Axial rub-impact test device for rotor and stator of engine

Abstract

The engine rotor and stator axial rub-impact test device comprises a shaft system, a rotor piece, a casing, a stator piece, a hydraulic device and a limiting block, the shaft system comprises a first rotating shaft, a second rotating shaft and a clutch, and the clutch is used for combining or separating the first rotating shaft and the second rotating shaft; the rotor piece is arranged on the second rotating shaft; the casing is positioned outside the shaft system; the stator part is arranged on the casing and is opposite to the rotor part; the hydraulic device is arranged at the axial rear part of the casing and is used for pushing the stator piece to move by virtue of hydraulic force; the limiting block is arranged in front of the casing in the axial direction, and a gap is formed between the limiting block and the casing so as to limit the axial impact of the stator part. The test device can simulate the axial rub-impact of the rotor and the stator.

Description

TECHNICAL FIELD

[0001] The utility model relates to the field of aero-engine, specifically relates to the field of testing device. BACKGROUND

[0002] The rotating shaft of aero-engine connects load system and power system, when the shaft system element fails, it will cause serious consequences. The rotating and static axial rub phenomenon is a common problem under the shaft failure. Therefore, aero-engine needs a test device which can simulate the rotating and static axial rub in the test stage. SUMMARY

[0003] One object of the utility model is to provide a kind of engine rotating and static axial rub test device.

[0004] To achieve the engine rotating and static axial rub test device of above-mentioned purpose includes shafting, rotor piece, casing, stator piece, hydraulic device and limit block, shafting includes first rotating shaft, second rotating shaft and clutch, the clutch is used to combine or separate the first rotating shaft, the second rotating shaft;Rotor piece is arranged on the second rotating shaft;Casing is located outside the shafting;Stator piece is arranged on the casing, and is opposite to the rotor piece;Hydraulic device is arranged in the axial rear of the casing, is used to push the stator piece to move by hydraulic pressure;And limit block, it is arranged in the axial front of the casing, and clearance is formed with the casing, to limit the axial impact of the stator piece.

[0005] In one or more embodiments, the device further comprises an air source for supplying an axial air flow.

[0006] In one or more embodiments, the rotor piece is provided with a counterweight assembly.

[0007] In one or more embodiments, the device further comprises a bracket and a center guide rail, the center guide rail and the shafting are coaxially arranged, the bracket is movably arranged on the center guide rail, and the hydraulic device is arranged on the bracket.

[0008] In one or more embodiments, the hydraulic device comprises a hydraulic cylinder, a piston and a control system, and the control system is used to adjust the size of hydraulic pressure.

[0009] In one or more embodiments, the rotor piece is a low-pressure turbine rotor piece, and the stator piece is a low-pressure turbine stator piece.

[0010] In one or more embodiments, the shafting is supported by a roller bearing and a ball bearing.

[0011] In one or more embodiments, the device further comprises a motor for driving the shafting to rotate.

[0012] The engine rotor-stator axial rub test device uses a clutch to simulate the process of shaft failure, simulates the process of rotor free rotation, and applies a given order, direction and law of axial force to the stator case through a hydraulic actuator, so that the stator piece collides with the rotor axially forward, realizing the simulation of the bidirectional composite motion of the rotor rotation and the stator collision after the shaft failure. BRIEF DESCRIPTION OF DRAWINGS

[0013] The above and other features, properties, and advantages of the present application will become more apparent by describing in detail the following embodiments with reference to the attached drawings and examples, of which:

[0014] Figure 1 is a structural schematic diagram of an aero-engine;

[0015] Figure 2 is a schematic diagram of an engine rotor-stator axial rub test device. DETAILED DESCRIPTION

[0016] The present application will be further described below with reference to specific embodiments and drawings, and more details are set forth in the following description in order to fully understand the present application, but the present application can obviously be implemented in various other ways different from the description, and those skilled in the art can make similar generalizations and deductions according to actual application conditions without departing from the connotation of the present application, therefore the protection scope of the present application should not be limited by the content of the specific embodiments.

[0017] It should be noted that these and other subsequent drawings are only examples, and are not drawn according to the condition of the same scale, and should not be used as a limitation on the actual protection scope required by the present application.

[0018] Figure 1 A simplified twin-rotor turbine engine 100 structure is shown, the engine 100 including a fan 21, a low-pressure compressor 22, a high-pressure compressor 23, a combustor 26, a high-pressure turbine 24, and a low-pressure turbine 25. The low-pressure compressor 22 is driven by the low-pressure turbine 25, and the two are connected by a low-pressure shaft 11, the high-pressure compressor 23 is driven by the high-pressure turbine 24, and the two are connected by a high-pressure shaft 12, the fan shaft 13 is connected and drives the fan 21 and the low-pressure compressor 22, and the fan 21 and the low-pressure compressor 22 are connected by a drum 14.

[0019] The low-pressure compressor 22 includes a rotor component 22a and a stator component 22b, the high-pressure compressor 23 includes a rotor component 23a and a stator component 23b, the high-pressure turbine 24 includes a rotor component 24a and a stator component 24b, and the low-pressure turbine 25 includes a rotor component 25a and a stator component 25b. The rotor components 22a, 23a, 24a and 25a constitute a rotor unit in the engine 100, and the stator components 22b, 23b, 24b and 25b constitute a stator unit in the engine 100.

[0020] The fan compressor connecting end of the low-pressure rotor system is supported by the roller bearing 1 and the ball bearing 2, the turbine connecting end is supported by the roller bearing 5, the compressor connecting end of the high-pressure shaft 12 is supported by the ball bearing 3, and the turbine connecting end is supported by the roller bearing 4. The roller bearings 1, 4 and 5 are mainly used to transmit radial force, and the ball bearings 2 and 3 can simultaneously transmit axial force and radial force. The axial force or radial force on the roller bearing 1, the ball bearing 2 and the ball bearing 3 is mainly transmitted outward through the front load-carrying casing 31, and the force on the roller bearing 4 and the roller bearing 5 is respectively transmitted outward by the turbine inter-stage load-carrying casing 32 and the rear load-carrying casing 33 in the low-pressure turbine stator component 25b. The outer side of the fan 21 is a fan casing 41, and the rear end is a guide vane 51.

[0021] After the main flow path high-energy gas 71 enters the fan 21, it moves backward, is pressurized and accelerated by the low-pressure compressor 22 and the high-pressure stage 23, enters the combustion chamber 26, mixes with fuel and burns, and the high-temperature and high-energy gas formed is discharged from the combustion chamber 26, sequentially passes through the high-pressure turbine 24 and the low-pressure turbine 25, and drives the high-pressure turbine rotor component 24a and the low-pressure turbine rotor component 25a to rotate. The high-pressure turbine rotor component 24a drives the front end high-pressure compressor rotor component 23a to rotate, and the low-pressure turbine rotor component 25a drives the low-pressure compressor rotor component 22a and the fan 21 to rotate.

[0022] When the shaft system element fails due to various reasons, the compressor and turbine components are instantaneously decoupled, and the engine actually enters the "load shedding" stage. At this time, the turbine is still driven by high-energy gas, and the instantaneous decrease in load will cause the turbine rotor speed to rise rapidly, and when the speed reaches the rupture speed of the wheel disc, the engine wheel disc is at risk of rupture. Therefore, it is necessary to determine the maximum possible overspeed of the engine rotor, which includes the rotor overspeed in the extreme case of shaft failure.

[0023] The rapid change in the aerodynamic performance of the turbine input end after the shaft failure will cause the rotor speed to rise rapidly under the driving of the high-energy gas, but at the same time, the turbine rotor will move axially backward under the action of the gas, and when the axial movement distance exceeds the minimum gap between the rotor and the stator, the rotor and the stator will collide. Friction consumes kinetic energy and causes the speed to decrease, forming a "brake" effect. For example, when the shaft failure position occurs in the low-pressure turbine rotor component 25a, the turbine rotor will move axially backward under the action of the gas, and when the axial movement distance exceeds the minimum gap between the rotor and the stator, the rotor and the stator will collide.Figure 1 At position 61 of the low pressure turbine rotor unit 25a, the high energy gas 71 in the flow passage drives the low pressure turbine rotor unit 25a to rotate backward and impact the low pressure turbine stator unit 25b. It is necessary to determine the overspeed of the rotor under the combination of the two cases, i.e., in the extreme case of shaft failure.

[0024] Since the time of this process is extremely short, the test of shaft failure is extremely difficult, and therefore it is necessary to design an effective component-level test to evaluate the rotor-stator rub phenomenon. Based on this, the present disclosure provides an aero-engine rotor-stator axial rub test device to study the rotor-stator axial rub and determine the influence of axial rub on the rotor speed.

[0025] Referring to Figure 2 , the engine rotor-stator axial rub test device includes a shafting 81, a rotor member 86, a casing 88, a stator member 87, and a limiting block 89. The rotor member 86 and the stator member 87 face each other and can be the low pressure turbine rotor member and the low pressure turbine stator member of the real engine.

[0026] The shafting 81 includes a first rotating shaft 811, a second rotating shaft 812, and a clutch 82. The shafting 81 is driven by a motor 80 and is supported by a roller bearing 83 and a ball bearing 84. The clutch 82 is used to combine or separate the first rotating shaft 811 and the second rotating shaft 812. The rotor member 86 is arranged on the second rotating shaft 812 and rotates with the shafting. The clutch 82 includes but is not limited to a friction clutch, an electromagnetic clutch, etc. When the clutch is in the engaged state, the first rotating shaft 811 and the second rotating shaft 812 are connected together, and when the clutch is in the separated state, the first rotating shaft 811 and the second rotating shaft 812 are separated. Thus, the clutch can realize the connection or disconnection of the first rotating shaft 811 and the rotor assembly 86. After disconnection, the free rotation process of the rotor can be simulated.

[0027] The counterweight assembly 85 is connected to the two sides of the rotor member 86. The counterweight assembly 85 increases the rotational kinetic energy of the entire rotor system, simulates the process of the aerodynamic torque continuously working on the rotor, and prolongs the rotor-stator rub process.

[0028] The casing 88 is located outside the shafting 81, and the stator member 87 is arranged on the casing 88 and faces the rotor member 86.

[0029] The hydraulic device 90 is arranged axially behind the casing 88, i.e., on the right side as shown in Figure 2 , for pushing the stator member 97 axially forward by hydraulic pressure. The hydraulic loading system 90 is installed on the bracket 97 and controlled by the central guide rail 98 to control the axial force loading direction. The central guide rail 98 and the shafting 81 are coaxially arranged.

[0030] The hydraulic device 90 mainly includes hydraulic oil 91, piston 92, hydraulic cylinder 93, control system 95 and data line 96, etc. to push the casing 88 to drive the stator 97 to move forward. The key design parameters of the hydraulic loading system 90 need to be determined according to the axial force, for example, by improving the piston area, pressure and number of parameters to control the size of the axial force, setting the control system to respond to the command to control the axial force loading law, to realize the accurate control and fast response of the direction, size and law of the axial force loading.

[0031] In this way, the axial force is loaded on the stator structure by the hydraulic loading device, which promotes the stator structure to axially impact the rotor and rotate and rub with the rotor, realizing the simulation and control of the bidirectional composite motion of the real engine after the shaft failure.

[0032] To limit the movement of the stator, the device also sets a limiting block 89 in the axial direction in front of the casing 88, and forms a gap with the casing 88 to limit the axial impact of the stator, and to control the length of the rubbing process and the degree of rubbing. By adjusting the gap between the limiting block 89 and the casing 88, the degree of axial impact of the casing 88 and the stator 87 can be controlled.

[0033] In some embodiments, the device also includes an air source for supplying axial airflow. The axial airflow flows through the rotor and the stator to simulate the aerodynamic torque.

[0034] During the test, the key parameters of the hydraulic loading system are determined according to the axial force level, and the loading command of the control system is determined according to the axial force variation law. Start the motor to drive the rotor to the preset speed, start the air source to make the axial airflow flow through the rotor and the stator.

[0035] At the preset speed, the clutch is selected to be disengaged at a time, at which the second shaft is free to rotate, driving the rotor to rotate freely. Under the aerodynamic action of the axial airflow, the rotor speed rises rapidly.

[0036] Start the hydraulic loading device to load the axial force, the casing drives the stator to rub with the rotor, and the relevant test parameters are obtained to complete the test.

[0037] The mass and moment of inertia of the rotor counterweight assembly can be adjusted to prolong the rubbing process during the test, and the limiting device can be increased to control the degree of rubbing between the rotor and the stator. This process converts the complex motion of the rotor rotating and impacting the stator backward into the complex motion of the rotor rotating and the stator axially impacting the rotor forward.

[0038] Therefore, the device can simulate the axial rubbing phenomenon between the rotor and the stator of the aero-engine after the shaft failure, the axial force loading level, loading law and loading direction can meet the design requirements, and the axial force loading control precision is high, the control response is fast, and the simulation of the shaft failure at the preset speed of the rotor can be realized.

[0039] It should be noted that the use of the terms "first", "second", etc. to define parts is only for the convenience of distinguishing the corresponding parts, and the above terms have no special meaning unless otherwise stated, and therefore cannot be understood as a limitation on the scope of protection of the present application.

[0040] At the same time, specific terms are used in the present application to describe the embodiments of the present application. For example, "one embodiment", "an embodiment", and / or "some embodiments" means a certain feature, structure or characteristic related to at least one embodiment of the present application. Therefore, it should be emphasized and noted that the "one embodiment" or "one embodiment" or "one alternative embodiment" mentioned in different positions in the specification does not necessarily refer to the same embodiment. In addition, some features, structures or characteristics of one or more embodiments of the present application can be properly combined.

[0041] Although the utility model discloses the above-mentioned with preferable embodiment, it is not used to limit the utility model, and any person skilled in the art can make possible change and modification without departing from the spirit and scope of the utility model. Therefore, any modification, equivalent change and modification made to the above-mentioned embodiment according to the technical essence of the utility model, which does not deviate from the technical scheme of the utility model, falls within the protection scope defined by the claims of the utility model.

Claims

1. An engine rotor-stator rub test apparatus, characterized by, The device comprises: a shaft system comprising a first rotating shaft, a second rotating shaft and a clutch for coupling or decoupling the first rotating shaft and the second rotating shaft; a rotor arranged on the second rotating shaft; a casing located outside the shaft system; a stator arranged on the casing and facing the rotor; a hydraulic device arranged axially behind the casing and used for moving the stator by hydraulic pressure; and a limiting block arranged axially in front of the casing and forming a gap with the casing to limit the axial impact of the stator. The device further comprises an air source for supplying axial air flow.

2. The test device of claim 1, wherein A counterweight assembly is arranged on the rotor.

3. The test device of claim 1, wherein The device further comprises a support and a central guide rail coaxially arranged with the shaft system, and the support is movably arranged on the central guide rail, and the hydraulic device is arranged on the support.

4. The test device of claim 1, wherein The hydraulic device comprises a hydraulic cylinder, a piston and a control system for adjusting the hydraulic pressure.

5. The test device of claim 1, wherein The rotor is a low-pressure turbine rotor, and the stator is a low-pressure turbine stator.

6. The test device of claim 1, wherein The shaft system is supported by a roller bearing and a ball bearing.

7. The test device of claim 1, wherein The device further comprises a motor for driving the shaft system to rotate.

8. The test device of claim 1, wherein ​

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