CN115655947A - Friction experiment device for blades of air compressor of aircraft engine under composite micro-motion - Google Patents
Friction experiment device for blades of air compressor of aircraft engine under composite micro-motion Download PDFInfo
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- CN115655947A CN115655947A CN202211361412.9A CN202211361412A CN115655947A CN 115655947 A CN115655947 A CN 115655947A CN 202211361412 A CN202211361412 A CN 202211361412A CN 115655947 A CN115655947 A CN 115655947A
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- 238000002474 experimental method Methods 0.000 title claims description 9
- 238000003825 pressing Methods 0.000 claims abstract description 16
- 238000012360 testing method Methods 0.000 claims abstract description 7
- 230000001360 synchronised effect Effects 0.000 claims description 7
- 238000001514 detection method Methods 0.000 claims 2
- 150000001875 compounds Chemical class 0.000 claims 1
- 238000012545 processing Methods 0.000 abstract description 12
- 238000000034 method Methods 0.000 abstract description 6
- 238000003754 machining Methods 0.000 description 7
- 238000005096 rolling process Methods 0.000 description 5
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- 238000004458 analytical method Methods 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 238000007405 data analysis Methods 0.000 description 1
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- 238000006073 displacement reaction Methods 0.000 description 1
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Abstract
An experimental device for rotation-movement composite fretting friction of an air machine blade belongs to the field of air machine testing of aircraft engines and comprises a pair of fixed frames and a movable frame arranged between the fixed frames, wherein a pair of friction wheels are arranged in the movable frame, rotating devices are respectively connected with the friction wheels, pressing devices which are oppositely pressed and are perpendicular to the direction of a fixed sliding rail are arranged on the peripheries of the friction wheels, a micromotion device which is used for reciprocating movement of the movable frame is arranged on one fixed frame, a blade is horizontally fixed on the other fixed frame, and the friction wheels are pressed or rotated and rubbed on two sides of the blade to simulate actual processing of the blade and further detect torque and friction force, so that the operating condition of fretting friction damage of a connection interface between a blade tenon and a clamp groove is simulated, a friction and wear mechanism and influence factors in the actual processing process are obtained, and data support is provided.
Description
Technical Field
The invention relates to an experimental device, in particular to a friction experimental device of an aircraft engine compressor blade under composite micromotion, and belongs to the field of aircraft engine compressor testing.
Background
The aeroengine belongs to a heat engine, and the working principle is to convert heat energy into mechanical energy. The aero-engine compressor blade is a key component for generating thrust through gas of an aero-engine and mainly comprises a blade body and a tenon. Fig. 4 is a schematic view of a part of connection structure between a plurality of blades connected between a wheel disc and the blades and the wheel disc, the blades 30 and the wheel disc 32 are connected together through a mortise and tenon structure, tenons 31 on the sides of the blades 30 and mortises on the periphery of the wheel disc are connected together, separation of the blades cannot be generated due to centrifugal force generated by rotation of the blades, and when an engine fan rotates, the tenons of the blades drive the wheel disc to rotate together, and simultaneously, loads borne by the blades are transferred to the wheel disc.
Because the blade of the air compressor of the aero-engine works in a complex environment with high temperature, high pressure, high speed and multiphase flow coupling, the turbine working blade is connected with the turbine disc by the tenon which is a part with larger load in the engine, the centrifugal force borne by the tenon of 1 blade of the engine is as high as 100 to 150kN (about 15 tons), the tenon works at high temperature, the mechanical property of the material is greatly reduced, and due to the particularity of the service environment of the blade, the influence brought to the characteristic of the blade in the processing process of the blade directly relates to the characteristic of the blade, in order to prevent the tenon from easily breaking down in the use of the blade, each detail in the design and the processing process needs to be paid attention, and the influence of the processing on the blade needs to be researched.
Fig. 5 is a schematic view of a clamping structure for clamping a blade in a clamp groove in a blade rolling process, and fig. 5 only shows a lower clamp groove in order to see a structure in the clamp groove, in the blade rolling process, the blade 30 generally clamps a tenon 31 in a clamp groove 33 through a clamp and then processes the blade 30, and due to the fact that an alternating load acts on a clamping interface between the tenon 31 and the clamp groove 33 of the blade, the tenon 31 is further slightly displaced, so that fretting wear occurs in a fretting contact area between the tenon 31 and the clamp 34, and positioning accuracy is reduced, and blade characteristics are affected, so far, how to the fretting wear characteristics of a connection interface of the clamp groove 33 in the blade 30 rolling process, how much influence is given to the tenon 31 of the blade, how to know a fretting wear mechanism and an influence factor thereof in an actual processing process, and a subject to be solved by related research and development personnel.
Disclosure of Invention
Aiming at the problem that in the rolling process of an aero-engine compressor blade, a fixed interface between a blade tenon and a clamp is subjected to alternating load to generate micro displacement, and a fretting contact area between the tenon and the clamp generates friction wear, so that the influence of positioning accuracy and machining accuracy is an unknown number, in order to obtain one-hand data, the invention provides a friction experiment device of the aero-engine compressor blade under composite fretting, which aims to simulate the operation condition of fretting friction damage of a connection interface between the blade tenon and a clamp groove, implement a rotation-movement composite friction wear experiment, obtain a friction wear mechanism and influence factors thereof in the actual machining process, so that proper measures are taken to slow down the friction wear phenomenon, and provide data support for the machining of the compressor blade.
The technical scheme of the invention is as follows: a friction experiment device of an aircraft engine compressor blade under composite micromotion comprises a rack, wherein the rack comprises a pair of fixed racks and a movable rack arranged between the fixed racks, the fixed racks are vertically arranged on a bottom plate in a relatively parallel mode, a pair of fixed slide rails are further arranged on the bottom plate in a parallel mode, the movable racks are arranged on the fixed slide rails in a sliding mode, a pair of friction wheels are arranged in the movable rack, the axes of the friction wheels are respectively connected, pressing devices which are oppositely pressed are arranged on the peripheries of the friction wheels, the pressing direction of the pressing devices is perpendicular to the direction of the fixed slide rails, a micromotion device for reciprocating movement of the movable rack is arranged on one of the fixed racks, blades are horizontally fixed on the fixed rack on the other side, a reciprocating micromotion driving device drives the movable rack to move in a reciprocating linear mode, meanwhile, the friction wheels and the blade edges are subjected to linear friction along the direction of the slide rails, the friction wheels are driven to rotate, a torque sensor and a friction force sensor are respectively arranged on a rotating shaft of the rotating shaft and a driving shaft of the micromotion device, and the torque sensor and the friction force sensor are respectively connected to a data feedback device;
furthermore, the micro-motion device is a pair of synchronous rotation piezoelectric actuators, the pair of synchronous rotation piezoelectric actuators are connected with the moving rack through a driving shaft, and a pair of friction wheels are respectively connected to rotating shafts of the pair of synchronous rotation piezoelectric actuators;
furthermore, the pressing device is a pair of air cylinders, the pair of air cylinders are arranged in the vertical direction of the reciprocating movement of the movable rack outside the movable rack, the air cylinder rods on the two sides respectively extend to the inner side of the movable rack, the rod ends of the air cylinder rods on the two sides are respectively connected with respective movable sliding blocks, the movable sliding blocks on the two sides and the movable rack are respectively connected in the movable rack through movable pairs, and the movable sliding blocks on the two sides and the friction wheels on the same side are respectively connected through revolute pairs;
furthermore, a pair of long holes are formed in the moving rack, a rotating shaft of the rotating piezoelectric actuator penetrates through the long holes, the rotating piezoelectric actuator is arranged above the moving rack, and when the pressing device presses the moving slide block to slide along the vertical direction of the fixed slide rail, the rotating piezoelectric actuator moves synchronously;
further, sliding blocks are arranged on two sides of the fixed sliding rail and fixed at the bottom of the movable rack;
furthermore, one side of the moving slide block, which faces the friction wheel, is of an arc structure consistent with the periphery of the friction wheel;
further, an encoder is arranged on the micro rotating device, a pressure sensor is arranged on the pressing device, and the encoder and the pressure sensor are also connected to the data feedback device.
The invention has the following positive effects: the rotating friction wheel is arranged in the movable rack, the torque sensor is arranged on the rotating shaft of the friction wheel, and the torque force generated between the rotation of the friction wheel and the blade is detected, so that the torsional friction moment generated when the blade rotates slightly relative to the clamping groove during blade machining is simulated, and the torque data generated under the rotating speed of the friction wheel can be changed; further simulating torque data of the blades under different rotating speeds in actual processing; the micro-motion device drives the movable rack to move in a reciprocating micro-motion manner, the friction wheel arranged in the movable rack is further driven to synchronously perform the reciprocating micro-motion with the movable rack, and the edge of the blade is clamped by the clamping device along a clamping force vertical to the length direction of the fixed slide rail, so that the friction force generated between the friction wheel and the edge of the blade during micro-motion under the clamping condition of the blade can be detected, the friction force between the blade and the friction wheel under different clamping forces can be obtained, the friction force caused by the micro-motion generated under the pressing force during actual blade clamping processing can be simulated, and the friction force generated under different movement amounts can be generated under different clamping forces; the friction and wear mechanism and the influence factors thereof in the actual processing process can be obtained through data analysis, so that proper measures are taken to slow down the friction and wear phenomenon, data support is provided for the processing of the compressor blade of the aircraft engine, and the processing quality of the blade is further ensured.
Drawings
FIG. 1 is a schematic view of the overall structure of the experimental apparatus.
Fig. 2 is a schematic view of the arrangement and the micro-motion device.
Fig. 3 is a schematic perspective view of the micro-motion device.
FIG. 4 is a schematic view of a connection structure between a plurality of blades connected between a disk and a blade and a part of the disk.
FIG. 5 is a schematic view of the clamping structure of the clamping blade in the clamp groove during the rolling process of the blade.
Description of the reference symbols: 10-a first fixed support, 11-a second fixed frame, 12-a friction force sensor, 13-a movable piezoelectric actuator, 14-a first rotary piezoelectric actuator, 15-a second rotary piezoelectric actuator, 16-a bottom plate, 17-a sliding block, 18-a first fixed sliding rail, 19-a second fixed sliding rail, 20-a first cylinder, 21-a second cylinder, 22-a movable frame, 24-a first friction wheel, 25-a second friction wheel, 26-a first movable sliding block, 27-a second movable sliding block, 28-a torque sensor, 29-a driving shaft, 30-a blade, 31-a tenon, 32-a wheel disc, 33-a clamp groove and 34-a clamp.
Detailed Description
The following describes the technical aspects of the present invention in detail with reference to the accompanying drawings.
The technical scheme of the invention is as follows: a friction experiment device of an aircraft engine compressor blade under composite fine motion is disclosed, wherein FIG. 1 is a schematic diagram of the whole structure of the experiment device, FIG. 2 is a schematic diagram of the structure provided with a fine motion device, FIG. 3 is a schematic diagram of the three-dimensional structure provided with a fine motion device, the experiment device comprises a frame, the frame comprises a pair of fixed frames and a movable frame 22 arranged between the fixed frames, the fixed frames are respectively a first fixed frame 10, a second fixed frame 11, a first fixed frame 10 and a second fixed frame 11 which are vertically arranged on a bottom plate 16 in parallel, the bottom plate 16 is also provided with a pair of fixed slide rails with the same structure in parallel, the fixed slide rails are a first fixed slide rail 18 and a second fixed slide rail 19, the movable frames 22 are arranged on the first fixed slide rail 18 and the second fixed slide rail 19 in a sliding manner, a pair of friction wheels are arranged in the movable frame 22, the friction wheels are a first friction wheel 24 and a second friction wheel 25, the friction wheel 24 and the friction wheel 25 are arranged on the friction wheel 25 in parallel, the friction wheel 24 and the friction wheel 25, the friction wheel 25 have the same structure, the axes, the edges are respectively connected, the peripheries of the first friction wheel 24 and the friction wheel 25 are respectively, the friction wheel 24 and the friction wheel 25 are provided with a linear driving device, the edge part which are provided with a linear driving force sensor 30 which makes the fixed on the fixed slide rail 22 and a linear driving device 22, a linear driving device which make the fixed slide rail 22 and a piezoelectric actuator 22 which make the piezoelectric actuator 22 rotate along the fixed slide rail 22, the piezoelectric actuator 14 and a linear driving device 22, a linear driving device which make the piezoelectric actuator 22 move along the linear driving device 22, a linear driving device 22 and a piezoelectric actuator 30 which make the piezoelectric actuator 22 move synchronously with a linear driving device 22, a linear driving device which make the piezoelectric actuator 22 move along the piezoelectric actuator 22, the torque sensor 28 and the friction sensor 12 are each connected to a data feedback device.
Referring to fig. 1-3, the micro-motion device is a moving piezoelectric actuator 13, and the pair of synchronous rotating piezoelectric actuators specifically includes a first rotating piezoelectric actuator 14 and a second rotating piezoelectric actuator 15 with the same structure, the moving piezoelectric actuator 13 is connected to the moving frame 22 through a driving shaft 29, and a first friction wheel 24 and a second friction wheel 25 are respectively connected to the rotating shafts of the first rotating piezoelectric actuator 14 and the second rotating piezoelectric actuator 15.
The pressing device is a pair of air cylinders, the pair of air cylinders are an air cylinder I20 and an air cylinder II 21, the air cylinder I20 and the air cylinder II 21 are arranged in the vertical direction of the reciprocating movement of the moving rack 22 outside the moving rack 22, cylinder rods of the air cylinder I20 and the air cylinder II 21 on two sides respectively extend to the inner side of the moving rack 22, rod ends of the air cylinder I20 and the air cylinder II 21 on two sides are respectively connected with respective moving sliders through pressure sensors, the moving sliders are a moving slider I26 and a moving slider II 27, the moving slider I26 and the moving slider II 27 on two sides are respectively connected with the moving rack 22 in the moving rack 22 through moving pairs, and the moving slider I26 and the moving slider II 27 on two sides are respectively connected with the friction wheel I24 and the friction wheel II 25 on the same side through rotating pairs.
Referring to fig. 1 to 3, a pair of long holes is formed in the moving frame 22, the rotating shafts of the first rotary piezoelectric actuator 14 and the second rotary piezoelectric actuator 15 penetrate through the long holes above the moving frame 22, the first rotary piezoelectric actuator 14 and the second rotary piezoelectric actuator 15 are arranged above the moving frame 22, when the pressing device presses the first movable slider 26 and the second movable slider 27 to slide along the first fixed slide rail 18 and the second fixed slide rail 19 in the vertical direction, the first rotary piezoelectric actuator 14 and the second rotary piezoelectric actuator 15 synchronously move along the long holes in the directions of the two sides of the blade, the sliders 17 are arranged on the two sides of the first fixed slide rail 18 and the second fixed slide rail 19, and the sliders 17 are fixed at the bottom of the moving frame 22.
The first moving slide block 26, the second moving slide block 27 face the first friction wheel 24 and the second friction wheel 25 respectively, and are in arc structures consistent with the peripheries of the first friction wheel 24 and the second friction wheel 25.
Encoders are arranged on the first rotary piezoelectric actuator 14 and the second rotary piezoelectric actuator 15, and pressure sensors are arranged at the rod ends of the first air cylinder and the second air cylinder and are respectively used for detecting torque and friction force generated under different rotating speeds and different pressing forces.
The micro rotating device is provided with an encoder, the pressing device is provided with a pressure sensor, and the encoder and the pressure sensor are also connected to the data feedback device.
In the invention, the synchronous mode of the first rotary piezoelectric actuator 14 and the second rotary piezoelectric actuator 15 is realized by a frequency converter.
The moving piezoelectric actuator 13 is also realized by using a frequency converter, and drives the moving frame 22 to realize reciprocating micromotion movement as a whole.
According to the invention, the first rotating friction wheel 24 and the second rotating friction wheel 25 are arranged in the movable rack 22, and the torque sensors 28 are respectively arranged on the rotating shafts of the first and second friction wheels, so that the torque between the blade 30 and the friction wheels can be detected, the torque generated when the blade 30 slightly rotates relative to the clamping groove 33 in actual processing can be simulated, and the torque data received by the blade 30 at different rotating speeds can be detected; the micro-motion device drives the moving rack 22 to move in a reciprocating micro-motion manner, the first friction wheel 24 and the second friction wheel 25 arranged in the moving rack 22 are further driven to synchronously perform micro-motion in a reciprocating manner, and the edge of the blade 30 is clamped by clamping force along the direction perpendicular to the length direction of the first fixed slide rail 18 and the second fixed slide rail 19 through the clamping device, so that the friction force generated between the friction wheel and the blade 30 during micro-motion can be detected, the friction force between the blade 30 and the friction wheel under different clamping forces can be further obtained, therefore, under the condition of different clamping forces, the different micro-motion amounts generated between the blade 30 and the clamp groove 33 under different clamping forces and the different friction forces generated under different micro-motion amounts during actual blade machining can be simulated, through the torque and friction force data, the friction wear mechanism and the influence factors thereof in the actual machining process can be obtained through analysis, and appropriate measures can be taken to slow down the friction wear phenomenon, so that data support is provided for the machining of the blades of the aircraft engine compressor 30, and the quality of the blades 30 is further ensured.
Claims (7)
1. The utility model provides an aircraft engine compressor blade friction experimental apparatus under compound fine motion, includes the frame, its characterized in that: the machine frame comprises a pair of fixed machine frames and a movable machine frame arranged between the fixed machine frames, the fixed machine frames are oppositely and parallelly arranged on a bottom plate, a pair of fixed slide rails are further arranged on the bottom plate in parallel, the movable machine frames are arranged on the fixed slide rails in a sliding mode, a pair of friction wheels are horizontally arranged in the movable machine frames, micro rotating devices are respectively connected to the axes of the friction wheels, pressing devices which are opposite to each other and are perpendicular to the direction of the fixed slide rails are arranged on the peripheries of the friction wheels, a micro moving device which can move the movable machine frames in a reciprocating mode is arranged on one of the fixed machine frames, blades are horizontally fixed on the other fixed machine frame, the micro moving device drives the movable machine frames to move in a reciprocating mode horizontally and enables the friction wheels and the edge portions of the blades to conduct linear friction along the direction of the slide rails, the micro rotating device drives the friction wheels to rotate and enables the friction wheels to conduct rotating friction with the edge portions of the blades, a torque detection instrument and a friction force detection instrument are respectively arranged on a rotating shaft of the micro rotating device and a driving shaft of the micro moving device, and a torque sensor and a friction force sensor are respectively connected to a data feedback device.
2. The friction test device for the compressor blade of the aircraft engine under the composite micromotion as claimed in claim 1, is characterized in that: the micro-motion device is a moving piezoelectric actuator, the micro-rotation device is a pair of synchronous rotation piezoelectric actuators, the moving piezoelectric actuators are connected with the moving rack through a driving shaft, and a pair of friction wheels are connected to the rotating shafts of the pair of synchronous rotation piezoelectric actuators respectively.
3. The friction test device for the compressor blade of the aircraft engine under the composite micromotion as claimed in claim 1, is characterized in that: the pressing device is a pair of air cylinders, the pair of air cylinders are arranged in the vertical direction of the reciprocating movement of the moving rack outside the moving rack, air cylinder rods on two sides respectively extend to the inner side of the moving rack, rod ends of the air cylinder rods on two sides are respectively connected with respective moving sliding blocks, the moving sliding blocks on two sides and the moving rack are respectively connected in the moving rack through moving pairs, and the moving sliding blocks on two sides and the friction wheels on the same side are respectively connected through rotating pairs.
4. The friction test device for the compressor blade of the aircraft engine under the composite micromotion as claimed in claim 1, is characterized in that: the pair of long holes are formed in the moving rack, the rotating shaft of the rotating piezoelectric actuator penetrates through the long holes, the rotating piezoelectric actuator is arranged above the moving rack, and when the pressing device presses the moving slide block to slide along the vertical direction of the fixed slide rail, the rotating piezoelectric actuator moves synchronously.
5. The friction test device for the compressor blade of the aircraft engine under the composite micromotion as claimed in claim 1, is characterized in that: and sliding blocks are arranged on two sides of the fixed sliding rail and fixed at the bottom of the movable rack.
6. The friction experiment device for the compressor blade of the aircraft engine under the composite micromotion as claimed in claim 1, characterized in that: one side of the movable sliding block, which faces the friction wheel, is of an arc structure matched with the periphery of the friction wheel.
7. The friction test device for the compressor blade of the aircraft engine under the composite micromotion as claimed in claim 1, is characterized in that: the micro rotating device is provided with an encoder, the pressing device is provided with a pressure sensor, and the encoder and the pressure sensor are also connected to the data feedback device.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211361412.9A CN115655947A (en) | 2022-11-02 | 2022-11-02 | Friction experiment device for blades of air compressor of aircraft engine under composite micro-motion |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211361412.9A CN115655947A (en) | 2022-11-02 | 2022-11-02 | Friction experiment device for blades of air compressor of aircraft engine under composite micro-motion |
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| Publication Number | Publication Date |
|---|---|
| CN115655947A true CN115655947A (en) | 2023-01-31 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211361412.9A Withdrawn CN115655947A (en) | 2022-11-02 | 2022-11-02 | Friction experiment device for blades of air compressor of aircraft engine under composite micro-motion |
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| CN (1) | CN115655947A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116678777A (en) * | 2023-08-03 | 2023-09-01 | 常州富安切削技术有限公司 | Wear resistance testing device and method for PVD (physical vapor deposition) cutter coating |
-
2022
- 2022-11-02 CN CN202211361412.9A patent/CN115655947A/en not_active Withdrawn
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116678777A (en) * | 2023-08-03 | 2023-09-01 | 常州富安切削技术有限公司 | Wear resistance testing device and method for PVD (physical vapor deposition) cutter coating |
| CN116678777B (en) * | 2023-08-03 | 2023-10-03 | 常州富安切削技术有限公司 | Wear resistance testing device and method for PVD (physical vapor deposition) cutter coating |
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Application publication date: 20230131 |
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