Engine rotor piece runout measurement method and system

Abstract

The engine rotor piece runout measurement method is used for measuring a rotor piece located in an inner cavity of a whole engine, the whole engine comprises a hole, and the method comprises the following steps that a runout measurement optical fiber probe is installed on a crawling device, and the crawling device penetrates through the hole and enters the inner cavity of the whole engine; enabling the crawling device to move to a static part, close to a rotor part, of an inner cavity of the whole engine; and the rotor part is operated, the jump measurement optical fiber probe is used to obtain jump data of the rotor part, and then a jump test result is obtained. According to the rotor piece runout measurement method, runout measurement of rotor pieces at different cross sections in a complete machine can be realized on the premise that the complete machine of the engine is not disassembled. The invention also provides an engine rotor piece runout measurement system.

Description

Technical Field

[0001] The present invention relates to the field of aviation engines, and in particular to the field of engine assembly. Background Art

[0002] The assembly technology of the engine is directly related to the engine performance, safety, reliability and stability. In the state of the complete aircraft engine, the inner cavity is a blind cavity, the rotor and stator are coupled, and the high and low pressures are coupled. The accessibility and visibility are poor, and the measurement and detection methods are stretched. There is currently no effective method to measure the rotor vibration of the complete engine state, and there is no effective evaluation method for the assembly quality of the complete engine, and a complete closed-loop control of the assembly quality has not been formed. In view of this, it is necessary to propose a measurement method for the complete engine to solve the above problems. Summary of the invention

[0003] An object of the present invention is to provide a method for measuring the vibration of an engine rotor component, which can realize the vibration measurement of rotor components with different cross-sections in the entire engine without disassembling the entire engine.

[0004] To achieve the above-mentioned purpose, the engine rotor component vibration measurement method is used to measure the rotor component located in the inner cavity of the engine, and the engine includes an orifice. The method includes the following steps: installing the vibration measurement fiber optic probe on the crawling device, and allowing the crawling device to pass through the orifice and enter the inner cavity of the engine; moving the crawling device to a stationary position of the inner cavity of the engine close to the rotor component; operating the rotor component, and using the vibration measurement fiber optic probe to obtain the vibration data of the rotor component, and then obtaining the vibration test result.

[0005] In one or more embodiments, the engine assembly includes a borescope observation window, and opening the borescope observation window allows the engine assembly to generate an opening leading to an inner cavity of the engine assembly.

[0006] In one or more embodiments, the engine assembly includes a casing and a tubular member located outside the casing, and the end plug of the tubular member is removed, so that the tubular member is used to create an opening in the engine assembly leading to the inner cavity of the engine assembly.

[0007] In one or more embodiments, a plurality of crawling devices are used to respectively perform the runout measurement of different rotor components at different positions within the entire engine.

[0008] In one or more embodiments, the rotor component includes a shaft, a disk, a bucket, and a drum.

[0009] In one or more embodiments, the stationary part includes a comb-toothed compression nut cylinder, a connecting nut cylinder, a stator, a wheel disc, a casing, a disc cavity, and a bearing cavity.

[0010] In one or more embodiments, the radial runout data of the rotor member is obtained using the runout measurement fiber optic probe.

[0011] Another object of the present invention is to provide an engine rotor component vibration measurement system, which is used to operate the above-mentioned engine rotor component vibration measurement method. The measurement system includes a vibration measurement component, a crawling device and a control device. The vibration measurement component includes a vibration measurement optical fiber probe, a data acquisition module and a signal processing module; the crawling device is used to detachably carry the vibration measurement optical fiber probe; the control device is connected to the crawling device and the vibration measurement component in a bidirectional signal manner.

[0012] In one or more embodiments, the crawling device includes a driving system, a walking system, a posture adjustment system, a lighting system, a calibration device, and a fiber optic probe fixing device.

[0013] In one or more embodiments, the body length of the crawling device is no more than 30 mm, and the width and height are no more than 7 mm.

[0014] The above-mentioned engine rotor component vibration measurement method and system take into account the overall structural form of the engine as a whole, and propose to use the orifices provided on the engine as a whole as the measurement entrance, such as the borescope observation window or the connection ports between the ventilation pipeline, the oil return pipeline and the casing, so that the crawling device carrying the measurement device passes through the above-mentioned orifices, and the vibration of each rotor component in the engine as a whole is measured without destroying or disassembling the engine as a whole, thus reducing unnecessary disassembly work and being able to obtain test data on the assembly quality of the aircraft engine as a whole. In addition, through the test data of multiple components, various assembly qualities such as the centering effect of the bearings in the aircraft engine as a whole and the operation of the bearings can also be evaluated. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] The above and other features, properties and advantages of the present invention will become more apparent through the following description in conjunction with the accompanying drawings and embodiments, in which:

[0016] Figure 1 It is a flow chart of the whole engine measurement method;

[0017] Figure 2A This is a schematic diagram of measuring the compression nut of the front grate teeth at the front end of the high-pressure rotor through the ventilation pipe;

[0018] Figure 2B is a schematic diagram of the path through the ventilation duct;

[0019] Figure 3 It is a schematic diagram of measuring the rotor blade tip through the high-pressure rotor borescope hole;

[0020] Figure 4It is a schematic diagram of measuring the rotor disc by extending the lead hole of the casing;

[0021] Figure 5 It is a schematic diagram of measuring the high-vortex rotor position through the high-pressure turbine borescope;

[0022] Figure 6 It is a schematic diagram of measuring the four-point bearing cavity through the interstage casing oil drain pipe. DETAILED DESCRIPTION

[0023] The present invention is further described below in conjunction with specific embodiments and drawings. More details are elaborated in the following description to facilitate a full understanding of the present invention. However, the present invention can obviously be implemented in a variety of other ways different from the description herein. Those skilled in the art can make similar generalizations and deductions based on actual application situations without violating the connotation of the present invention. Therefore, the protection scope of the present invention should not be limited by the content of this specific embodiment.

[0024] It should be noted that these and other subsequent drawings are only examples and are not drawn to scale, and should not be used to limit the actual scope of protection required by the present invention.

[0025] The complete engine is also called the engine assembly, which includes the assembled core engine, casing, and the complex cross-intake and exhaust pipes, various pipelines and parts located on the outside of the casing. The assembly process of the complete engine is relatively tedious and meticulous, usually taking several days or even months.

[0026] After the engine is assembled, it is not easy to disassemble the whole machine, and the inner cavity is a blind cavity, but there is still a need to measure the components in the whole machine to ensure that the assembly quality of the whole machine meets the requirements. The engine whole machine measurement method disclosed in the present invention does not require complex operations such as decomposition and disassembly of the engine, but directly performs corresponding measurements on the aircraft engine whole machine, reducing unnecessary decomposition work and facilitating overall analysis and research.

[0027] The engine has relatively large openings such as the borescope observation window, ventilation pipeline, and oil return pipeline. This method uses the existing openings on the engine as a channel for the measuring component to enter the engine. The method includes steps S12-S13: installing the vibration measurement fiber optic probe on the crawling device, and passing the crawling device through the hole to enter the inner cavity of the engine; moving the crawling device to a stationary position of the inner cavity of the engine close to the rotor; operating the rotor, and using the vibration measurement fiber optic probe to obtain the vibration data of the rotor.

[0028] The term "rotor component" refers to the components that produce circular motion when the engine is in operation, such as shafts, impellers, moving blades, drums, etc.

[0029] The term "stationary part" in step S13 refers to a part that does not move when the engine is in operation, such as a comb tooth pressing nut cylinder, a connecting nut cylinder, a stator, a casing, a disc cavity, a bearing cavity, etc.

[0030] Specifically, you can Figure 1 The steps S101 and S102 shown enable the engine assembly to generate an opening leading to the inner cavity of the engine assembly.

[0031] One way is to open the borescope observation window on the engine assembly; another way is to remove the end plug of the tubular member and use the tubular member itself to create an opening leading to the inner cavity of the engine assembly.

[0032] The tubular parts include pipelines and lines. The pipelines are, for example, ventilation pipes, oil return pipes, oil drain pipes, etc. The pipelines are, for example, "hydraulic pipes" of hydraulic systems with larger diameters, cables of electronic systems, and lubricating oil lines of lubrication systems.

[0033] It is understandable that any openings on the entire machine can be applied to the present method, such as extending the lead hole of the receiver, without being limited to the above method.

[0034] The position of the orifice is determined according to the position of the rotor part to be measured. For example, if the rotor part to be measured is a high-pressure rotor wheel, the orifice close to the high-pressure rotor of the compressor is selected. A crawling device is used to carry the measuring assembly; the crawling device is driven by an engine to pass through the opening and / or pipeline, and the measuring assembly is sent to the part to be measured for measurement, thereby reducing the disassembly state of the parts. Preferably, the radial runout of the rotor part is measured.

[0035] After the crawling device passes through the opening of the engine and enters the inner cavity of the engine, the crawling device can also pass through the extended casing lead hole in the inner cavity of the engine to move in the inner cavity of the engine.

[0036] Combined with the above introduction to the engine rotor component vibration measurement method, it can also be understood that an engine rotor component vibration measurement system includes a vibration measurement component, a crawling device and a control device. The vibration measurement component includes a vibration measurement optical fiber probe, a data acquisition module and a signal processing module; the crawling device is used to detachably carry the vibration measurement optical fiber probe; the control device is connected to the crawling device and the vibration measurement component by two-way signal to transmit data and control instructions in both directions.

[0037] Specifically, the crawling device is preferably a micro robot, including a drive system, a walking system, a posture adjustment system, a lighting system, a calibration device, and a fiber optic probe fixing device. In some embodiments, the robot body length is not more than 30mm, the width and height are not more than 7mm, and the maximum crawling speed of the robot is 150mm / s, that is, 5 times the body length. The load capacity is greater than 5g. The micro robot as a crawling device has a faster crawling speed and better maneuverability, and can achieve crawling motion in straight lines, arcs, and other trajectories, with a minimum turning radius of about 30mm.

[0038] The runout measurement component is a fiber optic measuring device. For example, the runout measurement fiber optic probe can be a laser displacement sensor. By being set at a stationary position close to the rotor part, it uses a high-frequency light spot to detect the vibration value and runout value on the measuring surface of the rotor part to be measured, and transmits the data to the data acquisition module for processing through the signal processing module to obtain the runout value of the rotor part.

[0039] In some embodiments, the vibration measurement fiber optic probe is small in size, and the fiber diameter is no more than 3mm, which can be easily carried by the crawling device into the inner cavity of the whole machine. The measuring range is preferably 0.3mm. When the sampling frequency is 100hz, the accuracy is 0.15μm; when the sampling frequency is 200hz, the accuracy is 2.5μm. The fiber optic measuring device is carried by a micro robot into the inner cavity of the entire engine for measurement. For example, the fiber optic measuring device is sent into the orifice of the ventilation pipe and other pipelines to perform a vibration test on the front comb teeth compression nut of the high-pressure rotor front end, and the rotor blade tip is measured through the high-pressure rotor borescope hole.

[0040] The measurement process includes debugging and calibration of the measurement system - the robot carries the measurement device into the engine cavity to measure the part - side head posture adjustment - measurement - data collection - data analysis - end of measurement. This measurement solution disassembles very few engine components, which can realize line maintenance, reduce overhaul disassembly actions, and save cycle and labor costs.

[0041] The above-mentioned engine rotor component vibration measurement system and method can perform vibration measurement on multiple rotor components to be measured. For example, by analyzing the radial vibration quality of different cross sections of the engine's high-pressure rotor, not only can a qualitative analysis of the rotor blade wear be obtained, but also the stability and smoothness of the engine bearing operation can be grasped. It is also a means of inspecting the load-bearing system of the engine stator casing, that is, the coaxial alignment effect of the bearing seat is also monitored and observed.

[0042] The above-mentioned engine rotor component runout measurement system and method, based on traditional borescope inspection and troubleshooting, can perform radial runout measurement on different rotor components with different cross-sections through a measuring device without the need to disassemble the entire engine, thereby facilitating the acquisition of runout data of multiple installed rotor components, reducing unnecessary disassembly work, and saving cycle and labor costs.

[0043] The following introduces the engine rotor component vibration measurement system and method through a specific vibration measurement embodiment.

[0044] Reference Figure 2A-Figure 6 As shown, for the whole engine, five positions can be selected to obtain the measurement section of the high-pressure rotor: the front comb teeth clamping nut cylinder at the front end of the IGB, the high-pressure rotor blade tip in the middle, the high-pressure rotor disc, the high-pressure turbine rotor tip at the rear end, and the four-point bearing cavity of the interstage casing, which are used to measure the runout of the front shaft diameter, the high-pressure rotor disc, and the rear shaft diameter, respectively.

[0045] The runout measurement of the high-pressure rotor in the complete machine state can be carried out by moving a highly maneuverable micro-crawling device to a stationary position such as the nut cylindrical surface, the inner peripheral surface of the bearing cavity, the casing, etc., and placing a runout measurement fiber optic probe.

[0046] The accessory drive gearbox is driven by an external motor to rotate the entire engine, thereby achieving stable and slow movement of the high-pressure rotor.

[0047] For the runout measurement of the shaft diameter at the front end of the high-pressure rotor, the runout measurement optical fiber probe and crawling device are sent in through the ventilation pipe of the intermediate casing, see Figure 2A-2B The path R shown is used to move the crawler device to the front comb teeth clamping nut at the front end of the high-pressure rotor to measure the runout of the front end shaft diameter.

[0048] For the runout measurement of the high-pressure turntable in the middle of the high-pressure rotor, the runout measurement fiber optic probe and the crawling device can be inserted through the borescope observation window. The borescope hole diameter is about 8mm, and the engine high-pressure rotor tip clearance range is about 0.75-1.5mm. The measuring device can be used to measure the rotor blade tip runout. Figure 3 The borescope positions A1-A8 of each stage of the moving blades are shown.

[0049] For the measurement of the turntable runout at the middle position of the high-pressure rotor, the opening where the lead hole of the extended casing is located can be used, such as Figure 4 At position C shown, the optical fiber measuring device is transported and placed into the disc cavity of the turbine rotor to perform runout measurement on the rotating disc.

[0050] The high-pressure turbine can be observed through the borescope observation window. The borescope hole diameter is about 10mm. The highly maneuverable micro-crawling device can be transported through the borescope hole to place the optical fiber measurement device into the disc cavity of the turbine rotor to measure the blade tip runout. Figure 5 The borescope position is shown at H in the middle.

[0051] For the radial runout of the high-pressure turbine rotor at the interstage casing, the optical fiber measuring device can be transported and placed in the four-point bearing cavity through the oil drain pipe for runout measurement. Figure 6Path D.

[0052] By analyzing the radial runout quality of different sections of the high-pressure rotor of the engine, a qualitative analysis of the rotor blade scraping can be obtained, and the stability and smoothness of the engine bearing operation can be grasped. It is also a means of testing the load-bearing system of the engine stator casing, that is, the coaxial alignment effect of the bearing seat is also monitored and observed. The above method and system can make up for the lack of effective evaluation methods for the assembly quality of traditional aircraft engines at home and abroad, and realize relevant tests in the inner cavity of the whole machine under the premise of disassembling very few engine components.

[0053] The present application uses specific words to describe the embodiments of the present application. For example, "one embodiment", "an embodiment", and / or "some embodiments" refer to a certain feature, structure or characteristic related to at least one embodiment of the present application. Therefore, it should be emphasized and noted that "one embodiment" or "an embodiment" or "an alternative embodiment" mentioned twice or multiple times in different positions in this specification does not necessarily refer to the same embodiment. In addition, some features, structures or characteristics in one or more embodiments of the present application can be appropriately combined.

[0054] Although the present invention is disclosed as above with preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications without departing from the spirit and scope of the present invention. Therefore, any modification, equivalent change and modification made to the above embodiments according to the technical essence of the present invention without departing from the content of the technical solution of the present invention shall fall within the protection scope defined by the claims of the present invention.

Claims

1. A method for measuring the runout of an engine rotor component, used for measuring a rotor component located in an inner cavity of an engine complete machine, wherein the engine complete machine has an orifice, characterized in that: The method comprises the following steps: Installing the runout measurement optical fiber probe on the crawling device, allowing the crawling device to pass through the hole and enter the inner cavity of the engine; The crawling device is moved to a stationary position of the inner cavity of the engine close to the rotor member; The rotor component is operated, and the runout data of the rotor component is obtained using the runout measurement optical fiber probe.

2. The engine rotor component vibration measurement method according to claim 1, characterized in that: The engine assembly includes a borescope observation window, and opening the borescope observation window allows the engine assembly to generate an opening leading to the inner cavity of the engine assembly.

3. The engine rotor component vibration measurement method according to claim 1, characterized in that: The engine assembly comprises a casing and a tubular component located outside the casing. The end plug of the tubular component is removed, and then the tubular component is used to form an opening leading to the inner cavity of the engine assembly.

4. The engine rotor component runout measurement method according to claim 1, characterized in that: A plurality of crawling devices are used to respectively measure the vibration of different rotor parts at different positions in the entire engine.

5. The engine rotor component runout measurement method according to claim 1, characterized in that: The rotor components include a shaft, a wheel disc, moving blades and a drum.

6. The engine rotor component runout measurement method according to claim 1, characterized in that: The stationary part comprises a comb teeth pressing nut cylindrical surface, a connecting nut cylindrical surface, a stator component, a casing, a disc cavity, and a bearing cavity.

7. The engine rotor component runout measurement method according to claim 1, characterized in that: The radial runout data of the rotor component is obtained using the runout measurement optical fiber probe.

8. Engine rotor vibration measurement system, characterized in that: The engine rotor component vibration measurement method according to any one of claims 1 to 7 is performed, and the measurement system comprises: A runout measurement component, including a runout measurement optical fiber probe, a data acquisition module and a signal processing module; a crawling device for detachably carrying the beat measurement optical fiber probe; and The control device is connected to the crawling device and the vibration measurement component via two-way signals.

9. The engine rotor component runout measurement system according to claim 8, characterized in that: The crawling device comprises a driving system, a walking system, a posture adjustment system, a lighting system, a calibration device and a fiber optic probe fixing device.

10. The engine rotor component runout measurement system according to claim 8, characterized in that: The body length of the crawling device is no more than 30 mm, and the width and height are no more than 7 mm.

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