Engine pitch angle adjusting device and adjusting method

Abstract

The invention relates to an engine pitch angle adjusting device and method. The engine propeller pitch angle adjusting device comprises a propeller fan cap cover, a propeller pitch angle measuring device, propeller fan blades, a propeller pitch joint adjusting device, a propeller fan installation hub and a propeller fan input shaft. The propeller pitch joint adjusting device comprises a rocker arm, a linkage disc and a locking device. According to the propeller pitch joint adjusting device, the propeller pitch angles of the whole row of propeller fan blades are adjusted, measured and locked at the same time through the linkage disc and the multiple rocker arms, high adjusting efficiency and reliability are achieved, and the propeller pitch joint adjusting device has great significance in improving the test efficiency and the consistency of the propeller pitch angles of the whole row of propeller fan blades.

Description

Technical Field

[0001] The invention relates to the field of aviation engines, and in particular to an engine pitch angle adjustment device and an adjustment method. Background Art

[0002] The propfan engine adjusts the pitch angle of the propfan blades through the variable pitch mechanism, so that the fan blades in different working conditions work at the appropriate incoming flow angle, improve working efficiency, and reduce the fuel consumption rate of the engine. In the working state, the propfan blades are affected by centrifugal torque, aerodynamic torque and friction torque. The variable pitch mechanism needs to overcome these external loads to drive the propfan to change pitch. In the process of designing the propfan blade type, speed and pitch angle, fluid simulation analysis will be used to determine these design parameters first to achieve the required thrust, efficiency and noise indicators, but ultimately propfan performance tests are required to correct, confirm and verify.

[0003] Some large open propfan engines are tested on scaled test pieces during performance testing. Due to the small internal space of the scaled test piece, it is sometimes impossible to install a variable pitch mechanism for pitch adjustment. At this time, it is necessary to adjust the pitch of each blade, measure and confirm the pitch angle, and lock the pitch angle, which is very inefficient. In particular, modern propfans have many blades (many open propfans have more than 10 blades) and complex performance conditions. In a performance test of a propfan, dozens or hundreds of conditions are often involved, which means that a lot of time will be spent on pitch adjustment and measurement, wasting a lot of precious test resources. At the same time, the process of measuring the pitch angle and locking one by one will cause a certain dispersion of the pitch angle of the entire row of blades. Therefore, it is necessary to design a simple and reliable pitch joint adjustment mechanism that can adjust, measure and lock the pitch angle of the entire row of blades at one time, which is of great significance for improving test efficiency and the consistency of the pitch angle of the entire row of propfan blades.

[0004] When testing the propfan performance of a propfan engine, due to space limitations and other factors, there is often no variable pitch mechanism or pitch joint adjustment device inside the propfan structure, resulting in a lot of time wasted in the propfan blade pitch angle adjustment and measurement process. Therefore, for the propfan test process, it is necessary to design a device that can perform joint pitch adjustment and measurement, so as to achieve one-time adjustment and measurement of the pitch angle of the entire row of blades, shorten the test cycle and reduce the dispersion of the pitch angle. Summary of the invention

[0005] In view of the shortcomings of the prior art, the present invention proposes an engine pitch angle adjustment device and adjustment method. The adjustment device and adjustment method use a linkage disk plus multiple rocker arms to perform linkage adjustment, measurement and locking of the pitch angles of a whole row of propeller blades, thereby improving the efficiency and reliability of pitch angle adjustment.

[0006] On the one hand, the present invention proposes an engine pitch angle adjustment device, comprising a propeller cover, a pitch angle measuring device, a propeller blade, a pitch joint adjustment device, a propeller mounting hub and a propeller input shaft; wherein the propeller cover can be opened to adjust the pitch angle of the propeller blade; the pitch angle measuring device is used to measure the pitch angle of the propeller blade; the propeller blade is mounted on the propeller mounting hub, and the propeller blade is connected to the pitch joint adjustment device; the pitch joint adjustment device radially cooperates with the propeller mounting hub, and radial positioning support is provided by the propeller mounting hub; the propeller mounting hub is connected to the propeller input shaft Fixed installation; wherein the pitch coupling device includes a rocker arm, a linkage disk and a locking device; the rocker arm abuts against the inner side of the propeller fan mounting hub and is connected to the root of the propeller fan blade, and the number of the rocker arms is consistent with the number of the propeller fan blades; the linkage disk overlaps the propeller fan mounting hub and the linkage disk is connected to the rocker arm, and the linkage disk is sleeved on the propeller fan input shaft and is threadedly matched with the propeller fan input shaft, when the linkage disk rotates on the propeller fan input shaft to achieve axial movement, it can drive the rocker arm to rotate to adjust the pitch angle; the locking device is used to lock the linkage disk.

[0007] Furthermore, the rocker arm includes a rocker arm disc and an eccentric pin, and the rocker arm disc is fixed to the root of the propeller fan blade; a U-shaped groove is arranged on the linkage disc, and the eccentric pin is arranged in the U-shaped groove.

[0008] Furthermore, the locking device includes a locking screw, a locking plate and a nut; the locking plate is installed on the propeller input shaft; the locking screw is arranged on the linkage plate and can lock the linkage plate by screwing the locking screw to abut against the locking plate; the nut is sleeved on the propeller input shaft and is threadedly matched with the propeller input shaft, and the nut can lock the linkage plate by screwing it to abut against the end of the linkage plate.

[0009] Furthermore, the propeller fan cap includes a left side portion and a right side portion, and the left side portion and the right side portion are detachably connected.

[0010] Furthermore, the pitch angle measuring device includes a dial mounting seat, a dial, a dial pointer and a dial pointer mounting seat; the dial mounting seat is installed on the right side of the propeller fan cap, the dial is fixed to the dial mounting seat, the dial pointer mounting seat is installed on the propeller fan blade, and the dial pointer is installed on the dial pointer mounting seat.

[0011] Furthermore, the locking disk is separately arranged from the propeller fan input shaft; a notch parallel to the axial direction is arranged on the radial outer side of the propeller fan input shaft to form a step portion, and the locking disk is sleeved on the propeller fan input shaft, and the locking disk abuts against the step portion.

[0012] Furthermore, a plurality of locking screws are arranged in the circumferential direction.

[0013] Furthermore, the linkage disk cooperates with the propeller fan input shaft thread through a fine thread, and the pitch of the fine thread is 1 mm to 2 mm.

[0014] Furthermore, the left side portion of the propeller fan cap and the right side portion of the propeller fan cap are detachably connected by bolts.

[0015] On the other hand, the present invention further provides an engine pitch angle adjustment method, which is implemented by using the above-mentioned engine pitch angle adjustment device. The specific implementation steps of the adjustment method are as follows: S1. Preparation work before pitch angle adjustment, including: (1) Open the propeller fan cover: Remove the left side of the propeller fan cover. (2) Install the pitch angle measurement device on the propeller-fan test piece, including: a) Install the dial mounting base on the right side of the propeller fan cap; b) Fix the dial on the dial mounting base; c) Install the dial pointer mounting base to the propeller blade corresponding to the dial pointer mounting base, ensuring that there is no relative movement between the dial pointer mounting base and the propeller blade; d) Install the dial pointer on the dial pointer mounting seat, adjust the dial pointer to point to the current pitch angle position of the propeller blade, and then lock it; S2. Pitch angle adjustment, including: (1) Loosen the nut to ensure that the nut does not contact the linkage plate during pitch angle adjustment; (2) Loosen the locking screw to ensure that the locking screw does not contact the locking plate during pitch angle adjustment. (3) According to the pitch angle adjustment direction, turn the linkage dial clockwise or counterclockwise and observe the position of the dial pointer. The rotation speed should be fast at the beginning. When the dial pointer approaches the target scale, slowly turn the linkage dial until the target pitch angle is reached. (4) Tighten the locking screw; (5) Tighten the nut; S3. Preparations before restarting, including: (1) Remove the dial pointer mounting base and the dial pointer mounted on the dial pointer mounting base from the propeller blade; (2) Remove the dial mounting seat and the dial mounted on the dial mounting seat from the right side of the propeller fan cap; (3) Assemble the left side of the propeller fan cap to the right side of the propeller fan cap and secure them together.

[0016] The present invention has the following beneficial effects: (1) by jointly adjusting, measuring and locking a whole row of propeller blades, the efficiency of pitch angle adjustment is greatly improved, and at the same time, the consistency of the pitch angle can be well maintained; (2) the pitch angle is adjusted by thread feeding, and the pitch angle adjustment accuracy is high; (3) the pitch angle is effectively locked by locking screws and nuts to ensure the consistency of the pitch angle during rotation; (4) the joint adjustment device has a simple structure and a small size, and can be applied to many occasions requiring pitch adjustment. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings required for use in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For those skilled in the art, other drawings can be obtained based on these drawings without creative work.

[0018] Figure 1 This is a schematic diagram of the working status of the propeller fan test piece.

[0019] Figure 2 It is a schematic diagram of the propeller-fan pitch angle linkage adjustment and measurement device.

[0020] Figure 3 This is the relationship diagram between the rocker arm swing angle and the linkage plate displacement.

[0021] Figure 4 Schematic diagram of the pitch angle measurement device.

[0022] Figure 5 The present invention is a flow chart of the implementation method of propeller-fan pitch angle linkage adjustment. DETAILED DESCRIPTION

[0023] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0024] In the description of the present invention, it should be noted that the terms "upper", "lower", "inner", "outer", "front end", "rear end", "two ends", "one end", "the other end" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply 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 limiting the present invention. In addition, the terms "first" and "second" are used for descriptive purposes only and cannot be understood as indicating or implying relative importance.

[0025] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "provided with", "connected", etc. should be understood in a broad sense. For example, "connected" can be a fixed connection or a movable connection, or a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0026] See also Figure 1 and Figure 2 The propeller fan test piece mainly includes a propeller fan cap 1, a pitch angle measuring device 2, a propeller fan blade 3, a pitch coupling device 4, a propeller fan mounting hub 5, and a propeller fan input shaft 6. The propeller fan cap 1 is divided into two parts, left and right, which are connected by bolts at the dotted line A. The pitch angle measuring device 2 is only installed on a propeller fan blade when the pitch angle is adjusted during shutdown. The propeller fan blade 3 is installed on the propeller fan mounting hub 5 through a bearing or a bushing, and is connected to the rocker arm 401 of the pitch coupling device 4; the propeller fan mounting hub 5 is fixedly installed with the propeller fan input shaft 6; the pitch coupling device 4 is radially matched with the propeller fan mounting hub 5, and is also matched with the propeller fan input shaft 6 through a thread.

[0027] The left side portion 101 and the right side portion 102 of the propeller fan cap are connected by bolts. After loosening the bolts, the left side portion 101 of the propeller fan cap can be opened to the left and removed to install the pitch angle measuring device 2 and the pitch adjustment device 4.

[0028] See also Figure 4 The pitch angle measuring device 2 includes a dial mounting seat 201, a dial 202, a dial pointer 203 and a dial pointer mounting seat 204; the dial mounting seat 201 is mounted on the right side portion 102 of the propeller fan cap, the dial 202 is fixed to the dial mounting seat 201, the dial pointer mounting seat 204 is mounted on the propeller fan blade 3, and the dial pointer 203 is mounted on the dial pointer mounting seat 204.

[0029] Continue to see Figure 2, the pitch coupling device 4 includes a rocker arm 401, a linkage disk 402, a locking screw 403, a locking disk 404, and a nut 405. The rocker arm 401 includes a rocker arm disk and an eccentric pin. The number of rocker arms is consistent with the number of propeller blades. The rocker arm 401 is fixed at the bottom of the propeller blade root, and the eccentric pin of the rocker arm 401 is matched with the U-shaped groove of the linkage disk 402. In order to improve the consistency of pitch angle adjustment, the processing and matching accuracy of the eccentric pin and the U-shaped groove are improved. The linkage disk 402 is overlapped with the propeller mounting hub 5, and radial positioning support is provided by the propeller mounting hub 5, and the linkage disk 402 is sleeved on the propeller input shaft 6 and is threadedly matched with the propeller input shaft 6. In this embodiment, the linkage disk 402 is matched with the propeller input shaft 6 through a fine thread. Optionally, the pitch of the fine thread is 1mm to 2mm to improve the accuracy of adjustment.

[0030] The locking disk 404 is installed on the propeller fan input shaft 6. In order to facilitate installation, a notch parallel to the axial direction is provided on the radial outer side of the propeller fan input shaft 6 to form a step portion. The locking disk 404 is sleeved on the propeller fan input shaft 6, and its right side abuts against the left side of the step portion of the propeller fan input shaft 6. The locking disk 404 is set separately from the propeller fan input shaft 6. This is because when the test piece is initially assembled, the propeller fan input shaft 6 needs to be installed from right to left into the propeller fan installation hub 5. By making the locking disk 404 and the propeller fan input shaft 6 into separate parts, it is convenient to install both.

[0031] When the linkage disk 402 rotates around the axial direction (X direction), the linkage disk 402 moves along the axial direction on the propeller input shaft 6, thereby driving the eccentric pin of the rocker arm 401 to rotate around the root center of the propeller blade 3, thereby changing the pitch angle of the propeller. At the same time, due to the use of fine thread transmission, the pitch is very small, and the pitch angle can be finely adjusted.

[0032] Assume that the rocker arm length is L (the rocker arm length is the distance from the eccentric pin center to the propeller blade root rotation center), the pitch is P, and the pitch angle adjustment range is α , the pitch angle adjustment range is α The corresponding rotation angle of the linkage disk 402 is θ , then according to Figure 3 have: ; ; Linkage disk 402 rotation angle three-price The corresponding average change in pitch angle is ,So: .

[0033] Assuming that the nominal diameter of the thread is 60 mm, the pitch P = 1.5 mm, the rocker arm length L = 15 mm, and the pitch angle adjustment range is 100°, then when the linkage disk 402 rotates Pitch angle changes =0.18°. It can be seen that very fine pitch angle adjustment can be achieved through thread rotation feeding.

[0034] Continue to see Figure 2 The locking screw 403 is disposed on the linkage disk 402 and can lock the linkage disk 402 by screwing the locking screw 403 to abut against the locking disk 404. When the locking screw 403 is loosened and does not contact the locking disk 404, the linkage disk 402 can be easily screwed in or out, and when the locking screw 403 is tightened and contacts the locking disk 404, the linkage disk 402 is locked. Exemplarily, a plurality of locking screws 403 are arranged in the circumferential direction, for example, 4, and have an anti-loosening function.

[0035] Nut 405 is disposed at the end of linkage disk 402, and is used to fix the linkage disk on propeller fan input shaft 6. Exemplarily, nut 405 is sleeved on propeller fan input shaft 6 and threadedly matched with propeller fan input shaft 6, and nut 405 can be screwed to abut against the end of linkage disk 402 to lock linkage disk 402.

[0036] After the pitch angle is adjusted to the desired position according to the pitch angle measuring device, the originally loosened locking screw 403 is tightened onto the locking disk 404, and finally the nut 405 is tightened, so that the pitch angle can be locked at the current position. Through the double locking of the locking screw 403 and the nut 405, when the entire test piece is rotated, the linkage disk 402 will not move forward and backward along the axial direction, and the pitch angle of the propeller blade will remain unchanged during the rotation of the engine.

[0037] The propeller fan pitch angle adjustment structure has the following characteristics: (1) The linkage disk cooperates with the rocker arm to achieve simultaneous linkage adjustment of multiple propeller blades, which improves the efficiency of pitch angle adjustment and helps to ensure the consistency of the pitch angle of the entire row of blades; (2) The linkage plate can adjust the pitch angle by feeding through fine-pitch threads, which can finely adjust the pitch angle; (3) The locking screw cooperates with the nut to achieve double locking of the thread, which can effectively ensure that the pitch angle remains unchanged during rotation; (4) The pitch angle measuring device can measure the pitch angle without disassembling the propeller fan blades.

[0038] The present invention aims at the measurement demand of propeller fan blade pitch angle adjustment, and combines Figure 5 A method for adjusting the pitch angle during a propeller fan performance test is provided. The specific steps are as follows: S1. Preparation before pitch angle adjustment (1) Open the propeller fan cap 1. Loosen the bolts connecting the left side 101 of the propeller fan cap 1 and the right side 102 of the propeller fan cap, and remove the left side 101 of the propeller fan cap to the left; (2) Install the pitch angle measuring device 2 onto the propeller-fan test piece; a) Install the scale plate mounting seat 201 on the right side 102 of the propeller fan cap; b) fixing the scale plate 202 on the scale plate mounting seat 201; c) installing the dial pointer mounting seat 204 to the propeller fan blade 3 corresponding to the dial mounting seat 201, ensuring that there is no relative movement between it and the propeller fan blade 3; d) Install dial pointer 203 onto dial pointer mounting seat 204, adjust dial pointer 203 so that it points to the current pitch angle position of the propeller blade and then lock it.

[0039] S2. Pitch angle adjustment (1) Loosen the nut 405 to ensure that the nut 405 does not contact the linkage plate 402 during the pitch angle adjustment process; (2) Loosen the locking screw 403 to ensure that the locking screw 403 does not contact the locking plate 404 during the pitch angle adjustment process; (3) According to the pitch angle adjustment direction, rotate the linkage disk 402 clockwise or counterclockwise, and observe the position of the dial pointer 203; the rotation speed is fast at the beginning, and when the dial pointer approaches the target scale, slowly rotate the linkage disk 402 until the target pitch angle is reached; (4) Tighten the locking screw 403; (5) Tighten nut 405.

[0040] S3. Preparation before restart (1) Remove the dial pointer mounting seat 204 and the dial pointer 203 thereon from the propeller blade 3; (2) Remove the scale plate mounting seat 201 and the scale plate 202 thereon from the right side portion 102 of the propeller fan cap; (3) Assemble the left side portion 101 of the propeller fan cap to the right side portion 102 of the propeller fan cap and fasten them with bolts.

[0041] It will be apparent to those skilled in the art that the invention is not limited to the details of the exemplary embodiments described above and that the invention can be implemented in other specific forms without departing from the spirit or essential features of the invention. Therefore, the embodiments should be considered exemplary and non-limiting in all respects, and the scope of the invention is defined by the appended claims rather than the foregoing description, and it is intended that all variations falling within the meaning and scope of the equivalent elements of the claims be included in the invention. Any reference numeral in a claim should not be considered as limiting the claim to which it relates.

Claims

1. An engine pitch angle adjustment device, characterized in that: It includes a propeller fan cap, a pitch angle measuring device, a propeller fan blade, a pitch joint adjusting device, a propeller fan mounting hub and a propeller fan input shaft; Wherein, the propeller fan cap can be opened to adjust the pitch angle of the propeller fan blades; The pitch angle measuring device is used to measure the pitch angle of the propeller fan blade; The propeller fan blades are mounted on the propeller fan mounting hub, and the propeller fan blades are connected to the pitch joint adjustment device; the pitch joint adjustment device is radially matched with the propeller fan mounting hub, and radial positioning support is provided by the propeller fan mounting hub; the propeller fan mounting hub is fixedly mounted to the propeller fan input shaft; Among them, the pitch adjustment device includes a rocker arm, a linkage disk and a locking device; the rocker arm abuts against the inner side of the propeller fan mounting hub and is connected to the root of the propeller fan blade, and the number of the rocker arms is consistent with the number of the propeller fan blades; the linkage disk overlaps the propeller fan mounting hub and the linkage disk is connected to the rocker arm, and the linkage disk is sleeved on the propeller fan input shaft and threadedly matched with the propeller fan input shaft, when the linkage disk rotates on the propeller fan input shaft to achieve axial movement, it can drive the rocker arm to rotate to adjust the pitch angle; the locking device is used to lock the linkage disk.

2. The engine pitch angle adjustment device according to claim 1, characterized in that: The rocker arm includes a rocker arm disc and an eccentric pin, wherein the rocker arm disc is fixed to the root of the propeller fan blade; a U-shaped groove is arranged on the linkage disc, and the eccentric pin is arranged in the U-shaped groove.

3. The engine pitch angle adjustment device according to claim 2, characterized in that: The locking device comprises a locking screw, a locking plate and a nut; The locking plate is mounted on the propeller input shaft; the locking screw is arranged on the linkage plate and can lock the linkage plate by screwing the locking screw to abut against the locking plate; the nut is sleeved on the propeller input shaft and is threadably matched with the propeller input shaft, and the nut can lock the linkage plate by screwing it to abut against the end of the linkage plate.

4. The engine pitch angle adjustment device according to claim 3, characterized in that: The propeller fan cap includes a left side portion and a right side portion, and the left side portion and the right side portion are detachably connected.

5. The engine pitch angle adjustment device according to claim 4, characterized in that: The pitch angle measuring device comprises a dial mounting seat, a dial, a dial pointer and a dial pointer mounting seat; The dial mounting seat is installed on the right side of the propeller fan cap, the dial is fixed to the dial mounting seat, the dial pointer mounting seat is installed on the propeller fan blade, and the dial pointer is installed on the dial pointer mounting seat.

6. The engine pitch angle adjustment device according to claim 3, characterized in that: The locking disk is separately arranged from the propeller fan input shaft; a notch parallel to the axial direction is arranged on the radial outer side of the propeller fan input shaft to form a step portion, the locking disk is sleeved on the propeller fan input shaft, and the locking disk abuts against the step portion.

7. The engine pitch angle adjustment device according to claim 3, characterized in that: A plurality of locking screws are arranged in the circumferential direction.

8. The engine pitch angle adjustment device according to claim 1, characterized in that: The linkage disk cooperates with the propeller fan input shaft thread through a fine thread, and the pitch of the fine thread is 1mm to 2mm.

9. The engine pitch angle adjustment device according to claim 4, characterized in that: The left side portion of the propeller fan cap and the right side portion of the propeller fan cap are detachably connected by bolts.

10. A method for adjusting an engine pitch angle, implemented by using the engine pitch angle adjustment device according to claim 5, characterized in that: The specific implementation steps of the adjustment method are as follows: S1. Preparation work before pitch angle adjustment, including: (1) Open the propeller fan cover: Remove the left side of the propeller fan cover. (2) Install the pitch angle measurement device on the propeller-fan test piece, including: a) Install the dial mounting base on the right side of the propeller fan cap; b) Fix the dial on the dial mounting base; c) Install the dial pointer mounting base to the propeller blade corresponding to the dial pointer mounting base, ensuring that there is no relative movement between the dial pointer mounting base and the propeller blade; d) Install the dial pointer on the dial pointer mounting seat, adjust the dial pointer to point to the current pitch angle position of the propeller blade, and then lock it; S2. Pitch angle adjustment, including: (1) Loosen the nut to ensure that the nut does not contact the linkage plate during pitch angle adjustment; (2) Loosen the locking screw to ensure that the locking screw does not contact the locking plate during pitch angle adjustment. (3) According to the pitch angle adjustment direction, turn the linkage dial clockwise or counterclockwise and observe the position of the dial pointer. The rotation speed should be fast at the beginning. When the dial pointer approaches the target scale, slowly turn the linkage dial until the target pitch angle is reached. (4) Tighten the locking screw; (5) Tighten the nut; S3. Preparations before restarting, including: (1) Remove the dial pointer mounting base and the dial pointer mounted on the dial pointer mounting base from the propeller blade; (2) Remove the dial mounting seat and the dial mounted on the dial mounting seat from the right side of the propeller fan cap; (3) Assemble the left side of the propeller fan cap to the right side of the propeller fan cap and secure them together.

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