CN211930403U

CN211930403U - Dual-redundancy structural bearing for aero-generator

Info

Publication number: CN211930403U
Application number: CN202020689990.5U
Authority: CN
Inventors: 苏泽洋; 晏德平
Original assignee: Hubei Hangda Technology Co ltd
Current assignee: Hubei Hangda Technology Co ltd
Priority date: 2020-04-29
Filing date: 2020-04-29
Publication date: 2020-11-13
Anticipated expiration: 2030-04-29

Abstract

The utility model discloses a two redundant structure bearings for aerogenerator. The device comprises an auxiliary bearing, a bearing chamber with a sensor, a main bearing, a tail shell, a rotor and an electric connector; the sensored bearing housing is mounted within the aft case and supports the rotor via the main bearing; the bearing chamber with the sensor is connected with the electric connector through a signal wire; the auxiliary bearing and the main bearing are both arranged at one end of the rotor; wherein the main bearing is over-fitted with the sensored bearing housing; the auxiliary bearing is in clearance fit with the bearing chamber with the sensor. The utility model has the advantages of guarantee the reliability of bearing work.

Description

Dual-redundancy structural bearing for aero-generator

Technical Field

The utility model relates to an aeronautical technical field, it is a bearing dual-redundancy structure for aerogenerator that says so more specifically.

Background

When the bearing of the conventional aero-generator can not work normally due to the failure of ball abrasion, the main bearing can not normally support a rotor due to the fact that the ball abrasion is reduced, the bearing of the generator needs to be replaced as soon as possible, and the completion of the current task of the airplane is influenced.

The prior application number is CN201410648986.3, the patent name is 'a double-redundancy rotary supporting structure', and the double-redundancy rotary supporting structure reduces bearing loss and prolongs the service life; but the required radial space is large, the volume and the weight are large, and the application in an aviation generator is difficult.

Therefore, there is a need to develop a dual-redundancy structure of a bearing, which can be applied to an aircraft generator and can ensure the operational reliability of the bearing.

Disclosure of Invention

The utility model aims at providing a reliability, small, light in weight that are used for aero-generator's two redundant structure bearings, guarantee bearing work.

In order to realize the purpose, the technical scheme of the utility model is that: the utility model provides a two redundant structures of bearing for aeronautical generator which characterized in that: the device comprises an auxiliary bearing, a bearing chamber with a sensor, a main bearing, a tail shell, a rotor and an electric connector;

the sensored bearing housing is mounted within the aft case and supports the rotor via the main bearing;

the bearing chamber with the sensor is connected with the electric connector through a signal wire;

the auxiliary bearing and the main bearing are both arranged at one end of the rotor; wherein the main bearing is over-fitted with the sensored bearing housing; the auxiliary bearing is in clearance fit with the bearing chamber with the sensor.

In the technical scheme, a main bearing failure sensor is installed in the bearing chamber with the sensor.

The utility model has the advantages of as follows:

(1) the utility model has compact structure, small volume, light weight and small required radial space, and can be applied to an aircraft generator;

(2) the utility model is provided with a bearing failure sensor, which can report the failure condition of the bearing in time, inform the aircraft to change the motor in time and ensure the safety of the operation of the aircraft;

(3) the utility model can ensure the reliability of the bearing work; under normal conditions, the main bearing works, the auxiliary bearing does not work, and the bearing failure signal is in a disconnection state; when the main bearing cannot normally work due to the abrasion failure of the ball bearings, the main bearing does not work and assists the bearing to work; when the auxiliary bearing works, the main bearing failure sensor sends a fault signal to the generator control device to prompt a pilot and a ground crew that the generator bearing has faults and needs to be replaced, and after the main bearing has faults, the current task is not affected, and the auxiliary bearing can maintain the continuous work of the motor for more than or equal to 10 hours.

Drawings

Fig. 1 is a schematic structural diagram of the present invention.

Fig. 2 is a partial structural view of the main bearing of the present invention during normal operation.

Fig. 3 is a partial structure view of the main bearing ball of the present invention when it is worn out.

Fig. 4 is a schematic view of the bearing chamber with sensor according to the present invention.

Fig. 5 is a schematic diagram of a main bearing failure signal in the present invention.

In fig. 2, a indicates a clearance where the auxiliary bearing and the sensor-equipped bearing housing are in clearance fit when the main bearing 3 is in normal operation.

In fig. 3, B indicates a contact portion between the auxiliary bearing outer ring and the bearing chamber inner ring when the main bearing 3 does not normally operate.

In the figure 1-auxiliary bearing, 2-bearing chamber with sensor, 3-main bearing, 4-tail shell, 5-rotor, 6-electric connector and 7-main bearing failure sensor.

Detailed Description

The following detailed description of the embodiments of the present invention will be made with reference to the accompanying drawings, which are not intended to limit the present invention, but are merely exemplary. While the advantages of the invention will be clear and readily appreciated by the description.

With reference to the accompanying drawings: a dual-redundancy structure bearing for an aircraft generator comprises an auxiliary bearing 1, a bearing chamber 2 with a sensor, a main bearing 3, a tail shell 4, a rotor 5 and an electric connector 6;

the sensor bearing housing 2 is mounted in the tail housing 4, the sensor bearing housing 2 supporting the rotor 5 via the main bearing;

the bearing chamber 2 with the sensor is connected with the electric connector 6 through a signal line, when the auxiliary bearing works, the main bearing failure sensor 7 sends a fault signal to the generator control device through the electric connector 6 to prompt a pilot and ground crew that the generator bearing is in fault and needs to be replaced;

the auxiliary bearing 1 and the main bearing 3 are both arranged at one end of the rotor; wherein the main bearing 3 is over-fitted with the sensor bearing housing 2; when the main bearing fails to work normally due to the abrasion of the balls, the main bearing cannot normally support the rotor due to the fact that the abrasion of the balls is reduced, the outer ring of the auxiliary bearing is in contact with the inner ring of the bearing chamber, and the auxiliary bearing works (as shown in fig. 1, fig. 2 and fig. 3);

the auxiliary bearing 1 is in clearance fit with the sensor bearing chamber 2 (as shown in fig. 2); under normal conditions, the main bearing works, the auxiliary bearing is in clearance fit with the bearing chamber with the sensor, the outer ring of the bearing is not in contact with the inner ring of the bearing chamber, so that the auxiliary bearing does not work, and the failure signal of the bearing is in a disconnection state (as shown in figure 5).

Further, a main bearing failure sensor 7 (shown in fig. 4) is installed in the sensor bearing chamber 2; when the auxiliary bearing works, the main bearing failure sensor sends a fault signal to the generator control device to prompt a pilot and ground crew that the generator bearing has faults and needs to be replaced.

Aviation generator with two redundancy high reliability bearings's theory of operation as follows:

under normal conditions, the main bearing works, the auxiliary bearing is in clearance fit with the bearing chamber with the sensor, and the outer ring of the bearing is not in contact with the inner ring of the bearing chamber, so that the auxiliary bearing does not work, and the failure signal of the bearing is in a disconnection state (as shown in figure 2);

when the main bearing cannot normally work due to the abrasion failure of the balls, the main bearing cannot normally support the rotor due to the fact that the abrasion of the balls is reduced, the outer ring of the auxiliary bearing is in contact with the inner ring of the bearing chamber, the auxiliary bearing works, and a main bearing failure sensor arranged in the bearing chamber beside the auxiliary bearing sends a fault signal (as shown in figures 3 and 5);

when the auxiliary bearing works, the main bearing failure sensor sends a failure signal to a generator control device (as shown in fig. 3 and 5) to prompt a pilot and a ground crew that the generator bearing has a failure and needs to be replaced, and after the main bearing has a failure, the completion of the current task is not influenced, and the auxiliary bearing can maintain the continuous work of the motor for more than or equal to 10 hours.

Other parts not described belong to the prior art.

Claims

1. The utility model provides a two redundant structure bearings for aeronautical generator which characterized in that: the device comprises an auxiliary bearing (1), a bearing chamber (2) with a sensor, a main bearing (3), a tail shell (4), a rotor (5) and an electric connector (6);

the sensored bearing housing (2) is mounted in the tail housing (4) and supports the rotor (5) via the main bearing (3);

the sensor bearing chamber (2) is connected with the electric connector (6) through a signal wire;

the auxiliary bearing (1) and the main bearing (3) are both arranged at one end of the rotor (5); wherein the main bearing (3) is over-fitted with the sensor bearing housing (2); the auxiliary bearing (1) is in clearance fit with the bearing chamber (2) with the sensor.

2. A dual-redundancy structural bearing for an aircraft electrical generator, according to claim 1, wherein: and a main bearing failure sensor (7) is arranged in the bearing chamber (2) with the sensor.