Thermal tripping structure of aero-generator

Abstract

The utility model provides a thermal tripping structure of an aero-generator. The thermal tripping structure comprises an input shaft connected with a generator and a power source; the end part of the input shaft is in transmission connection with the front end of the disengagement assembly in a disengagement manner through an end surface transmission structure, the disengagement assembly is sleeved in the hollow shaft, the disengagement assembly and the hollow shaft are in transmission through a spline transmission structure, and the hollow shaft is sleeved in a generator rotor structure; the rear end of the disengaging assembly is connected into a lubricating oil way. A disengaging spring is arranged in the disengaging assembly and used for abutting against the end face transmission structure to complete transmission. When the internal temperature of the oil-cooled generator is too high, the spring is triggered to act, so that the transmission shaft is separated from the input shaft, the generator is mechanically separated from the power source, the generator can be protected from being burnt out due to faults, and the power source can be protected from being damaged due to the faults of the generator.

Description

Technical Field

[0001] This utility model relates to a thermal tripping structure for an aircraft generator, belonging to the field of mechanical engineering technology. Background Technology

[0002] With the continuous upgrading of aerospace weapons and equipment, the power and speed requirements of aircraft generators are getting higher and higher. At the same time, aircraft also have higher and higher requirements for the health management of power generation and power systems. Therefore, when the internal temperature of the generator is abnormal, it is necessary to be able to disconnect the power source in time to protect the motor from being burned out and to protect the power source from being damaged due to problems with the power generation system. Utility Model Content

[0003] To solve the above-mentioned technical problems, this utility model provides a thermal trip structure for an aircraft generator. This thermal trip structure can effectively solve the problem of being able to disconnect the power source in a timely manner when the internal temperature rise of an aircraft oil-cooled generator is abnormal, thus protecting the motor from being burned out and the power source from being damaged due to problems with the power generation system.

[0004] This utility model is achieved through the following technical solution.

[0005] This utility model provides a thermal release structure for an aircraft generator, including an input shaft connecting the generator and a power source; the end of the input shaft is detachably connected to the front end of a release assembly via an end-face transmission structure, the release assembly is fitted in a hollow shaft, and the release assembly and the hollow shaft are driven by a spline transmission structure, the hollow shaft is fitted in the generator rotor structure; the rear end of the release assembly is connected to a lubricating oil circuit; the release assembly contains a release spring for pressing against the end-face transmission structure to complete the transmission.

[0006] The disengagement assembly includes a drive shaft, with the front end of the drive shaft abutting against the input shaft. A pull rod is coaxially mounted inside the drive shaft, and a base plate is coaxially mounted at the front of the pull rod. A disengagement spring is located between the base plate and the drive shaft. The front end face of the base plate and the input shaft form an end-face transmission structure. A thermoplastic block is fitted onto the pull rod.

[0007] The front end of the hot melt block abuts against the protruding structure on the inner wall of the drive shaft, the rear end of the hot melt block abuts against the guide seat, the rear end of the pull rod is installed in the guide seat, and the guide seat is connected to the lubricating oil circuit.

[0008] A sealing ring is installed between the pull rod and the guide seat, and the sealing ring is located in a groove on the outer wall of the pull rod.

[0009] There is a molten block liquid cavity at the front end of the guide seat between the pull rod and the guide seat. There is a gap between the front end of the guide seat and the outer wall of the pull rod, so that the hot molten block can melt and flow into the molten block liquid cavity when heated.

[0010] The rear end of the release spring is fitted onto the pull rod.

[0011] The front end face of the hot melt block has a sealing ring fitted between the drive shaft and the tie rod.

[0012] The guide seat is coaxially mounted inside the drive shaft.

[0013] A sealing ring is installed at the rear end of the drive shaft between the drive shaft and the guide seat.

[0014] The beneficial effects of this utility model are: when the internal temperature of the oil-cooled generator is too high, the spring is triggered to separate the transmission shaft from the input shaft, thereby mechanically disengaging the generator from the power source. This helps protect the generator from burnout due to malfunction and protects the power source from damage caused by generator malfunction. Attached Figure Description

[0015] Figure 1 This is a schematic diagram of the structure of at least one embodiment of the present utility model;

[0016] Figure 2 yes Figure 1 A schematic diagram of the structure of the detachment component;

[0017] Figure 3 yes Figure 2 A schematic diagram of its decomposed structure.

[0018] In the diagram: 1-Input shaft, 2-Disengagement assembly, 3-Hollow shaft, 4-End face transmission structure, 5-Spline transmission structure, 21-Transmission shaft, 22-Pull rod, 23-Guide seat, 24-Disengagement spring, 25-Base plate, 26-Hot melt block, 27-Sealing ring, 28-Hot melt liquid chamber. Detailed Implementation

[0019] The technical solution of this utility model is further described below, but the scope of protection is not limited to what is described.

[0020] Example 1

[0021] like Figures 1 to 3 The illustrated thermal release structure for an aircraft generator includes an input shaft 1 connecting the generator and a power source. The end of the input shaft 1 is detachably connected to the front end of a release assembly 2 via an end face transmission structure 4. The release assembly 2 is fitted inside a hollow shaft 3, and the release assembly 2 and the hollow shaft 3 are driven by a spline transmission structure 5. The hollow shaft 3 is fitted inside the generator rotor structure. The rear end of the release assembly 2 is connected to a lubricating oil circuit. A release spring 24 is located inside the release assembly 2 to press against the end face transmission structure 4 to complete the transmission.

[0022] Example 2

[0023] Based on embodiment 1, the disengagement assembly 2 includes a drive shaft 21, the front end of the drive shaft 21 abuts against the input shaft 1, a pull rod 22 is coaxially inside the drive shaft 21, a base plate 25 is coaxially at the front of the pull rod 22, a disengagement spring 24 is between the base plate 25 and the drive shaft 21, and the front end face of the base plate 25 and the input shaft 1 constitute an end face transmission structure 4; a hot melt block 26 is sleeved on the pull rod 22.

[0024] Furthermore, the front end of the hot melt block 26 abuts against the protruding structure on the inner wall of the drive shaft 21, the rear end of the hot melt block 26 abuts against the guide seat 23, the rear end of the pull rod 22 is installed in the guide seat 23, and the guide seat 23 is connected to the lubricating oil circuit.

[0025] Furthermore, the rear end of the release spring 24 is mounted on the pull rod 22.

[0026] Furthermore, when the motor temperature rises, the hot melt block 26 melts, and the transmission shaft 21 separates from the input shaft 1 under the action of the spring force, realizing the tripping action.

[0027] Example 3

[0028] Based on embodiment 2, a sealing ring 27 is installed between the pull rod 22 and the guide seat 23, and the sealing ring 27 is located in the groove on the outer wall of the pull rod 22.

[0029] Furthermore, there is a molten metal cavity 28 between the pull rod 22 and the guide seat 23 at a position at the front end of the guide seat 23. There is a gap between the front end of the guide seat 23 and the outer wall of the pull rod 22, so that the hot molten metal 26 can melt when heated and flow into the molten metal cavity 28.

[0030] Furthermore, the front end face of the hot melt block 26 has a sealing ring fitted between the drive shaft 21 and the pull rod 22.

[0031] Furthermore, the guide seat 23 is coaxially mounted inside the drive shaft 21.

[0032] Furthermore, a sealing ring is installed between the drive shaft 21 and the guide seat 23 at the rear end of the drive shaft 21.

[0033] Example 4

[0034] Based on the above embodiments, the input shaft is used to connect the generator and the power source. It is designed as a detachable structure to facilitate disassembly and maintenance. The input shaft and the disengagement assembly transmit torque through end face meshing. The end face meshing structure is conducive to axial disengagement.

[0035] The disengagement assembly consists of a drive shaft, a base plate, a disengagement spring, a thermoplastic block, a tie rod, and a guide seat. The drive shaft transmits power from the input shaft to the hollow shaft via an external spline, thereby driving the rotor component to rotate. The drive shaft contains a compressed spring; one end of the spring acts on the base plate, and the other end acts on the end face of the drive shaft. The base plate is located inside the drive shaft's circular hole and can move freely axially. The thermoplastic block is located between the drive shaft and the guide seat. One end of the guide seat extends into the drive shaft and can move freely axially; the other end of the guide seat has an external thread for connecting to the hollow shaft. One end of the tie rod is threaded to the base plate, and the other end is a tapered structure fixed inside the guide seat. The end of the tie rod also has an internal hexagonal socket. During assembly, the tie rod is continuously tightened using hexagonal bolts. Under the spring force, the drive shaft, base plate, thermoplastic block, and guide seat are axially locked, and the spring is in a compressed state.

[0036] The disengagement assembly and the hollow shaft are connected by a thread. During assembly, the external thread of the guide seat is screwed into the hollow shaft to fix the disengagement assembly. Then, the input shaft is installed from the end of the hollow shaft so that the input shaft meshes with the end face of the disengagement assembly.

[0037] The specific process of tripping action:

[0038] When the internal temperature of the generator is abnormal, the oil temperature between the hollow shaft and the drive shaft rises. The hot melt block melts under the action of high temperature, and the spring in the pre-tightened state is released. Under the action of spring force, the drive shaft moves to one end of the guide seat, causing the drive shaft to disengage from the input shaft, thereby triggering the tripping action.

[0039] Therefore, overall, this utility model:

[0040] 1. It adopts a hot melt block (mainly tin-soldering component) that can automatically melt at a limited temperature. The melting temperature can be adjusted according to the actual working conditions to cope with different temperature protection thresholds.

[0041] 2. It adopts a mechanical triggering structure with direct spring action, which has high reliability;

[0042] 3. An independent tripping assembly is adopted, and the tripping assembly and hollow shaft are detachable for easy maintenance and reset;

[0043] 4. A cavity is designed between the guide seat and the tie rod. After the hot melt block melts, it enters the cavity along the axial direction for storage.

[0044] 5. The sealed trip assembly design prevents the liquid from the molten hot melt block from entering the generator's main oil circuit and contaminating the lubricating oil.

[0045] 6. The tripping assembly is designed inside the hollow rotor shaft, which does not occupy the axial space of the generator. In addition, the tripping assembly is compact and has a weight advantage.

Claims

1. A thermal trip structure for an aircraft generator, comprising an input shaft (1) connecting the generator and a power source, characterized in that: The input shaft (1) is connected to the front end of the disengagement assembly (2) in a detachable manner through the end face transmission structure (4). The disengagement assembly (2) is fitted in the hollow shaft (3). The disengagement assembly (2) and the hollow shaft (3) are driven by the spline transmission structure (5). The hollow shaft (3) is fitted in the generator rotor structure. The rear end of the disengagement assembly (2) is connected to the lubricating oil circuit. The disengagement assembly (2) contains a disengagement spring (24) to press against the end face transmission structure (4) to complete the transmission.

2. The thermal trip structure for an aircraft generator as described in claim 1, characterized in that: The disengagement assembly (2) includes a drive shaft (21), the front end of the drive shaft (21) abuts against the input shaft (1), a pull rod (22) is coaxially inside the drive shaft (21), a base plate (25) is coaxially at the front of the pull rod (22), a disengagement spring (24) is between the base plate (25) and the drive shaft (21), and the front end face of the base plate (25) and the input shaft (1) constitute an end face transmission structure (4); a hot melt block (26) is sleeved on the pull rod (22).

3. The thermal trip structure for an aircraft generator as described in claim 2, characterized in that: The front end of the hot melt block (26) abuts against the protruding structure on the inner wall of the drive shaft (21), the rear end of the hot melt block (26) abuts against the guide seat (23), the rear end of the pull rod (22) is installed in the guide seat (23), and the guide seat (23) is connected to the lubricating oil circuit.

4. The thermal trip structure for an aircraft generator as described in claim 3, characterized in that: A sealing ring (27) is installed between the pull rod (22) and the guide seat (23), and the sealing ring (27) is located in the groove on the outer wall of the pull rod (22).

5. The thermal trip structure for an aircraft generator as described in claim 3, characterized in that: There is a molten metal cavity (28) between the pull rod (22) and the guide seat (23) at a position at the front end of the guide seat (23). There is a gap between the front end of the guide seat (23) and the outer wall of the pull rod (22), so that the hot molten metal (26) can melt and flow into the molten metal cavity (28) when heated.

6. The thermal trip structure for an aircraft generator as described in claim 2, characterized in that: The rear end of the release spring (24) is fitted onto the pull rod (22).

7. The thermal trip structure for an aircraft generator as described in claim 3, characterized in that: The front end face of the hot melt block (26) has a sealing ring fitted between the drive shaft (21) and the pull rod (22).

8. The thermal trip structure for an aircraft generator as described in claim 3, characterized in that: The guide seat (23) is coaxially mounted inside the drive shaft (21).

9. The thermal trip structure for an aircraft generator as described in claim 8, characterized in that: A sealing ring is installed at the rear end of the drive shaft (21) between the drive shaft (21) and the guide seat (23).

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