An aviation propeller blade interchangeable balancing device and a matching method

Abstract

The present invention relates to an interchangeable balancing device and method for propeller blades of an aviation propeller, the device comprising: a load-bearing shaft, both ends of which are supported on a balancing frame; a torque converter mechanism that moves along the axis of the load-bearing shaft; a pull sleeve, one end of the torque converter mechanism is connected to a pull sleeve, and a bearing seat for mounting a blade shaft is arranged on the outer wall of the pull sleeve away from the torque converter mechanism; a first channel through which the load-bearing shaft passes in the middle of a propeller shell, and an open channel is arranged near the torque converter mechanism to facilitate the movement of the torque converter mechanism; two second channels are arranged on the propeller shell perpendicular to the first channel direction, which pass from the outer end of the propeller shell inward to the bearing seat; the blade shafts of a standard blade and a blade to be balanced are respectively inserted into the bearing seat through the corresponding second channels, and the ends of the blade shafts are provided with eccentric pins, which are eccentrically matched with the bearing seat. The present invention has a simple structure and high reliability, and can be directly compared with a standard blade, so that the mutual difference of the large axis torque between the blades is less than 2gm, meeting the requirements for blade interchangeability.

Description

Technical Field

[0001] The invention relates to the technical field of propellers, and more particularly to an aviation propeller blade interchangeable balancing matching device and matching method. Background Art

[0002] At present, propellers generally use composite blades and aluminum alloy hubs to reduce weight. In order to better meet the needs of field maintenance, single blades should have good interchangeability. Therefore, it is particularly important to control the large and small axis torques of the blades. The small axis torque of the blade is only related to the axial position of the blade, and the large axis torque of the blade is related to the distance of the rotation center on the hub. The weight of a single blade is about 32Kg, and an axial movement of 0.1mm will generate a torque of about 3.2gm. The small axis torque of the existing single blade can be measured by a torque scale and then adjusted and controlled. Since the torque scale cannot simulate the rotation center of the propeller at this stage, and the positioning reference and the hub do not coincide, the large axis torque generated by the symmetrical assembly on the hub of the blades with the same large axis torque value measured and adjusted by the torque scale at this stage is not consistent, and cannot meet the requirements of single blade interchangeability.

[0003] Therefore, how to design an aviation propeller blade interchangeable balancing device so that the blades can meet the large axis torque difference of less than 2gm with the standard blades and truly meet the interchangeability of single blades is an urgent problem that technical personnel in this field need to solve. Summary of the invention

[0004] To this end, an object of the present invention is to provide an aviation propeller blade interchangeable balancing device to solve the problem that the blades matched with the existing moment scale measurement cannot meet the requirements of interchangeability.

[0005] The present invention provides an aviation propeller blade interchangeable balancing device, comprising:

[0006] A load-bearing shaft, with both ends of the load-bearing shaft supported on a balancing frame;

[0007] A torque converter mechanism, the torque converter mechanism moves along the axis direction of the bearing shaft;

[0008] A pull sleeve, one end of the torque converter is connected to the pull sleeve, and a bearing seat for mounting a blade shaft is arranged on the outer wall of the pull sleeve away from the torque converter;

[0009] A propeller shell, wherein the middle portion of the propeller shell has a first passage through which the bearing shaft passes, and the first passage is provided with an open passage near the torque converter mechanism to facilitate the movement of the torque converter mechanism; the propeller shell is provided with two second passages extending from the outer end of the propeller shell inwardly to the bearing seat in a direction perpendicular to the first passage; and

[0010] A standard blade, wherein the blade shafts of the standard blade and the blade to be balanced are respectively inserted into the bearing seat through the corresponding second channels, and the ends of the blade shafts are provided with eccentric pins, and the eccentric pins are eccentrically matched with the bearing seat.

[0011] It can be seen from the above technical solution that, compared with the prior art, the present invention discloses an aviation propeller blade interchangeable balancing device with a simple structure and high reliability. It can be directly compared with the standard blades so that the mutual difference in the large axis torque between the blades is less than 2gm, thus meeting the blade interchange requirements.

[0012] Furthermore, the torque converter mechanism includes: a torque converter nut, a guide sleeve and a screw key; the torque converter nut is connected to the main shaft section of the load-bearing shaft, and its lower part is inserted into the guide sleeve; the guide sleeve can slide on the load-bearing shaft; a limiting groove is provided on the load-bearing shaft along its axial direction, and the screw key passes through the guide sleeve and slides in the limiting groove.

[0013] Furthermore, a thrust bearing is installed between the interior of the guide sleeve and the outer wall of the torque converter nut, and is stopped and limited by a stop nut.

[0014] Furthermore, a flange is extended outwardly from the outer wall of the guide sleeve, and the flange is fixed to the pull sleeve by bolts.

[0015] Furthermore, a double-row ball bearing is installed in the bearing seat, and the double-row ball bearing is eccentrically matched with the eccentric pin.

[0016] Furthermore, it also includes a positioning plate, a die is provided on the side of the paddle housing away from the open channel, the positioning plate is a convex die adapted to the concave die, and the end of the bearing shaft away from the torque converter mechanism is positioned by the mating convex die and the concave die.

[0017] Furthermore, it also includes a counterweight key, which is fixed to the propeller shell by a screw and is used for initial balance adjustment of the supporting device.

[0018] Another object of the present invention is to provide a method for exchanging and balancing aviation propeller blades, comprising the following steps:

[0019] S1. Lift the propeller housing, place both ends of the load-bearing shaft on the balancing frame, and place the standard propeller blade and the propeller blade to be balanced in a horizontal position;

[0020] S2. Initial measurement and inspection of the blade angle. At the first design angle, observe whether the balanced blade and the standard blade are balanced, and record the difference between the unbalanced amount of the blade to be balanced and the standard blade.

[0021] S3. Use a wrench to turn the pitch nut so that the guide cylinder drives the shifting sleeve to move. The movement of the shifting sleeve changes the matching position of the eccentric pin of the blade shaft relative to the bearing seat. Since the blade is installed in the second channel of the propeller shell, the blade angle changes. When the standard blade and the blade to be balanced are at the second design angle position, observe whether the balanced blade and the standard blade are balanced, and record the difference between the unbalanced amount of the blade to be balanced and the standard blade.

[0022] S4. Calculate and weigh lead bars of equal weight according to the imbalance difference between the blade to be balanced and the standard blade, disassemble the lower blade, install lead on the counterweight hole of the blade after measurement, and reinstall the blade;

[0023] S5. Repeat steps S2 and S3 to perform a second balance measurement until the static balance requirement is met, that is, a weight not greater than 2g is placed 1000mm from the blade's rotation center, which can keep the standard blade and the lead-loaded blade horizontal and motionless.

[0024] It can be seen from the above technical solution that, compared with the prior art, the present invention discloses a method for interchangeable and balancing aviation propeller blades, which solves the problem that the blades matched with the existing moment scale measurement cannot meet the requirements of interchangeability and facilitates measurement. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] 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.

[0026] Figure 1 The accompanying drawing is a partial cross-sectional view of an aviation propeller blade interchangeable balancing device provided by the present invention;

[0027] Figure 2 The accompanying drawing shows a top view of an aviation propeller blade interchangeable balancing device provided by the present invention in a testing state on a balancing frame;

[0028] In the figure:

[0029] 100-bearing shaft, 200-torque converter, 202-torque converter nut, 203-guide sleeve, 204-screw key, 205-thrust bearing, 206-stop nut, 300-shift sleeve, 301-bearing seat, 400-propeller housing, 500-standard propeller blade, 600-propeller blade to be balanced, 700-positioning plate, 800-counterweight key, P-balance frame. DETAILED DESCRIPTION

[0030] 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.

[0031] In the description of the present invention, it is necessary to understand that the terms "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating the orientation or position relationship are based on the orientation or position relationship shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention.

[0032] In the present invention, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0033] Since the existing moment scale cannot simulate the rotation center of the propeller at this stage, and the positioning reference and the hub do not coincide, the moment scale is currently used to measure and adjust the blades with consistent large axis moment values. The large axis moment generated by symmetrical assembly on the hub is not consistent, and the requirements for single blade interchangeability cannot be met. Therefore, an embodiment of the present invention provides an aircraft propeller blade interchangeable balancing device. See attached Figure 1 and 2 , specifically comprising: a load-bearing shaft 100, wherein both ends of the load-bearing shaft 100 are supported on a balancing frame P; a torque converter 200, wherein the torque converter 200 moves along the axial direction of the load-bearing shaft 100; a shifting sleeve 300, wherein one end of the torque converter 200 is connected to the shifting sleeve 300, wherein a bearing seat 301 for mounting a blade shaft is disposed on an outer wall of the shifting sleeve 300 on a side away from the torque converter 200; a propeller shell 400, wherein a first passage through which the load-bearing shaft 100 passes is disposed in the middle of the propeller shell 400, wherein an open passage is disposed near the torque converter 200 to facilitate movement of the torque converter 200; and the propeller shell 400 is provided with two second passages perpendicular to the direction of the first passage, which pass inward from the outer end of the propeller shell 400 to the bearing seat 301; and

[0034] The standard blade 500 and the blade shafts of the standard blade 500 and the blade to be balanced 600 are respectively inserted into the bearing seat 301 through the corresponding second channels. The ends of the blade shafts are provided with eccentric pins, and the eccentric pins are eccentrically matched with the bearing seat 301.

[0035] Advantageously, the torque conversion mechanism 200 comprises: a torque conversion nut 202, a guide sleeve 203 and a screw key 204; the torque conversion nut 202 is connected to the main shaft section of the bearing shaft 100, and its lower part is inserted into the guide sleeve 203; the guide sleeve 203 can slide on the bearing shaft 100; a limiting groove is provided on the bearing shaft 100 along its axial direction, and the screw key 204 passes through the guide sleeve 203 and slides in the limiting groove. The torque conversion nut is tightened by external force, and the guide sleeve is pushed to move along the axial direction of the bearing shaft. The movement of the sleeve changes the matching position of the eccentric pin of the blade shaft relative to the bearing seat. Since the blade is installed in the second channel of the blade shell, the blade angle is changed. A thrust bearing 205 is installed between the inside of the guide sleeve 203 and the outer wall of the torque conversion nut 202, and is stopped and limited by a stop nut 206.

[0036] Advantageously, a flange is extended outward from the outer wall of the guide sleeve 203, and the flange is fixed to the pull sleeve 300 by bolts.

[0037] In the embodiment of the present invention, a double-row ball bearing is installed in the bearing seat 301, and the double-row ball bearing is eccentrically matched with the eccentric pin.

[0038] In some other embodiments of the present invention, a positioning plate 700 is further included. A die is provided on the side of the paddle housing 400 away from the open channel. The positioning plate 700 is a convex die matched with the concave die. The end of the bearing shaft 100 away from the torque converter mechanism 200 is positioned by the mating convex die and the concave die. This facilitates the positioning of the support shaft.

[0039] In some other embodiments of the present invention, a counterweight key 800 is further included. The counterweight key 800 is fixed to the propeller housing 400 by screws, and balance adjustment is performed after the initial installation of the supporting device.

[0040] The present invention also provides a method for exchanging and balancing aviation propeller blades, comprising the following steps:

[0041] S1. Lift the propeller housing, place both ends of the load-bearing shaft on the balancing frame, and place the standard propeller blade and the propeller blade to be balanced in a horizontal position;

[0042] S2. Initial measurement and inspection of the blade angle. At the first design angle, observe whether the balanced blade and the standard blade are balanced, and record the difference between the unbalanced amount of the blade to be balanced and the standard blade.

[0043] When observing whether the propeller is balanced, hold the propeller still for 10 seconds and then let go. When observing whether the propeller is rotating, the propeller must be left still for at least 20 seconds.

[0044] S3. Use a wrench to turn the pitch nut so that the guide cylinder drives the shifting sleeve to move. The movement of the shifting sleeve changes the matching position of the eccentric pin of the blade shaft relative to the bearing seat. Since the blade is installed in the second channel of the propeller shell, the blade angle changes. When the standard blade and the blade to be balanced are at the second design angle position, observe whether the balanced blade and the standard blade are balanced, and record the difference between the unbalanced amount of the blade to be balanced and the standard blade.

[0045] S4. Calculate and weigh lead bars of equal weight based on the imbalance difference between the blade to be balanced and the standard blade, disassemble the lower blade, add lead to the counterweight holes of the blade after measurement, and reinstall the blade; the counterweight holes include large counterweight holes and small counterweight holes. Fill lead bars into different counterweight holes according to actual needs, and then block the lead bars with retaining rings.

[0046] S5. Repeat steps S2 and S3 to perform a second balance measurement until the static balance requirement is met, that is, a weight not greater than 2g is placed 1000mm from the blade's rotation center, which can keep the standard blade and the lead-loaded blade horizontal and motionless.

[0047] If the above steps do not meet the requirements, repeat steps S1-S5 until the requirements are met, disassemble the matching blades, mark them and set them aside for use.

[0048] Standard blades can be divided into two groups, A and B. Blades of the same group are assembled on one propeller, and other blades of the same group can be used interchangeably.

[0049] The first design angle and the second design angle are determined according to relevant parameters. In one embodiment of the present invention, the first design angle may be 0.9°, and the second design angle may be 45°.

[0050] In order to ensure the accuracy of the above measurements, they need to be carried out in a dedicated static balancing room. The assembly process of the aviation propeller blade interchangeable balancing device is as follows:

[0051] 1) Install the load-bearing shaft into the propeller housing and tighten the four nuts symmetrically and evenly with a torque of 175 N·m to 185 N·m.

[0052] 2) Adjust the outer diameter of the end teeth of the propeller shell (attached Figure 1 The runout of the outer surface of the load-bearing shaft (at point C) should be within 0.02mm.

[0053] 3) Adjust the end face of the propeller shell (attached Figure 1 The verticality between the center point A and the load-bearing axis should be within 0.02mm.

[0054] 4) Adjust the inner hole of the propeller housing (attached Figure 1 The coaxiality between point B in the middle and the load-bearing shaft should be within 0.02mm.

[0055] 5) Static balance the assembly of the propeller shell and the bearing shaft: Place the assembly of the propeller shell and the bearing shaft on the balance frame and perform static balancing on it. When the propeller shell is rotated to any position, it can remain stationary. The balance requirement can be met by adjusting the weight of the counterweight key.

[0056] 6) Install the standard blades and the blades to be balanced.

[0057] In the description of this specification, the description with reference to the terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" etc. means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described may be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art may combine and combine different embodiments or examples described in this specification.

[0058] Although the embodiments of the present invention have been shown and described above, it is to be understood that the above embodiments are exemplary and are not to be construed as limitations of the present invention. A person skilled in the art may change, modify, replace and vary the above embodiments within the scope of the present invention.

Claims

1. An aircraft propeller blade interchangeable balancing device, characterized in that: include: A load-bearing shaft (100), wherein both ends of the load-bearing shaft (100) are supported on a balancing frame (P); A torque converter mechanism (200), wherein the torque converter mechanism (200) moves along the axial direction of the bearing shaft (100); A shifting sleeve (300), one end of the torque converter mechanism (200) is connected to the shifting sleeve (300), and a bearing seat (301) for mounting a blade shaft is provided on an outer wall of the shifting sleeve (300) at a side away from the torque converter mechanism (200); A paddle shell (400), wherein the middle portion of the paddle shell (400) has a first passage through which the bearing shaft (100) passes, and the first passage is provided with an open passage near the torque converter (200) to facilitate the movement of the torque converter (200); the paddle shell (400) is provided with two second passages extending inwardly from the outer end of the paddle shell (400) to the bearing seat (301) in a direction perpendicular to the first passage; as well as A standard blade (500), wherein the blade shafts of the standard blade (500) and the blade to be balanced (600) are respectively inserted into the bearing seat (301) through the corresponding second channels, and the ends of the blade shafts are provided with eccentric pins, and the eccentric pins are eccentrically matched with the bearing seat (301); The torque conversion mechanism (200) comprises: a torque conversion nut (202), a guide sleeve (203) and a screw key (204); the torque conversion nut (202) is connected to the main shaft section of the bearing shaft (100), and the lower part thereof is inserted into the guide sleeve (203); the guide sleeve (203) can slide on the bearing shaft (100); a limiting groove is provided on the bearing shaft (100) along its axial direction, and the screw key (204) passes through the guide sleeve (203) and slides in the limiting groove; A thrust bearing (205) is installed between the interior of the guide sleeve (203) and the outer wall of the torque converter nut (202), and is stopped and limited by a stop nut (206); A flange is extended outward from the outer wall of the guide sleeve (203), and the flange is fixed to the pull sleeve (300) by bolts.

2. The aircraft propeller blade interchangeable balancing device according to claim 1, characterized in that: A double-row ball bearing is installed in the bearing seat (301), and the double-row ball bearing is eccentrically matched with the eccentric pin.

3. The aircraft propeller blade interchangeable balancing device according to claim 1, characterized in that: It also includes a positioning plate (700), a concave mold is arranged on the side of the paddle housing (400) away from the open channel, the positioning plate (700) is a convex mold adapted to the concave mold, and the end of the bearing shaft (100) away from the torque converter (200) is positioned by the mating convex mold and the concave mold.

4. An aviation propeller blade interchangeable balancing device according to any one of claims 1 to 3, characterized in that: It also includes a counterweight key (800), which is fixed to the propeller housing (400) by means of screws and is used for initial balance adjustment of the supporting device.

5. A method for matching the aircraft propeller blade interchangeable balancing matching device according to any one of claims 1 to 4, characterized in that: The following steps are involved: S1. Lift the propeller housing, place both ends of the load-bearing shaft on the balancing frame, and place the standard propeller blade and the propeller blade to be balanced in a horizontal position; S2. Initial measurement and inspection of the blade angle: At the first design angle, observe whether the blade to be balanced and the standard blade are balanced, and record the difference between the unbalanced value of the blade to be balanced and the standard blade; S3. Use a wrench to turn the pitch nut so that the guide sleeve drives the shift sleeve to move. The movement of the shift sleeve changes the matching position of the eccentric pin of the blade shaft relative to the bearing seat. Since the blade is installed in the second channel of the propeller shell, the blade angle changes. When the standard blade and the blade to be balanced are at the second design angle position, observe whether the blade to be balanced and the standard blade are balanced, and record the difference between the unbalance amount of the blade to be balanced and the standard blade. S4. Calculate and weigh lead bars of equal weight according to the imbalance difference between the blade to be balanced and the standard blade, disassemble the lower blade, install lead on the counterweight hole of the blade after measurement, and reinstall the blade; S5. Repeat steps S2 and S3 to perform a second balance measurement until the static balance requirement is met, that is, a weight not greater than 2g is placed 1000mm from the blade's rotation center, which can keep the standard blade and the lead-loaded blade horizontal and motionless.

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