CN113432847A - Aeroengine rotor simulation test measurement system - Google Patents
Aeroengine rotor simulation test measurement system Download PDFInfo
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- CN113432847A CN113432847A CN202110546211.5A CN202110546211A CN113432847A CN 113432847 A CN113432847 A CN 113432847A CN 202110546211 A CN202110546211 A CN 202110546211A CN 113432847 A CN113432847 A CN 113432847A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01D—MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE; ARRANGEMENTS FOR MEASURING TWO OR MORE VARIABLES NOT COVERED IN A SINGLE OTHER SUBCLASS; TARIFF METERING APPARATUS; MEASURING OR TESTING NOT OTHERWISE PROVIDED FOR
- G01D21/00—Measuring or testing not otherwise provided for
- G01D21/02—Measuring two or more variables by means not covered by a single other subclass
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/02—Details or accessories of testing apparatus
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Abstract
The invention belongs to the technical field of aero-engine rotor dynamics, and particularly relates to a measuring system for an aero-engine rotor simulation test, which comprises: the device comprises a cantilever rotor testing device, an oil lubricating unit and a multi-physical-quantity acquisition device; the oil lubricating unit can perform circulating oil lubrication on the cantilever rotor testing device; the multi-physical quantity acquisition device can acquire various physical quantity data shown by the cantilever rotor test device in a simulation test; the plurality of physical quantity data includes at least: chip data, temperature data, eddy current data, acceleration data and displacement data in circulating oil lubrication. The simulation test system provided by the invention can truly simulate the dynamic evolution process of the aircraft engine rotor during operation, and simultaneously, the multi-physical-field synchronous measurement can record the change of each physical quantity parameter of the rotor simulation test system in real time.
Description
Technical Field
The invention belongs to the technical field of aero-engine rotor dynamics, and particularly relates to a simulation test measuring system for an aero-engine rotor.
Background
At present, with the improvement of the power performance requirement of the five-generation engine on the aeroengine, the power-weight ratio of the small and medium turbine shaft engine is gradually improved. The main reason for the improvement of the power performance of the aircraft engine is the increase of the engine speed. Therefore, in the process of engine development and development, the importance of the dynamic development of the high-speed rotor of the aircraft engine is greatly increased, and particularly, the dynamic characteristics of the rotor of the aircraft engine are very important. Researchers need to fully test rotor systems during the development phase of new machines.
Most of the domestic rotor test beds are too simple, can only measure a single physical quantity, cannot truly simulate the actual working environment of an engine, and meanwhile, a few rotor simulation systems can collect two or even more than two physical quantities, but cannot realize synchronous collection, and can only manually calibrate collection time, and certain time deviation exists in collection of each physical quantity.
Disclosure of Invention
Technical problem to be solved
Aiming at the existing technical problems, the invention provides a measuring system for an aircraft engine rotor simulation test, which can truly simulate the dynamic evolution process of the aircraft engine rotor during operation, and simultaneously, the multi-physical-field synchronous measurement can record the change of each physical quantity parameter of the rotor simulation test system in real time. The method contributes to improving and improving the related structural design of the engine rotor system, modifying and perfecting the related design standard of the product, promoting the development of new models and prolonging the service life of the engine.
(II) technical scheme
In order to achieve the purpose, the invention adopts the main technical scheme that:
an aircraft engine rotor simulation test measurement system, comprising: the device comprises a cantilever rotor testing device, an oil lubricating unit and a multi-physical-quantity acquisition device;
the oil lubricating unit can perform circulating oil lubrication on the cantilever rotor testing device;
the multi-physical quantity acquisition device can acquire various physical quantity data shown by the cantilever rotor test device in a simulation test;
the plurality of physical quantity data includes at least: chip data, temperature data, eddy current data, acceleration data and displacement data in circulating oil lubrication.
Preferably, the cantilever rotor testing apparatus comprises: the method comprises the following steps: the device comprises a T-shaped groove platform, a high-speed motor, a spline transmission shaft, a slender shaft, a short shaft, a movable turbine disc and a supporting device;
the high-speed motor, the spline transmission shaft, the slender shaft, the short shaft and the moving turbine disc are arranged on the T-shaped groove platform by means of the supporting device;
the high-speed motor is in transmission connection with one end of the slender shaft by means of the spline transmission shaft;
the other end of the slender shaft is connected with the short shaft in an interference fit manner;
the moving turbine disc is arranged on the short shaft;
the high-speed motor can drive the moving turbine disc to rotate by means of the slender shaft, and is used for simulating dynamic evolution of an aircraft engine rotor during operation.
Preferably, the supporting means comprises: the motor support seat, the auxiliary support seat, the front support seat and the rear support seat;
the high-speed motor is arranged on the motor supporting seat;
the slender shaft is respectively arranged on the front supporting seat and the rear supporting seat in a penetrating way;
the spline transmission shaft is arranged on the auxiliary supporting seat;
the short shaft is provided with a bearing, and can freely rotate on the rear supporting seat by virtue of the bearing;
the motor supporting seat, the auxiliary supporting seat, the front supporting seat and the rear supporting seat are sequentially and fixedly arranged on a T-shaped groove of the T-shaped groove platform.
Preferably, the oil lubricating unit includes: the oil tank, the oil supply pipeline with the oil supply pump, and the oil return pipeline with the oil return pump;
one end of the oil supply pipeline is communicated with the oil tank, and the other end of the oil supply pipeline supplies oil to the lubricating oil circuit of the movable turbine disc and the short shaft;
one end of the oil return pipeline is communicated with the lubricating oil way, and the other end of the oil return pipeline returns oil into the oil tank.
Preferably, the multiple physical quantity acquisition apparatus includes: the device comprises a data recording and sorting terminal, a chip acquisition unit, a temperature acquisition unit, an eddy current acquisition unit, an acceleration acquisition unit and a displacement acquisition unit;
the chip acquisition unit can acquire chip data in the oil return pipeline and send the acquired chip data to the data recording and sorting terminal;
the temperature acquisition unit can acquire temperature data of the outer ring of the bearing on the short shaft and send the acquired temperature data to the data recording and sorting terminal;
the eddy current acquisition unit can acquire eddy current data on the slender shaft and send the acquired eddy current data to the data recording and sorting terminal;
the acceleration acquisition unit can acquire acceleration data of the slender shaft and send the acquired acceleration data to the data recording and sorting terminal;
the displacement acquisition unit can acquire the displacement data of the slender shaft and send the acquired displacement data to the data recording and sorting terminal.
Preferably, the chip collecting unit comprises: a scrap collecting card and a scrap sensor;
the chip acquisition card is in data connection with the chip sensor;
the chip sensor is arranged on the oil return pipeline and used for collecting chip data;
the chip sensor can send the collected chip data to the chip collecting card;
the chip acquisition card is used for sending chip data to the data recording and sorting terminal.
Preferably, the temperature acquisition unit includes: a temperature acquisition card and a temperature sensor;
the temperature acquisition card is in data connection with the temperature sensor;
the temperature sensor is in contact with the outer ring of the bearing on the short shaft and is used for acquiring temperature data;
the temperature sensor can send the acquired temperature data to the temperature acquisition card;
the temperature acquisition card is used for sending temperature data to the data recording and sorting terminal.
Preferably, the eddy current collecting unit includes: the eddy current acquisition card and the eddy current sensor;
the eddy current acquisition card is in data connection with the eddy current sensor;
the eddy current sensor measures the slender shaft in a non-contact mode and is used for collecting eddy current data;
the eddy current sensor can send acquired eddy current data to the eddy current acquisition card;
the eddy current acquisition card is used for sending eddy current data to the data recording and sorting terminal;
the acceleration acquisition unit includes: an acceleration acquisition card and an acceleration sensor;
the acceleration acquisition card is in data connection with the acceleration sensor;
the acceleration sensor is arranged on the supporting device and used for acquiring acceleration data of the slender shaft;
the acceleration sensor can send the acquired acceleration data to the acceleration acquisition card;
the acceleration acquisition card is used for sending acceleration data to the data recording and sorting terminal.
Preferably, the displacement acquisition unit includes: a displacement acquisition card and a displacement sensor;
the displacement acquisition card is in data connection with the displacement sensor;
the displacement sensor is arranged on the supporting device and used for acquiring displacement data of the slender shaft;
the displacement sensor can send the collected displacement data to the displacement collection card;
the displacement acquisition card is used for sending displacement data to the data recording and sorting terminal.
Preferably, the method further comprises the following steps: an oil-gas lubrication unit;
the oil-gas lubricating unit is used for lubricating the auxiliary supporting seat and the front supporting seat;
the oil-air lubrication unit includes: the system comprises an air compressor, an air storage tank, an oil-gas mixing device and an oil gas pipeline;
the air compressor is connected with the air storage tank and can transmit air into the oil-gas mixing device;
the oil-gas mixing device is connected with the oil-gas transmission pipeline, and lubricating oil gas is respectively transmitted to the auxiliary supporting seat and the front supporting seat by means of the oil-gas transmission pipeline.
(III) advantageous effects
The invention has the beneficial effects that: the invention provides a simulation test measurement system for an aircraft engine rotor, which has the following beneficial effects:
the dynamic evolution process of the aircraft engine rotor during operation can be simulated really, and the change of each physical quantity parameter of the rotor simulation system can be recorded in real time by the multi-physical-field synchronous measurement method. The method contributes to improving and improving the related structural design of the engine rotor system, modifying and perfecting the related design standard of the product, promoting the development of new models and prolonging the service life of the engine.
Drawings
Fig. 1 is a schematic structural diagram of a simulation test measurement system for an aircraft engine rotor provided by the invention.
Fig. 2 is a schematic structural diagram of a cantilever rotor testing device in an aircraft engine rotor simulation test measurement system provided by the invention.
Fig. 3 is a schematic diagram of a lubricating oil path design of a moving turbine disc in a simulation test measurement system for an aircraft engine rotor provided by the invention.
[ description of reference ]
1: a T-shaped groove platform; 2: a high-speed motor; 3: a spline transmission shaft; 4: an elongated shaft; 5: a front support base; 6: a rear support base; 7: a first-stage equivalent turbine disk; 8: a second stage equivalent turbine disk; 9: an acceleration sensor; 10: an eddy current sensor; 11: a temperature sensor.
Detailed Description
For the purpose of better explaining the present invention and to facilitate understanding, the present invention will be described in detail by way of specific embodiments with reference to the accompanying drawings.
As shown in fig. 1: the embodiment of the invention discloses an aeroengine rotor simulation test measurement system, includes: the device comprises a cantilever rotor testing device, an oil lubricating unit and a multi-physical-quantity acquisition device; the oil lubricating unit can perform circulating oil lubrication on the cantilever rotor testing device; the multi-physical quantity acquisition device can acquire various physical quantity data shown by the cantilever rotor test device in a simulation test; the plurality of physical quantity data includes at least: chip data, temperature data, eddy current data, acceleration data and displacement data in circulating oil lubrication.
It should be noted that: the temperature data refers to temperature data of the bearing when the cantilever rotor is tested, the eddy current data refers to eddy current data of the cantilever rotor when the cantilever rotor is tested, and the acceleration data and the displacement data refer to vibration signal data of the cantilever rotor when the cantilever rotor is tested.
Specifically, as shown in fig. 2: the cantilever rotor test device in this embodiment includes: the method comprises the following steps: t type groove platform 1, high-speed motor 2, spline transmission shaft 3, slender axles 4, minor axis, move turbine dish and strutting arrangement.
The high-speed motor 2, the spline transmission shaft 3, the slender shaft 4, the short shaft and the moving turbine disc are arranged on the T-shaped groove platform 1 by means of the supporting device; the high-speed motor 2 is in transmission connection with one end of the slender shaft 4 by means of the spline transmission shaft 3; the other end of the slender shaft 4 is connected with the short shaft in an interference fit manner; the moving turbine disc is arranged on the short shaft; the high-speed motor 2 can drive the moving turbine disc to rotate by means of the slender shaft 4, and is used for simulating dynamic evolution of an aircraft engine rotor during operation. Here the elongate shaft 4 and the moving turbine disk are used to simulate a rotor.
In this embodiment, the support device includes: the motor support seat, the auxiliary support seat, the front support seat 5 and the rear support seat 6; the high-speed motor 2 is arranged on the motor supporting seat; the slender shaft 4 is respectively arranged on the front supporting seat 5 and the rear supporting seat 6 in a penetrating way; the spline transmission shaft 3 is arranged on the auxiliary supporting seat; the short shaft is provided with a bearing, and can freely rotate on the rear supporting seat 6 by virtue of the bearing; the motor supporting seat, the auxiliary supporting seat, the front supporting seat 5 and the rear supporting seat 6 are sequentially and fixedly arranged on the T-shaped groove of the T-shaped groove platform 1.
It should be noted that: the moving turbine disk herein comprises: a first-stage equivalent turbine disk 7 and a second-stage equivalent turbine disk 8; the first-stage equivalent turbine disk 7 and the second-stage equivalent turbine disk 8 are equivalent to the secondary turbine of the aircraft engine in terms of structure, mass and inertia coefficient.
The oil lubrication unit in this embodiment includes: the oil tank, the oil supply pipeline with the oil supply pump, and the oil return pipeline with the oil return pump; one end of the oil supply pipeline is communicated with the oil tank, and the other end of the oil supply pipeline supplies oil to the lubricating oil circuit of the movable turbine disc and the short shaft; one end of the oil return pipeline is communicated with the lubricating oil way, and the other end of the oil return pipeline returns oil into the oil tank.
As shown in fig. 3: the lubricating oil path is designed to lubricate a bearing in the moving turbine disc by adopting an oil lubricating unit, when the bearing is worn, the generated chips return to the oil tank along the oil return path through the chip sensor, and the size and the quantity of the chips in the oil path are also collected by the chip sensor.
The multi-physical quantity acquisition apparatus described in this embodiment includes: the device comprises a data recording and sorting terminal, a chip acquisition unit, a temperature acquisition unit, an eddy current acquisition unit, an acceleration acquisition unit and a displacement acquisition unit; the chip acquisition unit can acquire chip data in the oil return pipeline and send the acquired chip data to the data recording and sorting terminal; the temperature acquisition unit can acquire temperature data of the outer ring of the bearing on the short shaft and send the acquired temperature data to the data recording and sorting terminal; the eddy current acquisition unit can acquire eddy current data on the slender shaft and send the acquired eddy current data to the data recording and sorting terminal; the acceleration acquisition unit can acquire acceleration data of the slender shaft and send the acquired acceleration data to the data recording and sorting terminal; the displacement acquisition unit can acquire the displacement data of the slender shaft and send the acquired displacement data to the data recording and sorting terminal.
It should be noted that: the data record arranging terminal comprises an acquisition instrument and intelligent terminal equipment, such as a computer and the like.
The chip collecting unit in this embodiment comprises: a scrap collecting card and a scrap sensor; the chip acquisition card is in data connection with the chip sensor; the chip sensor is arranged on the oil return pipeline and used for collecting chip data; the chip sensor can send the collected chip data to the chip collecting card; the chip acquisition card is used for sending chip data to the data recording and sorting terminal.
In this embodiment, the temperature acquisition unit includes: a temperature acquisition card and a temperature sensor 11; the temperature acquisition card is in data connection with the temperature sensor 11; the temperature sensor 11 is in contact with the outer ring of the bearing on the short shaft and used for acquiring temperature data; the temperature sensor 11 can send the acquired temperature data to the temperature acquisition card; the temperature acquisition card is used for sending temperature data to the data recording and sorting terminal.
The eddy current collection unit described in this embodiment includes: an eddy current acquisition card and an eddy current sensor 10; the eddy current acquisition card is in data connection with the eddy current sensor 10; the eddy current sensor 10 measures the slender shaft 4 in a non-contact mode and is used for collecting eddy current data; the eddy current sensor 10 can send the acquired eddy current data to the eddy current acquisition card; the eddy current acquisition card is used for sending eddy current data to the data recording and sorting terminal; the acceleration acquisition unit includes: an acceleration acquisition card and an acceleration sensor 9; the acceleration acquisition card is in data connection with the acceleration sensor 9; the acceleration sensor 9 is arranged on the supporting device and used for acquiring acceleration data of the slender shaft 4; the acceleration sensor 9 can send the acquired acceleration data to the acceleration acquisition card; the acceleration acquisition card is used for sending acceleration data to the data recording and sorting terminal.
The displacement acquisition unit in this embodiment includes: a displacement acquisition card and a displacement sensor; the displacement acquisition card is in data connection with the displacement sensor; the displacement sensor is arranged on the supporting device and used for acquiring displacement data of the slender shaft 4; the displacement sensor can send the collected displacement data to the displacement collection card; the displacement acquisition card is used for sending displacement data to the data recording and sorting terminal.
The aeroengine rotor simulation test measurement system that provides in this embodiment still includes: an oil-gas lubrication unit; the oil-gas lubricating unit is used for lubricating the auxiliary supporting seat and the front supporting seat; the oil-air lubrication unit includes: the system comprises an air compressor, an air storage tank, an oil-gas mixing device and an oil gas pipeline; the air compressor is connected with the air storage tank and can transmit air into the oil-gas mixing device; the oil-gas mixing device is connected with the oil-gas transmission pipeline, and lubricating oil gas is respectively transmitted to the auxiliary supporting seat and the front supporting seat by means of the oil-gas transmission pipeline.
The technical principles of the present invention have been described above in connection with specific embodiments, which are intended to explain the principles of the present invention and should not be construed as limiting the scope of the present invention in any way. Based on the explanations herein, those skilled in the art will be able to conceive of other embodiments of the present invention without inventive efforts, which shall fall within the scope of the present invention.
Claims (10)
1. The utility model provides an aeroengine rotor analogue test measurement system which characterized in that includes: the device comprises a cantilever rotor testing device, an oil lubricating unit and a multi-physical-quantity acquisition device;
the oil lubricating unit can perform circulating oil lubrication on the cantilever rotor testing device;
the multi-physical quantity acquisition device can acquire various physical quantity data shown by the cantilever rotor test device in a simulation test;
the plurality of physical quantity data includes at least: chip data, temperature data, eddy current data, acceleration data and displacement data in circulating oil lubrication.
2. The aircraft engine rotor simulation test measurement system of claim 1,
the cantilever rotor test device includes: the method comprises the following steps: the device comprises a T-shaped groove platform, a high-speed motor, a spline transmission shaft, a slender shaft, a short shaft, a movable turbine disc and a supporting device;
the high-speed motor, the spline transmission shaft, the slender shaft, the short shaft and the moving turbine disc are arranged on the T-shaped groove platform by means of the supporting device;
the high-speed motor is in transmission connection with one end of the slender shaft by means of the spline transmission shaft;
the other end of the slender shaft is connected with the short shaft in an interference fit manner;
the moving turbine disc is arranged on the short shaft;
the high-speed motor can drive the moving turbine disc to rotate by means of the slender shaft, and is used for simulating dynamic evolution of an aircraft engine rotor during operation.
3. The aircraft engine rotor simulation test measurement system of claim 2,
the support device includes: the motor support seat, the auxiliary support seat, the front support seat and the rear support seat;
the high-speed motor is arranged on the motor supporting seat;
the slender shaft is respectively arranged on the front supporting seat and the rear supporting seat in a penetrating way;
the spline transmission shaft is arranged on the auxiliary supporting seat;
the short shaft is provided with a bearing, and can freely rotate on the rear supporting seat by virtue of the bearing;
the motor supporting seat, the auxiliary supporting seat, the front supporting seat and the rear supporting seat are sequentially and fixedly arranged on a T-shaped groove of the T-shaped groove platform.
4. The aircraft engine rotor simulation test measurement system of claim 3,
the oil lubricating unit comprises: the oil tank, the oil supply pipeline with the oil supply pump, and the oil return pipeline with the oil return pump;
one end of the oil supply pipeline is communicated with the oil tank, and the other end of the oil supply pipeline supplies oil to the lubricating oil circuit of the movable turbine disc and the short shaft;
one end of the oil return pipeline is communicated with the lubricating oil way, and the other end of the oil return pipeline returns oil into the oil tank.
5. The aircraft engine rotor simulation test measurement system of claim 4,
the multi-physical quantity acquisition device includes: the device comprises a data recording and sorting terminal, a chip acquisition unit, a temperature acquisition unit, an eddy current acquisition unit, an acceleration acquisition unit and a displacement acquisition unit;
the chip acquisition unit can acquire chip data in the oil return pipeline and send the acquired chip data to the data recording and sorting terminal;
the temperature acquisition unit can acquire temperature data of the outer ring of the bearing on the short shaft and send the acquired temperature data to the data recording and sorting terminal;
the eddy current acquisition unit can acquire eddy current data on the slender shaft and send the acquired eddy current data to the data recording and sorting terminal;
the acceleration acquisition unit can acquire acceleration data of the slender shaft and send the acquired acceleration data to the data recording and sorting terminal;
the displacement acquisition unit can acquire the displacement data of the slender shaft and send the acquired displacement data to the data recording and sorting terminal.
6. The aircraft engine rotor simulation test measurement system of claim 5,
the chip collection unit comprises: a scrap collecting card and a scrap sensor;
the chip acquisition card is in data connection with the chip sensor;
the chip sensor is arranged on the oil return pipeline and used for collecting chip data;
the chip sensor can send the collected chip data to the chip collecting card;
the chip acquisition card is used for sending chip data to the data recording and sorting terminal.
7. The aircraft engine rotor simulation test measurement system of claim 5,
the temperature acquisition unit includes: a temperature acquisition card and a temperature sensor;
the temperature acquisition card is in data connection with the temperature sensor;
the temperature sensor is in contact with the outer ring of the bearing on the short shaft and is used for acquiring temperature data;
the temperature sensor can send the acquired temperature data to the temperature acquisition card;
the temperature acquisition card is used for sending temperature data to the data recording and sorting terminal.
8. The aircraft engine rotor simulation test measurement system of claim 5,
the eddy current collection unit includes: the eddy current acquisition card and the eddy current sensor;
the eddy current acquisition card is in data connection with the eddy current sensor;
the eddy current sensor measures the slender shaft in a non-contact mode and is used for collecting eddy current data;
the eddy current sensor can send acquired eddy current data to the eddy current acquisition card;
the eddy current acquisition card is used for sending eddy current data to the data recording and sorting terminal;
the acceleration acquisition unit includes: an acceleration acquisition card and an acceleration sensor;
the acceleration acquisition card is in data connection with the acceleration sensor;
the acceleration sensor is arranged on the supporting device and used for acquiring acceleration data of the slender shaft;
the acceleration sensor can send the acquired acceleration data to the acceleration acquisition card;
the acceleration acquisition card is used for sending acceleration data to the data recording and sorting terminal.
9. The aircraft engine rotor simulation test measurement system of claim 5,
the displacement acquisition unit includes: a displacement acquisition card and a displacement sensor;
the displacement acquisition card is in data connection with the displacement sensor;
the displacement sensor is arranged on the supporting device and used for acquiring displacement data of the slender shaft;
the displacement sensor can send the collected displacement data to the displacement collection card;
the displacement acquisition card is used for sending displacement data to the data recording and sorting terminal.
10. The aircraft engine rotor simulation test measurement system of claim 3,
further comprising: an oil-gas lubrication unit;
the oil-gas lubricating unit is used for lubricating the auxiliary supporting seat and the front supporting seat;
the oil-air lubrication unit includes: the system comprises an air compressor, an air storage tank, an oil-gas mixing device and an oil gas pipeline;
the air compressor is connected with the air storage tank and can transmit air into the oil-gas mixing device;
the oil-gas mixing device is connected with the oil-gas transmission pipeline, and lubricating oil gas is respectively transmitted to the auxiliary supporting seat and the front supporting seat by means of the oil-gas transmission pipeline.
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| CN202110546211.5A CN113432847A (en) | 2021-05-19 | 2021-05-19 | Aeroengine rotor simulation test measurement system |
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| CN202110546211.5A CN113432847A (en) | 2021-05-19 | 2021-05-19 | Aeroengine rotor simulation test measurement system |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114427970A (en) * | 2021-11-29 | 2022-05-03 | 中国航发沈阳发动机研究所 | Bearing monitoring method for aero-engine main bearing test |
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Application publication date: 20210924 |