CN116358860A - Propeller blade fatigue test equipment - Google Patents
Propeller blade fatigue test equipment Download PDFInfo
- Publication number
- CN116358860A CN116358860A CN202310641920.0A CN202310641920A CN116358860A CN 116358860 A CN116358860 A CN 116358860A CN 202310641920 A CN202310641920 A CN 202310641920A CN 116358860 A CN116358860 A CN 116358860A
- Authority
- CN
- China
- Prior art keywords
- transverse
- cylinder
- load
- clamping
- seat
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000009661 fatigue test Methods 0.000 title claims abstract description 20
- 238000001514 detection method Methods 0.000 claims abstract description 17
- 230000000149 penetrating effect Effects 0.000 claims description 3
- 238000012360 testing method Methods 0.000 abstract description 22
- 238000000034 method Methods 0.000 abstract description 8
- 230000035882 stress Effects 0.000 description 6
- 238000006073 displacement reaction Methods 0.000 description 3
- 210000003781 tooth socket Anatomy 0.000 description 3
- 230000002929 anti-fatigue Effects 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 230000032683 aging Effects 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
Images
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/70—Wind energy
- Y02E10/72—Wind turbines with rotation axis in wind direction
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The invention relates to the technical field of propellers, in particular to a propeller blade fatigue test device which comprises a propeller hub and a plurality of blade bodies uniformly and fixedly arranged on the outer side of the propeller hub, wherein the propeller hub is supported and fixed through a central positioning table, a clamping fixing piece is arranged on each blade body, a detection bracket is arranged on the periphery of each clamping fixing piece, a longitudinal load component is arranged at the top end of each detection bracket, a transverse load component is arranged on one side of each detection bracket, the longitudinal load component and the transverse load component are respectively connected with the clamping fixing pieces, a positioning seat is fixedly arranged at one end, far away from the propeller hub, of each blade body, and is connected with a torque load component, and a centrifugal tension load component is arranged below the torque load component. The invention can simultaneously realize the load application of vertical pressure, horizontal tangential force, torque and centrifugal tension, so as to carry out the multi-project fatigue test process on the blade body in an omnibearing manner, and effectively ensure the test efficiency and the detection accuracy.
Description
Technical Field
The invention relates to the technical field of propeller testing, in particular to a device for testing fatigue of propeller blades.
Background
The propeller blade is a component which can not obtain the engine rotation power into the propulsion, and has the characteristics of light weight, corrosion resistance, aging resistance and good fatigue resistance. Fatigue performance is an important performance parameter of propeller blades, and therefore fatigue testing of the blades is particularly important.
The conventional fatigue testing machine can only perform axial stretching/compression or rotating bending fatigue test of a simple sample, and an effective fatigue performance testing system is not available for a propeller blade structural member with axial centrifugal force and alternating transverse load.
Disclosure of Invention
The invention aims to provide a propeller blade fatigue test device which aims to solve the technical problems.
The aim of the invention can be achieved by the following technical scheme:
the utility model provides a screw blade fatigue test equipment, includes the oar hub and evenly fixes a plurality of blade main parts that set up in the oar hub outside, the oar hub is supported fixedly through central location platform, every be provided with the centre gripping mounting in the blade main part, the periphery of centre gripping mounting is provided with the detection support, the top of detecting the support is provided with vertical load subassembly, one side of detecting the support is provided with horizontal load subassembly, vertical load subassembly is connected with the centre gripping mounting respectively with horizontal load subassembly, the one end that the oar hub was kept away from to the blade main part is fixed to be provided with the positioning seat, the positioning seat is connected with moment of torsion load subassembly, moment of torsion load subassembly below connection is provided with centrifugal tension load subassembly, moment of torsion load subassembly and centrifugal tension load subassembly all are on a parallel with the length direction setting of blade main part.
The clamping fixing piece comprises a pair of clamping blocks which are arranged up and down oppositely, wing-shaped holes matched with the blade body are formed in the clamping blocks in a penetrating mode, the inner walls of the wing-shaped holes are always kept fit with the outer surfaces of the blade body, positioning portions are arranged at two ends of each clamping block in an extending mode, a group of positioning portions which are adjacent up and down are fixedly connected with the positioning clamping seats through positioning bolts, the longitudinal load assembly comprises a longitudinal cylinder, the output end of the longitudinal cylinder is connected with a longitudinal load force application rod, the longitudinal load force application rod is fixedly connected with the clamping blocks at the upper end, the transverse load assembly comprises a transverse cylinder, the output end of the transverse cylinder is connected with a transverse load force application rod, the transverse load force application rod is fixedly connected with the positioning clamping seats at one side of the transverse load application rod, the longitudinal load assembly and the transverse load assembly linearly move according to different clamping positions of the clamping blocks on the blade body to adjust load application positions, and the moving directions of the longitudinal load assembly and the transverse load assembly are parallel to the length direction of the blade body.
As a further scheme of the invention: the longitudinal load assembly further comprises a first cylinder fixing seat, a first fixed transverse plate and a first movable frame, the longitudinal cylinder is vertically and fixedly arranged in the first cylinder fixing seat, the first cylinder fixing seat is fixedly connected with the first movable frame through a first connecting block, a first transverse gear is installed in the first movable frame in a rotating mode, a first driving motor is fixedly arranged on the outer side of the first movable frame, an output end of the driving motor is connected with the first transverse gear, the top end of the first fixed transverse plate is fixedly arranged on the top end of the detection support through a fixed mounting seat, a first tooth groove is formed in the bottom of the first fixed transverse plate along the length direction, and the first transverse gear is matched with the first tooth groove in a toothed mode.
As a further scheme of the invention: the two sides of the top end of the movable frame are provided with clamping support parts I, the two sides of the upper end of the fixed transverse plate are provided with clamping support sliding grooves I, and the clamping support parts I are adapted to be slidably installed in the clamping support sliding grooves I.
As a further scheme of the invention: the transverse load assembly further comprises a cylinder fixing seat II, a fixed transverse plate II and a movable frame II, wherein the transverse cylinder is horizontally and fixedly arranged in the cylinder fixing seat II, the cylinder fixing seat II is fixedly connected with the movable frame II through a connecting block II, a transverse moving gear II is rotatably installed in the movable frame II, a driving motor II is fixedly arranged at the bottom of the movable frame II, the output end of the driving motor II is connected with the transverse moving gear II, one side of the fixed transverse plate II is slidably installed on one side of the detection support through a sliding installation seat, tooth grooves II are formed in the other side of the fixed transverse plate II along the length direction, and the transverse moving gear II is matched with the tooth grooves II in a toothed manner.
As a further scheme of the invention: the movable frame is characterized in that a second clamping support portion is arranged at the second end of the movable frame, a second clamping support sliding groove is arranged on the side wall of the second fixed transverse plate, and the second clamping support sliding groove is arranged in the second clamping support sliding groove in a sliding manner.
As a further scheme of the invention: the detection support is characterized in that a lifting chute is arranged on the side wall of the detection support, the sliding mounting seat is in sliding fit with the lifting chute, and the sliding mounting seat is connected with the detection support through a fixing bolt when moving to a designated height along the lifting chute.
As a further scheme of the invention: the torque load assembly comprises a rotary cylinder, the rotary cylinder is fixedly arranged at the upper end of an L-shaped bottom plate, the output end of the rotary cylinder is connected with a torsion connecting block, the torsion connecting block is fixedly connected with a positioning seat, and sliding limiting seats are arranged on two sides of the L-shaped bottom plate.
As a further scheme of the invention: the centrifugal tension load assembly comprises a fixed bottom plate and a tension cylinder, the tension cylinder is fixedly arranged in a cylinder seat, the cylinder seat is fixedly arranged on the fixed bottom plate, the output end of the tension cylinder is connected with a tension load force application rod, the tension load force application rod is fixedly connected with the L-shaped bottom plate, linear guide rails are arranged on two sides of the upper end of the fixed bottom plate, and the sliding limiting seat is in sliding fit with the linear guide rails.
The invention has the beneficial effects that:
(1) According to the invention, the blade main body and the hub are supported and fixed through the central positioning table, the clamping fixing piece is used as a stress carrier, load can be directly transmitted to the blade main body, the positioning seat is arranged at the end part of the blade main body, the stress transmission is carried out through the positioning seat, and corresponding sensors are configured in different load components in the actual test process, so that the load application of vertical pressure, horizontal tangential force, torque and centrifugal tension can be simultaneously realized, the multi-project fatigue test process of the blade main body is further carried out in an omnibearing manner, different test requirements of the blade main body are met, and the test efficiency and the test accuracy are effectively ensured.
(2) Through setting up the clamp block, adopt the detachable connection between two clamp blocks, because its cross-sectional shape of paddle main part is also different in different test positions, therefore the clamp block is provided with the multiunit, and the wing section hole shape in every clamp block of group is also different, every wing section Kong Shandu of group corresponds the paddle main part of a certain specific position, when need to exert the position of load on the paddle main part and adjust, only need dismantle and change corresponding clamp block can, longitudinal load subassembly and transverse load subassembly can do rectilinear movement according to clamp block in the different clamping position of paddle main part simultaneously, thereby realize carrying out longitudinal load and transverse load's application to the different positions of paddle main part, thereby comprehensively calculate the holistic antifatigue degree of paddle main part, effectively improved test result.
Drawings
The invention is further described below with reference to the accompanying drawings.
Fig. 1 is a schematic view of the overall structure of the present invention.
Fig. 2 is a schematic view of the installation of the blade body in the present invention.
Fig. 3 is a schematic view of the longitudinal load assembly of the present invention.
Fig. 4 is an enlarged schematic view of the structure at a in fig. 2.
Fig. 5 is a schematic view of the transverse load assembly of the present invention.
Fig. 6 is a schematic diagram of the torque load assembly and centrifugal tension load assembly of the present invention.
In the figure: 10. a hub; 101. a blade body; 102. a center positioning table; 103. a positioning seat; 20. clamping the fixing piece; 201. a clamping block; 202. an airfoil hole; 203. a positioning part; 204. positioning bolts; 205. positioning a clamping seat; 30. detecting a bracket; 301. lifting sliding grooves; 40. a longitudinal load assembly; 401. a longitudinal cylinder; 402. a longitudinal load force applying rod; 403. a first cylinder fixing seat; 404. fixing a transverse plate I; 4041. the clamping support chute I; 405. a first moving frame; 4051. the first clamping and supporting part is connected; 406. a first connecting block; 407. a transverse moving gear I; 408. driving a first motor; 409. fixing the mounting base; 410. tooth sockets I; 50. a lateral load assembly; 501. a transverse cylinder; 502. a lateral load force application rod; 503. a cylinder fixing seat II; 504. fixing a transverse plate II; 5041. the second clamping support chute is connected with the second clamping support chute; 505. a second moving frame; 5051. the clamping support part II is connected with the clamping support part II; 506. a second connecting block; 507. a transverse moving gear II; 508. a second driving motor; 509. a sliding mounting seat; 510. tooth grooves II; 60. a torque load assembly; 601. a rotary cylinder; 602. an L-shaped bottom plate; 603. twisting the connecting block; 604. a sliding limit seat; 70. a centrifugal tension load assembly; 701. a fixed bottom plate; 702. a stretching cylinder; 703. a cylinder block; 704. a tension load force application rod; 705. a linear guide rail.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
Referring to fig. 1 and 2, the present invention is a propeller blade fatigue test apparatus, including a hub 10 and a plurality of blade bodies 101 uniformly and fixedly disposed outside the hub 10, wherein the hub 10 is supported and fixed by a central positioning table 102, each blade body 101 is provided with a clamping fixing member 20, the periphery of the clamping fixing member 20 is provided with a detecting bracket 30, the top end of the detecting bracket 30 is provided with a longitudinal load assembly 40, one side of the detecting bracket 30 is provided with a transverse load assembly 50, the longitudinal load assembly 40 and the transverse load assembly 50 are respectively connected with the clamping fixing member 20, one end of the blade body 101 far away from the hub 10 is fixedly provided with a positioning seat 103, the positioning seat 103 is connected with a torque load assembly 60, a centrifugal tension load assembly 70 is connected under the torque load assembly 60, and the torque load assembly 60 and the centrifugal tension load assembly 70 are both parallel to the length direction of the blade body 101.
Specifically, the blade main body 101 and the hub 10 in the invention are supported and fixed through the central positioning table 102, the clamping fixing piece 20 is used as a stress carrier, load can be directly transmitted to the blade main body 101, the longitudinal load component 40 can apply load on the vertical direction to the blade main body 101, the transverse load component 50 component can apply load on the horizontal direction to the blade main body 101, the positioning seat 103 is arranged at the end part of the blade main body 101, the positioning seat 103 is used for carrying out stress transmission, the torque load component 60 can carry out torsion action on the blade main body 101, meanwhile, the centrifugal tension component can carry out stretching action on the blade main body 101 in the centrifugal direction, and corresponding sensors are arranged in different load components in the actual test process, so that the load application of vertical pressure, horizontal force, torque and centrifugal tension can be simultaneously realized, and the multi-project fatigue test process can be carried out on the blade main body 101 in all directions, different test requirements of the blade main body 101 are met, and the test efficiency and the detection accuracy are effectively ensured.
The number of the blade bodies 101 in this embodiment is three, and the detecting supports 30 and the corresponding load components are also correspondingly provided with three groups, and uniformly distributed around the hub 10, so as to simultaneously realize the test requirements of the three groups of blade bodies 101. Of course, the number of the blade bodies 101 may be 4, 5 or 6, and the detecting bracket 30 and the corresponding load component are correspondingly provided with 4 groups, 5 groups or 6 groups, so as to improve the reliability and the detecting efficiency of the detecting result.
As shown in fig. 3, the clamping fixture 20 includes a pair of clamping blocks 201 disposed vertically opposite to each other, an airfoil hole 202 adapted to the blade body 101 is disposed in the clamping blocks 201 in a penetrating manner, an inner wall of the airfoil hole 202 is always kept in contact with an outer surface of the blade body 101, two ends of each clamping block 201 are extended to form positioning portions 203, a group of positioning portions 203 adjacent vertically are fixedly connected with the positioning clamping seat 205 through positioning bolts 204, the longitudinal load assembly 40 includes a longitudinal cylinder 401, an output end of the longitudinal cylinder 401 is connected with a longitudinal load force applying rod 402, the longitudinal load force applying rod 402 is fixedly connected with the clamping block 201 at an upper end, the transverse load assembly 50 includes a transverse cylinder 501, an output end of the transverse cylinder 501 is connected with a transverse load force applying rod 502, the transverse load force applying rod 502 is fixedly connected with the positioning clamping seat 205 at one side thereof, the longitudinal load assembly 40 and the transverse load assembly 50 move linearly according to different clamping positions of the clamping blocks 201 on the blade body 101 to adjust load applying positions, and a moving direction of the longitudinal load applying assembly is parallel to a length direction of the blade body 101.
Specifically, through setting up clamp block 201, adopt detachable connection between two clamp blocks 201, because blade main body 101 is in the different test position its cross-sectional shape also different, therefore clamp block 201 is provided with the multiunit, and the wing section hole 202 shape in every clamp block 201 of group is also different, every wing section hole 202 of group corresponds the blade main body 101 of a certain specific position alone, when need to exert the position of load on blade main body 101 and adjust, only need dismantle change corresponding clamp block 201 can, longitudinal load subassembly 40 and transverse load subassembly 50 can do the rectilinear movement according to clamp block 201 in the different clamping position of blade main body 101 simultaneously, thereby realize carrying out longitudinal load and transverse load's application to the different positions of blade main body 101, thereby calculate the holistic antifatigue degree of blade main body 101, effectively improved test result.
As shown in fig. 3, the longitudinal load assembly 40 further includes a first cylinder fixing seat 403, a first fixed transverse plate 404, and a first moving frame 405, the first cylinder 401 is vertically and fixedly disposed in the first cylinder fixing seat 403, the first cylinder fixing seat 403 is fixedly connected with the first moving frame 405 through a first connecting block 406, a first transverse gear 407 is rotatably mounted in the first moving frame 405, a first driving motor 408 is fixedly disposed at the outer side of the first moving frame 405, an output end of the first driving motor 408 is connected with the first transverse gear 407, a top end of the first fixed transverse plate 404 is fixedly disposed at a top end of the detecting bracket 30 through a fixed mounting seat 409, a first tooth slot 410 is disposed at a bottom of the first fixed transverse plate 404 along a length direction, and the first transverse gear 407 is in toothed engagement with the first tooth slot 410.
Specifically, when the first driving motor 408 is started, the first traversing gear 407 is driven to rotate, and the first traversing gear 407 and the first tooth socket 410 are meshed, so that the whole moving frame 405 can linearly move along the first fixed transverse plate 404, and the position of the longitudinal cylinder 401 for applying the longitudinal load can be synchronously adjusted according to different clamping positions of the clamping block 201 on the blade main body 101.
As shown in fig. 3, two sides of the top end of the first moving frame 405 are provided with a first clamping support portion 4051, two sides of the upper end of the first fixed transverse plate 404 are provided with a first clamping support chute 4041, and the first clamping support portion 4051 is adapted to be slidably mounted in the first clamping support chute 4041.
Specifically, in the process that the moving frame one 405 integrally moves linearly along the fixed transverse plate one 404, the first clamping support portion 4051 always slides in the first clamping support chute one 4041, which has the function of ensuring the stability and reliability of the moving process of the moving frame one 405, and providing the stable support function for the moving frame one 405.
As shown in fig. 5, the transverse load assembly 50 further includes a second cylinder fixing seat 503, a second fixed transverse plate 504 and a second moving frame 505, the transverse cylinder 501 is horizontally and fixedly arranged in the second cylinder fixing seat 503, the second cylinder fixing seat 503 is fixedly connected with the second moving frame 505 through a second connecting block 506, a second transverse gear 507 is rotatably mounted in the second moving frame 505, a second driving motor 508 is fixedly arranged at the bottom of the second moving frame 505, an output end of the second driving motor 508 is connected with the second transverse gear 507, one side of the second fixed transverse plate 504 is slidably mounted on one side of the detecting bracket 30 through a sliding mounting seat 509, a second tooth groove 510 is arranged on the other side of the second fixed transverse plate 504 along the length direction, and the second transverse gear 507 is in toothed connection with the second tooth groove 510.
Specifically, in the same manner as the longitudinal load assembly 40, when the second driving motor 508 is started, the second traversing gear 507 is driven to rotate, and the second traversing gear 507 and the second tooth socket 510 are meshed, so that the whole moving frame 505 can linearly move along the second fixed transverse plate 504, and thus the position of the transverse cylinder 501 for applying the transverse load can be synchronously adjusted according to different clamping positions of the clamping block 201 on the blade main body 101.
As shown in fig. 4, the end of the second moving frame 505 is provided with a second clamping support portion 5051, the side wall of the second fixed transverse plate 504 is provided with a second clamping support chute 5041, and the second clamping support chute 5041 is adapted to be slidably mounted in the second clamping support chute 5041.
Specifically, in the same way as the first clamping support portion 4051, the second clamping support portion 5051 and the second clamping support chute 5041 are in sliding fit to provide stable support for the second moving frame 505, and limit guiding can be performed on the linear displacement process of the second moving frame 505.
As shown in fig. 4, the side wall of the detecting bracket 30 is provided with a lifting chute 301, a sliding mounting seat 509 is slidably matched with the lifting chute 301, and the sliding mounting seat 509 is connected with the detecting bracket 30 through a fixing bolt when moving to a designated height along the lifting chute 301.
Specifically, when the clamping block 201 is clamped at different positions on the blade main body 101, the overall height of the clamping block 201 is slightly changed along with different horizontal positions, so that in order to eliminate stress interference generated by the height change when a transverse acting force is applied to the transverse load assembly 50, the sliding fit of the sliding mounting seat 509 and the lifting chute 301 can be utilized to finely adjust the height positions of the fixed transverse plate two 504 and the air cylinder fixing seat two 503, so that the transverse load force application rod 502 can be always perpendicular to the clamping fixing piece and apply acting force, and the detection accuracy is ensured.
As shown in fig. 6, the torque load assembly 60 includes a rotary cylinder 601, the rotary cylinder 601 is fixedly disposed at the upper end of an L-shaped bottom plate 602, an output end of the rotary cylinder 601 is connected with a torsion connection block 603, the torsion connection block 603 is fixedly connected with a positioning seat 103, and sliding limit seats 604 are disposed on two sides of the L-shaped bottom plate 602.
Specifically, when the torque test is performed, the rotary cylinder 601 drives the positioning seat 103 to rotate through the torsion connection block 603, the positioning seat 103 directly transmits the rotation torque to the end part of the blade body 101, the torque applied is monitored in real time through the torque sensor, and the torsion deformation degree of the end part of the blade body 101 is monitored through the pressure sensor or the displacement sensor, so that the torsion fatigue performance of the blade body 101 is tested.
As shown in fig. 6, the centrifugal tension load assembly 70 includes a fixed bottom plate 701 and a stretching cylinder 702, the stretching cylinder 702 is fixedly arranged in a cylinder seat 703, the cylinder seat 703 is fixedly arranged on the fixed bottom plate 701, the output end of the stretching cylinder 702 is connected with a tension load force applying rod 704, the tension load force applying rod 704 is fixedly connected with an L-shaped bottom plate 602, two sides of the upper end of the fixed bottom plate 701 are provided with linear guide rails 705, and the sliding limit seat 604 is in sliding fit with the linear guide rails 705.
Specifically, when the centrifugal tension test is performed, the tension cylinder 702 applies a tension load to the L-shaped bottom plate 602 through the tension load force applying rod 704, the L-shaped bottom plate 602 directly transmits the tension load to the blade body 101, and meanwhile, the L-shaped bottom plate 602 can directly move on the linear guide rail 705 through the sliding limiting seat 604, so that the purpose of testing the tensile fatigue degree of the blade body 101 under the centrifugal force is achieved.
The working principle of the invention is as follows: when the blade body 101 and the hub 10 are supported and fixed through the center positioning table 102 during use, the clamping fixing piece 20 is used as a stress carrier, load can be directly transmitted to the blade body 101, the longitudinal load component 40 can apply load on the vertical direction to the blade body 101, the transverse load component 50 component can apply load on the horizontal direction to the blade body 101, when the position of the load applied to the blade body 101 needs to be adjusted, only the corresponding clamping block 201 needs to be detached and replaced, and meanwhile, the longitudinal load component 40 and the transverse load component 50 can linearly move according to different clamping positions of the clamping block 201 on the blade body 101, so that the application of longitudinal load and transverse load to different positions of the blade body 101 is realized.
When the torque test is performed, the rotary cylinder 601 drives the positioning seat 103 to rotate through the torsion connecting block 603, the positioning seat 103 directly transmits the rotation torque to the end part of the blade main body 101, the torque applied is monitored in real time through the torque sensor, and the torsion deformation degree of the end part of the blade main body 101 is monitored through the pressure sensor or the displacement sensor, so that the torsion fatigue performance of the blade main body 101 is tested.
When the centrifugal tension test is performed, the tension cylinder 702 applies tension load to the L-shaped bottom plate 602 through the tension load force application rod 704, the L-shaped bottom plate 602 directly transmits the tension load to the blade main body 101, and meanwhile, the whole L-shaped bottom plate 602 can directly move on the linear guide rail 705 through the sliding limiting seat 604, so that the purpose of testing the tension fatigue degree of the blade main body 101 under the centrifugal force is achieved.
The foregoing describes one embodiment of the present invention in detail, but the description is only a preferred embodiment of the present invention and should not be construed as limiting the scope of the invention. All equivalent changes and modifications within the scope of the present invention are intended to be covered by the present invention.
Claims (8)
1. The utility model provides a screw blade fatigue test equipment, includes oar hub (10) and evenly fix a plurality of blade main part (101) that set up in oar hub (10) outside, oar hub (10) are supported fixedly through central location platform (102), a serial communication port, be provided with centre gripping mounting (20) on every blade main part (101), the periphery of centre gripping mounting (20) is provided with detection support (30), the top of detection support (30) is provided with longitudinal load subassembly (40), one side of detection support (30) is provided with transverse load subassembly (50), longitudinal load subassembly (40) are connected with centre gripping mounting (20) respectively with transverse load subassembly (50), the one end that oar hub (10) were kept away from to blade main part (101) is fixedly provided with positioning seat (103), positioning seat (103) are connected with moment load subassembly (60), moment load subassembly (60) below connect and are provided with centrifugal tension load subassembly (70), moment load subassembly (60) and centrifugal tension load subassembly (70) are all parallel to the length direction of blade main part (101);
the clamping fixture (20) comprises a pair of clamping blocks (201) which are arranged vertically oppositely, an airfoil hole (202) which is matched with the blade main body (101) is formed in the clamping blocks (201) in a penetrating mode, the inner wall of each airfoil hole (202) is always attached to the outer surface of the blade main body (101), positioning portions (203) are arranged at two ends of each clamping block (201) in an extending mode, a group of positioning portions (203) which are vertically adjacent are fixedly connected with the positioning clamping seat (205) through positioning bolts (204), the longitudinal load assembly (40) comprises a longitudinal cylinder (401), the output end of the longitudinal cylinder (401) is connected with a longitudinal load force application rod (402), the longitudinal load force application rod (402) is fixedly connected with the clamping blocks (201) at the upper end, the transverse load assembly (50) comprises a transverse cylinder (501), the output end of each transverse cylinder (501) is connected with one side of the corresponding positioning clamping seat (205), and the longitudinal load assembly (40) and the blade main body (201) are subjected to linear movement in parallel to the clamping direction of the blade main body (101).
2. The propeller blade fatigue test device according to claim 1, wherein the longitudinal load assembly (40) further comprises a first cylinder fixing seat (403), a first fixed transverse plate (404) and a first moving frame (405), the longitudinal cylinder (401) is vertically and fixedly arranged in the first cylinder fixing seat (403), the first cylinder fixing seat (403) is fixedly connected with the first moving frame (405) through a first connecting block (406), a first transverse moving gear (407) is rotatably mounted on the first moving frame (405), a first driving motor (408) is fixedly arranged on the outer side of the first moving frame (405), the output end of the first driving motor (408) is connected with the first transverse moving gear (407), the top end of the first fixed transverse plate (404) is fixedly arranged on the top end of the detecting bracket (30) through a fixed mounting seat (409), the first transverse moving bottom of the first fixed transverse plate (404) is provided with a first transverse moving gear (410) along the length direction, and the first transverse moving gear (407) is meshed with the first tooth groove (410).
3. The propeller blade fatigue test apparatus according to claim 2, wherein two sides of the top end of the first moving frame (405) are provided with a first clamping support portion (4051), two sides of the upper end of the first fixed transverse plate (404) are provided with a first clamping support chute (4041), and the first clamping support portion (4051) is adapted to be slidably mounted in the first clamping support chute (4041).
4. The propeller blade fatigue test device according to claim 1, wherein the transverse load assembly (50) further comprises a cylinder fixing seat two (503), a fixing transverse plate two (504) and a moving frame two (505), the transverse cylinder (501) is horizontally and fixedly arranged in the cylinder fixing seat two (503), the cylinder fixing seat two (503) is fixedly connected with the moving frame two (505) through a connecting block two (506), a transverse moving gear two (507) is rotatably mounted on the moving frame two (505), a driving motor two (508) is fixedly arranged at the bottom of the moving frame two (505), the output end of the driving motor two (508) is connected with the transverse moving gear two (507), one side of the fixing transverse plate two (504) is slidably mounted on one side of the detecting bracket (30) through a sliding mounting seat (509), the transverse moving other side of the fixing transverse plate two (504) is provided with a tooth groove two (510) along the length direction, and the gear two (507) is in toothed fit with the tooth groove two (510).
5. The propeller blade fatigue test apparatus according to claim 4, wherein the second movable frame (505) has a second clamping support portion (5051) at an end, the second fixed cross plate (504) has a second clamping support chute (5041) on a side wall thereof, and the second clamping support chute (5041) is adapted to be slidably mounted in the second clamping support chute (5041).
6. The propeller blade fatigue test device according to claim 5, wherein a lifting chute (301) is provided on a side wall of the detection bracket (30), the sliding mounting seat (509) is slidably matched with the lifting chute (301), and the sliding mounting seat (509) is connected with the detection bracket (30) through a fixing bolt when moving to a specified height along the lifting chute (301).
7. The propeller blade fatigue test device according to claim 1, wherein the torque load assembly (60) comprises a rotary cylinder (601), the rotary cylinder (601) is fixedly arranged at the upper end of an L-shaped bottom plate (602), the output end of the rotary cylinder (601) is connected with a torsion connecting block (603), the torsion connecting block (603) is fixedly connected with a positioning seat (103), and sliding limiting seats (604) are arranged on two sides of the L-shaped bottom plate (602).
8. The propeller blade fatigue test device according to claim 7, wherein the centrifugal tension load assembly (70) comprises a fixed bottom plate (701) and a stretching cylinder (702), the stretching cylinder (702) is fixedly arranged in a cylinder seat (703), the cylinder seat (703) is fixedly arranged on the fixed bottom plate (701), the output end of the stretching cylinder (702) is connected with a tension load force application rod (704), the tension load force application rod (704) is fixedly connected with an L-shaped bottom plate (602), linear guide rails (705) are arranged on two sides of the upper end of the fixed bottom plate (701), and the sliding limit seat (604) is in sliding fit with the linear guide rails (705).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310641920.0A CN116358860B (en) | 2023-06-01 | 2023-06-01 | Propeller blade fatigue test equipment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310641920.0A CN116358860B (en) | 2023-06-01 | 2023-06-01 | Propeller blade fatigue test equipment |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN116358860A true CN116358860A (en) | 2023-06-30 |
| CN116358860B CN116358860B (en) | 2023-08-11 |
Family
ID=86905500
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310641920.0A Active CN116358860B (en) | 2023-06-01 | 2023-06-01 | Propeller blade fatigue test equipment |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116358860B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116734702A (en) * | 2023-08-07 | 2023-09-12 | 江苏烨培干燥工程有限公司 | Screw blade continuous detection equipment for blade dryer |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR20100079680A (en) * | 2008-12-31 | 2010-07-08 | 한국항공우주연구원 | Apparatus for testing helicopter rotor blade fatigue |
| EP2241873A2 (en) * | 2009-04-15 | 2010-10-20 | Rolls-Royce Plc | Apparatus and method for simulating lifetime of and/or stress experienced by a rotor blade and rotor disc fixture |
| CN103743556A (en) * | 2013-12-20 | 2014-04-23 | 西安交通大学 | Testing apparatus for steam turbine blade with shroud ring and boss lashing wire structures |
| US20190094104A1 (en) * | 2016-03-22 | 2019-03-28 | Vestas Wind Systems A/S | Fatigue testing of a wind turbine blade |
| CN113670739A (en) * | 2021-08-17 | 2021-11-19 | 无锡瑞来检测科技有限公司 | Helicopter main rotating blade fatigue test device |
| CN215851966U (en) * | 2021-03-25 | 2022-02-18 | 安徽羲禾航空科技有限公司 | Blade fatigue test device for propeller |
| CN114166489A (en) * | 2021-11-23 | 2022-03-11 | 中国直升机设计研究所 | Loading test device of rigid main propeller hub connecting piece |
| CN216247153U (en) * | 2021-10-25 | 2022-04-08 | 北京航景创新科技有限公司 | Paddle static force testing device |
| CN218411653U (en) * | 2022-10-19 | 2023-01-31 | 保定华翼风电叶片研究开发有限公司 | Wind power blade fatigue test loading device based on use of linear motor |
-
2023
- 2023-06-01 CN CN202310641920.0A patent/CN116358860B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR20100079680A (en) * | 2008-12-31 | 2010-07-08 | 한국항공우주연구원 | Apparatus for testing helicopter rotor blade fatigue |
| EP2241873A2 (en) * | 2009-04-15 | 2010-10-20 | Rolls-Royce Plc | Apparatus and method for simulating lifetime of and/or stress experienced by a rotor blade and rotor disc fixture |
| CN103743556A (en) * | 2013-12-20 | 2014-04-23 | 西安交通大学 | Testing apparatus for steam turbine blade with shroud ring and boss lashing wire structures |
| US20190094104A1 (en) * | 2016-03-22 | 2019-03-28 | Vestas Wind Systems A/S | Fatigue testing of a wind turbine blade |
| CN215851966U (en) * | 2021-03-25 | 2022-02-18 | 安徽羲禾航空科技有限公司 | Blade fatigue test device for propeller |
| CN113670739A (en) * | 2021-08-17 | 2021-11-19 | 无锡瑞来检测科技有限公司 | Helicopter main rotating blade fatigue test device |
| CN216247153U (en) * | 2021-10-25 | 2022-04-08 | 北京航景创新科技有限公司 | Paddle static force testing device |
| CN114166489A (en) * | 2021-11-23 | 2022-03-11 | 中国直升机设计研究所 | Loading test device of rigid main propeller hub connecting piece |
| CN218411653U (en) * | 2022-10-19 | 2023-01-31 | 保定华翼风电叶片研究开发有限公司 | Wind power blade fatigue test loading device based on use of linear motor |
Non-Patent Citations (1)
| Title |
|---|
| 康浩，梅卫胜: "直升机复合材料尾桨叶疲劳试验研究", 南京航空航天大学学报, no. 01, pages 54 - 58 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116734702A (en) * | 2023-08-07 | 2023-09-12 | 江苏烨培干燥工程有限公司 | Screw blade continuous detection equipment for blade dryer |
| CN116734702B (en) * | 2023-08-07 | 2023-10-13 | 江苏烨培干燥工程有限公司 | Screw blade continuous detection equipment for blade dryer |
Also Published As
| Publication number | Publication date |
|---|---|
| CN116358860B (en) | 2023-08-11 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN116358860B (en) | Propeller blade fatigue test equipment | |
| CN105486594A (en) | Rubber material tension-torsional fatigue combined testing machine | |
| CN113138115B (en) | Full-size marine pipeline resonance rotation bending fatigue testing machine | |
| CN113466037B (en) | Integrated tester for dynamic and static mechanical properties of clamp and application method thereof | |
| CN210802890U (en) | Testing device | |
| CN117054264A (en) | Metal diaphragm fatigue simulation testing machine | |
| CN113324851A (en) | Multifunctional metal pull rod testing device | |
| CN219348200U (en) | Fatigue test equipment for automotive suspension system | |
| CN111017685B (en) | Clamp for elevator traction machine test and clamping method thereof | |
| CN112710419A (en) | Tension and torque testing device of unmanned aerial vehicle test bench | |
| CN216954933U (en) | Measuring device | |
| CN115791443A (en) | Bending test instrument for high-insulation composite material | |
| CN216847225U (en) | Tension-torsion composite testing machine | |
| CN215851966U (en) | Blade fatigue test device for propeller | |
| CN113959687A (en) | Adjustable ball head assembly testing mechanism for automobile chassis | |
| CN203881533U (en) | Chain tensioner test bench | |
| CN113390356A (en) | Full-automatic multi-parameter measuring equipment and using method thereof | |
| CN215677565U (en) | Motor load testing device | |
| CN219871475U (en) | New forms of energy motor test equipment | |
| CN215003428U (en) | Precision measurement testing fixture for automobile crankshaft journal | |
| CN217034034U (en) | Quick detection device is used in electric wire circuit maintenance | |
| CN214217392U (en) | Pneumatic clamping device | |
| CN215811623U (en) | A accredited testing organization for detecting high speed reducer special bearing intensity that bears | |
| CN220583258U (en) | Test fixture of external rotor generator | |
| CN221484736U (en) | Crankshaft dynamic balance performance detection device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |