An aircraft engine N1 rotor drive device

Abstract

The present application belongs to the field of aircraft engine structural design, and particularly relates to an aircraft engine N1 rotor drive device. The device comprises: a connecting ring plate, comprising an annular plate and a connecting rod connected to the annular plate and extending radially outward, a plurality of fixing screws arranged circumferentially on the inner side of the annular plate, the annular plate being sleeved on the engine air intake cap cone and connected to the process bolt holes of the engine air intake cap cone via the fixing screws; a friction wheel, the friction wheel being mounted on the end of the connecting rod away from the annular plate via an adapter plate, the friction wheel being pressed against the inner wall of the fan case, and generating a pre-compression force between the friction wheel and the inner wall of the fan case, the friction wheel being mounted with a DC reduction motor; and an electronic control system, the electronic control system comprising a drive mechanism and a remote control handle, the drive mechanism being used to control the rotation state of the DC reduction motor according to a command signal sent by the remote control handle.

Description

Technical Field

[0001] The present application relates to the field of aircraft engine structural design, and in particular to an aircraft engine N1 rotor drive device. Background Art

[0002] The appearance of the flow path components of the N1 rotor (fan blades, boost stage, and low-pressure turbine blades) of aircraft engines must be inspected regularly on-site. During the inspection, the industrial endoscope probe is inserted into the pre-installed inspection hole on the casing, and the N1 rotor is rotated to check the status of all blades around the entire circumference of each rotor stage.

[0003] The current method of rotating the N1 rotor during inspection is: the N1 rotation personnel manually stand in the aircraft air inlet and, according to the instructions of the flow path inspector, manually turn the large fan blades to drive the N1 rotor to rotate.

[0004] This approach has the following shortcomings:

[0005] 1. After the engine is installed on the aircraft, it is 3 meters in the air. The operator squats at the engine inlet to operate the N1. The wind is strong, cold in winter and hot in summer. The inspection lasts for a long time, the working surface is high, and the labor intensity is high. Endoscopic inspection requires close communication between the driver and the endoscope inspector to avoid interference from surrounding noise.

[0006] 2. During endoscopic inspection, especially when tracking damaged blades, it is necessary to frequently change the N1 rotation state. The existing inspection method is difficult to find damaged blades and the workload is large.

[0007] Therefore, it is desired to have a technical solution to overcome or at least alleviate at least one of the above-mentioned deficiencies of the prior art. Summary of the Invention

[0008] The purpose of this application is to provide an aircraft engine N1 rotor drive device to solve at least one problem existing in the prior art.

[0009] The technical solution of this application is:

[0010] An aircraft engine N1 rotor drive device, comprising:

[0011] A connecting ring plate, comprising an annular plate and a connecting rod connected to the annular plate and extending radially outward, a plurality of fixing screws arranged circumferentially on the inner side of the annular plate, the annular plate being sleeved on the engine air intake cap cone and connected to the process bolt holes of the engine air intake cap cone via the fixing screws;

[0012] a friction wheel, the friction wheel being mounted on an end of the connecting rod away from the annular plate via an adapter plate, the friction wheel being pressed against the inner wall of the fan casing, and generating a pre-compression force between the friction wheel and the inner wall of the fan casing, and a DC reduction motor being mounted on the friction wheel;

[0013] The electronic control system includes a drive mechanism and a remote control handle. The drive mechanism is used to control the rotation state of the DC reduction motor according to the command signal sent by the remote control handle.

[0014] In at least one embodiment of the present application, the connecting ring plate is a flexible polyurethane plate.

[0015] In at least one embodiment of the present application, three fixing screws are arranged at equal intervals along the circumferential direction on the inner side of the annular plate.

[0016] In at least one embodiment of the present application, the friction wheel is made of rubber.

[0017] In at least one embodiment of the present application, the driving mechanism is installed at the connection between the annular plate of the connecting ring plate and the connecting rod.

[0018] In at least one embodiment of the present application, the driving mechanism includes a first wireless transceiver module, a motor driver module, a DC power supply module and a counting module, wherein:

[0019] The first wireless transceiver module is used to realize data transmission between the driving mechanism and the remote control handle;

[0020] The motor driver module is used to control the rotation state of the DC reduction motor according to the command signal sent by the remote control handle;

[0021] The DC power supply module is used to provide power;

[0022] The counting module is used to count the rotation angle of the N1 rotor.

[0023] In at least one embodiment of the present application, the counting module collects the number of rotations n of the friction wheel, converts the number of rotations n of the friction wheel into the number of rotations N of the N1 rotor, and obtains the rotation angle of the N1 rotor according to the number of rotations N of the N1 rotor;

[0024] The conversion relationship between the number of rotations n of the friction wheel and the number of rotations N of the N1 rotor is:

[0025]

[0026] Among them, r is the radius of the friction wheel, and R is the radius of the fan casing.

[0027] In at least one embodiment of the present application, the remote control handle includes a second wireless transceiver module, a command module and an N1 display module, wherein:

[0028] The second wireless transceiver module is used to realize data transmission between the remote control handle and the driving mechanism;

[0029] The instruction module is used to generate an instruction signal;

[0030] The N1 display module is used to display the rotation angle of the N1 rotor.

[0031] The invention has at least the following beneficial technical effects:

[0032] The aircraft engine N1 rotor drive device of the present application can avoid and solve the inconvenience and problems that occur in the N1 rotor drive operation of the engine endoscopy inspection. It can drive smoothly, reverse, start and stop by inching, and integrate functions such as angle counting and positioning. In addition, only one industrial endoscope inspector is needed to realize endoscopy inspection and N1 drive, meet the positioning of each blade when checking each level of blades, and replace manual operation of squatting in the air inlet. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] Figure 1 This is a front view of an aircraft engine N1 rotor drive device according to one embodiment of the present application;

[0034] Figure 2 This is a side view of an aircraft engine N1 rotor drive device according to one embodiment of the present application;

[0035] Figure 3 This is a schematic diagram of the engine fan inlet structure according to one embodiment of the present application;

[0036] Figure 4 This is an assembly diagram of an aircraft engine N1 rotor drive device according to one embodiment of the present application;

[0037] Figure 5 This is a schematic diagram of the electronic control system of the aircraft engine N1 rotor drive device according to one embodiment of the present application;

[0038] Figure 6 This is a working principle diagram of the aircraft engine N1 rotor drive device according to one embodiment of the present application.

[0039] in:

[0040] 1-Connecting ring plate; 2-Drive mechanism; 3-Friction wheel; 4-DC reduction motor; 5-Fixing screw; 6-Adapter plate. DETAILED DESCRIPTION

[0041] In order to make the purpose, technical solutions and advantages of the implementation of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below in conjunction with the drawings in the embodiments of this application. In the drawings, the same or similar reference numerals throughout represent the same or similar elements or elements with the same or similar functions. The described embodiments are part of the embodiments of this application, not all of the embodiments. The embodiments described below with reference to the drawings are exemplary and are intended to be used to explain this application, and should not be understood as limitations on this application. Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application. The embodiments of this application are described in detail below in conjunction with the drawings.

[0042] In the description of this application, it should be understood that the terms "center", "longitudinal", "lateral", "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 accompanying drawings, and are only for the convenience of describing this application 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. Therefore, it should not be understood as limiting the scope of protection of this application.

[0043] The following is combined with Figures 1 to 6 This application is described in further detail.

[0044] The present application provides an aircraft engine N1 rotor drive device, comprising: a connecting ring plate 1, a friction wheel 3 and an electronic control system.

[0045] like Figure 1-2 As shown, the connecting ring plate 1 includes an annular plate and a connecting rod connected to the annular plate and extending radially outward. Multiple fixing screws 5 are arranged circumferentially on the inner side of the annular plate. The annular plate is sleeved onto the engine air intake cone and connected to the process bolt holes of the engine air intake cone via the fixing screws 5. The friction wheel 3 is mounted on the end of the connecting rod away from the annular plate via an adapter plate 6. The friction wheel 3 is pressed against the inner wall of the fan casing, and a pre-compression force is generated between the friction wheel 3 and the inner wall of the fan casing. A DC reduction motor 4 is mounted on the friction wheel 3, which can drive the friction wheel 3 to rotate. When the friction wheel 3 rotates, the connecting ring plate 1 rotates, and in turn, the N1 rotor rotates. The electronic control system includes a drive mechanism 2 and a remote control handle. The drive mechanism 2 is used to control the rotation state of the DC reduction motor 4 according to the command signal sent by the remote control handle.

[0046] In the preferred embodiment of this application, the connecting ring plate 1 is a flexible polyurethane plate that deforms upon installation, thereby generating a pre-compression force between the friction wheel 3 and the inner wall of the fan case. In this embodiment, three fixing screws 5 are evenly spaced along the inner circumference of the ring plate, and the friction wheel 3 is a low-temperature-resistant rubber wheel. The drive mechanism 2 is mounted at the junction of the connecting ring plate 1 and the connecting rod.

[0047] In one embodiment of the present application, the engine fan inlet structure is as follows Figure 3 As shown, it includes a fan casing, fan blades and an air intake cone, and the air intake cone is provided with three process screw holes. Figure 4 As shown, during assembly of the aircraft engine N1 rotor drive device of this application, the connecting ring plate 1 is pre-compressed and installed using fixing screws 5 to three process screw holes on the engine intake cap cone. The bottom of the connecting ring plate 1 is deformed, generating a certain pre-compression force, which tightly fits the friction wheel 3 to the inner wall of the fan case. When the drive mechanism 2 receives a motion command, the DC reduction motor 4 drives the friction wheel 3 to perform circumferential rotation along the inner wall of the fan case.

[0048] In a preferred embodiment of the present application, the electronic control system is as follows: Figure 5 As shown, the drive mechanism 2 includes a first wireless transceiver module, a motor driver module, a DC power supply module, and a counting module. The first wireless transceiver module is used to transmit data between the drive mechanism 2 and the remote control handle; the motor driver module is used to control the rotation state of the DC reduction motor 4 according to the command signal sent by the remote control handle; the DC power supply module is used to provide power; and the counting module is used to count the rotation angle of the N1 rotor. The remote control handle includes a second wireless transceiver module, a command module, and an N1 display module. The second wireless transceiver module is used to transmit data between the remote control handle and the drive mechanism 2; the command module is used to generate command signals; and the N1 display module is used to display the rotation angle of the N1 rotor. In this embodiment, the drive mechanism 2 provides driving power and receives command signals from the remote control handle, controls the rotation state of the DC reduction motor 4, and counts the rotation angle. The relevant signals are transmitted to the remote control handle via wireless communication. The remote control handle can provide forward, reverse, start, stop, numerical display, and speed adjustment command signals.

[0049] The aircraft engine N1 rotor drive device of this application, such as Figure 6 As shown, the counting module of the driving mechanism 2 collects the number of rotations n of the friction wheel, converts the number of rotations n of the friction wheel into the number of rotations N of the N1 rotor, and obtains the rotation angle of the N1 rotor through the number of rotations N of the N1 rotor;

[0050] The conversion relationship between the number of rotations n of the friction wheel and the number of rotations N of the N1 rotor is:

[0051]

[0052] Among them, r is the radius of the friction wheel, and R is the radius of the fan casing.

[0053] In the aircraft engine N1 rotor drive device of the present application, the drive mechanism 2 receives command signals from the remote control handle and controls the rotational state (direction, start and stop) of the DC reduction motor 4. The counting module collects the number of revolutions n of the friction wheel and converts it proportionally into the rotation angle of the N1 rotor. This is then transmitted to the remote control handle via the wireless transceiver module, allowing the operator to monitor the rotation angle of the N1 rotor in real time. The remote control handle command module issues start, stop, and speed regulation signals, thereby changing the rotation speed of the DC reduction motor 4 and, in turn, adjusting the speed and rotation angle of the N1 rotor.

[0054] The aircraft engine N1 rotor drive device of this application is used as follows:

[0055] (1) Install the connecting ring plate 1 to the engine inlet;

[0056] (2) When the forward rotation command of the remote control handle is pressed, the motor rotates forward and stops immediately after it is released; when the reverse rotation command is pressed, the motor rotates reversely and stops immediately after it is released; the speed of the DC reduction motor is adjusted through the speed control command;

[0057] (3) N1 angle counting: Select the zero reference of the N1 rotation angle. Click the "Reset" button at this time, and the digital tube will display 0. After that, perform an endoscopic inspection of the N1 rotor at each level. When N1 rotates, the remote control handle will display the rotation angle of the N1 rotor relative to the zero reference in real time. After aligning with the zero reference, drive to the specified angle to reposition the blade of interest without repeatedly driving and searching piece by piece, which is convenient for finding and monitoring the blade of interest.

[0058] The aircraft engine N1 rotor drive device of the present application has a stable driving speed and convenient reversing and inching start and stop control. Only one endoscopic inspection personnel is needed to realize N1 drive and endoscopic inspection. The automatic counting system is used to facilitate the positioning of the blades of interest. This solution saves the number of personnel, reduces work intensity, and reduces ineffective operations.

[0059] The above description is merely a specific embodiment of the present application, but the scope of protection of the present application is not limited thereto. Any changes or substitutions that can be easily conceived by a person skilled in the art within the technical scope disclosed in this application should be included in the scope of protection of the present application. Therefore, the scope of protection of the present application should be based on the scope of protection of the claims.

Claims

1. An aircraft engine N1 rotor drive device, characterized in that: include: A connecting ring plate (1), the connecting ring plate (1) comprising an annular plate and a connecting rod connected to the annular plate and extending radially outward, a plurality of fixing screws (5) being arranged circumferentially on the inner side of the annular plate, the annular plate being sleeved on the engine air intake cap cone and connected to the process bolt holes of the engine air intake cap cone via the fixing screws (5); A friction wheel (3), the friction wheel (3) being mounted on an end of the connecting rod away from the annular plate via an adapter plate (6), the friction wheel (3) being pressed against an inner wall surface of a fan casing, and a pre-compression force being generated between the friction wheel (3) and the inner wall surface of the fan casing, and a DC reduction motor (4) being mounted on the friction wheel (3); An electric control system comprises a drive mechanism (2) and a remote control handle, wherein the drive mechanism (2) is used to control the rotation state of the DC reduction motor (4) according to a command signal sent by the remote control handle.

2. The aircraft engine N1 rotor drive device according to claim 1, characterized in that: The connecting ring plate (1) is a flexible polyurethane plate.

3. The aircraft engine N1 rotor drive device according to claim 2, characterized in that: Three fixing screws (5) are arranged at equal intervals along the circumferential direction on the inner side of the annular plate.

4. The aircraft engine N1 rotor drive device according to claim 3, characterized in that: The friction wheel (3) is made of rubber.

5. The aircraft engine N1 rotor drive device according to claim 1, characterized in that: The driving mechanism (2) is installed at the connection between the annular plate of the connecting ring plate (1) and the connecting rod.

6. The aircraft engine N1 rotor drive device according to claim 1, characterized in that: The driving mechanism (2) comprises a first wireless transceiver module, a motor driver module, a DC power supply module and a counting module, wherein: The first wireless transceiver module is used to realize data transmission between the driving mechanism (2) and the remote control handle; The motor driver module is used to control the rotation state of the DC reduction motor (4) according to the command signal sent by the remote control handle; The DC power supply module is used to provide power; The counting module is used to count the rotation angle of the N1 rotor.

7. The aircraft engine N1 rotor drive device according to claim 6, characterized in that: The counting module collects the number of rotations n of the friction wheel, converts the number of rotations n of the friction wheel into the number of rotations N of the N1 rotor, and obtains the rotation angle of the N1 rotor through the number of rotations N of the N1 rotor; The conversion relationship between the number of rotations n of the friction wheel and the number of rotations N of the N1 rotor is: Among them, r is the radius of the friction wheel, and R is the radius of the fan casing.

8. The aircraft engine N1 rotor drive device according to claim 7, characterized in that: The remote control handle includes a second wireless transceiver module, a command module and an N1 display module, wherein: The second wireless transceiver module is used to realize data transmission between the remote control handle and the driving mechanism (2); The instruction module is used to generate an instruction signal; The N1 display module is used to display the rotation angle of the N1 rotor.

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