A propeller blade fatigue test device

Abstract

The present invention discloses a propeller blade fatigue test device, including a blade root holding end flange and a blade tip load loading device, wherein the propeller blade root is fixed to the blade root holding end flange, and the blade tip is fixed to the blade tip load loading device; the blade tip load loading device includes a device housing, a central cylinder, a cylindrical pull rope, a crossbeam, and an actuator connector. The device of the present invention fixes the blade root on the test bench through the blade root holding end flange, and the main loading load of the blade tip has three main components, including the centrifugal force in the blade axis direction, the aerodynamic force in the vertical direction, and the loading torque acting on both sides, which can truly simulate the force condition of the blade. The test device is simple to operate, has good safety, strong load-bearing capacity, accurate blade loading, avoids concentrated stress, conforms to actual working conditions, and fully meets the requirements of fatigue testing.

Description

Technical Field

[0001] The invention relates to the field of testing devices, and more particularly to a propeller blade fatigue testing device. Background Art

[0002] During the use of engineering structures, they are subjected to alternating loads and fatigue damage will occur. In order to ensure their safety, their fatigue performance needs to be tested. For example, as one of the most critical components of an aircraft, propeller blades are subjected to complex cyclic alternating loads for a long time. Therefore, the performance of propeller blades directly affects the overall performance of the aircraft and is also related to flight safety. At present, the effective way to solve this problem is to obtain the fatigue performance of the blades through fatigue testing.

[0003] However, the existing propeller blade fatigue test equipment has limited load-bearing capacity, the load application points are relatively concentrated, there is a deviation from the actual working conditions of the blades, and the structure is complex.

[0004] Therefore, it is necessary to specifically analyze the working principle and fatigue test requirements of propeller blades and design a fatigue test device to solve the above technical problems. Summary of the invention

[0005] In view of this, the present invention provides a propeller blade fatigue test device, and its specific technical solution is as follows:

[0006] A propeller blade fatigue test device, comprising a blade root holding end flange and a blade tip load loading device, the blade root holding end flange is fixed to a test bench, and the propeller blade root is fixed to the blade root holding end flange, and the blade tip is fixed to the blade tip load loading device; the blade tip load loading device comprises a device shell, a central cylinder, a cylinder pull rope, a crossbeam and an actuator cylinder connector, the interior of the device shell is a hollow structure, the central cylinder is arranged inside the device shell, and is fixed to the blade tip extending into the device shell; the cylinder pull rope is fixed to the central cylinder away from the propeller one side of the blade tip; there are two crossbeams, and the direction in which the blade tip extends is defined as the front end, then the two crossbeams are respectively arranged on the left and right sides of the device housing, and the axial direction of the crossbeam is perpendicular to the axial direction of the blade; the ends of the two crossbeams extend into the interior of the device housing and are respectively fixed to the two sides of the blade tip; each of the two crossbeams is provided with a force loading device, and the corresponding forces loaded on the crossbeam by the two force loading devices are upward and downward respectively; the actuator connector is vertically fixed to the upper surface of the device housing to drive the blade tip load loading device and the blade to realize up and down swing in the vertical direction.

[0007] By adopting the above technical scheme, the present invention provides a propeller blade fatigue test device, which fixes the root of the blade on the test bench through the flange plate at the root holding end of the blade, and the main loading load at the tip of the blade has three main components, including the centrifugal force in the direction of the blade axis, the aerodynamic force in the vertical direction, and the loading torque acting on both sides.

[0008] The device of the present invention can realistically simulate the stress conditions of the blades, including the centrifugal force of the blades themselves, aerodynamic torque, centrifugal torque, aerodynamic force, etc. The test device is simple to operate, has good safety, strong bearing capacity, can load a large load, accurately loads the blades, avoids concentrated stress, conforms to actual working conditions, and fully meets the requirements of fatigue tests, and has great practical application value for fatigue tests and life assessment of blades.

[0009] Preferably, the device housing and the central cylinder are both steel structures, and the cylinder pull rope is a steel wire rope.

[0010] Preferably, the crossbeam is divided into a first crossbeam and a second crossbeam, the first crossbeam is provided with a first force loading device, and the second crossbeam is provided with a second force loading device; the first force loading device includes a pulley arranged above the first crossbeam and a first tension rope with one end arranged on the upper surface of the first crossbeam, the other end of the first tension rope hangs down after passing through the slide groove of the pulley, and a first hook is correspondingly arranged at the end; the second force loading device includes a second tension rope with one end arranged on the lower surface of the second crossbeam, the other end of the second tension rope hangs down, and a second hook is correspondingly arranged at the end.

[0011] By pulling the first hook and the second hook downwards, or hanging weights of corresponding weights on the first hook and the second hook, torque can be loaded on both sides of the blade.

[0012] Preferably, the first tension rope and the second tension rope are both steel wire ropes.

[0013] Preferably, the position of the first tension rope on the upper surface of the first beam is adjustable, and the position of the second tension rope on the lower surface of the second beam is adjustable, so as to perform targeted adjustment on the size of the load applied on both sides of the paddle tip load loading device.

[0014] Preferably, the bottom of the actuator connector is connected to the device housing via a base and screws.

[0015] Preferably, the area of ​​the base is not less than 30% of the upper surface of the device housing, so as to achieve loading a larger load on the upper part of the paddle tip load loading device.

[0016] Preferably, the base is petal-shaped.

[0017] Preferably, the blade root holding end flange is a steel structure, the end face of which is provided with no less than 10 screws, a circular hole is opened in the center, and the shape of the blade root holding end flange is square, circular or elliptical.

[0018] Preferably, the crossbeam is a steel structure with a length of not less than 500 mm, so as to achieve torque loading on the blades and load a larger load on both sides of the load loading device at the tip of the propeller. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the provided drawings without paying creative work.

[0020] Figure 1 It is a schematic diagram of the overall structure of the present invention.

[0021] In the figure: 1-blade root holding end flange, 2-device housing, 3-center cylinder, 4-cylindrical pull rope, 5-actuator connector, 6-first crossbeam, 7-second crossbeam, 8-pulley, 9-first tension rope, 10-first hook, 11-second tension rope, 12-second hook, 13-base, 14-blade. DETAILED DESCRIPTION

[0022] Embodiments of the present invention are described in detail below, examples of which are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are intended to be used to explain the present invention, and should not be construed as limiting the present invention.

[0023] Example:

[0024] like Figure 1 As shown, an embodiment of the present invention provides a propeller blade fatigue test device, including a blade root holding end flange 1 and a blade tip load loading device.

[0025] The blade root holding end flange 1 is fixed on the test bench, and the root of the propeller blade 14 is fixed to the blade root holding end flange 1, and the tip of the blade 14 is fixed to the blade tip load loading device.

[0026] Furthermore, the blade root holding end flange 1 is a steel structure, and its end face is provided with no less than 10 M16 screws, a round hole is opened in the center, and the outer shape of the blade root holding end flange 1 is not limited, and can be square, round or oval, etc.

[0027] The blade tip load loading device includes a device housing 2, a central cylinder 3, a cylinder pull rope 4, a crossbeam and an actuator connector 5.

[0028] The interior of the device housing 2 is a hollow structure. The central cylinder 3 is arranged inside the device housing 2 and fixed to the tip of the blade 14 extending into the device housing 2. The cylindrical pull rope 4 is fixed on the side of the central cylinder 3 away from the tip of the blade 14.

[0029] Meanwhile, the device housing 2 and the central cylinder 3 are both steel structures, and the cylinder pull rope 4 is a steel wire rope.

[0030] The cylindrical pull rope 4 can realistically simulate the centrifugal force load in the axial direction of the blade 14 by pulling the central cylindrical 3 structure outward, and can further load a larger load.

[0031] There are two crossbeams, both of which are steel structures and have a length of not less than 500 mm; the direction in which the tip of the blade 14 extends is defined as the front end, and the two crossbeams are arranged on the left and right sides of the device housing 2, and the axial direction of the crossbeam is perpendicular to the axial direction of the blade 14; the ends of the two crossbeams extend into the interior of the device housing 2 and are fixed to the left and right sides of the tip of the blade 14 respectively.

[0032] A force loading device is respectively arranged on the two cross beams, and the forces loaded on the cross beams by the two force loading devices are respectively upward and downward.

[0033] Specifically, the crossbeam is divided into a first crossbeam 6 and a second crossbeam 7. A first force loading device is provided on the first crossbeam 6, and a second force loading device is provided on the second crossbeam 7. The first force loading device includes a pulley 8 provided above the first crossbeam 6 and a first tension rope 9 provided at one end on the upper surface of the first crossbeam 6. The other end of the first tension rope 9 passes through the slide groove of the pulley 8 and hangs down, and a first hook 10 is provided at the end correspondingly. The second force loading device includes a second tension rope 11 provided at one end on the lower surface of the second crossbeam 7. The other end of the second tension rope 11 hangs down, and a second hook 12 is provided at the end correspondingly. Both the first tension rope 9 and the second tension rope 11 are steel wire ropes.

[0034] In order to further optimize the above technical solution, the position of the first tension rope 9 on the upper surface of the first cross beam 6 is adjustable, and the position of the second tension rope 11 on the lower surface of the second cross beam 7 is also adjustable.

[0035] The above two force loading devices can truly simulate the combined torque on both sides of the loading blade 14 by applying forces in opposite directions to the corresponding crossbeams, and can further load a larger load.

[0036] The actuator connector 5 is vertically fixed to the upper surface of the device housing 2 to drive the blade tip load loading device and the blade 14 to achieve up and down swing in the vertical direction.

[0037] Furthermore, the bottom of the actuator connector 5 is connected to the device housing 2 through a base 13 and screws.

[0038] Furthermore, the area of ​​the base 13 of the actuator connector 5 is not less than 30% of the upper surface of the device housing 2. At the same time, the base 13 is preferably in a petal shape.

[0039] The above-mentioned actuator connector 5 structure can truly simulate the aerodynamic force and aerodynamic torque of loading the blade 14 in the vertical direction by continuously doing work, and can further load a larger load.

[0040] Therefore, the device of the present invention can realistically simulate the stress conditions of the blade 14, including the centrifugal force of the blade 14 itself, aerodynamic torque, centrifugal torque, aerodynamic force, etc. The test device has good safety, strong carrying capacity, can load a large load, accurately loads the blade 14, is easy to operate, fully meets the requirements of fatigue testing, and has great practical application value for fatigue testing and life evaluation of the blade 14.

[0041] The above description of the disclosed embodiments enables one skilled in the art to implement or use the present invention. Various modifications to these embodiments will be apparent to one skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the present invention. Therefore, the present invention will not be limited to the embodiments shown herein, but rather to the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A propeller blade fatigue test device, characterized in that: The invention comprises a blade root holding end flange (1) and a blade tip load loading device, wherein the blade root holding end flange (1) is fixed on a test bench, and the root of a propeller blade (14) is fixed to the blade root holding end flange (1), and the tip of the blade (14) is fixed to the blade tip load loading device; the blade tip load loading device comprises a device housing (2), a central cylinder (3), a cylinder pull rope (4), a crossbeam and an actuator cylinder connector (5), the interior of the device housing (2) is a hollow structure, the central cylinder (3) is arranged inside the device housing (2) and is fixed to the tip of the blade (14) extending into the interior of the device housing (2); the cylinder pull rope (4) is fixed to the central cylinder (3) at a distance from the center cylinder (3) The cross beams are arranged on the side away from the tip of the blade (14); two cross beams are arranged, and the direction in which the tip of the blade (14) extends is defined as the front end, and the two cross beams are arranged on the left and right sides of the device housing (2), and the axial direction of the cross beam is perpendicular to the axial direction of the blade (14); the ends of the two cross beams extend into the interior of the device housing (2) and are respectively fixed to the two sides of the tip of the blade (14); a force loading device is respectively arranged on the two cross beams, and the forces loaded on the cross beams by the two force loading devices are respectively upward and downward; the actuator connector (5) is vertically fixed to the upper surface of the device housing (2) to drive the blade tip load loading device and the blade (14) to realize up and down swinging in the vertical direction.

2. A propeller blade fatigue test device according to claim 1, characterized in that: The device housing (2) and the central cylinder (3) are both steel structures, and the cylinder pull rope (4) is a steel wire rope.

3. A propeller blade fatigue testing device according to claim 1, characterized in that: The crossbeam is divided into a first crossbeam (6) and a second crossbeam (7), the first crossbeam (6) being provided with a first force loading device, and the second crossbeam (7) being provided with a second force loading device; the first force loading device comprises a pulley (8) arranged above the first crossbeam (6) and a first tension rope (9) having one end arranged on the upper surface of the first crossbeam (6), the other end of the first tension rope (9) passing through the slide groove of the pulley (8) and then hanging down, and a first hook (10) is correspondingly arranged at the end; the second force loading device comprises a second tension rope (11) having one end arranged on the lower surface of the second crossbeam (7), the other end of the second tension rope (11) hanging down, and a second hook (12) is correspondingly arranged at the end.

4. A propeller blade fatigue testing device according to claim 3, characterized in that: The first tension rope (9) and the second tension rope (11) are both steel wire ropes.

5. A propeller blade fatigue testing device according to claim 3 or 4, characterized in that: The position of the first tension rope (9) on the upper surface of the first crossbeam (6) is adjustable, and the position of the second tension rope (11) on the lower surface of the second crossbeam (7) is adjustable.

6. A propeller blade fatigue test device according to claim 1, characterized in that: The bottom of the actuator connector (5) is connected to the device housing (2) via a base (13) and screws.

7. A propeller blade fatigue test device according to claim 6, characterized in that: The area of ​​the base (13) is not less than 30% of the upper surface of the device housing (2).

8. A propeller blade fatigue test device according to claim 6 or 7, characterized in that: The base (13) is in the shape of a petal.

9. A propeller blade fatigue testing device according to claim 1, characterized in that: The blade root holding end flange (1) is a steel structure, with no less than 10 screws provided on its end surface and a round hole provided at the center. The blade root holding end flange (1) is in the shape of a square, a circle or an ellipse.

10. A propeller blade fatigue testing device according to claim 1, characterized in that: The crossbeam is a steel structure with a length of not less than 500 mm.

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