 71. Base; 711. Slideway 1; 7111. Elastic part 2; 712. Support; 72. Measuring assembly; 721. Infrared emitter 1; 722. Infrared sensor 1; 8. Adjusting mechanism; 81. Power part; 811. Connecting gear; 82. Rack; 9. Driving mechanism; 91. Bidirectional motor; 92. Screw 2; 93. Connecting assembly; 931. Component 1; 932. Component 2; 933. Intermediate part; 9331. Toggle part; 94. Fixed seat; 941. Slideway 2; 942. Perforation; 95. Connecting part; 96. Slideway 3; 97. Elastic part 1; 98. Adjusting rope; 10. Spacing measuring assembly; 101. Infrared emitter 2; 102. Infrared sensor 2. DETAILED DESCRIPTION

[0047] The following is combined with Figure 1 -Attached Figure 6 , further details of this application are given.

[0048] A high-speed aircraft engine rotor grinding device comprises a tooling table 1 having a length direction 11 and a width direction 12. The tooling table 1 is provided with a carrying mechanism 2, a grinding mechanism 3 and a control system 4.

[0049] Reference Figure 2 The carrying mechanism 2 includes a main seat 21, a support seat 22 and a track mechanism 23.

[0050] Reference Figure 1 and Figure 2 The track mechanism 23 is disposed between the main base 21 and the workbench 1 and comprises a track 1 231 and a power assembly 232. Track 1 231 is affixed to the workbench 1 along its length 11 and has a T-shaped cross-section. A slide groove is provided on the main base 21, through which track 1 231 is slidably connected to the main base 21.

[0051] The power assembly 232 includes a motor 2321 and a screw 2322. The screw 2322 is inserted into the main seat 21 along the length direction of the track 231, and the screw 2322 and the main seat 21 are threadedly connected. The motor 2321 is fixed to the workbench 1. The motor 2321 is used to drive the screw 2322 to rotate, thereby realizing the reciprocating motion of the main seat 21 on the track 231.

[0052] The support base 22 is mounted to the main base 21. A clamping plate 2211 for fixing the aircraft rotor is rotatably connected to the support base 22. A driving member 212 for rotating the clamping plate 2211 is mounted on the main base 21. The driving member 212 is generally a motor.

[0053] Specifically, the support base 22 includes two sub-bases 221 fixed to the main base 21, and two clamping plates 2211 are provided. The two clamping plates 2211 are fixed to the two sub-bases 221 respectively, and the two clamping plates 2211 are arranged opposite to each other. The driving member 212 is connected to one of the two clamping plates 2211.

[0054] Reference Figure 1 The grinding mechanism 3 includes a base 31, a lifting assembly 32 and a grinding assembly 33. The base 31 includes a horizontal portion 311 and two vertical portions 312, which together form a "U"-shaped structure with an opening facing downward.

[0055] The lifting assembly 32 is disposed directly below the horizontal portion 311. The lifting assembly 32 includes a lifting seat 321 and a lifting member 322. The lifting member 322 is used to drive the lifting seat 321 to move up and down.

[0056] The lifting member 322 is a hydraulic cylinder. The lifting member 322 is vertically fixed between the lifting seat 321 and the horizontal portion 311 , and a piston rod of the lifting member 322 is connected to the lifting seat 321 downward.

[0057] To ensure that the lifting base 321 remains vertical during the lifting process and to minimize damage to the lifting member 322 caused by lateral deviation of the lifting base 321 due to uneven load, a guide member 3211 is fixed to the lifting base 321. A guide hole 3111 is defined in the horizontal portion 311. The guide member 3211 passes through the guide hole 3111, and a sliding connection is formed between the guide member 3211 and the horizontal portion 311.

[0058] The grinding assembly 33 is mounted on the lifting base 321. The grinding assembly 33 includes a grinding member 331 and a second motor 332. The grinding member 331 is typically a grinding wheel and is rotatably connected to the lower surface of the lifting base 321. The second motor 332 is mounted on the lifting base 321 and is used to drive the grinding member 331 to rotate.

[0059] During the rotor grinding process, the assembly personnel attach each end of the rotor to the two clamping plates 2211 on the two sub-bases 221. The drive member 212 then rotates the rotor. The grinding member 331 gradually approaches the rotor and begins grinding. During the grinding process, the track mechanism 23 drives the main base 21 to slide, allowing the grinding member 331 to grind different locations on the rotor.

[0060] A real-time measurement device for high-speed aero-engine rotor blade tip grinding, referring to Figure 3 , including track 2 5, a displacement measuring mechanism 6 and two groups of measuring mechanisms 7.

[0061] Reference Figure 1 A layout groove 13 is provided on the tooling table 1, and the layout groove 13 passes directly below the track 1 231 along the width direction 12 of the tooling table 1, and the track 2 5 is fixed in the layout groove 13 along the length direction of the layout groove 13.

[0062] Reference Figure 3 The track 2 5 includes two T-shaped cross sections and two T-shaped steel sections 51 arranged parallel to each other. The steel sections 51 can be detachably fixed to the tooling table 1 by bolts or screws.

[0063] The two sets of measuring mechanisms 7 are respectively arranged on both sides of the main seat 21 .

[0064] Specifically, the measuring mechanism 7 includes a base 71 and a measuring assembly 72. The base 71 is provided with a slide groove for use with the track 2 5, and the base 71 is slidably connected to the track 2 5 through the slide groove.

[0065] The measuring assembly 72 is located on the side of the base 71 facing the main base 21. The measuring assembly 72 includes an infrared emitter 721 and an infrared sensor 722, which are mounted to the base 71. The infrared emitter 721 and the infrared sensor 722 are located on the same straight line, and the line containing the infrared emitter 721 and the infrared sensor 722 is vertical. The infrared emitter 721 can be located above or below the infrared sensor 722. In this embodiment, the infrared emitter 721 is located above the infrared sensor 722.

[0066] Reference Figure 3 An adjustment mechanism 8 is provided between the base 71 and the track 2 5 to drive the base 71 to reciprocate along the track 2 5. The adjustment mechanism 8 includes a power member 81 and a rack 82. The power member 81 is a motor, which is vertically fixed to the lower surface of the base 71. The output shaft of the power member 81 faces downward, and a connecting gear 811 is coaxially fixed to the output shaft of the power member 81. To save space for the power member 81, a mounting groove is provided on the lower surface of the base 71, and the power member 81 is fixedly mounted within the mounting groove.

[0067] A rack 82 is secured to the second track 5 along the width 12 of the slot 13 and positioned between the two T-shaped steel sections 51. The rack 82 can be removably secured to the workbench 1 using bolts or screws. A gear 811 is connected to the power member 81 and meshes with the rack 82. During operation, the power member 81 drives the seat 71 to reciprocate along the second track 5.

[0068] The displacement measuring mechanism 6 includes a grating scale main scale 61 arranged between two "T"-shaped steels along the width direction 12 of the workbench 1. Two grating scale reading heads 62 are installed on the grating scale main scale 61. The two grating scale reading heads 62 correspond one-to-one to the two base bodies 71 respectively, and the grating reading heads are fixed to the base body 71.

[0069] The main scale 61 of the grating ruler is provided with two zeroing positions, and the two base bodies 71 correspond to the two zeroing positions. During the grinding process of the aircraft rotor, infrared emitter 1 721 continuously emits infrared rays to infrared sensor 1 722. The power element 81 on the base body 71 drives the base body 71 toward the aircraft rotor.

[0070] When the infrared light emitted by infrared emitter 1 721 is blocked by the aircraft rotor, infrared sensor 1 722 senses the change in the infrared signal and feeds it back to control system 4. Control system 4 records and determines the position and displacement of the grating scale reading heads 62 on the grating scale main scale 61 corresponding to the two base bodies 71, then controls base bodies 71 to stop or reset. The system then calculates the size of the aircraft rotor using a formula. This allows for convenient real-time measurement of aircraft rotor size.

[0071] The specific formula is: X-2Y-2Z=W. X is the distance between the two zero positions, Y is the displacement of the grating readhead on the grating scale main scale 61, and Z is the distance between the intersection of the line between infrared sensor 1 and infrared sensor 1 722 and the grating scale main scale 61 and the grating readhead 62. W is the diameter of the aircraft rotor.

[0072] Reference Figure 3 Furthermore, two vertical and collinear slideways 711 are provided on the base body 71. The slideway 711 can be a channel steel with a dovetail-shaped cross section. In this embodiment, in order to save the space occupied by the slideway 711, the slideway 711 is configured as a groove body opened to the base body 71, and the cross section of the slideway 711 is dovetail-shaped.

[0073] A support 712 is slidably connected in the slideway 1 711 , and the two supports 712 on the same base 71 correspond to the infrared emitter 1 721 and the infrared sensor 1 722 respectively.

[0074] A driving mechanism 9 is provided between the two supports 712 , and the driving mechanism 9 is used to drive the two supports 712 to move closer to or away from each other.

[0075] Specifically, the driving mechanism 9 includes a bidirectional motor 91 and two screw rods 92 .

[0076] The bidirectional motor 91 is detachably fixed to the base body 71 by bolts or screws.

[0077] The two second screw rods 92 correspond to the two supports 712 one by one, respectively. The second screw rod 92 passes through the support 712 , and the second screw rod 92 and the support 712 are threadedly connected.

[0078] The two screw rods 92 correspond to the two output shafts of the bidirectional motor 91 one by one, and the screw rods 92 are coaxially connected to the output shaft of the bidirectional motor 91 . The two screw rods 92 rotate in opposite directions.

[0079] The two screw rods 92 are driven to rotate by the driving mechanism 9, so that the two supports 712 can be moved closer to or farther away from each other.

[0080] A connecting assembly 93 is provided between the output shaft of the bidirectional motor 91 and the second screw 92 for realizing a detachable connection between the output shaft and the second screw 92 .

[0081] The connecting component 93 includes component one 931 , component two 932 and an intermediate component 933 .

[0082] In this embodiment, both component one 931 and component two 932 are tubular structures with polygonal cross sections.

[0083] Component 1 931 is sleeved onto one end of screw 2 92 facing the bidirectional motor 91 , and component 1 931 and screw 2 92 are detachably connected via a threaded member, which may be a bolt or a screw.

[0084] The second component 932 is sleeved onto the output shaft of the bidirectional motor 91 , and the second component 932 and the output shaft of the bidirectional motor 91 are detachably connected via a threaded member, which may be a bolt or a screw.

[0085] The middle piece 933 is a rod-shaped structure with a polygonal cross section. The middle piece 933 is disposed between the first component 931 and the second component 932, and the two ends of the middle piece 933 are respectively slidably connected to the first component 931 and the second component 932.

[0086] Reference Figure 4 and Figure 5A fixing seat 94 is provided on one side of the intermediate member 933, and the fixing seat 94 is fixedly connected to the bidirectional motor 91. A second slideway 941 is provided on the fixing seat 94, and is arranged along the output axis of the drive mechanism 9. The second slideway 941 can be a channel steel with a dovetail cross section. In this embodiment, in order to save space occupied by the second slideway 941, the second slideway 941 is configured as a slot body opened on the fixing seat 94, and the cross section of the second slideway 941 is dovetail-shaped.

[0087] A connecting piece 95 is slidably connected in the slideway 2 941, and a circular slideway 3 96 is fixed on the connecting piece 95. The slideway 3 96 is a channel steel with a dovetail cross section, and the slideway 3 96 is sleeved to the output shaft of the bidirectional motor 91 and the periphery of the component 2 932.

[0088] A toggle member 9331 is fixedly connected to the middle member 933 . The bottom end of the toggle member 9331 is adapted to the slideway three 96 , and the bottom end of the toggle member 9331 is slidably connected to the slideway three 96 .

[0089] An elastic member 1 97 is provided in the component 2 932 . The elastic member 1 97 is located between the middle member 933 and the output shaft of the bidirectional motor 91 . Under the action of the elastic member, the middle member 933 extends into the component 1 931 .

[0090] An adjustment rope 98 is fixedly connected between the two connecting members 95 .

[0091] As the output shaft of the bidirectional motor 91 drives screw 2 92 through the intermediate piece 933, the two screws 92 rotate in opposite directions, causing the two supports 712 to move closer or further away from each other. This allows for adjustment of the distance between infrared emitter 1 721 and infrared sensor 1 722, allowing the measurement device to accommodate a wider range of rotor diameters. Furthermore, as the intermediate piece 933 rotates, the toggle member 9331 rotates within the slideway 3 96.

[0092] When removing the bidirectional motor 91 from the seat body 71, pull the adjustment rope 98, which drives the two slideways 96 to move closer to each other. The slideway 96 drives the middle piece 933 to separate from the component 1 931 through the toggle piece 9331. At this time, the bidirectional motor 91 can be removed from the seat body 71 more conveniently.

[0093] When installing the drive mechanism 9 to the base 71, the adjustment rope 98 is pulled to bring the two intermediate pieces 933 closer together, and the drive mechanism 9 is then installed between the two first components 931. The adjustment rope 98 is then loosened, and the intermediate piece 933, under the action of the elastic member, extends into the first component 931. The drive mechanism 9 is then fixed to the base 71.

[0094] The bottom of the fixing base 94 is provided with a through-hole 942, through which the adjustment rope 98 passes from the fixing base 94 toward the output shaft. The through-hole 942 guides the adjustment rope 98, ensuring a more uniform arrangement of the adjustment rope 98 on the drive mechanism 9. Furthermore, when the adjustment rope 98 is pulled, the guiding effect of the through-hole 942 ensures that the pulling force exerted by the adjustment rope 98 on the slideway 3 96 is directed vertically downward, making it easier for personnel to adjust the position of the intermediate member 933.

[0095] Reference Figure 3 A second elastic member 7111 is provided within the first slideway 711 and is fixedly connected between the support 712 and the base 71. When the drive mechanism 9 is not installed between the two supports 712, the second elastic member 7111 can position the support 712 to a certain extent, thereby preventing the support 712 from sliding to the bottom of the first slideway 711 under its own weight. When installing the drive mechanism 9, people need to manually adjust the position of the support 712 and manually maintain the position of the support 712. This makes the installation of the drive mechanism 9 between the two supports 712 more convenient.

[0096] Reference Figure 6 The real-time measurement device also includes a distance measurement assembly 10 for monitoring the distance between the two supports 712 on the base 71. This distance measurement assembly 10 includes a second infrared emitter 101 and a second infrared sensor 102. Each infrared emitter 101 and second infrared sensor 102 corresponds to each of the two sets of measuring mechanisms 7. Both the second infrared emitter 101 and second infrared sensor 102 are fixedly mounted on the top of the supports 712 within the measuring mechanism 7. The second infrared emitter 101 and second infrared sensor 102 are located in a straight line. The second infrared sensor 102 is used to receive infrared rays emitted by the second infrared emitter 101.

[0097] The second infrared transmitter 101 continuously transmits infrared signals to the second infrared sensor 102. When the second infrared sensor 102 continuously receives the infrared signals, the bidirectional motor 91 stops working. At this time, the distance between the two supports 712 is fixed.

[0098] When the aviation rotor with a larger diameter is replaced, the aviation rotor blocks the infrared signal emitted by the infrared transmitter 2 101. At this time, the infrared sensor 2 102 senses the change in the infrared signal and feeds back to the control system 4. At this time, the control system 4 controls the bidirectional motor 91 to start. The bidirectional motor 91 drives the two supports 712 away from each other, increasing the distance between the two supports 712 until the infrared sensor 2 102 can sense the infrared signal. When the infrared sensor 2 102 senses the infrared signal, it feeds back a signal to the control system 4. At this time, the bidirectional motor 91 stops working.

[0099] By disposing the spacing measurement assembly 10 , when facing aircraft rotors with different diameters, the real-time measurement device can automatically adjust the spacing between the two supports 712 , so that the real-time measurement device can better adapt to aircraft rotors with different diameters.

[0100] The implementation principle of the embodiment of the present application is as follows: the aviation rotor is installed between the two clamping plates 2211. The main seat 21 is driven to slide along the track 1 231 by the power component 232, so that the aviation rotor is adjusted to a suitable grinding position. The motor 2 332 is started, and the motor 2 332 drives the grinding member 331 to rotate. At the same time, the driving member 212 is started, so that the driving member 212 drives the aviation rotor to rotate, and the aviation rotor and the grinding member 331 are in opposite directions. The rear lifting component 32 controls the height of the grinding member 331 so that the grinding member 331 contacts the aviation rotor, thereby achieving the grinding of the aviation rotor. During the grinding process, the position of the aviation rotor can be continuously adjusted by the power component 232, thereby achieving the grinding of different positions on the aviation rotor by the grinding member 331.

[0101] During the process of the grinding member 331 grinding the aviation rotor, a real-time measuring device may be used to measure the diameter of the aviation rotor.

[0102] Specifically, infrared transmitter 2 101 continuously transmits infrared signals to infrared sensor 2 102 . When the larger diameter of the aircraft rotor blocks the infrared signal from infrared transmitter 2 101, preventing infrared sensor 2 102 from receiving the infrared signal, infrared sensor 2 102 transmits the signal to control system 4 . Control system 4 then controls bidirectional motor 91 to operate, and drive mechanism 9 drives the two supports 712 away from each other, increasing the distance between the two supports 712 to an appropriate distance. When infrared sensor 2 102 receives the airborne signal, bidirectional motor 91 stops operating. Adjustment mechanism 8 drives the two supports 71 from the zero position toward the aircraft rotor. During this process, infrared sensor 1 722 continuously receives the signal from infrared transmitter 1 721 .

[0103] When the infrared light emitted by infrared emitter 1 721 is blocked by the aircraft rotor, infrared sensor 1 722 senses the change in the infrared signal and feeds it back to control system 4. Control system 4 records and determines the position and displacement of the grating scale reading heads 62 on the grating scale main scale 61 corresponding to the two base bodies 71, then controls base bodies 71 to stop or reset. The system then calculates the size of the aircraft rotor using a formula. This allows for convenient real-time measurement of aircraft rotor size.

[0104] The examples of this specific embodiment are all preferred embodiments of this application and are not intended to limit the scope of protection of this application. Identical components are represented by the same reference numerals. Therefore, any equivalent changes made based on the structure, shape, and principle of this application should be included in the scope of protection of this application.

Claims

1. A real-time measurement device for high-speed aircraft engine rotor tip grinding, characterized in that: It comprises a track 2 (5), two sets of measuring mechanisms (7) and a displacement measuring mechanism (6) mounted on the track 2 (5); The measuring mechanism (7) comprises a base (71) slidably connected to the second track (5); an infrared emitter (721) and an infrared sensor (722) for receiving infrared signals emitted by the infrared emitter (721) are installed on the sides of the two bases (71) facing each other; The displacement measuring mechanism (6) comprises a grating scale main scale (61) arranged along the length direction of the second track (5), and two grating scale reading heads (62) slidably connected to the grating scale main scale (61), the two grating scale reading heads (62) corresponding to and connected to the two base bodies (71) respectively. The seat body (71) is provided with an adjusting mechanism (8) for driving the seat body (71) to reciprocate along the second track (5); The seat body (71) is provided with two slideways (711), and the slideways (711) are slidably connected with supports (712); The infrared emitter 1 (721) and the infrared sensor 1 (722) are respectively mounted on the two supports (712); A driving mechanism (9) is installed on the seat body (71) for driving the two supports (712) to move closer to or away from each other; The driving mechanism (9) includes a bidirectional motor (91) and two screw rods (92); The two second screw rods (92) are respectively threadedly connected to the two supports (712), and the rotation directions of the two second screw rods (92) are opposite, and the two second screw rods (92) are respectively connected to the two output shafts of the bidirectional motor (91); an elastic member (7111) is provided between the support (712) and the base (71); A connecting assembly (93) is provided between the output shaft and the second screw (92); The connecting assembly (93) includes a first component (931), a second component (932) and an intermediate component (933); The first component (931) and the second component (932) are both tubular structures with polygonal cross sections; the middle piece (933) is a rod-shaped structure adapted to the first component (931) and the second component (932); The first component (931) is sleeved onto the second screw (92), and the second component (932) is sleeved onto the output shaft of the bidirectional motor (91); The two ends of the middle piece (933) are respectively slidably connected to the first component (931) and the second component (932); The intermediate member (933) is fixedly connected to an elastic member 1 (97), and the elastic member 1 (97) is connected to the output shaft of the component 2 (932) or the driving mechanism (9); Under the action of the elastic member 1 (97), the intermediate member (933) extends into the member 1 (931); A fixing seat (94) is provided on one side of the middle piece (933), and the fixing seat (94) is fixed to the bidirectional motor (91); A second slideway (941) is vertically provided on the fixed seat (94), a connecting member (95) is slidably connected inside the second slideway (941), a ring-shaped slideway (96) is fixedly connected to the connecting member (95) and is sleeved on the outer periphery of the output shaft of the bidirectional motor (91), a toggle member (9331) is slidably connected inside the third slideway (96), and the toggle member (9331) is fixedly connected to the intermediate member (933).

2. A high-speed aircraft engine rotor tip grinding real-time measurement device according to claim 1, characterized in that: The straight line where the infrared emitter 1 (721) and the infrared sensor 1 (722) on the same base (71) are located is in a vertical state.

3. The real-time measurement device for high-speed aircraft engine rotor tip grinding according to claim 1, characterized in that: An adjustment rope (98) is fixedly connected between the two slideways (96) on the same seat body (71).

4. The real-time measurement device for high-speed aircraft engine rotor tip grinding according to claim 1, characterized in that: Also included is a spacing measurement component (10); The distance measurement component (10) includes a second infrared emitter (101) and a second infrared sensor (102), and the second infrared emitter (101) and the second infrared sensor (102) are respectively located on the top of the upper supports (712) of the two base bodies (71); When the second infrared sensor (102) does not sense the infrared signal emitted by the second infrared transmitter (101), the bidirectional motor (91) is started, and the two supports (712) move away from each other; When the second infrared sensor (102) senses the infrared signal emitted by the second infrared transmitter (101), the bidirectional motor (91) stops working.

5. A high-speed aircraft engine rotor blade tip grinding device: characterized by: It comprises a tooling table (1), a carrying mechanism (2), a grinding mechanism (3), a control system (4), and the rotor blade tip grinding real-time measurement device according to any one of claims 1 to 4; The bearing mechanism (2) comprises a main seat (21) mounted on the workbench (1); and a support seat (22) mounted on the main seat (21), wherein a clamping disc (2211) is rotatably connected to the support seat (22); and a driving member (212) for driving the clamping disc (2211) to rotate. The polishing mechanism (3) comprises a base (31), a lifting assembly (32) and a polishing assembly (33); The lifting assembly (32) includes a lifting seat (321); a lifting component (322) installed between the lifting seat (321) and the base (31) for achieving lifting of the lifting seat (321); The grinding assembly (33) includes a grinding member (331) rotatably connected to the lifting seat (321) and located above the clamping plate (2211); and a driving member (212) mounted on the lifting seat (321) for driving the grinding member (331) to rotate. The rotor blade tip grinding real-time measurement device is installed on the tooling table (1); The control system (4) is used to control various electrical components.

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