CN114441795A - Airplane generator rotor overspeed testing device and method - Google Patents

Abstract

The invention relates to the technical field of rotor high-speed testing, and provides an aircraft generator rotor over-speed testing device and method. The device includes an input spline shaft, an upper casing, a lower casing, a rotor to be tested, and a cooling oil circuit; the The rotor to be tested is placed horizontally in the sealed space formed by the upper casing and the lower casing; the cooling oil circuit is used to provide cooling and lubrication for the bearings at both ends of the rotor to be tested; the input One end of the spline shaft is connected to the drag stage of the power input end, and the other end is connected to the rotor to be tested, and an overload shearing point is set in the middle of the input spline shaft. The driving end of the present invention adopts the spline meshing form, which can ensure good coaxiality and smooth transmission of input torque, and has no impact on the equipment; a separate lubricating and cooling oil circuit is designed inside the testing device, which can greatly improve the lubrication and stability of the support bearings at both ends. Cooling, increasing the service life of the bearing and ensuring the safe and reliable testing process.

Description

An aircraft generator rotor overspeed test device and method

technical field

The invention relates to the technical field of rotor high-speed testing, in particular to an aircraft generator rotor overspeed testing device and method, which realizes the failure verification of the aircraft generator rotor in a high-speed state.

Background technique

The civil aircraft generator is an important part of the aircraft power system. It is installed on the gearbox of the aircraft engine and converts the mechanical power output by the engine into the electrical power required by various loads on the aircraft. Aircraft generator is an electrical product with complex structure. It is mainly composed of permanent magnet exciter, AC exciter, main generator and pump system for cooling. Among them, the rotor, the core component of the main generator, is in a normal power generation state. It is always in a state of high-speed rotation, and its failure will usually cause great destructive damage to the aircraft generator body, which will eventually cause the aircraft generator to stop and cut out, which will reduce the redundancy of the aircraft power system.

At this stage, the manufacturer or supplier of the aircraft requires that the rotor inside the generator must perform an overspeed test when the winding is newly installed or repaired and reinstalled for the manufacture and maintenance of the aircraft generator. The speed of the overspeed test is divided into three grades. They are 12000 rpm, 24000 rpm and 30000 rpm respectively to verify whether the rotor fails at different speeds. For the overspeed test of the rotor, there are currently special test devices abroad, which mainly drive the rotor to rotate at high speed by the vertical suspension motor of the rotor. However, this installation method has certain defects in the use process. The connection between the rotor and the drive shaft of the test device It is rigidly crimped and fixed, which will cause the motor drive shaft to be out of axis with the rotor shaft, which will cause the rotor to move irregularly under high-speed rotation, and finally cause the rotor to fly out of the hinge point, damaging the test device and the test piece. For the domestic rotor overspeed test device, it is mainly placed horizontally and openly. The main disadvantages are: the rotor does not have a protective cover when it rotates at high speed and lacks safety protection; the cooling method of the support bearing is air cooling, the heat dissipation efficiency is not high, and the rotor speed cannot exceed High; the coupling is connected without failover overload protection.

SUMMARY OF THE INVENTION

The purpose of the present invention is to overcome at least one of the deficiencies of the prior art, and to provide an aircraft generator rotor overspeed testing device and method, which greatly improves the heat dissipation of the bearing and improves the service life of the bearing. Moreover, this solution is compact in structure, convenient in installation, and labor-saving.

The present invention adopts following technical scheme:

In one aspect, the present invention provides an aircraft generator rotor overspeed test device, comprising an input spline shaft, an upper casing, a lower casing, a rotor to be tested, and a cooling oil circuit;

the rotor to be tested is placed horizontally in the sealed space formed by the upper casing and the lower casing;

The cooling oil circuit is used for cooling and lubricating the bearings at both ends of the rotor under test;

One end of the input spline shaft is connected to the drag stage of the power input end, and the other end is connected to the rotor to be tested, and an overload shearing point is set in the middle of the input spline shaft.

In any of the possible implementations described above, an implementation is further provided, wherein the rotor to be tested includes a first end and a second end, and the first end has its own first bearing and a first bearing seat; the first end of the rotor to be tested is mounted in the upper housing through the first bearing and the first bearing seat;

A second bearing seat is arranged in the lower housing, and a support bearing is arranged in the second bearing seat; the support bearing is used for supporting the second end of the rotor to be tested.

The support bearing at the second end of the rotor under test is used to axially fix the rotor through the bearing retaining ring that comes with the rotor. The bearing retaining ring is connected to the lower casing by bolts, and bolt holes are reserved in the lower casing for connecting the bearing retaining ring and the lower casing. .

According to any of the possible implementations described above, an implementation is further provided, wherein the apparatus further includes a vibration sensor disposed at the second end of the rotor to be tested, the vibration sensor is connected to the detection system by wireless or wired signal.

Any of the possible implementations described above further provides an implementation, wherein the cooling oil passage is provided in the side walls of the upper casing and the lower casing, and the cooling oil passes through the cooling oil passage The support bearing and the first bearing are reached, and the support bearing and the first bearing are cooled and lubricated by means of spraying.

Any of the above-mentioned possible implementations further provides an implementation in which the cooling oil first reaches the rotor to be tested through the cooling oil passages provided in the side walls of the upper casing and the lower casing. The support bearing at the end of the test rotor is used to cool and lubricate the support bearing; the cooling oil then reaches the first bearing at the first end of the tested rotor through a separate cooling oil circuit set in the center of the tested rotor to cool and lubricate the first bearing. The cooling oil circuit design scheme uses a separate cooling oil circuit inside the tested rotor to reduce unnecessary drilling operations, and it is more beneficial to use one oil circuit to ensure oil pressure and oil volume.

Any of the above-mentioned possible implementations further provides an implementation, wherein the input spline shaft and the input shaft of the drag table are connected by gear meshing, and the input spline shaft and the rotor to be tested pass through canine teeth. Mesh connection.

Any of the above-mentioned possible implementations further provides an implementation, wherein the rotor under test is fixedly connected to the lower casing through its own bearing retaining ring to limit the axial displacement of the rotor under test .

According to any of the above possible implementation manners, an implementation manner is further provided, wherein the upper casing and the lower casing are fixedly connected by screws.

According to any of the above-mentioned possible implementation manners, an implementation manner is further provided, wherein the upper casing is fixed with the flange of the drag table through the mounting flange.

On the other hand, the present invention also provides an aircraft generator rotor overspeed test method, the method uses the above-mentioned device, and the method includes:

S1. Install the device on the flange of the drag table, and connect the cooling liquid circulation equipment of the drag table to the cooling oil road of the device;

S2. At the beginning of the test, the drag table sets different speeds, and the drag table transmits torque to the tested rotor through the input spline shaft, which drives the tested rotor to rotate at a high speed; at the same time, the cooling oil passes through the cooling oil circuit to the support The bearing and the first bearing are cooled and lubricated; after that, the cooling oil is pumped out to the drag table to complete cooling and cooling, and the reciprocating cycle is continued until the overspeed test of all speed levels is completed;

S3. The vibration sensor installed at the second end of the rotor to be tested detects the vibration of the rotor to be tested. When the vibration amplitude exceeds the allowable value, real-time shutdown protection occurs; if an emergency overload occurs and the bearing of the rotor to be tested fails, the input spline is cut through the overload protection point. axis to ensure safe and reliable testing.

According to any of the possible implementation manners described above, an implementation manner is further provided. In step S2, the rotational speed level is three levels, which are 12000 rpm, 24000 rpm, and 30000 rpm respectively.

The beneficial effects of the present invention are:

Due to the adoption of the technical solution of the present invention, both ends of the rotor to be tested are installed horizontally in a closed manner, which can ensure good coaxiality and safety; the bearings at both ends are cooled and lubricated by oil spray, which greatly improves the heat dissipation of the bearings. Increased bearing life. Moreover, this solution has a compact structure, is easy to install, saves manpower, and can quickly complete the deployment of the test device. In order to improve the safety level of the test device, the overload shearing function of the input spline shaft is designed, and the vibration value of the test device is monitored during the test to see if the vibration value exceeds the allowable value. If the vibration value exceeds the standard, the drive end will stop for protection in real time. In addition, if the present invention can be effectively implemented, it is expected that considerable test income can be obtained every year.

Description of drawings

FIG. 1 is a schematic three-dimensional structure diagram of an aircraft generator rotor overspeed test device according to an embodiment of the present invention.

FIG. 2 is a schematic diagram (partial section) of the overall structure of the embodiment.

FIG. 3 is a schematic top view of the overall structure of the embodiment.

FIG. 4 is a schematic right side view of the overall structure of the embodiment.

FIG. 5 is a schematic diagram of the cooling oil circuit in the embodiment.

FIG. 6 is a schematic diagram showing the structure of the input spline shaft in the embodiment.

In the figure, 1- input spline shaft; 2- oil outlet plug; 3- upper casing; 4- lower casing; 5- fixing bolts (8 pieces); 6- oil inlet plug; 7- No. Two bearing seats; 8-support bearing; 9-tested rotor; 10-cooling oil circuit; 11-installation fixing hole; 12-oil inlet; 13-oil outlet; 14-key slot hole; 15-lower oil port; 16- Oil port.

Detailed ways

Hereinafter, specific embodiments of the present invention will be described in detail with reference to the accompanying drawings. It should be noted that the technical features or combinations of technical features described in the following embodiments should not be considered isolated, and they can be combined with each other to achieve better technical effects. In the drawings of the following embodiments, the same reference numerals appearing in the various drawings represent the same features or components, which may be used in different embodiments.

Aiming at the problem of the overspeed test of the rotor of the existing aircraft generator, the embodiment of the present invention proposes a device for the overspeed test of the rotor of the aircraft generator. The key technology of the device is that the tested rotor 9 is a horizontally placed closed type during the test. Installation, the support method is bearing support at both ends, the cooling method of the bearing is oil spray cooling, and the connection between the drive end and the rotor is designed as a special spline shaft connection. When performing the rotor overspeed test: the rotor needs to be installed in the test device first, and then the two are installed on the drag table as a whole; the cooling oil circulation equipment on the drag table can be connected to realize real-time cooling of the bearings at both ends of the rotor ; At the same time, it is also necessary to install a vibration sensor on the test device. When the vibration value of the rotor at high speed exceeds the specified value, the drag table can be stopped in time; in addition, for the rotor rotation failure in extreme cases, connect the drag table and the rotor. The spline shaft at the end is designed with overload protection, which can be cut in time to realize the safety protection of equipment and personnel.

As shown in FIGS. 1-4 , an aircraft generator rotor overspeed test device according to an embodiment of the present invention includes an input spline shaft 1 , an upper casing 3 , a lower casing 4 , a tested rotor 9 , and a cooling oil circuit 10 ; The tested rotor 9 is placed horizontally in the sealed space formed by the upper casing 3 and the lower casing 4 ; the cooling oil circuit 10 is used to provide bearings at both ends of the tested rotor 9 Cooling and lubricating; one end of the input spline shaft 1 is connected to the drag stage of the power input end, and the other end is connected to the tested rotor 9 , and an overload shear point is set in the middle of the input spline shaft 1 .

In a specific embodiment, in order to reduce the weight, the flange of the upper casing 3 adopts a material-removed design, and at the same time, eight mounting and fixing holes 11 are punched on the mounting flange of the upper casing 3, and the mounting and fixing holes 11 are used for In conjunction with the flange of the drag table to fix the overspeed test device, it is necessary to punch a positioning hole 14, an oil inlet 12 and an oil outlet 13, and reserve 1 on the side of the flange for installation and outlet. The threaded hole of the oil port plug 2 and the keyway hole 14 are used for the installation and positioning of the entire test device.

In a specific embodiment, the upper housing 3 and the lower housing 4 are connected together by fixing bolts 5; the second bearing seat 7 is fixedly connected with the lower housing 4 by screws; the rotor to be tested 9 passes through Its own bearing retaining ring (not shown in the figure) is fixedly connected with the lower casing 4 to limit the axial displacement of the rotor 9 under test.

In a specific embodiment, the upper casing 3 and the lower casing 4 are connected together by 8 fixing bolts 5, and the side wall of the upper casing 3 is designed with a cooling oil circuit 10, and the side wall and bottom of the lower casing 4 are designed with a cooling oil circuit 10. A cooling oil circuit 10 is designed. The end of the cooling oil circuit 10 of the lower casing 4 is designed with an upper oil port 16 and a lower oil port 15. The upper oil port 16 is used to lubricate and cool the support bearing 8, and the lower oil port 15 is used to lubricate and cool the cooling pad The cylindrical bearing on the other side of the test rotor 9, that is, the first bearing; the lower housing 4 is designed with a structure specially designed to install the second bearing seat 7, and the second bearing seat 7 and the lower housing 4 are fastened with screws.

In a specific embodiment, the support bearing 8 is installed in the second bearing seat 7 to support the second end of the tested rotor 9 , and the first end of the tested rotor 9 is installed to the first bearing seat of the upper casing 3 Supporting place (Note: the tested rotor 9 has its own first bearing and first bearing seat); in addition, the outer side of the lower housing 4 has reserved threaded holes for installing the oil inlet plug 6.

In a specific embodiment, the upper casing 3 and the lower casing 4 are used to design the cooling oil circuit 10 separately. The cooling oil flows into the oil circuit of the upper casing 3 and is transmitted to the second bearing seat 7 through the oil circuit of the lower casing 4 (Reverse drive end bearing seat) bottom, realize the cooling and lubrication of the first bearing (drive end bearing) through the lower oil port 15 of the lower shell 4, and realize the support bearing 8 (reverse drive end bearing) through the upper oil port 16 of the lower shell 4 end bearings) cooling and lubrication. As shown in FIG. 5 , the oil inlet plug 6 is installed on the lower casing 4 ; the oil outlet plug 2 is installed on the upper casing 3 .

The cooling oil circuit 10 can be flexibly arranged. In another specific embodiment, the cooling oil circuit 10 is only arranged in the side walls of the upper casing 3 and the lower casing 4, and the cooling oil reaches the support bearing 8 and the cooling oil respectively. first bearing.

In a specific embodiment, the rotor under test 9 is engaged with the input spline shaft 1 through splines, the connection between the input spline shaft 1 and the rotor under test 9 is a clearance fit, and the middle part of the input spline shaft 1 is designed with For the overload protection function, for example, an overload shear point can be designed, and the section diameter at the overload shear point is smaller than the section diameter of other areas of the input spline shaft 1, as shown in Figure 6. In the event of emergency overload, the input spline shaft 1 can be overloaded and cut off, which can ensure the safe and reliable operation of the equipment to a certain extent. The diameter of the overload shearing point is determined by experiment or calculation. When the load at the overload shearing point exceeds the critical value, the input spline shaft will be automatically overloaded and sheared.

In a specific embodiment, the other end of the input spline shaft 1 is connected to the input shaft of the drag table, and the drag table has a dedicated hydraulic oil cooling system. Before performing the test, it is necessary to install the inlet/outlet of the oil cooling system From the oil circuit to the mounting flange of the drag table, it is also necessary to install the vibration sensor to the anti-driving end of the test device (for example, on the second end of the rotor 9 to be tested). Set different speed levels, start the drag table to perform the overspeed test, at this time the drag table will drive the input spline shaft 1 and the tested rotor 9 to rotate at high speed, and the oil cooling system outside the drag table will also start to work synchronously to complete the interior of the test device. The lubrication and cooling of the support bearings at both ends, the lubricated and cooled hydraulic oil will be concentrated at the bottom of the inner cavity formed by the upper shell 3 and the lower shell 4, and then pumped out to the external heat exchanger through the cooling oil pump of the drag stage. Cooling of hydraulic fluid. If the vibration value detected by the vibration sensor of the drag table exceeds the allowable value during the test, the drag table will immediately stop for protection to ensure the safety of personnel and equipment.

An aircraft generator rotor overspeed test method according to the embodiment of the present invention is specifically:

S1. Install the overspeed test device on the flange of the drag table, and connect the cooling circulation equipment of the drag table to the oil inlet and outlet on the flange.

S2. After the test starts, set different rotational speeds on the operating interface of the drag table, and the drag table transmits torque to the tested rotor 9 through the input spline shaft 1, which drives the tested rotor 9 to rotate at a high speed, and the tested rotor 9 rotates at the same time , the cooling oil pump of the drag table is also turned on at the same time, it continuously pumps the cooling oil through the oil inlet 12 into the oil inlet oil passage 10 of the upper casing 3 and the lower casing 4, and finally the cooling oil passes through the oil inlet. The upper oil port 16 of the oil circuit 10 injects oil to lubricate the support bearing 8, and the lower oil port 15 of the oil inlet oil circuit 10 passes through the oil circuit in the inner cavity of the tested rotor 9 to inject oil to lubricate the first bearing on the other side of the tested rotor. , the oil after cooling the bearing is pumped out to the heat exchanger of the cooling system of the drag table through the oil outlet 13 to complete the cooling and cooling, and continue to reciprocate and circulate until the overspeed test of all speed levels is completed.

S3. Install the vibration sensor to the reverse drive end of the overspeed test device before the test, that is, the second end. The acquisition channel on the drag table can complete the vibration monitoring of the test device in real time; when the vibration amplitude exceeds the allowable value, real-time shutdown protection ; If an emergency overload occurs and the bearing of the tested rotor 9 fails, cut off the input spline shaft 1 through the overload protection point to ensure safe and reliable testing.

The innovation of the present invention is to propose a horizontally placed closed overspeed test device, and the driving end adopts the spline meshing form, which can ensure good coaxiality and smooth transmission of input torque, and has no impact on the equipment; Designing a separate lubrication and cooling oil circuit can greatly improve the lubrication and cooling of the support bearings at both ends, improve the service life of the bearings, and ensure the safe and reliable testing process. In addition, the introduction of vibration value monitoring of test equipment can further improve the safety of personnel and equipment.

Although several embodiments of the present invention have been presented herein, those skilled in the art should understand that changes may be made to the embodiments herein without departing from the spirit of the present invention. The above-mentioned embodiments are only exemplary, and the embodiments herein should not be construed as limiting the scope of the rights of the present invention.

Claims (10)

1. an aircraft generator rotor overspeed testing device, is characterized in that, described device comprises input spline shaft, upper casing, lower casing, tested rotor, cooling oil circuit; the rotor to be tested is placed horizontally in the sealed space formed by the upper casing and the lower casing; The cooling oil circuit is used for cooling and lubricating the bearings at both ends of the rotor under test; One end of the input spline shaft is connected to the drag stage of the power input end, and the other end is connected to the rotor to be tested, and an overload shearing point is set in the middle of the input spline shaft. 2. The aircraft generator rotor overspeed test device according to claim 1, wherein the tested rotor comprises a first end and a second end, and the first end has its own first bearing and a first a bearing seat; the first end of the rotor to be tested is mounted in the upper housing through the first bearing and the first bearing seat; A second bearing seat is arranged in the lower housing, and a support bearing is arranged in the second bearing seat; the support bearing is used for supporting the second end of the rotor to be tested. 3. The aircraft generator rotor overspeed testing device according to claim 2, wherein the device further comprises a vibration sensor disposed at the second end of the rotor to be tested. 4. The aircraft generator rotor overspeed test device according to claim 2, wherein the cooling oil circuit is arranged in the side walls of the upper casing and the lower casing, and the cooling oil passes through the The cooling oil passage reaches the support bearing and the first bearing, and cools and lubricates the support bearing and the first bearing by means of spraying. 5. aircraft generator rotor overspeed testing device as claimed in claim 1 is characterized in that, described input spline shaft and drag stage input shaft are connected by gear meshing mode, described input spline shaft and described tested The rotors are connected by canine teeth. 6. The aircraft generator rotor overspeed test device according to claim 1, wherein the tested rotor is fixedly connected to the lower casing through its own bearing retaining ring, limiting the Axial displacement. 7 . The aircraft generator rotor overspeed test device according to claim 1 , wherein the upper casing and the lower casing are fixedly connected by screws. 8 . 8. The aircraft generator rotor overspeed test device according to any one of claims 1-7, wherein the upper casing is fixed in cooperation with the flange of the drag table through a mounting flange. 9. An aircraft generator rotor overspeed test method, wherein the method uses the device according to any one of claims 1-8, and the method comprises: S1. Install the device on the flange of the drag table, and connect the cooling liquid circulation equipment of the drag table to the cooling oil road of the device; S2. At the beginning of the test, the drag table sets different speed levels, and the drag table transmits torque to the tested rotor through the input spline shaft, which drives the tested rotor to rotate at high speed; at the same time, the cooling oil passes through the cooling oil circuit to the said The support bearing and the first bearing are cooled and lubricated; then the cooling oil is pumped back to the drag table to complete cooling and cooling, and the reciprocating cycle is continued until the overspeed test of all speed levels is completed; S3. The vibration sensor installed at the second end of the rotor to be tested detects the vibration of the rotor to be tested. When the vibration amplitude exceeds the allowable value, real-time shutdown protection occurs; if an emergency overload occurs and the bearing of the rotor to be tested fails, the input spline is cut through the overload protection point. axis to ensure safe and reliable testing. 10. The aircraft generator rotor overspeed test method as claimed in claim 9, characterized in that, in step S2, the rotational speed level is three levels, which are respectively 12000 rpm, 24000 rpm and 30000 rpm.

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